LJE-681 -75-078

CSCTM756137

INTERNATIONAL ULTRAVIOLET EXPLORER (IUE) SATELLITE MISSION ANALYSIS

(NASA-CR-144813) INTERNATIONAL ULTRAVIOLET N77-15064

EXPLORER (IUE) SATELLITE MISSIN0 ANALYSIS (Computer Sciences Corp) - 92 p fiC A05NFl A01 CSCL 22A UnclasG31I5_ 59027_____

Prepared For

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

Goddard Space Flight Center

Greenbelt Maryland

CONTRACT NAS 5-11999 Task Assignment s

id44

SEPTEMBER 1975

I-RECEI -4~y

INP BRANC

3 - - --- -~ 9 -

httpsntrsnasagovsearchjspR=19770008121 2020-02-14T074934+0000Z

CSCTM-756 137

INTERNATIONAII ULTRAVIOLET EXPLORER (IUE) SATELLITE

MISSION ANALYSIS

Prepared for

GODDARD SPACE FLIGHT CENTER

By

COMPUTER SCIENCES CORPORATION

Under

Contract NAS 5-11999 Task Assignment 544

Prepared by Reviewed by

R A Cook Date 0 L Dial Date

J HGtiffin- Date Approved by

D K Yeomans Section Manager

Date

ABSTRACT

This technical memorandum presents the results of the mission analysis pershy

formed by Computer Sciences Corporation (CSC) in support of the International

Ultraviolet Explorer (IUE) satellite The launch window is open for three sepashy

rate periods (for a total time of 7 months) during the year extending from

July 20 1977 to July 20 1978 The synchronous orbit shadow constraint limits

the launch window to approximately 88 minutes per day Apogee boost motor

fuel was computed to be 455 pounds (206 kilograms) and on-station weight was

931 pounds (422 kil6grams)gtThe target orbit is elliptical synchronous with

eccentricity 0272 and 24 hour period

iii

TABLE OF CONTENTS

Section 1 - Introduction 1-1

Section 2 - Launch Window Analysis oshy

21 Launch Window Constraints 2-1 22 Launch Window Definition 22-2

Section 3 - Fuel Requirements 3-1

31 Apogee Boost Motor Sizing 3-1 32 Hydrazine and On--station Weight 3-1

Section 4 - Nominal Trajectory 4-1

41 Shadow Time Constraint 4-1 42- Tracking Requirements 4-1

45 Nominal Mission- Profile 4-3

4 4 Nominal Orbital Elements 4-3

Appendix-A - Parameter Histograms

Appendix B - Shadow-History-Curves

45 Nominal Station Acquisition Sequence 4-4

Appendix C - Tracking Coverage

Appendix D - Launch Window Constraint Parameter Contour Plots

Appendix E - Evolution of Orbital Elements

NOT IF

V

LIST OF ILLUSTRATIONS

Figure

2-1 Definition of Solar Aspect Angle (a) 2-3 2-2 Definition of Separation Angle (f) 2-4 2-3 iE Launch Window 2-5 3-1 ABM Fuel Penalty Versus Inclination (for Fixed

Apogee Bias and Fixed Drift Rate) 3-5 4-1 Ecliptic Inclination 4-5 4-2 Ecliptic Argument of Perigee 4-10 4-3 Nominal Synchronous Orbit Shadow History 4-11 4-4 Synchronous Orbit Shadow for 99th Percentile

Low Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-12

4-5 Synchronous Orbit Shadow for 99th Percentile Low Afrgiment of Perigee and Node Angle 20 Degrees Above Nominal 4-13

4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-14

4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 20 Degrees Above Nominal 4-15

4-8 GSFC Tracking Mask and Nominal Tracking Pattern 4-16

4-9 VILFRA Tracking Mask and Nominal Tracking Pattern 4-17

4-10 Longitude Interval4 for Acceptable Tracking 41

Ovege 4-18 4-11 Stationkeeping Limits for Nominal Orbit 4-19

4-12 Groundtrack for Transfer Orbit (Apogee I and 2) 4-20 4-13 Groundtrack for Transfer Orbit (Apogee 3 4

and 5) 4-21 4-14 Groundtrack for Drift Orbit Phase 1 4-22

4-15 Groundtrack for Drift Orbit Phase 2 4-23 4-16 Groundtrack for Drift Orbit Phase3 4-24 4-17 Groundtrack for Synchronous Orbit 4-25 4-18 Stdtion Acquisition 4-26 4-19 Evolution of Longitude at Ascending Node 4-27

A4

LIST OF TABLES

Table

3-1 Covariance Matrix at Transfer Injection 3-3 3-2 Approximate Weight Breakdown for IUE 3-4 4-1 Longitude Intervals for Good Tracking 4-5 4-2 IUE Nominal Orbits 4-6 4-3 99th Percentile Errors in Orbital Parameters 4-7 4-4 Time TaAcquire Station for Easterly and

Westerly Drift Rates 4 4-8

vii

SECTION 1 - INTRODUCTION

the objective of the joint United StatesEuropean International Ultraviolet Exshy

plorer (IUE) satellite is to observe the ultraviolet spectra of stars galaxies

and the brighter gaseous nebulae The UE spacecraft will be launched by a 2914

Delta rocket and placed in a 24-hour elliptical orbit over the Atlantic Ocean

In support of this mission Computer Sciences Corporation (CSC) has extended

the mission analysis by performing the following tasks

1 The launch window analysis was updated to reflect a nominal launch

date of July 20 1977 The FORTRAN Launch Analysis Program (FLAP) was

used to determine the launch opportunities as a function of launch date and right

ascension of the ascending node The launch window is presented for a 1-year

period beginning July 20 1977

2 The spacecraft weight was increased to accommodate higher payshy

load requirements The Two-Body Error Analysis (TBERR) Program was used

to resize the apogee boost motor (ABM) assuming an apogee yaw maneuver

in order to satisfy -trackingrequirements in the synchronous orbit The resultshy

ing ABM fuel weight is 455 pounds (206 kilograms) which corresponds to a velocshy

ity change of 3540 feet per second (10789 meters per second) The hydrazine

fuel requirements were computed for a nominal drift rate of 6 degrees per day

east The study assumed that drift rate errors would be corrected The 99th

percentile hydrazine required for station acquisition is 23 pounds (10 kilograms)

3 The shadow time history of the elliptical synchronous orbit was reshy

evaluated in light of recent changes in the constraints To achieve maximum

sunlight over a 5-year mission a node and argument of perigee were selected

to assure a high ecliptic inclination and apogee position well above the shadow

cone of the Earth The nominal node angle is 220 degrees and argument of

perigee is 234 degrees

1-1

4 The synchronous orbit inclination was chosen to satisfy tracking

requirements at Goddard Space Flight Center (GSFC) and Villafranca del

Castillo Spain (VILFRA) The tracking time prediction program (SANDTRACKS)

was used to determine tracking coverage as a function of inclination and station

longitude If the nominal inclination is chosen to be 265 degrees thenthe

tracking constraints are satisfied Furthermore there is no significant loss

of tracking time for points inside the 90 probability error ellipse centered at

the nominal inclination

5 The nominal trajectory parameters were computed for a July 20

1977 launch The transfer orbit node and argument of perigee were compenshy

sated for the apogee motor firing (AMF) maneuver Second apogee was selected

as nominal position for the AMF because of extensive-tracking poverage from

US sites The drift orbitwas divided into three phases to achieve station

acquisition in approximately10 days -The nominal synchronous orbit has an

-eccentricity of 02729 inclination of 265 degrees and initial station longitude

of about 42 degrees west

Section 2 presents the -launch window extending from July 20 1977 to July 20

1978 Section 3 updates the spacecraft weight breakdown including a resized

apogee boost motor and hydrazine fuel required for station acquisition Secshy

tion 4 outlines the nominal UE mission profile presents the trajectory conshy

straints and tabulates the nominal orbital elements designed to satisfy these

constraints

1-Station longitude is defined as geographic longitude of the ascending node when the spacecraft is at the ascending node

1-2

SECTION 2 - LAUNCH WINDOW ANALYSIS

21 I AUNCH WINDOW CONSTRAINTS

The launch window analysis forIUE was updated to extend from July 20 19771 for a 1-year period The launch window constraints assumed for this study

are as follows

Maximum continuous shadow duration prior toAMP must be less

than 60 minutes

Third-stage solar aspect angle must lie between 45 and 135 degrees

a Fourth-stage solar aspect angle must lie beteen 45 and 135 degrees

Earth-spacecraft-Sun separation angle must be between 30 and

150 degrees for the 3-hour period prior to apogee

Minimum daily launch window duration must be at least 20 minutes

0 -Synchronous orbit shadow duration must beldss_thm 72 minutes

per revolution for the entire mission -

The pre-AMF shadow constraint must be satisfied from fairing ejection up to

AMF The solar aspect angle is measured between the spacecraft spin axis

and the spacecraft-Sun vector (Figure 2-1) The separation angle is measured

Between thespacecraft-Sun vector and the spacecraft-Earth vector (Figure 2-2)

Thampthird stage injects the satellite into the transfer orbit from the parking

orbit The fourth stage is the ABM and is used to inject the satellite into the

desired drift orbit

Computer Sciences Corporation 3000-2700-07TN Launch Window Analysis

for the International Ultraviolet Explorer (IUE) Satellite J H Griffin March 1975

2-1

OF THESRoD-UCIBIUTY 0 V1 ]Icent PAGE Is PO

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

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FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

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I

-shyl

Iq I

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2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

CSCTM-756 137

INTERNATIONAII ULTRAVIOLET EXPLORER (IUE) SATELLITE

MISSION ANALYSIS

Prepared for

GODDARD SPACE FLIGHT CENTER

By

COMPUTER SCIENCES CORPORATION

Under

Contract NAS 5-11999 Task Assignment 544

Prepared by Reviewed by

R A Cook Date 0 L Dial Date

J HGtiffin- Date Approved by

D K Yeomans Section Manager

Date

ABSTRACT

This technical memorandum presents the results of the mission analysis pershy

formed by Computer Sciences Corporation (CSC) in support of the International

Ultraviolet Explorer (IUE) satellite The launch window is open for three sepashy

rate periods (for a total time of 7 months) during the year extending from

July 20 1977 to July 20 1978 The synchronous orbit shadow constraint limits

the launch window to approximately 88 minutes per day Apogee boost motor

fuel was computed to be 455 pounds (206 kilograms) and on-station weight was

931 pounds (422 kil6grams)gtThe target orbit is elliptical synchronous with

eccentricity 0272 and 24 hour period

iii

TABLE OF CONTENTS

Section 1 - Introduction 1-1

Section 2 - Launch Window Analysis oshy

21 Launch Window Constraints 2-1 22 Launch Window Definition 22-2

Section 3 - Fuel Requirements 3-1

31 Apogee Boost Motor Sizing 3-1 32 Hydrazine and On--station Weight 3-1

Section 4 - Nominal Trajectory 4-1

41 Shadow Time Constraint 4-1 42- Tracking Requirements 4-1

45 Nominal Mission- Profile 4-3

4 4 Nominal Orbital Elements 4-3

Appendix-A - Parameter Histograms

Appendix B - Shadow-History-Curves

45 Nominal Station Acquisition Sequence 4-4

Appendix C - Tracking Coverage

Appendix D - Launch Window Constraint Parameter Contour Plots

Appendix E - Evolution of Orbital Elements

NOT IF

V

LIST OF ILLUSTRATIONS

Figure

2-1 Definition of Solar Aspect Angle (a) 2-3 2-2 Definition of Separation Angle (f) 2-4 2-3 iE Launch Window 2-5 3-1 ABM Fuel Penalty Versus Inclination (for Fixed

Apogee Bias and Fixed Drift Rate) 3-5 4-1 Ecliptic Inclination 4-5 4-2 Ecliptic Argument of Perigee 4-10 4-3 Nominal Synchronous Orbit Shadow History 4-11 4-4 Synchronous Orbit Shadow for 99th Percentile

Low Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-12

4-5 Synchronous Orbit Shadow for 99th Percentile Low Afrgiment of Perigee and Node Angle 20 Degrees Above Nominal 4-13

4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-14

4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 20 Degrees Above Nominal 4-15

4-8 GSFC Tracking Mask and Nominal Tracking Pattern 4-16

4-9 VILFRA Tracking Mask and Nominal Tracking Pattern 4-17

4-10 Longitude Interval4 for Acceptable Tracking 41

Ovege 4-18 4-11 Stationkeeping Limits for Nominal Orbit 4-19

4-12 Groundtrack for Transfer Orbit (Apogee I and 2) 4-20 4-13 Groundtrack for Transfer Orbit (Apogee 3 4

and 5) 4-21 4-14 Groundtrack for Drift Orbit Phase 1 4-22

4-15 Groundtrack for Drift Orbit Phase 2 4-23 4-16 Groundtrack for Drift Orbit Phase3 4-24 4-17 Groundtrack for Synchronous Orbit 4-25 4-18 Stdtion Acquisition 4-26 4-19 Evolution of Longitude at Ascending Node 4-27

A4

LIST OF TABLES

Table

3-1 Covariance Matrix at Transfer Injection 3-3 3-2 Approximate Weight Breakdown for IUE 3-4 4-1 Longitude Intervals for Good Tracking 4-5 4-2 IUE Nominal Orbits 4-6 4-3 99th Percentile Errors in Orbital Parameters 4-7 4-4 Time TaAcquire Station for Easterly and

Westerly Drift Rates 4 4-8

vii

SECTION 1 - INTRODUCTION

the objective of the joint United StatesEuropean International Ultraviolet Exshy

plorer (IUE) satellite is to observe the ultraviolet spectra of stars galaxies

and the brighter gaseous nebulae The UE spacecraft will be launched by a 2914

Delta rocket and placed in a 24-hour elliptical orbit over the Atlantic Ocean

In support of this mission Computer Sciences Corporation (CSC) has extended

the mission analysis by performing the following tasks

1 The launch window analysis was updated to reflect a nominal launch

date of July 20 1977 The FORTRAN Launch Analysis Program (FLAP) was

used to determine the launch opportunities as a function of launch date and right

ascension of the ascending node The launch window is presented for a 1-year

period beginning July 20 1977

2 The spacecraft weight was increased to accommodate higher payshy

load requirements The Two-Body Error Analysis (TBERR) Program was used

to resize the apogee boost motor (ABM) assuming an apogee yaw maneuver

in order to satisfy -trackingrequirements in the synchronous orbit The resultshy

ing ABM fuel weight is 455 pounds (206 kilograms) which corresponds to a velocshy

ity change of 3540 feet per second (10789 meters per second) The hydrazine

fuel requirements were computed for a nominal drift rate of 6 degrees per day

east The study assumed that drift rate errors would be corrected The 99th

percentile hydrazine required for station acquisition is 23 pounds (10 kilograms)

3 The shadow time history of the elliptical synchronous orbit was reshy

evaluated in light of recent changes in the constraints To achieve maximum

sunlight over a 5-year mission a node and argument of perigee were selected

to assure a high ecliptic inclination and apogee position well above the shadow

cone of the Earth The nominal node angle is 220 degrees and argument of

perigee is 234 degrees

1-1

4 The synchronous orbit inclination was chosen to satisfy tracking

requirements at Goddard Space Flight Center (GSFC) and Villafranca del

Castillo Spain (VILFRA) The tracking time prediction program (SANDTRACKS)

was used to determine tracking coverage as a function of inclination and station

longitude If the nominal inclination is chosen to be 265 degrees thenthe

tracking constraints are satisfied Furthermore there is no significant loss

of tracking time for points inside the 90 probability error ellipse centered at

the nominal inclination

5 The nominal trajectory parameters were computed for a July 20

1977 launch The transfer orbit node and argument of perigee were compenshy

sated for the apogee motor firing (AMF) maneuver Second apogee was selected

as nominal position for the AMF because of extensive-tracking poverage from

US sites The drift orbitwas divided into three phases to achieve station

acquisition in approximately10 days -The nominal synchronous orbit has an

-eccentricity of 02729 inclination of 265 degrees and initial station longitude

of about 42 degrees west

Section 2 presents the -launch window extending from July 20 1977 to July 20

1978 Section 3 updates the spacecraft weight breakdown including a resized

apogee boost motor and hydrazine fuel required for station acquisition Secshy

tion 4 outlines the nominal UE mission profile presents the trajectory conshy

straints and tabulates the nominal orbital elements designed to satisfy these

constraints

1-Station longitude is defined as geographic longitude of the ascending node when the spacecraft is at the ascending node

1-2

SECTION 2 - LAUNCH WINDOW ANALYSIS

21 I AUNCH WINDOW CONSTRAINTS

The launch window analysis forIUE was updated to extend from July 20 19771 for a 1-year period The launch window constraints assumed for this study

are as follows

Maximum continuous shadow duration prior toAMP must be less

than 60 minutes

Third-stage solar aspect angle must lie between 45 and 135 degrees

a Fourth-stage solar aspect angle must lie beteen 45 and 135 degrees

Earth-spacecraft-Sun separation angle must be between 30 and

150 degrees for the 3-hour period prior to apogee

Minimum daily launch window duration must be at least 20 minutes

0 -Synchronous orbit shadow duration must beldss_thm 72 minutes

per revolution for the entire mission -

The pre-AMF shadow constraint must be satisfied from fairing ejection up to

AMF The solar aspect angle is measured between the spacecraft spin axis

and the spacecraft-Sun vector (Figure 2-1) The separation angle is measured

Between thespacecraft-Sun vector and the spacecraft-Earth vector (Figure 2-2)

Thampthird stage injects the satellite into the transfer orbit from the parking

orbit The fourth stage is the ABM and is used to inject the satellite into the

desired drift orbit

Computer Sciences Corporation 3000-2700-07TN Launch Window Analysis

for the International Ultraviolet Explorer (IUE) Satellite J H Griffin March 1975

2-1

OF THESRoD-UCIBIUTY 0 V1 ]Icent PAGE Is PO

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

ABSTRACT

This technical memorandum presents the results of the mission analysis pershy

formed by Computer Sciences Corporation (CSC) in support of the International

Ultraviolet Explorer (IUE) satellite The launch window is open for three sepashy

rate periods (for a total time of 7 months) during the year extending from

July 20 1977 to July 20 1978 The synchronous orbit shadow constraint limits

the launch window to approximately 88 minutes per day Apogee boost motor

fuel was computed to be 455 pounds (206 kilograms) and on-station weight was

931 pounds (422 kil6grams)gtThe target orbit is elliptical synchronous with

eccentricity 0272 and 24 hour period

iii

TABLE OF CONTENTS

Section 1 - Introduction 1-1

Section 2 - Launch Window Analysis oshy

21 Launch Window Constraints 2-1 22 Launch Window Definition 22-2

Section 3 - Fuel Requirements 3-1

31 Apogee Boost Motor Sizing 3-1 32 Hydrazine and On--station Weight 3-1

Section 4 - Nominal Trajectory 4-1

41 Shadow Time Constraint 4-1 42- Tracking Requirements 4-1

45 Nominal Mission- Profile 4-3

4 4 Nominal Orbital Elements 4-3

Appendix-A - Parameter Histograms

Appendix B - Shadow-History-Curves

45 Nominal Station Acquisition Sequence 4-4

Appendix C - Tracking Coverage

Appendix D - Launch Window Constraint Parameter Contour Plots

Appendix E - Evolution of Orbital Elements

NOT IF

V

LIST OF ILLUSTRATIONS

Figure

2-1 Definition of Solar Aspect Angle (a) 2-3 2-2 Definition of Separation Angle (f) 2-4 2-3 iE Launch Window 2-5 3-1 ABM Fuel Penalty Versus Inclination (for Fixed

Apogee Bias and Fixed Drift Rate) 3-5 4-1 Ecliptic Inclination 4-5 4-2 Ecliptic Argument of Perigee 4-10 4-3 Nominal Synchronous Orbit Shadow History 4-11 4-4 Synchronous Orbit Shadow for 99th Percentile

Low Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-12

4-5 Synchronous Orbit Shadow for 99th Percentile Low Afrgiment of Perigee and Node Angle 20 Degrees Above Nominal 4-13

4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-14

4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 20 Degrees Above Nominal 4-15

4-8 GSFC Tracking Mask and Nominal Tracking Pattern 4-16

4-9 VILFRA Tracking Mask and Nominal Tracking Pattern 4-17

4-10 Longitude Interval4 for Acceptable Tracking 41

Ovege 4-18 4-11 Stationkeeping Limits for Nominal Orbit 4-19

4-12 Groundtrack for Transfer Orbit (Apogee I and 2) 4-20 4-13 Groundtrack for Transfer Orbit (Apogee 3 4

and 5) 4-21 4-14 Groundtrack for Drift Orbit Phase 1 4-22

4-15 Groundtrack for Drift Orbit Phase 2 4-23 4-16 Groundtrack for Drift Orbit Phase3 4-24 4-17 Groundtrack for Synchronous Orbit 4-25 4-18 Stdtion Acquisition 4-26 4-19 Evolution of Longitude at Ascending Node 4-27

A4

LIST OF TABLES

Table

3-1 Covariance Matrix at Transfer Injection 3-3 3-2 Approximate Weight Breakdown for IUE 3-4 4-1 Longitude Intervals for Good Tracking 4-5 4-2 IUE Nominal Orbits 4-6 4-3 99th Percentile Errors in Orbital Parameters 4-7 4-4 Time TaAcquire Station for Easterly and

Westerly Drift Rates 4 4-8

vii

SECTION 1 - INTRODUCTION

the objective of the joint United StatesEuropean International Ultraviolet Exshy

plorer (IUE) satellite is to observe the ultraviolet spectra of stars galaxies

and the brighter gaseous nebulae The UE spacecraft will be launched by a 2914

Delta rocket and placed in a 24-hour elliptical orbit over the Atlantic Ocean

In support of this mission Computer Sciences Corporation (CSC) has extended

the mission analysis by performing the following tasks

1 The launch window analysis was updated to reflect a nominal launch

date of July 20 1977 The FORTRAN Launch Analysis Program (FLAP) was

used to determine the launch opportunities as a function of launch date and right

ascension of the ascending node The launch window is presented for a 1-year

period beginning July 20 1977

2 The spacecraft weight was increased to accommodate higher payshy

load requirements The Two-Body Error Analysis (TBERR) Program was used

to resize the apogee boost motor (ABM) assuming an apogee yaw maneuver

in order to satisfy -trackingrequirements in the synchronous orbit The resultshy

ing ABM fuel weight is 455 pounds (206 kilograms) which corresponds to a velocshy

ity change of 3540 feet per second (10789 meters per second) The hydrazine

fuel requirements were computed for a nominal drift rate of 6 degrees per day

east The study assumed that drift rate errors would be corrected The 99th

percentile hydrazine required for station acquisition is 23 pounds (10 kilograms)

3 The shadow time history of the elliptical synchronous orbit was reshy

evaluated in light of recent changes in the constraints To achieve maximum

sunlight over a 5-year mission a node and argument of perigee were selected

to assure a high ecliptic inclination and apogee position well above the shadow

cone of the Earth The nominal node angle is 220 degrees and argument of

perigee is 234 degrees

1-1

4 The synchronous orbit inclination was chosen to satisfy tracking

requirements at Goddard Space Flight Center (GSFC) and Villafranca del

Castillo Spain (VILFRA) The tracking time prediction program (SANDTRACKS)

was used to determine tracking coverage as a function of inclination and station

longitude If the nominal inclination is chosen to be 265 degrees thenthe

tracking constraints are satisfied Furthermore there is no significant loss

of tracking time for points inside the 90 probability error ellipse centered at

the nominal inclination

5 The nominal trajectory parameters were computed for a July 20

1977 launch The transfer orbit node and argument of perigee were compenshy

sated for the apogee motor firing (AMF) maneuver Second apogee was selected

as nominal position for the AMF because of extensive-tracking poverage from

US sites The drift orbitwas divided into three phases to achieve station

acquisition in approximately10 days -The nominal synchronous orbit has an

-eccentricity of 02729 inclination of 265 degrees and initial station longitude

of about 42 degrees west

Section 2 presents the -launch window extending from July 20 1977 to July 20

1978 Section 3 updates the spacecraft weight breakdown including a resized

apogee boost motor and hydrazine fuel required for station acquisition Secshy

tion 4 outlines the nominal UE mission profile presents the trajectory conshy

straints and tabulates the nominal orbital elements designed to satisfy these

constraints

1-Station longitude is defined as geographic longitude of the ascending node when the spacecraft is at the ascending node

1-2

SECTION 2 - LAUNCH WINDOW ANALYSIS

21 I AUNCH WINDOW CONSTRAINTS

The launch window analysis forIUE was updated to extend from July 20 19771 for a 1-year period The launch window constraints assumed for this study

are as follows

Maximum continuous shadow duration prior toAMP must be less

than 60 minutes

Third-stage solar aspect angle must lie between 45 and 135 degrees

a Fourth-stage solar aspect angle must lie beteen 45 and 135 degrees

Earth-spacecraft-Sun separation angle must be between 30 and

150 degrees for the 3-hour period prior to apogee

Minimum daily launch window duration must be at least 20 minutes

0 -Synchronous orbit shadow duration must beldss_thm 72 minutes

per revolution for the entire mission -

The pre-AMF shadow constraint must be satisfied from fairing ejection up to

AMF The solar aspect angle is measured between the spacecraft spin axis

and the spacecraft-Sun vector (Figure 2-1) The separation angle is measured

Between thespacecraft-Sun vector and the spacecraft-Earth vector (Figure 2-2)

Thampthird stage injects the satellite into the transfer orbit from the parking

orbit The fourth stage is the ABM and is used to inject the satellite into the

desired drift orbit

Computer Sciences Corporation 3000-2700-07TN Launch Window Analysis

for the International Ultraviolet Explorer (IUE) Satellite J H Griffin March 1975

2-1

OF THESRoD-UCIBIUTY 0 V1 ]Icent PAGE Is PO

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

TABLE OF CONTENTS

Section 1 - Introduction 1-1

Section 2 - Launch Window Analysis oshy

21 Launch Window Constraints 2-1 22 Launch Window Definition 22-2

Section 3 - Fuel Requirements 3-1

31 Apogee Boost Motor Sizing 3-1 32 Hydrazine and On--station Weight 3-1

Section 4 - Nominal Trajectory 4-1

41 Shadow Time Constraint 4-1 42- Tracking Requirements 4-1

45 Nominal Mission- Profile 4-3

4 4 Nominal Orbital Elements 4-3

Appendix-A - Parameter Histograms

Appendix B - Shadow-History-Curves

45 Nominal Station Acquisition Sequence 4-4

Appendix C - Tracking Coverage

Appendix D - Launch Window Constraint Parameter Contour Plots

Appendix E - Evolution of Orbital Elements

NOT IF

V

LIST OF ILLUSTRATIONS

Figure

2-1 Definition of Solar Aspect Angle (a) 2-3 2-2 Definition of Separation Angle (f) 2-4 2-3 iE Launch Window 2-5 3-1 ABM Fuel Penalty Versus Inclination (for Fixed

Apogee Bias and Fixed Drift Rate) 3-5 4-1 Ecliptic Inclination 4-5 4-2 Ecliptic Argument of Perigee 4-10 4-3 Nominal Synchronous Orbit Shadow History 4-11 4-4 Synchronous Orbit Shadow for 99th Percentile

Low Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-12

4-5 Synchronous Orbit Shadow for 99th Percentile Low Afrgiment of Perigee and Node Angle 20 Degrees Above Nominal 4-13

4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-14

4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 20 Degrees Above Nominal 4-15

4-8 GSFC Tracking Mask and Nominal Tracking Pattern 4-16

4-9 VILFRA Tracking Mask and Nominal Tracking Pattern 4-17

4-10 Longitude Interval4 for Acceptable Tracking 41

Ovege 4-18 4-11 Stationkeeping Limits for Nominal Orbit 4-19

4-12 Groundtrack for Transfer Orbit (Apogee I and 2) 4-20 4-13 Groundtrack for Transfer Orbit (Apogee 3 4

and 5) 4-21 4-14 Groundtrack for Drift Orbit Phase 1 4-22

4-15 Groundtrack for Drift Orbit Phase 2 4-23 4-16 Groundtrack for Drift Orbit Phase3 4-24 4-17 Groundtrack for Synchronous Orbit 4-25 4-18 Stdtion Acquisition 4-26 4-19 Evolution of Longitude at Ascending Node 4-27

A4

LIST OF TABLES

Table

3-1 Covariance Matrix at Transfer Injection 3-3 3-2 Approximate Weight Breakdown for IUE 3-4 4-1 Longitude Intervals for Good Tracking 4-5 4-2 IUE Nominal Orbits 4-6 4-3 99th Percentile Errors in Orbital Parameters 4-7 4-4 Time TaAcquire Station for Easterly and

Westerly Drift Rates 4 4-8

vii

SECTION 1 - INTRODUCTION

the objective of the joint United StatesEuropean International Ultraviolet Exshy

plorer (IUE) satellite is to observe the ultraviolet spectra of stars galaxies

and the brighter gaseous nebulae The UE spacecraft will be launched by a 2914

Delta rocket and placed in a 24-hour elliptical orbit over the Atlantic Ocean

In support of this mission Computer Sciences Corporation (CSC) has extended

the mission analysis by performing the following tasks

1 The launch window analysis was updated to reflect a nominal launch

date of July 20 1977 The FORTRAN Launch Analysis Program (FLAP) was

used to determine the launch opportunities as a function of launch date and right

ascension of the ascending node The launch window is presented for a 1-year

period beginning July 20 1977

2 The spacecraft weight was increased to accommodate higher payshy

load requirements The Two-Body Error Analysis (TBERR) Program was used

to resize the apogee boost motor (ABM) assuming an apogee yaw maneuver

in order to satisfy -trackingrequirements in the synchronous orbit The resultshy

ing ABM fuel weight is 455 pounds (206 kilograms) which corresponds to a velocshy

ity change of 3540 feet per second (10789 meters per second) The hydrazine

fuel requirements were computed for a nominal drift rate of 6 degrees per day

east The study assumed that drift rate errors would be corrected The 99th

percentile hydrazine required for station acquisition is 23 pounds (10 kilograms)

3 The shadow time history of the elliptical synchronous orbit was reshy

evaluated in light of recent changes in the constraints To achieve maximum

sunlight over a 5-year mission a node and argument of perigee were selected

to assure a high ecliptic inclination and apogee position well above the shadow

cone of the Earth The nominal node angle is 220 degrees and argument of

perigee is 234 degrees

1-1

4 The synchronous orbit inclination was chosen to satisfy tracking

requirements at Goddard Space Flight Center (GSFC) and Villafranca del

Castillo Spain (VILFRA) The tracking time prediction program (SANDTRACKS)

was used to determine tracking coverage as a function of inclination and station

longitude If the nominal inclination is chosen to be 265 degrees thenthe

tracking constraints are satisfied Furthermore there is no significant loss

of tracking time for points inside the 90 probability error ellipse centered at

the nominal inclination

5 The nominal trajectory parameters were computed for a July 20

1977 launch The transfer orbit node and argument of perigee were compenshy

sated for the apogee motor firing (AMF) maneuver Second apogee was selected

as nominal position for the AMF because of extensive-tracking poverage from

US sites The drift orbitwas divided into three phases to achieve station

acquisition in approximately10 days -The nominal synchronous orbit has an

-eccentricity of 02729 inclination of 265 degrees and initial station longitude

of about 42 degrees west

Section 2 presents the -launch window extending from July 20 1977 to July 20

1978 Section 3 updates the spacecraft weight breakdown including a resized

apogee boost motor and hydrazine fuel required for station acquisition Secshy

tion 4 outlines the nominal UE mission profile presents the trajectory conshy

straints and tabulates the nominal orbital elements designed to satisfy these

constraints

1-Station longitude is defined as geographic longitude of the ascending node when the spacecraft is at the ascending node

1-2

SECTION 2 - LAUNCH WINDOW ANALYSIS

21 I AUNCH WINDOW CONSTRAINTS

The launch window analysis forIUE was updated to extend from July 20 19771 for a 1-year period The launch window constraints assumed for this study

are as follows

Maximum continuous shadow duration prior toAMP must be less

than 60 minutes

Third-stage solar aspect angle must lie between 45 and 135 degrees

a Fourth-stage solar aspect angle must lie beteen 45 and 135 degrees

Earth-spacecraft-Sun separation angle must be between 30 and

150 degrees for the 3-hour period prior to apogee

Minimum daily launch window duration must be at least 20 minutes

0 -Synchronous orbit shadow duration must beldss_thm 72 minutes

per revolution for the entire mission -

The pre-AMF shadow constraint must be satisfied from fairing ejection up to

AMF The solar aspect angle is measured between the spacecraft spin axis

and the spacecraft-Sun vector (Figure 2-1) The separation angle is measured

Between thespacecraft-Sun vector and the spacecraft-Earth vector (Figure 2-2)

Thampthird stage injects the satellite into the transfer orbit from the parking

orbit The fourth stage is the ABM and is used to inject the satellite into the

desired drift orbit

Computer Sciences Corporation 3000-2700-07TN Launch Window Analysis

for the International Ultraviolet Explorer (IUE) Satellite J H Griffin March 1975

2-1

OF THESRoD-UCIBIUTY 0 V1 ]Icent PAGE Is PO

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

LIST OF ILLUSTRATIONS

Figure

2-1 Definition of Solar Aspect Angle (a) 2-3 2-2 Definition of Separation Angle (f) 2-4 2-3 iE Launch Window 2-5 3-1 ABM Fuel Penalty Versus Inclination (for Fixed

Apogee Bias and Fixed Drift Rate) 3-5 4-1 Ecliptic Inclination 4-5 4-2 Ecliptic Argument of Perigee 4-10 4-3 Nominal Synchronous Orbit Shadow History 4-11 4-4 Synchronous Orbit Shadow for 99th Percentile

Low Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-12

4-5 Synchronous Orbit Shadow for 99th Percentile Low Afrgiment of Perigee and Node Angle 20 Degrees Above Nominal 4-13

4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal 4-14

4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 20 Degrees Above Nominal 4-15

4-8 GSFC Tracking Mask and Nominal Tracking Pattern 4-16

4-9 VILFRA Tracking Mask and Nominal Tracking Pattern 4-17

4-10 Longitude Interval4 for Acceptable Tracking 41

Ovege 4-18 4-11 Stationkeeping Limits for Nominal Orbit 4-19

4-12 Groundtrack for Transfer Orbit (Apogee I and 2) 4-20 4-13 Groundtrack for Transfer Orbit (Apogee 3 4

and 5) 4-21 4-14 Groundtrack for Drift Orbit Phase 1 4-22

4-15 Groundtrack for Drift Orbit Phase 2 4-23 4-16 Groundtrack for Drift Orbit Phase3 4-24 4-17 Groundtrack for Synchronous Orbit 4-25 4-18 Stdtion Acquisition 4-26 4-19 Evolution of Longitude at Ascending Node 4-27

A4

LIST OF TABLES

Table

3-1 Covariance Matrix at Transfer Injection 3-3 3-2 Approximate Weight Breakdown for IUE 3-4 4-1 Longitude Intervals for Good Tracking 4-5 4-2 IUE Nominal Orbits 4-6 4-3 99th Percentile Errors in Orbital Parameters 4-7 4-4 Time TaAcquire Station for Easterly and

Westerly Drift Rates 4 4-8

vii

SECTION 1 - INTRODUCTION

the objective of the joint United StatesEuropean International Ultraviolet Exshy

plorer (IUE) satellite is to observe the ultraviolet spectra of stars galaxies

and the brighter gaseous nebulae The UE spacecraft will be launched by a 2914

Delta rocket and placed in a 24-hour elliptical orbit over the Atlantic Ocean

In support of this mission Computer Sciences Corporation (CSC) has extended

the mission analysis by performing the following tasks

1 The launch window analysis was updated to reflect a nominal launch

date of July 20 1977 The FORTRAN Launch Analysis Program (FLAP) was

used to determine the launch opportunities as a function of launch date and right

ascension of the ascending node The launch window is presented for a 1-year

period beginning July 20 1977

2 The spacecraft weight was increased to accommodate higher payshy

load requirements The Two-Body Error Analysis (TBERR) Program was used

to resize the apogee boost motor (ABM) assuming an apogee yaw maneuver

in order to satisfy -trackingrequirements in the synchronous orbit The resultshy

ing ABM fuel weight is 455 pounds (206 kilograms) which corresponds to a velocshy

ity change of 3540 feet per second (10789 meters per second) The hydrazine

fuel requirements were computed for a nominal drift rate of 6 degrees per day

east The study assumed that drift rate errors would be corrected The 99th

percentile hydrazine required for station acquisition is 23 pounds (10 kilograms)

3 The shadow time history of the elliptical synchronous orbit was reshy

evaluated in light of recent changes in the constraints To achieve maximum

sunlight over a 5-year mission a node and argument of perigee were selected

to assure a high ecliptic inclination and apogee position well above the shadow

cone of the Earth The nominal node angle is 220 degrees and argument of

perigee is 234 degrees

1-1

4 The synchronous orbit inclination was chosen to satisfy tracking

requirements at Goddard Space Flight Center (GSFC) and Villafranca del

Castillo Spain (VILFRA) The tracking time prediction program (SANDTRACKS)

was used to determine tracking coverage as a function of inclination and station

longitude If the nominal inclination is chosen to be 265 degrees thenthe

tracking constraints are satisfied Furthermore there is no significant loss

of tracking time for points inside the 90 probability error ellipse centered at

the nominal inclination

5 The nominal trajectory parameters were computed for a July 20

1977 launch The transfer orbit node and argument of perigee were compenshy

sated for the apogee motor firing (AMF) maneuver Second apogee was selected

as nominal position for the AMF because of extensive-tracking poverage from

US sites The drift orbitwas divided into three phases to achieve station

acquisition in approximately10 days -The nominal synchronous orbit has an

-eccentricity of 02729 inclination of 265 degrees and initial station longitude

of about 42 degrees west

Section 2 presents the -launch window extending from July 20 1977 to July 20

1978 Section 3 updates the spacecraft weight breakdown including a resized

apogee boost motor and hydrazine fuel required for station acquisition Secshy

tion 4 outlines the nominal UE mission profile presents the trajectory conshy

straints and tabulates the nominal orbital elements designed to satisfy these

constraints

1-Station longitude is defined as geographic longitude of the ascending node when the spacecraft is at the ascending node

1-2

SECTION 2 - LAUNCH WINDOW ANALYSIS

21 I AUNCH WINDOW CONSTRAINTS

The launch window analysis forIUE was updated to extend from July 20 19771 for a 1-year period The launch window constraints assumed for this study

are as follows

Maximum continuous shadow duration prior toAMP must be less

than 60 minutes

Third-stage solar aspect angle must lie between 45 and 135 degrees

a Fourth-stage solar aspect angle must lie beteen 45 and 135 degrees

Earth-spacecraft-Sun separation angle must be between 30 and

150 degrees for the 3-hour period prior to apogee

Minimum daily launch window duration must be at least 20 minutes

0 -Synchronous orbit shadow duration must beldss_thm 72 minutes

per revolution for the entire mission -

The pre-AMF shadow constraint must be satisfied from fairing ejection up to

AMF The solar aspect angle is measured between the spacecraft spin axis

and the spacecraft-Sun vector (Figure 2-1) The separation angle is measured

Between thespacecraft-Sun vector and the spacecraft-Earth vector (Figure 2-2)

Thampthird stage injects the satellite into the transfer orbit from the parking

orbit The fourth stage is the ABM and is used to inject the satellite into the

desired drift orbit

Computer Sciences Corporation 3000-2700-07TN Launch Window Analysis

for the International Ultraviolet Explorer (IUE) Satellite J H Griffin March 1975

2-1

OF THESRoD-UCIBIUTY 0 V1 ]Icent PAGE Is PO

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

LIST OF TABLES

Table

3-1 Covariance Matrix at Transfer Injection 3-3 3-2 Approximate Weight Breakdown for IUE 3-4 4-1 Longitude Intervals for Good Tracking 4-5 4-2 IUE Nominal Orbits 4-6 4-3 99th Percentile Errors in Orbital Parameters 4-7 4-4 Time TaAcquire Station for Easterly and

Westerly Drift Rates 4 4-8

vii

SECTION 1 - INTRODUCTION

the objective of the joint United StatesEuropean International Ultraviolet Exshy

plorer (IUE) satellite is to observe the ultraviolet spectra of stars galaxies

and the brighter gaseous nebulae The UE spacecraft will be launched by a 2914

Delta rocket and placed in a 24-hour elliptical orbit over the Atlantic Ocean

In support of this mission Computer Sciences Corporation (CSC) has extended

the mission analysis by performing the following tasks

1 The launch window analysis was updated to reflect a nominal launch

date of July 20 1977 The FORTRAN Launch Analysis Program (FLAP) was

used to determine the launch opportunities as a function of launch date and right

ascension of the ascending node The launch window is presented for a 1-year

period beginning July 20 1977

2 The spacecraft weight was increased to accommodate higher payshy

load requirements The Two-Body Error Analysis (TBERR) Program was used

to resize the apogee boost motor (ABM) assuming an apogee yaw maneuver

in order to satisfy -trackingrequirements in the synchronous orbit The resultshy

ing ABM fuel weight is 455 pounds (206 kilograms) which corresponds to a velocshy

ity change of 3540 feet per second (10789 meters per second) The hydrazine

fuel requirements were computed for a nominal drift rate of 6 degrees per day

east The study assumed that drift rate errors would be corrected The 99th

percentile hydrazine required for station acquisition is 23 pounds (10 kilograms)

3 The shadow time history of the elliptical synchronous orbit was reshy

evaluated in light of recent changes in the constraints To achieve maximum

sunlight over a 5-year mission a node and argument of perigee were selected

to assure a high ecliptic inclination and apogee position well above the shadow

cone of the Earth The nominal node angle is 220 degrees and argument of

perigee is 234 degrees

1-1

4 The synchronous orbit inclination was chosen to satisfy tracking

requirements at Goddard Space Flight Center (GSFC) and Villafranca del

Castillo Spain (VILFRA) The tracking time prediction program (SANDTRACKS)

was used to determine tracking coverage as a function of inclination and station

longitude If the nominal inclination is chosen to be 265 degrees thenthe

tracking constraints are satisfied Furthermore there is no significant loss

of tracking time for points inside the 90 probability error ellipse centered at

the nominal inclination

5 The nominal trajectory parameters were computed for a July 20

1977 launch The transfer orbit node and argument of perigee were compenshy

sated for the apogee motor firing (AMF) maneuver Second apogee was selected

as nominal position for the AMF because of extensive-tracking poverage from

US sites The drift orbitwas divided into three phases to achieve station

acquisition in approximately10 days -The nominal synchronous orbit has an

-eccentricity of 02729 inclination of 265 degrees and initial station longitude

of about 42 degrees west

Section 2 presents the -launch window extending from July 20 1977 to July 20

1978 Section 3 updates the spacecraft weight breakdown including a resized

apogee boost motor and hydrazine fuel required for station acquisition Secshy

tion 4 outlines the nominal UE mission profile presents the trajectory conshy

straints and tabulates the nominal orbital elements designed to satisfy these

constraints

1-Station longitude is defined as geographic longitude of the ascending node when the spacecraft is at the ascending node

1-2

SECTION 2 - LAUNCH WINDOW ANALYSIS

21 I AUNCH WINDOW CONSTRAINTS

The launch window analysis forIUE was updated to extend from July 20 19771 for a 1-year period The launch window constraints assumed for this study

are as follows

Maximum continuous shadow duration prior toAMP must be less

than 60 minutes

Third-stage solar aspect angle must lie between 45 and 135 degrees

a Fourth-stage solar aspect angle must lie beteen 45 and 135 degrees

Earth-spacecraft-Sun separation angle must be between 30 and

150 degrees for the 3-hour period prior to apogee

Minimum daily launch window duration must be at least 20 minutes

0 -Synchronous orbit shadow duration must beldss_thm 72 minutes

per revolution for the entire mission -

The pre-AMF shadow constraint must be satisfied from fairing ejection up to

AMF The solar aspect angle is measured between the spacecraft spin axis

and the spacecraft-Sun vector (Figure 2-1) The separation angle is measured

Between thespacecraft-Sun vector and the spacecraft-Earth vector (Figure 2-2)

Thampthird stage injects the satellite into the transfer orbit from the parking

orbit The fourth stage is the ABM and is used to inject the satellite into the

desired drift orbit

Computer Sciences Corporation 3000-2700-07TN Launch Window Analysis

for the International Ultraviolet Explorer (IUE) Satellite J H Griffin March 1975

2-1

OF THESRoD-UCIBIUTY 0 V1 ]Icent PAGE Is PO

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

SECTION 1 - INTRODUCTION

the objective of the joint United StatesEuropean International Ultraviolet Exshy

plorer (IUE) satellite is to observe the ultraviolet spectra of stars galaxies

and the brighter gaseous nebulae The UE spacecraft will be launched by a 2914

Delta rocket and placed in a 24-hour elliptical orbit over the Atlantic Ocean

In support of this mission Computer Sciences Corporation (CSC) has extended

the mission analysis by performing the following tasks

1 The launch window analysis was updated to reflect a nominal launch

date of July 20 1977 The FORTRAN Launch Analysis Program (FLAP) was

used to determine the launch opportunities as a function of launch date and right

ascension of the ascending node The launch window is presented for a 1-year

period beginning July 20 1977

2 The spacecraft weight was increased to accommodate higher payshy

load requirements The Two-Body Error Analysis (TBERR) Program was used

to resize the apogee boost motor (ABM) assuming an apogee yaw maneuver

in order to satisfy -trackingrequirements in the synchronous orbit The resultshy

ing ABM fuel weight is 455 pounds (206 kilograms) which corresponds to a velocshy

ity change of 3540 feet per second (10789 meters per second) The hydrazine

fuel requirements were computed for a nominal drift rate of 6 degrees per day

east The study assumed that drift rate errors would be corrected The 99th

percentile hydrazine required for station acquisition is 23 pounds (10 kilograms)

3 The shadow time history of the elliptical synchronous orbit was reshy

evaluated in light of recent changes in the constraints To achieve maximum

sunlight over a 5-year mission a node and argument of perigee were selected

to assure a high ecliptic inclination and apogee position well above the shadow

cone of the Earth The nominal node angle is 220 degrees and argument of

perigee is 234 degrees

1-1

4 The synchronous orbit inclination was chosen to satisfy tracking

requirements at Goddard Space Flight Center (GSFC) and Villafranca del

Castillo Spain (VILFRA) The tracking time prediction program (SANDTRACKS)

was used to determine tracking coverage as a function of inclination and station

longitude If the nominal inclination is chosen to be 265 degrees thenthe

tracking constraints are satisfied Furthermore there is no significant loss

of tracking time for points inside the 90 probability error ellipse centered at

the nominal inclination

5 The nominal trajectory parameters were computed for a July 20

1977 launch The transfer orbit node and argument of perigee were compenshy

sated for the apogee motor firing (AMF) maneuver Second apogee was selected

as nominal position for the AMF because of extensive-tracking poverage from

US sites The drift orbitwas divided into three phases to achieve station

acquisition in approximately10 days -The nominal synchronous orbit has an

-eccentricity of 02729 inclination of 265 degrees and initial station longitude

of about 42 degrees west

Section 2 presents the -launch window extending from July 20 1977 to July 20

1978 Section 3 updates the spacecraft weight breakdown including a resized

apogee boost motor and hydrazine fuel required for station acquisition Secshy

tion 4 outlines the nominal UE mission profile presents the trajectory conshy

straints and tabulates the nominal orbital elements designed to satisfy these

constraints

1-Station longitude is defined as geographic longitude of the ascending node when the spacecraft is at the ascending node

1-2

SECTION 2 - LAUNCH WINDOW ANALYSIS

21 I AUNCH WINDOW CONSTRAINTS

The launch window analysis forIUE was updated to extend from July 20 19771 for a 1-year period The launch window constraints assumed for this study

are as follows

Maximum continuous shadow duration prior toAMP must be less

than 60 minutes

Third-stage solar aspect angle must lie between 45 and 135 degrees

a Fourth-stage solar aspect angle must lie beteen 45 and 135 degrees

Earth-spacecraft-Sun separation angle must be between 30 and

150 degrees for the 3-hour period prior to apogee

Minimum daily launch window duration must be at least 20 minutes

0 -Synchronous orbit shadow duration must beldss_thm 72 minutes

per revolution for the entire mission -

The pre-AMF shadow constraint must be satisfied from fairing ejection up to

AMF The solar aspect angle is measured between the spacecraft spin axis

and the spacecraft-Sun vector (Figure 2-1) The separation angle is measured

Between thespacecraft-Sun vector and the spacecraft-Earth vector (Figure 2-2)

Thampthird stage injects the satellite into the transfer orbit from the parking

orbit The fourth stage is the ABM and is used to inject the satellite into the

desired drift orbit

Computer Sciences Corporation 3000-2700-07TN Launch Window Analysis

for the International Ultraviolet Explorer (IUE) Satellite J H Griffin March 1975

2-1

OF THESRoD-UCIBIUTY 0 V1 ]Icent PAGE Is PO

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

4 The synchronous orbit inclination was chosen to satisfy tracking

requirements at Goddard Space Flight Center (GSFC) and Villafranca del

Castillo Spain (VILFRA) The tracking time prediction program (SANDTRACKS)

was used to determine tracking coverage as a function of inclination and station

longitude If the nominal inclination is chosen to be 265 degrees thenthe

tracking constraints are satisfied Furthermore there is no significant loss

of tracking time for points inside the 90 probability error ellipse centered at

the nominal inclination

5 The nominal trajectory parameters were computed for a July 20

1977 launch The transfer orbit node and argument of perigee were compenshy

sated for the apogee motor firing (AMF) maneuver Second apogee was selected

as nominal position for the AMF because of extensive-tracking poverage from

US sites The drift orbitwas divided into three phases to achieve station

acquisition in approximately10 days -The nominal synchronous orbit has an

-eccentricity of 02729 inclination of 265 degrees and initial station longitude

of about 42 degrees west

Section 2 presents the -launch window extending from July 20 1977 to July 20

1978 Section 3 updates the spacecraft weight breakdown including a resized

apogee boost motor and hydrazine fuel required for station acquisition Secshy

tion 4 outlines the nominal UE mission profile presents the trajectory conshy

straints and tabulates the nominal orbital elements designed to satisfy these

constraints

1-Station longitude is defined as geographic longitude of the ascending node when the spacecraft is at the ascending node

1-2

SECTION 2 - LAUNCH WINDOW ANALYSIS

21 I AUNCH WINDOW CONSTRAINTS

The launch window analysis forIUE was updated to extend from July 20 19771 for a 1-year period The launch window constraints assumed for this study

are as follows

Maximum continuous shadow duration prior toAMP must be less

than 60 minutes

Third-stage solar aspect angle must lie between 45 and 135 degrees

a Fourth-stage solar aspect angle must lie beteen 45 and 135 degrees

Earth-spacecraft-Sun separation angle must be between 30 and

150 degrees for the 3-hour period prior to apogee

Minimum daily launch window duration must be at least 20 minutes

0 -Synchronous orbit shadow duration must beldss_thm 72 minutes

per revolution for the entire mission -

The pre-AMF shadow constraint must be satisfied from fairing ejection up to

AMF The solar aspect angle is measured between the spacecraft spin axis

and the spacecraft-Sun vector (Figure 2-1) The separation angle is measured

Between thespacecraft-Sun vector and the spacecraft-Earth vector (Figure 2-2)

Thampthird stage injects the satellite into the transfer orbit from the parking

orbit The fourth stage is the ABM and is used to inject the satellite into the

desired drift orbit

Computer Sciences Corporation 3000-2700-07TN Launch Window Analysis

for the International Ultraviolet Explorer (IUE) Satellite J H Griffin March 1975

2-1

OF THESRoD-UCIBIUTY 0 V1 ]Icent PAGE Is PO

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

SECTION 2 - LAUNCH WINDOW ANALYSIS

21 I AUNCH WINDOW CONSTRAINTS

The launch window analysis forIUE was updated to extend from July 20 19771 for a 1-year period The launch window constraints assumed for this study

are as follows

Maximum continuous shadow duration prior toAMP must be less

than 60 minutes

Third-stage solar aspect angle must lie between 45 and 135 degrees

a Fourth-stage solar aspect angle must lie beteen 45 and 135 degrees

Earth-spacecraft-Sun separation angle must be between 30 and

150 degrees for the 3-hour period prior to apogee

Minimum daily launch window duration must be at least 20 minutes

0 -Synchronous orbit shadow duration must beldss_thm 72 minutes

per revolution for the entire mission -

The pre-AMF shadow constraint must be satisfied from fairing ejection up to

AMF The solar aspect angle is measured between the spacecraft spin axis

and the spacecraft-Sun vector (Figure 2-1) The separation angle is measured

Between thespacecraft-Sun vector and the spacecraft-Earth vector (Figure 2-2)

Thampthird stage injects the satellite into the transfer orbit from the parking

orbit The fourth stage is the ABM and is used to inject the satellite into the

desired drift orbit

Computer Sciences Corporation 3000-2700-07TN Launch Window Analysis

for the International Ultraviolet Explorer (IUE) Satellite J H Griffin March 1975

2-1

OF THESRoD-UCIBIUTY 0 V1 ]Icent PAGE Is PO

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

22 LAUNCH WINDOW DEFINITION

The launch window is defined in terms of launch date and node of the parking

orbit The composite launch window plot is presented in Figure 2-3 and the

individual constraints are plottedin Appendix D

The acceptable launch periods are approximately as follows

July 20 1977 - August 24 1977

November 10 1977 - February 14 1978

May 9 1978 - July 20 1978

These dates are determined primarily by the third- and fourth-stage solar asshy

pect angle constraints which rule out a total of about 5 months of the year

The acceptable node values are limited by the synchronous shadow history conshy

straints which are discussed in detail in Section 4 Thes4 limits slope downshy

ward in order to account for node regression in the synchronous orbit For

example on the launch date of July 20 1977 the shadow history can be comshy

puted with a given initial node value To achieve the same shadow history for

a-launchdate 5 monthilater for example the initial node must be compensated

by an amount equal to a 5-month node regression

It should be noted that the synchronous orbit node values will be about 6 degrees

less than the parkingorbit nodes because of the plane change at AMF This

is true for any launch date In Figure 2-3 this constant node shift has been

accounted for in plotting the node limits associated with the synchronous orbit

shadow history constraints

Also in Figure 2-3 note that there are no violations of the Earth-Sun separashy

tion angle constraint for the node range under consideration This is due to

the relatively high Inclination of the orbit with respect to the ecliptic plane

2-2

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

SUN

Ii

SPIN AXIS

shy

SPIN PLANEI

Figure 2-1 Definition of Solar Aspect Angle (a)

2-3

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

SUN

SPACECqAFT

EARTH

Figure 2-2 Definition of Separation Angle (f

2-4

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

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74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

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S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

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7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

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1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

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501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

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51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

260shy

5O

S 02

TH

LAUNCH WINDOW

GREENWICH MEANTIME AT LAUNCH IHOURS)

240

-

-

HNOOEW

SYNCHRONOUS ~SHADOWow-HISTORY LIMIT

ALLOWAN OR r

00

O0 0

C2 ar H -- dIINo 6

220

-

H4

ALLOWANce NODE ERROR

210 1

2001 0 30 60 90 120 150 180

DAYS FROM STARTING DATE

210 240

(JULY201977

II 270 300 330 360

Figure 2-3 TUE Launch Window

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

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51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

SECTION 3 - FUEL REQUIREMENTS

31 APOGEE BOOST MOTOR SIZING

Using the TBERR Program the ABM was resized to account for increased

spacecraft weight The transfer orbit inclination was 287 degrees (defined by

launch azimuth) and the apogee bias was 57001 nautical miles (10556 kilometers)

The target inclination was varied from 24 0 to 28 7 degrees and the ABM fuel

was computed assuming a nominal target drift rate of 6 degrees per day east

The ABM fuel penalty versus inclination is shown in Figure 3-1 where zero

penalty represents no plane change between the transfer and synchronous orbits

The selection of the nominal inclination (265 degrees) ii discussed in Section 42

For an inclination of 265 degrees the impulsive velocity change (AV) is

3540 feet per second (1078 9 meters per second) The corresponding ABM

fuel required is 455 pounds (206 kilograms) assuming an effective specific

impulse of 2806 seconds

32 HYDRAZINE AND 6N-STATION WEIGHT

To determine the stiion acquisition hydrazine required a Monte Carlo simushy

lation was performed using the TBERR Program The covariance matrix for

position and velocity at transfer orbit injection is presented in Table 3-1

Additional errors are introduced during the AMF The ABM 3-sigma pointing

error was assumed to be 5 degrees in both yaw and pitch The 3-sigma error

in ABM AV was assumed to be 075 percent

Two hydrazine maneuvers were simulated in the drift orbit If the sample

drift rate deviated by more than 01 degree per day from the nominal value of

6 degrees per day a hydrazine burn was performed to correct the drift rate

back to the nominal value A second hydrazine burn reduces the drift rate to

zero to achieve a synchronous orbit (The purpose of the drift orbit is to allow

1This bias is a project requirement imposed to limit eccentricity in the synshychronous orbit

3-1 REPRODUCIBLITY OF THE oplusmn1 jiNAL PAGE IS POOR

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

the spacecraft to acquire a specified station longitude) If the sample eccenshy

tricity was greater thhn nominal two hydrazine burns were performed to

achieve the synchronous orbit The eccentricity waslowered to the nominal

value while the drift rate was reduced to zero In either case the 99th pershy

centile I hydrazine fuel is 23 pounds (10 kilograms) assuming a specific imshy

pulse of 220 seconds This does not include any fuel required for spin rate

control or attitude trim maneuvers Table 3-2 presents an approximate IWE

weight breakdown The pre-AMF and post-AMF reorientation hydrazine values

are estimated to be 4 and 2 R~punds respectively Histograms for pertinent

parameters are presented in Appendix A

1For hydrazine used to acquire station N percent of the sample values are less than the Nth percentile value

3-2

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

Table 3-l Covdriance Matrix at Transfer Injection

X y 7 X y

x

y

z

1163224500

-15289324

-305653410

59126868

-15289324

636023750

70610971

-11912372

-30 653410

10 10071

249260 0

-22264382

59126868

-11912372

- 22 26 4382

2550

8356098

59006438

16078010

11707503

-14297558

18635505

64165883

-2002417

y 83506098

-14207558

59006438

18635595

16078010

64165883

11707503

-2002417

88361771

-011295046

-011295046

90509395

1 POSITION IN FEET VELOCITY IN FEETSECOND

2 COORDINATE SYSTEM Z=R Y=RxV X=(BxV)xB

WHERE R AND V ARE THE INERTIAL POSITION AND-VELOCITY VECTORS

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

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) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

Table 3-2 Approximate Weight Breakdowh for UE

t

ENGLISH METRIC UNITS UNITSITEM

WEIGHT ATTHIRD STAGE BURN-OUT 1415 LBS 642 KG

PRE-AMF REORIENTATION HYDRAZINE (ESTIMATE) -4 -2

-WEIGHTATAMF 1411 640

ABM PROPELLANT ANDINERT CONSUMMABLES -455 -206

POST-AMF WEIGHT 956 434

POST-AMF REORIENTATION HYDRAZiNE (ESTIMATE) -2 -1

STATION ACQUISITION HYDRAZINE (99TH PERCENTILE) - 23 -10

ON-STATION WEIGHT (99TH PERCENTILE) 931 422

3-4

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

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iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

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I

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Iq I

rjI~I

2 1

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7 O-4 -T I C 3 f 0

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4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

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~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

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1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

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$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

ABM FUEL PENALTY (LBS)

TRANSFER ORBIT INCLINATION 287

0 I3

It

r4

m Figure 3-1 ABM Fuel Penalty Versus Inclination (for Fixed Apogee Bias t- and Fixed Drift Rate)

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

SECTION 4 - NOMINAL TRAJECTORY

41 SHADOW TIME CONSTRAINT

The nominal node and argument of perigee of the elliptical synchronous orbit

were chosen to satisfy the shadow time constraint Synchronous shadow dura-

tion must be less than 72 minutes per ievolution over a 5-year mission Due

to the orbital eccentricity the actual shadow durations could be as high as

95 minutes To avoid these situations the orientation geometry of the orbit

plane must be controlled The shadow constraint is satisfied when the orbit

plane achieves a relatively high ecliptic inclination (Figure 4-1) and when the

apogee position is well above the shadow cone of the Earth (Figure 4-2 ecliptic

argument of perigee near 270 degrees) These conditionsare met using an

initial node of 220 degrees and argument of perigee of 234 degrees

Figure 4-3 shows the 5-year synchronous orbit shadow history for the nominal

elements In generating this curve semimajor axis eccentricity and inclishy

nation were held fixed while node and argument of perigee were allowed to

evolve at constant rates of -0 024 and +0 027 -degree per day respectively

Figure 4-4 through 4-7 show the shadow histories for the 99th percentile values

of argument of perigee for various node angles For node angles from -10 to

+20 degrees about the nominal value the umbra shadow curves are acceptable

and provide launch window durations of about 88 minutes per day (after comshy

pensating for possible node errors) as shown in Figure 2-3 For higher or

lower node angles the shadow curves are marginal or unacceptable as

shown in Appendix B

42 TRACKING REQUIREMENTS

The synchr6nous orbit inclination was chosen to satisfy tracking requirements

at GSFC and VILFRA GSFC tracking time must be 24 hours per day and

This is due to the oblateness of the Earth as reflected in the J2 coefficient

in the gravitational potential

4-1

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

VILFRA tracking time must be at least 10 hours per day Figure 4-8 shows

tle GSFC tracdng mask (NTTE 12-meter antenna) and a portion of the noninal

tracking pattern Figure 4-9 shows the VILFRA tracking mask and the nominal

tracking pattern The physical mask plus 10 degrees was used in computing

all tracking time for VILFRA

SANDTRACKS was used to compute tracking time as a function of inclination

argument of perigee and longitude at the ascending node 1 A representative

sample of this data is presented in Table 4-1 The western-most limit of

longitude at the ascending node is determined by the VILFRA tracking con-

straint and the eastern-most limit is determined by the GSFC tracking conshy

straint Some of the longitude intervals where-both tracking requirements

are satisfied are indicdted in Figure 4-10

This figure also shows the 90 pr6bability error ellipse for argument of perigee

and inclination The ellipse is centered at the hominal inclination of 26 Sdeshy

grees Even though the ellipse extends into the region of tracking constraint

violation the loss of-tracking time was not considered significant For points

A B and D on the ellipse the VILFRA tracking time is about 94 hours when

GSFC has 24 hours of coverage At point C theVILFRA coverage is 88 hours

As the orbit evolves the inclination tends to decrease and the argument- of

perigee increases resulting in better tracking coverage If point C reptesents

the initial conditions for the synchronous orbit then after approximately 5

months the tracking requirements would be completely satisfied

For nominal initial conditions the orbit was allowed to evolve over a 5-year

mission and the longitude limits were determined as shown in Figure 4-11

To keep the orbit within these limits it is necessary to perform stationkeeping

maneuvers throughout the mission

1 This longitude is the geographic longitude of the ascending node when the spacecraft is at the ascending node

4-2

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

43 NOMINAL MISSION PROFILE

The current nominal launch date for IWE is July 20 1977 On this date the

launch window is open from approximately 69 to 84 hours GMT This corshy

responds to a transfer node range of 220 to 242 degrees or a synchronous

node of 214 to 236 degrees

IUE will be launched by a three-stage Delta 2914 vehicle from Cape Kennedy at

a launch azimuth of 95 degrees At an altitude of 100 nautical miles it will be

injected into a circular parking orbit with an inclination of 287 degrees After

coasting for about 26 minutas the booster injects the spacecraft into a transfer

orbit with an argument of perigee of 228 7 degrees Following injection into the

transfer orbit the spacecraft orbit and attitude will be computed from tracking

and telemetry data The hydrazine reaction control system will then reorient

the spacecraft into the apogee motor firing attitude On the second apogee

passage of the transfer orbit the ABM will inject the satellite into a nearshy

synchronous drifting orbit The ABM will perform a plane change maneuver

resulting in an inclination of 265 degrees node of 220 degrees and argument

of perigee of 234 degrees -Drift rate will be controlled by the hydrazine system

until the satellite acquires station The final orbit will be elliptical synchroshy

- nous

44 NOMINAL ORBITAL ELEMENTS

Theparking orbit is defined by the following parameters

Parameter Description

Altitude 100 nautical miles (185 kilometers)

Eccentricity 0

Inclination 287 degrees

Injection latitude 2477 degrees

Injection longitude 5949 degrees west

injection azimuth 10528 degrees

4-3

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

Parameter Description

Time from launch to injection 53037 seconds

Coast time 159935 seconds

Epoch date July 20 1977 7H 13 M 42S

Epoch time

The transfer drift and synchronous orbits are defined in Table 4-2 At AMF

the spin axis right ascension is 5 27 degrees and the declination is 11 26 deshy

grees for the nominal orbit Errors in the orbital elements are listed in

Table 4-3 and shown in histogram form in Appendix A Figures 4-12 through 4-17

display the spacecraft groundtracks while Appendix C presents the corresponding

tracking coverage

45 NOMINAL STATION ACQUISITION SEQUENCE

As presented in Table 4-2 the drift orbit is divided into three phases with

drift rates of 6 and 2 degrees per day east This repreqents only one of

many possible station acquisition sequences to achieve asynchronous orbit

Table 4-4 indicates time to acquire station for easterly and westerly drift

rates of 6 degrees per day assuming AMF occurs on one of the first five

transfer apogee passes (second apogee is nominal) Initial station longitude

is near 42 degrees west Figure 4-18 presents the station acquisition sequence

in terms of longitude at the ascending node as a function of the number of revolushy

tions in the drift orbit After station longitude has been achieved the higher

order gravitational effects cause the orbit to deviate significantly away from

the initial conditions Figure 4-19 shows the evolution of the longitude at the

ascending node if there are no stationkeeping maneuvers Appendix E preshy

sents the evolution of the orbital elements and thegroundtrack evolution

4-4

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

Table 4-1 Longitude Intervals for Good Tracking

VILFRA MINUS GSFC STATIONKEEPING LONGITUDES ARGUMENT OF (DEGREES WEST)

PERIGEE(DEGREES) INCLINATION = 25 DEG INCLINATION = 26 DEG INCLINATION = 265 DEG

226 44-36=8 44-38-6 44-38=6

230 44-34= 10 44-36=8 44-36=8

234 44-32=12 44-34=10 44-40=4

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

PARAMETER

SEMIMAJOR AXIS (KM)

ECCENTRICITY INCLINATION (DEG) ASCENDING NODE (DEG) ARGUMENT OF PERIGEE (DEG)

MEAN ANOMALY (DEG)

EPOCH DATE EPOCH TIME

DRIFT RATE (DEGDAY EAST)[

PERIOD (HR)

PERIGEE RADIUS (KM)

APOGEE RADIUS (KM)

INITIAL STATION 42 0 W

Table 4-2

TRANSFERORBIT

29642

077858 287

2259

2287

00

72077

7 H4 9 M2 1S

14110

6563 52720

UE Nominal Orbits

DRIFT PHASE 3

42119

027144 265 220

234

00

72777

14 H4 1M53 S

0577

23896

30686

53552

SYNCHRONOUS ORBIT

42164

027221 265 220

234

00

72977 14H29M30S

00

23934

30686

53642

DRIFTPHASE 1

41703

026417 265 220

234

180

72177

4 H53 M21 S

60

23543

30686

52720

DRIFTPHASE 2

42010

026955 265

220

234

00

72477

15 H 17M2 7S

20

23803

30686

53334

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

Table 4-3Z 99th Percpntlle Errors in Orbital Parameters

PA TRANSFER DRIFT SYNCHRONOUSPARAMETER ORBIT ERRORS ORBIT ERRORS ORBITERRORS

04ECCENTRICITY -0003 40004 +0007 - 014 00

INCLINATION (DEG) -02 +02 -10 +11 -10 +11

NODE (DEG) -06 +06 -34 +31 -34 +31

ARGUMENT OF PERIGEE (DEG) -10 +11 -56 +56 -56 +56

RADIUS OF PERIGEE (KM) -36 +33 -696 +504 00 +590

RADIUS OF APOGEE (KM) -972 +1004 -993 +1017 -590 00

DRIFT RATE (DEGDAY) -110 +99 00 00

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

Table 4-4 Time To Acquire Station for Easterly and Westerly Drift Rates

DEGREES DAYS TO STATION TO STATION

TRANSFER APOGEE PASS DRIFT DRIFT

EAST WEST 6 DEGDAY 6 DEGDAY

1 176 184 29 31

2 27 333 - 5 55

3 238 122 40 20

4 90 270 15 45

5 301 59 50 10

4-8

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

Co

40 80 120 160 200 240 280 320 360

EQUATORIAL NODE ANGLE (DEGREES)

Figure 4-1 Ecliptic Inclination

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

360

S 240 0

20

A I--Z

o 180

CC)

D60 120 180 240 300 360

C) EQUATORIALARGUMENT OF PERIGEE (DEGREES)

Figure 4-2 Elillptic Argument of Perigee

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

100

WE SHADOW HISTORY

NODE f20 AOP= 234 ---

UMBRA PENUMBRA

80

72-MINUTECONSTRAINT

60

I 20

I

0 200 400 600 800 1000 1200 1400 160D IWOD

MISSION DAYS FROM AUG 11977

Figure 4-3 Nominal Synchronous Orbit Shadow History

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

IUE SHADOW HISTORY

NODE=210 AOP=228

UMBRA

PENUMBRA

80

II

V ft

A

t4 0 40

20

-

A I

0

0200 400 600 800 1000 1200 140 16D0 180C

Figure 4-4

MISSION DAYS FROM AUG 1 1977

Synchronous Orbit Shadow for 99th Percentile Low Argument of Perigee and Node Angle 10 Degrees Below Nominal

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

IUE SHADOW HISTORY - UMBRA

NODE 240 AOP 223 -- PENUMBRA

100

80

II it -

60

oA 40

20

0200 400 600 goo 1000 1200 1400 1600 1800

MISSION DAYS FROM AUG 1 1977

Figutre 4-5 Synchronous Orbit Shadow for 99th Perentile Low Argumeni of Perigee and Node Angle 20 Degrees Above Nominal

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

IUE SHADOW HISTORY UMBRA

NIOOE =210 AOP= 240 PENUMBRA

100

80

I -bull

60

O I

lL40

20

01 1 1 1 ]11 1210011~l 1D0 11 0 200 400 660 am 1000 1200 1400 1600

MISSION DAYS FROM AUG 1 1977

Figure 4-6 Synchronous Orbit Shadow for 99th Percentile High Argument of Perigee and Node Angle 10 Degrees Below Nominal

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

100

IUE SHADOW HISTORY

NODE =240 AOP = 240 ---

UMBRA

PENUMBRA

8O

go

S40 -

I

20shy

0

- ii - I1

A

0200 4O 600 800 100

MISSI ON DAYS FROM AUG 1 1977

1200 1400 1600 1800)

Figure 4-7 Synchronous Orbit Shadow for 99th Percentile High Argument of

]Perigee and Node Angle 20 Degrees Above Nominal

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

14

1 HOUR BETWEEN TICK MARKS

12

10

US 84

UM cZ 8

4

2

0

110 M2 130 140 150 160 170 180 190 20D 210

1IMUTH (DEGREES)

Figure 4-8 GSFC Tracking Mask and Nominal Tracking Pattern

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

32

28

IHOUR BETWEEN

24

S20

wi

z0

gt w

MASK + 100

AMAS

4

200 210 220 230 240 260

AZIMUTH

260

(DEGREES)

270 280 290 00 310

Figure 4-9 VILFRA Tracking Mask and Nominal Tracking Pattern

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

AR

GU

MIE

NT

OF

PE

RIG

EE

(D

EG

RE

ES

N

4

H

0 -

o

00

)

VIO

LA

TIO

N O

F T

RA

CK

ING

CO

NS

TR

IN

VO

C

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

so

I VILFRA 10IHOUR LIMIT LINE 45 (MASK+I1001

0e

I -VILFRA1I-HOURtLINS

w o

I (MASK + 100) -

040

z

z

-II REGION

ACCEPTABLE

35

z 0

0 7

25- -

o I I I f

ARGUMENT OF PERIGEE(DEGR EES)

266 262 259 257 2 25 2 52 24

INCLINATION (DEGREES)

0 1 2 3 4 ELAPSED MISSION TIME (YEARS)

0

Figure 4-11 Stationkeeping Limits for Nominal Orbit

4-19

5

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

so I F r =-

I-l -1-ll -1----- L1 I

-I5- I I AIii iI I-

P-PRI E - - - - - - - - - I I

I k1IIU I I W (I I l i l Il l 1

n 1A II-45 shy

-l 0-165-150-13-120-105-MJ -75 -WD -45 -30 -15 0 lM M 45 0 75 90 105 20 135 150 165 1

Figure 4-12 Groundtrack for Transfer Orbit (Apogeel1and 2)

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

--- -- -- -- - - -- --

--- -

- -- - -- -- -- _V - - - -- -

A A3

-1F T I I

-45 - Il

IE]OII6----[ - 2 - -S- - 7- --- -- ----- [3 4 0 7 t 5 I 1 t t- [ C

FigW 113 Gr1m1rc fornfrObt(pge3 ad5

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

Fi gur 41 Groudtak I Dift IOrbIit1Phase1 i1OlW 5 r 45 I5 1i 1I 140

IC-S -5 -3 -2 -0 -S -7 -6 l45l-3 -1 0 i 30l4I5i~ 75 I 120 I135 15

1OlS -SO- I-II -S 5ll lll-I r--M 30 EU 93 S1S1 165iI

-- 15 I0 II-r 16II

I I I ~~~~~~igure1 lDr~lI4 Grunt-ac if Or Phs I1lli1fo it IIII ~

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

IIIIIIIII 4 11 I111 I IJ I I I I 1 1 I ~ rTITF A I I I - i I l l ll i llql 1 I I =I I IN IA l II I III I 1 1 I-L il lI1

IIIIIIIII5--l5U-ll - -6 -4~1--r -I0-23- -I1 It I1S ~i -7 - -0I-- shy1 Ibt-Igur 1 GroI rt IItIIIafrse

iiiiIiiiw Illllllll~ ~ lll ~ R III~ ~ V IIItlllllllllllll

-7-M_--- -+-HI 1 1 I 1 1 1 I I I 1 1 1 1 11L 1 1 11

20 -I -75 -I 75 J LM3I16515-II1- 1-3 -1 -I SO -6 -45 -303-15 30 45 6] gol 105 iL 5 110t3

Figure 4-15 Groundtrack for Drift Orbit P~hase 2

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

r I I I I

tso

i_30------ I TIshy

7--I6-1- 1-a-7-si -l2- IO -shy1 -- -I 5 31 4 u 7 1 [3 ~J151015I

Fb I Il 1 T IT

-0 FiurIT -1 runtrc_ fo Dif ~rb i3Phsii i

1 4 IU 16 -5 -15 12 0 -M -7 -6 -shy 5 3 1 0 15 30 45 Go 75 90 10 12 13 5 15 0

td i-f

O3H

Figure 4-16 Groundtraek for Drift Orbit Phase 3

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

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Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

90

75

I I I

IUI I1 I

I I

l

11llU1l1l1 I l lI l l l I ll l J l l l

A I deg-

IIIIIIII~--llamp ~l

bull K

I11111 li lI lI

1 11 1 1 1 11 1I _ I I JL 1 1 1 1 II

-I I I I IA A I

----shy ---li l ll l lxJ~ Fl

III

I

-shyl

Iq I

rjI~I

2 1

- -shy 91ol-lnl5-

~Fgr

7 O-4 -T I C 3 f 0

FIIrII4-7 Groundtrack for SynIchon ous

4I111 Grondac frI ilSynchonou

7 9315to

OritII~

stois

I I

1111

t

I

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

S

U o70

O(OEGDAY

-

-lt

DRIFT RATES EAST)

A 6020

C o77

0 00

z

z 60

aB

Ao

w 50 -- - - -- - - -

40

TJARGET LONGITUDE C D

20

01 2 3 4

NUMBER

5 6

OF REVOLUTIONS IN DRIFT ORBIT

78 9

Figure 4-18 Station Acquisition

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

62

w~ 50

so W

o z 0

48

46

to

2

04

40

0 20 40 60 80 100 120 140

MISSION DAYS FROM JULY 291977

Figure 4-19 Evolution of Longitude at Ascending Node

160 180

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

APPENDIX A - PARAMETER HISTOGRAMS

This appendix presents the histograms generated using the Monte Carlo option

in the TBERR Program The parameters for which histograms are provided

tre

1 Drift orbit semimajor axis

2 Drift orbit eccentricity

3 Drift orbit inclination

4 Drift orbit node

5 Drift orbit argument of perigee

6 Drift orbit true anomaly

7 Drift orbit perigee radius

8 Drift orbit apogee radius

9 Post-AMF velocity to acquire station

10 Drift rate

11 On station weight

12 Hydrazine used to acquire station

13 Velocfty required to correct semimajor axis and eccentricity

4 Hydrazine used to correct semimajor axis and eccentricity

15 Velocity required to correct drift rate errors

16 Hydrazine used to correct drift rate errors

17 Synchronous orbit eccentricity

A-1

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

1l0 111lllfxtltil 34 54247i-03 50379F03 088000 942S706 - - -U -1411111111- 060000H26O~QIPN ]11]]II 111 35 024600Tl3 66541E-03 0 601300 95 33695n223631

51 37 J65Oi-33 7)023E-03 0480000 990393560 - l - - - L44--144 W Il- -704-0-460fr9SS111Ill[lll~l 31 74704-133 70715T10 0190000 q99430376

0 IhhII li 43 7370 2-3 32867F-03 0179999 9966)8333

f1I11101 l 2 494 - 3 41029r-03 1)801000 999Z95035 I II ______33D290 511 -03 n0603000 9931311allAIILLULIAII ~

SITO 14l 44 5111-03 941I2-03 0020003) 99 939730 043 tlllIiZIliIllIII1tll 45 99100-03 |0I07-0 0qlo0000 9g291345 -023 - amp1U4-amp1110$III|11l-- -- ----- o37--02--plusmn0O+E-0-E -00300000 -994a33shy0 II[IIIIIIIIITII[I1E1 47 107352-12 1114-02 002)0000 99969723

141~~4 3 111101110210 00103000 99)766011440-02 t525-02 ------- tl-I-rTn-Ilr-1-T t 11 1 -Ovr-0cC-0r-Ue

- 143 00 1I 60E3Z LOS 14 00TIlI11100011110Uh11 1[0111 INF 9a7559 -- gt LLt I-- IJ I 1IILIJ1 -I - o -- o- ---IILU-LL -- -- 11111

) z) 75 3o35r 4) 45 5) Nf10g4S

9500332 0007~plusmn1If nO 900 2

Figure A-2- Drift Orbit Eccentricity Histogram

I TCTSVAL dit N0N4L -CT FRQO S)4

240-12162E 23 03 00400000 205020002 -11645E 3 -1645 03 -112E 03 00 00000 0NLO00

9405 -10610E 33 - 0092E 03 00503000 01r97999

2O7 7 tS7SIF 22 -90577S 02 014000 0499S a S -905775 02 -95403C 0 03202000 03990

0IS -80C3F 22 -55056E 02 03900000 14 999843 92499952 040001M5to9I0194020040

74)5 -5361- 02 -491875 02 21099997 7871 16 -4918- 3 -401417 02 297995 105199q66

13 -3dt4OE 12 -33666V 02 40590995 27t9957

- -32-- 1- -3366 -2803E 02- 42S03A00 PyO ~ 1i 9A20 2 21 -2333F 02 -181450 02 48 92995 319199 100 - 1I zxatss lo2 25fffS 37-f99143 - -

5nI lit 23 -12972E 22 -17979- 01 965999 3t373fl560 111111 24 7774f01 -2b22- 02 64$9)991 49)4995t2

2) I 1111[11 26 Z$5F Cl 7232S 02 60002000 51759t5T - -~ IlIl- 27 7732 CI t2d97F 02 559099 63199463

S TITTITrr--22-r faofoE 02 S 151f939 titt993 1 I I83lS 2324 4759993 772399292llIlll 29 02 02

440 11Z1LuI 3 -) 2fl 02 Z0ta 02 oi)99S Si2509f4 XIIIUlIII 31 22422 02 33592E 02 3489)998 84749)OS4 0 I111llll1lI1 32 33S92 02 36765C 02 3239998 879898787

11tI111121lt 3 3-325 02 Oll35 02 22S92200 9299 67 41 IIIlhIh_ 35 17113z 32 S4286E 02 18099995 97998962

I 117-rTTTrr shy311 -- --- TT s-arn 39460EC0296 116969~861 112 IjllIlItlItlIl 3 S9162 02 64634E 02 12097791 973t99793

-Afi IIIIILI+I -- 3a 6t 02 SS307E 02 08403000 984S0865t1~ -shy3 6lO 12 4981E C2 0650)000 905395590

7 Illll lIllllltll 3 050s 02 801550 02 039000 992208584

~ I1U1211111 1 2 53245 02ii62 02 11503003 9Q55523II v0S0 ZI21111 2111 IItl 43 02 9S67860 02 110)000 997398376

- 111zrirrIII - 4Ft56 12 t2oss 03 00303 990298340 IIIIil11211W 111q 45 lO0A5- 23 I0602r 03 0060)000 29956315 121 UIIIIIIILIIIIII111121 -- 5 40 32 23 41120L 03 00302300 -9921330321 ltllt11t 1221121 4 1112W 03 I16303 00602000 9910820 )2 IIIIII lilt2122lllllIl 124370 33 I22S4 03 00 994792 79

34) - 227W Il~l(Il llIl ZIX lI III 5) 1262V D3 US INF 000)000 990998169

9 in 5 i 0 23-11 it4 O 45-30

1)0 225 902 950 99700

f 04926M nS Is )j __041253) 05 )415) )5 34I65S 06 Aa4l~sw0 5 042129)_05 042ZS12 3$-42440

Figure A-i Drift Orbit Semirnajor Axis Histogram (Kilometers)

at MERVAL 01T N3494AL -CT FlQ SI

301 2 -763051-03 -722ampE-03 00 00100O

400 -68142E-23 -64061E-03 00200000 00600000 140 5 -64061--03 -599801-03 00300000 00903000

5 54________ ---- 0-0C-03---$SS0a-0-0 01000-- 0- 000 400 -55898F-03 -51011E-03 01500000 03102949 q50 3 -5|517I-)3 -47736E-03 01400000 04 599)9

A41 i2 -4365-03 -39573-03 0600000 499)990 1 3tT-2J33549ZE- 03 2Sf22amp421 _____________ _______________________ 257 10299992

92 -35492E-)3 -3IIO0 399992 366D9950 130 13 -31410-03 -27329--03 1729995 55)2)75

- 2-7246-47 - -24- 03 230949 -4-9599 4) 15 -232400-03 -19166E23 14099990 1I3990

_ IS -119166-03 -S55- 3 4297493 1561)961

4 W0 lit 36 -1130z-33 6Q Z3t-04 8009999 2S53900fl

-23-3 -2810E-0 12403E-04 6199996 3930)97Z5 110 11II 21 I~~3-a53 1I7L0006999996 451429664

501 tl012 23 94030-3 13434E-03 68990296 5966995Z4 16711111 94 13414t-23 t7566E-03 04s99991 661094T

5z ll1tt11 26 21fA7-03 2572-C03 521)9493 6899t6 411~~ lL - - - - 2LTZ0r329t~O i2qzo00J -af~~ - - -shy

PIi 1 23 29310-33 33091E-03 406P9997 8553)030 gt- 4 11IlI 27 339lr-33 37425-03 315000000 890094030

$ 21 tllIllIllIlI I 42)4P-03 461355103 20000000 93595920 ta 01 6135t03 5021603 12f995 95Sf

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Figure A-2- Drift Orbit Eccentricity Histogram

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Figure A-3 Drift orbit inclination Hjistogram- (Degrees)

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Figure A-4 Drift Orbit Node Histogram (Degrees)

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Figure A-6 Drift Orbit True Anomaly Histogram (Degrees)

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6 ItO0

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2 -730e-0234117=-0i 27- -1 21117 75$330 Z5 76633E-01t l2171 S 00 2p 1172S 00 15866E 00

64197991 60799292 58597297 60177995

54 559q53661 7699432 67$fl286 73st76

4 0211

Ill102 -----it---f---l$4n-)-Till122Il ll1 sill12121l

3plusmn 32

2001i33 00 241705 0)

20036plusmn 24170C 203215

00 00 00

6429199 47903000 3899996

9109103 433647036 07693775

SIi

223

------- lTrTT1V111111111

rill[13plusmn111 1IIilit12 21ItI 1 ll t1U Uillicit I ll llt illici

Jr 2t7r4r lCU -shy34 324731 00 36624 00 33ll 16-fl 40TSE 0036 4o

76 3) 44920F 00

3 44S26 00 49079C 00 -34- 907z 7- 3232plusmn-001) 53242plusmn 00 53O2C 00

VV9272)7995 te009

9 29

1697994 104999 086999990403020

93267)22 950743795 9659324

S094502 0-)655391149425

41 plusmn112fl2222122[[1 13 57521 00 62534g 00 0342)000 911593359

1N 2ltill 111111lIH4 t--5JE 43I2 b6-3 6913plusmnfS 10739e 0000 1170000000600000 9931395199 42S29shy

14

24

11222[1i 1t221[ 4 7o3)97 0 7$140c00 45 78140E 00 O22q2e 00

22 2

13132221231h2--4afa0443500211i212131l22lll1n2l[2 47 e 643

= 30 10595E 0

00202000 00103300 00 00

999693plusmn02 99)775126 49fl746126 99i4t26

2IU2UUIEISlIIT1IIII 9 )595 0 94747 DO0 0101000 9999171

14 fII li2 ll I2II2222 [I 212lJlt321l2t2l2121211llJ _

5) 9aPn8e 00 PLUS IMF 00100000 999016

I MI T Fiue

1 4 L S 1 4$ n eig

1-r)233- ] ST2 700 90) s 13

Figure A-5 Drift Orbit Argument of Perigee Histogram (Degrees)

ICT INTERVA_ ORT N3MnAL -CT FQCO SUM

2 -36000E 02 -352505 02 505099945 50529QM0g0 -3 35250 02 -34500E 02 003090QQ A5l9070

I - 0N flSrOIEbo 50498c-34504E 040) 53 -33750E 02 -330006 02 00 50549 78

0 -32250r 02 -3500 02 00 505187580 3 -31500E 02 -30750E 02 00 505 fle8

13 -30000E 02 -292506 02 00 535 a878 -- 11 -29 50 02 -18500C 02 O0 -- 5_____h~VLd 2aarrZro6 00 54g7

13 -27750E 02 -270005 02 00 5)5499070751336D2O-242500- - 0E 02 -04 5059f7S4

350015 -26250f 02 -255000 02 00 50549575 2 -25500f 32 -247500 02 00 50549987a

-2 0 C 2 - 00 505fS87613 4 5 0 2 2 3 2 50 0 02I2 -1350i 02 -2Z5000 02 00 50549 50 -212000T2 02 567o54872500 O-O

77 21 -227501 02 -2l(000 02 00 So3599878 22t mZI001E 3-202506 02 00 - 5 908

231 -20250 02 -t9500C 02 00 505f9lg7e 2 -5SO0 02 -127505 02 00 505497879

25 -i 80005 02 -1 72500 02 00 53549978 ) 21 27 -17250E 02 -t65000 02 00 S05499876

0 - - -r--1- -fl3s 02 Zj576006 02 0C 50549118 S1 2l -1S750 02 -250005 02 00 505499978

gt 1 3 - 02 - 2500 02 00 505t09$7633 5000i I 1 31 -142500 3 2 -l3500 02 00 s05499070

4)J j 1 12 -11900i 02 -t27509 02 00 505199878

0 0 I 3334 -12500- 1250i 03 -11508 0103 0000 505499575 141 3 -91502E 03 -90000C 01 00 50599875

33 7SOQo- a2 62500C 02 00 503499078

02 8 5000 s o3 P07

Fi r An500053D4f-60rbi 02 02 00 50549907521 14 -6000E 0 -5500E 02 00 S0549178W4245noo

Ii~ S 37500S 02 -300000 03l 00 535499979 If - T 41 01 -475000t 01 00 50549987a

Ig I 1 It 3 ~ 01cfj0g220Ec a0s amp ~ fS0O1100 so549970I 1 ~43 3 5 Qc5 0 C 72 00

I SO SQ1W5 US5 INF 00 09998452 -shy

1125 43 ~ 52

~ h 3-2iAS l-321 b 03 - 2530 03 03 03 04 0175450 0178480 3IT924o 0179550 03

Figure A-6 Drift Orbit True Anomaly Histogram (Degrees)

6 ItO0

tINrFPVA

2 -10036E WIT N044AL

02 -96226C 00 PCT FREQ 00100000

Sum 00203000

3 76226= 17 -92075S__00 010SMOQOAD

P 3Z1 - - -

4 5

S

2 Fi3K- 4fli3r9C07735 95 -61423E 32 -63112E 00

fl2F--O040 00 -79620 30 -75468E 00 -54860 3 -71317 00

0 0 0020000

- 4040000 00600000 01000000

0 01 00000O 00300000 4080)000-0139)999 0 392999

-

n473 -67265plusmn 20 -63040 00 01600000 0152998

101 -- - -shy _________ -- 00 0222000 0 76 1 --shy 2 5592 30 54410E

3 7s0E20 -0I E S40lb -46407- 20 -42256E

0463 20000000 05900000 Ow-~ 090000000 12199993

II379727996 -- 4)6---------shy355975

I-S26 -42256F O0 -381040 0 18997996 570)971

I 13 -339531 00 -29001C 00 31479996 113329963 41

i 1 D 21

9plusmn-25649E -21449

00I 2-5495E0 -2198C 00 -7146E

0000 00

64 9

99445 fl995_______45499992 19 55V4922 45400000 241049654

4100 iI 461

Lill I [rill2[1

2-4 23 24

T44nF 04-I3)o5E -40 -045plusmn0 -90430Z-01 -0433Z-01 -46114E-01

442q4994 shy Z9-amp39-G 5o9099 53s9731 62579993 1 6677

gt1112 4i1

UTIAiIII

112212211

it ntil

-6

2 -730e-0234117=-0i 27- -1 21117 75$330 Z5 76633E-01t l2171 S 00 2p 1172S 00 15866E 00

64197991 60799292 58597297 60177995

54 559q53661 7699432 67$fl286 73st76

4 0211

Ill102 -----it---f---l$4n-)-Till122Il ll1 sill12121l

3plusmn 32

2001i33 00 241705 0)

20036plusmn 24170C 203215

00 00 00

6429199 47903000 3899996

9109103 433647036 07693775

SIi

223

------- lTrTT1V111111111

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Jr 2t7r4r lCU -shy34 324731 00 36624 00 33ll 16-fl 40TSE 0036 4o

76 3) 44920F 00

3 44S26 00 49079C 00 -34- 907z 7- 3232plusmn-001) 53242plusmn 00 53O2C 00

VV9272)7995 te009

9 29

1697994 104999 086999990403020

93267)22 950743795 9659324

S094502 0-)655391149425

41 plusmn112fl2222122[[1 13 57521 00 62534g 00 0342)000 911593359

1N 2ltill 111111lIH4 t--5JE 43I2 b6-3 6913plusmnfS 10739e 0000 1170000000600000 9931395199 42S29shy

14

24

11222[1i 1t221[ 4 7o3)97 0 7$140c00 45 78140E 00 O22q2e 00

22 2

13132221231h2--4afa0443500211i212131l22lll1n2l[2 47 e 643

= 30 10595E 0

00202000 00103300 00 00

999693plusmn02 99)775126 49fl746126 99i4t26

2IU2UUIEISlIIT1IIII 9 )595 0 94747 DO0 0101000 9999171

14 fII li2 ll I2II2222 [I 212lJlt321l2t2l2121211llJ _

5) 9aPn8e 00 PLUS IMF 00100000 999016

I MI T Fiue

1 4 L S 1 4$ n eig

1-r)233- ] ST2 700 90) s 13

Figure A-5 Drift Orbit Argument of Perigee Histogram (Degrees)

ICT INTERVA_ ORT N3MnAL -CT FQCO SUM

2 -36000E 02 -352505 02 505099945 50529QM0g0 -3 35250 02 -34500E 02 003090QQ A5l9070

I - 0N flSrOIEbo 50498c-34504E 040) 53 -33750E 02 -330006 02 00 50549 78

0 -32250r 02 -3500 02 00 505187580 3 -31500E 02 -30750E 02 00 505 fle8

13 -30000E 02 -292506 02 00 535 a878 -- 11 -29 50 02 -18500C 02 O0 -- 5_____h~VLd 2aarrZro6 00 54g7

13 -27750E 02 -270005 02 00 5)5499070751336D2O-242500- - 0E 02 -04 5059f7S4

350015 -26250f 02 -255000 02 00 50549575 2 -25500f 32 -247500 02 00 50549987a

-2 0 C 2 - 00 505fS87613 4 5 0 2 2 3 2 50 0 02I2 -1350i 02 -2Z5000 02 00 50549 50 -212000T2 02 567o54872500 O-O

77 21 -227501 02 -2l(000 02 00 So3599878 22t mZI001E 3-202506 02 00 - 5 908

231 -20250 02 -t9500C 02 00 505f9lg7e 2 -5SO0 02 -127505 02 00 505497879

25 -i 80005 02 -1 72500 02 00 53549978 ) 21 27 -17250E 02 -t65000 02 00 S05499876

0 - - -r--1- -fl3s 02 Zj576006 02 0C 50549118 S1 2l -1S750 02 -250005 02 00 505499978

gt 1 3 - 02 - 2500 02 00 505t09$7633 5000i I 1 31 -142500 3 2 -l3500 02 00 s05499070

4)J j 1 12 -11900i 02 -t27509 02 00 505199878

0 0 I 3334 -12500- 1250i 03 -11508 0103 0000 505499575 141 3 -91502E 03 -90000C 01 00 50599875

33 7SOQo- a2 62500C 02 00 503499078

02 8 5000 s o3 P07

Fi r An500053D4f-60rbi 02 02 00 50549907521 14 -6000E 0 -5500E 02 00 S0549178W4245noo

Ii~ S 37500S 02 -300000 03l 00 535499979 If - T 41 01 -475000t 01 00 50549987a

Ig I 1 It 3 ~ 01cfj0g220Ec a0s amp ~ fS0O1100 so549970I 1 ~43 3 5 Qc5 0 C 72 00

I SO SQ1W5 US5 INF 00 09998452 -shy

1125 43 ~ 52

~ h 3-2iAS l-321 b 03 - 2530 03 03 03 04 0175450 0178480 3IT924o 0179550 03

Figure A-6 Drift Orbit True Anomaly Histogram (Degrees)

ICT INTERVA_ ORT N3MnAL -CT FQCO SUM

2 -36000E 02 -352505 02 505099945 50529QM0g0 -3 35250 02 -34500E 02 003090QQ A5l9070

I - 0N flSrOIEbo 50498c-34504E 040) 53 -33750E 02 -330006 02 00 50549 78

0 -32250r 02 -3500 02 00 505187580 3 -31500E 02 -30750E 02 00 505 fle8

13 -30000E 02 -292506 02 00 535 a878 -- 11 -29 50 02 -18500C 02 O0 -- 5_____h~VLd 2aarrZro6 00 54g7

13 -27750E 02 -270005 02 00 5)5499070751336D2O-242500- - 0E 02 -04 5059f7S4

350015 -26250f 02 -255000 02 00 50549575 2 -25500f 32 -247500 02 00 50549987a

-2 0 C 2 - 00 505fS87613 4 5 0 2 2 3 2 50 0 02I2 -1350i 02 -2Z5000 02 00 50549 50 -212000T2 02 567o54872500 O-O

77 21 -227501 02 -2l(000 02 00 So3599878 22t mZI001E 3-202506 02 00 - 5 908

231 -20250 02 -t9500C 02 00 505f9lg7e 2 -5SO0 02 -127505 02 00 505497879

25 -i 80005 02 -1 72500 02 00 53549978 ) 21 27 -17250E 02 -t65000 02 00 S05499876

0 - - -r--1- -fl3s 02 Zj576006 02 0C 50549118 S1 2l -1S750 02 -250005 02 00 505499978

gt 1 3 - 02 - 2500 02 00 505t09$7633 5000i I 1 31 -142500 3 2 -l3500 02 00 s05499070

4)J j 1 12 -11900i 02 -t27509 02 00 505199878

0 0 I 3334 -12500- 1250i 03 -11508 0103 0000 505499575 141 3 -91502E 03 -90000C 01 00 50599875

33 7SOQo- a2 62500C 02 00 503499078

02 8 5000 s o3 P07

Fi r An500053D4f-60rbi 02 02 00 50549907521 14 -6000E 0 -5500E 02 00 S0549178W4245noo

Ii~ S 37500S 02 -300000 03l 00 535499979 If - T 41 01 -475000t 01 00 50549987a

Ig I 1 It 3 ~ 01cfj0g220Ec a0s amp ~ fS0O1100 so549970I 1 ~43 3 5 Qc5 0 C 72 00

I SO SQ1W5 US5 INF 00 09998452 -shy

1125 43 ~ 52

~ h 3-2iAS l-321 b 03 - 2530 03 03 03 04 0175450 0178480 3IT924o 0179550 03

Figure A-6 Drift Orbit True Anomaly Histogram (Degrees)

-- o JoMz J0e1 ar ~l~S00 Cr IITtRVA tfl NOWIAL PCT FR-G SUm

110 2 -12315C 03 -31855E 03 00 00100000 11 3 -tteSSrE 03 1139- 03 00 00100_000

-4 -1 r~l5r-U-rfl093-6y--rd 7100 020Z00000 045 -10935F 03 -3047E5 03 00200000 00400000

-00 7 -Z0015E 03 -95545S 02 00201000 03700000 41 a -95515F 32 -90955 02 00700000 01400000

-064E027 02 0o300000 021l901

13 07254352 -373E 02 01300000 33499096

I 35 -63340-- 02 -5739E 02 08699999 25+)9989

333) 4976 2 - 0~65 230000 0~3997

231133335741E 02 -379341 02 00397990 14990

1315323 -2335 02 -28733 02 5899996 271799774 331 -2139E 0 02 565999 325399655S4) 24 - 7 02 -57332F 03 26779990 7339126

41 33 ZS 03 - 03 r02 66899f9 6522$99310717911l-133i13111123 -2 4437E3314 3E0 7t-21913F6721 51996

21 -36735E 02 -3134 02 53591998 164599902 -0) l3ll3l33l3 J2 3e745 02 ]0441 02 4639)099 8337)9303

i61 M73ill3331 14 20751 02 -1676 02 35597998 25390944

- t tt-tt-tt 3 111 13311133111 3 3273 02 24ZE 02 3609997 56)8650

S) 33 11 1133131lllll U) 0)5 32 536001 02 1392994 g590419740 - H 5It50 32 5620-9 02 05703000 954298403131133ll11131 4l 1 - I l XIIIIIIIIIIIlI l 2 0 206 6V 02 35597995 NS-9 09 2

33333113133Zll 4 00832 5621= 01 300000 9960593 00l 42 10273F 02 53-997 7649951565it41111 0236 TrITIItril 16464E -202 619000099f10836932r11at

3 4 l[1lll1133l3ll3lll3l 5 sP4F 0 920155 02 O00000 998299035 shy02_ 62 06 -54298-shy33133 SIR__ 0 O

3H Hitt 2 33I3 -- 1131313113133113 37 bJ885502 38456F 02 00500000 999397385S1 Illl i3ll

111 133 t 333 Csit bO1116 32 )308 02 1099990 916809

303 O 00 900 9949816Fiure A-7 erig R adi H2 516ogra 9KilotersDriftOrIIIit e m0

IZ2J 9I6i N wfp 9976

Figure A-7 Drift Orbit Perigee Radius Histogram (Kilometers)

i7(

c1 DTERVAL WTI NOW4AL PCT FREO SUM

Z -14837E 33 -14176E 03 00 00100000Iql 3 -14176E 03 -1351SEF 03 0000000 00600000

2 03 -12192ES1 2B535 03 00600000 01t9)999 07 -11531- 03 -10869E 03 01700000 05299999Aq7 + 10469E 03 -10208E 03 02900000 05190995

euro0 I 0-9 54665 02 -60853 02 04700000 7199984421 11 -BBA53E 02 -02239E 02 08400000 25599976

13 -75626 02 -69013 02 13899994 40699965 4115 -62399E 02 -55186E OZ 2159)996 8799990

M20 16 -55786E 02 -49172S Q2 27599993 11559967

6 8 -425503 02 -369466 02 4049992 191799927461) -W3546i 02 -29332c 02 49099990 2OS2l1l1

0 21 22719- 02 -16106 02 55993994 352299652

23 -4919-310 -28785e 01 5167995 4613994454424 -20785i 01 37349E 01 61599998 5289993293ZZI[I25 3739 0i10 e0 609952 S1121TIT 1 24 10343- 2 169625 02 55000009 644209316

IlIlIII 1 27 16962E 02 23575E 02 50697997 694999237

-61 I1II1I 1 2 3J01PRE 02 16002E 02 46092996 93999023 11) 30 36802 02 43415E 02 40899992 83659a987IIIIIIhILI

471 IIJII[I1 31 43415- 02 50029F 02 37997992 872595065600 lIII u111 32 50029 02 56642S 02 28297999 901198730

Al UIIIll II11111 34 6325W 02 69069e 02 20499292 943498535141 1IIlIlllII1 35 69567- 02 76482E 02 13597994 057378529

1-Tf I T 1111t I-- rn ~ r0 oz5sras9r~l94c11 11TlIIZIII 3 3095F 02 89096 02 09400000 99398346 ++P UUIIJIiIUII I ILI 3EIZ09112 96322E 02 0S7200009860933 h) I1JIlItllII[lil B7 46322F 02 10294E 03 04803000 990852852 IIlIIll1III M111 4) 10 94= 03 1055 03 02803000 9936a213

311 IhiIJIIlIllIl 4a 11616E 13 1227BE 03 01799999 997608059111 tlI1lJ~lIltz riz 43 l22BE 33 12939E 03 00530000 99812793784 Ir I IzItItrIzt- 1- 930 03 13600E 03 030703000 99T88955

IlllllllIiiIlllllll 45 13(00c 03 14262F 03 00600000 999497933 1IIHIZ Zi[11111111111_S-- J 422Z03 T 2 ac 03 00 03300 -992697723 893 l~llllllllIczzIIIIololll 7 1 414z36 33 155084 03 00 99967723

1a0 I1111111I~luxzlrzzzl l 4i 15584z 03 16246F 03 00200000 99989614

I I41 ll lll|IIlll1lilll 3 I607E 03 -- UV 14F 00100000 999997559-i i u ilr 3lhlu 43-Iorxu 7l ronilI

Siure A-52 ODri O bApoge (Kilometers)

Figure A-8 Drift Orbit Apogee Radius Histogram (Kilometers)

i7(

c1 DTERVAL WTI NOW4AL PCT FREO SUM

Z -14837E 33 -14176E 03 00 00100000Iql 3 -14176E 03 -1351SEF 03 0000000 00600000

2 03 -12192ES1 2B535 03 00600000 01t9)999 07 -11531- 03 -10869E 03 01700000 05299999Aq7 + 10469E 03 -10208E 03 02900000 05190995

euro0 I 0-9 54665 02 -60853 02 04700000 7199984421 11 -BBA53E 02 -02239E 02 08400000 25599976

13 -75626 02 -69013 02 13899994 40699965 4115 -62399E 02 -55186E OZ 2159)996 8799990

M20 16 -55786E 02 -49172S Q2 27599993 11559967

6 8 -425503 02 -369466 02 4049992 191799927461) -W3546i 02 -29332c 02 49099990 2OS2l1l1

0 21 22719- 02 -16106 02 55993994 352299652

23 -4919-310 -28785e 01 5167995 4613994454424 -20785i 01 37349E 01 61599998 5289993293ZZI[I25 3739 0i10 e0 609952 S1121TIT 1 24 10343- 2 169625 02 55000009 644209316

IlIlIII 1 27 16962E 02 23575E 02 50697997 694999237

-61 I1II1I 1 2 3J01PRE 02 16002E 02 46092996 93999023 11) 30 36802 02 43415E 02 40899992 83659a987IIIIIIhILI

471 IIJII[I1 31 43415- 02 50029F 02 37997992 872595065600 lIII u111 32 50029 02 56642S 02 28297999 901198730

Al UIIIll II11111 34 6325W 02 69069e 02 20499292 943498535141 1IIlIlllII1 35 69567- 02 76482E 02 13597994 057378529

1-Tf I T 1111t I-- rn ~ r0 oz5sras9r~l94c11 11TlIIZIII 3 3095F 02 89096 02 09400000 99398346 ++P UUIIJIiIUII I ILI 3EIZ09112 96322E 02 0S7200009860933 h) I1JIlItllII[lil B7 46322F 02 10294E 03 04803000 990852852 IIlIIll1III M111 4) 10 94= 03 1055 03 02803000 9936a213

311 IhiIJIIlIllIl 4a 11616E 13 1227BE 03 01799999 997608059111 tlI1lJ~lIltz riz 43 l22BE 33 12939E 03 00530000 99812793784 Ir I IzItItrIzt- 1- 930 03 13600E 03 030703000 99T88955

IlllllllIiiIlllllll 45 13(00c 03 14262F 03 00600000 999497933 1IIHIZ Zi[11111111111_S-- J 422Z03 T 2 ac 03 00 03300 -992697723 893 l~llllllllIczzIIIIololll 7 1 414z36 33 155084 03 00 99967723

1a0 I1111111I~luxzlrzzzl l 4i 15584z 03 16246F 03 00200000 99989614

I I41 ll lll|IIlll1lilll 3 I607E 03 -- UV 14F 00100000 999997559-i i u ilr 3lhlu 43-Iorxu 7l ronilI

Siure A-52 ODri O bApoge (Kilometers)

Figure A-8 Drift Orbit Apogee Radius Histogram (Kilometers)

Cr I9TERVA WIT NDOM AL OCT FRO SUM

- 2 -1 7912-04 10644E-03 419999 41799954 3 I 0644S-3 g 3T67z0IU 2079295 124fl9

4 iiZ3TFf 0 O 86899996 2I119984t3 6 9 0S 356005-D3 4812E-03 80690997 2920 762

60351-03 3256E-03 69279994 437099609 D 85781E-03 61191999 4952995617325R03

-2 i 13 93304E-33 11083E-02 50549995 60 1g9S 4 11 TUl - --- JI IUCQrt I245E02 4939995 A53599396-2 wf T 12 12335E-32 13587E-02 469994 100399323 76 11bull 13 a35BE-02 14840E-02 3709)992 735399200

753 fl~~~~~~~t ~~-4 -- A--4s0E-4--aoF4- A992-7~041 till l692E-02 30199995 804590545 IJ44E-02 pt)1 ittHS 17344F-02 18596F-02 2859997 533099907

I lIT IS t9844E-02 21101E-02 19099998 87295737

2l 23o066-02 15999994 1S5af till1235F02 43 2III23606E-02 24858502 13099995 9214)5553

633 111111 -n-----e~-2-e4l 4 115-~ 1--30499995- -03-491 3 -shy- 02 S 111T1l 23 26110E-O2 27362E-02 1019095 945698395

I I|JI7i 24 27362S-02 28615E-02 03000000 95368273

bull5 HlZIET 26 29e6E-3 3iI9r-02 0559999 9641821

43 11II1lIlt t - - - 2~1111 3Z372E-02 0 amp4Q2DI poundplusmnzsnIL - - 6 |lfltl l y 23 32372f-02 33624E-02 05103000 97535|6354 IIfItIIIIl 2) 3362-E-02 3466E-02 03097909 99428138

|TIIiIl11 T 31 3612eF-02 3781r-02 02397999 9859992S

v IIIITIIIIIf 3 3gJE5-02 111331-02 01900000 991597693 V) tti - tllJO+-0423906-2 02003003 -93522662 -shy

35 423926-02 4342E-02 01303000 99k75541111 [trlllIlT 31 43642F-32 448O5E-02 00903000 995397522 280 131U1111111I II-- -- 004 974II0 amp 3 lllllllZIliICl 37 6167-32 4739gq-02 00903000 994f7405 4 trilllupIIzrlr1 43 41397-02 48651E-02 OC401100 9989339

TIlIltTIIII[IIIII tt - 40-j2 g3tQ1t-02 J04UJ0Q003 lll 42 4 4o-0F-32 5 3135-02 00)05000 9961720v99221l~) iii III (Iii------------------ n110000331SS2 993726002 048

123 IIiiZJll IETii 94-13F-92- S614E--0 -00100000-99939693 113 43

TITlIIITIITTIIT TIIIIlIl1TI Itililll

47 45

561657-D2 57427i-a2

574167-02 586706-02

00101000 00230000

99)6916 09)695308

140 ITTIIIYIITITIITIITTTIII 53 922f-02 OUS I 00102000 999966-3

I TO 3ZO 5 la 31 4) 35 51

SL S

igure A 90 osA 2V y 30A5c0 o 700 900 95 9o

Figure A-9 Post-AMF Velocity To Acquire Station Histogram (KilometersSecond)

T PNTEampVAL Olt N3MINAL OCT F4EQ SUM a 00Z5n at

3 - 3- 59E - 5977 3D1 -5 5970-1 5274E 001 004000000200000 0050000000700000 - -- rzT57E-n--z1~-1-Trvr

- 6132 00 -13928E O U300

00603000 0r71aIFr 0159919

324E 22 l250JE03 01500 00 039999 2-t2563E 01 -tI350E 01 02007000 05799799

43 1 3701 03 -105150 03 03403000 1i499990 - 05255 01 -9831E 00 15000000 1744990

0 3 tOE 20 -34662C 00 09899999 34792196 - - tkC462E00 -7f350-00 - 11293222 A609Zl2-shy

-4 -

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Figure A-10 Initial Longitudihal Drift Rate Histogram (DegreesDay)

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Figure A-11 On-Station Weight Histogram (Pounds)

CI4TFRVA l WIT N3414AL PCT FRTG sum

t - 26345-02 4604E-01 41099997 41099997 eqO ~34604E-31 10036E 00 8 112 9 bull)J ~

41 5 15467 00 20018E 00 80699997 269999

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2CT ITFPVA_ WIT NaMI4AL OCT f EO Sum

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Figure A-l3 Velocity Change Required To Correct Semimajor Axis and Eccentricity Histogram (KilometersSecond)

T PNTEampVAL Olt N3MINAL OCT F4EQ SUM a 00Z5n at

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157-9999 28n9996

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9R 1419960

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2

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3877992 4077790 5142996

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50597295 262966458392992 305399620

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Figure A-10 Initial Longitudihal Drift Rate Histogram (DegreesDay)

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9

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4ITERVAL lqT NOMINAL PCT FREQ sUm

2 -25-87E 03 -2543E 1 0020)000 00300000 33 -2t54431 02 =24900 _II_l 0O-- 0O5000

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Figure A-11 On-Station Weight Histogram (Pounds)

CI4TFRVA l WIT N3414AL PCT FRTG sum

t - 26345-02 4604E-01 41099997 41099997 eqO ~34604E-31 10036E 00 8 112 9 bull)J ~

41 5 15467 00 20018E 00 80699997 269999

0 263295 00 3 1760E 0O0 69093998 31 9567 q 9 3 1760E 0 0 31191E O0 6199 94094

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Figure A-12 Hydrazine Fuel Used To Acquire Station Histogram (Pounds)

2CT ITFPVA_ WIT NaMI4AL OCT f EO Sum

2 -6791E-4 -I0253E-4 01190999 O|2909f9 62409 3 -10253E-D4 -17147r-05 0l0000 239 shy

- - 4r- 3 a-- 16EO 1t5904 31130981 5 S82361-05 15362E-04 337399902 7t5799713

tAQ -- - - 4SSS2Ot2J0-OA 434709 fl1S940- -S 5 1 2OO4 32439E04 44691993 19U99500 5 32439f-34 409775-04 20403000 91259432

Up t~7~~001 M 0r 1t 15 49SISE-54 SAOSCG-04 08303000 92102924121 I| 5e05-34 66592E-04 06197999 936099Z43

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- 13 523rF-3 63669E-04 05107000C 946199158 5 is 2207-34 10175S-03 07001003 96209139

I IS I005-03 10928 -03 5597999 967695975

I Ii ~i1742--03 12b6E0 169999515983 it -- 1 12-36E-03 13403 037aO00 f09907T9I490E-3230500 98 2ga37 I al I51962-03 1 03000 98398 t121 14344F-03 12216-03 26051503 0190300 083-1S055I

Z It 23 16017=-03 16905F-03 01903000 9809856 2 24 1)5SE-13 17759E-03 01500000 9297840I

1 -202 1 467E-03 t27 6103 01301000 f9345837

I 25 a3 3 01 30000 99219131 l9A 20321E-03

ITt 5 203 -O3 2t27S-43 3l502000 9999131572 3 I 25 21174-03 2202F-03 0I101000 095097 71 2 I 33 22325=-33 22811303 0 03000 99497633 I I 31 2212C33 23 7-03 Do0000099729763

If a 3o5736-03 24$0-03 00303000 q9191656 it 34 25144--D3 Z62S7E-C 0533000 90 14467

35 2af2q2-03 2ISIV-03 00400500 99989400711 3 5 3 q43O52-03 0011000 )93973622-5~ 37 2SOOSL-33 2d6S9 -0 10101000 997077240 2BSOIE-03 29113E-03 00103000 999L97z23~f 3t 24712-03 30567S-03 3CIOOOOO 99297133

r C I 45 3057i-03 31420E-03 0013000 990397t25

gr I e JV2o74t-03 33l2eR-03 0020300 99o 9o 5x6s and3 r3 3312Ers 3312-o03 00 6969I60

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0 13 Z 1 1 15 AD i5 3

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Figure A-l3 Velocity Change Required To Correct Semimajor Axis and Eccentricity Histogram (KilometersSecond)

_

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bullAO0 fl3-__

9

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4ITERVAL lqT NOMINAL PCT FREQ sUm

2 -25-87E 03 -2543E 1 0020)000 00300000 33 -2t54431 02 =24900 _II_l 0O-- 0O5000

24 90 1 435 41 00200000 006000005 -24357 31 -2381-E 03 0010000 0070000 - J444--4rfl)S -O-- O4040---4004 ------ -232E1 01 -2228E 01 00400000 01299929

943 22728E 01 -2123851E 0 0010)000 01399999

-

4

315

44 20

S4 5 4

--

Ills

129 ~~~

-

-

Yfl it

1 1-

311111

illI 111111

1111111

$2l 13 -21642E M -21098E 0L

Zta0J Q5IS_ 5l l2-osss OI - 0012E 01 13 201121 01 -1046C 01

IS -16926- 01 -10353E 01 -2f733 31 -17040E 01

is -172-71E 01 -16753E OA 2317hW20 1 15600

21 -45667- 01 -15124E 01

23 -1451k 03 -140383 0l 24 -14038F 31 -13495[ 01

25 -12152F 01 -12409E 01

00400000 QQ0QQ 01000000 00500000

01799909 01500000

000000 00000 03803000

05300000 05900000

06402000

0 092919 f

03599918 0t099997

06899996 05399496

12099979 35999979 2799911

29799967 35699959

4799952

I- I 023 ^ 41 111131it

1[llllllllll ~llll 323221 1111 2

-lOflE36 0-69301-969301 30 -91499731165 1179 3 24 ot6~S304 93

0000 00

1503000t900000 21094993

l07599936125499935 699998

stZlIff01334- 3-1 -84l 01 -469f 00 - 9 4

3 796

111131111 J[l ti t1113111111

1111 32A)

-5q)l3t 03 -S34121E 00

-53492 4 405E

00 00

1S90090 4669293

353496 60992 _________

- 1 41 - 12

333 3~0

3

IIU1IIII1

1113lI[ 111115 42 220 00 -3971 00

I it4ll31 3 1l 111111 1 I 4 -3 l753 00 -26 3261 00 1 1 1 11 1 1 5I 632 1G -2 0 90010 0

I| t41 11I11I 4-EII--4----4-3a42E-- --shy wS-64E 00-

1lll3I l~lIl1lI33321 47 -15464 30 -10033E 00 113213lllti[i11110111 4 lfl330 0 -60a1-01

11131133111lll~ll[I11111111 53 b2605-02 LUS INF llliltl llll l 11111 11- I I

54599991

69199993 409299 4

-60597991

0559995 8139)994

00

505899506

6372 93 7 35 399 546 -701399207shy

677599132 9557)9176

999992054

Srto 3V L

$) 120 3) 500 00 900 950 925

Figure A-11 On-Station Weight Histogram (Pounds)

CI4TFRVA l WIT N3414AL PCT FRTG sum

t - 26345-02 4604E-01 41099997 41099997 eqO ~34604E-31 10036E 00 8 112 9 bull)J ~

41 5 15467 00 20018E 00 80699997 269999

0 263295 00 3 1760E 0O0 69093998 31 9567 q 9 3 1760E 0 0 31191E O0 6199 94094

a2622f 00 0011a 4| 10053F 50897992 $99599304

nbull 00 489999459S|992a07 1 11 13 Sallar 30 6434nP 00 40000000 135199280

I t]ilt 15 69778F 00 75209E 0 - 30499992 800999146 f it is5 1 5709F 00 80640E 00 29099998 830094330

41 lITT Ib 66071F 30 71502F 00 197996 S74599999 I Ififfl 1 91502F O0 a6933- 00 17797997 41913989 L7

a ITIT 21 10236E 01 10780P 01 14899998 92156B22

Ill 23 11323F 01 11866= 01 10097993 943393621 j ITTlll 24 11-66E 21 1209E 01 08200000 952DO5541

41 TTl~ll 2S |2M5F O 13495 Ol 0 MOO000 6 Z9O01

illl 2 14E le01 5Z4 01 03697999 974193303 s40 IITTIIIII X) - t 01 15667S 01 03903000 9849981g

11111117111TIJ 31 15667E 31 1621H 01l 0290)000 9553)81 32 I 3 16IIF 31 16754E 01 02000000 987395102llIIIIlIIII

16 If flillTllI 14 1 72-7F 31 1784OF 0t 0200000 q915 5s lllllll 35 IP40ft 01 ie383 01 0lS03000 99309792

II| Jf 37 18926- 01 19469E O 01 10O0000 1955ITOZ7 ) |I]I||1I 3 A9469i It 20012C 01 00500000 99637705

TIM 11lllll 34 Z 12- 01 2055SE 01 01003000 92397614IIII ITT 1111111l~ P 43 055 I1 21099F ofO 0050000 g 74T)

illl 11 111111 111 42 1142E 01 2218SE 01 00300000 99917414 1I1 fitlllll~l 3 011 O 99a597357ItI Z2185E 22728r 00101300

TIil 11111IIYTITI U 2 21720 0I aIZ71E O 0 0 01000 99 a0q210 11111111111T1IiimII 45 2- 7j of 236i-C of 00200000 9992971SO

1 |l~lll][Iilllll - k5 at0 2J5YE 01 001O00000 O0D37I2S t~) l[l[lllll~ll v 2435IE 01 2900C 01 00100000 99 7497070

101 [1 1l 111111 l1111ll 49 01 01 999695950It 24005 2543E 00201000

llj~ 5) 41 11111 Illll I ll] [Il[~ 25q86E 01 PLUS IV 001030000 09 n96796

bull rI) )I33))510 700 900 951 915

Figure A-12 Hydrazine Fuel Used To Acquire Station Histogram (Pounds)

2CT ITFPVA_ WIT NaMI4AL OCT f EO Sum

2 -6791E-4 -I0253E-4 01190999 O|2909f9 62409 3 -10253E-D4 -17147r-05 0l0000 239 shy

- - 4r- 3 a-- 16EO 1t5904 31130981 5 S82361-05 15362E-04 337399902 7t5799713

tAQ -- - - 4SSS2Ot2J0-OA 434709 fl1S940- -S 5 1 2OO4 32439E04 44691993 19U99500 5 32439f-34 409775-04 20403000 91259432

Up t~7~~001 M 0r 1t 15 49SISE-54 SAOSCG-04 08303000 92102924121 I| 5e05-34 66592E-04 06197999 936099Z43

I - -1r-g602 0 7siatF-a a6a2000 q4plusmn1i3

- 13 523rF-3 63669E-04 05107000C 946199158 5 is 2207-34 10175S-03 07001003 96209139

I IS I005-03 10928 -03 5597999 967695975

I Ii ~i1742--03 12b6E0 169999515983 it -- 1 12-36E-03 13403 037aO00 f09907T9I490E-3230500 98 2ga37 I al I51962-03 1 03000 98398 t121 14344F-03 12216-03 26051503 0190300 083-1S055I

Z It 23 16017=-03 16905F-03 01903000 9809856 2 24 1)5SE-13 17759E-03 01500000 9297840I

1 -202 1 467E-03 t27 6103 01301000 f9345837

I 25 a3 3 01 30000 99219131 l9A 20321E-03

ITt 5 203 -O3 2t27S-43 3l502000 9999131572 3 I 25 21174-03 2202F-03 0I101000 095097 71 2 I 33 22325=-33 22811303 0 03000 99497633 I I 31 2212C33 23 7-03 Do0000099729763

If a 3o5736-03 24$0-03 00303000 q9191656 it 34 25144--D3 Z62S7E-C 0533000 90 14467

35 2af2q2-03 2ISIV-03 00400500 99989400711 3 5 3 q43O52-03 0011000 )93973622-5~ 37 2SOOSL-33 2d6S9 -0 10101000 997077240 2BSOIE-03 29113E-03 00103000 999L97z23~f 3t 24712-03 30567S-03 3CIOOOOO 99297133

r C I 45 3057i-03 31420E-03 0013000 990397t25

gr I e JV2o74t-03 33l2eR-03 0020300 99o 9o 5x6s and3 r3 3312Ers 3312-o03 00 6969I60

-I 4 4 3 35Al7-33 34616-01 10t01000 q906906 Pt45 14-361-3 356902-03 I0 999795315

II4S 35620-O3 365437-03 00103003 09O81SSI$t ni III I 3ampS4J3- 3 3 3139E-03 00 99 18964510124 fil 37397F-13 3 25IV- CS3 00 99 59651

I IfP133415tSc Iff~~ - shyfitly 51 39205E-33

3 LU5 INdr 0OIC3000 9994614o

0 13 Z 1 1 15 AD i5 3

C21st13) 30) 53O 700 90 950 90

OA 1 1 -I 91 2 I )2o) JlIaD-)I 312SIb-11 013911c-Ct 04t32I5)-2l 3I372I0-)I 31 75-3I

Figure A-l3 Velocity Change Required To Correct Semimajor Axis and Eccentricity Histogram (KilometersSecond)

CI4TFRVA l WIT N3414AL PCT FRTG sum

t - 26345-02 4604E-01 41099997 41099997 eqO ~34604E-31 10036E 00 8 112 9 bull)J ~

41 5 15467 00 20018E 00 80699997 269999

0 263295 00 3 1760E 0O0 69093998 31 9567 q 9 3 1760E 0 0 31191E O0 6199 94094

a2622f 00 0011a 4| 10053F 50897992 $99599304

nbull 00 489999459S|992a07 1 11 13 Sallar 30 6434nP 00 40000000 135199280

I t]ilt 15 69778F 00 75209E 0 - 30499992 800999146 f it is5 1 5709F 00 80640E 00 29099998 830094330

41 lITT Ib 66071F 30 71502F 00 197996 S74599999 I Ififfl 1 91502F O0 a6933- 00 17797997 41913989 L7

a ITIT 21 10236E 01 10780P 01 14899998 92156B22

Ill 23 11323F 01 11866= 01 10097993 943393621 j ITTlll 24 11-66E 21 1209E 01 08200000 952DO5541

41 TTl~ll 2S |2M5F O 13495 Ol 0 MOO000 6 Z9O01

illl 2 14E le01 5Z4 01 03697999 974193303 s40 IITTIIIII X) - t 01 15667S 01 03903000 9849981g

11111117111TIJ 31 15667E 31 1621H 01l 0290)000 9553)81 32 I 3 16IIF 31 16754E 01 02000000 987395102llIIIIlIIII

16 If flillTllI 14 1 72-7F 31 1784OF 0t 0200000 q915 5s lllllll 35 IP40ft 01 ie383 01 0lS03000 99309792

II| Jf 37 18926- 01 19469E O 01 10O0000 1955ITOZ7 ) |I]I||1I 3 A9469i It 20012C 01 00500000 99637705

TIM 11lllll 34 Z 12- 01 2055SE 01 01003000 92397614IIII ITT 1111111l~ P 43 055 I1 21099F ofO 0050000 g 74T)

illl 11 111111 111 42 1142E 01 2218SE 01 00300000 99917414 1I1 fitlllll~l 3 011 O 99a597357ItI Z2185E 22728r 00101300

TIil 11111IIYTITI U 2 21720 0I aIZ71E O 0 0 01000 99 a0q210 11111111111T1IiimII 45 2- 7j of 236i-C of 00200000 9992971SO

1 |l~lll][Iilllll - k5 at0 2J5YE 01 001O00000 O0D37I2S t~) l[l[lllll~ll v 2435IE 01 2900C 01 00100000 99 7497070

101 [1 1l 111111 l1111ll 49 01 01 999695950It 24005 2543E 00201000

llj~ 5) 41 11111 Illll I ll] [Il[~ 25q86E 01 PLUS IV 001030000 09 n96796

bull rI) )I33))510 700 900 951 915

Figure A-12 Hydrazine Fuel Used To Acquire Station Histogram (Pounds)

2CT ITFPVA_ WIT NaMI4AL OCT f EO Sum

2 -6791E-4 -I0253E-4 01190999 O|2909f9 62409 3 -10253E-D4 -17147r-05 0l0000 239 shy

- - 4r- 3 a-- 16EO 1t5904 31130981 5 S82361-05 15362E-04 337399902 7t5799713

tAQ -- - - 4SSS2Ot2J0-OA 434709 fl1S940- -S 5 1 2OO4 32439E04 44691993 19U99500 5 32439f-34 409775-04 20403000 91259432

Up t~7~~001 M 0r 1t 15 49SISE-54 SAOSCG-04 08303000 92102924121 I| 5e05-34 66592E-04 06197999 936099Z43

I - -1r-g602 0 7siatF-a a6a2000 q4plusmn1i3

- 13 523rF-3 63669E-04 05107000C 946199158 5 is 2207-34 10175S-03 07001003 96209139

I IS I005-03 10928 -03 5597999 967695975

I Ii ~i1742--03 12b6E0 169999515983 it -- 1 12-36E-03 13403 037aO00 f09907T9I490E-3230500 98 2ga37 I al I51962-03 1 03000 98398 t121 14344F-03 12216-03 26051503 0190300 083-1S055I

Z It 23 16017=-03 16905F-03 01903000 9809856 2 24 1)5SE-13 17759E-03 01500000 9297840I

1 -202 1 467E-03 t27 6103 01301000 f9345837

I 25 a3 3 01 30000 99219131 l9A 20321E-03

ITt 5 203 -O3 2t27S-43 3l502000 9999131572 3 I 25 21174-03 2202F-03 0I101000 095097 71 2 I 33 22325=-33 22811303 0 03000 99497633 I I 31 2212C33 23 7-03 Do0000099729763

If a 3o5736-03 24$0-03 00303000 q9191656 it 34 25144--D3 Z62S7E-C 0533000 90 14467

35 2af2q2-03 2ISIV-03 00400500 99989400711 3 5 3 q43O52-03 0011000 )93973622-5~ 37 2SOOSL-33 2d6S9 -0 10101000 997077240 2BSOIE-03 29113E-03 00103000 999L97z23~f 3t 24712-03 30567S-03 3CIOOOOO 99297133

r C I 45 3057i-03 31420E-03 0013000 990397t25

gr I e JV2o74t-03 33l2eR-03 0020300 99o 9o 5x6s and3 r3 3312Ers 3312-o03 00 6969I60

-I 4 4 3 35Al7-33 34616-01 10t01000 q906906 Pt45 14-361-3 356902-03 I0 999795315

II4S 35620-O3 365437-03 00103003 09O81SSI$t ni III I 3ampS4J3- 3 3 3139E-03 00 99 18964510124 fil 37397F-13 3 25IV- CS3 00 99 59651

I IfP133415tSc Iff~~ - shyfitly 51 39205E-33

3 LU5 INdr 0OIC3000 9994614o

0 13 Z 1 1 15 AD i5 3

C21st13) 30) 53O 700 90 950 90

OA 1 1 -I 91 2 I )2o) JlIaD-)I 312SIb-11 013911c-Ct 04t32I5)-2l 3I372I0-)I 31 75-3I

Figure A-l3 Velocity Change Required To Correct Semimajor Axis and Eccentricity Histogram (KilometersSecond)

2CT ITFPVA_ WIT NaMI4AL OCT f EO Sum

2 -6791E-4 -I0253E-4 01190999 O|2909f9 62409 3 -10253E-D4 -17147r-05 0l0000 239 shy

- - 4r- 3 a-- 16EO 1t5904 31130981 5 S82361-05 15362E-04 337399902 7t5799713

tAQ -- - - 4SSS2Ot2J0-OA 434709 fl1S940- -S 5 1 2OO4 32439E04 44691993 19U99500 5 32439f-34 409775-04 20403000 91259432

Up t~7~~001 M 0r 1t 15 49SISE-54 SAOSCG-04 08303000 92102924121 I| 5e05-34 66592E-04 06197999 936099Z43

I - -1r-g602 0 7siatF-a a6a2000 q4plusmn1i3

- 13 523rF-3 63669E-04 05107000C 946199158 5 is 2207-34 10175S-03 07001003 96209139

I IS I005-03 10928 -03 5597999 967695975

I Ii ~i1742--03 12b6E0 169999515983 it -- 1 12-36E-03 13403 037aO00 f09907T9I490E-3230500 98 2ga37 I al I51962-03 1 03000 98398 t121 14344F-03 12216-03 26051503 0190300 083-1S055I

Z It 23 16017=-03 16905F-03 01903000 9809856 2 24 1)5SE-13 17759E-03 01500000 9297840I

1 -202 1 467E-03 t27 6103 01301000 f9345837

I 25 a3 3 01 30000 99219131 l9A 20321E-03

ITt 5 203 -O3 2t27S-43 3l502000 9999131572 3 I 25 21174-03 2202F-03 0I101000 095097 71 2 I 33 22325=-33 22811303 0 03000 99497633 I I 31 2212C33 23 7-03 Do0000099729763

If a 3o5736-03 24$0-03 00303000 q9191656 it 34 25144--D3 Z62S7E-C 0533000 90 14467

35 2af2q2-03 2ISIV-03 00400500 99989400711 3 5 3 q43O52-03 0011000 )93973622-5~ 37 2SOOSL-33 2d6S9 -0 10101000 997077240 2BSOIE-03 29113E-03 00103000 999L97z23~f 3t 24712-03 30567S-03 3CIOOOOO 99297133

r C I 45 3057i-03 31420E-03 0013000 990397t25

gr I e JV2o74t-03 33l2eR-03 0020300 99o 9o 5x6s and3 r3 3312Ers 3312-o03 00 6969I60

-I 4 4 3 35Al7-33 34616-01 10t01000 q906906 Pt45 14-361-3 356902-03 I0 999795315

II4S 35620-O3 365437-03 00103003 09O81SSI$t ni III I 3ampS4J3- 3 3 3139E-03 00 99 18964510124 fil 37397F-13 3 25IV- CS3 00 99 59651

I IfP133415tSc Iff~~ - shyfitly 51 39205E-33

3 LU5 INdr 0OIC3000 9994614o

0 13 Z 1 1 15 AD i5 3

C21st13) 30) 53O 700 90 950 90

OA 1 1 -I 91 2 I )2o) JlIaD-)I 312SIb-11 013911c-Ct 04t32I5)-2l 3I372I0-)I 31 75-3I

Figure A-l3 Velocity Change Required To Correct Semimajor Axis and Eccentricity Histogram (KilometersSecond)

PCT l1jTFPgA- 04Y NMI14AL PCT FREQ SUM

2 -82634E-02 -45121-02 01199999 01200999 A23 ___ ____________________________3 -4St22002 -76083E-03 Ot 11000-00 P2]99 W

- - - ~ r~t)E~i6s~zri-4~c937689987247 S 29051-02 67417C-02 338199921 715099772

-fl--------------1- - ----47 --- ~Z2E -1049M-41 -T32l40493 0472052 shy50) 7 IO4Q3c-Ot 14244E-01 4899990 89219554

14244E-01 20400000410 1 17996E-01 91259451

0 i 274Th-0l 2549E-01 0400000 92f119945 - 1 292---01- 3-30--E-0- 06600000 9 49925-37

10 13 33001i - 36752n-0 05700000 9bS19158

amp4255S 96 10 4 1 4 8006E-01 0 580 0000 7S 9 522

I -23 51757E-0 555008-01 13503000 975008658 S

- 2 5-2-OF-- 63011[-01 1239999 902Z95554 1101 y 21 6302l-o1t 66762E-01 01701000 983978556

II 23 105141-_1 42 6SE-0 0190300 957798339 -7I It 24 74265E-)I 7801f6-01 01500000 98029BZ45

S II 26 d2767F-Ot S519F-0I 0130700 99298029 40 it 27 -655191-ol 892T0E-0 03900000 99397)25 -

I -411 - B 8f9 3021F-01 01500000 99499066~-3t1 111 I2 2 302IE-01 06773E-01 11100000 996097717

2Z0 I -3 - 7 01 O0af2 00- 00400000- W964976S0 1 If - 31 1052F 30 10420E 00 00800000 997297561

| - 32 2242F O0 20603f 00 00300000 997597534 3J-up- )o~rrL 00 UUU 9 dJ

032 1n It 3 0227F 31rS8 00500000 09 4731430 00 I1 7 5 L153 01 129258 00 00405000 99332724

335 IIC28t 20 12303r CO OOq000 993971921 V 37 1203F 30 1ZC7O 00 00200003 99 97137 I 34 27E00 23053S 00 001 00000-- 0441070

12 IC - - 3 3051 00 134298 00 03133000 0992v0a | III -43 13421 00 23 04 00 0010)000 9973l)73

-- tiF O02411 i 42 0 414 00200000 99459S338 ~~~~4- 221- ~AI4554-E 00 1429 00 10 99 as1amp33--------shy71 1 00 304E

7f -5 L54E 00 1b691 00 00 99919653 -- - 4 20E - 00 00103000 99)796751

623 III - -- o4- 67 -00 1S06 00 00100000 9g4596698) 3f1 47 26151- 30 264308 00 99575698 00

5 T1 - 4430i6 30 266051 03 00 999896698

201 ITT f 17150amp 00 U 14F 00130000 9096643

I) l 0 30 b Is i ~ shy

2Cr - i )To- 3 501 03 5)9

IT--2 -zc -A IJfL- l)op~ O- z38453 0) 00 p4520

Figure A-14 Hydrazine Fuel Used To Correct Semimajor Axis and Eccentri6ity Histogram (Pounds)

INTERVA_ dUT NOMINAL -Cf FREO SUM

9999 VflQ220 9 2 238E-03 2 3 l2347E-03 247749-03 82999992 160799S56

~2- - -- 919485a29 a4 -5 32161-03 495485-03 71399994 310599823

3 7 6l9l5F-03 743225-03 64392996 $09954a8 Bq5 14322E-13 8609E-03 60297997 506399536

14 3 2) 90951-03 111451702 49893998 6t0199408 1i 4- 111451-22 12387E-02 47799997 65__59326

II1 a 1z~23626E12 1064E-02 38099095 43399353

I4 fit 2is 162031-02 17342E02 30400000 0 71237 I+fII is 734E-02 2eS999 83$0990912$ 16580E-02

IITI I9IE-02 [I- -- 21055e-02 22296E-02 1799992 9046

M 1 21051F-02 1997996 890)756 31111

JI211 I - IT 355Q 1529 99rit3vv53 ITT 21 2335-02 24774E-y2 12691995 92509824

IIII -2L--2l L -02 26013x-02 1169a900 4Jamp479S4amp 2 N 23 26013-02 27251E-02 0929999 946398633[171111

[ill 24 272 i 0 2QOF-02 OL200000 9S4299551

2 Zq77f-02 I lI111 i 1V167E-02 05263000 96$1113S40

ITT 11~l 21 30 65fl 3206F10Z (0000009 gl=3_

411 f~IjItl1 29 33451-IZ 3-0663F-O2 0133030000 971198126 4 Ill - 3 - 3amp6302 3S2s-02 04100000 9O-$30$0I4 shy

4 l IIIll 32 35 22S-2 37261-02 02303000 98$197953 32 376-02 333991-02 01933000 98509783)

a lTjJltlll 32 3q63 E12 40177F-02 01433000 9916Q7693 03 14 1111 - 33 4O67L-02 422116-02 02101000 Q~

7 9

I T7TITITIT1 M 2 334E-02 0 1300300o 90519Y5O0shy[f1IillItIllIll - 3 amp3354F-02 44593r-02 0090000 995097364

I -lIIjITIII - 37 45-32-02 4707OO-02 00703000 99749TZ53 I [ItllII1TT1ii 4 47070E-32 4R3095-02 10403000 997397156

IraftP14 H V- 10_0+ t Iff I IL-9I ltttlTilIt 42 454 r-3 2 507a6E-02 00303030 99157107 I lI llllIIIIT 3 A 075G-02 2Qz5[-04 130 9 7 5

i r7ITtTTTTITIrIXII i- -i- 3 2 53264e02 00403003 999096985 1 1 - 45 532641-32 0C200000 99)2953754ItlltnIill 54502E-32 I [llIIll~tZ1III8Il - A t50a-j3 55741-02 00123000 - 994396amp2a 111 llll7llII 557-21--02 S600E-0 0013000 99994765

FllltIllII1 564e0r-02I2 521102 00200000 9996n5655

I [fl11 t IIIII1rIn 1t1ll1 5) 0Q57-02 - US INF 00200000 99)99640

I 1 ~ 19 Ivo-lf~ shy

I32 22500 700 900 950 9T3

F1 2 421111-4 tt 3---tJ I ulltt 7

t 3 ) nj2- 2I~Q)2) 341730-)2 1553J40-22 -tlf501O0aiZS)2amp -9-15j 1 932ALIDt41-

Figure A215 Velocity Change Required to Correct Drift Rate Errors Histogram (KilometersSecond)

INTERVA_ dUT NOMINAL -Cf FREO SUM

9999 VflQ220 9 2 238E-03 2 3 l2347E-03 247749-03 82999992 160799S56

~2- - -- 919485a29 a4 -5 32161-03 495485-03 71399994 310599823

3 7 6l9l5F-03 743225-03 64392996 $09954a8 Bq5 14322E-13 8609E-03 60297997 506399536

14 3 2) 90951-03 111451702 49893998 6t0199408 1i 4- 111451-22 12387E-02 47799997 65__59326

II1 a 1z~23626E12 1064E-02 38099095 43399353

I4 fit 2is 162031-02 17342E02 30400000 0 71237 I+fII is 734E-02 2eS999 83$0990912$ 16580E-02

IITI I9IE-02 [I- -- 21055e-02 22296E-02 1799992 9046

M 1 21051F-02 1997996 890)756 31111

JI211 I - IT 355Q 1529 99rit3vv53 ITT 21 2335-02 24774E-y2 12691995 92509824

IIII -2L--2l L -02 26013x-02 1169a900 4Jamp479S4amp 2 N 23 26013-02 27251E-02 0929999 946398633[171111

[ill 24 272 i 0 2QOF-02 OL200000 9S4299551

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Figure A-16 Hydrazine Fuel Used To Correct Drift Rate Errors Histogram (Pounds)

INTERVAL W4T NOMINAL PCT Fq0G SUN

0400 32

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Figure A-17 Synchronous Orbit Eccentricity Histogram

APPENDIX B - SHADOW HISTORY CURVES

This appendix presents several plots of synchronous orbit shadow over a 5-year

mission For the node values used here the 72-minute constraint is violated

by both the umbra and penumbra shadow durations- Each figure is listed below

1 Shadow History for 99th Percenftile Low Argument ofPerigee and

a Node Angle 40 Degrees Below Nominal

2 Shadow History for 99th Percentile Low Argument of Perigee and

a Node Angle 50 Degrees Above Nominal

3 Shadow History for 99th Percentile High Argument of Perigee and

a Node Angle 40 Degrees Below Nominal

4 Shadow History for 99th Percentile High -Argument of Perigee and

a Node Angle S0 DegreesAbove Nominal

B-i

IUESHADOW HISTORY NOPE-ziv AOP-228

100

Ba

Ld

Ir

an

In 20shy

a 200 400 Goo 600 1100 1210 14o0 IG00 100

MISSION DAYS FROM AUG11977

Figure B-1 Shadow History for 99th Percentile Low Argument of Perigee and a Node Angle 40 Degrees Below Nominal

IUE SHADOW HISTORY NOVE-270 AOP-eee

rI

w 40

In k0o 4an Can 1100 -Iu10001a Mo la

MISSION DAYS FROM AUG11977

Figare B-2 Shadow History for 99th Percentile Low Argument of Perigee and a Node Angle 50 Degrees Above Nominal

UE SHADOW HISTORY NODE-lOG AOP-240

Bo-

W I p

80

aw C) so -

Ur 2o

0o

0 200 400 Goo Sao tOo0 1200 1400 160 Wge1oo

MISSION DAYS FROM AUG11977

Figure B-3 Shadow H~istory for 99th Percentile High Argument of Perigee and a Node Angle 40 Degrees Below Nominalshy

JUE SHADOW HISTORY NODE-270 AOP-210

Cp

C2 0

a 2o 400 Goo 6 1oo 1400 1600 coosos00o

MISSION DAYS FROM AUG 11977

Figure B-4 Shadow History for99th Percentile High Argument of Perigee and

a Node Angle 50 Degrees Above Nominal

APPENDIX C - TRACKING COVERAGE

This appendix presents tracking coverage for five apogee passages in the transshy

fer orbit and for each phase of the drift orbit up to station acquisition For all

tracking sites except GSFC and VILFRA a constant 5-degree elevation mask

was assumed For GSFC the mask for the NTTF 12-meter antenna (STDN

no 705) was used Two masks were used for the VILFRA tracking site In

the following figures the label VILFRA means the physical mask was used

the label VIL+10 means the physical mask plus 10 degrees was used The list

of figures follows

1 Tracking Coverage for First Apogee in Transfer Orbit

2 Tracking Coverage for Second Apogee in Tranfer Otbit

3- Tracking Coverage for Third Apogee in Transfer Orbit

4 Tracking Coverage for Fourth Apogee in Transfer Orbit

5 Tracking Coverage for Fifth Apogee in Transfer Orbit

6 -Tracking Coverage for Drift Orbit Phase 1

7 - TrackingCoverage for fDrift Orbit Phase 2

8- Tiacking Coverage for Drift Orbit Phase3

9i Tracking Coverage for First Day of Synchronous Orbit

C-I

P- PEFlGEE 4- APOGEE

P1 Al

VIL + 10 __

VILFRA -

SANTIAGO

BOSMAN QUITO ORORA L MERRITT

RF_HRNAII - --

GSFC FSCNSION

_ALASKA

00 20 60 i0 12WW00 40

TIME FROM EPOCH (HOURS)

Figure C-l Tracking Coverage for First Apogee in Transfer Orbit

___

A-APOGEEP2 A2VIL + 10 r= PPRGE VIL~l ___ P-PERIGEE-V ILFRA - 1_ _ - __ _

SANT I AGOI I BOSMAN QUITO-OBORAL

MERRITT HAI I I-- -

GSFC I ASCNSION -

RLASKA

1400 1600 1800 2000 200 2100 2600

TIME FROM EPOCH (HOURS)

Figure C-2 Tracking Coverage for Second Apogee in Transfer Orbit

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

APPENDIX B - SHADOW HISTORY CURVES

This appendix presents several plots of synchronous orbit shadow over a 5-year

mission For the node values used here the 72-minute constraint is violated

by both the umbra and penumbra shadow durations- Each figure is listed below

1 Shadow History for 99th Percenftile Low Argument ofPerigee and

a Node Angle 40 Degrees Below Nominal

2 Shadow History for 99th Percentile Low Argument of Perigee and

a Node Angle 50 Degrees Above Nominal

3 Shadow History for 99th Percentile High Argument of Perigee and

a Node Angle 40 Degrees Below Nominal

4 Shadow History for 99th Percentile High -Argument of Perigee and

a Node Angle S0 DegreesAbove Nominal

B-i

IUESHADOW HISTORY NOPE-ziv AOP-228

100

Ba

Ld

Ir

an

In 20shy

a 200 400 Goo 600 1100 1210 14o0 IG00 100

MISSION DAYS FROM AUG11977

Figure B-1 Shadow History for 99th Percentile Low Argument of Perigee and a Node Angle 40 Degrees Below Nominal

IUE SHADOW HISTORY NOVE-270 AOP-eee

rI

w 40

In k0o 4an Can 1100 -Iu10001a Mo la

MISSION DAYS FROM AUG11977

Figare B-2 Shadow History for 99th Percentile Low Argument of Perigee and a Node Angle 50 Degrees Above Nominal

UE SHADOW HISTORY NODE-lOG AOP-240

Bo-

W I p

80

aw C) so -

Ur 2o

0o

0 200 400 Goo Sao tOo0 1200 1400 160 Wge1oo

MISSION DAYS FROM AUG11977

Figure B-3 Shadow H~istory for 99th Percentile High Argument of Perigee and a Node Angle 40 Degrees Below Nominalshy

JUE SHADOW HISTORY NODE-270 AOP-210

Cp

C2 0

a 2o 400 Goo 6 1oo 1400 1600 coosos00o

MISSION DAYS FROM AUG 11977

Figure B-4 Shadow History for99th Percentile High Argument of Perigee and

a Node Angle 50 Degrees Above Nominal

APPENDIX C - TRACKING COVERAGE

This appendix presents tracking coverage for five apogee passages in the transshy

fer orbit and for each phase of the drift orbit up to station acquisition For all

tracking sites except GSFC and VILFRA a constant 5-degree elevation mask

was assumed For GSFC the mask for the NTTF 12-meter antenna (STDN

no 705) was used Two masks were used for the VILFRA tracking site In

the following figures the label VILFRA means the physical mask was used

the label VIL+10 means the physical mask plus 10 degrees was used The list

of figures follows

1 Tracking Coverage for First Apogee in Transfer Orbit

2 Tracking Coverage for Second Apogee in Tranfer Otbit

3- Tracking Coverage for Third Apogee in Transfer Orbit

4 Tracking Coverage for Fourth Apogee in Transfer Orbit

5 Tracking Coverage for Fifth Apogee in Transfer Orbit

6 -Tracking Coverage for Drift Orbit Phase 1

7 - TrackingCoverage for fDrift Orbit Phase 2

8- Tiacking Coverage for Drift Orbit Phase3

9i Tracking Coverage for First Day of Synchronous Orbit

C-I

P- PEFlGEE 4- APOGEE

P1 Al

VIL + 10 __

VILFRA -

SANTIAGO

BOSMAN QUITO ORORA L MERRITT

RF_HRNAII - --

GSFC FSCNSION

_ALASKA

00 20 60 i0 12WW00 40

TIME FROM EPOCH (HOURS)

Figure C-l Tracking Coverage for First Apogee in Transfer Orbit

___

A-APOGEEP2 A2VIL + 10 r= PPRGE VIL~l ___ P-PERIGEE-V ILFRA - 1_ _ - __ _

SANT I AGOI I BOSMAN QUITO-OBORAL

MERRITT HAI I I-- -

GSFC I ASCNSION -

RLASKA

1400 1600 1800 2000 200 2100 2600

TIME FROM EPOCH (HOURS)

Figure C-2 Tracking Coverage for Second Apogee in Transfer Orbit

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

IUESHADOW HISTORY NOPE-ziv AOP-228

100

Ba

Ld

Ir

an

In 20shy

a 200 400 Goo 600 1100 1210 14o0 IG00 100

MISSION DAYS FROM AUG11977

Figure B-1 Shadow History for 99th Percentile Low Argument of Perigee and a Node Angle 40 Degrees Below Nominal

IUE SHADOW HISTORY NOVE-270 AOP-eee

rI

w 40

In k0o 4an Can 1100 -Iu10001a Mo la

MISSION DAYS FROM AUG11977

Figare B-2 Shadow History for 99th Percentile Low Argument of Perigee and a Node Angle 50 Degrees Above Nominal

UE SHADOW HISTORY NODE-lOG AOP-240

Bo-

W I p

80

aw C) so -

Ur 2o

0o

0 200 400 Goo Sao tOo0 1200 1400 160 Wge1oo

MISSION DAYS FROM AUG11977

Figure B-3 Shadow H~istory for 99th Percentile High Argument of Perigee and a Node Angle 40 Degrees Below Nominalshy

JUE SHADOW HISTORY NODE-270 AOP-210

Cp

C2 0

a 2o 400 Goo 6 1oo 1400 1600 coosos00o

MISSION DAYS FROM AUG 11977

Figure B-4 Shadow History for99th Percentile High Argument of Perigee and

a Node Angle 50 Degrees Above Nominal

APPENDIX C - TRACKING COVERAGE

This appendix presents tracking coverage for five apogee passages in the transshy

fer orbit and for each phase of the drift orbit up to station acquisition For all

tracking sites except GSFC and VILFRA a constant 5-degree elevation mask

was assumed For GSFC the mask for the NTTF 12-meter antenna (STDN

no 705) was used Two masks were used for the VILFRA tracking site In

the following figures the label VILFRA means the physical mask was used

the label VIL+10 means the physical mask plus 10 degrees was used The list

of figures follows

1 Tracking Coverage for First Apogee in Transfer Orbit

2 Tracking Coverage for Second Apogee in Tranfer Otbit

3- Tracking Coverage for Third Apogee in Transfer Orbit

4 Tracking Coverage for Fourth Apogee in Transfer Orbit

5 Tracking Coverage for Fifth Apogee in Transfer Orbit

6 -Tracking Coverage for Drift Orbit Phase 1

7 - TrackingCoverage for fDrift Orbit Phase 2

8- Tiacking Coverage for Drift Orbit Phase3

9i Tracking Coverage for First Day of Synchronous Orbit

C-I

P- PEFlGEE 4- APOGEE

P1 Al

VIL + 10 __

VILFRA -

SANTIAGO

BOSMAN QUITO ORORA L MERRITT

RF_HRNAII - --

GSFC FSCNSION

_ALASKA

00 20 60 i0 12WW00 40

TIME FROM EPOCH (HOURS)

Figure C-l Tracking Coverage for First Apogee in Transfer Orbit

___

A-APOGEEP2 A2VIL + 10 r= PPRGE VIL~l ___ P-PERIGEE-V ILFRA - 1_ _ - __ _

SANT I AGOI I BOSMAN QUITO-OBORAL

MERRITT HAI I I-- -

GSFC I ASCNSION -

RLASKA

1400 1600 1800 2000 200 2100 2600

TIME FROM EPOCH (HOURS)

Figure C-2 Tracking Coverage for Second Apogee in Transfer Orbit

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

IUE SHADOW HISTORY NOVE-270 AOP-eee

rI

w 40

In k0o 4an Can 1100 -Iu10001a Mo la

MISSION DAYS FROM AUG11977

Figare B-2 Shadow History for 99th Percentile Low Argument of Perigee and a Node Angle 50 Degrees Above Nominal

UE SHADOW HISTORY NODE-lOG AOP-240

Bo-

W I p

80

aw C) so -

Ur 2o

0o

0 200 400 Goo Sao tOo0 1200 1400 160 Wge1oo

MISSION DAYS FROM AUG11977

Figure B-3 Shadow H~istory for 99th Percentile High Argument of Perigee and a Node Angle 40 Degrees Below Nominalshy

JUE SHADOW HISTORY NODE-270 AOP-210

Cp

C2 0

a 2o 400 Goo 6 1oo 1400 1600 coosos00o

MISSION DAYS FROM AUG 11977

Figure B-4 Shadow History for99th Percentile High Argument of Perigee and

a Node Angle 50 Degrees Above Nominal

APPENDIX C - TRACKING COVERAGE

This appendix presents tracking coverage for five apogee passages in the transshy

fer orbit and for each phase of the drift orbit up to station acquisition For all

tracking sites except GSFC and VILFRA a constant 5-degree elevation mask

was assumed For GSFC the mask for the NTTF 12-meter antenna (STDN

no 705) was used Two masks were used for the VILFRA tracking site In

the following figures the label VILFRA means the physical mask was used

the label VIL+10 means the physical mask plus 10 degrees was used The list

of figures follows

1 Tracking Coverage for First Apogee in Transfer Orbit

2 Tracking Coverage for Second Apogee in Tranfer Otbit

3- Tracking Coverage for Third Apogee in Transfer Orbit

4 Tracking Coverage for Fourth Apogee in Transfer Orbit

5 Tracking Coverage for Fifth Apogee in Transfer Orbit

6 -Tracking Coverage for Drift Orbit Phase 1

7 - TrackingCoverage for fDrift Orbit Phase 2

8- Tiacking Coverage for Drift Orbit Phase3

9i Tracking Coverage for First Day of Synchronous Orbit

C-I

P- PEFlGEE 4- APOGEE

P1 Al

VIL + 10 __

VILFRA -

SANTIAGO

BOSMAN QUITO ORORA L MERRITT

RF_HRNAII - --

GSFC FSCNSION

_ALASKA

00 20 60 i0 12WW00 40

TIME FROM EPOCH (HOURS)

Figure C-l Tracking Coverage for First Apogee in Transfer Orbit

___

A-APOGEEP2 A2VIL + 10 r= PPRGE VIL~l ___ P-PERIGEE-V ILFRA - 1_ _ - __ _

SANT I AGOI I BOSMAN QUITO-OBORAL

MERRITT HAI I I-- -

GSFC I ASCNSION -

RLASKA

1400 1600 1800 2000 200 2100 2600

TIME FROM EPOCH (HOURS)

Figure C-2 Tracking Coverage for Second Apogee in Transfer Orbit

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

UE SHADOW HISTORY NODE-lOG AOP-240

Bo-

W I p

80

aw C) so -

Ur 2o

0o

0 200 400 Goo Sao tOo0 1200 1400 160 Wge1oo

MISSION DAYS FROM AUG11977

Figure B-3 Shadow H~istory for 99th Percentile High Argument of Perigee and a Node Angle 40 Degrees Below Nominalshy

JUE SHADOW HISTORY NODE-270 AOP-210

Cp

C2 0

a 2o 400 Goo 6 1oo 1400 1600 coosos00o

MISSION DAYS FROM AUG 11977

Figure B-4 Shadow History for99th Percentile High Argument of Perigee and

a Node Angle 50 Degrees Above Nominal

APPENDIX C - TRACKING COVERAGE

This appendix presents tracking coverage for five apogee passages in the transshy

fer orbit and for each phase of the drift orbit up to station acquisition For all

tracking sites except GSFC and VILFRA a constant 5-degree elevation mask

was assumed For GSFC the mask for the NTTF 12-meter antenna (STDN

no 705) was used Two masks were used for the VILFRA tracking site In

the following figures the label VILFRA means the physical mask was used

the label VIL+10 means the physical mask plus 10 degrees was used The list

of figures follows

1 Tracking Coverage for First Apogee in Transfer Orbit

2 Tracking Coverage for Second Apogee in Tranfer Otbit

3- Tracking Coverage for Third Apogee in Transfer Orbit

4 Tracking Coverage for Fourth Apogee in Transfer Orbit

5 Tracking Coverage for Fifth Apogee in Transfer Orbit

6 -Tracking Coverage for Drift Orbit Phase 1

7 - TrackingCoverage for fDrift Orbit Phase 2

8- Tiacking Coverage for Drift Orbit Phase3

9i Tracking Coverage for First Day of Synchronous Orbit

C-I

P- PEFlGEE 4- APOGEE

P1 Al

VIL + 10 __

VILFRA -

SANTIAGO

BOSMAN QUITO ORORA L MERRITT

RF_HRNAII - --

GSFC FSCNSION

_ALASKA

00 20 60 i0 12WW00 40

TIME FROM EPOCH (HOURS)

Figure C-l Tracking Coverage for First Apogee in Transfer Orbit

___

A-APOGEEP2 A2VIL + 10 r= PPRGE VIL~l ___ P-PERIGEE-V ILFRA - 1_ _ - __ _

SANT I AGOI I BOSMAN QUITO-OBORAL

MERRITT HAI I I-- -

GSFC I ASCNSION -

RLASKA

1400 1600 1800 2000 200 2100 2600

TIME FROM EPOCH (HOURS)

Figure C-2 Tracking Coverage for Second Apogee in Transfer Orbit

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

JUE SHADOW HISTORY NODE-270 AOP-210

Cp

C2 0

a 2o 400 Goo 6 1oo 1400 1600 coosos00o

MISSION DAYS FROM AUG 11977

Figure B-4 Shadow History for99th Percentile High Argument of Perigee and

a Node Angle 50 Degrees Above Nominal

APPENDIX C - TRACKING COVERAGE

This appendix presents tracking coverage for five apogee passages in the transshy

fer orbit and for each phase of the drift orbit up to station acquisition For all

tracking sites except GSFC and VILFRA a constant 5-degree elevation mask

was assumed For GSFC the mask for the NTTF 12-meter antenna (STDN

no 705) was used Two masks were used for the VILFRA tracking site In

the following figures the label VILFRA means the physical mask was used

the label VIL+10 means the physical mask plus 10 degrees was used The list

of figures follows

1 Tracking Coverage for First Apogee in Transfer Orbit

2 Tracking Coverage for Second Apogee in Tranfer Otbit

3- Tracking Coverage for Third Apogee in Transfer Orbit

4 Tracking Coverage for Fourth Apogee in Transfer Orbit

5 Tracking Coverage for Fifth Apogee in Transfer Orbit

6 -Tracking Coverage for Drift Orbit Phase 1

7 - TrackingCoverage for fDrift Orbit Phase 2

8- Tiacking Coverage for Drift Orbit Phase3

9i Tracking Coverage for First Day of Synchronous Orbit

C-I

P- PEFlGEE 4- APOGEE

P1 Al

VIL + 10 __

VILFRA -

SANTIAGO

BOSMAN QUITO ORORA L MERRITT

RF_HRNAII - --

GSFC FSCNSION

_ALASKA

00 20 60 i0 12WW00 40

TIME FROM EPOCH (HOURS)

Figure C-l Tracking Coverage for First Apogee in Transfer Orbit

___

A-APOGEEP2 A2VIL + 10 r= PPRGE VIL~l ___ P-PERIGEE-V ILFRA - 1_ _ - __ _

SANT I AGOI I BOSMAN QUITO-OBORAL

MERRITT HAI I I-- -

GSFC I ASCNSION -

RLASKA

1400 1600 1800 2000 200 2100 2600

TIME FROM EPOCH (HOURS)

Figure C-2 Tracking Coverage for Second Apogee in Transfer Orbit

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

APPENDIX C - TRACKING COVERAGE

This appendix presents tracking coverage for five apogee passages in the transshy

fer orbit and for each phase of the drift orbit up to station acquisition For all

tracking sites except GSFC and VILFRA a constant 5-degree elevation mask

was assumed For GSFC the mask for the NTTF 12-meter antenna (STDN

no 705) was used Two masks were used for the VILFRA tracking site In

the following figures the label VILFRA means the physical mask was used

the label VIL+10 means the physical mask plus 10 degrees was used The list

of figures follows

1 Tracking Coverage for First Apogee in Transfer Orbit

2 Tracking Coverage for Second Apogee in Tranfer Otbit

3- Tracking Coverage for Third Apogee in Transfer Orbit

4 Tracking Coverage for Fourth Apogee in Transfer Orbit

5 Tracking Coverage for Fifth Apogee in Transfer Orbit

6 -Tracking Coverage for Drift Orbit Phase 1

7 - TrackingCoverage for fDrift Orbit Phase 2

8- Tiacking Coverage for Drift Orbit Phase3

9i Tracking Coverage for First Day of Synchronous Orbit

C-I

P- PEFlGEE 4- APOGEE

P1 Al

VIL + 10 __

VILFRA -

SANTIAGO

BOSMAN QUITO ORORA L MERRITT

RF_HRNAII - --

GSFC FSCNSION

_ALASKA

00 20 60 i0 12WW00 40

TIME FROM EPOCH (HOURS)

Figure C-l Tracking Coverage for First Apogee in Transfer Orbit

___

A-APOGEEP2 A2VIL + 10 r= PPRGE VIL~l ___ P-PERIGEE-V ILFRA - 1_ _ - __ _

SANT I AGOI I BOSMAN QUITO-OBORAL

MERRITT HAI I I-- -

GSFC I ASCNSION -

RLASKA

1400 1600 1800 2000 200 2100 2600

TIME FROM EPOCH (HOURS)

Figure C-2 Tracking Coverage for Second Apogee in Transfer Orbit

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

P- PEFlGEE 4- APOGEE

P1 Al

VIL + 10 __

VILFRA -

SANTIAGO

BOSMAN QUITO ORORA L MERRITT

RF_HRNAII - --

GSFC FSCNSION

_ALASKA

00 20 60 i0 12WW00 40

TIME FROM EPOCH (HOURS)

Figure C-l Tracking Coverage for First Apogee in Transfer Orbit

___

A-APOGEEP2 A2VIL + 10 r= PPRGE VIL~l ___ P-PERIGEE-V ILFRA - 1_ _ - __ _

SANT I AGOI I BOSMAN QUITO-OBORAL

MERRITT HAI I I-- -

GSFC I ASCNSION -

RLASKA

1400 1600 1800 2000 200 2100 2600

TIME FROM EPOCH (HOURS)

Figure C-2 Tracking Coverage for Second Apogee in Transfer Orbit

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

___

A-APOGEEP2 A2VIL + 10 r= PPRGE VIL~l ___ P-PERIGEE-V ILFRA - 1_ _ - __ _

SANT I AGOI I BOSMAN QUITO-OBORAL

MERRITT HAI I I-- -

GSFC I ASCNSION -

RLASKA

1400 1600 1800 2000 200 2100 2600

TIME FROM EPOCH (HOURS)

Figure C-2 Tracking Coverage for Second Apogee in Transfer Orbit

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

bullP3

VIL + 10

VILFRA

SRNTIPGO FOSMRN QUITO

MORL MERRITT

_

r _

I

_I==

-

A13

-

A-APOGEEP-PERIGEE

HRNPII GSFC ___

ASCNSION

ALRSKR I _1

28W0 300 3200 S40 3600

TIME FROM EPOCH (HOURS)

3800 tQO0

Figure 0 3 Tracking Coverage for Third Apogee in Transfer Orbit

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

IA-APOGEE P-PERIGEEA4P4

VIL + 10 VILFRR SFNTIRGO BOSMRN z QUITO R

=]URORRL MERRITT HRNRII I E_ -

GSFC

RSCNSION RLRSKR ___+

200W40 IW 10a 00 20 10

TIME FROM EPOCH (HOURS)

Figure C-4 Tracking Coverage for Fourth Apogee in Transfer Orbit

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

A-APOGEE

I5-PERIGEE

P5 AS IP =

VIL + 10 Ll -

VILFAR

SANTIRGI -ROSMW ----__ QUITO - _ -

OR RRL MERRITT RE-

HRWRII I-GSFC-ASCNSION

_

RLASKA - -

TIME FROM EPOCH (HOURS)

Figure C-5 Tracking Coverage for Fifth Apogee in Transfer Orbit

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

--

A-APOGEE

JP-PERIGEE

VIL + 1=10

VILFRF SANTIAGO

ROSMAN MQITO

MERRITT HAWAII 1I

GSFC

ABCNSION E ALASKA I I

000 iZ00 2400 36 m 40 0 eoo 7z oa50oo

TIME FROM EPOCH (HRS)

Figure C-6 Tracking Coverage for Drift Orbit Phase I

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

A-APOGEE P-PERIGEE

VIL + 10

VILFRA

SANTIAGO

ROSMAN

QUITO OHfIZUFIAL _

MERFRITT

HRIIFI

GSFC RSCNSIONt I II

AtLASKAF -= II E-

uno0 120 400 W0a 610 0000

TIME FROM EPOCH (HRS)

Figure C-7 Tracking Coverage for Drift Orbit Phase 2

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

A-APOGEE P-PERIGEE

VIL + 1l0 VILFHA - -

SANT IAGO ---ROSMAN

QUITO-

MORAL MERRI TT

HAAII

OSFC _

ASCNSION E-1

ALASKA

000 le0o 2400 3602 4o

TIME FROM EPOCH (HRS)

Figure 0-8 Tracking Coverage for Drift Orbit Phase 3

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

PERIGEE APOGEE PERIGEE

VIL + 10 VILFRR

SPNTIPGO

IOSMPN

QUITO

OHORPL MEBITT HAWAII GSFC

ASCNSION

ALASKA t 4

TIME FROM EPOCH (HRS)

Figure C-9 Trackdng Coverage for First Day of Synchronous Orbit

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

APPENDIX D-- LAUNCH WINDOW CONSTRAINT PARAMETER CONTOUR PLOTS

This appendix presents contour plots of the individual constraint parameters

used in defining the launch window Each figure is plotted in terms of parking

orbit node and launch date Contour angles are in degrees The figures are

1 Transfer Shadow Contours

2 Contours of Solar Aspect Angle at Third-Stage Ignition

(Transfer Orbit Injection)

3 Contours of Solar Aspect Angle at Fourth-Stage Ignition

(Apogee Boost Motor)

4 Contours of Minimum Separation Angle During 3 Hours

Prior to Apogee

5 Contours of Maximum Separation Angle During 3 Hours

Prior to Apogee

D-1

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

II

260

250

240

0

230

too

210

200 0 30 6 90 120 150 180 210 240 270 300 330 360

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-1 Transfet Shadow Contours (Minutes)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

260

250

240

230

2 2o 0

210 220

a __ CI

200 0 30 60 90 120 150 180 210 240

DAYS FROM STARTING DATE (JULY 201977)

270 300 330 360

C Figure D-2 Contours of Solar Aspect Angle at Third-StageIgnition (Transf6r Orbit Injection)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

260

250

240

iLI

00

=

2000

0 30 w 90 120 ISO IGO 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-3 Contours of Solar Aspect Angle at Fourth-Stage Ignition (Apogee Boost Motor)

330 360

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

260

250

240

CJ

0

210

2001 0 30 60 90 120 150 180 210 240 270 300

DAYS FROM STARTING DATE (JULY 20 1977)

Figure D-4 Contours of Minimum Separation Angle During i3 Hours Prior to Apogee

330 360

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

CR

0 2

300 330 360240 270180 220120 150

30 60 90 C

FROM STARTING DATE (JULY20 1977) DAYS

Contours of Maximum Separation Angle During 3 Hours Prior to Apogee

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

APPENDIX E - EVOLUTION OF ORBITAL ELEMENTS

The l apid Orbit Prediction (ROP) program was usea to compute the orbital evshy

olution assuming that no stationkeeping maneuvers were performed during the

mission The gravitational potential included the fields due to the Earth Moon

and Sun A 6 x 6 field was assumed for the Earth The figures are listed

below

1 Evolution of Semimajor Axis

2 Evolution of Eccentricity

3 Evolution of Inclination

4 Evolution of Node

5 Evolution of Argument of Perigee

6 Evolution of Groundtrack

E-1

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

42200

42180

0

-

42160

42140

42120

0 -24250 5I 9 1350 155 I

MISSION DAYS FROM JULY 30 1977

Figure E-1 Evolution of Semimajor Axis

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

02900 F

13 2860 -

I-I

C--

W 02740shy

02700 0

II 225 450 675 Boo 1125

MISSION DAYS FROM JULY 30 1977

Figure E-2 Evolution of Eccentricity

1350 1575 1oS

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

IL

265-

Ishy

-

255Q

250 --

245 0 225 450 675 900 pound125

MISSION DAYSFROM JULY 30 1977

Figure E-3 Evolution of Inclination

1350 1575 1800

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

230

218

170

O0 225 450 675 900 1125 1350 1575 1800

MISSION DAYS FROM JULY 301977

FigEure E-4 E-volution of Node

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

29

ltD O

27e0

LIl

(D 266

I~ LL

0 Ishy

254shy

z LI

E C 242

230

230 I I I I I I I -n 225- 450 S75 900 1125 1350 1575 1BOB

MISSION DAYS FROM JULY 30 1977

Figure E-5 Evolution of Argument of Perigee

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

ttj

I-EA INITIAL

16-77jamp4LIE165LiE~i A L Jt1 -1 65-150-135-12[31S-I -75 -- -45 -30 15 30 752) 90 [f5 120 135 150 16545 f15 too

Figure E-6 Evolution of Groundtrack (1 of 2)

C

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)

- - -

I II I F I I Il 1 ITI II I I I IItAI= l f ~ l

60 -f 0--ll l l ll l l -hl-l-- -n-ll-it- -l ll

0J 4 -1] 1- P 11 I I i i I 1TII 1 1 1 I 1]I i I NI I t1 l II 1 I

m II I I IF t l l Mll Ifl l l l ll l l i t l l l l ~

-li l l l l I lZl- Ii1IA kIL I Ir I I I I N III I

-1130-165-150-135-120-1053-M0 -75 -W -45 -30 -15 0 15 30 45 603 75 90] 10]5 IM L35 150 L65 1BG]

iueE-6 Evolution of Groiundtack (2 of 2)