NASA CONTRACTOR REPORT

W

u

NASA CR-61238

June 30, 1968

SUPER LOKl DART METEOROLOG ICAL ROCKET SYSTEM Prepared under Contract No. NAS 8-20797 by Bruce Bollermann and Robert L. Walker

SPACE DATA CORPORATION

Huntsville, Alabama

https://ntrs.nasa.gov/search.jsp?R=19680026183 2020-04-20T13:16:47+00:00Z

June 30, 1968 NASA CR-6 1238

SUPER LOKI DART METEOROLOGICAL ROCKET SYSTEM

(Final Report)

Bruce BollermaM and Robert L. Walker

Prepared under Contract No. NAS 8-20797 by

SPACE DATA CORPORATION Phoenix, Arizona

For

Aero-Astrodynamics Laboratory

1)istrit)ution of this report is provided in the i n t e r e s t of inlornmtion exchange. Responsihility for the contents rcsicles in the author or organization that prepared it.

N A S A - G E O R G C . M A R S H A L L S P A C E F L I G H T C E N T E R

FOREWORD

This document presents the results of work performed by the Space Data

Corporation, Phoenix, Arizona, i n support of the Aerospace Environment Division,

Aero-Astrodynamics Laboratory, Marshall Space Flight Center, Huntsville, Alabama,

under contract NAS8-20797.

Appreciation is given to Mr. Robert Turner of the above laboratory for his

support of this program and to the personnel of the White Sands Missile Range for

their cooperation in the init ial flight testing of the Super Loki Dart.

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1 . 2 . 3 . 4 . 5 . 6 . 7 . 8 . 9 . 10 .

TABLE OF C O N T E N T S

INTRODUCTION ............................................ 1

DEVELOPMENT PROGRAM .................................... 2

VEHICLE DESCRIPTION ....................................... 3

AERODY NAMl CS DATA ...................................... 18

VEHICLE PERFORMANCE ..................................... 24

RANGE SAFETY INFORMATION .............................. 36

VEHICLE ASSEMBLY. CHECKOUT AND LAUNCH PROCEDURES ... 41

DEVELOPMENT FLIGHT TEST RESULTS ......................... 49

HIGH ALTITUDE WIND PROFILE MEASUREMENT ................ 52

OTHER APPLICATIONS ....................................... 60

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L I S T OF I L L U S T R A T I O N S

FIGURE NO. TITLE PAGE

3.1

3.2

3.3

3.4

3.5

3.6

3.7

3.8

3.9

3.10

3.11

4.1

4.2

4.3

4.4

5.1

5.2

5.3

5.4

Super Loki Vehicle Configuration 4 *

High Altitude Super Loki Chaff Dart Vehicle Configuration 5 d

Super Loki - Loki Dart Vehicle Comparison 6

Super Loki - Rocket Motor Configuration 8

Cross-Section View of Rocket Motor 9

Super Loki Chaff Dart Configuration 10

Cross-Section View of Chaff Dart 1 1

Super Loki Launch Rail Assembly

Launch Rail on Typical Base

13

14 Y

Super Loki Chaff Dart C.G. vs Time 16

Chaff Dart Pitch Moment of Inertia vs Time 17

First Stage Normal Force Coefficient vs Mach No. 19

Dart Normal Force Coefficient vs Mach No. 20

First Stage Center of Pressure vs Mach No. 21

Dart Center of Pressure vs Mach No. 22

Dart AI titude vs Range (80° Q . E .) 25

Dart Altitude vs Time

Dart Velocity vs Time

26

27 %

L

Dart Altitude vs Range 28

I V

5.5

5.6

5.7

5.8

5.9

6.1

6.2

7.1

7.2

7.3

7.5

7.5

7.6

7.7

8.1

9.1

9.2

9.3

9.4

10.1

Dart Apgee Altitude and Impact Range vs Launch Apogee

Booster Nominal Trajectory 80 Q.E. Sea Level Launch

Booster AI titude vs Time, 80 Q. E. Sea Level Launch

Booster Apogee AI ti tude and 1 mpact Range vs Q . E. Super Loki Chaff Dart Roll Rate vs Time

Dart Wind Weighting Factor Sum vs Altitude

Booster Wind Weighting Factor Sum vs Altitude

Super Loki Dart System Components

Super Loki Vehicle Assembly

Init ial Launch Installation

Intermediate Launch lnsta lation (Forward View)

Intermediate Launch lnsta lation (Rear View)

Final Launch Installation

0

0

Dart Firing Line Connection

Super Loki Dart Flight Test Impact ('NSMR 80' Q .E .)

Chaff Fall Rate (Theoretical)

Typical Chaff Descent Profile (WSMR Flight Test Series)

Typical Chaff Fall Rate Profile for WSMR Flights

29

30

31

32

35

39

40

42

43

44

45

45

46

47

51

53

54

55

High Altitude Wind Data (WSMR) 56 Thru 59

Super Loki Instrumented Dart Nominal Trajectory (89 Sea Level Launch) 61

V

LIST O F TABLES

TABLE NO.

3.1

3.2

3.3

4.1

5.1

5.2

6.1

6.2

a. 1

10.1

TITLE PAGE

7

7

Vehicle Mass Properties 15

Drag Coefficient Data 23

Nominal Trajectory Summary (80 Q . E . Sea Level Launch) 33

- Super Loki Rocket Motor Design Characteristics

Super Loki Chaff Dart Design Characteristics

0

Trajectory Data (Computer Printouts) 34

Ordnance Data 37

I mpact Dispersion Data 38

Flight Test Summary

Dart Systems Comparison

50

62

vi

1. I NTRODUCJI ON

The Super Loki Dart Meteorological rocket system has been developed for NASA - Marshall Space Flight Center to obtain high-altitude (85 km) wind data with a low cost rocket vehicle and a radar-reflective chaff payload. The Super Loki Dart consists of a scale-up of the older Loki Dart system which has been i n use for many years to gather wind data to altitudes up to 65 km. The Super Loki Dart two-stage vehicle consists of a high-impulse solid-propellant rocket motor as the f i rs t stage, and a non-propulsive dart which contains the chaff payload as the sec- ond stage.

Altitudes as high as 125 km have been obtained wi th this vehicle system dur- ing the development flight tests at White Sands Missile Range. Altitudes to 113 km are expected for flights from sea level launch sites. A helical-rail launcher has been developed to inpart spin or roll to the vehicle prior to release i n order to minimize impact dispersion and associated range safety problem.

The basic Super Loki rocket motor can be used to propel larger diameter in- strumented dart systems to altitudes on the order of 85 k m to upgrade the atmospheric temperature profile measurements currently being conducted by the standard-size Loki.

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2. DEVELOPMENT PROGRAM

The Super Loki Dart vehicle has been designed as a low cost replacement for the Cajun Dart for high altitude wind measurements. The goal of the Super Loki system was to achieve an altitude of a t least 95 km at less than one-half the cost of the Cajun Dart. A further goal was versatility of the Super Loki rocket motor so that i t could be used to propel darts of various sizes containing various kinds of meteorologi ca I pay loads.

Design efforts were initiated during July 1967, and the first static firing of the rocket motor was conducted during November. Three additional static firings were conducted through January 1968 to verify the init ial results and ob- tain a reliability history. Al l static firings were completely successful and the results were repeatable.

A series of five development flight tests were conducted at the White Sands Missile Range during the months of April and May 1968. The three units which were radar tracked over apogee achieved altitudes of about 125 km. Late radar aquisition of the descending chaff cloud from a fourth unit permitted an es- timate of apogee altitude slightly over 125 km. A fifth unit was not tracked bv radar, and no estimate of performance could be made. The White Sands perfor- mance data indicated that the vehicle should be able to achieve altitudes of about 1 1 3 k m from sea level launch sites. Therefore, the design was frozen, and the remaining twenty units i n the contract were sent to Cape Kennedy for operation- al use. Complete range safety and performance documentation was supplied to conclude the current program.

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3. VEHI CLE DESCRIPTION

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3.1 General.

The Super Ldt i Dart as shown in Figure 3.1 i s a two-stage sounding vehicle consisting of a so'lid-propellant Super Loki rocket motor as the first stage and a non- propulsive dart containing the payload as the second stage. A dimensional sketch of the vehicle i s shown in Figure 3.2. This vehicle i s essentially a scaled-up ver- sion of the standard Loki Dart vehicle as indicated i n Figure 3.3.

3.2 Rocket Motor.

The Super Loki rocket motor consists of an aluminum case with an internal burning cast-in-the-case solid propellant. Major design characteristics of the rocket motor are presented in Table 3.1. An aluminum interstage coupling structure i s lo- cated at the head end of the rocket motor. The propellant fuel i s a polysulfide poly- mer and the oxidizer i s ammonium perchlorate. A photograph of the rocket motor is shown in Figure 3.4. The igniter consists of two parallel 1 watt/ 1 ampere no- fire squibs and an appropriate ignition charge. The igniter i s separable from the motor and i s installed at the launch site. A cross-section view of the Super Loki rocket motor wi th the igniter installed i s shown in Figure 3.5.

3.3 Dart.

The high altitude chaff dart as shown i n Figure 3.6 for the Super Loki system consists of a steel cylindrical body with a steel ogive and an aluminum tail piece. The cylindrical body contains the chaff payload which i s packaged into split steel staves. The ogive i s retained a t the forward end of body with shear-screws which are sheared during payload expulsion out from the forward end of the dart. The tail piece contains an electrically-actuated 145-second pyrotechnic time delay and a small payload ejection charge. Four steel f ins are roll-pinned into the dart tail for flight stability. The aft end of the dart tail i s boattailed to reduce aerodynamic drag and to be used to mate the dart to the booster. A cross-section view of the chaff dart i s shown in Figure 3.7. Major chaff dart characteristics are presented in Table 3.2.

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S U P E R L O K l V E H I C L E CONFIGURATION

FIGURE 3 . 1

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DART

E 3.2 /

HIGH ALTITUDE SUPER LOKl CHAFF D4RT VEHl CLE CONFIGURATION

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m m- 0 -

h

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0

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t-

L br

hl h i - c

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TABLE 3 .1

I . I

I L

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S U P E R LOKl ROCKET MOTOR DE SIGN CHARACTER1 S T I CS SUMMARY

Length (inches) Diameter (inches)

Weights: Inert Motor With lnterstage (kg) Propellant (kg) Total (kg)

Motor Mass Fraction Burning Time (seconds)

Chamber Pressure: Maximum (Atmospheres) Average (Atmospheres)

Thrust at Sea Level: Maximum (kg) Average (kg)

78 4

5.26 (11.6 Ib) 16.87 (37.2 lb) 22.14 (48.8 Ib)

0.76 2.0

100.02 (1470 PSlg) 83.69 (1 230 PSIg)

2608.20 (5750 Ib) 2018.52 (4450 Ib)

Total Impulse at Sea Level (nt-sec) 3.96 (8900 Ib-sec)

Specific Impulse at Sea Level 239

TABLE 3.2 SUPER LOKl CHAFF DART DESIGN CHARACTERISTICS

Length 122.33 cm (48.16 inches)

Diameter 4.13 cm (1.625 inches)

Weight

Payload Volume

6.12 kg (13.5 pounds)

491.61 cm3 (30 inches 3

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I S U P E R L O K I ROCKET MOTOR

FIGURE 3 . 4

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. I 1 -

I

p:

I- 0 O z c W

Y u

- 9 -

I SUPER L O K l CHAFF DART

F IGURE 3 . 6

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Y 0 2

QL w P,

v)

u,

3

0 3 w - > Z 0 - c

w v)

v) v)

V

0 e v

The payload consists of 0.0127 mm (0.5 mil) "SI'-band, aluminumized- mylar chaff.

3.4 Launcher Description.

The Super Loki Launcher consists of four helical rails which complete ap- proximately one-third of a revolution throughout the launch rail length. The launch rai l assembly as shown i n Figure 3.8 consists of six cast aluminum sections which are bo1 ted together to form a continuous 4.39 m (1 2 feet) long rai I assembly. The four internal rails are equally spaced and form four continuous helices throughout the 4.39 meter (12 feet) length. The edges of the rails are stepped to support the vehicle by the dart fins and the rocket motor nozzle ring. The outside diameter of the launch rail assembly i s 26.04 cm (10-1/4 inches).

The purpose of the launch rail i s to impart an 8.5 rps spin to the vehicle by constraining the dart fins to a helical path during their travel along the launch rails. The aft end of the motor travels for 4.39 meter (12 feet) prior to i t s release from the launcher.

The Super Loki Launch Rail Assembly can be mounted to any suitable laun- cher base by means of forward and aft mounting brackets. A launcher base specific- al ly designed for this rail as shown in Figure 3.9.

A pullaway umbilical harness i s provided with the launch rai l assembly to re- tract the dart firing l ine during first motion of the vehicle.

3.5 Vehicle Mass Properties.

The mass properties of the. Super Loki Dart Vehicle are presented i n Table 3.3. Vehicle center-of-gravity vs time i s presented in Figure 3.10. Vehicle pitch mo- ment of inertia vs time i s presented in Figure 3. l l.

- 1 2 -

S 0 .-

- 1 3 -

- 1 4 -

TABLE 3 . 3

.

SUPER L O K I DART VEHICLE MASS P R O P E R T t E S

Chaff Dart: Weight Center-of-G ravi ty

Pitch Moment of inertia

Booster: Loaded Weight Expended Weight Loaded Center-of-Gravity

Expended Center-of-Gravi fy

6.12 kg (13.50 Ib) 87.63 cm (34.5 inches) from

aft y d of dart 0.610 kg-m (0.450 sIug/ft2)

22.19 kg (48.93 Ib) 5.28 kg (11.63 Ib) 85.6 cm (33.70 inches) from

85.09 cm (33.50 inches) from aft end of motor

aft end of motor Load Pitch Moment of Inertia Expended Pitch Moment of Inertia

7.28 kg-,,;2 (5.37 slug/ft2) 3.08 kg-J(2.27 Sludft2)

Ve hi c I e: Launch Weight Burnout Weight Launch Center-of-Gravity

Burnout Center of Gravity

Launch Pitch Moment of Inertia Burnout Pitch Moment of Inertia

28.32 kg (62.43 Ib) 11.40 kg (25.13 Ib) 1 18.36 cm (46.6 inches) from

aft end of motor 173.74 cm (68.4 inches ) from

aft end of motor 20.42 kg-rr? (15.06 sIug/f?) 10.56 k g - 2 (7.79 slug/f?)

- 1 5-

I l l

I I I +.

I I

1 1 1

I I

---A- I I

--:t---

I

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4. A ~ O D Y NAMI c DATA

rfie aerodynamic data for the Super Loki Dart vehicle i s presented as follows:

Figure 4.1 CN,VS Mach No., First Stage

Figure 4.2 CN,VS Mach No., Dart

Figure 4.3

Figure 4-4

Cp vs Mach No., First Stage

Cp vs Mach No., Dart

The Super Loki Dart i s stable during two-stage propulsive flight at essentially a zero degree angle of attack. After dart separation at motor burnout, the dart coasts to apogee in a stable flight made at essentially a zero degree angle of attack in the sensible atmosphere. After rocket motor burnout and stage separation, the expended booster becomes unstable and tumbles. Eventually the booster descends in a flat spin to impact at a relatively slow rate of speed. The drag coefficients for the various stage configurations are presented in Table 4.1.

- 1 0-

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--+-

I

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+-

t I

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1 I

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T A B L E 4 .1

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DRAG C O E F F I C I E N T D A T A

Super Loki Dart Vehicle - Two Stages Reference Area 85.47 cn? (0.0920 f?)

CD - Mach No.

0 0.50 0.80 0.81 1.40 1.50 1.75 2.00 2.25 2.50 2.75 3.00 3.25 3.50 3.75 4.00 4.25 4 , s 4-75 5.00 5.25 5-50 5.75 6.00 7.00

0.400 0.420 0.430 0.930 0.930 0.880 0.770 0.682 0.620 0. n o 0.533 0.500 0.470 0.440 0.420 0.397 0.380 0.360 0.345 0.331 0.320 0.310 0.300 0.290 0.260

Dart - Coasting Reference Area 9.84 cn? (0.0107 f?) Stage Weight - 6.12 kg (13.50 Ib)

CD - Mach No.

0 0.90 1 .oo 1.50 1.75 2.00 2.25 2.50 2.75 3.00 3.50 4.00 4.50 5.00 6.00 7.00 8.00

0.350 0.350 0.576 0.576 0.489 0,432 0.393 0.365 0.345 0.329 0.308 0.294 0.284 0.277 0.277 0.262 0.262

Expended Booster - Unstable Stage Weight - 5.28 kg (1 1.63 Ib) Reference Area - 80.22 CIT? (0.0872

ft2)

CD - Mach No.

0 22.423 1 .OO 22.423 2.00 1 5.376 3.00 6.407 4.00 1.068 5.00 0.945

10.00 0.945

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5. VEHICLE PERFORMANCE

The nominal traiectory data for the Super Loki Dart launched from sea level altitudes i s presented i n the series of graphs as follows:

Figure 5.1 Altitude vs Range, 8 0 ° Q E , Dart

Figure 5.2 Altitude vs Time, 80° QE, Dart

Figure 5.3 Velocity vs Time, 80' QE Dart

Figure 5.4 Altitude vs Range, Various Q E ' s

Figure 5.5

Figure 5.6 Altitude vs Range, 80 QE, Booster

Apogee Altitude and Impact Range vs QE, Dart

0

Figure 5.7 Altitude vs Time, 80°QE, Booster

Figure 5.8 Apogee Altitude and Impact Range vs QE, Booster

A summary of the maior trajectory points for the Super Loki Dart vehicle i s presented i n Table 5.1. The nominal trajectory details are presented i n Table 5.2.

The dart trajectory i s based upon stable dart flight prior to and after stage separation. The booster trajectory i s based upon stable flight to the point of stage separation. After stage separation; the booster goes unstable and decelerates rap- idly to a slow velocity. The booster then descends rather slowly i n a flat spin.

The vehicle spin or rol l rate profile i s presented i n Figure 5.9. The vehicle i s launched from a helical-rail launcher which imparts a spin rate of 8.5 rps during launch. The booster and dart fins are canted to control the rol l rate during the boost and coast phases of flight.

3

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0 5 /o I 5 Y

- z / -

8 CL

- 2 8 -

- 2 9 -

9,000

7,000

6,000

0

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3,000

0

‘8 00

‘600

1400

600

400

200

Q, E. (D€GP&ES * ,I

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TABLE 5 . 1

N O M I N A L TRAJECTORY S U M M A R Y

SUPER L O K l DART, 80' Q.E.SEA LEVEL LA

Burnout Altitude (m)

Burnout Range (m)

Burnout Time (sec)

Apogee Altitude (m)

Apogee Range (m)

Apogee Time (sec)

Impact Range (m)

Impact Time (sec)

Boo6 ter

1577.6 45,176 ft)

298.1 m (978 ft)

2.1

231 8.9 m (7, 608 ft)

446.2 m (1,464 ft)

6.1

4-62.4 m (1,517 ft)

108

I E CH

Dart

1577.6 m (5,176 ft)

298.1 m (978 ft)

2.1

113.4 krn (372,000 ft)

41.8 km (137,000 ft)

6.1

83.8 krn (275,000 ft)

309

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TABLE 5 . 2

S U P E R L O K l DART T R A J E C T O R Y D A T A

C O M P U T E R PRINTOUTS ,

~ TWO OEGWEE OF FREEDOM - POINT MASS SIMULATION SPACE OATA CORP 1 -

RUN 1 SUPER L O K I = DAXT 11063 LB INERT # T 13.5 LH,l 5 / 8 D I A DART 80 DEG SEA LEVEL DRAG TABLES 3010 AND 4004

0.025 0 o G 9 2 80 0000 62.330 0.953

00100 1 5 0 0 0 O o C 1 3 1 0.000 0.000 1000.000

0 0 000 00000 0.000 10.000

250 130 370200 1.000 100.000

*+ OUTPUT uhiITS ** FEET SECONDS POUNDS(FORCE1 POUNDS(MASS1 DEGREES

-34. i-

T I V E A L T VEL RANGE M A C H 0 A h G THRUST D R A G MASS A C C / G V V E R T

0.0 o b 0 o b 0.0 0. 80.0 o b 0 62.3 -0.98 0 0.1 6 r 138 l b 0.1 2 2 . 79.8 2887. 0 61.1 47.13 136

0.3 63. 448 11. 0.4 2300 75.5 3041. 9 58.6 50.34 440 0.4 115. 6 1 9 2 1 . 0.6 455. 79.5 3277. 1 7 57.2 55.28 60Y

30 55.8 60.67 795 0.6 275. 1 0 1 5 5 c b 0.9 1216. 79b* 3797. 104 54.1 66.33 998

0.8 520. 1 4 9 1 96. 1.3 2604. 79.3 4367. 2 2 2 50.7 79.67 1465 '

1.0 867. 2059 161. 1.9 4914. 79.3 4879. 332 46.7 95.09 2023 1.1 1085. 2379 203. 2.1 6519. 79.3 5016. 3 8 8 & 4 r 5 1 0 1 r 8 2 2338 ' 1.2 1336, 2 7 2 1 250. 2.4 8465. 79.3 5154. 451 42 .6108r74 2674 1.3 1621. 3083 304. 2.8 1 0 7 7 7 . 7 9 0 2 5196r 524 40.1114.34 3029 1.4 1942r 3 4 6 3 364. 3.1 13472. 79.2 5238. 6 0 1 37.9120.23 3 4 0 3 l e 5 2302. 3864 432. 3.5 16588. 79.2 5277. 6 7 3 35.7126.75 3796 1.6 2702. 4 2 8 3 5080 3.9 20140. 79.2 5231, 757 33 .4131r89 4208 1.7 3145, 4728 592. 4.3 24219. 70.2 5350. 840 31r1142.08 4645 1.8 3633. 5 2 1 1 685. 4.7 28595. 79.2 5469. 9 2 3 2 8 r 8 1 5 4 r 6 1 5120 1.9 4168. 5662 786. 5.1 33684. 79.2 4312. 1005 26.7126.90 5562 2.0 4739. 5925 895. 5.4 36259. 79.2 1744. 1047 25.3 42.26 5821 2.1 5176. 5893 978. 5.4 35388. 79.2 o b 1 0 2 5 2 5 r l - 3 3 r 9 1 5789

0.2 27. 289 4. 0.3 99. 79.6 2927. 3 59.9 47.59 285

0.5 185. 808 34. 0.7 773. 7904 3513.

0.7 3Phb 1 2 4 2 71. 1.1 1815. 79.4 4082. 155 52.4 72 .94 1221

0.9 690. 1762 126. l e 6 3621, 79.3 4622. 281 48.7 87.00 1732

* + * * * * * + + X * + + + * + + * + * + + + ~ ~ ~ ~ * + * * ~ ~ ~ * ~ * ~ ~ ~ + * ~ * ~ * * ~ * u ~ % + ~ * ~ * ~ * ~ * * * * ~ ~ ~ ~ ~ ~ u ~ * * + * + ~ COAST STAGE A m 0.0107 M= 13.50 T l = + + i + + w T 2 a 1.0 N= 0

2 . 1 5320. 3.1 10976. 4.1 16411. 5.1 21666. 6.1 26773. 7.1 31756. 8.1 36634. 9.1 41421. 10.1 46131, 11.1 50774. 1 2 . 1 55358. 13.1 59888. 14.1 64369. 15.1 68805. 16.1 73197. 17.1 77550. 1801 81863. 19.1 86140. 20.1 90380. 21 .1 94585. 22 .1 98755. 23.1 102890. 24.1 106992. 25.1 111061r 26.1 115197. 27.1 119198. 28.1 123167. 29.1 127104. 30.1 131008. 31.1 134680. 3 2 . 1 138720r 33.1 142527. 34.1 1463021 35.1 150046r

5886 5637 5 4 3 7 5272 5136 5021 492 3 4839 4767 4704 4640 4590 4551 4507 4466 4427 4390 4354 4319 4 2 8 4 4250 4 2 1 7 4184 4152 4119 4087 4055 4023 3992 3960 3929 3898 3867 3 8 3 6

1005. 20R3. 3125. 4139. 5130. 6103.

8009 7062 b

8948 b 9879.

10806. 11727. 12646. 13561. 14474. 15386. 16296. 17205. 18113. 19021 19927. 20834. 21739. 22645. 23573 24478 25383. 26288. 27 192 28097. 29001. 29906 e 30810. 31714.

o b 1 0 3 o b 79 o b 62 00 49 o b 39 o b 3 1 o b 2 4 o b 19 o b 1 4 o b 11 o b 9 o b 7 o b 5 o b 4 o b 3 o b 2 o b 2 00 1 o b 1 o b 1 o b 0 o b 0 o b 0 o b 0 o b 0 o b 0 o b 0 o b 0 o b 0 o b 0 o b 0 o b 0 o b 0 o b 0

5 7 8 2 *

5537 5 3 3 9 5176 - 5041 4 9 2 7 4 8 30 4 7 4 6 4675 4612 4 5 > 6 4505 4458 4414 4372 4333 4295 4258 4 2 2 2 4 1 6 7

4 1 i 9 43b5 4052 . 4 u 1 8 3 4 8 3 3 9 5 3 3523 3 Q 8 8 3 8 5 6 3 6 2 4 3 7 9 2 3760 3728

4153 ,

T I M E

ORBITAL PARAMETERS

E A P OC 0 e 9 9 8 7 8 8 E 00 0 0 1 0 6 5 5 7 E OB 0025H070E 05 00220312E-01

APOGEE CGQDSTIONS

T I M E A L T R A W E A L T l K X ) R A h C E ( KM 1 0 0 1 5 4 5 5 4 E 03 0 0 3 7 1 8 9 1 E 06 0 0 1 3 7 4 1 6 E 0 6 0 0 1 1 3 3 5 2 E 03 0 0 4 1 8 8 4 6 E 02

I M P A C T COll lDITIONS

TIME A L T RANGE A L T t K M ) RAlLCE ( KM 1 00309004E 03 00000000E 00 01274891E 06 Oa000000E 00 Oo837871E 0 2

- 34.3-

urULJU J I U U U

b u r u

U A T A C i)i< c.‘

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. .

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- 34.4-

27u9 i 7

4 9

1: I 1 11 11 11 11 i l l i l i

'd

. . A A

A I . - i l ;1 i i A i i i i l A1 i l 11 11 11 11

-_

-34.5-

_ _ . . . .

- . . . .

-- ... ---- .......................................

.............. ._ . .

. . . . . . . . . . . . .

.. ~ -------._. _,--------- ............... - . . . . . . . . . . . . . . . . . . .

.- . . . . . . . . . . . . . .-

__-_- _-. ...... -_ _ _ ................... _. .......

. . . . . . _- .... - . . . . . . . . . . . - - . . -

.... ............ ...........

. . . -. ... - .. . . . . . . . . . . . . . . . .

... - ................ - .. - . . . . . . . . . .

-35-

6 . RANGE SAFETY DATA

Complete range safety documentation has previously been presented in Space Data Corporation's TM-309, and the results are summarized as follows:

Table 6.1 Ordnance Data

Table 6.2 I T a c t Dispersion Data

Figure 6.1 Dart Wind-Weighting Data

Figure 6.2 Booster Wind-Weighting Data

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Q

Q n

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-37-

TABLE 6 . 2

I M P A C T D I S P E R S I O N D A T A

Vehicle Stage Dart

80°QE Impact Range 83.8 km 1 (275,000 ft) I

I Maximum Three-Sigma 1 9,516 m

(31,220 ft) i Impact Dispersion Radius

Booster I 462 m (1,517 ft)

136 m (447 feet)

- 3 8 -

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. . ! . . . . _ 1 . . . . . . . . . . . ! : : : . .--:. . . .

N ’I Q? 1 4:

10 9

9

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5

4

3

2

.

.

7. VEHICLE ASSEMBLY, CHECKOUT AND LAUNCH PROCEDURES

The Super Loki Dart system i s supplied in three component parts shown i n Figure 7.1 , as follows:

1. Super Loki Rocket Igniter.

2. Super Loki Rocket Motor

3. Super Loki Chaff Dart

At the launch site the dart i s assembled to the rocket motor, the vehicle i s inserted into the launcher, the dart initiator leads are connected to the dart tail and the igniter i s installed i n the rocket motor. After a continuity check through the ig- niter and dart leads separately, the system i s ready to launch.

A step-by-step procedure for vehicle assembly, checkout and launch is pre- sented as follows:

1.

2.

3.

4.

5.

6 .

7.

Remove dart and rocket motor from shipping boxes.

Insert aft end of dart into forward end of rocket motor as shown i n Figure 7.2, assuring that anti-roll pin i n dart tail i s aligned with slot in motor headplate dart alignment cup.

Insert aft end of assembled vehicle into forward end of launch rails as shown i n Figure 7.3, and slide vehicle back until dart fins reach launch rails.

Align dart fins with the four launch rails as shown in Figure 7.4, so the booster fins wi l l be located between the rails as shown i n Figure 7.5.

Slide the vehicle completely back to the rear of the launcher as shown in Figure 7.6.

Assemble the dart firing leads to the dart tail by means of the respec- tive conr?ectors utilizing the pullaway harness shown in Figure 7.7.

Assemble igniter into aft end of rocket motor by screwing igniter base into rocket motor nozzle closure.

-41 -

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oc W a

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- 4 4 -

F I G U R E 7 . 4 L A U N C H I N S T A L L A T I O N - I N T E R M E D I A T E ( F O R W A R D V I E W )

I - F I G U R E 7 . 5 L A U N C H I N S T A L L A T I O N - I N T E R M E D I A T E (REAR V I E W )

ROCKET MOTOR F I N 1 (s:;;d 1-

/ ROCKET MOTOR BOURRELET

- 4 5 -

RAIL

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a. Perform continuity test of dart initiator through firing leads. Resistance should be within 0.80 to 1.30 ohms.

9 . Perform continuity test of igniter through firing leads connector positions C and D. Resistance should be within 0.50 to 0.70 ohms.

.

10. Vehicle i s now ready for launch, Provide at least 5.0 amperes to fire dart delay and 10.0 amperes to fire rocket motor igniter. Dart initiator ignition reliability wi l l be enhanced by supplying initiation current of 5.0 amperes at T-5 seconds (i.e., 5 seconds before rocket motor i s ignited)

- 4 a -

1

8. DEVELOPMENT FLIGHT TEST RESULTS

A series of five developmental flight tests of the Super Loki Dart were con- ducted at the White Sands Missile Range to prove out the vehicle system. As i s the custom at White Sands for Loki Dart type vehicles, the launch angles were not adjusted for wind effects, and a l l vehicles were launched at an azimuth setting of 344 degrees, even though surface level winds varied from 1.03 m/sec to 12.87 m/ sec ( 2 to 25 knots). Complete radar tracks were obtained for flights number 2, 4 and 5, and these agreed quite well with the theoretical trajectory. A late radar aquisition of the descending chaff payload for flight number 1 permitted an estimate of apogee altitude for this flight. N o radar data was obtained for flight number 3. A summary of the flight test results i s presented in Table 8.1. Since, after apogee, the radar tracks the descending chaff target rather than the vehicle, the vehicle inpact data had to be estimated from the apogee data.

A plot of the estimated dart impacts i s presented i n Figure 8.1. These impact displacements from the nominal include the full effect of the winds, since launcher adjustments were not made to compensate for wind effects.

At least four of the vehicles in this flight test series performed i n accordance with the theoretical trajectories and demonstrated impact dispersions within predic- ted values. Although the fifth vehicle was not tracked by radar, visual observation indicated a normd flight at least through the propulsive phase.

.

- 4 9 -

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350

300

250

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F/GURE 8.f

- 5 1 -

9. HIGH ALTITUDE WIND PROFILE MEASUREMENT

The Super Loki Dart payload consists of 0.0127mm (0.5 mil) thickness alumin- ized Mylar chaff. This chaff i s cut to " S " band radar dipole length which i s the same as full wavelength for the "C" band radar. Thus both " S " band and 'IC" band radars may be used for tracking. The advantage of this chaff, over other possible radar tar- gets, i s that i t has the lowest sectional density available for a radar target, and there- fore, results in the slowest fall rates for wind tracking.

L

As can be seen from the theoretical fall rate curves of Figure 9.1, the higher the apogee and ejection altitude, the faster the descent velocity i s at altitudes above 85 km. Wind shear measurement error i s a function of the square of the descent vel- ocity, therefore, i t i s important to obtain as slow a descent rate as possible through- out the altitude region of interest. Since the current program requires wind data for sea level launch sites from an altitude of 85 km to 65 km, the apogee altitude of the system should be about 90 km.

The developmental flight tests at the White Sands Missile Range (1219 m - 4,000 ft. launch elevation) were primarily to test vehicle performance and the apogee altitudes were too high for aptimum wind measurement. The sea level launches should result i n apogees close to the optimum for the stated measurement requirements.

Although the flights at White Sands were too high for optimum wind measure- ment, the data i s presented here as an example. The chaff descent profiles for the White Sands flights were quite similar and are represented by Figure 9.2. The match- ing fall rate profile as shown in Figure 9.3 indicates that maximum descent velocities of over 609.6 d s e c (2,000 fps) were obtained at an altitude of about 90 km.

The high altitude wind profiles derived from the Super Loki flights at White Sands are presented i n Figure 9.4. The wind profiles obtained from the High Energy Loki (apogee 85 km) and the regular Loki (apogee 65 km) chaff targets are also plotted for comparison purposes. From sea level launch sites wind data i s expected at higher altitudes with the Super Loki system since the vehicle apogee wi l l be low- er and the chaff descent rates not as great.

52

T H E O R E T I C A L F A L L RATE O F 0 . 5 m i l M Y L A R C H A F F ( 2 8 9 m/sec ( 9 5 0 fps) H O R I Z O N T A L V E L O C I T Y A T A P O G E E )

F I G U R E 9 . 1 -53-

-t

---I--- -+ I

B

8

~~~- ~

F I G U R E 9 . 3 T Y P I C A L C H A F F FALL RATE P R O F I L E FOR WSMR F L I G H T S

0 A

i

0 250

S U P E R L O K l # 4 - F A L L RATE v s A L T I T U D E 20 k y 1968

RATE OF D € J i T - M€7ieS PEPJ~OND ? 4w 6w

- 5 5 -

Z a v)

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3

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- 5 7 -

.

-58-

- 5 9 -

10. OTHER APPLICATIONS

The development of a two-inch (5.08 cm) diameter instrument dart for the Super Loki system i s proposed as a follow-on to the chaff dart system devel- opment to improve the altitude and measurement capability of current instrumen- ted systems. An 85 k m apogee i s achievable with the proposed instrumented dart system, and the payload volume i s more than double that of the current in- strumented dart systems. This increased volume can be used for additional sen- sors, a transponder/teIemetry sonde, and most important, an increased-size par- achute to obtain significantly slower descent rates of the sonde during the measure- ment period. Temperature and wind measurement errors of current systems are functions of the square of the descent velocity, and a significant improvement i n measurement accuracy can accrue by reducing the parachute descent rate. The cost of this instrumented dart system should not be significantly greater than the current instrumented dart systems.

The proposed Super Loki Instrumented Dart system consists of the Super Loki rocket motor and a two-inch diameter (5.08 cm) dart. The dart i s design- ed to contain a maximum diameter parachute to extend the altitude and improve the accuracy of wind and temperature measurements. Performance of this sys- tem i s as follows:

Launch Angle Dart Weight Apogee Altitude Apogee Range Apogee Time Burnout Velocity Maxi mum Ac ce I era ti on

8 5' 14 Ib (6.35 kg) 85 km 15 km 132 sec. Mach 5.4 102 g

A nomina trajectory i s plotted i n Figure 10.

The two-inch (5.08cm) diameter instrumented dart contains a payload vol- ume of 80 cubic inches (131 1.2 cm3). This i s more than twice the payload volume of the 1.437 inch diameter (3.65 cm) instrumented dart which i s currently being used. Either a 1680 mc/GMD-(x) or a 403 mc/SMQ-l sonde can be used with the proposed dart depending upon ground-station equipment. SDC i s currently manu- facturing both kinds of sondes for the USAF, PMR and WSMR and the Navy, res- pectively. Descent rates of the sonde system can be slowed to 230 fps (70.1 m/sec) at 61 k m with a Super Loki system (-& = 0.015 Ib/ft2), or 0.073 kg/m2. Ad- vantages of the Super Loki two-inch(5.08 cm) Instrumented Dart over the current Loki 1.437 (3.65 cm) inch Instrumented Dart are presented in Table 10.1.

.

- 6 0 -

SPACE DATA CORpoRATwlN C.ll*l.. Y I m

SUPER LOU1 INSTRUMENTED DART NOMINAL TRAJECTORY 8S0 S E A L E V E L L A U N C H

5 .44 KG ( 1 2 LB) /5 .08 CM (2.0001N) INSTRUMENTED DART

0 20 40 60 80 100 120 140 160 180 FLIGHT TIME - (SECONDS)

FIGURE 10.1

-61 - A- 1 675

TABLE 1 0 . 1

C O M P A R I S O N OF THE SUPER L O K l 5.08 C M INSTRUMENTED DART SYSTEM

WITH THE CURRENT 3 . 6 5 CM INSTRUMENTED DART SYSTEM

Apogee AI ti tude

Dart Diameter

Payload Volume

Payload Volume Available for Parach Ute

Parachute-Sonde Ballistic Coefficient, W/CdA

Descent Rate at 61 km

Dart Ablative Coating

Super Loki System

85 km

2.0 in (5.08 cm)

80 cu in. (131 1.2 cm3)

67 cu in. (1098.1 cm3)

0.073 kg/m2 (0.01 5 Ib/ft2)

70.1 m/sec (230 ft/sec)

Not Required

Standard Loki System

63 km

1.437 in (3.65 cm)

33 cu. in. (540.9 cm3)

20 cu in. (327.8 cm3)

0.146 kg/m 2

(0.030 I b/ft2)

2 100.6 d s e c (330 ft/sec)

Required

- 6 2 -

An inflatable falling sphere payload has been suggested by the Army personnel at White Sands Missile Range for use with the existing chaff dart design. Since altitudes of 125 km were obtained at White Sands, reasonably good density data may be derived with the Robin falling sphere payload to al- titudes below 90 km with the Super Loki . Since the apogee altitude for a sea level launch w i l l only be about 113 km, the falling sphere density data may be restricted to a maximum altitude of 85 km for sea level sites.

- 6 3 -

DISTRIBUTION

INTERNAL

R-DIR Mr . Weidner

R-AS -DIR

Mr. F. Williams

R-ASTR Dr . Haeus s ermann

R-P&VE Dr. Lucas

I-MO-MGR Dr. F. A. Speer

I-s/AA Mr. Leland F. Belew

MS-IL (8)

MS-IP

MS -H - R-COMP-R

Mr. R. J. Cochran Mr. Paul Harness

R-SSL-DIR Dr. Stuhlinger

R-AERO Dr. Geissler Mr . Jean Mr. W. Vaughan (5) Mr. 0. Smith (2) Mr. Kaufrnan Mr. Daniels Mr. Turner (25) Dr. L. DeVries Mr. S. C Brown Mr. D. Johnson

Mr. H. J. Horn Mr. W. K. D a h Mr. W. Murphree

R- EO-DIR Dr. W. Johnson

. R-SE-DIR Mr. L. Richards

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I -

I - i i

.

NASA Representative (25)

Scient i f ic & Technical Information

Box 33 College Park, Maryland

S-AK/RKT

Fac il i t y

National Aeronautics & Space Admin Washington, D. C. 20546 ATTN: Tech Library (2) Off ice of Advanced Res & Tech Off ice of Manned Space F l igh t

NASA-Manned Spacecraft Center 2101 Webster Seabrook Road Houston, Texas 77058 ATTN: Director

Mr. J. Eggelston M r . D. Wade M r . J. P. Mayer

NASA Langley Research Center Langley S ta t ion Hampton, Virginia 23365 ATTN: Director

M r . Tolefson Tech Library (2)

NASA John F. Kennedy Space Center Kennedy Space Center, Flor ida 32899 ATTN: M r . R. Clark

M r . A. Ta ian i M r s . Russel l , Tech Library

NASA Electronics Research Center Cambridge, Massachusetts 02142 ATI'N: Director

Tech Library

NASA Lewis Research Center 21000 Brookpark Road Cleveland, Ohio 44135 ATTN: M r . Jack E s t e s Technical Library

M r . J. Giraytys CODE: W 1 4 1 Chief, Requirements Branch U. S. Weather Bureau, ESSA S i lve r Spring, Md. 20910

M r . S. F. Kubinski CODE: AMSEL-BL-WS-S Atmospherics Science Off ice Atmospherics Sciences Lab. USA Electronics Command White Sands Missile Range, NM 88002

Lt./Col. W. D. K l e i s , S(=wT A i r Force Systems Command Andrews A i r Force Base Washington, D. C. 20331

Lt./Col. D. E. McPherson, SSaJ SSD S ta f f Meteorologist Hq. Space Systems Division A i r Force Systems Command Los Angeles A i r Force S ta t ion A i r Force Unit Post Off ice Los Angeles, Cal i fornia 90045

M r . R. Leviton (CRER) A i r Force Cambridge Research Lab. L. G. Hanscom Field Bedford, Mass. 01730

M r . V. S. Hardin (AWVAR) A i r Weather Service Scot t Weather Service Scot t AFB, Ill. 62225

M r . A. L. Miller CODE: AIR-5403 Naval A i r Systems Command Wahington, D. C. 20360

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M r . R. M. Fenn CODE: KXR U. S. Naval Weapons Laboratory Dahlgren, Va. 22448

M r . H. Demboski CODE: 421 Office of Naval Research Washington, D. C. 20360

Comd. F. F. Duggan, Jr., USN CODE: 70 Naval Weather Service Washington (Navy Yard Annex) Washington, D. C. 20390

M r . G. P. Tennyson, Jr. Meteorology & Sounding Branch Hq., National Aeronautics & Space

Administration, OSSA Washington, D.C. 20546

M r . Kenneth C. Steelman AMs EL -BL - E D U. S. Army Electronics Labs. For t Monmouth, New Jersey 07703

Commander, Sixth Weather Wing Andrews A i r Force Base Washington, D. C. 20331

Commander ( 2 ) A i r Weather Service (MATS) U. S. A i r Force Scot t A i r Force Base, I l l i n o i s

M r . Kenneth Nagler Spacefl ight Meteorology Group U. S. Department of Commerce Weather Bureau Washington, D. C. 20235

M r . Clyde D. Martin Technical Staff Rockwell Corp . 12214 Lakewood Boulevard Downey, Cal i fornia 90241

Dr- 0. Essenwanger, AMSMI-RRA U.S. Army Missile Command Redstone Arsenal, Alabama 35809

AMC Technical Library Redstone Arsenal, Alabama 35809

Meteorological & Geo-Astrophysical

P. 0. Box 1735 Washington, D. C. 20300

Abstracts

M r . Robert Walker (10) Space Data Corporation 2875 Sky Harbor Boulevard Su i t e 204 Phoenix, Arizona

M r . Bruce Bollermann (10) Space Data Corporation 2875 Sky Harbor Boulevard Su i t e 204 Phoenix, Arizona

M r . W i l l i a m C. Spreen, FM ( 3 ) National Aeronautics & Space Admin Off ice of Space Science & Application Washington, D. C. 20546

M r . Norman Sissenwine A i r Force Cambridge R e s Labs L. G. Hanscom Fie ld Bedford, Mass. 01730

62225 Maj. Ralph R. Ruyle, PGGW U. S. A i r Force A i r Proving Ground Center Eglin A i r Force Base, Flor ida 32542

M r . Lawrence B. Smith Sandia Corporation Sandia Base Albuquerque, N. Id. 87115

-66-

M r . C. J. Callahan, FC-3 Federal Coordinator Off ice U. S. Department of Commerce

Washington, D. C, 20235 ESSA

Mr. 0. H. Daniel CODE: MU 235, Bldg. 800 Pan American World Airways, Inc. A i r Force Western Test Range Pat r ick AFB, Fla. 32925

Lt./C61. mdd, USAB Det.11, 4th-Weather Group A i r Force Eastern T e s t Range Pa t r i ck AFB, Fla. 32925

M a j . G. L. Tucker, USAF CODE: WEA A i r Force F l igh t T e s t Center Edwards AFB, Calif . 93523

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Lt./Col. C. J. Loisel , USAF CODE: SMSW SAMs0 Los Angeles Unit Post Office Los Angeles, Cal i f . 90045

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National Aeronautics & Space Admin O f f i c e of Space Sciences & Appli Washington, D. C. 20546 A": Director

Dr . Tepper (3)

Mr. K, R. Jenkins AMSEL U. S. Axmy Electronics R&D Act iv i ty White Sands Missile Range, N.M. 88002

M r . Lee L. Sims USAERDAA Meteorology Department U. S. Army Electronic Proving Ground Fort Hauchuca, Arizona 85613

M r . J. F. Spurling Associate Member, MHG Inter-Range Instrumentation Geoup Meteorological Projects & Systems Range Engineering Division Wallops S ta t ion , NASA Wallops Is land, Virginia 23337

Major E. V. Von Gohren Aerospace Environmental Consultant Headquarters 6 th Weather Wing (MAC) Andrews A i r Force Base Washington, D. C. 20331

M r . W. L. Webb AMSEL-BL-WS Atmospheric Sciences Off ice Atmospheric Sciences Laboratory U.S.A. Electronic Command White Sands Missile Range, N.M. 88002

Lt/Col. J. G. Coblenz PGLW U. S. A i r Force A i r Proving Ground Center Eglin A i r Force Base, Flor ida 32542

-67-

M r . B. R. Hixon CODE: 3252. 30, Box 22 Pac i f i c Missi le Range Point Mugu, Cal i f . 93041

Capt. T. H. R. O ' N e i l l , USN Chief, Environmental Sciences Div. Off ice of Asst. Director, (RSCH) OSD/Dept of Defense Rsch & Engr Room 3C-128, Pentagon Washington, D. C. 20301

M r . C. A. Olson CODE: 7221 Sandia Corporation Albuquerque, N.M. 87115

M r . P. E. Carlson

Meteorology Division Dugway Proving Ground, Utah 84022

S TE DP -TO-M

M r . A. J. Krueger CODE: 602 Naval Weapons Center China Lake, Cal i fornia 93555

-68-