mariner v handbook

8/7/2019 Mariner v Handbook

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Table 15. Assembly level environmental test requirements

l es t TA test level FA test level

Bench handling

Drop test

Transportationvibration

ExpI sive

Humidity

atmosphere

Shock

Static

V ibration

acceleration

Sinusoidal(allassemblies)Sinusoidal(asse nbl es

210 IbRandom noise

Vacuu n/ tern-perature

Thermalshock(for externalassemblies)

Free-fall corner drop

Height variable to weigh!

1.3 g peak, 2-35 Hs3.0 g peak, 35-48 Hz5.0 g peak, 48-50 Hz

he 1 and .iir during assembly

75% humidity a n i varied

Five 20r)-g, 0.7 kO.2 ms TPST

+14 g, 3 axes

operation

temperature

pulses, 3 axes

5 min

-c 1.5 in., 1--':' Hz3g peak, 4.4-15 Hz 3 min

2.0 g rms sine, 15-40 Hr"9.0 g rms sine, 40-250 Hzb

4.5 g rms sine, 250-2000 H t16.4 g rms noise, shaped

600

spectrum 180 s

- 0C ( + 14F) 4 h+750C (+ 167F) 12 days

lo-' torr+750 to -46C (167" o -50F)

Not applicable

I

Not applicable

I.7 g rms noise,shaped spec-trum, 60 s0C 320F1,2 h55C (131F),

torr

Not applicable

40

Game for assemblies < l o Ib.

b9.0 g rms sine, 40-2000 Hz for assemblies < l o !b.

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c.-E

&

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L

.-v)cQ)

S.cI.-

M

h

E.-E

8.-0E

E

2

00

t

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2n5

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Table 17. Subsystem environmental test summaryivibrationand thermal-vacuum)

-

Problem

Environment

Spacecraft Spacecraft

(backup) (flight)67-1 67-2

Failurerate, yoIotalfailuresIotal itemsI in test

TA testsV ibration 21 4 19

Vacuum/temperature 22 7 32

FA tests

Vacuum/ tempe ra u e 51 5 6.2

Vibration 117 7 6.5

Table 18. System leve l environmental tes t summary

Failure that should have been detected

Failure that could be detected only at

at subsystem level 2

systems level 4

Ta b k 19. Spacecraft tests

A t JPL I A t RFETRSubsystem testsSubsystem interface tests

System tests

Attitude colltrol quantitative leak

Electrical modal survey

test

Space simulator test

Vibration test

Weight and center-of-gravitymeasurement

Sys ern tests

SpacecraftIAgena adaptermatchmate

Electrical test

RF loop calibration

Dummy run countdowri

Umbilical release test

Weight and center-af-gravity

Cooling test

measurement

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Table 19. (Contd)

Channel

~

A t JPL A t AFElR1

Calibration rangeMeasurement (nominal)

Free mode t es t

Magnetic mapping

Joint f l ght-acceptance compositetests

Science instrument calibrations

Agend/spacecraft interface tes t Magnetic mapping

Launch countdown dummy run

Space Flight Operations/

Spacecraft /Agena matchmaie

Final system test

spacecraft/Deep Space Final electrical testsNetwork compatibility test Spacecraft post-matchmate

System tests Simulated launch

Current loop test checkout

Table 20. launch environmental telemetry channel assignment

Launch spacecraft - Agena telemetry

1213

15(44)

16 (17)

16 (18)

17

18

F

Spacecraft V- ba d strain gage 1Spacecraft V-band strain gage 2

Shroud separation monitor 0-28V

Shroud pressure &15 psia

Spacecraft-Agen? temperature 0-165 *F

0-2700 Ib0-2700 Ib

Spacecraft axial vibration t 2 0 g

Adapter axial vibration +30 g

JPL base band~~ ~~~~ ~

Launch complex environmental acoustic instrumentation

1 Umbilicalboom microphone 1 150 dS

2 Umbilicalbtjom micruyhone 2 150 dB

3 Umbilical bcom microphone 3 150 dB

4 UmbilicalbGom misrophone 4 150 dB

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106


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.-CI.-

*Em

c,

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L

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a

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0 - 2Y

hd

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CD03

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=?

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d m - 0 0( V N NZ f l d

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ILL0

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110


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L L L L LL L L LL0 0 0 0 0

L L L0 0

5hm

m +

0

-=r.*

". 09m oN

111


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ILL L L L L0 0 0

0

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m

v)3,

m

m

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c9

L L - i L L0 0 0

L0 0

LL0

W h 0 0 0 5N N N Nd b d b

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I& L L L L LL LL0 0 0 0 0

L

5:EQJmL=

m

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11 3


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114


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Table 23. List of commands

Command address

Binary OctalCommand name

ommand- umbert

DC-Vi

DC-V2

DC-V3

DGV4

DC-V5

DC-V6

DC-V7DC-VS

DGV9

DC-VI0

DC-V11

DC-V12

DC-V13

DC-V14

DC-Y15

DC-VI6

DC-V17DC-Vl8

DGVl9

DGV20

DC-V21

DC-V22

Command TLMmode 1Command TLMmode 2,

Track change command

Command TLMmode 4

Command switch data rate

Command switchADC/PNG

Switch power amplifierSwitch exciters

Switch ranging

Transmit high-receive low

Transmit high-receive high

Transmit low-receive low

Maneuver command inhibit

inhibit prop command(turn on Canopus s5nsor

and attitt-de control

Remove maneuver inhibitRemove prop inhibit(resets DC-Vl3)

turn on science

Canopus gate inhibit override

Start encounter backup clock

Cycle Canopus cone angleGyros on-inertial control

Gyros off-normal control

(2nd-roll positive tncrement)

(resets DG-V15,DC-V18,&DC-V20)

Remove roilcontrol

110 000 011 00

110011011 10

110 101011 00

110 011 10100110@00 0. VI

110 000 1111w

110 ~ 1 0 0 1 0 0'IO 110 101 10110 110011 10

110 110 00000

110 101 11000

110 101 10100

!10 010 111 00

110 010 10000

110 001 100 OG

110 101000 23

110 010 00100

110 100 loll 00

I10 100 010 00

110 111 10000

Rolloverride-negative increment

110 111010 00Aiitenna pointing angle change I10 111 001 00

6 030

6 332

6 530

6 50

6 50

6 060

6 1106 652

6 632

6 600

6 560

6 550

E270

6 240

&140

6 500

6 210

6 440

6 420

6 740

6 7206 710

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numberBinary-

DC-V23DC-V24

UC-V25

D C W 6

i)c-v27DGV28

DGV29QC-VI

QC-V1-1

QC-V13QC-V13

Octal

Arm second prop maneuverBegin DASencounter mode

(switch to data mode3)(pltanet sensor power on)(switch plasma probe to

Science on/overload inh ibit

Begin encounter sequence(tape recorder power on)(energize terminator sensor)(batterv charger to boost

mode 3)

override

-11ode)

Tlirli if science

mode)(battery charger to boost

h it iz te midcourse maneuverh i t c h battery charger

(tape recorder electronics off)Arm first prop maneuverManeuver command bitsto CC&S(Pitch turn duration)(Roilturr!duration)(Motor burn duration)

110 001 111 00

110 100 001 00

I10 010 010 00

111) 011 110 00110 10011100

110 110 110 10110 001010 00

110 011000 11-10110 01 1000 00-01110011 000 10-11

6 170

6 10

6 20

6 3606 70

6 6626 120

6 303-26 00-16 302-3

Table 24. Descriptionof cammands-Command Effect

~~

DC-V! Tiansfers the data encoder to mode 1 operation (all engineer-ing words) as soon as the transfer i s acceptable to the dataencoder transfer logic.

DC-V2 Transfers the data encoder to mode 2 operation (20 engineer-ing words, 40 science words) as soon as the transfer is ac-ceptable t o the data encoder transfer logic; applies2.4-kHzpower to the science instruments.


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Table 24. (Cont'd)

Command Effect

DC-V3

DGV4

DC-V5

DC-V6

DC-V7

DC-V8

DC-V9

DC-VI0

DC-VI1

DC-VI2

DEV13

DC-V14

Switches tape recorder data tracks (playback only).

Transfers the data encoder to mode 4/1 opGration (recordeddata or rsal-time engineering data) as soon as the transfer i sacceptable to the data encoder transfer logic. (If recordeddata are available from the ta::f : -o rder, recorded dataare telemetered; if no recorded data ave ; W S C R ~ (at end o ftapes), then engineering data in mode 1 (ire teizmetered.)Stops tape recorder record mode if in operation.

Transfers the data encoder from one bit rate to the other.The data encoder can operate at either 8-1/3 51 33-1/3 bps.

Transfers the data encoder from one (ADC/PNG) to the other.The data encoder has two ADC/PNi;s, A and B.

Transfers the radio from one power amplifiertr, the other. Theradio subsystem has two power amplifiers, A (traielingwave tube) and B (cavity).

Changes the radio from one exciter t o the other. The adiosubsystem has two exciters, A and B.

Turns the spacecraft radio ranging receiver either on 0 : 3ff.

Causes the radio subsystem circu!ator switches to he condi-tioned so that the spacecraft transmits via the high-gainantenna and receives via the low-gain antenna.

Causes the radio stlbsystem circulator switches to be condi-tioned so that ++e sbscecraft transmits and receives via thehigh-gain antenna.

itches to be comb-tioned so that the spacecraft transm;'ts and receives via thelow-gain antema.

Removes the attitude control excitation power fromCCSS con-trol lines so that the attitude control functions that arecontrolled by the CC&S are disabled. DC-V13 also preventsthe pyrotechnics control circuitry fromfiring the motorstart and stop squibs.

Reverses the state of all the relays acted cpon by DC-V13.DC-Vl4,therefore, is a reset for DC-Y13 and reverts theatti+:,de control and pyrotechcics subsvttems back to CC&SI n trol.

Causes the radio subsystem circulator

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Table 24. (Contd)

Cornmanti I SffectDC-Y15

DC-V16

DC-VI7

DC-VI8

DGV19DC-V20

DC-V21

cc-v22

DC-V23

DC-V24

Causes the Canopus sensor roll error signal to be apolieci to

the roll gas jet electronics a t a l l times, regardless o fwhether or not the roll acquisition logic is satisfied, andalso prevents the roll search signal from being applied tothe roll channel, and roli acquisition logic violations fromturningon the gyros.

Toggles DAS Timer A. Used to issue backup commandsforthe encounter sequence.

Causes a step change in the Cznopus sensor cone angle by

changing the voltage on the deflection plcltes o6 theCanopus sensors imbge dis:ector.

Turns on the gyros (ir; the inertial mode) and the Canopussznsor sun shutter and turns off the Canop!: sinsor.DC-V18 also turns on the turn cmmand generator andconditions the attitude control circuitryfor commzndedral! turns. Each succesive DC-V18causes positive rollrota!ion of 2.25 deg.

Serves as the reset fr>iDC-Vl5, DC-V18, andCS-?20.Turns off the Canopus sensor and turns on the Canopus

sensor sun shctter; alsc irlhibiis the roll acquisition logicfrom turningon t!v gyros.

Simulates a Canopus acquisition logic violation, turnson thcgyros, and applies a negative roll search signal to the .oilgas jet electronics, thereby causing the spacecraft tocounterclockwise roll search to acquire a new target. Eachscv-ssive DC-V21 willzlso cause the spcecraft to rollh r , i 2.25 deg if preceded by a DC-V18

Commands py:o to activate a pinpuller that allows theantenna to change position for opiimizingfh 2 S-band oc-cu lt awn experiment.

Sets relays in the pyrotechnics subsysterr so that CC&S com-mands M-6 and M-7 are routed to the squibs allottedt othe second motor burn.

Begins DAS encounter mode. Enable DAS timer E? (toggle).Switch tn :,A mode 3; planet sensor power on; .:witchplasma p x 4 2, to encounter forrnak.


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.

Command Effect

GC-V25

DC-V26

DC-V27

D C - V ~ ~

DC-v29

QC-Vl-1

QC-VI-2

QC-V1 3

Begins encounter sequence. Applies power to the termir?t?rsensor and io the tape recorder. Enables the batterycharger booFt mode arid rer oves Dooster regulator @velload inhibit.

Removes 2.4-kHz power from all the science lo-4s !taperecorder 2.4-kHz power rewsins 0-l; also enables thebattery charger boost mode.

starts the maiieuver sequence hy issuing the CC&ScommandM-1 (turn on gyros), by appiying power LO the maneuverclock, and by removing the mailewer clamp anda flip-flopreszt signal from the CC&S maneuver circuitry.

Transfers the battery chsrger from the charge m o ' io theb:iost enable mode or vice versa. Turns off 2.4-kHzpowerto the tape recorder.

Sets relays in thz pyroiech, :s subsystem so that the CC&Sccirnrnands M-6 and M-73re rocted to ti? - 3 2 1 s allottedto the firs t no to r burn.

Sets pitch turn polarity and preloadsthe'G3

pitch shiftrggister so that a t a counting rate of 1 pps the registerwill fill in the required time interval for the attitudecontrol subsystem t o pitch tu, nthe spacecraft the amountrequired for 2 given rn:dcourse maneuver.

Sets roll turn polarity and preloads the CC&S roll shiftregister so that a t a counting rate of 1 pps the reqisterwil!fill in the required time interval for the attitude con-trol subsystem to rLIl turn the spacecro?t the m t u n t

required for a given midcourse maneuver.Preloads tho CC&S velocity shift register so that a t a

count'ng rate of ?O pps the register v d l fiil ill ttic timcinterval necessary for the midcourse motorfo burn so thatthe spacecraft obtains thr required velocity change fora gi+en midcourse maneuver.

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Table 25 . CC&Scommands

command No.CCtS I Function and purposeL-l

L-2

L-3

M-1

M-2

w3

M4

M-5

M-6

M-7

MT-1

M-f-2

M i 3

MTQ

MT-5

MT-6

MT-7

MT-8

MT-9

Deploy solar panels. Gackup for separatioii initiated timer.

Turn on attitude control. Backupfor pyro araing switch.

Turn on Canopus sensor.

Turn on gyros for warmup. Maneuver star t command. IfCC&S commaodL-3has failed to operate, the automaticresetting of M-1 after the maneuver will turn theCanopus sensor off. This condition can be corrected bysending DC-V13after completiono f the maneuver.

All axes to inertial control. Places all three gyros inposition mode and places gas jet system under com-mand of gyro position errors. Turnsoff Canopus sensor.Turns on atitopilot,

Set turn polarity.

Command X axis (pitch) turn.

Command Z axis (roll) tuin.

Start motor burn.

Stop motor burn.

Set Campus sensor cone angle 1.

Se t Canopus sensor cone angle 2.

Set Canopus sensor cone angle 3.

Set Canopus sensor cone angle 4.

Transmit high-receive low.

Switch to 8-113 bps.

Turn on tape recorder power. Start terminator sensor

Begin DASencounter sequence.

Switch to mode4.

excitation.

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Table 25. (Csnt'd)

C C l S Icommand No.

Function and purpose

CY-1 Fc4owing DC-V9, switches ranging receiveroff; failure

switching to backup transmitter and switching ofantennas.

NOTE: In the case of interfaces with the attitude control subsystem, the CC&Scloses or interrtpts a circuit supplied by attitude control. Duration ofthe circuit closure or interruption depends on the fdnction to be per-formed. CC&S commands L-2, L-3, and MT-1 through MT-4 are permanentchanges in the circuit state. CC&S commands M-1 through M-5 requireresetting after controlled periods.

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FIGURES


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0 0

_ - .---o = 0

0 0

U loI

PL. - I,

127


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130


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UJznw2Ka 0I t

B Ea GI;'

d

* o - +

0I 4 \,

' 0

I

0

'u0-Pal iWK

0

131


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(D(D00

WcmL

0 )U00e:0 )

132


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**

P

WVIVIm

*

E

133


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40

-WKN-

0

0

0

0 I-

MuC0

.-L

134


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U

135


147/210

5mEv)v)a

\

wF-:

0 0 01 0I

L' 0 0 0 0 0 O J

E

13 6


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d

D O 0 0 0 0 0

137


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ui

bbG

138


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MT-l *E-56.4 d q r

MT-2-E-39.7 davr

MT-3-43.0 d a y s

II

II

II

I

d-125 -lw -75 -50 -25 0 25 50 75 100

i ME FROM ENCOUNTER, dmys

Fig. 7. Canopus sensor cone angle update

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L I I I I IA '2 MlnO MOSNX H l t l V 3

c

- 0 -

-

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TIME FROM LAUNCH,days

Fig. 13. Bus temperatures vs time from launch

Fig. 14. Sunlit component temperaturesvs time from launch

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Fig. 15. Shaded component temperaturesvs time from launch

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7

I I

151


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t

I

-D

Q

10 00 -

I

i m I

I I

0 0 0 02 2 f2

- 0

wn

>0

- 2

Lo

I-V

- 0

LD

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-1 I

15 3


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Fig. 18. Command subsystem

r. -I

I1

-I--IIII1L

Fig. 19. Command format

15 4


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I

'1 I ! I

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TO

(33&1)

Fig, 36. Heliummagnetometer subsystem

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\

0nlrr)

>>t

193


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I-

a

a

4 2 60

. ,1 9 O C T 1967

TIME, GM T

Fig. 53. Encounter velocities andaltitude

195


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ION #

* D

ATMI

........

QUAD ........... i;................................................

-.-j....

t"SUN

ATMF= final ohzervation of atmospheric effect on S-band signalATMI = in it ia l observation of atmospheric effect on S-band signa!

BL = bright limb of planet observed by ultr ovio let photometer

CO = center of geometrical occultation

DL = dark limb of planet observed by u ltr avi ole t photometer..E = periapsis

GO = Geometrical occultation; earth- spee craf t li ne of sight intersectsdark limb of planet

IONF = fin al detection of ionosphere by dual frequency receiver

ION1 = in it ia l detection of ionosphere by dual frequency receiver

LOS = loss of spacecraft radio signal resulting from occultation

ROS = reacquisition of signal by Goldstone DSCCQUAD= quadrature; sun-Venus-Mariner V angle 90 deg

TER= terminator crossing observed by ultraviolet photometer

XGO = ex it from geometrical occultatio n at bright l imb

fig. 54. Time and position of key encounter events

196


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4

2

102

6

4

2

IO'

r6090 61 00 61 IO 6120 6130 614C

DISTANCE FROM PLANET CENTER,R, km

Fig. 55. Refractivityas a function of height in the Venus atmosphere

19 7


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mariner v handbook

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