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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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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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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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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
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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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t
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-1 I
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Fig. 18. Command subsystem
r. -I
I1
-I--IIII1L
Fig. 19. Command format
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I
'1 I ! I
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TO
(33&1)
Fig, 36. Heliummagnetometer subsystem
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\
0nlrr)
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I-
a
a
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. ,1 9 O C T 1967
TIME, GM T
Fig. 53. Encounter velocities andaltitude
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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
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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
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