STS-51C Natonal Space Transportation Systems Promgram Mission Report

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JSC-20393

ri'....s 'p ( ) r ta i i ionSy l fems

Program Mission Report



JSC-20393

STS 51-C

NATIONAL SPACE TRANSPORTATION SYSTEMS PROGRAM

MISSI ON REPOR T

- - - - - - - - - - - - - - - - - ~ ~Michael A. Collins, Jr.

Manager, Shuttle Data

and Evaluation Office

A. D

Manager, Spa e Shuttle Projects

--~~-Z-~-'Glynn S. Lunney

nager, National STS Program



TABLE OF CONTENTS

Title Page

INTRODUCTION AND MISSION OBJECTIVES ••••••••••••• 1

MISS ION SUMMARY ••••••••••••••••••• • • •• 1

VEHICLE ASSESSMENT •

. . . . . . . . . . . . . . . . . . . . .3

3SOLID ROCK ET BOOSTER . . . . . . . . . . . . . . . . . . . . .EXTERNAL TANK • • • • • • • • • • • • • • • • • • • • • • •• 3

SPACE SHUTTLE MAIN ENGINE • • • • • • • • • • • • • • • • •• 3

]mproper Moding and Timing in BFS ••

TACAN 3 Failed to Lock Up During Entry

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

4

4

4

MAIN PROPULSION SYSTEM . . . . . . . . . . . . . . . . . . . .ORBITER . . . . . . . . . . . . . . . . . . . . . . . . . . .

. . . . • • • • • • • • 4

Radar Altimeter 2 Was Erratic At High Altitude •••••••• 4



IN TRODUC TION AN D MISSIO N OBJEC TIV ES

The STS 51~C National Space Transportation System Program Mission Report

contains a summary of the Orbiter, ET (external tank), SRB (solid rocket

booster), and SSME (Space Shuttle main engine)/MPS (main propulsion system)

systems operation for the fifteenth Space Shuttle mission, which was also

the third flight of the Orbiter vehicle, Discovery (OV-103). Because of

the security classification assigned to this mission, this report contains no

discussion of any of the mission activities or accomplishments.

Table I contains a partial sequence of events, including only those activitiesthat are unclassified. Additionally, this report contains a discussion of the

most significant Orbiter problems/anomalies. Table II is a listing of all

unclassified Orbiter problems/anomalies. Table III is the Marshall Space Flight

Center problem tracking list.

MISS ION SU MMARY

The STS 51-C mission was launched on January 24 , 1985, at 19:50:00 G.m.t.,

1 hour and 35 minutes into the 3-hour launch window. The flight was originallyscheduled to be launched on January 23, 1985, but because the expected cold

temperatures might cause ice formations on the vehicle, the launch was delayed

until January 24, 1985.

The crew for the STS S1-C mission were Thomas K. Mattingly, Capt., U.S. Navy,

Commander; Loren J. Shiver, Maj., U.S. Air Force, Pilot; Ellison S. Onizuka,

Maj., U.S. Air Force, and James F . Buchli, Maj., U.S. Air Force, Mission

Specialist; and Gary E. Payton, Maj., U.S. Air F orce, Payload Specialist.

The countdown phase was completed satisfactorily, however, two minor Orbiter

problems were noted during that period. The first occurred during the T-3 hour

hold and involved a force fight in the right inboard elevon actuator between



TABLE I. - STS SI-C SEQUENCE OF EVENT

Parameter

APU Activation (1)(2)

(3)

SRB HPU activation command (LH-Al)

MPS start command sequence (engine 3)

SRB ignition command from GPC (lift-off)

MPS throttle-down to 92-percent (engine 3)

MPS throttle-down to 65-percent (engine 3)

Maximum dynamic pressure

MPS throttle-up to 104-percent (engine 3)

SRB separation command from GPC

MPS throttle-down from 3g acceleration (engine 3)Main engine cutoff (MECO)

External tank separation

APUdeactivation (1)

(2)

(3)

Flight control system checkout APU 2 start

APU 2 shutdownAPU 3 activation

-----.--APU activation (1)

(2)

Ent ry In ter face

E nd bl ac ko ut

G .m .t ., h r:m in :s ec

024:19:45:08

024:19:45:09

024:19:45:10024:19:49:32.14

024:19:49:53.44

024:19:50:00

024:19:50:15.48

024:19:50:29.4

024:19:50:52

0 24 : 1 9: 5 1 : 0 1 .0 8

024:19:52:07

024:19:57:34.54024:19:58:32

024:19:58:49

024:20:06:15

024:20:06:17

024:20:06:14

026:22:15:02

026:22:20:20

027:20:11:03

027:20:39:29027:20:39:28

027:20:52:29

027:21:08:16



At external tank separation, the BFS (backup flight system) did notautomatically pro~eed to major mode 104. The crew performed the necessary

manual procedures, and the BFS operated satisfactorily until the deorbit

maneuver when the BFS time for deorbit maneuver ignition was 8 seconds late.

However, the BFS operated satisfactorily for entry.

The entry phase systems operations were satisfactory with the Orbiter landing on

runway 15 at Kennedy Space Center at 027:21:23:23 G.m.t. (4:23 p.m.e.s.t.) on

January 27, 1985 •. The rollout distance was 7352 ft. An inspection of the

Orbiter after landing showed the vehicle to be in excellent condition.

V EH IC LE A SS ES SM EN T

SOLID ROCKET BOOSTER

All SRB systems performed as expected. The SRB prelaunch countdown was nominal

with no problems noted. Performance of both SRM's (solid rocket motors) was

close to predicted values and well within the allowable envelopes.

The average head pressures during the first 20 seconds as well as the propellant

burn rates were approximately 1.0-percent below predicted values, thus resulting

in longer than predicted web and action times. Preliminary indications are that

the SRB separation occurred approximately 1.7 seconds later than predicted. The

SRB recovery system performed nominally, with both SRB's reported floating in

the normal manner.

EXTERNAL TANK

All ET systems performed as expected. There were no ET preflight or flight

anomalies. There was some ice/frost buildup observed as predicted, however,

the vehicle was clean at lift-off.



Improper Moding and Timing in BFS

The BFS did not automatically proceed to major mode 104 after ET separation.

The condition was nQted, and the crew manually made the mode change. The

criteria for the mode change is a 3.6 ft/sec velocity change after receiving the

ET separation indication. Assuming worst case timing and maximum acceleration

in the early porti6n of the separation maneuver, analysis indicates that the BFS

sensed only 3.5 of the required 3.6 ft/sec velocity change. For STS 51-E, nochange will be made to the software and the crew will be instructed to manually

proceed to the major mode 104, if the same problem recurs.

Also, the BF S TIG (ignition time) for the deorbit manuever was 8 seconds later

than the PASS (primary avionics software system). The TIG for the deorbit

maneuver ended on an even minute and the zero seconds were not entered by the

crew. As a result, the burn time for a previous maneuver which occurred 8

seconds after the even minute was still present in the register. The crew will

be instructed to enter all digits of maneuver times.

TACAN 3 Failed to Lock Up During Entry

During entry, TACAN 3 was operating in the search mode, but failed to lock up on

the selected ground station. Postflight tests at K ennedy Space Center revealed

r ed uc ed r ec ei ve r s en si ti vi ty .

Radar Altimeter 2 Was Erratic At High Altitude

During the descent phase, RA (radar altimeter) 2 did not lock on the ground

until the vehicle reached an altitude of 2300 feet. Normally, ground-lock

occurs at about 5000 feet. Between 2300 and 1400 feet, ground-lock was



TABLE 11.- JSC OV-I03 STS 51-C PROBLEM TRACKING UST

. . . ~ t " " ' ' ' ' ' ' ' ' ' ' ' f ' ' · · ' ' f . · · ++++++ · t ' ' 4 ' ' ' ' ' ' • • • • • • • • • • • • • • • • • • • • • , , • • , . + + , • • • • • • • • • • • • , • • • •JSC O V tl03 SIS 51+C PlO lL lM TRACKING LIST PE l 25, 1985

................. ,••••••,••••••••"•••••••t••••••••••••••••••••••••.•,••••"•••••••••,•••••,•••,•••••••••••,••••~ t t • • • • • • • • • • •

I NO . I TITLE I TIME , G .M .T . I COMMENTS I USP. HG a •

•t·••t . , • • • •t.I."tt ••••• ,., ••••••• t '. ~ f • • ' . + tt.t.t•••t t f . , . , • • , • • ' .f·.t '••••••.••~fl't ••••••••••• 't••, .

I

IJ. VERNON

I CAR 20POOI

I CLOSID

I02/20/85

I

I

MASS SPIC IN M ID tBODY INDICATED 11,200 PPM OR I P . corA

ABOUT 0.36 IIM IN . KPS PRESSURE DECAY TEST SHOWEDI CLOSED

N O LEAK . M rS PIESSURES N O R M A L DURIRG LAU llCH . I 02/20/85P RO BA BL E IN TE RF AC E S IA L LEAK A T G IlE QD ON 1J 12 T4 0

UMBILICAL.

1 lIGHT IIBOAID ELEYON C lW lNEL 4

SICO IDA lY DELTA PlISSUR I FORCE

FIGHT.

2 HE LIUM LEAK IN M ID tBODY FROM UNf

D OW II S OU RC E.

1 t NS TR UH lN TA TI ON F AIL U IE S

A APU 1 EIHAUST GAS TEM PIRA TUU 2

(Y 46 T0140 A) F AIL ED .

B SSHE 2 GIl2 O UT UT T EM PE RA TU RE

(Y 41 T1261 A) F AtL ED .

C MAIN BUS "B" FORWARD P O W E R COM+

TROLLER AHHETEI (Y76Cl076A ) VERY

IIOISY.

D IT Ul2 100 PDCIRT LIQ U ID LEVEL

POINT SIISO I (T4111718E) ERRATIC .

4 STS 41+D CARRYOVER :

A LEn OM S FU lL TOTAL Q UANTITY

(V 43 Q4331C ) FA IL ED .

PRELAUNCH

PRELAUNCH

LAUNCH

A PU S TA RT

LAUNCH

FLIGHT DA Y

LAUNCH

LAUNCH

STS 41D+8

fO RCE F IG HT CL EA RE D D URIN G P RE LA UN CH P RO FIL E.

SAME CHARR EL AND SAME AC TUA TOR HAD A P OICE

PIGHT PULAUIICB ON FIRST PLIGHT OFOV+103, JU T

IT CLIAR ID JUST PR IOR TO PRELAUNCH PROFILE .

RU ACTUATOR . CAUSE UNKNOW N.

READ OFF SCALE H IGH AND THEN FAILED LOW. SAME

M EASUREM ENT FAILED OFF SCALE LOW LAST FLIGHT 5

M IN UT ES IE fO RE T OU CH DO WN . S EN SO R W AS RE PL AC ED

PIIOR TO 51+C . REMOYED AND REPLACED .

CLOSURE

IN P RO CE SS

W . SCO TT

CA R 20POO4 ,

R E A D OFF SCALE HIGH A FEW MINUTES AFTER LIFTOFF. P . CorA

TRANSDUCER FAILE D. REM OVED AND REPLACED . . CA R 20F003

R EA D B ET WE EN 105 AND 155 A MP S F OR 1MINUTIS . R . ECUSQ UIZA

FU EL CE LL AND O TH ER F ORWAR D P OW ER C OR '1 'R OL LI R AM PS I

NORMAL. CAUSE URKROWN. FLY AS IS . I

I

READING WAS ERRATIC •. PROBABLE TRANSDUCEI , I. IGUSQ UIZA

PAILURE. I

I

ICLOSURE

I IN PROCESS,STOPPED AT INTERMEDIATE POSITION AFTER OMS.1 , J. HOOPER

SIM ILAR T O TH E LAST FLICHT W HEN PROBE ILECTRO NICS ' CA R 14F005

WERE REPLACED POSTFL IGHT. FLY AS IS . I



T AB LE 11.- J5C OV-I03 STS Sl-C PROB LEM TRACKING LIST

••••"••••t.~ ,.,••,••,•••,••+t+ ++ ++++++ t.~•••,•••'t +++++~++++++ ~ , _., •••JSC OYtl03 STS 51tC PROBLEM TRACKING L IST FEB 25. 1985

"'t••t., •••,••~ , ~ t " ' t ' t t " " f . " • • • •t...... ~..... ~ + ~ + + t ++ + + + + t + + + " t ' . _ • •• •• 't.+++..... +++. . . ~tt•••,......,••,••+ + + ~ ., NO. , TITLE , TIME. G.M. T • , COMMENTS , RESP. HeR.

f + + 4 , . , . t " l t t t ~ , . t• • • • " . , • • t . , • • . •tt+++++t·.~.++t·++"+~ •• "'.,." ••• + + + + + + + + + + + + + t + + . + + + " ' . ' . " " . " " " " " " " , I , " "

B RIGHT OMS FUEL TOTAL QUAlfTITY

( V4 3Q 53 31 C) F AI LE D.

C RIGHT OMS OXIDIZER TOTAL QUANTITY

(V 43 Q5 23 1C ) R EA D LO W.

5A BACKUP FLIGHT SYSTEM DID NOT PRO.

CEED TO MAJOR HODE 104 AFTER. E T

SEPARATION.

5B B ACK UP F LI GH T S YS TE M D EOR BI TIGNITION TIME WAS 8 SECONDS LATE.

6 AC I PHASES "A" A N D "B " L O W CURRENT

TRANSIENTS ON WCS FAN SEPARATOR 1.

7 O XY GE N T AN K 2 H EA TE R C ON TR OL

P RE SS UR E ( Y4 5P I2 10 A) F AI LE D

MOMENTARILY.

8 S TA R T RA CK ER . + Y AND . Z S HU TT ER

CLOSURES.

PRELAUNCH

STS+41D

PRELAUNCH

ST5.41D

LAUNCH

DEORBIT

FLIGHT DAY 2

FLIGHT DAY 2

FLIGHT DAY I,

2, AN D 3 (+Y)

FLIGHT DAY 3

(+Z)

FAILED PRIOR TO FIRST FLIGHT ON OV.I03 AND HAS

NEYER BEEN REPAIRED. FLY AS IS.

MEASUREMENT HAS HAD A SHALL ~EGATIVE SCALE

FACTOR ERROR. O F ABOUT 2% FULL SCALE FOR ALL

OV.I03 FLIGHTS. FLY AS IS.

CREW HODED MANUALLY. WORST+CASE TIMING DELAYS

WITH ACCELERATION VARIATIONS COULD CAUSE LOW

BFS SEPARATION VELOCITY INTEGRATION. CHANGE

INTEGRATION CONSTANT. FLY AS IS FOR 51.E.

BFS WAS OPERATIONAL FOR. ENTRY. CREW DID NOTENTER 00 SECONDS FOR DEORBIT TIG LEAVING

08 SECONDS FROM LAST ENTRY. CHIT J+I507.

S IM IL AR T O P RO BLE M ST S+ 5I A· 16 E XCE PT S IG NA TU RE

IS ALSO ON PHASE "B". NO IMPACT ON WCS OPERA.

TION. IN+FLIGHT TROUBLESHOOTING FOUND LOWCURRENT CORRELATED WITH OPERATION OF PANEL

LIGHTS. NO A CT IO N R EQ UI RE D.

READ OFF SCALE LOW FOR A MINUTE CAUSING AN

ONBOARD FSM. RETURNED TO NORMAL. SET LOW

LIMIT AT 500 PSI TO PREVENT ALARMS. CHIT J+1506.

T/S NO JOY. UNEXPLAINED ANOMALY. FLY AS IS.

TARGET SUPPRESS BIT WAS SET SEVERAL TIMES WITHOUT,

BRIGHT OBJECT SENSOR RESPONDING. CREW DID NOT ,

O PE N S HU TT ER S AND ST OPERATION CONTINUED. ST ,

tZ SHUTTER LATCHED UP LAST FLIGHT. SEE STS+51A+ ,

21. FOUND CONTAMINATION ON LIGHT SHADES. ,,

J . H OO PER

C AR 1 9F 01 3

J . H OO PE R

S . M UR RA Y

CLOSURE IN .

PROCESS

S . H UR RA YCLOSURE IN

PROCESS

R . E GU SQ UI ZA

CLOSED

02/20/85

T. DA VI ES

CLOSURE

I N P RO CE SS

I . S AU LI ET IS

CLOSURE

I N P RO CE SS



)

TABLE 11.- JSC OV-I03 STS 51-C PROBLEM TRACKING LIST

+ . ++ + t+ + t· + ++ ~. + ++ + ++ + ++ t +. + ++ + t+ + +· t ++ + . .~ . · +. .+t+~++++++~+~++t+ .. +t+t.++t ... ++tt·..t+.... ~.++t .. • .. ++.. . +++tt+t+••++++JSC OV+ 103 STS 5HC PROBLE~1 TRACKING L IST FEB 25. 1985

~+ ++t ~ .. .+ ++ 4. ~+ ++ ++ .t +. + .. .++++•• ·+++••••+++tt+~++t~~tt+++~+++++++t+·++·-+++++&.+,,+++++++++.·,'.f++t++t++++

, NO. , TITLE , TIME. G .M.T. , COMMENTS , RESP. MGR.~'t+-"+t+"++ .. +++.....+++tt ........ ++++.+.+1"t .. +-t++++++++++++++t+++++++tt+++++.+++t.,..+++++++ttt++tt+++ ...+t++ ..... ++t++++++tt++++f·

9 TACAN 3 DID NOT LOCK UP. ENTRY USED TACANS 1 A ND 2. KSC FOUND LOW RECEIVER , E.LATTIER

SENSITIVITY. R&R. " CAR 20F002, C LO SU RE

, IN PROCESS,GOUGE WAS ABOUT 5 FEET LONG, 3/8 INCH WIDE AND ,

1/4 INCH DEEP AND LOCATED OUTBOARD OF LEFT MAIN ,

LANDING GEAR DOOR. CAUSE UNKNOWN. TILE REPAIRED.,,JSC DATA ANALYSIS. INTERMITTENT GROUND LOCK FROM,

2300 TO 1400 FEET. T I s FOUND ~~RGINAL LOOP ,

SENSITIVITY ON FAR RANGE. R&R WITH RA 1. PLACEDSPARE IN RA 1.

10 THERMAL PROTECTION SYSTEM HAD A

LONG GOUGE UNDER THE LEFT WING.

11 R A DA R A L TI M ET E R 2 ERRATIC AT HIGH

ALTITUDE.

12 RIGHT OMS FUEL AND OXIDIZER

QUANTITY GAGES WENT TO ZERO DURING

ENTRY.

13 F OR WA RD R CS DI LEM MA D UR IN G D EO RBI T.

14 A C PH OTO FL OOD LIG HT F AI LE D.

15 FO RWA RD DA P P ANE L (C 3) R OT ATI ON

PULSE PITCH PBI LIGHT FAILED.

P R EP A RE n B Y :/ s /R J W

ROBERT J. WARn

LAUNCH

ENTRY

ENTRY FOUND FUSES BLOWN AND AN INTERNAL SHORT ON BOTH

BUSSES. TRACED TO TOTALIZER INPUT POWER

C IRC UIT RY. R &R TO TAL IZE R.

DEORBIT PREFLIGHT WAIVER DUE TO SLOW ACTIVATION OF AC

MOTOR VALVE MANIFOLD 4 OX PRELAUNCH. T I s

SNIFFED OX FUMES. R&R MANIFOLD 4 OX VALVE.

ON O RB IT FUSE BLOWN IN OLD FLOODLIGHT. SEE PROBLEMSTS+410+19. WILL USE NEW TWO+TUBE COLOR BALANCED,

FLORESCENT FLOODLIGHT ON STS 51+E AND SUBS. ,,,,,,,

ON O RB IT CREW REPORTED LIGHT FAILED BUT DAP MODE WORKED

PROPERLY. POSTFLIGHT TIS FOUND ACA 1 LlGlIT

CONTROL CIRCUIT INTERMITTENT. R&R WITH ACA FROM

OV+I02. SEE PROBLEM STS+41D429.

02/25/85

DATE

A P PR O VE D B Y :/ s /J E M

J OS EP H E . t lE CH EL AY

J. SMITH

CLOSURE

I N ~R OC ES S

D . R HO AD ES

C AR 2 0F 00 5

CLOSED02/20/85

J . H OO PER

C AR 2 0F 00 6

CLOSED

02/20/85

G . GR ,US H

CAR AC 9013

CLOSURE

I N P RO CE SS

D . Y EA TE SCLOSURE

I N P RO CE SS

R . B UR GD UF F

C AR 1 4F0 24

CLOSURE

I N P RO CE SS

02/25/85

DATE



TABLE 111.- MSFC ANOMALY AND FAILURE LIST

DATE: 02-27-85 PAG E 1 O f 1

N O . T I T L E6 M T

D: H: M C O M M E N T S

I'RWE[;T

C O . T A C T

co

1 f l > F T P D i s c h a r g e T 4 ! I I I P 4 ! ra t u r eFailure

2 Controller M F Y ServoactUitorSelf T e s t Failure

24:19:52

24: 19:54

M E - 2 ( 2 01 8 ) H P F T P d i s c h a r g e t e l p e r a - S SM [ture ( C h a n n e l B) d r i f t e d below ttle R. Bledsoe/EE21l o w e r l i . i t a t a p p r o x 1 . . tely 1 3 7seconds after 1f ftoff and becillee r r a t i c for the r e s t of the flight.

' F a i l u r e analysfs r e v e a ~ e d a c r a c k ofthe coax tube. S e n s o r has been re-p l a c e d . A d e s i g n p r o c e s s · change w i lbe tncorporated on a later flight fo.this sensor. Controller s o f t w a r ed i s q u a l i f i e s a fatled s e n s o r .C L O S E D for S T S - S 1 E

M E - Z controller ( F 9 ) fafled M F V S S M (servoactuator self test { C h a n n e l 8 1 R. 8ledsoe/EE2}I t a p } r o x t. a te 1 y 3 3 1 seconds a f t e rl f f t o f f . Controller h a s been r e -t u r n e d to Honeywell f o r testfng.The probltll WIS isolated to In fn-temfttent h a n g up of a DG 140 solidstate swttch. N o other flilures ofthfs nature have been o b s e r v e d i n t~.,fstory of the S S t I : progr... T M sprobletn fs considered a randOM

piece p a r t faflure. C L O S E D

)

IlASA-JSC

STS-51C Natonal Space Transportation Systems Promgram Mission Report

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