sts-9 national space transportation system program mission report

8/7/2019 STS-9 National Space Transportation System Program Mission Report

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I O W . SPACE T R ~ ~ P OR ?AT I OWSYST

MISSION REPORT

nager, Shuttle Rataand Evaluatlon Of f ic e

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~ V ~ D 0 ~ ~Be JOHNSON SPACE CENTER

MOUSTOM, TEXAS 77058

January 1984



. .

I ~ T R O D U E T I ~ ~AND MISSION OBJECTIVES

The STS-9 Nat iona l Space T r~nspor t a t i onSystems Program Mission Report contains a summary

e n t s o f t h i s f i r s t S pac ela b m i s si o n u s in g O r b i t e r

t i o n d i ff e re n c e s i n co r po r a r i o r t o STS-9 d nc lu de t h e f i r s t use o f t h e 3 substack fuelce)11s, t h e use o f 5 c ry0 t anks sets and t he add i t i on o f d g a l l e y and crew sleep stat ions.These d i f feren ces cmbfne d wi th t he Spacelab pay load res ul te d i n the heavl'ast landing

This rep ort als o summarizes the problems th a t occurred, as well asp r o v i d in g a p ro bl em t r a c k i n g l i s t o f a l l s i g n i f i c a n t a no ma lfe s t h a t o c c ur re d d u r in g t h em i ss i on.

The p rim a ry o b j ec t iv e o f t h i s f l i g h t(VFT's) o f Spacetab as an operat fanalr em a in in g t i m e l i n e c o n s t r a j n t s t o c on

The as-flwn time1 e f o r t h e STS-9 Space lab f l i gh t i s shown i nthe repor t . The s ue nce o f e v e nt s f o r t h i s STS-9 f l i g h t i s sh i n t a b l e I. Theproblem track 1ng 1 t s f o r th e launch vehicle , Orb iter , and Spa

table 11, al so a t t h e b ack of t he repor t.

This r e p o r t w i l l conta in on ly a br ie f summary o f t h e s c i e n t i f i c r e s u l t s with th e George

j o r a c t i v i t i e s and ace02. The ve hic le on th e STS-5 missfon. The s ign i f icant conf igura-

fght yet f lown.

success fu l l y conduc t ve r i f i ca t i on f l i g h t t e s t sn t o f the Space Transpo r tat ion System and wi t h i normal s c ie n t i f i c Spacelab operations.

gure 1 at the back of

ab a r e c o n ta i ne d i n

rshal l Space F l ight Center publ ish ing a more deta i led evaluat ion of each exper iment .

f 1i g h t o f t he E u r ~ ~ @ ~ ~ ~ ~ p ~ ~ ~ - ~ ~ @ ~ ~b dIt Space1ab,3, a t ~ ~ : 5 ~ : ~ ~ ' ~ ~ ~G.m. t c (l(O:59:59 91 a.mu ec5.t.) f r oma, and landed a t Edwards Mr Force sc?, Cal i far f i ia , onm. P.s*t. This F1Jqht ws l a n the most nor t he rnU. S. m m e d flight, The 6- ew Co r this Spacelab

oaauts and two non-foreign person t

oung, ~ ~ ~ ~

.ParkerB Phd.,

t ~ h ~ R ~ e r ~ ~PRd., a d U l f ~ ~ r b o ~ d ,Phd. Payload Sp ec ia lis ts .w ided in t o two teams, red and b lue , @ n a b i i ~ gtwo 12-hour workmax im iz ing t he sc ien t i f l c da ta ga ther ing from t h e 73 exper i -

This m d e o f o p e ra ti o n was very successful as i nd i ca ted by th evast amount o f s c i e n t i f l c d a ta c o l l e c t e d a nd t h e s u cc e ss fu l c p l e t i o n o f a l l 94 plannedf l i g h t t e s t o b j e c t i v e s .

#o 1aunch c m f t c r i t e r la

n m i n a l w i t h the vehfcle heilng f nse r

Spacelab ~ c t i w ~ ~ i a ~was f ~ i t i a t ~ ~on time and a l l x p e p l m @ ~ tsystems operatethus caus ing no $ ~ ~ t ~ h ~ ~ ~ rt o backup systems. On appnren t ly teapera t ure- re1 ated problemoccurred i n th e ~ e ~ Q t @a c q u i s i ti o n u n i t (RWU) 21. Th s u n i t 5ewes a l l NAo n t h e p a l l e t a nd th e h o r i ~ o nsensor. Ana lys is du r in t h e m iss ion sugges t

en t h e f r e s n f l u f d t ~ ~ ~ r ~ t u ~ eand the MU 1 pPoblerPi, ~ U ~ S ~ ~ t l ~

h t ~ ~ @ r n t u r ~ sabout 22" E r e s u l t e d i n problem-free ~ ~ ~ a t i ~ n .

nts on board Spacelab.

r e v i o l a t e d and o n l y t ~ ominor p rab lms occur red dur f ng t he; ~ ~ e v @ r ~net ther had any ac t on leunch operations. %e ascent phase was

i n t o 3 135 mb. c i r c u l a r o rb i t , as p lanned .

1



LE 1.- STS-9 SEQUENCE OF EWENTS

/

Event

&percent th r u s t (engine 3)

OMS-2 cu to f f

Actual

332:15:55:09332:15:59:32.6332: 15: 59: 53.4332:15:59:59.991332: 16:OO: 28.2

332: 16:OI :OL . 3332: 16 :02: 06.99322: 16~07:27,2332:16:08:29.195

332: 16:08:47332:16:10:29.4332: 16:11:33.2332: 16:13: 12332:16:40:37.4

332:20:31334:Oa :1 1335 :02: 30339:H8:25

332: 16 :00:51 e 4

3 3 m ~ ~ : i a . g

342: 22:46:5%1342:22: 52: 00.2342:22 :54:36.5

~ 4 2 : 2 3 : ~ a : 3 $842:23:59: 18.7

2



S f g n i f i c a n t 1t f e sciences Findings included:

t l o n s o f i nc re a se d r e l i a n c e up on v i s i o n f o r o r i e n t a t i o n i n space;p r o v o c a t ~ v @testfng ~ ~ ~ @ a r sp

c. E a r l y and s ign i f i can t adap ta t Jon f o r ss d i s c r i m i n a t ~ o nobserved;d. Fungus mainta ined c i rc adi an growth cyc le i n mfcrogra v i ty ;e, I n t e res t ing ca lo r l c nys tagmus resu l t s ; andf. Successfu l per formance o f o n-o rb i t phase of experiments dependent on po st f l ig ht

base l i ne da ta co l l ec t f on .

t f a l f o r S tu dy o f space adaptation syndrome;

S ign i f i can t mate r ia l s sc ience f i nd ings inc luded :

a. Successful ver io n o f mater ia l sc ience doub le rack ac t i v i t i es ;b. F i r s t s i l i c o n m r y s t a l growth i n space;C. C o n f ~ ~ a t ~ Q no ngoni convect ion ef fe c t i n space; andd. Sug gestive re s n f l u i d p h ys ic s.

The G m n d a r and P i l o t , who spen t t he i r sh i f t s on t he f l i gh t deck suppor t i ng Space lab

operat ions, also exposed about 9000 f r a B o f f i l m i n a u ~ - t~ ~ - w i n d o wphotographic act-t i v i t ies .

l e t i o n o f planned and extended Spacelab ac t i v i t i e s , the Spacelab wasd stowage p r @ p ~ ~ ~ t ~ o n ~wwe begun f o r entry.

lanned landing t ime, GBC (general

~~~~~ B w n fo r the r e s t o f the mdssfon.er , GPC-2 also failed. A t t m p t s t o b r f n g

ted t h a t mimy ~ ~ ~ ~ r ~ ~ iRad occurred,

f th e deorbit ~ ~ e u v @ rwhich was

s@ a t 342:23:47:24 G.m.t. The ro l loutrequ i red 8,456 feet .

out 6 1/2 m in ute s a f t e r l a ~ $ i n g *NU-X because of an underspeedt u r e t y s h u t down because ofu t 11 ~ i ~ u ~ ~ sa f t e r t~~~~

a

4



The degr-.e o f achiev n t o f s c i e n t i f i c o b j e c t iv e s i s e vi de n ce o f a s u cc e ss fu l p ay lo ad

i n te g r at io n . The s c i e n t i f i c p o r t i o n o f t h e SL-1 mission shows a hfgh degree! o f objec-t ives accomplished. A “quick-look“ assessment by t h e s c i e n t i s t s i n d i c a t e t h e f o ll o w i n gpercen t t\ccompl ishment; however, th e s c i e n t i f i c success car1 on ly be com pletely de termineda f t e r a l l c o l l e c t e d d a ta a r e e va lu ate d.

I n th e d i s c i p l fn e o f l i f e scfen ce s, 11 o f 16 exper iments were 100-percent successful ,and t he o ther f i v e achieved 50 t o 90 percen t o f t h e f r p lanned ob jec t i ves .

The astronomy and so la r physics exper iments d is c ip l i n e ind ic a te 100-percent success w it hfour of s ix exper iments and 95 percent with another. The s i x t h experiment, 1NA008, hasnot been assessed a t th i s tine.

.The plasma phys ics d is c ip l i n e indic ate s 100-percent success with one experiment and80 t o 90 percen t with t he o ther f ou r .

The atmospher ic phys ics and e ar t h o bservat fon d is c i p l in e experienced 75 t o 100-percent

Success with f i v e experiments . The othe r one ind ica ted l im i t e d success because o f t h el a u n c h s l i p t o November 28, 1983.

F ive mater ia ls process ing experiments , inc lud ing th e t r ib o lo gy , had 100-percent successfu laccompli shinent o f obj ectf ves . The remaining r e processed i n 1ES300. Wfthin th a t

f a c i l i t y experiments and m ir ro r heat ing f a c i l i t y experiments achieved 50 percent and 60percent , respect ive ly .

The ES A f a c i l i t y 1 E S 3 0 3 ( ~ ~ ~ @ ~ i a ~ sscience d w b l e r ack ) s t a p t d Q p ~ r ~ ~ i o n son day 2 a Awas v e ry s u c ce ss fu l i n o p e r a t i n g t h e f l u i d p h y si c s modu?a and th e grad ien t heat’irog f a c i l -f t y ; howeverp t h e iso therma l hea t ing f a c i l i t y and the m l r r o r heatdng facility f a l l e d ondqy 3 due t o power supply problems. The mlrror ~ ~ a ~ i ~ gf a c i l i t y was l a t e r r e st o re d t o ‘operat ion by crew act ion.

f a c i l i t y ( m a t e r i a ls s ci e nc e d o ub le ra ck ), t hf l u i d p h ys ic s module ex pe ri me nts e r e 1 0 0 ~ ~ e r c e n tsuccessfu l and the isothermal heat ing

rad ien t hea t ing f ac i l i t y exper imen ts and

ES A exper iments 1ES020 (pass ive u n it ) and 1ES022 (very wide f j e l d camera) were bo thsuccess fu l l y i n s t a l l e d and opera ted from t h e s c i e n t i f i c a i r l o c k o n days 2 and 5, respec-t i v e l y .

ES A exper iment 034 ~ m i c r o ~ a v ~remote sensing) began operations on day 3 and operateds u c c e ss f u ll y i n a pa ss ive mode, bu t

INS002 (SEPAC) operations began on day 0 and were successful ly conducted throughout them i ss io n e xc ep t f o r t h e f a i l u r e o f t h e EBA (e lec t ron beam assembly) t o operate i n a h igh-power beam mode.

Even though experfmnt INS003 ( A E P I ) had t o r em a in lo c k ed i n p o s it i o n , O r b i t e r a t t i t u d epo i n t i ng enab led 80 percen t o f t he da ta co f lec t f on ob jec t i ves t o be achieved.

u l d n o t f u n c t i o n i n an active mode.

w

rn

,VEHICLE ASSESSKtdT

SOLID ROCKET BOOSTERS

The SR B ( s o l i d r o c k e t b o os t er ) a f t s k i r t s hoe shim s from a l l fo ur n o r t h posts and fromone south post were re leased dur ing t h e ea r l y phases of l i f t - o f f .i s being pursued.

~ m p ~ o ~ ~ ~ n ti n b on din g

5



The engine s t a r t bu i ldu ps and t ran s i t io ns t o mainstage were normal.and performance du r i n ge appeared sa t isfa cto ry. Dur in g stead y-state performance,ET/ORB (O rb i t e r ) p res

s a t i s f i e d i n t e rf a c e r ts. Qufck-100 e r a t i o a nd t h r u s t v al ue s from t h ef l i g h t I n d i c a t e r ep ea i n e p er fo nn an c r - l e v e l t h r o t t l i n g o p e r a ti o n a pp ea re dnormal. Engine shutd at is fac tory . urre d approximately 1.0 second la t e rthan predicted.

The s t i ck ing closed of the gaseous hydrogen f l ow con t ro l va l ve no. 1, w hic h f a i l e d t orespond t o 13 o f 16 commands from T+10 t o T+375 seconds remain s under i n ve st ig a ti o n( t a b l e I I a ) . However, sa t is fac tor y tank p re ss ur im t io n was mainta ined throughout th erequi red t ime per iod.

The l i q u i d owgen u l la ge pressure s lump a t T+30 seconds t o 17.5 ps id (wa ive r l i m i t i s18.3 ps id ) con t inues t o be inves tiga ted .l i m i t w i l l b e p r o p o s e d f o r f u t u r e f l i g h t s ( t a b l e I I a ) .

Engfne ope rat io n

temperatures, and O ~ $ / S S ~ Epressures and temperatures

The problem can be reconstructed. A new waiver

7



SPACE^^ SYSTEM PERFOR

The SL-1 (Spacelab-l anission) was t he f i r s t o f two f l i g h t s comp r is ing the Spacelab VFT

( V er i f ic a t i o n F l ig h t Test) P r ~ ~ r ~ m .The S pa ce la b- l c o n f ~ ~ u r a t i o nc o n s is t e d o f a n i n t e r -connected Spacelab t ransfer tunnel, long module, and s in g le pal:&.support equipment) inclu ded th e S M M (Spacelab window adapter assembly), SAL ( s c i e n t i f i cai r lo ck ), and an af t - en d cone-mounted viewp ort assembly.inc lude d exper iment hardware i n th e module and on the p a l l e t r e p r e s e n ti n g f i v e b r oa d a re aso f i n v e s t i g a t io n .Spacelab-1 VFI ( V e r i f ic a t io n F l i g h t I ~ s t ~ n t a t i o n 9system t o p r o vi d e f o r t h e a c q u i s i t i o no f a d d i t i o n a l d a ta r e q u i re d t o a c c m p l i s h t h e o b j e ct iv e s o f t h e VFT Program.du rat i on was extended an ad di t io na l day because th e expend iture o f consumables was l e s st h an p r e d ic t ed , p r o v i d i n g t h e o p p o r t u n i ty f o r a d d i t t o n a l S p ace la b v e r i f i c a t i o n a ndexper iment activ ities.

CPSE i c

The Spacelab- l conf igurat ion,

A lso inc luded t h roughou t t he con f igu ra t ion was hardware cmpr i s ing t he

The mission

A ll SL-1 VFT fu nc t io na l ob jec t ive s are be l ieved t o have been per formed i n accordance w i t ht h e t i m e l i n e a nd f l i g h t p ro ce du re s. A p ro ce du ra l e r r o r i n t h e a c t i v a t i o n o f t h e V F I o r b i tmode, and a r e a l - t f m @. .c is ion t o cyc le power t o the VFI system dur ing a 27-hour per io d o ft he f l i g h t did r e s u l t i n t h e loss o f some YFI da ta (o r ig in a l l y p lanned t o be acqu ired

th roughou t t h e o rb i t a l phase o f th e missio n); however, no impact t o VFT eva lua t ion ob jec -t i v e s i s expected from t h i s loss of data.

W i t h t he excep tion o f a mino r number o f anomalies, th e Spacelab system operated sa t is fa c-t o r i l y t o s u p po rt t h e s ec on da ry o b j e c t i v e o f t h e m is s io n t h a t was t o o b t a i n v a l u ab l es c l e n t i f i c , a pp l k a t ? o n s , an4 t ec hn o lo g da ta f r om the jo i n t Un i t ed S ta tes and European

nity, t h e b r oa d c a p a b i l i t ys c t a n t f f i c r e s ~ a r ~ ~ ~f a b l e I I b con ta ins a com pila t ion o f Spacelab systemthe ~ ~ ~ c ~ ~ a ~ - ~f14ght. The problems are described i n subseguent sec t ions

ry ~ ~ y l o a dand t o ~ ~ 0 n $ t r ~ t e ~t o t h e u s er c

The Spacelab ECLS ( ~ n ~ ~ r Q ~ ~ tpay1oad f n t e r f a ca n m a lies occurr

hema? control system andg n i f i c a n t E C L S l t h e m l - re 1 a te d

S t r u c t u r a l S u b s ys t m

A l l low-f requency accelerometers were funct ional and y i e l d i ng measurements w i t h in t h e’ pred ic ted range. The la te ra l ( V 9 a c c e le r a ti o n s a t l a un c h w r e lw , c o n s is t e n t w i t h a

spectrum c ~ p a ~ ison, was c o n s i s te n t t h p r e f l i g h t p r e d lc t io n s . e

V i b r a t i o n and a c o u s t i c m a s u re n ~ i r o n ~ ~ n t a lp red ic t i ons .

I n general, t h e ~ e a $ u r ~ ~s t r a i n l e v e l s w ere 1

operations,

t r i c a l SRS th ru s t pro f i le s . The f requency content, evaluated on th e bas is o f shock

n t s were well within the measurement range and within

V

I) and w i t ~ i nthe predic ted ranges.

e SWAA was us& ~ x t ~ n s i ~ ~ ~ ydur i ng t he m iss ion t o suppor t pe riment 33 photographicA I I these o p ~ r a ~ ~ o n sM@reCO~dMcted~ i t ~ o u tinc ident .

r f o m a n c e d u r i n g SL-l wa s tandin^ din^. The SAL suppor ted both e l tper imnt 20and experiment 22 opera t ions i n accordance wf t h t he mfss ion tineline. The S i t was a l s oo p er at ed d u r i n g t h e c o l d t e s t arci th e hot. t e s t a s p a r t o f t h e VFP. A l l mechanisms wereoperated successful ly.



The performance of bo th vthroughout th e mission.i n c i d e n t and t h e o p t i c al q u a l i t y o f the triple-layer glass was demonstrated by l i v e TVdownl ink pic tures o f the pa l l e t t a ke n t h r ough the aft-end-cone viewport.

p o r t s (o ne i n t h e SWAA and one i n the aft-end cone) was nominalo u t e r cover l a tch and rota t ion mechanisms opera ted wi thou t

Camand and D a t a b n a g m n t System

Software Assessment:computer f unc t i one d nw dna l ly w i t h only minor problems during t h e mission,(ex per iwn t computer opera t ing sys tem) c r ash was exper ienced; however, t h i s c r a sh on lyoccur red as a result of a p a t c h t h a t was i n s e r t e d t o a t t e mpt t o work around the RAU 21problem and a c qu i r e da t a .RBU 21 problem an d these pa t c he s worked successfully.t ha t c a use d the ECOS crash, were v e r i f ie d a t th e HSFC Software Development Facility.v e r i f i c a t i o n o f th e pa t c h which caused the ECOS c r a s h was limited by th e i n a b il i t y t od e f i n e the RlUl 21 f a i l u r e c h a r a ct e r i s tj c s f o r a l l miss ion c onf igu r a t i ons i n r e a l- t ime .

An SCOS (subsystem computer o p e r a t i n g s y st e mj e r r o r message f s unde r i nve s t i ga t j on be ca uset h e e r r o r t h e o r e t f c a l i y s h o ul d h av eSCOS reported r e c e i v i n g a n " I n v a l i d C m n d . " One pa t c h was made t o SCO

addf t i o n a l e r r or - s up p o r t d a t a shoul S r e por t r e c e iv ing a no the r " I nva l i dSCOS did not report such a n e r r o r d u r f ng the remainder o f the miss ion, and th e problemremains under inves t iga t ion.

The Spacelab sof tware i n the exper iment computer and subsys tmAn ECOS

Severa l other pa t c he s were made t o the ECOS t o h e l p s o l v e th eA l l patches , inc luding the patch

The

detected by STS ground o r uplink systems. Th e

Subsystem Hardware: Ws a n i n t e g r a t e d s u b s y st , th e CDHS (command and data managementsubsystem) p e r ~ o ~ di n a l l y . CCTW ( c l os e d c i r c u i t t e l e v i s i o n ) v i de o was p a r t i c u l a r l yo u t s t a n ~ ~ n ~ .TWQa naccomplished.

The MDRR (high d a t a r a t e r e c o r d e r ) ~ ~ ~ a r @ ~ ~ ~ yexperfenced an electromechanical probfemr e s u l t i n g I n e x c e s s i v e d r ag i n t h e tape d r j v e , and the drag caused an overcur rent condi -t i o n i n the d r i v e motor ( table Xlb) . The c o n d i t i o n was c l e a r e d by g ~ o ~ n d ~ ~ ~ v e l o ~ e dr e a l -time procedures. The a n ~ ~ ~ yd i d no t recur.

The second anomaly was with WAU 21 ( t a b l e f Ib) .RAU were lost when the freon loop c o l d p l a t e tmtpera ture (on which th e RAU was mounted)exceeded 2 2 O C.m i ssion-dependent @ ~ u i ~ ~ n t ~~ r k a r o u n ~ swere imp1anent ?d, i nc lud ing ECOS patches andpower management t o reduce hea t induced intG the f r e on l r o p , a nd e xpe rimen t ope r a t i onsc o n ti n u ed i n a degraded mode.

ies occur red, but i n both cases ope r a t i ona l w r ka r ounds were

The d a t a a c q u i s i t i o n f u n c t i o n s o f thls

Ihe loss o f these Funct ions i m p a c ~ ~ dNASA p a ~ l e t - m o u ~ ~ @ ~experiments and

The EPOS ( e l e c t r f c a l power dis t r lbut ion sys tem) per formed nomina l ly throughout themission.Spacelab subsystem c o n s ~ ~ ~ ~ o nwas ne a r ly a t the l e v e l predicted,fo r the l ess- than-predic ted power cansimpt ion a r e tha t some exper imentsas much as o r ~ g i n ~ ~ l yt ~ m ~ l i n ~ ~a nd he a t e r du ty c yc l e sth e cold test. hand, some experim@nt$ a sthan predicted p

SL-I power consumption was ~ p p r o x ~ m a ~ e l y1.2 kW 1 er than predicted; however ,P a r t i

9



H a b i t a b i li t x

The Space lab c rew systems in t e r f ace s f unc tioned we l l w i t h no s i gn i f i ca n t c r w co m n t srepor ted. The genera l arch i tec ture, co lo r u t i1 iz a t i o n and subsystem work sta t io nsappeared sat isfactory.

The O r b i t e r f o o t r e s t r a i n t s w ere q u i t e e f f e c t i v e .modul e was s a tisf actory.The area l i g h t in g was very good.m i s s io n by t u r n i n g o f f s e l e ct e d l i g h t s t o h e l p r ed uc e f r e o n l o o p h ea t l o a d i n s up p or t o fRAU 21 workarounds. Na s i g n i f i c a n t i m p a c t on operetions was noted.

Communications us ing th e Spacelab inte rcom syste m eild th e wlre les s headsets were sat is -factory. Background nois e d i d not af fe c t communicat ions, except when e qu ip en t th a t wasknown premfssion t o be above s pe ci f ie d n oise values was operated.ef f ic ie nc y, th e f l i g h t crew has recommended rev is io ns be made t o th e Spacelab i .i tercom-munfcations system.

n r ia t io n wo uld p r o v i d e a f u n c t i o n a l c a p a b i l i t y s i m i l a r t o t h e p r e se n t O r b i t e r

system.

Handrai l placement throughout the

The l i g h t l eve ls were reduced d i r r i ng a por t i on o f t he

To improve operat ional

T h i s r e v i s i o n w ou ld a l l o w m o n it o ri n g and op e r a ti o n a l f l e x i b i l i t j .

The Spacelab Program i s r ev iew ing t h e recommendation.

Safety Assessment

A l l Spacelab caut io n and warning, and emergency parameters remained w it h in th e i r t i n i t sexcept f o r p lanned ac t i v i t i es . Dur ing changeout o f the LiOH canis ters , th e cabin fand i f f e ren t ia l p ressure exceeded t he lower 1i m i t. *en manually co nt ro l l in g th e atmospheret o o b ta in n i tr og e n re g ul at or o ~ e r a ~ ~ o n ,the SL-1 oxygen and n i t r o g t n f l o w r a te s e r eexceeded; a l so , t h e O r b i t e r cab'ln d e l t a p / d e t t e t measurmnent in di ca t io n exceeded i t sl i m i t d u r i n g t h i s o p er at io n .

F1 l g h t I ~ ~ t r ~ ~ n t a ~ ~ o n

The f l i g h t in stru me nta tio n $ u ~ s y s t ~p e ~ ~ o ~ a n c ewas sa t isfa cto ry. One an ma ly wasobserved. The VFI tape record er d i d not go i n to th e record mode when cmd nd ed t o QO

so v i a t h e RAU by a ground command. H ever, i t d i d f u n c t i o n n o r m a l l y v i a t h e c o n t r o l

nds. There was no impact t o VFT da ta acq u is i t i on requ i rements on o r b i t .Dur in g th e descent phase, on ly the f i r s t 7 minutes o f th e re qui re d descent d ata wererecorded. The cause and impact o f th e loss o f t hese da ta i s be ing assessed.

ORB1 TER/SPACELAB INTER FACES

The vehic le per formance invo lv in g th e SpacelabjOrb i ter e l ec t r ic a l , f l u i d , and mechanica lf n t e r f aces was e x c e l l e n t w i t h o n l y one s f g n i f t c a n t a nSpacelab S M S (Subsystem Computer Operating System) rejected MCC opl inked HPRR ( h igh da tar a t e reco rde r) "standby" conunands it s i n v a l i d ( t a b l e I I c ) .

ORBITER

ly. On tw occasions, the

c

The o v e r a l l p e r f o m n c ? o f t h e O r b l t e r was sa t i s f ac to ry .anomalies I s con ta ined i n t h e f o l l o w in g paragraphs.anomalies are contained i n t a b l e I I c .

A d i sc u ss io n o f t h e s i g n i f i c a n tA com plete l i s t o f t h e O r b it e r f l i g h t



During relaunch op era tio ns, the l ef t- ha nd ( o r b it a l ~ n @ u v @ r i n gsys t(Backup\ pitc h act ua tor fa ile d t o respond p c r l y i n the OFPS p r o f i l e t e

ry ac tu&tor , the backup actuator was dls-Ire secondary actuator was ac t iva ted and th e

backup actuator was disabled for theinder o f the m i ss

Water Tank B Quantity Increase Greater Than fuel Cell &iter Output

Beginning a t about 334:12:00 G.rn.t., the flow rate f r t h e fuel ce l l s t o water tank B was20 cclrnin greater than that calculated based on fue l -

Analysis o f the water dump prof i l es Ind ica ted t h a t an excesslve amount of gaseous hydrogenwas entrained i n the water output th e fuel c e l l s .and potable water systems was imp1

Successful management o f the supply

S-Band Antenna System Problem

Beginning a t about 338:21:16 G . r n . t . , several S-Band r

ni f i can t ly a f f ec ted ~ h ~ ~ ~ ~ ~ ~ u tthe mission.

r peaks (u p t o 16W)curred b r i e f l y (minutes) and randmly for ten the u pper quad ~ n t e n ~ a swere se lec ted ; h

A t 337:21:30 G.rnotrs th e S lock. ~ ~ ~data

trader of t h mission.RSf eo PA I , the two-

Shor t ly a f t e r l and ing a t 342:23:54:14 G .mr t . . MU-1 p r ~ ~ t u r @ l ys h u t down because o f an

p e c t i o n r ~ v ~ a l e dextensive damagehas been organized t o deternine

conditton. A t 3 2:23:58:38 6.rn.t.. AFO-2 a l s o s h u t dwn because o f an under-U-3 was s h u t down nomi nal ly.i n i t y o f these APU’s.

Postfl D ght iAn i nves t iga t ion t e

the cause o f these f a i lu res .

GPC-1 And GPC-2 Fai led

A t 342:11:10:21 G,m.t. during computer r econflgura t fon fo r en t ry , GPC-1, (OPS 2) failed.Shor tly th@reaf te ra t 342:11:16:45 G.m.t.* GPC-2 (OPS 2) a l so fal led. All a t tbr ing GPC-1 back on line were unsuccessful.

ory dump fndfcated somelned i n OPS 3 and was us

ry a1 terietions had occurred.n t set uith GPC-3

an d ~ ~ ~ $ ~ n g .A t Orbiter now wheel 2:11:16:45 G.rn.t.)

ne U n i t NO. 1 F a i led

342:16:42:31 G.rn.t. an 342:17:03:46 Gem. t . , f a u l t messages w@rerecelved‘Ich indfcated that IW-1 The B ITE ( b u i l t in test equipment) pe failure t o the dc/dc no. 1 card i n the IPW-1 power supply. IMU-1 was po

.and there was no mission impact.

. i

11



Brake Damage

The i n f t i a l Orbiter t ilng o p a t i o n from the Edwards Alr Force Base runwayby a locked r i g h t out ard brake. Fleld si te inspect ion revealed that theliner on t h e no. 3 rotor was damaged. All four brakes bere rvendor fo r a deta i led inspection and f a l lu re malys l s .

ved and returned t o the

Reaction Control System R30 Thruster leiiked

A t 335:10:36:58 G.m.t., the reaction control system primary thruster R3D incurred an oxi-dizer leak and was deselected. After 113 hours, the leak had stopped; and, alehoujh thenozzle temperature rose above t h e h o t - f i r e redline value of 65' F, t h e t h r u s t e r was no treselected and there as no impact t o t h e mission.

AERODYNMICS

0.25 Hertz O s c i l l a t i o n During Entry

On a l l previous f l i g h t s i n t h e r eg ion be twen ' ch 2 and 1, a small ampli tude lateral /direc tiona l os ci ll at or y motion has been presen

t r i c a l flow separat ion i n phase w i t h the rudder inputs due t o the large speedbrake

opped the l l w f t cycle was input

One explanatfon of t h e cause was

To test t h i s theory on STS-9, a s p @ ~ ~ r a k @reduction, whir' theoretfcally shouldB STS-9 f l i b h f d a t a s ~ ~ @ dt h a t the

levels o f o $ c i l l a t i ~ ~were as high o r higher than those observed on previous flights.Also the elevon moved u 2* rwe than was ~ ~ @ ~ i ~ ~ @ $which t h u s reduced th e atleron

cttan f n a ~ ? @ ~ ~ ~~~~~~t~~~~~~~du e t o etlcvon posi t ionloss in a ~ ~ @ ~ ~e f ~ @ ~ ~ ~ v e ~ @ ~ ~durfng STS-4 ~h~~~~~ SI'S-8 flights i s n

Eo be t h e cause o f th e ~ ~ c i l l ~ ~ ~ ~ ~ .

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sts-9 national space transportation system program mission report

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