STS-58 Space Shuttle Mission Report

8/7/2019 STS-58 Space Shuttle Mission Report

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NSTS-08287

STS-58

SPACE SHUTTLE

MISSION REPORT

Pre a d b

Robert

cke,LESC/Flight Evaluation and

Engineering Office

Approved by

E. Michael EngleSTS-58 Lead Mi sion Evaluation Room Manager

vid H. CampManager, Flight Engineering Office

D. M.

ny

Manager, Orbite

FE Projects

01,-' k7 .Brewster H. 'Shaw

Dire or, Space Shuttle Operations

Prepared byLockheed Engineering and Sciences Company

fo rFlight Engineering Office

NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONLYNDON B. JOHNSON SPACE CENTER

HOUSTON, TEXAS 77058

January 1 994


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STS-58 Tab le o f Con ten t s

Ti t l e

age

I NTR ODUCTI ON

MI SSI ONS UMMARY

PAYLOADS

SPACELAB LIFE SCIENCES-2 EXPERIMENTS

.

.

. 4Card iovascu la r /Card iopu lmonary Sys tem

.

4Neuroves t ibula r Sys tem .

4

Regula to ry Phys io logy 5Muscu loske le ta l Sys tem 5

ORBITAL ACCELERATION RESEARCH EXPERIMENT. . . . . . . . 6SHUTTLE AMATEUR RADIO EXPERIMENT. .

.

.

6URINE MONITORING SYSTEM .

6VEHICLE PERFORMANCE. 7SOLID ROCKET BOOSTER REDESIGNED SOLID ROCKET MOTOR . . . . . . 7

EXTERNAL TANK

.

8

SPACE SHUTTLE MAIN ENGINE .

9SHUTTLE RANGE SAFETY SYSTEM .

10

ORBITER SUBSYSTEMS

11Main Propu l s ion Sys tem .

11

Reac t ion Cont ro l Subsys tem .

12Orbi ta l Maneuver ing Subsys tem

. 12

Power Reac tan t S to rage and Dis t r ibu t ion Subsys tem 13Fue l Ce l l Powerp lan t Subsys tem .

. 13

Auxi l i a ry Power Uni t Subsys tem

. 14

Hydrau l i c s /Ha te r Spray Boi le r Subsys tem

. . . . . 14

Elec t r i ca l Power Dis t r ibu t ion and Cont ro l Subsys tem. 15Envi ronmenta l Con t ro l and L i fe Suppor t Subsys tem 15Smoke De tec t ion and F i re Suppress ion Subsys tem - 17Airlock Support System . 18Avion ics and Sof tware Subsys tems .

.

. 18Communica t ions and Track ing Subsys tems . . . .

. . 18

St ruc tu res and Mechan ica l Subsys tems .

. . .

. . 19Aerodynamics , Hea t ing , and Thermal In te r faces

. . 20

T h e r m a l C o n t r o l S u b s y s t e m 20Aero the rmodynamics

21

Thermal P ro tec t ion Subsys tem . .

21

ii i

P lW*A

PAGE M A3' % ttQ , F 9 R9^ ;

P

NTiQNMJ.Y 61lA


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STS-58 Tab le o f Con ten t s (Conc luded)

Tit le

age

F L I G H T C R E V E Q U I P M E N T / G O V E RN M E N T F U R N I S H E D E Q U I P M E N T . . . 2 3C A R G O I N T E G R AT I O N . . . . . . . . . . . . . . . . . . . . 2 3DEVELOPMENT TEST OBJECTIVES/DETAILED SUPP LEMENTARY

OBJECTIVES

. . . . . . . . . . . . . . . . . . . 3DEVELOPMENT TEST OBJECTIVES . . . . . . . . . . . . . .

3

DETAILED SUPPLEMENTARY OBJECTIVES . . . . . . . . . . .

5

P H O T O G R A P H I C A N D T E L E V I S I O N A N A LY S E S . . . . . . . . .

7

LAUNCH PHOTOGRAPHY AND VIDEO DATA ANALYSIS . . . . . .

7

ON-ORBIT PHOTOGRAPHY AND VIDEO DATA ANALYSIS . . . . .

7

LANDING PHOTOGRAPHY AND VIDEO DATA ANALYSIS . . . . .

7

Lis t o f Tab les

TABLE I - STS-58 SEQUENCE OF EVENTS . . . . . . . . . . . 8TABLE I I - STS-58 PROBLEM TRACKING LIST . . . . . . . . . 1TABLE I I I - MSFC IN-FLIGHT ANOMALY LIST . . . . . . . . .

3

Appendixes

A - DOCUMENT SOURCES . . . . . . . . . . . . . . . . . . . A-1

B - ACRONYMS AND ABBREVIATIONS . . . . . . . . . . . . . . B-1

iv


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INTRODUCTION

The STS-58 Space Shu t t l e P rogram Miss ion Repor t p rov ides a summary o f thePay load ac t iv i t i e s a s we l l a s the Orb i t e r, Ex te rna l Tank (ET) , So l id Rocke tBoos te r (SRB) and Redes igned So l id Rocke t Motor (RSRM), and the Space Shu t t l emain eng ine (SSME) s ubsys tems pe r fo rmance dur ing the f i f ty -e igh th miss ion o f theSpace Shu t t l e P rogram, and the f i f t een th f l igh t o f the Lrb i t e r veh ic le Co lumbia(OV-102) . In add i t ion to the Orb i t e r, t he f l igh t veh ic le cons i s t ed o f an ET(ET-57) ; th ree SSMEs which were des igna ted as se r i a l number 2024 , 2109 , and 2018in pos i t ions 1 , 2 , and 3 , r e spec t ive ly ; and two SRBs which were des igna tedBI-061 . The l igh twe igh t RSRMs tha t were ins ta l l ed in each SRB were des igna tedas 360L034A ( l igh twe igh t ) fo r the l e f t SRB and 36OW034B (we l t e rwe igh t ) fo r ther ight SRB.

The STS-58 Space Shu t t l e P rogram Miss ion Repor t fu l f i l l s the S pace Shu t t l eProgram requ i rement a s documented in LASTS 077 00 , Volume VI I I , Append ix E . Tha tdocument s t a t e s tha t each major o rgan iza t iona l e l ement suppor t ing the Programwi l l r epor t the r esu l t s o f i t s ha rdware eva lua t ion and miss ion pe r fo rmance p lusiden t i fy a l l r e l a t ed in - f l igh t anomal ies .

The p r imary ob jec t ive o f th i s miss ion was the success fu l pe r fo rmance o f theopera t ions o f the Space lab L i fe Sc iences (SLS) -2 pay load . The secondaryob jec t ive o f th i s f l igh t was to pe r fo rm the opera t ion s o f the Shu t t l e AmateurRad io Exper iment - I I (SAREX-I I ) pay load .

The sequence o f even t s fo r the STS-58 miss ion i s shown in Tab le I , t he base l in edOrb i t e r and GFE Pro jec t s in - f l igh t anomal ies a re shown in Tab le I I , and theoff i c i a l Marsha l l Space F l igh t Cen te r (MSFC) In -F l igh t Anomaly L i s t i s shown inTab le I I I . Append ix A l i s t s the sources o f da ta , bo th fo rmal and in fo rmal , tha t

were used i : i t he p repara t ion o f th i s document . Append ix B p rov ides thed e f i n i t i o n s o f a c r o n y m s a n d a b b r e v i a t i o n s u s e d i n t h i s d o c u m e n t . A l l t i m e sg iven in th i s r epor t a re in Greenwich Aean t ime (G. m. t . ) a s we l l a s miss ione lapsed t ime (MET) where app l i cab le .

The STS-53 miss ion was p lanned as a 14-day miss ion wi th two con t inge ncy daysus ing the Ex tended Dura t ion Orb i t e r (EDO) pa l l e t f o r ex t ra consumables .Four teen major exper iments compr i sed the SLS-2 pay load opera t ions conduc ted byseven crevmembers .

The c rew fo r th i s f i f ty -e igh th f l igh t o f the Space Shu t t l e P rogram was John E .Blaha , Co l . , USAF, Commander ; R ichard A. Sea r foss , L t . Co l . , USAF, P i lo t ; M.Rhea Seddon , M.D. , C iv i l i an , Pay load Commander and Miss ion Spec ia l i s t 1 ; Wi l l i amS. McAr thur, J r. , L t . Co l . , USA, Miss ion Spec ia l i s t 2 ; Dav id A. Wol f , M.D. ,C iv i l i an , Miss ion Spec ia l i s t 3 ; Shannon W. Luc id , Ph .D. , C iv i l i an , Miss ionSpec ia l i s t 4 ; and Mar t in J . Fe t tman , D .V.M. , Ph .D. , C iv i l i an , Pay loadS p e c i a l i s t . S T S - 5 8 w a s t h e f o u r t h s p a c e f l i g h t f o r t h e C o m m a n d e r a n d M i s s i o nSpec ia l i s t 4 ; the th i rd space f l ig h t fo r Miss ion Spec ia l i s t 1 ; and the f i r s tspace f l igh t fo r the P i lo t , Miss ion Spec ia l i s t 2 , Miss ion Spec ia l i s t 3 , and thePay load Spec ia l i s t .


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HISS10N SUMMARY

The coun tdown fo r the Oc tober 14 , 1993 , l aunch o f STS-58 , the second Space labmiss ion tha t was ded ica ted to l i f e sc iences r e sea rch , p roceeded nomina l ly up tothe T-9 minu te ho ld . The T-9 minu te ho ld was l eng thened to 2 hours because o funaccep tab le wea the r a t the l aunch s i t e . The wea the r became accep tab le and thecoun tdown was resumed fo r a l aunch a t 12 :53 :00 p .m. e .d . t . ; however, thecoun tdown was s topped a t T-31 seconds because o f a Range Safe ty p rob lem. S incethe LO dra inback had begun a t the t ime o f the ho ld , the ho ld was l imi ted to4 m i n u s e s 5 1 s e c o n d s from the hold po in t . Range Safe ty was unab le to cor rec tthe p rob lem in tha t pe r iod o f t ime , and the l aunch was sc rubbed . The l aunch wasreschedu led fo r 10 :53 a .m. e .d . t . on Oc tober 15 , 1993 .

A prob lem was no ted dur ing the coun tdown fo r the f i r s t l aunch a t t empt , a f t e rsupp ly t ank A was d ra ined and depressur ized , when the supp ly wa te r t ank A

quan t i ty began inc reas ing a t a f a s t e r r a t e than shou ld have occur red based onfue l ce l l wa te r p roduc t ion . Af te r the sc rub , compress ib i l i ty t e s t s o f supp lywate r t ank A and the ga l l ey showed tha t the re was no ga s in t ank A, bu tapparen t ly a i r had en te red the ga l l ey ho t wa te r t ank dur ing the routinepre launch wa te r t ank A depressur iza t ion and caused wa te r to f low f rom the ga l l eywater supp ly in to supp ly wate r t ank A. The ga l l ey was i so la ted f rom the supp lywate r fo r subsequen t l aunch a t t empts to p rec lude th i s cond i t ion f rom recur r ing .

The second a t t empt to l aunch STS-58 occur red on Oc tober 15 , 1993 , bu t wassc rubbed because the Orb i t e r S -band t r ansponder 2 f a i l ed , and loss o f th i sS-band t r ansponder was a Launch Commi t Cr i t e r i a (LCC) v io la t ion . Also , i t i sun l ike ly tha t the l aunch would have occur red because o f the unaccep tab le wea the rcond i t ions a t the l aunch s i t e . As a r e su l t , an ex tended sc rub tu rna round wasin i t i a t ed to r ep lace the S-band t r ansponder and se rv ice the Space labexper iments . The l aunch was reschedu led fo r Oc tober 18 , 1993 .

During the coun tdown fo r the th i rd l aunch a t t empt , a 10-second ho ld was ca l l eda t T-5 minu tes because o f an in t ruder a i r c ra f t in t h e E a s t e r n Te s t R a n g e . T h ecoun tdown vas r esumed , and the STS-58 veh ic le was l aunched success fu l ly on a39- degree inclination f rom launch complex 39B a t 291 :14 :53 :10 .009 G.m. t .(10 :53 a .m. e .d . t . ) on Oc tober 18 , 1 .993 . Al l Orb i t e r subsys tems opera teds a t i s f a c t o r i l y t h r o u g h o u t t h e a s c e n t . A t the completion of the OMS-2 maneuver,the Orbi ter was in a 155 by 151 nmi. orbi t .

Video t apes f rom th ree cameras moni to r ing the l aunch and the ascen t phase showeda s ing le whi te p iece o f debr i s near SSME 1 about 45 seconds a f t e r l i f to ff . F i lmanalysis a l so shoved a f l ex ib le , whi te ob jec t ex i t ing the a rea betveen 'SSHE 1and 3 at the same t ime . The ob jec t f e l l a f t in to the p lume and a f l a sh in thep lume was no ted about 1 second a f te r the ob jec t was s igh ted . Es t imates o f the

objec t ' s size ranged f rom 14 by 15 inches to 26 by 11 inches . Analysisindicated tha t the ob jec t ves p robab ly a p iece o f the dome-mounted hea t sh ie ld(DMHS) c loseou t b lanke t . Th i s conc lus ion i s based on pas t h i s to ry o f DMHSblanke t damage and the ob jec t ' s apparen t s i ze , shape , co lo r, and a rea o f o r ig i n .A p o s t l a n d i n g i n s p e c t i o n s h o ve d p o r t i o n s o f t h e D M H S a r o u n d S S H E 2 a n d 3 w e r emissing.

A pre l iminary ana lys i s o f the main p ropu l s ion sys tem (MPS) da ta f rom ascen tshoved tha t the SSME 1 GH 2 f low con t ro l va lve exhibited a s low response t ime


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PAYLOADS

The p r imary goa l o f the Space lab L i fe Sc iences -2 (SLS-2) miss ion was to conduc texper iments in a va r i e ty o f d i sc ip l ines address ing i m p or tan t b iomedica lques t ions re l a t ed to phys io log ica l r e sponse s to mic rograv i ty and the subsequen tre -adap ta t ion to g rav i ty. The SLS-2 pay load cons i s ted o f 14 exper iments . E igh tof the exper iments used the as t ronau t c rew as sub jec t s and s ix used ra t s a ssubjects .

In add i t ion to t he 14 SLS-2 exper iments , the pay load inc luded four middeckexper iments . These were the Orb i t a l Acce le ra t ion Resea rch Exper iment (DARE) ,the SAREX, the In te r Mars Ti s sue Equ iva len t P ropor t iona l Coun te r, and the Ur ineMoni to r ing Sys tem (UMS) .

SPACELAB LIFE SCIENCES-2 EXPERIMENTS

The Space lab L i fe Sc iences -2 exper iments were focused in four ma jo r a reas :ca rd iovascu la r, r egu la to ry, neuroves t ibu la r, and muscu loske le ta l sys tems . Theresu l t s o f the exper iments a re d i scussed in the fo l lowing pa ragraphs .

Card iovascu la r /Card iopu lmonary Sys tem

The th ree ca rd iovascu la r / ca rd iopu lmonary sys tem exper iments were the In - f l igh tS tudy o f Card iovascu la r Decond i t ion ing (Exper iment 066) , Card iovascu la rAdap ta t ion to Zero Grav i ty (Exper iment 294) , and Pu lmonary Func t ion Dur ingweigh t l e s sness (Exper iment 198) .

The ca rd iovascu la r exper iments began on f l igh t day 1 wi th cen t ra l venouspressure measurements be ing ob ta ined on the two c rewmembers wi th the ca the te r sinse r ted . Crewmembers pa r t i c ipa ted in b icyc le e rgomete r exerc i ses . Hear t r a te ,blood p ressure , and ca rd iac ou tpu t were de te rmined fo r the pay load c rew member.Al l o f the measurements schedu led fo r f l igh t days 2 , 4 , 8 , 12 , and 14 werecomple ted as p lanned .

Echocard iograms were a l so made on the c rewmembers on f l igh t days 1 , 2 , 8 , and 12of the miss ion . These images were accompanied by e lec t rocard iograms tha t wereused to r ecord ca rd iac rhy thm and e lec t r i ca l ac t iv i ty.

Pu lmonary func t ion t e s t s were comple ted th roughou t the f l igh t , a l though th i sexper iment was to be u t i l i zed as a rese rve ac t iv i ty. The c rewmembers were ab leto accompl i sh ex tens ive pu lmonary func t ion t e s t s a s add i t iona l sc ience ac t iv i ty.

Neuroves t ibu la r Sys tem

A s t u d y o f t h e h u m a n v e s t i b u l a r a d a p t a t i o n t o w e i g h t l e s s n e s s a n d t h e b a s i s o fspace mot ion s i ckness was pe r fo rmed us ing a complement i f experiments. The twoe x p e r i m e n ts i n t h e s c i e l t i f i c d i s c i pl i n e w e r e a S t u d y o f t h e E f f e c t s o f S p a c eTravel on Mammal ian Grav i ty Recep to r s (Exper iment 238) , and VestibularExperiments in Space lab (Exper iment 072) . Al l ha rdware assoc ia ted wi th theseexper iments pe r fo rmed wel l . These exper iments were compr i sed o f the ro ta t ingdome, d rop exper iment , ro ta t ing cha i r, awareness o f pos i t ion , head movement andcompar i son t es t , and the head movement and symptom moni to r ing . These

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exper iments r equ i red the c rewmembers to wear the acce le romete r r ecord ing un i t(ARU) to r ecord the i r head movements th roughou t the day and to r ecord anysymptoms in the da i ly log .

The ro ta t ing cha i r exper iment was pe r fo rmed on f l igh t days 4 and 10 and wascomple ted . Drop da ta were a l so co l l ec ted on f l igh t days 5 and 11 as p lannedp lus , two add i t iona l sub jec t s were t e s t ed on f l igh t day 11 . In add i t ion ,va luab le ARU da ta were co l l ec ted pe r iod ica l ly th roughou t the f l igh t by two o fthe crewmembers .

The ro ta t ing dome e xper iment was pe r fo rmed on f l igh t days 2 , 8 , and 11 wi th a l lsub jec t s comple t ing the exper iment . The As t ronau t Sc ience Advisor (ASA) was acompute r-based in te l l igen t a s s i s t an t tha t was des igned to he lp the as t ronau t swork more e ff i c i en t ly and improve the qua l i ty o f space sc ience . The ASA wasused to suppor t the ro ta t ing dome exper iment , and the p rogram per fo rmedsa t i s fac to r i ly.

Regu la to ry Phys io logy

Inves t iga t ions o f r egu la to ry phys io logy in space in c luded s tud ies o f bo th therena l / endocr ine and hemato log ica l sys tems . The exper iments f lown on SLS-2 inth i s d i sc ip l ine were the F lu id -E lec t ro ly te Regu la t ion Dur ing Spacef l igh t(Exper iment 192) , Regu la t ion o f B lood Volume Dur ing Spacef l igh t (Exper iment141) , Regu la t ion o f Ery th ropo ies i s in Ra t s Dur ing Space F l igh t (Exper iment 012) ,and In f luence o f Spacef l igh t on Ery th rok ine t i c s in Man (Exper iment 261) .

B lood samples , u r ine samples , and sa l iva samples were co l l ec ted on a l lc rewmembers . These samples wi l l be ana lyzed pos t f l igh t fo r pa ramete r s tha tind ica te changes in f lu id , e l ec t ro ly te , r ena l , and c i rcu la to ry s t a tus o f humansexposed to space f l igh t . The b lood samples were cen t r i fuged in the rack-mountedcen t r i fuge p r io r to r e f r ige ra t ion in the L i fe Sc ien ce Labora to ry Equ ipment(LSLE) re f r ige ra to r / f r eeze r s . The c rews iember me tabo l i c ac t iv i t i e s were ca r r i edou t dur ing the c rew ' s pos t s l eep pe r iods on f l igh t days 1 -4 , 6 , 8 , and 12-14 andwere comple ted . The I ron Uptake and Hemato logy Exper iment (Exper iment 261) andRena l Func t ion and To ta l Body Wate r Exper iment (Exper iment 192) were bo thsuppor ted by the ac t iv i t i e s pe r fo rmed fo r th i s d i sc ip l ine .

Muscu loske le ta l Sys tem

In microgravity, the body ' s bones and musc les a re no t used as e x tens ive ly as onEar th . As a resu l t , r e sea rchers have no ted a decrease in the mass o f bo thdur ing space f l igh t . The f ive exper iments tha t were conduc ted in th i s d i sc ip l inewere Pro te in Metabo l i sm Dur ing S pacef l igh t (Exper iment 120) ; Effec t s o f ZeroGrav i ty on the Func t iona l and Biochemica l P roper t i e s o f Ant i -g rav i ty Ske le ta lMusc les (Exper iment 127) ; Effec t s o f Mic rograv i ty on the E lec t ron MicroscopyHis tochemis t ry and Pro tease Ac t iv i t i e s o f Ra t H ind l imb Musc les (Exper iment 303) ;Pa thophys io logy o f Minera l Loss Dur ing Spacef l i gh t (Exper iment 305) ; and Bone ,Ca lc ium and Spacef l igh t (Exper iment 194) .

The c rewmembers were admin i s t e red dua l - s t ab le i so topes o f ca lc ium, one o ra l?yand one in t ravenous ly th roughou t the f l igh t in suppor t o f the P a thophys io logy o fMinera l Loss Dur ing Spacef l igh t exper iment . Glyc ine t race rs were a l so in jec teddur ing the f l igh t to suppor t the Pro te in Metabo l i sm Dur ing Spacef l igh t

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exper iment . Ur ine , sa l iva , and b lood samples were co l l ec ted fo r pos t f l igh teva lua t ion in con junc t ion wi th the Pro te in Metabo l i sm exper iment andPa thophys io logy o f Minera l Loss exper iment .

The Effec t s o f Zero Grav i ty on the Func t iona l and Biochemica l P roper t i e s o fSke le ta l Musc les ( in r a t s ) exper iment was suppor ted by the roden t d i s sec t ionwhich ach ieved a space f i r s t . The roden t was te t r ays a l so p rov ided da ta fo r theBone , Ca lc ium and Spacef l igh t exper iment .

ORBITAL ACCELERATION RESEARCE EXPERIMENT

The OARE was pe r fo rmed success fu l ly wi th a l l p l anned Orb i t e r opera t ions insuppor t o f the OARS be ing comple ted . Inc luded in the Orb i t e r opera t ions wereth ree se t s o f 360 0 veh ic le ro ta t ions abou t each o f the th ree bo dy axes , a60-minu te max imum drag a t t i tude t e s t , and a 25-minu te p i t ch -down drag t e s t . Inadd i t ion , the Orb i t e r was p laced in the STS-74 Uni ted S ta tes Mic rograv i tyLabora to ry (USML) -2 a t t i tude fo r 15 hours to acqu i re OARS acce le ra t ion da ta tode te rmine whe the r th i s i s the bes t a t t i tude fo r the U SML-2 mic rograv i ty sc ience .

The DARE acqu i red da ta th roughou t the o rb i t a l and en t ry phases . The raw sensorda ta were recorded on the pay load recorder and dumped pe r iod ica l ly to theg r o u n d . H o w e v e r, o n f l i g h t d y 10 , the recorder fa i l ed . The loss o f ther ecorder d id no t se r ious ly impac t the D ARE, because rea l - t ime p rocessed da tawere stored in the OARE' s solid-state memory throughout the mission.

Preliminary reviews of the dumped da ta ind ica te nomina l OARE opera t ion excep tfo r e r ra t i c Z-ax i s da ta when the OARE was in i t s sca le f ac to r ca l ib ra t ion mode .Th i s cond i t ion i s no t expec ted to impac t the f i na l da ta p rocess ing because goodca l ib ra t ion da ta can be ob ta ined as a r e su l t o f the 360 veh ic le ro ta t ions ,which were pe r fo rmed to ob ta in da ta fo r ca lcu la t ing the Orb i t e r ' s ac tua l cen te r

o f g r a v i t y a s w e l l a s p r o v i d e a b a c k u p t o t h e O A ' s s e l f c a l i b r a t i o n .

SHUTTLE AMATEUR RADIO EXPERIMENT

The SAREX equipment opera ted very wel l th roughout the miss ion . The SAREXpay load opera t ions were h igh ly success fu l wi th a to ta l o f 17 schoo l con t ac t sc o m p l e t e d. S i x t e e n U n i t e d S t a t e s s c h o o l s h a d d i r e c t c o n t a c t s w i t h t h e S h u t t l ec rew us ing SAREX. A br idge tha t used an amateur r ad io s t a t ion in Aus t ra l i a wasused fo r one con tac t wi th a school in France . Two school backup passes werer equ i red , one fo r a Uni ted S ta tes schoo l and a second fo r the French schoo l . Inadd i t ion , a con tac t was a r ranged wi th the Russ ian Space Station MIR during themission. The SAREX packe t mode was a l so used ve ry success fu l ly wi th g rounds ta t ions repor t ing severa l hundred con tac t s .

URINE MONITORING SYSTEM

The UMS operated nominally in the collection volume measurement and samplingof individual micturations in zero gravity.


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VEHICLE PERFORMANCE

SOLID ROCKET BOOSTER

Al l SRB sys tems pe r fo rmed nomina l ly wi th the excep t ion o f r igh t -hand SRB mainparachu te 2 . The SRB pre launch coun tdown was normal , and no SRB Launch Commi tCr i t e r i a (LCC) o r Opera t iona l Main tenance Requ i rements and Spec i f i ca t ionDocument (OMRSD) v io la t ions occur red .

Power-up and opera t ion o f a l l case , ign i t e r, and f i e ld jo in t hea te r s wasaccompl i shed rou t ine ly. For the STS-58 miss ion , the low-pressure hea ted g roundpurge in the SRB a f t sk i r t was used to ma in ta in the case /nozz le jo in t andf lex ib le bea r ing t empera tu res wi th in the requ i red LCC ranges . At T-15 minu tes ,the purge was changed to h igh p ressure to ine r t the SRB a f t sk i r t .

Bo th SRBs were success fu l ly separa ted f rom the ET a t T + 123 .8 seconds , andv i sua l s igh t ings in the recovery a rea ind ica ted tha t the dece le ra t ion sys temsper fo rmed accep tab ly. Ana lys i s o f f l igh t da ta ind ica tes tha t the r igh t -hand SRBmain pa rachu te 2 l agged in to second s t age . The pa rachu te in f l a t ed in i t i a l ly bu tc o l l a p s e d l a t e in the f i r s t s t age o f in f l a t ion and remained co l l apsed th roughthe f i r s t d i s ree f ing s t age . T. : e pa rachu te began inflating shor t ly a f t e r thef i r s t d i s ree f s t age and was fu l ly in f l a t ed p r io r to the second d i s ree f .R igh t -hand main pa rachu tes 1 and 3 remained fu l ly in f l a t e d th roughou t thedescen t pe r iod . Bo th SRBs were recovered and re tu rned to KSC fo r d i sassemblyand re fu rb i shment .

REDESIGNED SOLID ROCKET MOTOR

Al l RSRM tempera tu res were main ta ined wi th in accep tab le l imi t s th roughou t thecoun tdown. The RSRM prope l l an t mean tu lk t empera tu re (PMBT) was 80F a t

l i f to ff . No RSRM LCC or OMRSD v io la t ions occur red .

The f i e ld jo in t hea te r s opera ted fo r 11 hours 36 minu tes dur ing the l aunchcoun tdown. The to ta l ac t iva t ion t ime , which inc ludes the sc rubbed l auncha t t e m p t s , w a s 3 6 h o u r s 5 3 m i n u t e s . P o w e r w a s a p p l i e d t o t h e h e a t i n g e l e m e n tan average o f 19 pe rcen t o f the t ime to keep the f i e ld jo in t s wi th in the i rnormal opera t ing t empera tu re r ange .

Ign i t e r jo in t hea te r s opera ted fo r 18 hours 11 minu tes . The to ta l ac t iva t iont ime ( inc lud ing the sc rubbed l aunch a t t empts ) was 57 hours 3 minu tes . Power wasapp l i ed to the ign i t e r hea t ing e le ments an average o f 38 pe rcen t o f t he t ime tokeep the ign i t e r jo in t s wi th in the i r normal opera t in g t empera tu re r ange .

The a f t sk i r t gaseous n i t rogen ( GN ) purge was opera ted fo r a to ta l o f 2 hours3 6 m i n u t e s . T h e t o t a l a c t i v a t i o n l i m e including the sc rubbed l aunch a t t empts )w a s 1 2 h o u r s 3 8 m i n u t e s . To ensure a l l haza rdous gases were removed f rom thea f t sk i r t compar tment , the purge was opera ted a t h igh f low-ra te f romL-27 minu tes to l aunch . As a resu l t o f the purge opera t ion . the f l ex bear ingmean bulk temperature was 81F.

Da ta in the fo l lowing t ab le show tha t the pe r fo rmance o f the RSRMs was we l lw i t h i n t h e a l l o w a b l e p e r f o r m a n ce e n v e l o p e s and specification l imi t s , and wastyp ica l o f the pe r fo rmance obse rved on p rev ious f l igh t s .

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RSRM PROPULSION PERFORMANCE

Paramete r Lef t motor, 80F Rijzht motor, 80aFPred ic ted Actua l Predicted Actua l

Impul se ga a s I -20, 10 bf-sec 6 5 .92 6 5 . 6 0 65 .92 6 6 . 2 6I -60, 10 6 l b f - sec 175.58 175 .04 175.59 175.58I -AT, 10 6 l b f - sec 296 .83 295.10 296.58 296 .30

Vacuum Isp , lb f -se c/ l bm 26 8 .6 0 267 .10 268 .60 2 6 6 . 3 0

Burn ra te , in / sec @ 60 OF 0 . 3 6 7 2 0.36 84 0.36 7 4 0 . 3 6 9 9a t 6 2 5 p s i a

Burn ra te , in / sec @ 66 F 0 . 3 7 2 5 0 .3737 0.3727 0 . 3 7 4 0a t 625 ps ia

Even t t imes , secondsIgn i t ion in te rva l 0 .232 N/A 0.232 N/ AWeb t ime s 109.02 109 .40 109.20 108.80Separa t ion cue , 50 ps ia 119.00 118.6 0 118.90 18.20Act ion t ime 121.00 121.20 121.00 120 .40Separa t ion command 123.90 123 .70 123.90 123 .70

PHBT, OF 80-00 80 .00 80 . 00 80 .00

Maximum ign i t ion r i se r a t e , 90.4 N/A 90.4 N/Apsis /10 ms

Decay t ime , seconds 2.80 3 .10 2.80 3 .00(59 .4 ps i a to 85 K) ,

klb f - sec

Ta i lo f f i mba la nce P red ict ed Actua lImpulse d i ffe ren t i a l , N/A 5 0 1 . 4

Note:a All t imes a re r e fe renced to ign i t ion command t ime excep t where no ted by the

le t t e r a . These : i t ems a re r e fe renced to l i f t -o ff t ime ( ign i t ion in te rva l ) .

Minor p ressure f luc tua t ions were recorded on each motor. Us ing the ag i - d -uponmethod o f ca lcu la t ing the p ressure b l ip magn i tudes , the b l ip on the l e fc RSRMwas 8 . 0 ps i a t 67 seconds , and 11 .7 ps i a t 71 seconds on the r igh t RSRM. Bothof these va lues a re wi th in the RSRM exper ience base .

EXTERNAL TANK

ET per fo rmance was exce l l en t , and a l l ob jec t ives and requ i rements a s soc ia tedwith the ET prope l lan t load ing and f l igh t opera t ions were met . Al l ETelec t r i ca l equ ipment and ins t rumenta t ion opera ted sa t i s fac to r i ly. ET purge andhea te r opera t ions were moni to red and a l l pe r fo rmed p ruper l , . N o E T L C C o r O M R S Dvio la t ions were iden t i f i ed .


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Typica l i ce / f ros t fo rmat ions were obse rved on the ET dur ing the coun tdown. Noice o r f ros t was obse rved on the ac reage a reas o f the ET. However, normalquant i t ies of ice or f rost were present on the l iquid oxygen (LO 2 and l iqu idhydrogen (LH 2 ) f eed l ines and on the p ressur iza t ion b racke t s . These obse rva t ionswere acceptable per NSTS-08303.

During the f i rs t launch at tempt , the Ice/Frost "Red Team" reported one anomalousthe rmal p ro tec t ion sys tem (TPS) cond i t ion . Two c racks were obse rved in the TPSon the -Y ET/SRB at tach s t rut (one approximately 7 inches by 0 .125 inch and theothe r approx imate ly 14 inches by 0 .125 inch) . There was no i ce / f ros t a t thec racks , no ven t ing , and no o ff se t , i nd ica t ing no debonded a rea ex i s t ed . Noother anomalous TPS condi t ions were reported by the team.

Also dur ing the f i rs t launch at tempt , the ET inter tank oxygen concentra t ionexceeded the LCC l imit of 200 ppm (for the t . . per iod f rom star t of cryogenicsload to T-31 seconds) during an unscheduled hold at T-31 seconds. Analysisindicates that a i r in t rusion can be expected af ter in ter tank purge terminat iona t T-75 seconds . For the second and th i rd l aunch a t t empts , an LCCwaiver /deviat ion was processed to terminate moni tor ing of the LCC l imit a tT-75 seconds ins tead o f T econds.The newly implemented in te r t ank hea te r con t ro l ga in se t t ing and reduced in i t i a ltemperature control se tpoint used dur ing loading operat ions cont inued to besuccess fu l in p rov id ing a smoother t empera tu re pe r fo rmance fo r the purge sys temand more marg in fo r the in te r t ank purge In te r face Cont ro l Document ( ICD) maximumtemperature l imit .

The ET pressur izat ion system funct ioned proper ly throughout engine s tar t andf l igh t . The min imum LO u l l age p ressure exper ienced dur ing the u l l age p ressures lump was 14.7 psid .

ET separa t ion was conf i rmed fo l lowing a nomina l ma in eng ine cu to ff (MECO) . ETen t ry and b reakup occur red as expec ted . The ET impac t po in t was approx imate ly19 nmi. downrange of the pref l ight predict ion, wel l wi thin the predictedfootpr int .

During postf l ight review of photography taken from the Orbi ter umbil ical wel l ,one ET in - f l igh t anomaly was iden t i f i ed . An ET in te r t ank ac reage TPS d ivo t(24 inches by 4 inches ) was no ted a s was the los s o f TPS on each j ack padclose-out (approximately 25 percent) (Fl ight_ Problem STS-58-T-01) . Aninvest igat ion team has been formed to determine the cause and correct ive act ionfor the loss of TPS.

SPACE SHUTTLE MAIN ENGINE

All SSME parameters were normal throughout the prelaunch countdown and weretyp ica l o f p re launch pa ramete r s obse rved on p rev ious f l igh t s . Al l t ank ing andpre launch p repara t ions were comple ted nomina l ly. Al l moni to red LCC paramete r s ,ign i t ion conf i rmat ion l imi t s , and mainstage redl ine margins were sat isfactory.All ICD s ta r t and shu tdown t rans ien t r equ i rements were met . Eng ine pe r fo rmancewas nomina l and as p red ic ted wi th eng ine cu to ff t imes o f 521 .92 , 522 .04 , and522 .16 seconds fo r SSMEs 1 , 2 , and 3 , r e spec t ive ly, a s r e fe renced to the s t a r tcommand . The I sp was ra ted as 452 .3 seconds based on t r a j ec to ry da ta . B lock I Icontrol ler and sof tware performance was sat isfactory.

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Flight data indicate that the SSME performance dur ing mainstage, throt t l ing,shu tdown and p rope l l an t dump opera t ions was normal . High p ressure ox id ize rturbopump (HPOTP) and high pressure fuel turbopump (HPFTP) temperatures appearedto be we l l wi th in the spec i f i ca t ion th roughou t eng ine opera t ion . SSME cu to ffoccurred a t T + 515.56 seconds ( referenced to l i f toff) , and there were nofai lures or s ignif icant SSME problems ident i f ied.

Spiking was observed on both the SSME 2 HPFTP O-degree and 186-degree f l ightacce le ra t ion sa fe ty cu t -o ff sys tem (FASCOS) acce le romete r s . Sp ik ing was a l soobse rved on the SSME 3 HPFTP O-degree FASCOS acce le romete r. The modula rauxi l iary data system (MARS) recorder data are being reviewed to determine thelevel of spiking, and postflight troubleshooting is in progress.

The SSME 1 main combust ion chamber (MCC) pressure dr i f ted dur ing ascent , and apos t f l igh t inspec t ion fo r any con tamina t ion /obs t ruc t ion wi l l be made . The SSME1 MCC hot-gas inject ion pressure did not respond to the 3-g throt t le . Thiscondi t ion is common and is bel ieved to be caused by frozen mois ture in the sensel ine . L ikewise , the SSME 2 MCC ho t -gas in jec t ion p ressure dr i f ted 290 secondsin to a scen t . Th i s a l so i s a common occur rence tha t i s be l i eved to be caused byf rozen mois ture in the sense l ine .

SHUTTLE RANGE SAFETY SYSTE14

Analys i s o f the f l igh t da ta ind ica te s nomina l pe r fo rmance o f the Shu t t l e RangeSafe ty Sys tem (SRSS) . The SRSS c losed- loop t e s t ing was comple ted as schedu led. :u r ing the l aunch coun tdown. Al l SRSS sa fe and a rm (S&A) devices were armed andsys tem inh ib i t s tu rned o ff a t the appropr ia te t imes . Al l SRSS measurementsindicated that the system operated as expected throughout the successfu ' launchcountdown and f l ight .

As p lanned , the SRB S&A devices were safed, and SRB system power was turned offpr ior to SRB separat ion. The E 'T system remained act ive unt i l the ET wasseparated f rom the Orbi ter.

There was one new exper ience base da ta po in t e s t ab l i shed dur ing the secondlaunch a t t empt . The l e f t -hand SRSS A ba t t e ry open-c i rcu i t vo l t age was 31 .68 Vdcjus t p r io r to SRSS power-up . The p rev ious low exper ience b ase va lue fo r th i smeasurement was 31 .84 Vdc es tab l i shed on STS-57 . T he OMRSD lower l imit i s31.60 Vdc.

The ET SRSS s igna l s t r eng th v io la ted the LCC lower l imi t dur ing a r a in s to rm onthe second l aunch a t t empt . The LCC spec i f i e s a p rep lanned con t in gency p rocedure

to use the g round suppor t equ ipment (GSE) radio frequency (RF) signal source toverify proper flight hardware function. This procedure was performed and thes igna l s t r eng th inc reased to 4 .9 Vdc fo r the dura t ion tha t the GSE RP s igna l wasapp l i ed . The Ai r Force F l igh t Con t ro l Off i ce r was no t i f i ed o f the resu l t s andconcur red wi th the NASA conc lus ion tha t th i s was no t a , l aunch cons t ra in t . Thelaunch was l a t e r sc rubbed dur ing the T-9 minu te ho ld because o f a f a i lu re o fOrbi ter hardware.

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ORBITER SUBSYSTEMS

Main Propu l s ion Sys tem

The overa l l pe r fo rmance o f the MPS was as expec ted . LO and LH 2 l oad ings wereper fo rmed as p lanned wi th no s top- f lows o r r eve r t s . No OMRSD or LCC v io la t ionswere noted dur ing the countdown.

Throughout the per iod of pref l ight operat ions , no viola t ion of hazardous gasconcen t ra t ions was de tec ted . The maximum hydrogen concen t ra t ion l eve l in theOrbi ter af t compartment , which occurred af ter s tar t of fas t - f i l l ; wasapproximately 138 ppm, which compares favorably with previous data for th isvehicle.

LH2 loading operat ions were normal through chi l ldown, s low-f i l l , fas t - f i l l ,topp ing and rep len i sh . Based on the ana lys i s o f load ing sys tem da ta , the LH2load a t the end o f r ep len i sh was 231 ,891 lbm. Compared to the inven to ry(predicted) load of 231,853 lbm, this assessment yie lds a di fference of+0 .02 pe rcen t , wh ich i s w i th in the r c_u i red MPS load ing accuracy o f+ 0.37 percent .

LO loading operat ions were normal through chi l ldown, s low-f i l l , fas t - f i l l ,top p ing and rep len i sh . Based on the ana lys i s o f load ing sys tem da ta , the LOload a t the end o f r ep len i sh was 1 ,388 ,232 lbm. Compared to the inven to ry(p red ic t ed ) load o f 1 ,387 ,828 lbm, th i s a s sessmen t y i e lds a d i ff e rence o f+0 .03 pe rcen t , wh ich i s w i th in the r equ i red MPS load ing accuracy o f 0.43 percent .

Ascen t MPS per fo rmance appeared to be normal . Da ta in d ica te tha t the L0 2 andLH2 pressur izat ion systems performed as planned, and al l net posi t ive suct ionpressure (NPSP) requirements were met throughout the f l ight .

A quick- look determinat ion of vehicle performance was made using vehicleacce le ra t ion and p re f l igh t p ropu l s ion p red ic t ion da ta . F rom these da ta , theaverage f l ight-der ived engine Isp determined for the t ime per iod between SRBsepara t ion and s t a r t o f 3 -g th ro t t l i ng was 4 52 .3 seconds a s compared to an MPStag value of 452.96 seconds.

The LO and LH 2 pressur izat ion and feed systems performed nominal ly, wi th oneexcept ion, and sat isf ied a l l tank ul lage pressure and SSYX inle t NPSPr e q u i r e m e n t s . T h e exception was the SSME 1 GH 2 f low con t ro l va lve whichexh ib i t ed a s low open ing r e sponse t ime (0 .4 to 0 .5 second vs . spec i f i ca t ionr equ i rement o f 0 .3 - second maximum) (F l igh t P rob lem ST S-58-V-04) . Th i s s l ow

open ing r e sponse occur red f rom 2 seconds a f t e r l i f to ff t o 224 seconds a f t e rl i f to ff . The va lve was s lugg i sh fo r 49 o f the 59 cyc les in tha t t ime pe r iod .The pressure decay af ter valve opening was not a s tep funct ion as expected.During postf l ight analysis , contaminat ion was found in the poppet ass . -bly.s imilar to the occurrence on STS-28 on this vehicle .

The he l ium mass 'decay was nomina l ; however, the pneumat ic r egu la to r ou t l e tp ressure decay was fas te r than on p rev ious f l igh t s , a l though the decay was s t i l lwi th in the sys tem spec i f i ca t ion . Th i s cond i t io n may have been caused by anindividual component being out-of-specif icat ion in i ts leakage, and as a resul t ,

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a decay t e s t was pe r fo rmed pos t l and ing . The pos t l and ing decay t e s t showed thesame resu l t s a s the on-orb i t da ta . Troub leshoo t ing showed tha t CV23 ( the SSHE 3LH2 prevalve 3-way solenoid valve) was leaking 38 scims from i ts vent por t whenthe ven t por t was deenerg ized (c losed) . The a l lowable l eakage i s 7 .4 sc ims ;consequent ly, the CV23 valve wil l be replaced. The hel ium system performednominal ly dur ing entry with 55.5 lbm of hel ium used.

Review of the STS-58 umbil ical wel l f i lm showed that one piece of the LOlightning strip was miss ing af ter ET separat ion (Fl ight Problem STS-58-V-10) .This cond i t ion has been no ted on p rev ious f l igh t s . A f ix i s underway to be t t e rsecure the l igh tn ing s t r ips to the ET. No sa fe ty i s sue ex i s t s wi th thel igh tn ing s t r ip coming o ff . Add i t iona l ly, the th in f l ex ib le s t ruc tu re wi l l no timpede umbil ical door c losure should the s t r ip become lodged in the umbil ical

cavity.

R e a c t i o n C o n t r o l S u b s y s t e m

The RCS performed nominal ly in support of the miss ion as wel l as DevelopmentTest Object ive (DTO) 250 - Forward RCS Fl ight Control Surfaces Test - dur ingen t ry. A to ta l o f 3 ,67 4 .2 lbm of RCS prope l l an t s was consumed dur ing themiss ion in add i t ion to the 5 .57 pe rcen t o f OHS prope l l an t s used dur inginterconnect operat ions .

RCS per fo rmance on-orb i t was sa t i s fac to ry. Because o f the co ld a t t i tude and thenecessi ty to f i re the forward RCS thrusters in support of DTO 250 during entry,a concern exis ted that the forward RCS propel lant temperatures might go belowthe Shu t t l e Opera t iona l Da ta Book (SODB) cons t ra in t o f 70F. A re -eva lua t ion o fth is constra int resul ted in the constra int being lowered to 53F during thef l igh t , and th i s t empera tu re was no t exceeded dur ing the f l igh t . The lowes tt empera tu res obse rved on the fo rward pod was 61F fo r the ox id ize r, and 63F fo rthe fuel.

O r b i t a l M a n e u v e r i n g S u b s y s t e m

The OHS per fo rmed nomina l ly. The to ta l f i r ing t ime was 284 .9 seconds fo r thele f t eng ine and 303 . 5 seconds fo r the r igh t eng ine . A to ta l o f 12 ,142 lbm ofprope l l an t s was consumed dur ing the th ree OHS f i r ings and the two pe r iods o f RCSi n t e r c o n n e c t o p e r a t i o n s . T h e f o l l o w i n g t a b l e p r o v i d e s d e t a i l s o f e a c h O H Sf i r ing.

OHSfir ing

Engineused

Time, G.m.t . /HET Fir ingdurat ion,

sec

AVf t /sec

2 Both 291:15:35:04.8 G.m.t. 125.4 197.100 :00 ;41 :54 .8 MET

3 Right 296 :21':4 4 :10.0 G.m.t . 14 .8 19.105:06 :51 :00 .0 MET

Deorbi t Both 305:14:05:30 0 G.m.t. 16 6 266.713.23:12:20.0 MET

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T h e l e f t O H S e n g i n e c h a m b e r p r e s s u r e t r a n s d u c e r f a i l e d o f f - s c a l e l o w a t2 9 1 : 1 4 : 5 3 : 0 6 . 6 G . m . t . , w h i c h w a s a p p r o x i m a t e l y t h r e e s e c o n d s a f t e r m a i n e n g i n ei g n i t i o n f o r l a u n c h ( F l i g h t P r o b l e m S T S - 5 8 - V- 0 3 ) . T h e l o s s o f t h i s m e a s u r e m e n td i d n o t a f f e c t O H S e n g i n e o p e r a t i o n d u r i n g t h e O M S - 2 a n d d e o r b i t m a n e u v e r s .P o s t f l i g h t t r o u b l e s h o o t i n g i s o l a t e d t h e f a i l u r e c a u s e t o t h e s i g n a lc o n d i t i o n e r / a m p l i f i e r f o r t h i s m e a s u r e m e n t .

T h e g a g i n g s y s t e m p e r f o r m a n c e i n t h e o x i d i z e r t a n k s w a s satisfactory; hL' wever,both forward f u e l p r o b e s e x h i b i t e d a n o m a l o u s b e h a v i o r s i m i l a r t o t h a t o b s e r v e do n t h e t h r e e p r e v i o u s m i s s i o n s t h a t t h i s p o d h a s f l o w n .

T h e O H S a f t - f u s e l a g e c e n t e r - c r o s s f e e d o x i d i z e r - l i n e h e a t e r - c o n t r o l l e r A a p p e a r e dt o b e c y c l i n g in a higher- t h a n - e x p e c t e d c o n t r o l b a n d . T h i s c o n d i t i o n h a s b e e no b s e r v e d o n p r e v i o u s O V- 1 0 2 f l i g h t s a n d d i d n o t i m p a c t S T S - 5 8 o p e r a t i o n s .

D a t a f r o m O V- 1 0 2 f l i g h t s s i n c e S T S - 2 8 s h o w t h a t t h e t e m p e r a t u r e c o n t r o l b a n d i sh i g h e r w h e n t h e R C S i s c o n f i g u r e d f o r s t r a i g h t - f e e d o p e r a t i o n s t h a n w h e nc o n f i g u r e d f o r O H S i n t e r c o n n e c t ( i . e . , p r o p e l l a n t f l o w i n g t h r o u g h t h e O H Sc r o s s f e e d l i n e s t o t h e R C S m a n i f o l d s ) . D a t a f r o m o t h e r v e h i c l e s d o n o t s h o w ac o n t r o l h a n d s h i f t w h e n i n t e r c o n n e c t o p e r a t i o n s d a t a a r e c o m p a r e d w i t hs t r a i g h t - f e e d d a t a . T h e S T S - 5 8 c o n f i g u r a t i o n w a s s t r a i g h t - f e e d u n t i l f l i g h t d a y6, while the configuration for the previous two OV-1 02 flights was primarilyinterconnect. After reconfiguring t o i n t e r c o n n e c t o n f l i g h t d a y 6 , t h e c o n t r o lb a n d s h i f t e d d o w n a n d w a s c o n s i s t e n t w i t h p r e v i o u s O V- 1 0 2 f l i g h t s u s i n gi n t e r c o n n e c t o p e r a t i o n s .

P o w e r R e a c t a n t , t o r a g e a n d D i s t r i b u t i o n S u b s y s t e m

T h e 1 6 - t a n k p o w e r r e a c t a n t s t o r a g e a n d d i s t r i b u t i o n ( P R S D ) s u b s y s t e m p e r f o r m e ds a t i s f a c t o r i l y i n p r o v i d i n g 4 , 2 0 8 l b o f o x y g e n a n d 5 3 0 l b o f h y d r o g e n f o re l e c t r i c a l p o w e r g e n e r a t i o n , a n d 2 0 9 l b o f o x y g e n f o r c r e w b r e a t h i n g . T h e E D Oc r y o g e n i c s p a l l e t w a s u s e d f o r t h e s e c o n d t i m e i n a d d i t i o n t o t h e n o r m a l P R S Dtanks to provide t h e c r y o g e n i c s f o r t h i s l o n g - d u r a t i o n m i s s i o n . T h e t a n k s a tl i f t o f f c o n t a i n e d 5 7 6 6 l b m o f o x y g e n a n d 672 lbm of hydrogen, and 1349 lbm ofoxygen and f 4 2 l b m of hydrogen remained at landing.

Data w ere collected f o r t h e O n - O r b i t P R S D C r y o g e n i c H y d r o g e n B o i l o f f D TO ( 4 1 3 ) ,a n d t h e a n a l y s i s o f t h o s e d a t a i s p r e s e n t e d i n t h e D e v e l o p m e n t Te s t O b j e c t i v e ss e c t i o n o f t h i s r e p o r t .

F u e l C e l l P o w e r p l a n t S u b s y s t e m

T h e f u e l c e l l p o w e r p l a n t s u b s y s t e m p e r f o r m e d s a t i s f a c t o r i l y t h r o u g h o u t t h e14-day mission. A t o t a l o f 6 , 0 8 5 k i l o w a t t h o u r s ( k W h ) o f e l e c t r i c a l e n e rg y w a sg e n e r a t e d a t a n a v e r a g e p o w e r l e v e l o f 1 8 . 1 k W a n d l o a d o f 5 9 4 a m p e r e s . I ng e n e r a t i n g t h i s e n e rg y, 5 3 0 l b o f h y d r o g e n a n d 4 , 2 0 8 l b of oxygen w e r e c o n s u m e d .A t o t a l of 4,738 lb o f w a t e r w a s p r o d u c e d b y the fuel cells. Seven fuel cellpurges were performed during t h e c o u r s e o f the mission. The actual fuel cellvoltages at the end of the mission were as predicted for fuel cell 1 and0.1 volt above the predicted level for fuel cells 2 and 3 .

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The fuel cel l 2 oxygen f low meter fa i led off-scale low just as i t had done onSTS-55 (Fl ight Problem STS-55-V-05) . This f low meter wil l be repaired when thefue l ce l l i s r emoved f rom the veh ic l e fo r r e fu rb i shmen t o r to co r rec t a moresignif icant fa i lure .

Auxi l i a ry Power Uni t Subsys tem

The countdown for the October 14, 1993, launch at tempt was s topped af ter APUstar t a t the T-31 second point , and as a resul t , the APUs were shut down af terapproximately 10 1/2 minutes of operat ion.

Fo l lowing the Oc tobe r 18 l aunch , ea r ly ac t iva t ion o f the APU tank / fue l l i ne H2Osystem heaters was required af ter ascent (about 25 minutes ear ly) to avoidvio la t ing the fau l t de tec t ion and annunc ia t ion (FDA) lower l imi t o f 48F. Th i scond i t ion a l so occur red on sys tem 1 on the p rev ious f l igh t o f th i s veh ic le . Thehea te r s opera ted nomina l ly fo l lowing ac t iva t ion . An eva lua t ion to de te rmine thepossibi l i ty of lowering the FDA l imit i s being made.

The fo l lowing t ab le shows the APU run t ime , fue l consumpt ion , and to t a l runn ingt ime for the miss ion.

APU 1 (SIX 409) APU 2

IN 403 APU 3 (SIN 408)F l igh t Phase Time, Fuel Time, Fuel Time, Fuel

min:sec consumption, min: sec consumption, min:sec consumption.,lb lb lb

Oct 14 Sc rub 10:25 36 10:26 36 10:27 34

Ascent 22:14 6 2 22:30 61 22:21 60

FCS checkout 05:48 1 2

En t r a 6 6 : 4 2 138 87:39 18 8 6 6 : 4 3 131

Total a b 88:56 200 110:09 49 94:52 2 0 3notes :

a APU s 1, 2, and 3 ran fo r 22 minu tes , 26 seconds a f t e r l and ing ( touchdown) .b Totals include ascent , FCS checkout , and entry.

Hydraul ics /Vater Spray Boiler Subsystem

The hydrau l i c s /wa te r sp ray bo i l e r NSB) subsys tem per fo rmed sa t i s fac to r i ly

th roughou t the STS-58 miss ion . No in - f l igh t anomal ies were no ted in the reviewand evaluat ion of the data .

VSB data indicate local ized boi l ing may have occurred in each of the VSB coresduring the first launch at tempt when the APU's ran for approximately10 1 /2 minu tes be fo re the l aunch was sc rubbed . Th i s cond i t ion ra i s ed a concernabou t the ven t p lugs be ing popped o ff p remature ly, a l lowing wa te r to be dumpedoverboard . Video , a s we l l a s a visual inspection, revealed that the vent plugsremained seated; therefore , no water was los t .

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No water spray boi ler f reeze-ups were noted dur ing ascent as spray cool ing wasin i t i a t ed nomina l ly. A to ta l o f 13 c i rcu la t ion pump runs were comple ted fo rt he rma l cond i t ion ing wi th on ly one accumula tor r echa rge occur r ing (WSB 3) .

The DTO 414 - AFU Shutdown Test (Sequence A) - was performed fol lowing ascentand the r e su l t s o f tha t DTO a re p resen ted in the Deve lopment Tes t Ob jec t ivesef` ion of th is report .

Fydraul ic system 3 was exercised for f l ight control system checkout andper fo rmed nomina l ly. WSB coo l ing was no t r equ i red because o f the shor t run- t imeof the APU. WSB hea te r opera t ion was nomina l .

Hydraul ics and WSB operat ion was nominal for entry with sat isfactory lubr icat ion( lube) oi l cool ing throughout entry and landing. Post land4^ . .g , a hydraul ics load

tes t was performed with sat isfactory resul ts .

E l e c t r i c a l P o w e r D i s t r i b u t i o n a n d C o n t r o l S u b s y s t e m

The electr ical power dis t r ibut ion and cor. t rol (EPDC) subsystem operatednominal ly throughout the miss ion.

Dur ing the sc rub o f the f i r s t l aunch a t t empt a t 287 :17 :16 G .m. t . , t he g roundpower system fai led to assume the e lectr ical load f rom fuel cel l 2 whent r ans fe r r ing to g round power. A remote sense t e s t , fue l ce l l backfeed t e s t , andcyc l ing o f veh ic l e and g round power con tac t s were pe r fo rmed , a f t e r wh ich powerwas success fu l ly t r ans fe r red . Power t r ans fe r was nomina l dur ing the secondsc rub . Al l g round e lements o f the power t r ans fe r sys tem checked ou tsa t i s fac to r i ly. Tes t s a re be ing pe r fo rmed to de te rmine i f the a f t powercontrol ler assembly (APCA) -5 is a t faul t .

E n v i r o n m e n t a l C o n t r o l a n d L i f e S u p p o r t S y s t e m

The Env i ronmenta l Con t ro l and L i fe Suppor t Sys tem (ECLSS) pe r fo rmed nomina l lythroughout the miss ion.

The ac t ive the rma l con t ro l sys t em (ATCS) pe r fo rmance was sa t i s f ac to ry dur ing themiss ion . The ammonia bo i l e r sys te m secondary A con t ro l l e r was opera ted fo r thef i rs t t ime s ince i t was ins ta l led dur ing the Orbi ter Maintenance Down Per iod(OMDP) . The con t ro l l e r opera ted sa t i s fac to r i ly and con t ro l l ed f reon coo lan tl oop (FCL) t empera tu res to 34 F.

A special cool ing tes t to determine i f the payload bay purge a i r could maintainvehicle cool ing whi le the FCLs were in radiator f low was performed af terl and ing . Normal ly the veh ic le i s dependen t on the g round coo l ing un i t whichin te r faces wi th the FCLs th rough the GSE hea t exchanger. The t e s t unexpec ted lyoccurred when both the pr imary and backup ground cool ing uni ts fa i led forapprox imate ly th ree hours . The purge a i r was main ta ined a t 70F wi th a460-ampere load on the Orb i t e r. The evapora to r ou t l e t t empera tu re s t ab i l i zed a t78F and began to d rop when the purge a i r t empera tu re was dzc reased to 6 5Faf te r the f i r s t hour and then aga in to 60F a f t e r the second hour. Notemperature l imits were exceeded in the crew cabin or the f reon coolant loops.

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The supp ly and was te wa te r subsys tem per fo rmed sa t i s fac to r i ly. Seven supp lywater dumps and seven waste water dumps were performed during the mission. Thesupply water dumps were performed through the nozzle a t an average ra te of1.56 percent /minute (2 .58 lb/min) , and the waste water dumps were performed atan average ra te o f 1 .87 pe rcen t /minute (3 .08 lb /min) . The supp ly wa te r dumpl i ne t empera tu re was ma in ta ined be tween 77 and 107F wi th the ope ra t ion o f thel ine heater, and the waste water dump l ine temperature was maintained between55 and 80F while the vacuum vent l ine temperature was between 59 and 75F.

Data f rom the f i rs t launch at tempt showed that the supply water tank A quant i tywas increasing a t a fas ter ra te than should occur, based on fuel cel l waterproduct ion calculat ions (Fl ight Problem STS-58-V-02) . The condi t ion, while anuisance, was considered acceptable for f l ight and the countdown cont inued.

Af te r the sc rub , the ga l l ey was i so la t ed and t ank A was p res su r i zed, and the rewas no compress ion o f the t ank A be l lows . However, when the ga l l ey i so la t ionva lve was opened , the be l lows d id compress . I t was conc luded tha t a i r haden te red the ga l l ey, bu t tha t no a i r was in supp ly t ank A. When the a i r en te redthe gal ley water tank, i t forced water back into tank A, and this caused thefaster increase discussed in the previous paragraph.

The scenar io fo r a i r en te r ing the ga l l ey began wi th the n i t rogen p ressure be ingremoved from tank A when the quant i ty was low (approximately 5 percent) . Thea t - res t pos i t ion o f the be l lows i s approx imate ly 66 pe rcen t . Wi th no res i s t ingni t rogen pressure the bel lows tend to expand to the a t - res t posi t ion, whichcreates a negat ive pressure in the water s ide of the tank and in the gal ley.The gal ley has two solenoid valves which may act as re l ief valves under thiscond i t ion , a l lowing a i r f low in whi le p reven t ing wa te r f low ou t . As a r e su l t , adecis ion was made to isola te the gal ley for launch.

Afte r l aunch , an in - f l igh t ma in tenance ( IFM) p rocedure was up l inked to a l low thec rew to purge the t r apped a i r f rom the ga l l ey. The ga l l ey ch i l l ad wa te r wasf lushed a t 291 :16 :10 G.m. t . (00 :01 :17 MET) . The ga l l ey n o t wa te r f lush pe r theIFM procedure was completed a t approximately 292:23:00 G.m.t . (01:08:07 MET).The c rew repor ted bubb les in the f low fo r the f i r s t 5 pe rcen t o f the supp ly t ankA quan t i ty dec rease . The c rew a l so s t a t ed tha t the re was no t a s t e o f gas in thewate r t aken a f t e r the f lush . Fo l lowing t he f lush , the supp ly and was te wa te rt anks were dumped . The c rew was asked whe the r they no t i ced a i r in the ho t wa te rd i spensed f rom the ga l l ey. The c rew s ta ted tha t they had no t no t i ced any a i r,but that they were get t ing inaccurate hot-water volumes dispensed when volumesgrea te r than 1 .5 ounces were se lec ted . As a r e su l t , t he c rew se lec ted ho t wa te rd i spenses in 1 .5 -ounce inc rements to p rese rve accuracy o f da ta be ing co l l ec ted

for the f luid and electrolyte s tudy.

Late r in the f l igh t , the c rew repor ted obse rv ing a i r mixed in the ga l l ey ho twa te r d i spenses . The p resence o f a i r a ffec ted the a ccuracy o f d i spenses , and asa resul t , the crew switched to cold water dispenses and heated the water asr equ i red us ing the oven . The ga l l ey wa te r hea te r s were tu rned o ff .

The was te co l l ec t ion sys tem (VCS) pe r fo rmed adequa te ly th roughou t the miss ion .L ikewise , the u r ine moni to r ing sys tem was used sa t i s fac to r i ly th roughou t themission.

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T h e c r e w r e p o r t e d a s m a l l a m o u n t o f f l u i d l e a k i n g a r o u n d t h e o d o r / b a c t e r i af i l t e r c a r v e r s e a l o n t h e V C S ( F l i g h t P r o b l e m S T S - 5 8 - V-0 5 ) a n d p r o v i d e d d o w n l i n kv i d e o o f t h e l e a k a g e . T h i s l e a k w a s o b s e r v e d b y t h e c r e w o n t h r e e e a r l i e ro c c a s i o n s a n d w a s w i p e d u p e a c h t i m e . T h e c r e w a l s o s t a t e d t h a t t h e f i r s t t i m et h i s l e a k w a s o b s e r v e d w a s p r i o r t o t h e g a l l e y h o t - w a t e r f l u s h I F M p r o c e d u r eb e i n g p e r f o r m e d . L i q u i d c a r r y - o v e r f r o m f a n s e p a r a t o r 1 t o t h e o d o r / b a c t e r i af i l t e r l i n e w a s s u s p e c t e d a s t h e c a u s e o f t h e l e a k . F a n s e p a r a t o r 2 w a s s t a r t e da t 2 9 1 : 2 3 : 5 6 : 3 5 C . m . t . ( 0 2 : 0 9 : 0 3 : 2 5 M E T ) a n d n o m i n a l s t a r t - u p c u r r e n t s w e r eo b s e r v e d . T h e c r e w r e p o r t e d t h a t n o f l u i d w a s o b s e r v e d a r o u n d t h e o d o r / b a c t e r i af i l t e r c o v e r. S u b s e q u e n t s t a r t - u p s o f f a n s e p a r a t o r 1 s h o w e d n o s i g n s o f b a c kl e a k a g e t h r o u g h t h e f a n s e p a r a t o r 1 c h e c k v a l v e s . T h e c r e w a l s o r e p o r t e d t h a tf l o w t h r o u g h t h e u r i n a l h o s e h a d n o t c h a n g e d s i n c e t h e f l i g h t b e g a n , i n d i c a t i n gt h a t t h e f i l t e r w a s p r o b a b l y n o t s a t u r a t e d w i t h l i q u i d . A n I F M p r o c e d u r e w a su p l i n k e d t o r e m o v e a n d i n s p e c t t h e o d o r / b a c t e r i a f i l t e r a n d t h e p r o c e d u r e w a sc o m p l e t e d a t 2 9 4 : 1 7 : 5 3 G . m . t . 03:03:00M E T ) . T h e c r e w r e p o r t e d f i n d i n g t h ef i l t e r w e t b u t n o t s a t u r a t e d . T h e 0 - r i n g a t t h e b a s e o f t h e f i l t e r w a si n s p e c t e d a n d f o u n d p r o p e r l y i n s t a l l e d a n d i n t a c t . P r i o r t o t h e i n i t i a t i o n o ft h e I F M p r o c e d u r e , f a n s e p a r a t o r 1 w a s p o w e r e d o n i n a n a t t e m p t t o r e m o v e a sm u c h f l u i d f r o m t h e f i l t e r a s p o s s i b l e . A f t e r c o m p l e t i o n o f t h e I F M p r o c e d u r e ,f a n s e p a r a t o r 2 w a s p o w e r e d u p a n d r e m a i n e d o n u n t i l t h e c r e w w e n t t o s l e e pa b o u t 9 h o u r s l a t e r. N o m o r e f l u i d l e a k a g e w a s n o t e d w h e n t h e c r e w w e n t t osleep. Beginning on flight day 3 f a n s e p a r a t o r 2 w a s u s e d f o r V C S o p e r a t i o n s .U M S o p e r a t i o n s w e r e c o n d u c t e d u s i n g t h e f a n s e p a r a t o r 2 c o n t i n g e n c y p r o c e d u r ew h i c h p r o v i d e d s t e p s f o r t h e c r e w t o m a n u a l l y a c t i v a t e a n d d e a c t i v a t e t h e V C Sf o r U M S o p e r a t i o n s .

A l l a t m o s p h e r i c r e v i t a l i z a t i o n s y s t e m c o m p o n e n t s o p e r a t e d p r o p e r l y t h r o u g h o u tthe mission. The CO 2 p a r t i a l p r e s s u r e w a s m a i n t a i n e d b e l o w 2 . 8 8 m m H g . C a b i na i r t e m p e r a t u r e a n d r e l a t i v e h u m i d i t y p e a k e d a t 8 1 . 3 F a n d 4 8 p e r c e n t ,respectively. Avionics bays 1, 2, and 3 a i r o u t l e t t e m p e r a t u r e s p e a k e d a t1 0 2 . 4 F, 1 0 3 . 7 F, a n d 8 7 . 5 F, r e s p e c t i v e l y. Av i o n i c s b a y 1 , 2 , a n d 3 w a t e rc o l d p l a t e t e m p e r a t u r e s p e a k e d a t 8 8 . 5 F, 9 1 . 5 F, a n d 8 0 . 0 F, r e s p e c t i v e l y.

T h e a t m o s p h e r i c r e v i t a l i z a t i o n p r e s s u r e c o n t r o l s y s t e m ( A R P C S ) p e r f o r m e dn o r m a l l y i n t h e S p a c e l a b p r e a c t i v a t i o n a n d p o s t a c t i v a t i o n t i m e p e r i o d s . T h eS p a c e l a b p r e s s u r e c o n t r o l s y s t e m w a s u s e d d u r i n g a l l o t h e r o n - o r b i t p e r i o d s .T h e r e d u n d a n t c o m p o n e n t c h e c k o f t h e O r b i t e r p r e s s u r e c o n t r o l s y s t e m w a sp e r f o r m e d a n d n o r m a l s y s t e m o p e r a t i o n w a s i n d i c a t e d f o r b o t h s y s t e m s .

D u r i n g t h e r e g e n e r a t i v e c a r b o n d i o x i d e r e m o v a l s y s t e m ( R C R S ) r e c o n f i g u r a t i o n t ot h e s y s t e m 2 c o n t r o l l e r , t h e c r e w r e p o r t e d t h a t t h e O P E R l i g h t o n p a n e l M 0 5 1 Ff a i l e d t o i l l u m i n a t e . T h e i l l u m i n a t i o n o f t h e O P E R l i g h t i s a v i s u a l i n d i c a t i o n

t h a t t h e s e l e c t e d c o n t r o l l e r i s o p e r a t i o n a l . D o w n l i n k e d d a t a i n d i c a t e t h a t t h eR C R S w a s o p e r a t i n g n o m i n a l l y. T h e c r e w p e r f o r m e d a l a m p t e s t o f t h e R C R S s y s t e m2 c o n t r o l l e r O P E R l i g h t a n d t h e l a m p f a i l e d t o i l l u m i n a t e . T h e c r e w p u s h e d t h eO P E R l a m p a s s e m b l y f u l l y i n a n d t h e O P E R l i g h t i l l u m i n a t e d . A l l R C R S i n d i c a t o rl i g h t s o p e r a t e d n o m i n a l l y f o r t h e r e m a i n d e r o f t h e m i s s i o n .

Smoke Detect ion and Fire Suppression

T h e s m o k e d e t e c t i o n s y s t e m s h o w e d n o i n d i c a t i o n s o f s m o k e g e n e r a t i o n d u r i n g t h ef l i g h t . U s e o f t h e f i r e s u p p r e s s i o n s y s t e m w a s n o t r e q u i r e d .

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Pi r lock Suppor t Sys tem

Use of the a i r lock support components was not required because no extravehicularac t iv i ty (EVA) was p lanned o r pe r fo rmed . Al l a i r lock sys tem paramete r s r emainedwithin normal ranges throughout the f l ight .

Avionics and Software Support Subsystems

The in tegra ted gu idance , nav iga t ion , and f l igh t con t ro l subsys tems pe r fo rmedsa t i s fac to r i ly. The subsys tems were used to pe r fo rm DTO 250 - Forward RCSFl igh t Tes t -Con t ro l Sur face Effec t s , and the da ta a re be ing ana lyzed .

The ine r t i a l measurement un i t s ( IMUs) pe r fo rmed nomia l ly th roughou t the f l igh t ,and the ship set i s considered acceptable for the next f l ight of th is vehicle .Maximum a l ignment e r ro rs a t l i f to ff were 25 a rc seconds in the A and B axes , and125 a rc seconds in the C ax i s . Vhi l e on o rb i t , t he IMU in s lo t 1 was moded tos tandby in accordance with the planned Group B power down at 291:15:52 G.m.t .(00 :00 :59 MET) . The un i t was re tu rned to opera te a t 305 :09 :42 G.m. t .(13:18:49 MET).

Also , a t 295 :03 :07 :55 G .m. t . (03 :12 :14 :45 MET) mul t ip l exe r /demul t ip l exer (MDM)FF2 shu t down due to an inadver ten t swi tch ing o f the power. Th i s cond i t ion intu rn caused the IMU in s lo t 2 to mode to s t an dby. The MDM was rese t and the IMUre tu rned to opera te , and subsequen t ly was a l igned wi th the IMU in s lo t 3s ix minu tes a f t e r the MDM shu tdown. The cond i t ion d id no t impac t subsequen tf l ight operat ions .

Likewise , t : i a s t a r t r acker pe r fo rmance was sa t i s fac to ry. The da ta p rocess ingsys tem (DPS) ha rdware and f l igh t so f tware pe r fo rmance was exce l l en t wi th noanomalies ident i f ied.

The d i sp lays and con t ro l s subsys tem, wi th the excep t ion o f the f lood l igh t s ,opera ted sa t i s fac to r i ly. The a f t por t and e i t he r the fo rward por t o r a f ts t a rboard f lood l igh t s had anomalous da ta t r aces dur ing pay load bay door c losureac t iv i t i e s . The pos t f l igh t inspec t ion s showed ev idence o f a rc ing in the fo rwardpor t and a f t po r t f lood l igh ts .

Communica t ions and Track ing Subsys tems

The communica t ions and t r ack ing subsys tems pe r fo rmed nomina l ly excep t fo r theproblems and anomalies discussed in the fol lowing paragraphs.

The second at tempt to launch the STS-58 f l ight occurred on October 15, 1993, butwas scrubbed because the Orbi ter S-band t ransponder 2 failed (F l igh t P rob lemSTS-58-V-01) , and loss o f th i s S -band t r ansponder was a LCC v io la t ion . As aresu l t , a sc rub tu rna round was in i t i a t ed to r ep lace the S-band t r ansponder, andthe launch was rescheduled for October 18, 1993.

The c rew repor ted hea r ing a beep ing sound when us ing the Space lab wi re less c rewcommunica t ions sys tem (VCCS) aud io in te r face un i t (AIU) -D in bo th thein te rcommunc ia t ion ( ICOM) and a i r- to -g round (A/G) modes (F l igh t P rob lemSTS-58-V-06) . The beep ing sound cou ld no t be reproduced whi le us ing the samecrew remote un i t (CRU) wi th ano the r wa l l un i t , and ba t t e ry rep lacement on the

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C R U s c o m m u n i c a t i n g w i t h A I U - D d i d n o t c l e a r t h e p r o b l e m . T h e c r e w a l s o s t a t e dt h a t t h e b e e p i n g t o n e d i d n o t s o u n d l i k e t h e b a t t e r y - l o w w a r n i n g . A s a r e s u l to f t h e A I U - D a n o m a l y, a c o m m u n i c a t i o n s y s t e m r e c o n f i g u r a t i o n p r o c e d u r e w a sp e r f o r m e d . T h i s p r o c e d u r e c o n n e c t e d t h e O r b i t e r V C C S A I U - C o n t h e m i d d e c k t ot h e P i l o t a u d i o t e r m i n a l u n i t ( AT U ) o n t h e f l i g h t d e c k a n d e n a b l e d t h e S p a c e l a bc r e w t o u t i l i z e A I U - C a n d d e a c t i v a t e A I U - D .

T h r o u g h o u t m o s t o f t h e f l i g h t , f r e q u e n c y m o d u l a t i o n ( F M ) t r a n s m i t t e r 1 w a s u s e db u t s h o w e d a s t e a d y d e c r e a s e i n p o w e r o u t p u t f ^ , m 1 5 w a t t s t o 1 3 . 5 w a t t s , w h i c h w a s s t i l l w i t h i n s p e c i f i c a t i o n l i m i t s . D u r i n g t h e O p e r a t i o n s R e c o r d e r d u m p o nf l i g h t d a y 1 3 a t 3 0 4 : 2 1 : 1 0 : 3 2 G . m . t . ( 1 3 : 0 6 : 1 6 : 5 2 M E T ) , t h e o u t p u t r a p i d l yd e c a y e d t o 6 . 5 w a t t s , w h i c h i s b e l o w t h e s p e c i f i c a t i o n l i m i t o f 1 0 w a t t s ( F l i g h tP r o b l e m S T S - 5 8 - V-0 8 ) . A s a r e s u l t , F M t r a n s m i t t e r 2 w a s s e l e c t e d f o r t h er e m a i n d e r o f t h e f l i g h t . P o s t f l i g h t i n s p e c t i o n v e r i f i e d t h a t t h e t r a n s m i t t e rh a d f a i l e d a n d i t w a s r e p l a c e d .

P e r f o r m a n c e o f t h e t h e r m a l i m p u l s e p r i n t e r s y s t e m ( T I P S ) w a s n o m i n a l w i t h t h ee x c e p t i o n o f a p a p e r j a m . T h e c r e w r e p o r t e d t h a t t h e p a p e r - f a u l t i n d i c a t o r w a si l l u m i n a t e d a n d t h a t p a p e r h a d f e d b a c k o n i t s e l f . I t i s b e l i e v e d t h a t t h ep a p e r w a s s l i g h t l y m i s a l i g n e d . T h e c r e w w a s a b l e t o q u i c k l y c l e a r t h e c o n d i t i o na n d t h e u n i t c o n t i n u e d t o o p e r a t e n o m i n a l l y. A t o t a l o f 3 6 2 p a g e s w e r e u p l i n k e dt h i s m i s s i o n v i a t h e K u - b a n e i n t e r f a c e . T h e a u d i o i n t e r f a c e o f t h e T I P S w a s n o tus ed t h i s m i s s ion .

At 301: 0 2 : 0 2 G . m . t . ( 0 9 : 11 : 0 9 M E T ) , t h e p a y l o a d r e c o r d e r w a s r e c o r d i n g o n t r a c k9 i n t h e S e r i a l R e c o r d B m o d e a n d t h e r e c o r d e r p e r c e n t - t a p e i n d i c a t o r r e a d96.77 p e r c e n t . V h e n t h e r e c o r d e r r e a c h e d t h e e n d - o f - t a p e E O T ) a n d w a s

p e r f o r m i n g i t s n o r m a l t u r n a r o u n d , t h e p e r c e n t - t a p e r e a d i n g w e n t t o 0 p e r c e n t ,t h e b e g i n n i n g - of-tape B O T ) a n d E O T i n d i c a t i o n s w e r e b o t h p r e s e n t s i m u l t a n e o u s l yi n t h e d a t a , a n d t h e t r a c k i d e n t i f i c a t i o n w e n t t o t r a c k 1 4 i n s t e a d o f t r a c k 1 0( F l i g h t P r o b l e m S T S - 5 8 - V- 0 7 ) . T h i s i s a s t r o n g i n d i c a t i o n t h a t t h e r e c o r d i n gt a p e h a d b r o k e n i n t h e p a y l o a d r e c o r d e r. . T h e m i s s i o n i m p a c t w a s t h e l o s s o f t h ea b i l i t y t o r e c o r d t h e r a w O A R S d a t a ; h o w e v e r , s e m i - p r o c e s s e d O A R E d a t a w e r eb e i n g s a v e d i n t h e O A R E m e m o r y.

Structures and Mechanical Subsystems

A l l s t r u c t u r a l a n d m e c h a n i c a l s u b s y s t e m s p e r f o r m e d s a t i s f a c t o r i l y w i t h n op r o b l e m s o r a n o m a l i e s i d e n t i f i e d . T h e l a n d i n g a n d b r a k i n g d a t a a r e p r e s e n t e d i nt h e f o l l o w i n g t a b l e .

T h e d r a g c h u t e a p p e a r e d t o h a v e f u n c t i o n e d p r o p e r l y. A l l d r a g c h u t e h a r d w a r e

w a s r e c o v e r e d a n d s h o w e d n o s i g n s o f a b n o r m a l o p e r a t i o n . S i x d a m a g e s i t e s w e r eo b s e r v e d o n t h e v e r t i c a l t a i l s t i n g e r d r a i n t i l e , a n d t h e s e w e r e p r o b a b l y c a u s e db y t h e c h u t e r i s e r l i n e s d u r i n g d e p l o y m e n t .

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LANDING AND BRAKING PARAMETERS

FromParamete r threshold . Speed, Sink ra t e , f t / s ec Pitch rate,

f t keas de /src

Hain gea r touchdown 3380 198.7 `2 .0 n/aNose gea r touchdown 6 9 4 8 155.5 n/a 3.16

Braking ini t ia t ion speed

29.9 knots (keas)

Brake-on t ime 42 .8 seconds (sus ta inedp

Rol lou t d i s t ance 9 ,640

eetRol lou t t ime 60 .9 seconds

Runway 22 concrete) at EAFBOrbi ter weight a t l and ing 29,116 b ( landing es t imate)PeakBrake sensor loca t ion pressure , Brake assembly Energy,rs ia million ft-lbLeft-hand inboard 1 1176 Left-hand outboard 26.52Left-hand inboard 3 1128 Left-hand inboard 27.29Left-hand outboard 2 1092 Right-hand inboard 14.04Left-hand outboard 4 1104 Right-hand outboard 16.26Right-hand inboard I 7 0BRight-hand inboard 3 6 7 2

Right-hand outboard 2 756Right-hand outboard 4 7 6 8

Aerodynamics , Hea t ing , and Thermal In te r faces

Ascen t ae rodynamics were nomina l wi th no unexpec ted cond i t ions no ted . Twoaerodynamic DTOs were performed (DTO-236 - Ascent Ving Aerodynamic Distr ibutedLoads Verif icat ion on OV-102, and DTO-253 - Elevon Deflect ion Load Sensi t ivi tyVerif icat iot . ) , and the prel iminary resul ts are presented in the Development TestObject ives sect ion of th is report .

Ent ry ae rodynamics were nomina l . Ana lys i s showed tha t con t ro l su r face pos i t ionsand ang le -o f -a t t ack compared we l l wi th p re f l igh t p red ic t ions . DT O 250 - ForwardRCS F l igh t Tes t - was pe r fo rmed sa t i s fac to ri ly dur ing en t ry a t Hach 4 wi th noprob lems no ted . P re l iminary ana lys i s o f veh ic le r e sponse compares we l l wi th theSTS-45 f l ight when the same DTO was performed.

Da ta r e f l ec t nomina l ae rodynamic and p lume hea t ing dur ing a scen t and en t ry.

Thermal Con t ro l Subsys tem

The pe r fo rmance o f the the rmal con t ro l subsys tem was nominal during al l phasesof the miss ion and a l l Orb i t e r subsys tem tempera tu res were main ta ined wi th inaccep tab le l imi t s .

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T h e O M S a f t f u s e l a g e c e n t e r c r o s s f e e d o x i d i z e r l i n e h e a t e r c o n t r o l l e r A a p p e a r e dt o b e o p e r a t i n g i n a h i g h e r c o n t r o l b a n d t h a n e x p e c t e d . T h i s c o n d i t i o n h a s b e e no b s e r v e d o n p r e v i o u s O V- 1 0 2 f l i g h t s a n d d i d n o t i m p a c t S T S - 5 8 o p e r a t i o n s .

A e r o t h e r m o d y n a m i c s

L o c a l h e a t i n g d u r i n g e n t r y w a s n o m i n a l , a l t h o u g h a l e a k a g e f l o w p a t h m a y h a v ee x i s t e d a r o u n d t h e r i g h t o u t b o a r d m a i n l a n d i n g g e a r d o o r. S o m e o v e r - h e a t i n g w a sn o t e d i n a 5 - i n c h l o n g b y 0 . 6 - i n c h d e e p a r e a o f t h e d a m a g e o n t h e l o w e rm i d f u s e l a g e .

A c r e a g e h e a t i n g w a s w i t h i n l i m i t s a n d t h e t e m p e a t u r e r i s e w a s w i t h i n t h ee x p e r i e n c e d a t a b a s e . T P S d a m a g e w a s a l s o w i t h i n t h e e x p e r i e n c e b a s e .

T h e r m a l P r o t e c t i o n S u b s y s t e m

T h e T P S p e r f o r m e d s a t i s f a c t o r i l y. S t r u c t u r a l t e m p e r a t u r e r e s p o n s e d a t a s h o wt h a t t h e e n t r y h e a t i n g w a s a v e r a g e , a n d t h e T P S p e r f o r m e d s a t i s f a c t o r i l y a n dp r e v e n t e d h e a t i n g d a m a g e e f f e c t i v e l y t h r o u g h o u t a s c e n t a n d e n t r y. T h e o v e r a l lb o u n d a r y l a y e r t r a n s i t i o n f r o m l a m i n a r f l o w t o t u r b u l e n t f l o w o c c u r r e d11 5 0 s e c o n d s a f t e r e n t r y i n t e r f a c e o n t h e f o r w a r d c e n t e r l i n e o f t h e v e h i c l e . a n d1145 s e c o n d s a f t e r e n t r y i n t e r f a c e o n t h e a f t c e n t e r l i n e o f t h e v e h i c l e .

Vi d e o s f r o m t h r e e c a m e r a s m o n i t o r i n g t h e l a u n c h a n d t h e a s c e n t p h a s e s h o w e d as i n g l e w h i t e p i e c e o f d e b r i s n e a r S S M E 1 a b o u t 4 5 s e c o n d s a f t e r l i f t o f f ( F l i g h tP r o b l e m S T S - 5 8 - V-0 9 ) . F i l m a n a l y s i s s h o w e d a f l e x i b l e , w h i t e o b j e c t e x i t i n g t h ea r e a b e t w e e n S S M E 1 a n d 3 a t t h e s a m e t i m e . T h e o b j e c t f e l l a f t i n t o t h e p l u m ea n d a f l a s h i n t h e p l u m e w a s n o t e d a b o u t 1 s e c o n d a f t e r t h e o b j e c t w a s s i g h t e d .E s t i m a t e s o f t h e o b j e c t ' s s i z e r a n g e d f r o m 1 4 b y 15 i n ches t o 26 by 11 i nches .A n a l y s i s i n d i c a t e d t h a t t h e o b j e c t w a s p r o b a b l y a p i e c e o f t h e D M H S c l o s e o u tb l a n k e t , b a s e d o n p a s t h i s t o r y o f D M H S b l a n k e t d a m a g e axid t h e ob j ec t ' s appa ren ts i z e , s h a p e , c o l o r , a n d a r e a o f o r i g i n . A p o s t l a n d i n g i n s p e c t i o n s h o w e d t h eS S M E 3 D M H S b l a n k e t w a s b a d l y t o r n f r o m 8 o ' c l o c k t o 1 0 o ' c l o c k . M u c h o f t h eb l a n k e t s o u t e r c o v e r a n d b a t t i n g w a s m i s s i n g , b u t t ; : . i n n e r f a b r i c w a s i n t a c t .T h e S S M E 2 D M H S b l a n k e t w a s a l s o t o r n a t t h e 3 o ' c l o c k p o s i t i o n s , b u t i t s o u t e rc o v e r w a s still intact.

Overall debris d a m a g e w a s a b o v e a v e r a g e w i t h t h e O r b i t e r T P S s u s t a i n i n g a t o t a lo f 1 5 5 h i t s o f w h i c h 2 6 h a d a m a j o r d i m e n s i o n o f o n e i n c h o r g r e a t e r. O f t h et o t a l h i t s , 7 8 w e r e o n t h e l o w e r s u r f a c e , 4 3 w e r e o n t h e u p p e r s u r f a c e , 1 9 w e r eo n t h e r i g h t s i d e , 3 w e r e o n t h e l e f t s i d e , a n d 1 2 w e r e o n t h e O M S p o d s . N o T P Sd a m a g e w a s a t t r i b u t e d t o m a t e r i a l f r o m t h e w h e e l s , t i r e s , o r b r a k e s .

O n e l a rg e d a m a g e s i t e ( 5 i n c h e s b y 2 i n c h e s b y 0 . 6 i n c h d e e p ) w a s located justforward and outboard of the right - h a n d E T d o o r. T h e t i l e w a s f r a c t u r e d t h r o u g ht o t h e s t r a i n i s o l a t i o n p a d ( S I P ) . T h e e x p o s e d t i l e s u b s t r a t e w a s m e l t e d , a n dt h e t i l e c o a t i n g w a s c u r l e d a n d p e e l e d a t t h e a f t p o r t i o n o f t h e d a m a g e a r e a .T h e t i l e w a s n o n - d e s t r u c t i v e l y r e m o v e d f r o m t t : v e h i c l e f o r a n a l y s i s .I n s p e c t i o n o f t h e r e m o v e d t i l e i n d i c a t e d t h a t a s m a l l s e c t i o n o f t h e SIP,approximately o n e - h a l f i n c h i n d i a m e t e r , w a s y e l l o w e d b e c a u s e o fo v e r - t e m p e r a t u r e c o n d i t i o n s a t t h a t l o c a t i o n . T h e d i s c o l o r a t i o n w a s l o c a t e db e l o w t h e m o l t e n p o r t i o n o f t h e t i l e . T h e a f t e d g e o f t h e SIP was also

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d i s c o l o r e d , i n d i c a t i n g t h a t t h e d a m a g e a l l o w e d f l o w t o p e n e t r a t e b e y o n d t h e g a pf i l l e r a n d c o n t i n u e b e t w e e n t h e S I P a n d t h e f i l l e r b a r. A s l i g h t l y o r a n g e - r e dd i s c o l o r a t i o n . w a s n o t e d o n a p o r t i o n o f t h e u n m e l t e d e x p o s e d t i l e s u b s t r a t e .

T h e p r i m a r y n o s e l a n d i n g g e a r d o o r ( N L G D ) t h e r m a l b a r r i e r w a s i n g o o d c o n d i t i o no v e r a l l , w i t h s e v e r a l f r a y e d p a t c h e s n o t e d . A l a rg e p o r t i o n ( 6 i n c h b y 4 i n c h )o f t h e i n b o a r d a f t c o r n e r t i l e o n t h e r i g h t - h a n d N L G D w a s b r o k e n o f f , a n d t h et i l e , a l t h o u g h f r a c t u r e d , w a s s t i l l i n t a c t . S i m i l a r d a m a g e t o t h i s t i l e h a so c c u r r e d o n p a s t m i s s i o n s .

A l l t h r e e E T / O r b i t e r s e p a r a t i o n d e v i c e s a p p e a r e d t o h - v e f u n c t i o n e d p r o p e r l y.T h e E T / O r b i t e r u m b i l i c a l o r d n a n c e r e t e n t i o n s h u t t e r s w e r e c l o s e d p r o p e r l y, a n dn o f l i g h t h a r d w a r e w a s f o u n d o n t h e r u n w a y b e l o w t h e E T d o o r s .

A l l O r b i t e r w i n d o w s e x h i b i t e d t y p i c a l h a z i n g w i t h w i n d o w 3 h a v i n g t h e m o s t h a z e .

T h e t h e r m a l i m a g e r w a s u s e d t o m e a s u r e s u r f a c e t e m p e r a t u r e s o n s e v e r a l a r e a s o ft h e O r b i t e r. A t 2 0 m i n u t e s a f t e r l a n d i n g , t h e O r b i t e r n o s e c a p r e u s a b l ec a r b o n - c a r b o n ( R C C ) t e m p e r a t u r e w a s 1 7 0 F, t h e r i g h t w i n g l e a d - g e d g e R C Cp a n e l 9 t e m p e r a t u r e w a s 8 8 F, a n d t h e p a n e l 1 7 t e m p e r a t u r e w a s 7 8 F.

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FLIGHT CREST EQUIPMENT/GOVERN4ENT FURNISHED EQUIPMENT

The f l igh t c rew equ ipment and Government fu rn i shed equ ipmen t (GFE) pe r fo rmednominal ly throughout the miss ion with no problems reported.

C RGO INTEGR TION

All cargo integrat ion hardware operated sat isfactor i ly throughout the miss ion.

DEVELOPMENT TEST OBJECTIVES/DETAILED SUPPLEMENTARY OBJECTIVES

A tota l of 16 development tes t object ives (DTOs) and 19 detai led supplementaryobjec t ives (DSOs) was ass igned to the STS-58 miss ion . P re l iminary ana lys i sindicates that data were col lected for a l l TO s and DSOs.

DEVELOPMENT TEST OBJECTIVES

The p re l imina ry r e su l t s o f the 16 DTOs a re p resen ted in the fo l lowingsubparagraphs.

DTO 236 - Ascent Wing Aerodynamic Dis t r ibuted Loads Veri f icat ion on OV-102 -STS-58 was the las t in a ser ies of e ight OV-102 f l ights on which DTO 236 wasper fo rmed . Wing loads da ta ( ex te rna l p ressures and in te rna l s t r a ins ) wereco l l ec ted dur ing ascen t . The t r a j ec to ry f lown inc luded a nega t ive ly b iasedangle-of-at tack prof i le dur ing the high dynamic pressure por t ion(Mach - 0 .8 to 1 .8 ) . P re l iminary ind ica t ions a re tha t a l l DTO ob jec t ives fo rth i s f l igh t were accompl i shed . The da ta co l l ec ted dur ing th i s e igh t - f l igh tprogram wil l be used to update the ascent aerodynamic loads database, which wil lbe base l ined in November, 1994 . The resu l t s o f the ana lys i s wi l l be r epor ted inseparate documentat ion.

DTO 250 - Forward RCS Fl ight Test - Control Surface Effects - Data were recordedfo r th i s DTO dur ing ascen t . The da ta have been g iven to the sponsor and theresul ts of the evaluat ion wil l be reported in separate documentat ion.

DTO 253 - Elevon Deflect ion Load Sensi t iv i ty Veri f icat ion for OV-102 - TheST S-58 f l igh t i s the f i r s t , l a s t , and on ly f l i gh t in suppor t o f DTO 253 . Forth i s f l igh t , an o ff -nomina l a scen t e l evon schedu le was f lown. The schedu lef lown was more cons i s t en t wi th the 6 .0 Loads Cer t i f i ca t ion schedu le and shou ldr e su l t in dec reased wing loads wi th s l igh t ly l a rge r e l e von h inge moments . Bo thinboard and ou tboard e levon schedu les were modi f i ed . The ascen t wing loadsf l ight measurements wi l l be evaluated against the exis t ing data base to ver i fyaccuracy o f e l evon load sens i t iv i ty. Based on the resu l t s o f th i s f l igh t , amodi f i ed e levon schedu le wi l l be cons ide red fo r fu tu re f l igh t s . The resu l t s o fthe evaluat ion Will be reported in separate documentat ion.

DTO 301D - Ascent Structural Capabi l i ty Evaluat ion - Data were col lected duringascen t fo r th i s DTO. The da ta have been g iven to the sponsor fo r eva lua t ion ,and the resul ts of that evaluat ion wil l be reported in separat- documentat ion.

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STS-58 Space Shuttle Mission Report

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Transcript of STS-58 Space Shuttle Mission Report