sts-45 space shuttle mission report

8/7/2019 STS-45 Space Shuttle Mission Report

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NASA CR7193 54

, 9

NSTS 08275

5T5 45SPACE SHUTTLEMISSION REPORT

NASA CR 193 541993 1677

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L y 992

~ ~ i i ~ ~ R ~i ~ ~


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_

STS 45

SPACE SHUTTLE

MISSION REPORT

NSTS 08275


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STS 45 Table of Contents

Tit le

INTRODUCTION

MISSION SUMM RY

VEHICLE PERFORM NCE . SOLID ROCKET BOOSTERS REDESIGNED SOLID ROCKET MOTORSEXTERNAL T N K SPACE SHUTTLE M IN ENGINE SHUTTLE R NGE SAFETY SYSTEM . . . ORBITER VEHICLE SUBSYSTEMS

Main Propulsion System Reaction Control Subsystem Orbital Maneuvering Subsystem Power Reactant Storage and Distribution SubsystemFuel Cell Powerplant Subsystem . Auxiliary Power Unit Subsystem Hydraulics Yater Spray Boiler Subsystem . . .Electr ical Power Distribution and Control Subsystem.Pyrotechnics Subsystem . Environmental Control and Life Support SubsystemSmoke Detection and Fire Suppression Airlock Support System Avionics and Software Subsystems Communications and Tracking SubsystemOperat ional In s trumen ta t ion Structures

and Mechanical Subsystems . Aerodynamics Heating and Thermal InterfacesThermal Control Subsystem Aerothermodynamics . Thermal Protection Subsystem

1

2

4

477

899

91011

12121213131314151516161616


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Table of Contents Concluded

Ti t l e

DEVELOPMENTTEST OBJECTIVES ND DETAILED SUPPLEMENT RYOBJECTIVES

DEVELOPMENTTEST OBJECTIVES . . .DETAILED SUPPLEMENT RY OBJECTIVES

PHOTOGRAPHIC ND TELEVISION ANALYSIS .L UNCH PHOTOGR PHY EV LU TION L NDING PHOTOGR PHY EV LU TION . .

i s t of Tables

Ti t l e

TABLEI -

STS 45SEQUENCE OF EVENTS

T LE - STS 45 PRO LEM TR CKING LIST

3

3

5 5 5

Page

6

29


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INTRODUCTION

The STS-45 Space Shuttle Program Mission Report contains a summary of thevehicle subsystem operations during the forty-sixth fl ight of the Space ShuttleProgram and the eleventh fl ight of th e Orbiter vehicle Atlantis OV-104). Inaddition to the Atlantis vehicle, the fl ight vehicle consisted of an ExternalTank ET) designated as ET-44 LVT-37); three Space Shuttle main engines SSME s), which were se r ia l numbers 2024, 2012, and 2028 in positions, 1, 2, and3, respectively; and two Solid Rocket Boosters SRB s) des igna ted as BI-049.

The lightweight redesigned Solid Rocket Motors RSRM s) installed in each of theSRB s were designated as 360L021A fo r th e l e f t SRM and 360V021B fo r th e r ightSRM

This report sat isf ies the Space Shuttle Program requirement, as documented inNSTS 07700, Volume VIII, Appendix E, which requires each major organizationsupporting the Space Shuttle Program to report th e results of i t s evaluation ofthe mission and identify a l l related in-f l ight anomalies.

The primary objective of this mission was to successfully perform the plannedoperations of th e Atmospheric Laboratory for Applica tions and Science-1 ATLAS-1) and th e Shuttle Solar Backsca tter Ultraviolet Instrument SSBUV)payloads. The secondary objectives were to successfully perform a l l operationsn ece ss ary to support th e requirements of th e Space Tissue Loss-01 STL-Ol)experiment, Radiation Monitoring Equipment-III RME-III) experiment, VisualFunction Tester-2 VFT-2) experiment, Cloud Logic to Optimize use of DefenseSystem CLOUDS-1A) experiment, Shuttle Amateur Radio Experiment I I SAREX-II)Configuration B, Inves tigat ion into Polymer Membranes Processing experiment; and

th e Get-Away Special GAS) payload G-229. The Ultraviolet Plume Instrument UVPI) was a payload of opportunity that required no special maneuvers. Inaddition to th e primary and secondary objectives, th e crew was tasked to performas many as 10 Development Test Objectives DTO S) and 14 Detailed SupplementaryObjectives DSO s)


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SU RY

During the STS-45 launch countdown for the March 23 launch attempt, the liquidoxygen L0 2) concentration in the af t compartment peaked at 860 ppm during th eslow f i l l operation. This level exceeded the Launch Commit Criteria LCC l imitof 500 ppm. The L02 concentration had decreased to 200 ppm beforetroubleshooting began. The l iquid hydrogen LH2) concentration in the a f tcompartment peaked a t 750 ppm during the fast fl11, a level which alsp exceededthe L l imi t . As a resul t , the LH2 flow was stopped, and the LH2 concentration

decreased to 100 ppm. After the L02 leak isolation tes t , similar LH2 leakisolation procedures were also performed. After extensive t roubleshoot ing, theLH2 leak could not be isolated and

i t did not recur thereafter. However, thetroubleshooting act ivi t ies for the L02 and LH2 concentration levels resulted inthe launch being rescheduled fo r Marcfi 24, 1992.

During the countdown to the launch on March 24, the L02 concentration againexceeded the L value, but rapidly recovered to within the L l imi t . Thisbehavior was anticipated and acceptable pe r a preflight agreement, and the

loading continued . The LH2 concentration never exceeded the LCC l imi t duringthis second countdown.

The STS-45 mission was launched from Kennedy Space Center KSC launch complex39 A at 8:13:40 a.m. e s t 084:13:13:39.991 G.m.t. on March 24, 1992. Thelaunch phase was satisfactory with no Orbiter anomalies noted. The launch wasdelayed 13 minutes 40 seconds because of unacceptable weather conditions on t h ~approach to th e return-to-launch-site RTLS runway Shutt le Landing Faci l i ty .

The to ta l vehicle weight at l i f t - o ff was 4,495,720 lb . The Orbiter weight a tthat time was 233,652 Ib of which the payload comprised 20,371 lb .

All SSME and RSRM s ta r t sequences occurred as expected and launch phaseperformance was satisfactory in l l respects Firs t stage ascent performance


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MECO underspeed condition, th e orbi ta l in-plane thrust from th e main propulsion

system MPS dump was less than planned because of the early at t i tude maneuverthat was made to observe and photograph the ET in fulfillment of DTO 312 - ETThermal Protection System Performance. As a result of these two conditions, asingle engine OMS-3 maneuver of 12.0 f t / sec was performed at 084:16:03:42.8G.m.t. 00:02:50:03 MET to circularize the orbit a t 160 nmi.

At 084:20:41 G.m.t. 00:07:01 MET , the APU fuel pump/gas generator B systemheaters were activated. The APU 2 and 3 systems operated properly; hpweverno response was noted from the APU 1 gas generator bed heater. As a resul t , the

APU system A heaters were activated. After verifying proper operation of th eAPU 1 A heaters, the B heaters were reactivated, and af ter two abnormal cycles,proper operation began. After three days of nominal operation, the APU 1 gasgenerator bed heater anomaly recurred with three abnormal heater cycles temperatures dropped into the mid-200-degree range but should have cycled onat; H 5 OF , each of which was separated by several normal heater cycles. TheAPU heaters were reconfigured to the A system fo r th e remainder of the missionin an attempt to i sola te the intermittent component. The controller containscircui t ry that is common to both th e A and B heater systems. No recurrence of

the heater anomaly was observed while operating on th e A heaters.Based on actual in-f l ight cryogenics usage data for the f i r s t five days inc on ju nc ti on w ith th e co nce rte d effort made by the f l ight crew to conservecryogenic consumables th e mission contingency extension capability hadincreased to greater than 3 days. On the morning of the sixth day the MissionManagement Team MMT decided to add a ninth day to th e planned mission so thatadditional scient i f ic data could be obtained.

Results of the f l ight control system FCS checkout using improved auxil iarypower unit IAPU 2 were satisfactory. The APU operated for 5 minutes 3seconds and no water spray boiler cooling was required. The hydraulicssubsystem operated nominally as did the improved APU.


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Main landing gear touchdown occurred at Kennedy Space Center Shuttle Landing

Faci l i ty runway 33 a t 093:11:23:05 G.m.t . 08:22:09:25 MET) on April 2, 1992.Nose landing gear touchdown occurred 8 seconds l a te r with wheels stop at093:11:24:04 G.m.t. The rollout was normal in a l l respects. The f l ightduration was 8 days 22 hours 10 minutes 24 seconds. The APU s were shut down by093:11:38:10.02 G.m.t. and the crew completed the required postfl ightreconfigurations and d ep art ed t he Orbiter landing area at 093:13:03:40 G.m.t. 7:03:40 a.m. e s t

VEHICLEPERFORM NCE

SOLID ROCKET BOOSTERS/REDESIGNED SOLID ROCKET MOTORS

Al l SR systems performed as expected throughout ascent. Al l SR thrust vectorcontrol prelaunch conditions and f l ight performance requirements were met withample margins. All electr ical functions were performed properly. No SRB orRSRM LCC or Operations and Maintenance Requirements and Specification Document

OHRSD) violations were identif ied.Power-up and o pe ra ti on o f a l l case igni ter and f ie ld- joint heaters wasaccomplished routinely. Al l RSRH temperatures were maintained within acceptablel imits throughout th e countdown. For this f l ight th e h eate d purge in the SRaf t sk ir t was powered up and the case/nozzle jo in t and f lexible bearingtemperatures were maintained within the required LCC ranges.

RSRH thrust different ia ls during the bui ldup s teady s ta te and ta i loff phases

were w el l w it hi n specifications. TheSR

prelaunch countdown was normal, and noSRB or RSRH in-f l ight anomalies were identif ied. The SRB f li gh t s tr uc tu ra ltemperature response was as expected. Postfl ight inspection of the recoveredhardware indicated that th e SRB thermal protection system TPS) performedproperly during ascent with very l i t t l e TPS acreage ablation Both SRB S were


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Parameter

RSRM PROPULSION PERFORM N E

Left motor, 66 OF i ~ t motor, 66 OFPredicted Actual Predicted Actual

Impulsega es1-20 10 6 lbf-sec1-60 106 lbf-secI-AT, 10 Ibf-sec

Vacuum Isp lbf-sec/lbm

Burn ra te in/sec

Event times secondsIgnition intervalVeb timeAct ion time

Separation cue, 50 psiaPMBT, of

Maximum ignition r ise ratepsia/10 ms

Decay t ime, seconds 59.4 psia to 85 K

63.85171.01296.80

268.50.365

0.232112.7124.7

122.666.0

90.4

2.8

63.37170.40295.82

267.60.3657

N/A112.4124.7

122.766.0

N/A

2. 8

64.12171.61296.84

268.50.366

0.232112.2122.1

122.166.0

90.4

2. 8

63.37170.17

.296.07

267.80.3652

N/A112.8125.6

122.866.0

N/A

3.5

Tailoff imbalanceImpulse different ia l

klbf sec

PredictedN/A

Actual-91.6


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ET separation was confirmed to have occurred properly. The crew reported

shortly af ter ET separation, as they were observing and photographing the ET tomeet the TO 312 requirements, continuous venting from th e vicinity of theET/Orbiter disconnects and also a pulsating venting from the intertank area.The crew photographed the ET extensively, and the photographs were analyzed indetai l af te r landing.

There are five valves in the ET/Orbiter disconnect area. Al l of the valves arefurnished to the ET Project by the Orbiter as part of the two i s o n n ~ tassemblies. t is u nl ik el y t ha t the 17-inch feedline valves were open fo r two

reasons.

a. The thrust of an open 17-inch valve would have caused the ET to tumble ata high rate and the crew reported that the tank was not tumbling a t a veryhigh ra te .

b. The ET 17- inch valve has to be closed fo r the Orbiter valve to close andth e pos i ti on indicato rs on the Orbiter showed t s valves to be closed.

The 4-inch L 2 recirculation valve on th e Orbiter is also mechanically coupledto the ET half of th e valve, which has a spring backup. Data show that thisv alv e c lo se d normally within the maximum allowable t ravel time. The 2-inchpressurization valves are spring loaded and close when the disconnect separates.

Even though th e 1 7-in ch and 4-inch valves were closed, the valves could havebeen leaking because of improper seating; however, no way exists to verify t i s ~condition. The allowable leakage from t he 17- inch LH 2 valve is 5,000 scims, and t i s ent i re ly possible that the crew saw only normal leakage. The condition of

th e 2-inch valves af te r separation is unknown One possible source of theobserved vapors could have been the normally trapped LH 2 between th e Orbiter andET halves of t he 1 7- in ch f lapper valves. At separation, th e hydrogen freezesinto ice crysta ls , a fact that was noted by th e umbilical cameras on OV 102Columbia on a number of f l ights


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SPACE SHUTTLE M IN ENGINE

Al l SSME parameters were normal throughout th e prelaunch countdown, and th eindications were typical of prelaunch parameters observed on previous f l ights .Engine ready was achieved at th e proper t ime, a l l LCC were met, and engine s ta r tand thrust buildup were normal.

Preliminary f l ight data indicate that th e SSME performance during mainstage,throt t l ing, shutdown, and propellant dump operations w well within .specifications. All three engines started and operated normally. High pressure

oxidizer turbopump (HPOTP) and high pressure fuel turbopump temperatures werewell within specification throughout engine operation.

n observation in th e STS-45 digi ta l data oxidizer preburner pump dischargepressure and HPOTP discharge pressure indicates a possible oxidizer preburnershutdown pop on main engine 1 S N 2024 and main engine 2 S N 2012 atshutdown 2.3 seconds. The pop c ri te ri a is based upon dynamic accelerometerdata and wil l be verified with accelerometer data when t becomes available.

The SSME controllers provided proper control of the engines throughout poweredf l igh t . Engine dynamic data generally compared well with p revious f l ights andtes t data. All on-orbit act ivi t ies associated with th e SSME s were accomplishedsuccessfully, and no significant SSME problems were noted in th e data.

SHUTTLE R NGE SAFETY SYSTEM

The Shuttle Range Safety System (SRSS) closed-loop test ing was completed asscheduled during th e launch countdown. All SRSS safe and arm (S A) devices were

armed and system inhibi ts were turned off at th e p rope r t imes . Al l SRSSmeasurements indicated that th e system performance was as expected throughoutthe f l ight . Prior to SRB separation, the SRB S devices were safed, and SRBsystem power w turned off as planned. The ET system remained active unt i l ET

i f h O bi Th i l h i d ll i hi


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procedures failed to reproduce or locate the sources of the leaks that occurreddur ing loading .

Analysisof

thedata indicates the

most probable causeof the

LH2 and L02 leaks was a transient distortion of the disconnect/seal material ineach system due to the thermal gradient that occurs early during fast f i l l

However the t roubleshoot ing act ivi t ies fo r the L02 and L82 concentration levelsresulted in the launch being rescheduled fo r March 24 1992.

The overall performance of th e MPS duri ng t he countdown and successful launch onMarch 24 was excellent. All pretanking purges were properly performep and L02and L82 loading was performed as planned with no stop flows or reverts. The

MPS

helium system performed sat isfactor i ly.Throughout the preflight operations no significant hazardous gas concentrationswere detected and the maximum LH 2 level in the Orbiter af t compartment was260 ppm, which compares very well with previous data for th is vehicle. The af tcompartment L02 concentration reached a maximum of approximately 1130 ppm earlyinto the L02 f a s t f i l l act ivi ty. The oxygen concentration stayed above the Ll imi t of 500 ppm fo r about 6 minutes and stabil ized a t about 180 ppm duringreplenish. This momentary high concentration level was anticipated and

acceptable pe r a preflight agreement. The a f t compartment helium concentrationpeaked at 9000 ppm, which was not a violation of the LCC.

A comparison of the calculated propellant loads at th e end of replenish versusthe inventory loads resul ts in a loading accuracy of 0.04 percent for liquidhydrogen and 0.035 percent for l iquid oxygen.

Ascent MPS performance was completely normal. Data indicate that th e liquidoxygen and hydrogen pressurization systems performed as planned and that l l

net positive suction pressure NPSP requirements were met throughout thef l ight . Space Shuttle ME O occurred 510.4 seconds af ter l i f t o ff .

The G02 pressurization system performed normally throughout th e e nt ir e f li gh t.Th G0 fl t l l hi d t t t it i di g t


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propellants were used by th e RCS during interconnect operations. During entry,

a single 10-second fir ing of l l

four forward RCS yaw thrusters was made atMach 4.0 in support of DTO 250 Forward RCS Flight Test - Control SurfaceEffects) .

A few occurrences of degraded chamber pressure on th e vernier thrusters,particularly F5L, L5L, and R5R, were noted. This condition has been noted onprevious fl ights with high vernier thruster usage. The lowest noted chamberpressure was 70 psia on L5L nominal pressure is 110 psia). These ~ chamberpressure occurrences were most l ikely caused by ei ther combustion residue

building up in the chamber pressure sensing tube, or ni t ra tes accumulating inthe oxidizer valve trim orifice resulting in an off-nominal mixture ra t io .Either case is cleared by a long-duration fir ing of th e thruster.

Orbital Maneuvering Subsystem

The OMS performance was excellent throughout the mission with no anomalies ori r regular i t ies r ep or te d o r noted in the data. Three maneuvers OMS-2, OMS-3,and deorbit) were performed with a to ta l fir ing time of 381.4 seconds. In

addition, the RCS was interconnected to th eOMS

fo r an extended period duringwhich 2.90 percent 376.6 lb) of the propellant from the l e f t OMS t anks and5.0 percent 647.6 lb) of th e propellant from the r ight OMS tanks was used.Total propellant consumption by the OMS i nc luding the RCS interconnect usage was9581 lb of oxidizer and 5778 lb of fuel .

A single engine l e f t ) OMS 3 maneuver of 12.0 f t / sec was required because of theunder-speed conditions existing at ME O This maneuver was performed at084:16:03:42.8 G.m.t . 00:02:50:03 MET to circularize the orbit a t 160 nmi. A

discussion of the conditions that required this maneuver is presented in th eAvionics and Software Subsystem section of this report .

Power Reactant Storage and Distribution Subsystem


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hydrogen and 2,291.0 lb of oxygen were consumed and 2,580 lb of water were

produced during the 9-day mission. The average Orbiter electr ical power loadwas 510 amperes during the mission.

At 084:14:30 G.m.t. 00:50:00 MET , the fuel ce l l 3 ce l l performance monitor CPM subs tack different ia l voltage remained at the periodic se l f - tes t value of50 mV for up to 3.5 minutes instead of the normal 2. 3 seconds Flight ProblemSTS-45-V-04 . The f l ight day 1 occurrence continued for 3 hours and the fl ightday 2 occurrence continued for 2 hours before the PM began o p r t i n ~properly.Main busses Band C had previously been tied together in accordance with normal

procedures for this mission, a condition which would have provided an insightinto fuel ce l l performance had a to ta l failure of the PM occurred. The PMperformed nominally for the remainder of the mission af te r the f l ight day 2occurrence. Preliminary analysis indicates a leaking capacitor in the PM asthe cause of the er ra t i c operation.

Auxiliary Power Unit Subsystem

The PU performance was nominal throughout the mission with an improved PU

IAPU flown in the 2 position. The IAPU performance was excellent withs ignif icant ly less heat soakback af ter IAPU shutdown. Three PU anomalies werenoted and are as follows:

a. PU 3 Z-axis vibration sensor accelerometer showed no output readoff-scale low throughout the mission Fl ight Problem STS-45-V-03 . Thisaccelerometer provides data for engineering evaluation and has no effect on th e operation of th e unit . Postfl ight test ing and analysis showed thatth e c on di ti on was caused by a shorted connector pin.

b. At 084:20:41 G.m.t. 00:07:01 MET , the PU fuel pump/gas generator Bsystem heaters were activated. The PU 2 and 3 systems operated properly;however, no response was noted from the PU 1 gas generator GG bedheater Flight Problem STS 45 V OS The GG bed temperature measurement


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c During ascent and FCS checkout, th e IAPU 2 gearbox nitrogen pressure

measurement was errat ic . This condition was in i t i a l ly attr ibuted toth e

relocation of th e s en so r on the IAPU. However, during entry, both th enitrogen and lubrication o il outlet pressure measurements were erra t ic andlow Flight Problem STS-45-V-11 . A few minutes af ter IAPU 2 was started,the nitrogen pressure dropped to approximately 5.5 psi and the gearbox wasrepressurized. In i t i a l ly, both the nitrogen and lubrication o il outletpressures increased and became smoother. However, over the next 38minutes, t he p re ssures slowly decreased and another repressurization wasrequired. This condi ti on d id no t impact entry operations; however, duringpostfl ight checks, the lubrication o il quantity in the gearbox was foundto be 150 cc s less than the level recorded during prefl ight preparations.

Fuel consumption and run time fo r each P U is presented in the following table.

PU 1 S/N 312 IAPU 2 S/N 407 PU 3 S/N 307Flight Phase Time, Fuel Time, Fuel Time, Fuel

min:sec consumption, min: sec consumption, min:sec consumption,Ib Ib Ib

Ascent 19:12 49 19:13 50 19:13 52FCS checkout 04:56 15Entry 82:19 154 59:10 130 59:10 130

Total a 101:31 203 83:19 195 78:23 182

a The to ta l includes 15 minutes 05 seconds of P U operation af ter landing duringwhich a hydraulics load tes t was performed.

In a dd it io n to the three anomalies, two other i r regular i t ies occurred in th esubsystem performance. The exhaust gas temperature EGT on PU 2 fai led af terlanding; however, t was an ol d design of the sensor which has fai led regularlyon previous missions. Since this loss occurred af ter landing, t did not impact


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One anomaly was noted during entry when VS 1 was overcooling while operating onth e B controller Flight Problem STS-45-V-10). Vhen cooling was in i t ia ted, thelubrication o i l return temperature dropped from 249 of to 177 of 72 of drop ,which i s i nd ic at iv e o f overcooling during a 5 1/2-minute period. Control wasswitched back to the A controller 1.5 minutes l a te r and the tempera turesre tu rne d to normal.

The VSB 2 gaseous nitrogen re l i e f valve failed th e in-f l ight checkout, and th eproblem i s believed to be an intermittent condit ion wi th in the pressuretransducer. This same signature was noted on STS-44. .

Electrical Power Distribution and Control Subsystem

The performance of th e e lec t r i ca l power distribution and control subsystem wasnominal during phases of t he mis sion .

Pyrotechnics Subsystem

The pyrotechnics subsystem operated nominally during the mission. One expendedumbilical separation system N S Standard In i t i a to r NSI) with an attachedconnector coupl ing ring fe l l to th e runway when th e right-hand L0 2 ) ETumbilical door was opened. A coupler retaining ring from the same in i t i a tor wasfound adhered to the room temperature vulcanizing RTV material on the innersurface of the right-hand door.

ET/Orbi te r separation ordnance device plungers 1 and 2 appeared to h v e -functioned properly; however, plunger 3 was obstructed by a detonator booster Flight Problem STS-45-V-12).

Environmental Control and Life Support Subsystem

The atmospheric revi ta l izat ion subsystem ARS performed nominally throughoutth e mission The redundant component check exercised th e alternate subsystem


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during the las t phase of entry unt i l about 10 minutes af ter landing when ammonia

boiler system A was activated fo r cooling unt i l th e ground support cooling wasin i t ia ted 43 minutes af ter landing.

Smoke Detection and Fire Suppression Subsystem

The smoke detection subsystem operated nominally and showed no indications ofsmoke during the mission. Use of the f i re suppression subsystem was no trequired.

AirlockSupport Subsystem

Use of the airlock support subsystem was no t required because no extravehicularact ivi ty was planned or performed. The active system monitor parametersindicated normal output levels throughout the mission.

Avionics and Software Subsystems

At HECO, a 5. 7 ft lsec under-speed condition existed. This condition was mostl ikely caused by the manner in which the onboard guidance t reats the effect ofgravity during ta i loff . The effect of gravity during ta ilo ff is assumed to bemission independent by guidance software; whereas in real i ty, th e gravityeffect is dependent on the specific orbi ta l inclination of the mission.Therefore , h igher f l ight-path-angle missions will generally have largerunder-speed conditions than the lower flight-path-angle missions. In additionto the ME O under-speed condition, the orbi ta l in-plane thrust from the HPS dumpwas less than planned because of the early at t i tude maneuver that was made toobserve and photograph the ET in fulf i l lment of T O 312 ET Thermal ProtectionSystem Performance . As a result of these two conditions, a small OMS-3maneuver was performed to circularize the orbit a t approximately 160 nmi.

The avionics subsystem performance was nominal. The new high accuracy iner t ia lnavigation system HAINS iner t ia l measurement unit IMU S N 203 was flown in


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Problem STS-45-V-13). The crew also stated that a l l other SM a le r t functionswere normal. Postfl ight functional tes ts of the caution and warning systemshowed nominal operation.

Communications and Tracking Subsystem

The communications and tracking subsystem performance was acceptable.

Ku-band frequency shif ts of 1 to 20 MHz in the downlink were noted th e WhiteSands ground s ta t ion. The f i r s t occasion of the shif ts caused a short loss ofchannels 1 and 2. Later in the mission, th e White Sands ground s ta t ion was ableto make a video recording of the spectrum analyzer during a Ku-band frequencysh i f t . The shif t occurred dur ing a video and instrumentation tape recorder VITR dump at approximately 089:07:20 G.m.t. 04:18:06:20 MET . An analysis ofth e data shows no apparent correlat ion between the Ku-band frequency sh i f t andth e SEPAC electron beam f i r ing. Onboard troubleshooting showed that each timeth e VITR playback command was sent th e Ku-band frequency shifted 20 MHz.

At 085:16:24 G.m.t. 01:03:11 MET , the Ku-band antenna di d no t automaticallytrack af ter lock-up on the forward l ink while in th e GPC acquisi t ion mode Flight Problem STS-45-V-07). Several instances of auto t rack failure occurredduring the mission and th e problem was cleared each time by selecting th e GPCdesignate mode. This same problem also occurred on this unit S N 107) duringth e STS-37 mission and was cleared each time by momentarily selecting the Pdesignate mode.

Postfl ight troubleshooting could no t duplicate the STS-37 problem, althoughmetal shavings were found on th e Ku-band antenna dish. This problem di d notrecur on th e STS-43 or STS-44 missions when th is unit was also flown.

In addition the Ku-band transmitter RF power output telemetry indication waserrat ic in that th e indicated power would drop from 31 W to -22 V, but theantenna continued to perform t s function sat isfactor i ly This was an


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During th e uplink of th e third page of th e morning mail on fl ight day 3 th e

text and graphics system TAGS indicated a jam condition. The jam was clearedby th e crew and th e TAGS operated sat isfactor i ly for th e remainder of thef l ight . This condition did not impact mission operations.

Operational Instrumentation

The operational instrumentation subsystem operated nominally except for th e lossof th e P U 3 Z axis vibration sensor prior to l i f t o f f and th e loss pf th e PU2 EG T 2 sensor af te r landing. Neither of th e fai lures had any impact on the

successful completion of th e mission and th e fai lures are discussed in th esubsystem sections of th e report .

Structures and Mechanical Subsystems

All structures and mechanical subsystems operated nominally during the missionwith no i r regular i t ies noted. The landing and braking data are presented in th efollowing table.

The debris found under th e right hand ET/Orbiter umbilical door was aconnector

and in i t i a to r fo r expended pyrotechnics. The debris originated from one of th e

LANDING N BRAKING P R METERS

FromParameter threshold Speed Sink ra te f t / sec Pitch rate

f t knots deg/sec

Main gear touchdown 1844 187.7 1.0 n/aNose gear touchdown 4402 162.6 n/a 3.56

Braking in i t i a t ion speed 135 3 knots


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umbilical attach points which currently have no debris containment system. The

modif icat ion to add th e new debris containment system to the OV-104 vehicle i sscheduled for th e Orbiter Maintenance Down Period OMDP af te r STS-46.

The postfl ight inspection revealed that th e ET/Orbi te r hole plugger was jammedby a booster cartr idge. A booster cartridge was also found in th e doormechanism. Some debris was missing and i s assumed to have been los t on orbi t .

Aerodynamics, Beating and Thermal Interfaces

Ascent and entry aerodynamics were satisfactory with l l

responses a s expec ted.Nominal aerodynamic and plume heating occur red dur ing ascent. Entry aerodynamicheating was w ith in the thermal protection subsystem TPS l imi ts . The prelaunchtemperatures on both th e launch attempt and th e actual launch were withinlimi t s .

Thermal Control Subsystem

The performance of th e thermal control subsystem TCS was nominal dur ing them is sion w ith l l temperatures being

maintainedwithin acceptable l imi ts . The

system B PU GG heater operation was intermittent fail ing off on severaloccasions prior to recovering apparently concurrently with th e activation of thefuel pump heater.

Aerothermodynamics

The aerothermodynamics for STS-45 were nominal with acreage heating nominal.Localized heating was also nominal. Damage was found to one wing leading edgereusable carbon carbon RCC panel. This damage i s reported in detai l in th enext section of this report Thermal Protection Subsystem .

Thermal Protection Subsystem


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Two impact damage s i tes were found on the upper surface of the r ight wing Rpanel 10 Fl ight Problem STS-45-V-08). These two gouges were 1. 9 inch by1. 6 i nch and 0. 4 inch by 1.0 inch, and the substrate was exposed. An evaluationi s being made to determine the cause of this damage and the time of occurrence.

The main landing gear door thermal barriers exhibited minor damage, the mostnotable being protrusion at the forward location.

A portable Shuttle thermal imager was used to measure the surface temperature oft hr ee a re as on the Orbiter TPS after landing. At 21 minutes af ter wheels stop,the Orbiter nose cap R was 140 of, the right-hand wing leading edge R panel9 was 77 of, and the right-hand wing leading edge R panel 17 was also 77 of .

Vindow hazing was less than normal, with l ight hazing observed on windows 3 and4. Greater than typical t i l damage was sustained on t he per iphe ry of l lwindows; however, in most cases the damage was surface coating loss only. TheET thermal barriers performed nominally. The payload bay doors, upper wings,and OMS pod TPS performance was nominal.

GOVERNMENT FURNISHED EQUIPMENT ND FLIGHT RE V EQUIPMENT

The overall performance of the government furnished equipment GFE and fl ightcrew equipment was very satisfactory except fo r the 16-mm Arriflex camera on/offswitch which operated intermittently. One other item of note was the operationof the vacuum cleaner when the thermal cutoff switch opened. The crew reportedthat the vacuum cleaner had been operating continuously with the f i l t e r cleaningtool attached for 45 minutes a t the time of the thermal cutoff . After coo ling ,the vacuum cleaner operated sat isfactor i ly for the remainder of the mission.

PAYLOADS/EXPERIMENTS


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of occasions to measure radiat ion aboard th e Orbiter; Inves t igat ions in toPolymer Membrane Processing IPMP , which was used to develop polymer membranesfo r use as f i l t e r s in many industr ies and in space; and th e Cloud Logic toOptimize Use of Defense Systems CLOUDS-1A , which was an i nvest iga tion intoquantifying th e variat ion in apparent c loud cover as a function of the angle atwhich th e clouds were viewed. All of these experiments were located on themiddeck during the mission.

In addition, th e Shuttle Amateur Radio Experiment SAREX provided m ~ t u rradiooperators throughout th e world, plus selected students a t several selecteds ights , th e op portun ity to converse with crew members aboard Atlantis . Thisexperiment was also located on th e middeck.

One S payload G-229 - Experiment in Crystal Growth was also flown. This wasth e second f l ight of a very successful S experiment that was performed onSTS-40, but with additional features included to enhance th e abi l i ty to analyzeconvection effects on crys ta l growth in microgravity.

Integration of th e cargo payloads) into th e Orbiter involved th e use of missionki t s , which c on si st ed o f standard payload bridges, latches and attach f i t t ings ,th e payload bay 13 S beam, and other miscellaneous hardware. All equipmentperformed properly and there were no anomalies recorded for this hardware.Verification analyses were performed in th e areas of loads, thermalcharacter is t ics , and elect r ical power, including electromagnetic compatibility.Data confirmed that performance was within p redi ct ed ranges, and no out-of-l imitconditions occurred.

SCIENTIFIC ACTIVITIES

Spacelab activation was completed at 2 hours 49 minutes MET, and payloadactivation was started about 30 minutes l a te r. The 13-minute 40-second delay inth e launch shifted th e shadow times approximate ly 1 degree 34 minutes and th eexper iment t imes were adjusted accordingly. During the remainder of th e f i r s tday s ac t iv i t i e s , l l scheduled instruments were activated and calibration


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SEPAC vir tual antenna experiments th e operation of th e EB was los t because a

fuse was blown in th e EBA, which i s located in th e payload bay. The SEPACscience team reported that th e EB achieved t objective. The orbi ta l pathallowed th e atmospheric i ns tr umen ts to make correlat ive measurements of th e samepart of th e atmosphere being observed by th e Upper Atmosphere Research Satel l i te UARS . The FAUST high-voltage sources began operat ing proper ly, andul t raviole t astronomy observations resumed.

Atmospheric science, space plasma physics, and ul t raviole t astronomy.experimentation continued during the fourth day of da ta ga ther ing . The

Atmospheric Trace Molecule Spectroscopy ATMOS and Grille Spectrometer GRILLEdata and video showed clear evidence o f a eros ol bands that are probably th eeffect of th e Mt. Pinatubo eruption l a s t year. The SSBUV experiment started tobservations, measuring th e global ozone in th e stratosphere. The SEPAC used t plasma c on ta ct or f or experimentation that will help verify a theory thatunderlies th e basic physics on th e formation of th e universe.

The f i f th day was excellent from th e aspect o f o bta in in g scient i f ic data. Thescient is ts believe that th e data collected will provide unprecedentedinformation about th e Earth s atmosphere. Atmospheric stat ions in India,Indonesia, Japan, and New Zealand made simultaneous observations with th einstruments aboard the ATLAS payload. The GRILLE instrument detected hydrogenchloride a t higher levels of th e atmosphere than previously measured. Plasmaphysics and ul t raviole t astronomy instruments were also active. Data werecollected on a br i l l i an t red and purple natural aurora stretching from Africa toAustralia, and a payload low-light camera photographed blue clouds of xenon gasas th e gas was released into th e area around th e Orbiter by one of th eexperiments. One of th e major i tems completed this f i f th day was th e second ofthree solar observation periods to gain information on th e solar spectra andvariat ions in th e Sun s energy output.

The s ix th day of act iv i ty was spent by many of th e science teams in planningth e ac t iv i t i e s fo r the ninth day that was added to th e f l ight plan by th e


24/36

of space plasma physics, the SEPAC plasma wave instrument detected a phenomenaca ll ed wh is tl e rs , which i s a radio wave signature of lightning in theatmosphere.

ATLAS-1 EXPERIMENTS

The primary objectives of the 12 ATLAS-1 instruments that were located on theSpacelab pal le t in th e payload bay were to measure th e v ariation in solaroutput; measure th e Earth s middle atmospheric constituents over the ~ u r s ofone solar cycle; and supplement the measurements from the Upper AtmosphereResearch Satel l i te .

Atmospheric Science

In th e field of atmospheric science, the Imaging Spectrometric Observatory ISO)measured spectral features in determining the composition of the atmosphere downto th e trace amounts of chemicals measured in parts-per- t r i l l ion. Theinvestigation, which previously flew on Spacelab 1, added data about the variedreactions and energy transfer processes that occur in th e Earth s environment.

The TMOS and th e Gri l le Spectrometer experiments mapped trace molecules,including carbon dioxide and ozone, in the middle atmosphere. The mapping wasaccomplished from orbi ta l sunrise to orbi ta l sunset, which occurred about every90 minutes throughout the f l ight , by measuring th e infrared radiation that themolecules absorb. Both of these experiments have flown previously, TMOS onSpace lab 3 in 1985 and GRILLE on Spacelab 1 in 1983.

The Atmospheric Lyman-Alpha Emissions ALAE) experiment measured th e abundanceof two forms of hydrogen common hydrogen and deuterium heavy hydrogen). L E observed ul t raviole t l igh t , called Lyman-Alpha, which hydrogen anddeuterium radiate a t s l ight ly different wavelengths. Deuterium s re la t iveabundance compared to hydrogen a t th e al t i tudes L E studied is an indication ofatmospheric turbulence in th e lower thermosphere After determining th e


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NIMBUS-7 sa te l l i t e to ensure that the most accurate readings were o bt ai ne d o fatmospheric ozone trends. The SS UV assessed instrument performance by directlycomparing data from identical instruments aboard th e NO sa te l l i t es and th eNIMBUS-7 sa te l l i t e as the Shuttle and sa te l l i t e passed over the same Earthlocation. SSBUV data also will be compared with data from the U RS launched inSeptember 1991 to study the processes that lead to ozone depletion. The solardata taken by SSBUV also wil l be compared with data from the four solarinstruments.

The SSBUV was physica l ly separate from the ATLAS-1 payload, housed two G Scanisters mounted in the payload bay. This mission was the fourth for th eSSBUV, having previously flown in October 1989, October 1990, and August 1991.

Solar Science

Four solar science investigations measured the Sun s energy output to determine t variat ions and spectrum. The Active Cavity Radiometer ACR and theMeasurement of Solar Constant SOLCON experiments measured the to ta l amount ofl ight and energy emitted by the Sun. These data a re e sp ec ia ll y important in th estudy of Earth climates.

The Solar Spectrum Measurement SOLSPEC and th e Solar Ultraviolet SpectralIrradiance Monitor SUSIM investigations along with the SSBUV discussedpreviously added significantly to the scient is ts understanding of howvariations in the Sun s energy output affects the chemistry of the atmosphere.Al l four of these experiments have previously flown on the Shuttle.

Space Plasma Physics

Two space plasma physics instruments, th e Atmospheric Emissions PhotometricImaging AEPI and SEPAC studied th e charged par t ic le and plasma environment. Athird investigation, Energe tic Neutral Atom Precipitation ENAP was conductedusing data from the ISO instrument discussed previous ly Active and passive


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which cannot be detected by ground-based astronomers. However, this radiationwas detectable by th e FAUST. FAUST which flew on Space lab 1, studiedastronomical radiation sources a t ul t raviole t wavelengths.

INVESTIGATIONS INTO POLYMER MEM R NE PROCESSING

The IPMP a middeck payload , was flown for the sixth time on th e STS-45 mission.The IPMP investigated th e physical and chemical effects induced by microgravitysuch that th e improved knowledge base can be applied to commercial m e ~ r n eprocessing techniques. Polymer membranes have been used by industry inseparation processes fo r many years. Typical applications include enriching th eoxygen content of a i r, desalination of water, and kidney dialys is .

Polymer membranes frequently are made using a two-step process. A samplemixture of polymer and solvents is applied to a cas ting sur face . The f i r s t stepi nvolves the evapora ti on o f s olv en ts from the mixture. In th e second step, anon-solvent typically water is introduced and the desired membrane isprecipitated, completing t he p rocess . Previous f l ights of IPMP where thecomplete process was flown were STS-41, -43, -48, and -42, and the evapora tionstep alone was flown on STS-31. The precipitat ion step was the only portion ofthe experiment that was flown on STS-45.

GET AVAY SPECIAL EXPERIMENT

The G S Program has sponsored the f l ight of 77 G S canisters on 17 missionsdurin g the Shutt le Program. The Experiment in Crystal Growth G-229 , flown onSTS-45, was designed to grow crystals of gallium arsenide GaAS . The GaAS i s aversat i le electronic material used in high-speed electronics andopto-electronics. A crysta l approximately 1 inch in diameter and 3.5 incheslong was planned for growth during a 11-hour period o f this mission.

The payload is ent i re ly sel f -suff ic ient and includes t own power system,growth sys tem, and control and data acquisi t ion systems. The experiment was


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calculated in real- t ime th e exposure in RADS-tissue equivalent. The data werestored in

memory modulesfo r postfl ight analysis

whichi s in progress.

VISUAL FUNCTION TESTER II

The VFT-II experiment measured changes in a number of vision parameters ofsubjects exposed to microgravity. The device measured changes in th e contrastra t io threshold of the subjects who were th e payload specia l is ts . The tes tsubjects were t es te d p ri or to th e f l ight daily during the f l ight ~ twice

C

during th e week following th e mission. This experiment was flown on threeprevious Shuttle missions.

CLOUD LOGIC TO OPTIMIZE USE OF DEFENSE SYSTEMS

The overall objective of the CLOUDS 1A program was to quantify th e variat ion inapparent c loud cover as a function of the angle a t which clouds of various typeswere viewed and to develop meteorological observation models for various cloudformations. A Nikon camera was used to obtain high-resolution photographs ofindividual cloud scenes over a wide range of viewing angles.

SPACE TISSUE LOSS

The STL experiment was a l i fe sciences experiment that studied ce l l growthduring spacefl ight . The objective of th e experiment was to study the responseof muscle bone and endothelial cel ls by evaluating various parametersincluding shape cytoskeleton membrane integri ty and metabolism act iv i ty ofenzymes that inactivate proteins and th e effects or change of response tovarious drugs on these parameters. The experiment was contained in a middecklocker.

DEVELOPMENT TEST OBJECTIVES ND DETAILED SUPPLEMENTARY OBJECTIVES


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that is noted lasted approximately 4.75 seconds followed by a pause in th eventing of 2.46 seconds . The second period of venting lasted 6 .79 seconds andt he v en ti ng paused again for 1.46 seconds. The third period of venting lasted5.38 seconds at which time the ET was los t from view. Several sma ll whiteobjects assumed to be ice were seen in the vapor during th e f i r s t venting.After further photographic enlargement at JSC venting from the ET intertankwas observed on frame 31 of th e Hasselblad film. Also noted on the enlargementswas a noticeable change in th e ET rotation ra te between frames 34 and 35 of theHasselblad film.

T 520 Edwards Air Force Base Lakebed Bearing Strength Evaluation.- This Twas no t performed since th e landing was made at KSC

T 623 Cabin Air Monitoring.- Instruments for this T were set up fo roperation on f l ight day 1 and were stowed on f l ight day 8. Samples weregathered during the f l ight and these data are being evaluated by t he s po ns or.

T 624 Radiator Deployment Performance.- This T was no t performed as trequired th e space radiators to be deployed. Conditions were such onboard th evehicle that no need arose to deploy the radiators.

T 633 VTR Demonstration.- Data were gathered fo r this T from f l ight day 1unt i l th e equipment was stowed jus t be fo re the deorbit maneuver. Data are beingevaluated by th e sponsor.

T 648 Electronic t l l Camera No downlink .- A c ti vi ti es i n support of this T were conducted from f l ight day 1 unt i l the equipment was stowed jus t before

th e deorbit maneuver. The data are being evaluated by t he sponsor.

T 728 Ku band Antenna Fric t ion.- This T was performed af te r completion ofth e science objectives for the ATLAS/SSBUV The data are being evaluated by thesponsor.


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DSO 6 8 - Effects of Space fl ight on Aerobic and Anaerobic Metabolism at Restand During Exercise.- The data were collected and ar e being evaluated by th esponsor.

DSO 611 - Air Monitoring Instrument Evaluat ion and Atmospheric and AtmosphericCharacterization Configurations A and B . The f i r s t sample for this DSO wastaken at 05:45:00 MET Samples were taken throughout th e mission and are beingevaluated by the sponsor. DSO 612 - Energy Conservation.- The data were collected and are being evaluatedby t he sponsor.

DSO 613 - Changes in Endocrine Regulation of Orthostatic Tolerance to SpaceFlight . - The data were collected as planned and are being evaluated by thesponsor.

DSO 614 - Head and Gaze Stabil i ty During Locomotion.- The data were collectedand are being evaluated by the sponsor.

DSO 621 - In-Flight Use of Florinef to Improve Orthostatic IntolerancePostf l ight . - The medicat ions were taken as planned and the data were taken fromthe two crewmembers. The data are being evaluated by the sponsor.

DSO 8 2 - Educational Activities The Atmosphere Below .- The DSO was completedwith good resul ts .

DSO 9 1 - Documentary Television.- The DSO was completed with good results andthe video data are being evaluated by the sponsor.

DSO 9 2 - Documentary Motion Picture Photography.- This DSO was completed withgood resul ts , and the data are being evaluated by the sponsor.

DSO 9 3 - Documentary S t i l l Photography - The data were collected as a part of


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TABLE I STS 45 SEQUENCE OF EVENTS

Event

PU activation

SRB HPU activation

Main propulsionSystem s t a r t

SRB ignit ion command l i f t - o ff

Thrott le up to100 percent thrust

Thrott le down to89 percent thrust

Thrott le down to74 percent thrust

Thrott le up to104 percent thrust

Maximum dynamicpressure q

Both SRM s chamberpressure a t 50 psi

Description

APU 1 GG chamber pressureAPU 2 GG chamber pressureAPU 3 GG chamber pressureLH HPU system A s t a r t commandLH HPU system B s ta r t commandRH HPU system A s ta r t commandRH HPU system B s ta r t commandEngine 3 s ta r t command acceptedEngine 2 s ta r t command acceptedEngine 1 s ta r t command acceptedSRB ignit ion command to SRB

Engine 3 command acceptedEngine 2 command acceptedEngine 1 command acceptedEngine 3 command acceptedEngine 2 command acceptedEngine 1 command acceptedEngine 3 command acceptedEngine 2 command acceptedEngine 1 command acceptedEngine 3 command acceptedEngine 2 command acceptedEngine 1 command acceptedDerived ascent dynamic

pressureLH SRM chamber pressure

mid range select

Actual timeG.m.t.

084:13:08:56.51084:13:08:57.47084:13:08:58.27084:13:13:12.17084:13:13:12.32084:13:13:12.49

084:13:13:12.65084:13:13:33.429084:13:13:33.585084:13:13:33.701084:13:13:39.991

084:13:13:44.549084:13:13:44.585084:13:13:44.582

084:13:14:01.990084:13:14:02.025084:13:14:02.022084:13:14:09.510084:13:14:09.545084:13:14:09.542084:13:14:42.951084:13:14:42.986084:13:14:42.983

084:13:14:50

084:13:15:42.59


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- ,

TABLE 1 STS-45 SEQUENCE O EVENTS Continued

OMS 1 ignit ion Left engine bi prop valveposition

Right engine b i p rop valveposition

OMS 1 cutoff Left engine bi prop valveposition

Right engine bi prop valveposition

PU deactivation APU 1 GG chamber pressureAPU 2 GG chamber pressureAPU 3 GG chamber pressure

OMS 2 ignit ion Left engine bi prop valveposition

Right engine b i p rop valveposit ion

OMS 2 cutoff Left engine bi prop valveposit ion

Right engine bi prop valveposition

Payload bay door open PLBD r ight open 1PLBD l e f t open 1

OMS 3 ignit ion Left engine b i p ro p v al veposit ion

Right engine b i p rop valveposit ion

OMS 3 cutoff Left engine b i pr op v alv eposit ion

Righ t eng ine bi prop valve

Event Description Actual time,G m t

N ANot performeddirect insert iontrajectory flownN ANot performeddirect insert iontrajectory flown084:13:28:08 29084:13:28:09 99084:13:28:11 01084:13:49:59 9

084:13:49:59 9

084:13:52:25 9

084:13:52:25 9

084:14:53:49084:14:55:07084:16:03:42 8

N A

084:16:03:57 6

N A


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TABLE 1 STS-45 SEQUENCE O EVENTS Concluded)

Event

Entry interface 400K)

Blackout ends

Terminal areaenergy management

Main l anding gea rcontact

Main l anding gea rweight on wheels

Nose l anding gea rcontact

Nose l anding gea rweight on wheels

Vheels stop

PU deactivation

Description

Current o r bi ta l a lt it ud eabove reference ell ipsoid

Data locked a t high samplerate

Major mode change 305)

LH MLG t i re pressureRH MLG t i re pressureLH MLG weight on wheelsRH MLG weight on wheelsNLG t i re pressure

NLG VT on Vheels 1

Velocity with respect torunway

APU GG chamber pressureAPU 2 GG chamber pressureAPU 3 GG chamber pressure

Actual time,G m t

093:10:51:49

No blackout

093:11:16 38

093:11:23:05093:11:23:05093:11:23:08093:11:23:08093:11:23:13

093:11:23:13

093:11:24:04

093:11:38:08 64093:11:38:09 09093:11:38:10 02


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Number Ti t l e

TABLE I I STS-45 PROBLEM TRACKIOO LIST

Reference Comments

\0

STS-45-V-Ol ILiquid Hydrogen LeakDuring Fi r s t LaunchAttempt

STS-45-V-02 Liquid oxygen Leak DuringFi r s t Launch Attempt

STS-45-V-03 IAPU 3 Z-axis Vibrat ionSensor Failed V46D0381A

STS-45-V-04 JFuel Cell 3 CellPerformance Monitor CPMAnomaly

STS-45-V-05 IAPU 1 Gas Generator BedHeater Sys tem B Errat ic

083:05:10 G.a.t .IPR 45V-0138 deferred UA

083:05:10 G.a.t .IPR 45V-0139 deferred UA

PrelaunchCAR 45RF-OlIPR 46V-0002

083:14:22 G.m.t.CAR 45RF-02IPR 46V-0003

084:20:41 G.IlI.t.CAR 45RF-03IPR 46V-000I

Af t compartment hydrogen concentration rose to 750 ppm LeC = 500 ppm3. 5 minutes i nt o f as t f i l l Terminated f i l l a t tha t t ime. Leakcondition c ou ld n ot reproduced. Concentration was within l imi t son second at tempt.

KSC: Troubleshooting plan available. Inspect and photographumbil icals a t landing s i t e Further inspect ions in OPF. Noc h i t required.

Af t compartment oxygen concentration rose to 850 ppm LeC = 5 00 p pmduring slow f i l l La ter dec rea sed . Exceeded l imi t on second at tempt,bu t minutes l a t e r stabil ized w it hi n t he LeC l imi t .

KSC: Same act ion as specif ied in STS-45-V-Ol.

Data showed no response from Z-axis sensor. X-axis nominal a tapproximately 5 g p ea k to peak. Cri t i ca l i ty 3 measurement. Acceptableto fl y as i s unt i l planned APU 3 changeout.

KSC: Wire wiggle and continui ty checks. Repair i f possible . No ch i trequired.

Cell performance moni tor hung up in 50 s e l f t e s t mode fo r periods upto 3 minutes. No impact to fuel c e l l performance. s u sp e ct l e ak ycapaci tor. Last f l i gh t occurrence was on f l igh t day 2.

KSC: Remove and replace CPM. Spare is available. No ch i t required.

Heater B f ai le d t o respond when i n i t i a l l y activated. Fuel pump/l ineh ea te rs a re operat ing sa t i s fac to r i ly. switched to system A an d be dheater r es po nd ed . s wi tc he d b ac k to system B. I n i t i a l er ra t i cb e ha v io r , t h en o p er at e d n or ma ll y. Errat ic behav io r r ecu rr ed on f l igh tday 5. Data indicates abnormal fuel system heater operat ion also.switched to system A on f l igh t day 6. Possible control ler problem,thermostat problem, or a ft load control ler assembly LCA problem.

KSC: Pos t f l igh t t roubleshoot ing required. Troubleshoot ing plann

available. No ch i t is required. Problem di d n ot r ec ur d ur in gtroubleshoot ing.

STS-45-V-06 la CCTV Camera A Q Ua li ty 0 86 :0 2: 15 G.a.t .Poor BFCE-029F049

b CCTV Camera C Noisy BFCE-029F050Video

c CCTV Camera Dperformance poor.

a Camera A picture quali ty SUddenly became very poor fuzzy , l a t e rrecovered. Intermit tent throughout f l igh t .

b camera C downlink video was intermit tently noisy, containing colorednoise l ines across th e i ma ge. The camer a la te r recovered. A bu mspot on th e camera C video image was noticed on th e upper l e f t par tof th e p ic tu re .

c Crew reported that camera D seldoll l worked in low l igh t . Also,occasional ly c ou ld n ot control pan and t i l t

KSC: Remove cameras A, C, and D and ship to Boeing FEPC.


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NwIIber Ti t le

TABLE I I STS-45 PROBLEM TRACKING LIST

Reference C o _ n t s

STS-45-V-07 la ) Ku-Band Antenna Loss ofI085:16:24 G t

Track in Acquisition 1M 45RF-04Mode

b) Ku-Band RF Power ou t IIPR 46V-0008Intermit tently Failed

a) Repeat of STS-37-v-04 with D 107. Loss of lock in acquisi t ion

mode. NOrlllll1 operations in GPC designate mode. Invest igat ingeffec t s of th e characteris t ics of payload data t r ansmi t ted v ialtu-Band channel 3. ltu-Band r equ i r ed nex t f l igh t of OV-104 TSS llli.ssion .

b) Loss of lock possibly associated with RF power monitor problem.Observed on previous f l igh t CAR 37RF-04 .

KSC: Approximately two sh i f t s OPF test ing required pr io r todeployed assembly DA removal and replacement. Spareavailable SIN 102). OPF testing scheduled fo r A pr il 1 6.Pos t f l igh t antenna inspect ion nOrllllll. Payload d at a n otrequired fo r troubleshooting. OPF t e s t data required tosupplement vendor analysis . Coordinated test / t roubleshootingplan in work. No ch i t required.

wo

STS-45-V-08 IDamage on Right RCC PanelNo 10 Post landingPR-TES-4-12-0l151M 45RF-05

Two gouges 1 .9 i nc h by 1. 6 inch, and 0. 4 inch by 1. 0 inch) noted onupper p or ti on o f r ig ht wing leading edge RCC panel no . 10 . Substratee x po s ed a n d t i l e s a re n ot repairable. Panel removed and shipped toDowney.

STS-45-V-09 Ine r t i a l Measurement unit2 Z -A xi s AccelerometerBias Shi f t

Post ascent1M 45RF-06IPR 46V-0012

HAINS SIN 203 experienced a z -a x is b ia s s h i f t of 120 micro-g duringascent 1 sigma = 30 micro-q). Suspect sens i t iv i ty to a t t i tude . Newcompensation va lue up l inked f or e nt ry .

KSC: Perform hangar calibration and pre f l igh t alignment

STs-45-V-10 IWater Spray Boiler 1OVercooling onB Control ler

STS-45-V-11 IAPU 2 Ni t rogen Pre ssu reLow

093:11:00 G.IlI.t.

093:10:38 G tIPR 46V-0006

When cooling was in i t i a ted , th e lube o il return temperature droppedf rom 249 OF to 177 OF over a p er io d o f approximately 5 1/ 2 minutes.switched to A control ler 1 1/ 2 minutes l a t e r when lube o il temperaturewas 181F. Violated O RS File IX requirement DV58AKO 050Suspect problem related to concur r en t dec rea se noted in drain cavitypressure. Indicat ions of high N

2H

4vapor content during gearbox lube

o il offload.KSC: Perform APUjHYD ho t o il f lush.

Nitrogen pressure decayed from 15.5 p si a t o 11.5 psia between FCSCheckout and APU s t a r t f or e nt ry . Pressure dropped to 7. 5 psia af te rAPU s t a r t Two repressurizations were made during entry.

KSC: Troubleshooting plan available.

STS-45-V-12 IETjOrbiter 3 Hol e plugger IPostf l i9htoJaRlled inspect ion

PR PYR4-12-o150

Hole plugger was jalllllled by a booster cartr idge. Booster cartr idge alsofound in door mechanism. Some debris is missing and i s assumed to havebeen los t while i n o r bi t.

STs-45-V-13 S Ale r t Ti_ / l one lwd ib l elon -o rb i tAlarm Intermit tent

The crew reported tha t on severalwhen using th e 8M A le rt a s a time8M Alert indicat ions were normal.

nominal.

occasions there was n o audible tonea l e r t fo r maneuvers, e tc . A ll o th er

Postf l ight C W funct ional t e s t was


35/36

NSTS-08275 - STS-45 Space Shut t le M i s s io n R e p o rt

GE Government Services1050 Bay Area Blvd.Houston, TX 77058Attn: A. Verrengia

James R. WomackJPL/233-3074800 Oak Grove DrPasadena, CA 91109

James V. ZimmermanNASA European Repc/ o American ElllbassyAPO New York, NY 09777

cap t . J Behl ing6555 ASTG/SMSPcape canaveral AFS FL.32925

LESC-HoustonB08jP. DavisC07jLESC LibraryC12jD. Harr isonC12jR. W. Fricke 5)C87jD. weiss inger

TRW1 Space Park DriveR11/1850 - L. Sty t l eRedondo Beach, CA 90278

HQ AFSPACECOM,IDOSLBldg 1 stop 7Peterson AF8Colorado spr ings , Co 80914Attn: cap t . S. M. Young

R. BirmanGeneral Elec t r i c Co.Space Divis ionP. o . Box 8555Phi ladelphia , PA 19101

Headquar ters , Space DivAt tn . : SSD/CLPLos Angeles AF s t a t i o nP. o . Box 92960WOrldway Postal CenterLos Angeles , CA 90009

Ames Research CenterMoffet t Fie ld , CA 94035233-17/J . Har t

N. Parmet5907 S u nr i se D ri v eFairway, ltansas 66205

Darryl Str icklandP. o. Box 1940N o r th H i g hl a n d s, CA95660-8940

C. Woodland Prog. Mgr.

SPAR Aerospace LiJlited9445 Airport RoadBrampton, Ontar io ,canada, I.6F4J3

A. S. Jones 2)SPAR Aerospace Lillli.ted9445 Airport RoadBrampton, Ontar iocanada L6F4J36

D. Molgaard2525 Bay Area Blvd.s u i t e 620Houston, TX 77058

Aerospace Corporat ionP. o. Box 92957Los Angeles, CA 90009Attn: W. Sa i th , MS/619

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