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STS-68 Space Shuttle Mission Report Was Prepared from Inputs Received from the Orbiter Project Office As Well As Other Organizations NASA-CR-199570 NSTS-08294 (---- STS-68 SPACE SHUTTLE NASA_CR-199570 MISSION REPORT 19960001493 ----- (NASA-CR-199570) STS-68 SPACE N96-11500 SHUTTLE MISSION REPORT (Lockheed Engineering dnd Sciences Co.) 58 P Unclas G3/16 0068431 January 1995 .. ~ .. :: /~ .. }. ~-::. .:! .. -. 1.. National Aeronautics and Space Administration Lyndon B. Johnson Space Center tiouston, Texas 111111111111111111111111111111111111111111111 NF01395 NOTE The STS-68 Space Shuttle Mission Report was prepared from inputs received from the Orbiter Project Office as well as other organizations. The following personnel may be contacted should questions arise concerning the technical content of this document. Bobbie Gail Swan Orbiter and subsystems 713-483-2528 C. A. Snoddy, MSFC MSFC Elements (SRB, 205-544-0391 RSRM, SSME, ET, SRSS, and MPS G. P. Buoni, JSC Flight Integration 713-483-0639 Manager, and DTOs and DSOs Ed J. Jung, Jr., JSC SRL Payload 713-483-1154 F. T. Bums, Jr., JSC FeE and GFE 713-483-1262 NSTS 08294 STS-68 SPACE SHUTTLE MISSION REPORT Approved by Bobbie iI Swan valuation Room Manager Da dW.Camp Manager, Flight Engineering and Vehicle Management Office Brewster H. Shaw Director, Space Shuttle Operations Prepared by Lockheed Engineering and Sciences Company for Flight Engineering Office NATIONAL AERONAUTICS AND SPACE ADMINISTRATION LYNDON B. JOHNSON SPACE CENTER HOUSTON, TEXAS n058 January 1995 STS-68 Table of Contents INTRODUCTION. 1 MISSION SUMMARY. • . 3 PAYLOADS. 7 SPACE RADAR LABORATORY-2 • • • • • • • • • • • • • • • • • • • • • • • 7 CHROMOSOME AND PLANT CELL DIVISION IN SPACE EXPERIMENT . • . 8 COMMERCIAL PROTEIN CRYSTAL GROWTH EXPERIMENT. 8 BIOLOGICAL RESEARCH IN CANISTERS EXPERIMENT. • • • • 9 COSMIC RADIATION EFFECTS AND ACTIVATION MONITOR EXPERIMENT. • • • • • • • • • • • • • • • • • • • • • • • • • 9 MILITARY APPLICATIONS IN SHIP TRACKS EXPERIMENT •• 9 GETAWAY SPECIALS. • . 9 VEHICLE PERFORMANCE •••••••••••••••••••••••••••••••••• 11 SOUD ROCKET BOOSTER. • • • • • • • • • • • • • • • • • • • • • • • • • • • • 11 Launch Abort .................................. 11 Launch. .. 11 REDESIGNED SOUD ROCKET MOTOR. • • • • • • • • • • • • • • • • •• 12 Launch Abort .................................. 12 Launch ........................................ 12 EXTERNAL TANK. .. 13 Launch Abort . .. 13 Launch. .. 14 SPACE SHUTTLE MAIN ENGINES. • • • • • • • • • • • • • • • • • • • • • •• 15 Launch Abort. .. 15 Launch ........................................ 15 SHUrrLE RANGE SAFETY SYSTEM. • • • • . • • • • • • • • • • • • • • •• 16 Launch Abort. .. 16 Launch ........................................ 17 ORBITER SUBSYSTEMS. • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • 17 Main Propulsion System • • • • • • • • • • • • • • • • • • • • • • • • •• 17 Reaction Control Subsystem ••••••••.••••••••••••• 18 Orbital Maneuvering Subsystem. • • • • • • • • • • • • • • • • • •• 19 Power Reactant Strorage and Distribution Subsystem.. 20 Fuel Cell Powerplant Subsystem. • • • • • • • • • • • • • • • • • .• 20 Auxiliary Power Unit Subsystem • • • • • • • • • • • • • • • • • • •• 21 HydraulicslWater Spray Boiler Subsystem. • • • • • • • • • •• 22 Electrical Power Distribution and Control Subsystem.. 23 Environmental Control and Life Support Subsystem •• 23 Airlock Support System .......................... 24 Smoke Detection and Fire Suppression Subsystem. • •. 24 STS-68 Table of Contents Avionics and Software Support System •••••..•••••• 25 Displays and Controls Subsystem • • • • • • • • • • • • • • • • •• 26 Communications and Tracklna Subsystems •••••••.• 26 OperatibnallnstrumentatlonIModular Auxiliary Data System • • • • • • • • • • • • • . • • • • • • • • •• 27 Structures and Mechanical Subsystems • • • • • • • • • • • •• 28 Intearated Aerodynamics. Heatina and Thermal Interfaces. .. 28 Thermal Control Subsystem • • • • • • • • • • • • • • • • • • • • • •• 29 Aerothermodynamics. • • • • • • • • • • • • • • • • • • • • • • • • . • .. 29 Thermal Protection Subsystem. • • • • • • • • • • • • • • • • • • •• 30 REMOTE MANIPULATOR SYSTEM. • • • • • • • • • • • • • • • • • • • • • • • • • • •• 32 FLIGHT CREW EQUIPMENT/GOVERNMENT FURNISHED EQUIPMENT . • . • . .. 33 CARGO INTEGRATION. • . .. 35 DEVELOPMENT TEST OBJEcnVESJDETAILED SUPPLEMENTARY OBJECTIVES. .. ........................... 36 DEVELOPMENT TEST OBJECTIVES. • • • • • • • • • • • • • • • • • • • •. 36 DETAILED SUPPLEMENTARY OBJEcnVES••••••••••••.••• 38 PHOTOGRAPHY AND TELEVISION ANALYSIS. • • • • • • • • • • • • • • • • •• 40 LAUNCH PHOTOGRAPHY AND VIDEO DATA ANALYSIS. • • • •• 40 ON-ORBIT PHOTOGRAPHY AND VIDEO DATA ANALYSIS •••• 40 LANDING PHOTOGRAPHY AND VIDEO DATA ANALYSIS ••••• 41 List of Tables TABLE I • ST8-68 SEQUENCE OF EVENTS. • • • • • • • • • • • • • • • • • • •• 42 TABLE II • STs-&8 ORBITER PROBLEM TRACKING LIST•••••••••• 45 TABLE III· STs-&8 GFE PROBLEM TRACKING LIST •••••••••••••• 48 TABLE IV· MSFC ELEMENTS PROBLEM TRACKING LIST ••••••••• 50 Appendixes A - DOCUMENT SOURCES. .. A·1 B • ACRONYMS AND ABBREVIATIONS ••••••••••••••••.••.••.. B·1 ii INTRODUCTION The STS-68 Space Shuttle Program Mission Report summarizes the Payload activities as well as the Orbiter, External Tank (ET), Solid Rocket Booster (SRB), Redesigned Solid Rocket Motor (RSRM), and the Space Shuttle main engine (SSME) systems performance during the sixty-fifth flight of the Space Shuttle Program and the seventh flight of the Orbiter vehicle Endeavour (OV-105). In addition to the Orbiter, the flight vehicle consisted of an ET that was designated ET-65; three SSMEs that were designated as serial numbers 2028,2033, and 2026 in positions 1, 2, and 3, respectively; and two SRBs that were designated BI-067. The RSRM's that were installed in each SRB were designated as 360W040A for the left SRB, and 360W040B for the right SRB. This STS-68 Space Shuttle Program Mission Report fulfills the Space Shuttle Program requirement as documented in NSTS onoo, Volume VIII, Appendix E. The requirement that is stated in that document is that each major organizational element supporting the Program will report the results of their hardware (and software) evaluation and mission performance, plus identify all related in-flight anomalies. The primary objective of this flight was to successfully perform the operations of the Space Radar Laboratory-2 (SRL-2). The secondary objectives of the flight were to perform the operations of the Chromosome and Plant Cell Division in Space (CHROMEX), the Commercial Protein Crystal Growth (CPCG), the Biological Research in Canisters (BRIC), the Cosmic Radiation Effects and Activation Monitor (CREAM), the Military Application of Ship Tracks (MAST), and five Get-Away Special (GAS) payloads. The STS-68 mission was planned with a 10-day duration plus 1 extension day plus 2 contingency days, which were available for weather avoidance or Orbiter contingency operations. The sequence of events for the STS-68 mission is shown in Table I, and the Orbiter Project Office Problem Tracking List is shown in Table II. The official Government Furnished Equipment (GFE) Problem Tracking List is shown in Table III, and the Marshall Space Flight Center (MSFC) Problem Tracking List is shown in Table IV. In addition, the Integration and Payload in-flight anomalies are referenced in applicable sections of the report. Appendix A lists the sources of data, both formal and informal, that were used in the preparation of this report. Appendix B provides the definition of acronyms and abbreviations used in this document. All times are given in Greenwich mean time (G.m.t.) as well as mission elapsed time (MET). The six-person crew for STS-68 consisted of Michael A. Baker, Capt., U. S. Navy, Commander; Terrence W. Wilcutt, Major, U. S. Marine Corps, Pilot; Steven L. Smith, Mission SpeCialist 1; Daniel W. Bursch, Cdr., U. S. Navy, Mission Specialist 2; Peter J. K. Wisoff, Ph.D., Mission Specialist 3; Thomas D. Jones, Ph. D., Payload 1 Commander and Mission Specialist 4. STS-68 was the third space flight for the Commander; the second flight for Mission Specialist 2, Mission Specialist 3, and Mission Specialist 4; and the first space flight for the Pilot and Mission Specialist 1. 2 MISSION SUMMARY The first launch attempt of the STS-68 mission on August 18, 1994, ended at 230:10:53:58.157 G.m.t. [1.8 seconds prior to Solid Rocket Booster (SRB) ignition], when the SSMEs were shut down. SSME 3 high pressure oxidizer turbine (HPOT) discharge temperature A exceeded the Launch Commit Criteria (LCC) red line of 1560 oR. As a result, the vehicle was returned to the Vehicle Assembly Building (VAB) and all three SSMEs were replaced. The second launch attempt of the STS-68 mission resulted in an on-time launch at 273:11 :16:00.011 G.m.t. (6:16 a.m. c.d.t.) on September 30, 1994, after a countdown with no unplanned holds. Main engine cutoff (MECO) occurred at 273:11 :24:35 G.m.t. (00:00:08:35 MET), after a nominal launch phase. All SSME and RSRM start sequences occurred as expected and launch phase performance was satisfactory in all respects. First stage ascent performance was as expected. SRB separation, entry, deceleration, and water impact occurred as antiCipated. Both SRBs were recovered and returned to Kennedy Space Center (KSC ) for refurbishment. Performance of the SSMEs, ET, and main propulsion system (MPS) was nominal. The water spray boiler (WSB) system 2 gaseous nitrogen (GN2) regulator had two periods of internal out-of-specification leakage when the isolation valves were opened during the prelaunch time-frame. The isolation valves
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