Gemini Program Mission Report Gemini Ix-A

8/8/2019 Gemini Program Mission Report Gemini Ix-A

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MSC-G-R-66-6_ 172

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

GEMINI PROGRAM MISSION REPORT

GEMINI IX-A(u)

NOTICE: This document may be exempt from_ublic disclosure under the,Freedom of In-ormation Act (5 U.S.C. 552). Requests foz, its release to persons outside of _ U.S.Government should be handled under the prcvisions of NASA Policy Directive 1382.2.

iiii!!iiiiliili GROUP ,4...... "" DOWNGRAOEDAFTER 12 YEARS:-."':::':'"'...." , ": :_'_e:'!:!:!:i:i' CLASSJFII:D DOCUMFNT This material contains information_i (,_,e.,,,.,,,,.. affecting the National Defense of the United States within

._..:.:.. " the meaning of the espionage laws, Title 18, U.S.C., Sees.783 and 794, the transmission or revelation of which in any:::: :::: manner to on unauthorized person is prohibited by law. = o

MANNED SPACECRAFT CENTERHOUSTON, TEXAS

JULY 1966... . , . . . ....


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GEMINI FLIGHT HISTORYLaunch

Mission Description date Major accomplishmentsGemini Unmanned Apr. 8_ Demonstrated structural integrity.I 64 orbits 1964 Demonstrated launch vehicle systems perform-ance.Gemini Unmanned Jan. 19_ Demonstrated spacecraft systems performance.II suborbital 1965Gemini Manned Mar. 23_ Demonstrated manned qualification of theIII 3 orbits 1965 Gemini spacecraft.Gemini Manned June 3, Demonstrated spacecraft systems performanceIV 4 days 1965 and crew capability for 4 days in space.Demonstrated EVA.Gemini Manned Aug. 21, Demonstrated long-duration flight.V 8 days 1965 Demonstrated rendezvous radar capability andrendezvous maneuvers.Gemini Manned Oct. 2_ Demonstrated dual countdown procedures (GAATVVl 2 days 196_ and GLV-spacecraft)_ flight performance of

rendezvous TLV and flight readiness of the GATVsecon-(canceled dary propulsion system.after fail- Mission canceled after GATV failed to achievet_re of GATV) orbit.

Gemini Manned Dec. 4_ Demonstrated 2-week duration flight andVII 14 days 1965 station keeping with GLV stage II_ evaluated

"shirt sleeve" environment_ acted as therendezvous target for spacecraft 6, and de-monstrated controlled reentry to within7 miles of planned landing point.

Gemini Manned Dec. 153 Demonstrated on-time launch procedures_VIrA 1 day 1965 closed-loop rendezvous capability_ andrendezvous station keeping technique with spacecraft 7-

Gemini Manned Mar. 16_ Demonstrated rendezvous and docking with GATV,VIII 3 days 1966 controlled landing_ emergency recovery, andrendezvous multiple restart of GATV in orbit.

and dock, Spacecraft mission terminated early because ofand EVA an electrical short in the control system.

Gemini Manned May 17, Demonstrated dual countdown procedures.IX 3 days 1966rendezvous

and dockjand EVA(canceledafter fail-ure of TLV)

Gemini Manned June 33 Demonstrated three rendezvous techniques, EVAIX-A 3 days 1966 with detailed work tasks_ and precision land-

rendezvous ing capability.and dock,and EVA


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GEMINI PROGRAM MISSION REPORTGEMINI IX-A

Prepared by: Gemini Mission Evaluation Team

Approved by:

Charles W_.VMathewsManager_ Gemini Program

ge M. LowDeputy Director

NATIONAL AERONAUTICS AND SPACE ADMINSTRATIONMANNED SPACECRAFT CENTER

HOUSTON_ TEXAS

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NASA-S-66-7042 JUN

View of Baja California taken by the pilot while standing in the openhatch.


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Section Page

TABLES .......................FIGL_ES ......................

i.0 MISSION SUMMARY ................... i-i2.0 IN2RODUCTION ................... 2-13.0 VEHICLE DESCRIPTION ................. 3-1

3-1 GEMINI SPACECRAFT ................ 3-73.1.1 Spacecraft Structure .......... 3-73.1.2 Major Systems .............. 3-7

3.i.2.i Communications System ..... 3-73.i.2.2 Instrumentation and Recording

System ........... 3-83.i.2.3 Environmental Control

System ........... 3-83. i. 2.4 Guidance and Control

System ........... 3-83.1.2.5 Time Reference System ..... 3-83. i.2.6 Electrical System ....... 3-83. i.2.7 Propulsion System ....... 3-83- i.2.8 Pyrotechnic System ...... 3-93. i. 2.9 Crew-station furnishings and

equipment .......... 3-93.1.2. i0 Landing System ........ 3-103.i.2. ii Postlanding and Recovery

System .......... 3-103.1.2-12 Extravehic_ar equipment 3-10

3.2 GEMINI lAUNCH VEHICLE ............. 3-293.3 WEIGHT AK_ BALANCE DATA ....... 3-313.4 GEMINI AGENA TARGET VEHICLE .......... 3-333.5 TARGET LAUNCH VEHICLE ........... 3-35

3.5.1 Structure ............ 3-3_3.5.2 Major Systems .............. 3-35UNCLASSIFIED


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3.5.2. i Propulsion System .... 3-353.5.2.2 Hydraulic System ....... 3-353.5- 2.3 Guidance System ........ 5-363.5.2.4 Flight Control System ..... 3-363.5.2.5 Electrical System ...... 3-363.5- 2.6 Pnettmatic System ..... 3-363._.2.7 Instrumentation System .... 3-373._.2.8 Range Safety Command System . . 3-37

3.6 WEIGHT AND BALANCE DATA .......... 3-393.7 AUGMENTED TARGET DOCKING ADAPl_R ...... 3-41

3.7.1 Structure ................ 3-413.7. 1.1 Ascent shroud ......... 3-413.7- 1.2 Target docking adapter .... 3-413- 7.1.3 Equipment section ....... 3-423.7.1.4 Reaction control system

section ......... 3-423- 7.i.5 Battery module ........ 3-42

3.7-2 Major Systems ........... 3-433.7.2. i Communications system ..... 3-433.7.2.2 Instrumentation ........ 3-443.7-2.3 Guidance and Control System . . 3-443.7. 2.4 Electrical system ....... 3-463.7. 2.5 Reaction control system .... 3-463.7.2.6 Target Docking Adapter .... 3-47

4.0 MISSION DESCRII_ION ................. 4-14.i ACTUAL MISSION ................. 4-i4.2 SEQUENCE OF EVENTS ............... 4-74.3 FLIGHT TRAJECTORIES ........... 4-13

4.3.1 Gemini Spacecraft ........... 4-134.3.i.1 Launch .......... 4-134.3. !.2 Orbit ............. 4-144.3. !.3 Reentry ............ 4-19

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4.3.2 Target Launch Vehicle/A1_mented TargetDocking Adapter ........... 4-20

4.3.2. i Launch .......... 4-204.3.2.2 Orbit ............ 4-20

4.3.3 Gemini Launch Vehicle Second Stage . . 4-214.3.4 Gemini Target launch Vehicle ...... 4-22

5.0 VEHICLE PERFORMANCE ............. 5-i5.i SPACECRAFT PERFORMANCE ............ 5-1

5.1. i Spacecraft Structure 5-i5.1.2 Con_munications Systems ........ 5-3

5-i.2.i Ultrahigh frequency voicecommunications ....... 5-3

5. i. 2.2 High frequency voicecommunications ...... 5-4

5.i.2.3 Radar transponder . 5-45.i.2.4 Digital Command System .... 5-45. i.2.5 Telemetry transmitters 5-45. i.2.6 Antenna systems ........ 5-45-i.2.7 Recovery aids ........ 5-5

5.1.3 Instrumentation and Recording System 5-75.1.3.1 PCM tape recorder failure . . . 5-75. !.3- 2 System performance ...... 5-95.1.3.3 Delayed-time data quality . . . 5-95. i.3.4 Real-time data quality .... 5-9

5.I.4 Environmental Control System ...... 5-135.!.4.! Cabin pressure decay ..... 5-135. !.4.2 Left-hand suit-inlet

temperature ...... 5-135.i.4.3 Increased carbon dioxide

indication ...... 5-135. i.4.4 Water inflow at landing .... 5-135. !.4.5 Depletion of (krinking water . . 5-145. i.4.6 Extravehicular Life Support

System ........ 5-!5

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5.1.5 Guidance and Control System ....... 5-175.1.5.1 Summary ............ 5-175.1.5.2 Inertial Guidance System

performance evaluation 5-175.1.5.3 Control system performance

evaluation ...... 5-265- i.5.4 Start-compute-discrete

anomaly ........... 5-275.1.6 Time Reference System .......... 5-755.1.7 Electrical System ......... 5-77

5.1.7.1 Silver-zinc batteries . 5-775.1.7.2 Fuel-cell power system .... 5-775.1-7.3 Reactant supply system 5-785.1.7.4 Fuel-cell water-storage

system ........... 5-785.1.7.5 Power distribution system . 5-785.1.7.6 Sequential system ....... 5-78

5.1.8 Spacecraft Propulsion System ...... 5-855.1.8.1 Orbital Attitude and Maneuver

System ......... 5-855.1.8.2 Reentry Control System .... 5-865.1.8.3 Retrograde rocket system 5-87

5.1.9 Pyrotechnics .............. 5-895.1.10 Crew Station .............. 5-9!

5.1.10.1 Crew-station design andlayout .......... 5-91

5.1.10.2 Pilots' operationalequipment .......... 5-92

5.1.10. 3 Pilots' personal equipment 5-945.1.10.4 Space suits .......... 5-945.1.10. 5 Extravehicular equipment . 5-955.1.10.6 Bioinstrumentation ...... 5-99

5.1.11 Landing System ............. 5-1015.1.12 Postlandimg ............... 5-103

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5.2 GEMINI LAUNCH VEHICLE PERFORMANCE ....... 5-1055.2. i Airframe ................ 5_107

5-2.!.i Structural loads ....... 5-1075.2. i.2 Longitudinal oscillation

(POGO) ........... 5-i075.2. i.3 Post-SEC0 disturbance ..... 5-108

5.2.2 Propulsion ............... 5_1095.2.2. i Engines ............ 5-1095.2.2.2 Propellants .......... 5-1105.2.2.3 Pressurization ......... 5-111

5.2.3 Flight Control System .......... 5-1215.2.3. ! Stage I flight ........ 5-1215.2.3.2 Staging sequence ....... 5-1225.2.3.3 Stage !I flight ........ 5-1225.2.3.4 Post-SEC0 and separation

phase ............ 5-1225.2.4 Hydraulic System ............ 5-1295.2.5 Guidance System ............. 5-131

5.2.5. i Programmed guidance ...... 5-1315.2.5.2 Radio guidance ........ 5-131

5.2.6 Elec_rica! ............... 5-1355-2.7 Instrumentation ............. 5-137

5.2.7. i Ground ............ 5-1375.2.7.2 Airborne ........... 5-137

5.2.8 Malfunction Detection System ...... 5-1395.2.8. i Engine MDS .......... 5-1395.2.8.2 Airframe MDS ......... 5-1395.2.8.3 Tank Pressure Indications . 5-139

5.2.9 Range Safety and Ordnance ........ 5-141

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5.2.9. I Flight termination system . . . 5-1415.2.9- 2 Range safety trackingsystem ........... 5-1415-2.9. } Ordnance ......... 5-141

5-2. i0 Prelauuch 0perat ions .......... 5-1435.2. i0. i Launch attempt ...... 5-1435.2.10.2 Recycle ............ 5-1435.2.lO.3 _unch ............ 5-143

5.3 SPACECRAfT-GEMINI LAUNCH VEHICLE INTERFACEPERFORMANCE ................. 5-145

5.4 GEMINI AGENA TARGET VEHICLE PERFORMANCE .... 5-1475.5 TARGET LAUNCH VEHICLE PERFORMANCE ....... 5-149

5-5.1 Airframe .......... 5-1495.5.2 Propulsion System ............ 5-150

5.5.2. i Propulsion System ....... 5-1505.5.2.2 Propellant utilization .... 5-1515.5.2.3 Propellant loading ...... 5-151

5-5.3 Flight Control System .......... 5-1525.5.4 Pneumatic and Hydraulic Systems .... 5-153

5.5.4. i Pneumatic System ....... 5-1535-5.4.2 Hydraulic System ...... 5-153

5.5.5 Guidance System ........... 5-1545.5.5. i Programmed guidance ..... 5-1545.5.5.2 Radio Guidance System . 5-154

5.5.6 Electrical System ............ 5-1555.5.7 Instrumentation System ......... 5-156

5.5- 7.i Telemetry ........... 5-1565.5.7.2 Landline ........... 5-156

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5.5.8 Range Safety System ........... 5.1565.6 ATDA/TLV INTERFACE PERFORMANCE ......... 5-1575.7 SPACECRA2T/AD_3MENTED TARGET DOCKING ADAPTER

INTERFACE .................. 5-1595.8 AUGMENfED TARGET DOCKING ADAPI_',RPERFORMANCE . . 5-161

5.8. i Structure ............... 5-1615.8. i.i Ascent Shroud ......... 5-1615.8. i.2 Thermal control ....... 5-164

5-8-2 Communications System .......... 5-1695.8.2. i Tracking subsystem .... 5-1695.8.2.2 Telemetry subsystem .... 5-1695.8.2.3 Digital Comn_nd System 5-1695.8.2.4 Antenna system ........ 5-169

5.8.3 Instrumentation System ......... 5-1715.8.4 ATDA Guidance and Control ........ 5-1735.8.5 Electrical System ........... 5-1815.8.6 ATDA Propulsion System ......... 5-183

6.0 MISSION SUPPORT PERFORMANCE ........... 6-16. ! FLIGHT CONTROL ................. 6-1

6.1. ! Premission Operations .......... 6-16.!.!.1 Premission activities ..... 6-i6.!.i.2 Documentation ......... 6-16.!. i.3 MCC/network flight-control

operations ......... 6-16.1.1.4 Target Launch Vehicle/AugmentedTarget Docking Adapter . 6-2

6.1.2 Powered Flight ............. 6-26.1.2.1 TLV/ATDA powered flight .... 6-2

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6.1.2.2 Prelaunch 2 (time period betweenTLV/ATDA lift-off and GeminiSpace Vehicle lift-off . . . 6-4

6. i. 2.3 Final Gemini Space Vehiclecountdown .......... 6-5

6. i. 2.4 Gemini Space Vehicle poweredflight ........... 6-76.1.3 Spacecraft Orbital Flight ........ 6-86.i.4 Reentry ............... 6-196.i.5 Augmented Target Docking Adapter Orbital

Flight ............. 6-196.2 NETWORK PERFORMANCE .............. 6-23

6.2. i MCC and Remote Facilities ........ 6-236.2.2 Network Facilities ........... 6-23

6.2.2. i Remote sites ......... 6-236.2.2.2 Remote Site Data Processor . . 6-246.2.2.3 Communications ........ 6-256.2.2.4 Additional comments ...... 6-25

6.3 RECOVERY OPERATIONS .............. 6-276.3. i Recovery Force Deployment ........ 6-276.3.2 Location and Retrieval ......... 6-286.3.3 Recovery Aids .............. 6-30

6.3.3. i _ recovery beacon(243.0 me) ......... 6-30

6.3.3.2 HF transmitter (15.016 mc) 6-316.3.3.3 UHF voice transmitter

(296.8 me) ......... 6-316.3.3.4 UHF survival radio(243.0e) ......... 6-316.3.3.5 Flashing light ........ 6-316.3.3.6 F!uorescein sea marker .... 6-316.3.3.7 Swimmer interphone ...... 6-31

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6.3.4 Postretrieval Procedures ........ 6-316.3_ 5 Spacecraft 9 RCS Deactivation ...... 6-32

7.0 FLIGHT CREW ..................... 7-i7.i FLIGHT CREW PERFOEMANCE ............ 7-i

7.!.i Crew Activities ............. 7-I7.i.!.i Prelaunch through insertion . . 7-I7.i.i.2 M=3 (first) rendezvous .... 7-27. !. !. 3 Separation maneuver and

sextant practice ...... 7-37.i.i.4 Equi-period rendezvous .... 7-37.i.i.5 Rendezvous from above ..... 7-47.i.i.6 Experiments .......... 7-67.i.i.7 Extravehicular crew

performance ......... 7-87.!.i.8 Retrofire and reentry ..... 7-i07.!.i.9 Landing and recovery ..... 7-!07.1. i.i0 Mission training and training

evaluation ......... 7-!07.1.2 Gemini IX-A Pilots' Report ....... 7-21

7-i.2.i Prelaunch ........... 7-217-i.2.2 Powered flight ........ 7-217-i.2.3 Pretransfer _m_neuvers ..... 7-227.i.2.4 Rendezvous .......... 7-237.i.2.5 Extravehicular activity .... 7-287.i.2.6 Experiments .......... 7-317.i.2.7 Reentry ............ 7-327.i.2.8 Landing ............ 7-347-i.2.9 Systems operation . ...... 7-34

7.2 AEROMED!CAL .................. 7-437.2.1 Preflight ................ 7-43

7.2. i.i Medical records review .... 7-437.2.1.2 Health_ fitness, and diet . . . 7-437.2. i.3 Medical examinations ..... 7-447.2. i.4 Special baseline measurements . 7-447.2.1.5 Prelaunch medical support . . . 7-45

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7.2.2 Inflight ................ 7-457.2.2.1 Physiological monitoring 7-457.2.2.2 Medical observations ..... 7-46

7.2.3 Postflight ............... 7-497.2.3.1 Planned recovery procedures . . 7-}07.2.3.2 Recovery activities ...... 7-507.2.3.3 Bicycle ergometer studies . . . 7-}i

8.0 EXPERIMENTS .................... 8-i8.1 EXPERIMENT D-12_ ASTRONAUT MANEUVERING UNIT 8-7

8.1.1 Experiment Objectives ......... 8-78.1.2 Equipment Concept ........... 8-78.1.3 AMUBackpack Subsystems ......... 8-7

8.1.3.1 Propulsion system ....... 8-88.1.3.2 Flight control system . . . 8-98.1.3.3 Oxygen supply system . . 8-!08.1.3.4 Power supply system ...... 8-!08.1.3.5 Malfunction detection system 8-!08.1.3.6 Communications system ..... 8-11

8.1.4 AMU Interfaces ............. 8-118.1.4.1 Installation ......... 8-Ii8.1.4.2 Servicing provisions ..... 8-!28.1.4.3 Thermal interface . 8-128.1.4.4 Donning hardware" . ...... 8-128.1.4.5 Instrumentation andcommunications ....... 8-128.1.4.6 Crew-station displays ..... 8-138.1.4.7 Extravehicular Life Support

System/AMU Interfaces .... 8-148.1.4.8 Space suit/AMU interface . . . 8-i_

8.1.5 AMUMission Activity Description .... 8-168.1.5.1 Flight planning .... 8-168.1.5.2 Actual mission ...... 8-17

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8.1.6 AMU Performance ........ 8-19

8.!.6.i Prelaunch .... 8-i 98.i.6.2 Launch ..... 8-208.i.6.3 Orbit ............. 8-208.i.6.4 Extravehicular activity (EVA) . 8-208.i.6.5 Post-EVA ....... 8-23

8.1.7 Conclusions and Recommendations ..... 8-258.i.7.i Conclusions .... 8-258.1.7.2 Recommendations . . 8-25

8.2 EXPERIMENT D-14_ UHF/VHF POLARIZATIONMEASUREMENTS ............... 8-49

8.2.1 Objectives ............... 8-498.2.2 Equipment .............. 8-498.2.3 Flight Procedures ............ 8-518.2.4 Results ................ 8-51

8.3 EXPERIMENT M-5, BI0-ASSAYS OF BODY FLUIDS 8-598.3-I Objectives ........... 8-598.3.2 Equipment ............... 8-598.3.3 Procedures ............. 8-598.3.4 Results and Conclusions ......... 8-59

8.4 EXPERIMENT S-I, ZODIACAL LIGHT PHOTOGRAPHY . 8-638.4.1 Objectives ......... 8-638.4.2 Equipment ............ 8-63

8.4.3 Procedure ................ 8-638.4.4 Results ................ 8-638.4.5 Conclusions ............. 8-64

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8.5 EXPERIMENT S-10_ AGENA MICROMETEORITECOLLECTION ................. 8-69

8.5.1 Objective .......... 8-698.5.2 Equipment ............. 8-698.5.3 Procedures ............. 8-698.5.4 Results and Conclusions .... 8-70

8.6 EXPERIMENT S-II, AIRGLOW BORIZON PHOTOGRAPHY . 8-738.6.1 Objective ................ 8-738.6.2 Equipment ................ 8-738.6.3 Procedure ................ 8-738.6.4 Results .............. 8-748.6.5 Conclusions ............ 8-748.6.6 Recommendations ........... 8-74

8.7 EXPERIMENT S-12_ MICROMETEOEITE COLLECTION . . . 8-79

8.7.1 Objectives ............... 8-798.7.2 Equipment ............... 8-798.7_3 Procedures ............... 8-808.7.4 Results ................. 8-80

9- 0 CONCLUSIONS .................. 9-!i0.0 RECOMMENDATIONS .................. i0-iii. 0 REFERENCES .................... Ii-i12.0 APPENDIX ................ 12-1

1"2-. VEHICLE HISTORIES ................ 12-1

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12. !.l Spacecraft Histories ............ 12-i12. i.2 Gemini l_umch Vehicle Histories ....... 12-112. !.3 Augmented Target Docking Ads,pter

History .................. 12-i12. !.4 Target Launch Vehicle Histories ....... 12-i12.i.5 Astronaut Maneuvering Unit and Extra-

vehicular Life Support SystemHistories ................. 12-i12.2 WEATHER CONDITIONS ............. 12-1312.3 FLIGHT SAFETY REVIEWS ............ 12-25

12.3. i Gemini IX Mission .......... 12-2312.3. l.l Spacecraft Readiness

Review ......... 12-2512.3.1.2 EVA Equipment Review . . 12-2612.3. i.3 Gemini Launch Vehicle

Technical and PreflightReviews . . 12-26

12.3. i.4 Gemini Launch Vehicle FlightSafety Review Board . 12-26

12.3.1.5 Gemini Atlas-Agena TargetVehicle Technical and Pre-flight Reviews 12-26

12.3. i.6 GAATV Flight Safety ReviewBoard .......... 12-26

12.3. i.7 Mission Briefing ..... 12-2712.3.2 Gemini llg-A Mission ......... 12-27

12.3.2.1 Air Force SSD Flight SafetyReview Board ...... 12-27

!2.3.2.2 Spacecraft ReadinessReview ......... 12-27

12.3.2.3 Gemini SLV-5304 TechnicalReview ......... 12-28

12.3.2.4 Gemini SLV-5304 PreflightReview ......... 12-28

12-3.2.5 Mission Briefing ..... 12-28

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12.3.2.6 Launch Vehicles FlightSafety Review Board . . 12-28

12.4 SUPPLEMENTAL REPORTS ............ 12-29!2.5 DATA AVAILABILITY .............. 12-3112.6 POSTFLIGHT INSPECTION ............ 12-39

12.6.1 Spacecraft Systems ......... 12-4012.6. i.i Structure ......... 12-4012.6. i.2 Environmental Control

System ......... 12-4112.6.1.3 Communications System . 12-4112.6.1.4 Guidance and Control

System ......... 12-4112.6.1.5 Pyrotechnic system .... 12-4212.6.1.6 Instrumentation and Record-

ing System ....... 12-4212.6.1.7 Electrical System ..... 12-4312.6.1.8 Crew station furnishings and

equipment ........ 12-4412.6.1.9 Propulsion System . . . 12-4412.6. i.i0 Landing System ...... 12-4412.6. i. i! Postlanding recovery aids . 12-4512.6. i.12 Experiments ........ 12-45

12.6.2 Continuing Evaluation ........ 12-4312.7 TARGET LAUNCH VEHICLE 5303 FLIGHT

EVALUATION ................ 12-4713.0 DISTRIBUTION .................... 13-I

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Table PageL

3.1-I SPACECRAFT 9 MODIFICATIONS ............ 3-133. l-II CREW-STATION STOWAGE LIST ............. 3-163.2-1 GLV-9 MODIFICATIONS ............. 3-293.5-I TLV-5304 MODIFICATIONS .............. 3-384.2-I SEQUENCE OF EVENTS FOR GEMINI SPACE VEHICLE

LAUNCH PHASE .......... 4-84.2-II SEQUENCE OF EVENTS FOR GEMINI SPACECRAFT ..... 4-94.2-II SEQUENCE OF EVENTS FOR TLV/ATDA LAUNCH PHASE . . . 4-114.3-I COMPARISON OF PLANNED AND ACTUAL GEMINI SPACE VEHICLE

TRAJECTORY PARAMETERS ......... 4-234.3-II COMPARISON OF SPACECRAFT ORBITAL ELEMENTS BEFORE

AND AFI_R MANEUVERS ............ 4-254.3-111 SPACECRAT RENDEZVOUS MANEUVERS .......... 4-284.3-IV COMPARISON OF SPACECRAFT ORBITAL ELEMENTS .... 4-344.3-V COMPARISON OF PLANNED AND ACTUAL ATDA TRAJECTORY

PARAMETERS ................. 4-354.3-VI COMPARISON OF PLANNED AND ACTUAL OSCULATING ELEMENTS

AT ATDA INSERTION ............. 4-374.3-VI! COMPARISON OF ATDA ORBITAL ELEMENTS ........ 4-385.1.3-I DELAYED-TIME DATA FROM SELECTED STATIONS ..... 5-105.l.3-II _m_L-TD4EDATARECEIVEDFROMSELECTEDSTATIONS 5-11D. 1.5-I SPACECBAF2 GUIDANCE AND CONTROL SUMMARY CHART . . . 5-305. i.5-II RESULTS OF INSERTION VELOCITY ADJUST ROUTINE

(_vAR) .................... 5-365.1.5-111 ASCENT IGS AND TRACKING SYSTEM ERRORS 5-37

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: viii UNCLASSIFIEDTable Page5.1.5-IV GUIDANCE ERRORS AT SEC0 + 20 SECONDS ..... 5-395.i.5-V ORBIT INJECTION PARAMETERS AT SEC0 + 20 SECONDS . . 5-405.i.5-VI TRANSLATION MANEUVERS ............... 5-415.i.5-vii pLAcFO_ Ar,TG__'_NTCCURACYPRIOR_0 MAJOR

MANEUVERS .................... 5-445. i.5-VIII COMPARISON OF COMPUTED SOLUTIONS WITH VEIOCITY

CHANGES ACCOMPLISHED ON M=3 RENDEZVOUSMANEUVERS .............. 5-49

5.i.5-IX THRUST HISTORIES FOR THREE SIMULATIONS OF M= 3RENDEZVOUS .................. 5-46

5-1.5-X CHANGE IN PITCH GIMBAL ANGLE AND RADAR ELEVATIONPRECEDING TPI ON M=3 RENDEZVOUS ......... 5-47

5. i. 5-Xl COMPARISON OF CALCULATED VELOCITY COMPONENTS FORM=3 RENDEZVOUS ........... 5-48

5.i.5-XII COMPARISON OF COMPUTED SOLUTIONS WITH VELOCITYCHANGES ACCOMPLISHED ON RENDEZVOUS FROM ABOVE . . 5-49

5.I.5-XIII THRUST HISTORIES FOR THREE SIMULATIONS OFRENDEZVOUS FROM ABOVE .............. 5-50

9. i. 5-XIV COMPUTER TELEMETRY REENTRY PABAMETERS ....... 5-515. i.5-XV START-COMPUITE-DISCRETE ANOMALY EVENTS ....... 5-525.2.2-1 STAGE I ENGINE PERFORMANCE ............ 5-1125.2.2-II STAGE II ENGINE PERFORMANCE ............ 5-i139.2.2-111 GLV-9 PROPELLANT LOADING SUMMARY ......... 5-1!45.2.2-IV STAGE I ULIAGE GAS PRESSURE ............ 5-i155.2.2-V STAGE II rAN]( _GE GAS PRESSURE ......... 5-i159.2.3-1 TARS ROLL AND PITCH PROGRAMS ........... 5-1235.2.3-If MAXIMUMRATESAm) ATTITUOEERRORSDtmiNGSTAGEI_IGNT .................. 5-124UNCLASSIFIED


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UNCLASSIFIEDTable Page5.2.3-111 _XIMUM STAGING RATES AND ATTITUDE ERRORS DURING

STAGE II _IG_ ............. 5_1255.2.3-IV VEHICLE RATES BETWEEN SEC0 AND SPACECP_

SEPARATION ................ 5-1265.2.4-1 HYDRAULIC PRESSURES ................ 5-1305.2.8-I GEMINI IX-A MALFUNCTION DETECTION SYSTEM SWITCHOVER

PARAmeTERS ................... 5-1405.8.3-I ATDA P_-TIME DATA RECEIVED FROM SEI_TED

STATIONS .................... 5-1726.2-I GEMini IX-A NETWORK CONFIGURATION ......... 6-266.3-1 RECOVERY SUPPORT ................. 6-347.1.1-1 CREW TRAINING SUMMARY .............. 7-ii7. i. 2- I PRETRANSFER MANEUVERS

(a) Prime rendezvous ............... 7-36(b) Equi-period rendezvous ............ 7-36(c) Rendezvous from above ............ 7-36

7.1.2-11 COMPARISON OF SOLUTIONS FOR THE TRANSFER MANEUVERSFOR THE M=3 RENDEZVOUS ............. 7-37

7.1.2-111 MANEUVERS FOR THE EQU!-PERIOD RENDEZVOUS ..... 7-387.1.2-IV COMPARISON OF SOLUTIONS FOR T_E TRANSFER _VEUVERS

FOR THE RENDEZVOUS FROM ABOVE .......... 7-397.2-1 URINALYSIS

(a) Command Pilot ............... 7-52(b) Pilot .................... 7-52

7.2-11 HEMATOLOGY(a) Command Pilot ................ 7-53(b) Pilot .................... 7-54

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= UNCLASSIFIEDTable Page7.2-III URINE CHEMISTRIES

(a) Command Pilot ................ 7-55(b) Pilot ................. 7-587.2-IV LAUNCH MORNING ACTIVITIES_ JUNE 3_ 1966 ...... 7-618.O- I EXPERIMENTS ................... 8-28.0-1I FINAL EXPERIMENT FLIGI_ PLAN FOR GEMINI IX-A . . 8-38.1-I BACKPACK WEIGHT .................. 8-278.1-II TELEMETRY PARA)_TER LIST ............. 8-2812.2-I LAUNCH AREA ATMOSPHERIC CONDITIONS FOR THE TARGET

LAUNCH VEHICLE/AI_]MENTED TARGET DOCKING ADAPTER . 12-1512.2-II LAUNCH AREA ATMOSPHERIC CONDITIONS FOR GEMINI

LAUNCH VEHICLE ................. 12-1712.2-III REENTRY AREA ATMOSPHERIC CONDITIONS ....... 12-1912.4-I GEMINI IX-A SUPPLEMENTAL REPORTS ......... 12-3012.5-I SUMMARY OF INSTRUMENTATION DATA AVAILABILITY 12-32

12.5-II SUMMARY OF PHOTOGRAPHIC DATA AVAILABILITY ..... 12-3412.5-III LAUNCH PHASE ENGINEERING SEQUENTIAL CAMERA DATAAVAILABILITY

(a) Spacecraft and GLV ........ " ...... 12-35(b) TLV and ATDA ................. 12-37

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UNCLASSIFIEDFIGURES

Figure Page3.0-1 GLV - spacecraft relationships

(a) lau_ich configuration ............... 3-2(b) Dimensional axes and guidance coordinates .... 3-3

3.0-2 TLV/ATDA relationship(a) launch configuration ............... 3.4(b) Dimensional axes and guidance coordinates,

ATDA ...................... 3-5(c) Dimensional axes and guidance coordinates,

TLV ...................... 3-63.1-1 Spacecraft arrangement and nomenclature ........ 3-213.1-2 Orbital Attitude and Maneuver System ......... 3-223.1-3 Reentry Control System ................ 3-233.1-4 Spacecraft controls and displays ........... 3-253.1-5 Spacecraft interior stowage areas

(a) View looking into con_nand pilot's side ...... 3-26(b) View looking into pilot's side .......... 3-27

3.1-6 Planned sequence for donning Astronaut ManeuveringUnit ........................ 3-28

3.7-1 Augmented Target Docking Adapter ........... 3-483.7-2 Simplified schematic of shroud pyrotechnic

circuit .................... 3_493.7-3 Shroud separation sequence .............. 3-503.7-4 ATDA equipment section .............. 3-513.7-5 Co_and link block diagram ........... 3-523.7-6 TSS system functional block diagram .......... 3-53

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UNCLASSIFIEDFigure Page3.7-7 ATDA power and power distribution ........... 3-543.7-8 Status display panel ................. 3-554.1-1 Planned and actual Gemini IX-A mission with

planned alternates included ............. 4-54.3-1 Ground track for the Gemini IX-A orbital mission

(a) Revolutions i through 5 ............. 4-39(b) Revolutions 12 through 14 ............ 4-40(c) Reentry .................... 4-41

4.3-2 Trajectory parameters for GLV - spacecraft launchphase

(a) Altitude and range ................ 4-42(b) Space-fixed velocity and flight-path angle .... 4-43(c) Earth-fixed velocity and flight-path angle .... 4-44(d) Dynamic pressure and Mach number ......... 4-45(e) Longitudinal acceleration ............ 4-46

4.3-3 Apogee and perigee altitude for the Gemini IX-Amission ....................... 4-47

4. 3. 4 Rendezvous during the Gemini IX-A Mission

(a) Relative range, azimuth, and elevation fromSpacecraft 9 to ATDA during midcoursemaneuvers for M=3 rendezvous .......... 4-48

(b) Relative range, azimuth, and elevation fromSpacecraft 9 to ATDA during terminalphase maneuvers of M=_ rendezvous ....... 4-49

(c) Relative trajectory profile for M=3 rendezvous,measured from ATDA to Spacecraft 9 in curvi-linear coordinate system ............ 4-50

(d) Relative range, azimuth, and elevation fromSpacecraft 9 to ATDA during midcoursemaneuvers of the equi-period rendezvous .... 4-51

(e) Relative range, azimuth, and elevation fromspacecraft 9 to ATDA during terminal phaseof the equi-period rendezvous ......... 4-52

(f) Relative trajectory profile of the equi-periodrendezvous measured from ATDA to Spacecraft 9in curvilinear coordinate system ........ 4-53

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UNCLASSIFIED iiiFigure Page

(g) Relative range, azimuth, and elevation fromSpacecraft 9 to ATDA during midcourse andterminal phase maneuvers of the rendezvousfrom above .................. 4-54

(h) Relative trajectory profile of the rendezvousfrom above, as measured fr_n ATDA to Space-craft 9 in curvilinear coordinate system . . . 4-55

4.3- 5 Trajectory parameters for the Gemini !X-A missionreentry phase

(a) latitude, longitude, and altitude ....... 4-56(b) Space-fixed velocity and flight-path angle . . . 4-57(c) Earth-fixed velocity and flight-path angle . . . 4-58(d) Dynamic pressure and Mach nt_nber ........ 4-59(e) Longitudinal deceleration ........... 4-60

4.3-6 Trajectory parameters for TLV/ATDA launch phase(a) Altitude and range ............... 4-61(b) Space-fixed velocity and flight-path angle . . . 4-62(c) Earth-fixed velocity and flight-path angle . . . 4-63(d) Dynamic pressure and Mach number ........ 4-64(e) Longitudinal acceleration ........... 4-65

5.1.5-1 Comparisons of launch vehicle and spacecraft ._steering errors .................. 5-55

5.1.5-2 Post-SECO acceleration and rate profile ....... 5-565.1.5-3 Insertion maneuvers ................. 5-575.1.5-4 Reconstructed IVI readings during insertion

maneuvers ..................... 5-585.1.5-5 Comparisons of spacecraft IGS and radar tracking

velocities ................... 5-595.1.5-6 IMU error coefficient history ............ 5-605.1.5-7 Radar RF characteristics as a function of time

for the M=3 rendezvous .............. 5-625.1.5-8 Radar RF characteristics as a function of time

during the equi-period rendezvous and rendez-vous from above .................. 5-63

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UNCLASSIFIEDFigure Page5.1.5-9 Radar azimuth and yaw-gimbal angle comparison .... 5-645.1.5-10 Total-velocity-to-rendezvous comparison for the

M=3 rendezvous .................. 5-655.1.5-11 Simulated relative trajectory profile,

measured from ATDA to Spacecraft 9, forM=3 rendezvous ................ 5-66

5.1.5-12 Closing trajectory for M=3 rendezvous ........ 5-675.1.5-13 Total-velocity-to-rendezvous comparison for the

rendezvous from above ............... 5-68

5.1.5-14 Simulated relative trajectory profile, measuredfrom ATDA %o Spacecraft 9_ for rendezvousfrom above .................... 5-69

5.1.5-15 Comparison of longitude and latitude from IGS andtracking data ............. 5-70

5.1.5-16 Touchdown comparisons .............. 5-715.1.5-17 Control system performance during the extra-vehicular activities

(a) Platform mode ................. 5-72(b) Pulse mode ................... 5-73

5.1.5-18 Reentry time history ............. 5-745.1.7-1 Spacecraft 9 fuel-cell performance ......... 5-795.1.7-2 Fuel-cell section i performance (Izncorrected for

temperature and pressure) ............ 5-805.1.7-3 Fuel-cell section 2 performance (uncorrected for

temperature and pressure) ............. 5-815.1.7-4 load sharing between fuel-cell sections ....... 5-825.1.7-5 load sharing between fuel-cell stacks ........ 5-835.1.$-i OAMS propellant consumption ............. 5-$8

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UNCLASSIFIEDFigure Page5.1.11-1 Landing system performance ............. 5-1025.2.2,1 Stage I engine start transient ........... 5-1165.2.2-2 Stage I engine performance ............. 5-1175.2.2- 3 Stage II engine performance ............. 5-1185.2.2-4 Stage II engine shutdown transient ......... 5-1195.2.3-i Attitude errors after SECO ............. 5-1275.8.1-1 Partially detached ATDA shroud ......... 5-1655.8.1-2 Band-clamp halves held together by _{iringto the connectors ................. 5-1665.8.1-3 ATDA orbital equipment temperatures ......... 5-1675.8.4-1 Comparison of ATDA primary and secondary control

system performance ................ 5-1765.8.4-2 Initial ATDA rate anomaly

(a) Yaw rate ................... 5-177(b) Roll rate ................... 5-178(c) Pitch rate ................... 5-179

6.3-1 Launch site landing area recovery forcedeployment .................... 6-36

6.3-2 Gemini IX-A launch abort areas and recoveryship and aircraft deployment ........... 6-37

6.3- 3 Gemini IX-A landing zone location and forcedeployment .................... 6-38

6.3-4 Contingency recovery force deployment ........ 6-39

6.3-5 Recovery force and network aircraftdeployment in primary landing area ........ 6-406.3-6 Spacecraft landing .............. 6-416.3-7 Spacecraft landing information, as

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UNCLASSIFIEDFigure Page7.i.i-i Summary flight plan

(a) 0 to I0 hours g.e.t .............. 7-12(b) i0 to 20 hours g.e.t ............ 7-13(c) 20 to 30 hours g.e.t .............. 7-14(d) 30 to 40 hours g.e.% .............. 7-15(e) 40 to 50 hours g.e.t .............. 7-16(f) 50 to 60 hours g.e.t ............. 7-17(g) 60 to 70 hours g.e.t ............ 7-18(h) 70 to 73 hours g.e.t .............. 7-19

7.i.2-! Onboard target-centered coordinate plot ofrendezvous

(a) M=3 rendezvous ................. 7-40(b) Equi-period rendezvous ............. 7-4!(c) Rendezvous from above ............. 7-42

7.2-1 Tilt table studies(a) Cormmand pilot ............. 7-62(b) Pi ot ..................... 7-63

7.2-2 Exercise capacity test result ........ 7-647.2-3 Physiological measurements

(a) Command pilot ................ 7-66(b) Pilot .................... 7-677.2-4 Physiological data during EVA ............ 7-687.2-5 Exercise studies on the Gemini IX-A pilot ...... 7-698.i-I Experiment D-12_ AMU configuration ......... 8-298.i-2 Experiment D-12_ AMU external structure ....... 8-308.1-3 Experiment D-12, AMU internal configuration ..... 8-318.i-4 Experiment D-12, AMU propulsion system ....... 8-328.i-5 Experiment D-12_ AMU propulsion system

schematic ..................... 8-33

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UNCLASSIFIED : viiFigure Page8.1-6 Experiment D-12, AMU thruster arrangement ...... 8-348.i-7 Experiment D-12, AMU stabilization and control

system ...................... 8-358.1-8 Experiment D-12, AMU flight control system ..... 8-368.1-9 Experiment D-12, AMU oxygen supply system

to ELSS ...................... 8-378.i-!0 Experiment D-12, oxygen supply functional diagram . . 8-388.i-ii Experiment D-12, battery pack assembly ....... 8-39

8.1-12 Experiment D-12, RCS electrical system ....... 8-408.1-13 Experiment D-12, AMU 28 V dc power supply ...... 8-418.1-14 Experiment D-12, malfunction detection system

functional diagram ................ 8-428.1-15 Experiment D-12, colmmunications, telemetry, and

electrical systems arrangement .......... 8-4 38.1-16 Experiment D-12, telemetry system flmctional

schematic ..................... 8-44

8.1-17 Experiment D-12, voice communications systemfunctional diagram ................ 8-458.1-18 Experiment D-12, stowage in adapter assembly .... 8-468.1-19 Experiment D-12, AMU donning hardwsm:e ........ 8-478.1-20 Experiment D-12, _h_YJcontrols and indicators .... 8-488.2-1 Experiment D-14_ onboard Gemini transmitter block

diagram ...................... 8-538.2-2 Experiment D-14, onboard Gemini transmitter ..... 8-548.2-3 Experiment D-14, colinear dipole antenna, extended

position ..................... 8-59

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UNCLASSIFIEDFigure Page8.2-4 Experiment D-14, colinear dipole antenna

folded position .................. 8-568.2- 5 Experiment D-14, functional diagram of ground

receiving equipment ................ 8-578.2-6 Experiment D-14, ground receiving equipment ..... 8-588.3-i Experiment M-5, onboard equipment .......... 8-618.4-1 Experiment S-I_ photograph of Milky Way ...... 8-668.4-2 Experiment S-l, photograph of zodiacal light .... 8-67

8.5-1 Experiment S-lO, sample collection device ...... 8-718.6-1 Experiment S-If, airglow horizon 20-second

exposure with filter ............... 8-758.6-2 Experiment S-II_ airglow horizon 5-second

exposure without filter .............. 8-768.6-3 Experiment S-II_ airglow horizon 2-second

exposure without filter ............ 8-778.7-1 Experiment S-12_ micrometeorite collection

equipment ..................... 8-828.7-2 Experiment S-12, micrometeorite collection

equipment configuration .............. 8-838.7-3 Experiment S-12, micrometeorite impact tear

hole, magnified 35 000 times ............ 8-848.7-4 Experiment S-12_ micrometeorite impact hole

magnified 35 000 times .............. 8-8512. i-i Spacecraft 9 test history at contractor facility 12-212.1-2 Spacecraft 9 problem areas at contractor

facility ..................... 12-312.1-3 Spacecraft 9 history at Cape Kennedy ........ 12-412.1-4 Spacecraft 9 significant problems at Cape Kennedy . 12-5

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UNCLASSIFIEDFigure Page12.1-5 GLV-9 history at Denver and Baltimore ........ 12-6

12.1-6 GLV-9 history at Cape Kennedy ............ 12- 712.1-7 ATDA manufacturing and systems test at

contractor facility ................ 12-812. I-8 ATDA history at Cape Kennedy ......... 12-912.1-9 SLV 5304 history at contractor facility ....... 12-1012.1-10 SLV-3 5304 history at Cape Kem_edy ......... 12-1112.1-11 AMU and ELSS history at Cape Kennedy ........ 12-1212.2-1 Variation of wind direction and velocity

with altitude for the TLV/ATDA at 15:28 G.m.t.,June i, 1966 ................... 12-21

12.2-2 Variation of wind direction and velocitywith altitude for the Gemini Space Vehicleat 12:00 G.m.t., June 3, 1966 ......... 12-22

12.2- 3 Variation of wind direction and velocity withaltitude for the Gemini IX-A reentry areaat 14:25 G.m.t., June 6, 1966 ......... 12-23

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UNCLASSIFIED 1_1i.0 MISSION SUMMARY

Gemini IX-A was the seventh manned mission and the third rendezvousmission of the Gemini program. The Target Launch Vehicle/Augmented Tar-get Docking Adapter was launched from Complex 14, Cape Kennedy, Florida,at 10:00:02 a.m.e.s.t, on June i, 1966. The Gemini Space Vehicle, withAstronaut Thomas P. Stafford as the Command Pilot and Astronaut EugeneA. Cernan as the Pilot, was launched from Complex 19, Cape Kennedy,Florida, at 8:39:33 a.m.e.s.t, on June 3, 1966_ at the exact secondfor a nominal rendezvous during the third revolution. The flight wassuccessfully concluded on June 6, 1966, with the recovery of the flightcrew in the spacecraft. They were hoisted aboard the prime recoveryship (U.S.S. Wasp) approximately 53 minutes after a very accurate land-ing within sight of the recovery ship. The crew completed the flightin good physical condition and demonstrated full control of the space-craft and competent management of all aspects of the mission.

After completing rendezvous, the docking portion of a primary ob-jective to rendezvous and dock could not be accomplished because theascent shroud was still attached to the Target Docking Adapter. Laterin the flight a primary objective to conduct extravehicular activitieswas completed when the pilot performed extravehicular activities forover two hours; however, evaluation of the Astronaut Maneuvering Unit,a secondary objective, was not completed due to fogging of the pilot'svisor. Secondary objectives that were accomplished were - to rendezvousduring the third revolution, to conduct systems evaluations, to accom-plish an equi-period rendezvous, to accomplish a rendezvous from above,and to demonstrate controlled reentry. A secondary objective to conductexperiments was not completely accomplished in that the Agena Microme-teorite Collection Experiment, S-IO, could not be completed because ex-travehicular activities were not conducted while near the target vehicle.

The launch of the Target Launch Vehicle/Augmented Target DockingAdapter was very satisfactory for the Gemini IX-A mission. The count-down was completed with no holds, and, as a result of a nominal lift-off and launch phase, the Augmented Target Docking Adapter was insertedinto a near-circular orbit having an apogee of 161.5 nautical miles anda perigee of 158.5 nautical miles, referenced to the Fischer ellipsoidearth model of 1960.

The Gemini Space Vehicle was to have lifted off approximatelyi hour 40 minutes after the target vehicle; h_ever_ the launch had tobe postponed when the T-3 minute launch-azimu_l update to the spacecraftcomputer could not be transmitted to the spacecraft because of ground

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1_2 UNCLASSIFIEDequipment problems. The launch was reschedu!ed for June 3, 1966, andtook place on that day, within one-half second of the desired time.The performance of the Gemini Imunch Vehicle was satisfactory in all re-spects. The first-stage flight was normal, with all planned events oc-curring within the required limits, and staging and second-stage flightwere completed normally. The spacecraft was inserted into an orbit witha perigee of 85.7 nautical miles and an apogee of 144.0 nautical miles,referenced to the Fischer ellipsoid earth model of 1960. The perigeewas 1.0 nautical mile lower than planned, and the apogee was 4.6 nauticalmiles below that planned. The offset yaw-steering technique placed thespacecraft into an orbital plane very close to the plane of the target-vehicle orbit and the slant range to the target vehicle was a nominal572 nautical miles.

During the following period of 4 hours 7 minutes, seven maneuverswere performed by the crew to effect a rendezvous with the AugmentedTarget Docking Adapter. The first three maneuvers were conducted usingground-computed values and pointing data. The terminal phase initiatemaneuver was conducted usimg information from the onboard computer_ground computer, and onboard charts. The final three maneuvers wereconducted line of sight using the onboard computer and displays. Con-tinuous radar lock-on was achieved at a range of 120 nautical miles_and no significant losses of lock occurred until the rendezvous was com-pleted st 4 hours 15 minutes ground elapsed time.

The crew reported that the shroud of the Augmented Target DockingAdapter had not separated from the vehicle and that docking could notbe accomplished. After approximately 45 minutes of station keepingand inspection of the target vehicle, the crew performed a radial sepa-ration maneuver in preparation for an equi-period remdezvous which wasto be performed using onboard optical techniques. The ground-computedmaneuvers and !GS solutions were not used for this rendezvous. Terminalphase initiate and the accompanying midcourse corrections and brakingmaneuvers were performed to complete the equi-period rendezvous at ap-proximately 6 hours 36 minutes ground elapsed time.

After station keeping for approximately40 minutes, a second sepa-ration maneuver was performed by the crew in preparation for a rendez-vous from above which was to be completed after the scheduled sleepperiod. During this third rendezvous_ seven maneuvers were performed,beginning at 18:23:19 ground elapsed time, resulting in a rendezvous atapproximately 21 hours 42 minutes ground elapsed time. The maneuversresulted in a rendezvous which simulated a Command Module rendezvouswith a Lunar Module in a lower orbit around the moon. It was discoveredthat the crew will probably not be able to track the target opticallyon the dayside pass during this type of rendezvous due to the low light

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UNCLASSIFIED 1-3contrast and high relative velocity between the target and the sunlitbackground. The crew stated that radar was essential until the rangehad closed to approximately two nautical miles.

After completing the third rendezvous_ ard prior to starting thepreparations for extravehicular activity_ the command pilot requestedthat the activity be delayed due to crew fatigue and ground control con-curred. The preparations were postponed and _e extravehicular activitywas rescheduled for the following day. At 22 hours 59 minutes groundelapsed time, the crew performed the final separation maneuver from theAugmented Target Docking Adapter. The crew rested and conducted experi-ments for the remainder of the second day.

After the second scheduled sleep period, the crew began preparationsfor extravehicular activity and the right-hand hatch was opened at49 hours 23 minutes ground elapsed time. The extravehicular phase ofthe flight proceeded in a satisfactory manner until the pilot began pre-paring the Astronaut Maneuvering Unit for dor_Ling. He immediately en-countered greater than anticipated difficulty in maintaining his positionrelative to the work area. This increased wo_load apparently causedthe Extravehicular Life Support System to become overloaded with moistureand the pilot's visor began fogging at the sides. The fogging steadilyincreased to the point that he was unable to see clearly in any direction.Rest periods were taken by the pilot in an unsuccessful attempt to clearthe visor_ and_ because it was anticipated that the workload to completethe Astronaut Maneuvering Unit evaluation wou]_ result in additionalfogging_ the extravehicular operations were terminated. The pilot in-gressed the spacecraft and the hatch was closed at approximately 51 hours28 minutes ground elapsed time. The spacecraft hatch was open for atotal of 2 hours and D minutes for extravehicular activity. The remain-der of the third day was spent conducting experiments.

After the third scheduled sleep period, _e crew began preparationsfor retrofire and landing in the revolution-4_ primary recovery area.The retrofire sequence was initiated over the Canton station in thePacific Ocean at 71:46:44 ground elapsed time. The landing point achievedwas approximately one-third mile from the planned landing point, and3.5 nautical miles from the prime recovery ship (U.S.S. Wasp). Afterlanding at 72:20:50 ground elapsed time, the crew elected to stay in thespacecraft and were hoisted aboard the prime recovery ship at approxi-mately 73 hours 13 minutes ground elapsed time, about 92 minutes afterlanding.

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UNCLASSIFIED 2-12.0 INTRODUCTION

A description of the Gemini IX-A mission and a discussion of theresults are contained in this report. The report covers the time fromthe start of the simultaneous countdown of the Target Launch Vehicle/Augmented Target Docking Adapter and the Gemini Space Vehicle to thedate of publication of this report. Detailed discussions are found inthe major sections related to each principal area of effort. Some re-dundancy may be found between the various sections where it is requiredfor a logical presentation of the subject matter. Included in the ap-pendix (section 12.0) is a report on the Target Launch Vehicle whichfailed during the Gemini IX mission. The evaluation of the Gemini AgenaTarget Vehicle fl_ on the Gemini IX mission is discussed in a supple-mental report to this report. No other formal report will be made onthe Gemini IX mission.

Data were reduced from telemetry; onboard records_ and ground-based radar tracking, but were reduced only in areas of importance. Inevaluating the performance of the Target Launc_ Vehicle and Gemini LaunchVehicle_ all available data were processed. _e evaluation of all ve-hicles involved in the mission consisted of analyzing the flight resultsand comparing these results with the results from ground tests and fromprevious missions.

Section 6.1, FLIGHT CONTROL, is based on observations and evalua-tions made in real time and, therefore, may not coincide with the re-sults obtained from the detailed postflight analysis.

Brief descriptions of the experiments flown on this mission arepresented in section 8.0; and preliminary results and conclusions ofthe experiments performed are included.

The mission objectives_ as set forth in _e Mission Directive,formed the basis for evaluation of the flight and were of paramountconsideration during preparation of this report. The primary objectivesof the Gemini !X-A mission were as follows:

(a) Perform rendezvous and docking(b) Conduct extravehicular activities.

The secondary objectives of the Gemini IX-A mission were asfollows:(a) Perform rendezvous and docking during the third revolution

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2_2 UNCLASSIFIED(b) Conduct systems evaluation(c) Perform equi-period re-rendezvous(d) Conduct experiments(e) Conduct docking practice(f) Perform re-rendezvous from above(g) Demonstrate a controlled reentry.At the time of publication of this report_ more detailed analyses

of data on the performance of both launch vehicles and the Radio GuidanceSystem were continuing. Analysis of the spacecraft Inertial GuidanceSystem was also continuing. Supplemental reports_ listed in section 12.4_will be issued to provide documented results of these analyses.

_he results of previous Gemini missions are reported in refer-ences i through 9.

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UNCLASSIFIED 3-13.0 VEHICLE DESCRIPTION

The manned vehicle for the Gemini IX-A mission consisted of Space-craft 9 and Gemini Launch Vehicle (GLV) 9. Tibe second vehicle consistedof the Augmented Target Docking Adapter (ATDA) and the Target LaunchVehicle (TLV) 5304.

The general arrangement and major reference coordinates of themanned Gemini Space Vehicle are shown in figure 3.0-1. Section 3.1 ofthis report describes the spacecraft configuration including the Extra-vehicular Life Support System (ELSS)_ section 3.2 describes the GLVconfiguration_ and section 3.3 provides the space vehicle weight andbalance data. The general arrangement and major reference coordinatesof the TLV and ATDA are shown in figure 3.0-2. Section 3.5 describesthe TLV configuration_ and section 3.6 provides the weight and balancedata of the ATDA and the TLV. Section 3.7 describes the ATDA con-figuration.

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UNCLASSIFIEDNASA-S-66-6882JUN

Spacecraftstations Launch-vehiclestations

Z239.28'b"jf [ Reentry ,--m ' _X

.X,_x 50.985Z233.97-" | I=1=1 56. 295Spacecraft assembly _ _

Adapter /assembly .... . , _.Z13.44 ' I n'x X 276.82.5 Compartment1Oxidizer_- _iZ 1'= ---------X 299.151q "n"_'---'_-_ X 319.522 ---Fuel "-. :'-", _, -_ _.._X 384.522 Compartment 2

Engine _- ','J[_ "' _ X 424.522=lP_l=l, -_ X 430.000 -- --u,mua, ,.LL', I dzstation-_--_ ,--7 _X 499o130

separation X 583.200

"2_ X 621o727X 649.727 -- --

Launchvehicle OxidizerIIt IIiII- ----"-- ' X 887.826 Ti I , L." Compartment4t / ;-_ \I ! 1- --i' ,, X 982.326 --i II I,III

Fuel',',IiIItlIII Ii I

- ---[,_7 X 1224.311 ___

Engine " k---,J /gimbal , ,.-- ,' Compartment5station _ _ "':,,, X ]274.21

' L-t--.,, X 1342.31 --(a) Launch configuration.

Figure 3.0-1. - GLV- spacecraftrelationships.

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Launch vehicle pitchaxis _ /----- Launch vehicleSpacecraftyawaxis / _y quadrantsystem

Spacecraftcoordinatesystem

Launch vehiclecoordinatesystem r Launch vehicle yawaxis] Spacecraftpitch axisZo F

SpacecraftZ_axis =/"_ _/--_--_;--]-]-- _ -perpendicularto \ \ ,_"(_,--"x_"=-_,;'"_,;---__///) -- hplane of fi La-Un_ser_Cnl[Icular

point

mSpacecraft coordinate system ../-Launch vehicle+Y coordinate systemDimensional axes

TrueNorthZSIC 1 -Y, Z

Theseaxes 5ot__/- Pperpendicularto pageatvehicle centerline

(sign indicatedis towardviewe____.

- e- Programmedroll angleLV,XS/C,-Y_Zn [/ \\ \ ], ,-, , II v _ I i L : ZLV, YS/C

(_TL_ Xp,x

xLv,YLV, ZLV -launchvehicleroll,itch,awbodyaxes,respectivelyXSIC,YS/C,ZSIC-spacecraftroll, yaw, pitch axes, respectivelyXp, Y., Z.- IGSplatform inertialcooVrdinVateseferencedto launch standGuidancecoordinates X, Y, Z - IGScomputercomputationalcoordinates

(b) Dimensionalaxesandguidancecoordinates.Figure3.O-l.Concluded.UNCLASSIFIED


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l Sta139.17AugmentedTargetDockingAdapter

197,.23 in. Sta 0.00 ATDAplane_ Sta-54.06 stations_, planem Sta-55.68TargetLaunch VehicleAdapter144.32 in. Sta-164.Sg

Sta-198.38Sta 502.O0

114_ 55in.

TargetLaunch .. -- --.Vehicle / Sta 960.0 TLVstations808.00in.

Sta1310.0

(a)Launch configuration,Figure 3.0-2. - TLV/ATDArelationship.

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NASA-S-65-11,278A Gemini spacecraft Z station 253.50 (spacecraft and_ +Y

Note: TDA rigidized),TDA station 0.030, _ _-X "_

1. The coordinate axes for the TDA Gemini spacecraft Z station 229.705_ _, -Zare the same a s that shown for (spacecraft andTDA rig[d_zed), TDAthe Gemini spacecraft in the station 23.765,

rigidized configuration.

2. Positive sense of axes and angles \are indicated by arrows.Ascent shroud / / '_ \ XZstationlO3.44 22"_Y (+Y) +Z m TDAZ station 13A4 u. Spacecraft- ATDAcontractor design and weights group coordinate system"_ (+X) +g in direction of crew's head(yaw axis) "1"1@..+Z forwardin direction crew is facing (roll axis)spacecraft-Z k_, -Z forwardin direction crew is facing (rol, axis)ATDA

m _TM. +X in direct ion ofcrew's right arm(pitch axis) --ltJ _ BY _-v) 2. Spacecraft- ATDA contractor guidance and control mechanicsand aero- Vdynamicsgroups coordinate system_.._@-Zup in direction of crew's head(yaw axis)ATDA quadrant designations CltC_ +X forward in direction crewis facing (rol l axis)(looking toward docking cone) (h_'_'_+Y indirection ofcrew s r ight arm(pitch axis)

+Y

-y(b)Dimensionalaxesandguidancecoordinates,ATDA. L_IFigure3.0-2. - Continued. ,_


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UNCLASSIFIEDNASA-S-66-6899 JUN

1 1 - positive Z axis for aerodynamic coefficienLs (C n)

__ 1--positive Y axis for weight sunlmaries

(_'1 - positive Y axis for autopilot and guidancei - negative Z axis for dynamic analysisPositive yaw for autopilot, guidance, and dynamic analysis

2 - positive Y axis for aerodynamic coefficients (Cy)_-'_---_,.- 2 2 - positive X axis for weight summaries/-_ _J I " 2 - positive X axis for autopiloL and guidance

l _-_-J/ 2 - positive axisfordynamicanalysis/ _'_..._ _ Positive piLch for autopilot, guiclaace, and dynamic

3

3 - positive X axis for aerodynamic coefficients (Ca)

3 - positive Z axis for weight summaries3 - negative Z axis for autopilot and guidance3 - negative X axis for dynamic analysis(_ Positive roll for autopilot, guidance, and dynamicanalysis

Vehicle shown in fl ight attitude(c) Dimensional axes and guidances coordinates, TLV.

Figure 3.0-2. - Concluded.

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UNCLASSIFIED 3-73.i GEMINI SPACECRA_

The structure and major systems of Spacecraft 9 (fig. 3.1-1) wereof the same general configuration as the previous Gemini spacecraft.Reference 2 provides a detailed description Of the basic spacecraft(Spacecraft 2) and references 3 through 9 describe the modifications in-corporated into the subsequent spacecraft. Except for the window coversand the extravehicular equipment_ Spacecraft 9 closely resembled Space-craft 8 (ref. 9), and only the significant differences (table 3.1-1) be-tween those two spacecraft are included in this report. A detaileddescription of Spacecraft 9 is contained in reference 10.

3.1.1 Spacecraft Structure

The primary load-bearing structure of Spacecraft 9 was essentiallythe same as that of Spacecraft 8. However_ tlhe few major changes aredescribed in the following paragraphs.

An externally mounted transparent cover for each hatch window wasinstalled to protect the windows from the film encountered during thepowered phase of flight. The covers were outer spacecraft windowsremoved from spacecraft flown on previous Gemini missions. In addition_each cover incorporated two hook-type hinges inserted in the hinge pinsmounted on the hatch, two torsion springs for jettisoning, and amachined tab for attachment of the latch-release mechanism in the hatch.A molded gasket seal between the cover frame and outer window framewas attached to the cover frame to afford a positive parting plane atcover jettison. The covers were jettisoned manually by rotating alatch-release knob mounted inside the spacecraft on each hatch afterthe spacecraft was inserted into orbit.

The Astronaut Maneuvering Unit (AMU) was mounted in the adaptersection in place of the Extravehicular Support Package (ESP) installedon Spacecraft 8. Also, a spring-clip device was added to the right-hand handhold assembly in the adapter AMUinstal!ation to restrain the25-foot umbilical to the handhold for donning the AMU. (For additionalchanges required to support the extravehicular activities_ see para-graph 3.!.2.12. )

3.1.2 _jor Systems3.1.2. i Communications System.- The Communications System was

basically the same as the one used on Spacecraft 8, including the voicecontrol center modification to permit recording of the pilot's voice

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3-8 UNCLASSIFIEDwhile communicating with the command pilot during EVA. This modifica-tion also permitted the recording of UHF communications from the ground.

3.1.2.2 Instrumentation and Recordins System.- Wiring changeswere incorporated to permit recording of AMUtelemetry data while theAMUwas in the stowed configuration. The changes provided the cap-ability to extend the AMUtelemetry antennas (by initiating the EVABARS EXTEND switch) and to record the telemetry data on track B of thetape recorder. There was no playback capability; therefore_ the datacould be reduced only after recovery of the spacecraft.

3.1.2.3 Environmental Control System.- The Environmental ControlSystem (ECS) was similar to the one used on Spacecraft 8.

3.1.2.4 Guidance and Control System.- The Guidance and ControlSystem_ including the Auxiliary Tape Memory Unitj was basically thesame as the Spacecraft 8 system except for the following changes.

During previous missions_ the horizon sensor system has been sus-ceptible to certain combinations of atmospheric and earth-climate con-ditions. These conditions have caused reduced accuracy of the pitchand roll output signals. On Spacecraft 9_ the secondary horizon sensorsystem was modified to include a narrower band-pass optical system forflight evaluation. This modification replaced the 8-micron filter andcollimator with a narrow band (13 to 22 microns to roll off ofgermanium) optical coating. This spectral band-pass selection reducedthe erroneous inputs by rejecting the ozone absorption band and thewater-absorption continuum window.

The OAMS CNTL POWER switch was changed to a four-pole single-throw lever-lock switch to provide the crew with the capability toremove power from all Orbital Attitude and Maneuver System (0AMS)thrusters by actuating one switch.

To preclude the firing of an 0AMS thruster by a shorted internalconnection_ all exposed connections in the orbital attitude and maneuverelectronics (OAME) package were insulated with a light coat of varnishor epoxy.

3.1.2.5 Time Reference System.- The Time Reference System con-figuration was the same as the one used on Spacecraft 8.

3.1.2.6 Electrical System.- The Electrical System included afuel-cell power system that was the same as the Spacecraft 8 system.

3.1.2.7 Propulsion System.- The Propulsion System (figs. 3.1-2and 3.1-3) was the same as the system flown on Spacecraft 8.

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UNCLASSIFIED 3-93.1.2.8 Pyrotechnic System.- Except for deletion of the pyrotech-

nic devices associated with the Gemini VIII experiments, the PyrotechnicSystem was similar to the one used on Spacecraft 8.

3.1.2.9 Crew-station furnishings and equipment.- The followingchanges were incorporated into crew-station furnishings and equipment.

3.1.2.9.! Controls and displays: In addition to the followingchanges_ the crew-station controls and displays also included minorchanges in the nomenclature of indicators and switch positions (seefig. 3.1.4).

(a) Both attitude indicators were changed to include the improvedquantitative markings used on the command pilot's attitude indicator onSpacecraft 8.

(b) Each of the six ammeters on the fuel-cell monitor and controlpanel were used to monitor the fuel-cell stack currents. (On Space-craft 8_ the two center ammeters monitored th_ two main-bus currents.)

(c) The MMUDEPLOY-OFF-TM ON switch replaced the BACK-PACK DEPLOY-SAFE switch that was installed on Spacecraft 8.

(d) The elapsed-time digital clock display light was dimmedmechanically (using a hood assembly) instead ,of electrically (using apotentiometer).

(e) The MMU hydrogen-peroxide warning indicator was added to theannunciator panel on the center panel.

(f) Displays and controls were installed as required for the ex-periments (see section 8.0).

(g) Eight switches located on the center and lower instrumentpanels and on the right circuit-breaker panel were replaced by switcheswhich had increased pushbutton travel and actuator plate spring preload.The change was the result of one of this type switch having been pres-sure sensitive on Spacecraft 6 and thereby not actuating properly.

3.1.2.9.2 Miscellaneous equipment changes: The following changeswere made in the spacecraft cabin.

(a) A single quick-release pin capable of simu/taneously stowingthe ejection control handle and safetying the ejection control mech-anism replaced the safety pin and quick-release stowage pin used onprevious spacecraft.

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3- o UNCLASSIFIED(b) The spacecraft hatch-holding device was modified to permit

rigging the hatches with a maximum closing force of 40 pounds. Also_a loop was added to the end of the fabric strap on the pilot's hatch-closing device to provide a means for the comlr_nd pilot to assist inclosing the right-hand hatch.

3.1.2.9.3 Stowage facilities: The stowage containers are shownin figure 3.1-5. Table 3.1-II lists the major items of equipment stowedin the containers at launch.

3.1.2.3_0 Landing System.- No significant changes were made to theLanding System.

3.1.2.11 Postlandin_ and Recovery System.- No significant changeswere made to the Postlanding and Recovery System.

3.1.2.!2 Extravehicular equipment.- The following modificationswere incorporated in the spacecraft and space suit to support the ex-travehicular activities (EVA). In addition_ the Extravehicular LifeSupport System (ELSS) and the AMUwere provided to equip the pilot forthe EVA.

3.1.2.12.1 Structural modifications: The structural modifications(handrai!_ Velcro patches) installed on Spacecraft 8 were included onSpacecraft 9. The adapter modifications to provide handholds_ footsupports_ and floodlighting were also on Spacecraft 9. In addition_two aluminum stirrups were installed on %he footbar to provide footrestraint during AMU donning activities. The modifications which weremade to the adapter-equipment-section thermal curtain to accommodatethe ESP on Spacecraft 8 were the same as those required on Spacecraft 9for the AMU (see fig. 3.1-6).

3.1.2.12.2 Space suits: The space-suit configuration for the com-mand pilot was basically the same as that used on the Gemini VIIImission - a G4C suit with a light coverlayer. The helmet pressurevisor for both crewmen was fabricated from a po!ycarbonate materialwhich is more resiliant than p!exiglass.

The space suit for the pilot was also a G4C suit but included anextravehicular cover!ayer and a modified overvisor. The EVA coverlayerwas modified to provide protection to the legs from the high-temperature,high-velocity plume impingement of the lower forward-firing and thedownward-firing thrusters of the AMU.

The visor modifications included a polycarbonate pressure visorand a single-lens sun visor in lieu of the multi-lens unit previouslyprovided. The use of the single-lens sun visor was possible because

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UNCLASSIFIED 3- 1the polycarbonate pressure visor provided the impact protection requiredin the sun visor. A low-emittance coating was applied to the exteriorsurface of the pressure visor to prevent interior surface cooling duringnighttime EVA.

3.1.2.12.3 Extravehicular Life Support System: The ELSS was asemi-open-loop system utilizing externally s_lied oxygen for ventila-tion and for removal of carbon dioxide. This system, contained in achestpack_ was the same as the ELSS flown on _e Gemini VIII mission_but with the following modifications:

(a) The umbilical configuration was modified such that, when theumbilical was attached to the chestpack oxygen fitting and the electri-cal connection_ the umbilical assembly extended forward of the pilotinstead of aft.

(b) Bypass flow was rerouted downstream of the ejector throat bya tube from the existing bypass valve.

(c) The chestpack wiring was altered to permit paralleling of theELSS power switching relay contacts.

(d) A light was added to the chestpack panel to indicate the useof either spacecraft or ELSS power. On the Spacecraft 8 ELSS, the RCSAMUwarning light illuminated when the power source changed from thespacecraft power supply to the ELSS battery. The Gemini IX-A configu-ration permitted the use of the RCS light for AMU status reporting andthe additional light (S/C POWER) illuminated _enspacecraft power wasutilized and extinguished when a switchover to ELSS battery power oc-curred.

3.1.2.12.4 Astronaut Maneuvering Unit: The AMUwas a highly com-pact unit consisting of a basic structure and six major systems. Thesesystems were: propulsion, flight control, oxygen supply_ power supply_malfunction detection, and communications.

The structure consisted of a backpack shell, two folding sidearmcontrollers_ and folding nozzle extensions, q_e size of the backpackwas determined prirm_rily by the size of the hydrogen peroxide_ oxygen_and nitrogen tanks. The thrusters were located in the corners of thestructure to provide controlling forces and moments about the center ofgravity of the entire AMU. The remainder of the components were locatedin the available space inside the backpack. _e total volume and shapewere further constrained by the stowage location in the equipment ofthe adapter section. A thermal curtain covered the stowage cavity toprovide passive temperature control for the A_. It was jettisonedprior to the start of AMUdonning activities. As a part of the donning

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3- _2 UNCLASSIFIEDactivities_ the pilot unfolded the nozzle extensions and sidearm con-troller heads. This permitted the control handles to be in am ac-cessible position.

The evaluation of the AMUwas an integral part of an experiment;therefore_ for a detailed description of the AMU_ see section 8. i_EXPERIMENT D-12_ ASTRONAUTMAIVEUVERING UNIT.

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UNCLASSIFIED 3- 3TABLE 3.!-1.- SPACECRAg-T 9 MOD]3_ICATIONS

System Significant differences between Spacecraft 9and Spacecraft 8 configurationsStructure (a) A transparent cover for each hatch windowwas installed.

(b) EVA provisions were modified.Communications No significant difference.Instrumentation and (a) Additional telemetry of the 0AMS wasRecording installed.

(b) Wiring changes were incorporated to permitrecording AMUtelemetry data while the A_was stowed.

(c) Additional telemetry parameters were in-stalled to provide data for evaluation ofthe ATMU.

Environmental A modification was incorporated to eliminateControl air from the drinking water system.

Guidance and The secondary horizon sensor system was modi-Control fled to include a narrower band-pass opticalsystem for flight evaluation.

Time Reference No significant difference.Electrical No significant difference.Propulsion (a) A switch and associated circuitry were

added to permit the crew to remove powerfrom all 0AMB thrusters by actuating oneswitch.

(b) All exposed connections in the 0A_ME pack-age were insulated.Pyrotechnics No significant difference.

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3- 4 UNCLASSIFIEDTABLE 3.1-1.- SPACECRAFT 9 MODIFICATIONS - Continued

System Significant differences between Spacecraft 9and Spacecraft 8 configurationsCrew-station (a) Both attitude indicators had improvedfurnishings and quantitative markings.equipment

(b) Each of the six ammeters on the fuel-cellcontrol panel were used to monitor fuel-cell stack currents.

(c) An MMU switch replaced the BACK-PACK switch,

(d) An MMU H202 indicator was added to thecenter panel.(e) A mechanical dimmer was installed on the

elapsed-time digital-clock-display light.(f) Displays and controls were added as re-

quired to support the experiments.(g) A single quick-release pin capable of

simultaneously stowing the ejection controlhandle and safetying the mechanism was used.

(h) The hatch-closing device and fabric strapwere modified to allow the command pilotto assist in closing the hatch.

(i) Both helmet pressure visors were made ofa polycarbonate material.

Landing No significant change.Postlanding and No significant change.RecoveryEVA equipment (a) Foot restraints were mounted on the

adapter foot support.(b) The pilot's sun visor was a single-lens

type.

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UNCLASSIFIEDTABLE 3.i-I.- SPACECRAF_ 9 MODIFICATIONS - Concluded

Significant differences between Spacecraft 9System and Spacecraft 8 configurations

EVA equipment - (c) The pilot's EVA cover!ayer was modifiedconcluded to provide protection from AMU thruster

firing.(d) The AMU replaced the ESP.(e) The ELSS bypass flow was rerouted down-

stream of the ejector throat.(f) The ELSS wiring was altered to permit

paralleling of the power switchingcontacts.(g) The ELSS RCS light was used for AMU

status reporting and a new S/C POWERlight indicated which power source wasin use.

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3-16 UNCLASSIFIEDTABLE 3.i-I!.- CREW-STATION STOWAGE LIST

Stowage area Item Quantity(Seefig.Centerline stowage 70-rmm camera I

container 16-mm camera 270-mm camera, super-wide angle, iwith film magazine

18-mm lens, 16-rmm camera i75-_n lens, 16-_i camera i5-mm lens, 16-rm_ camera iLens, f/2.8 i16-mm film magazine i070-_ filmmagazine 3Ring viewfinder iSighting device iMirror mounting bracket i

Left sidewall Personal hygiene towel icontainers Waste container i

Urine receiver iPenlight iDefecation device iVoice tape cartridge 5Velcro pile, 2 by 6 in. iVelcro hook, 2 by 6 in. iPlastic zipper bag 6Urine hose assembly iBandolier iUrine sample bag 6Adjustable wrench, 6 in. IPilot's preference kit i

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... UNCLASSIFIED 3-17TABLE 3.1-11.- CREW-STATION STOWAGE LIST - Continued

p

Stowage area(See fig. 3.1-4) Item Quantity

l_ft aft stowage Components for EVA consisting of:containerEVA remote control cable, i16-mm cameraELSS umbilical assembly iJumper cable iDual connector 2ELSS restraint assembly 2Pressure thermal gloves i pr.EVA rearview mirror iEVA wrist mirror and band iThermal cover_ 16-_mm camera !EVA remote control cable iEVA hand pad 2Movie camera adapter iELSS hose_ short_ with iinterconnectorELSS hose_ long_ with iinterconnectorExtension cable assembly iHose assembly_ red, 9 in. iHose assembly_ b_ue_ 9 in. iPouch_ harness_ electrical i

cable, "Y" connectorHose nozzle interconnector i

Left pedestal Lightweight headset with oral itemperature probe

Velcro, 8 by i in. 4

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3-18 UNCLASSIFIEDTABLE 3.1-II.- CREW-STATION STOWAGE LIST - Continued


Left footwell Personal hygiene t_el ITissue dispenser iAuxiliary window shade iReflective window shade i

Right sidewall Inflight medical kit icontainers Personal hygiene towel i

Waste container iPenlight iDefecation device IVoice tape cartridges $Velcro pile_ 2 by 6 in. IVelcro hook_ 2 by 6 in. iPlastic zipper bag 6Oral hygiene kit iSurgical scissor iDebris cutter iUrine sample bag 6Pilot's preference kit i

Right aft stowage Mirror mounting bracket icontainer 16-mm camera bracket i

18-mml lens_ 16-mm camera i70-mm camera i16-mm film magazine I0Spotmeter and exposure i

dial70-mmfilmmagazine 4

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UNCLASSIFIED 3- 9TABLE 3.1-11.- CREW-STATION STOWAGE LIST - Continued

St_age area(See fig. 3.1-4) Item Quantity

Right aft stowage Postlanding kit assembly icontainer - Manual inflator_ blood pressure iconcludedWaste container 2Defecation device 4Circuit breaker module 2Urine sample bag 12Zodiacal camera iMounting bracket, 70--rmlcamera i

Right pedestal Light_eigh% headset with ioral temperature probe

Velcro, $ by i in. 4Right footwell Orbital-path display assembly i

Celestial display - Mercator iPersonal hygiene towel iTissue dispenser iAuxiliary window shade iReflective window shade i

Plotboard pouch Flight data book 2Flight booklet iFlight data cards 2Splash curtain clip 6Transparent reticle i

Orbital utility Helmet stowage bag 2pouch

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3-2o UNCLASSIFIEDTABLE 3.1-II.- CREW-STATION STOWAGE LIST - Concluded


Right and left Clamps for urine collection 2circuit breaker devicefairings Latex roll-on cuff 4

(urine system)Tape, 3/4 in. i0 ftUrine receiver removable cuff 2Tape_ 1/2 in. by i0 ft 2Glareshield i

Center stowage EISS chestpack irackHatch torque Sextant ibox Lens_ 50-_, f/0.95 I

Objective filter_ 50-_u lens iB,Water rmanagement Roll-on cuff receiver i

console (urine system)

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,/ I

NASA-S-66-6898 JUN )ment sectionElectronic module0AMSECS coolant moduleECS primary 02 module/ RSS/fue l cell moduleWater tank AAMUATMU :abin section

'ade section Instrumentation SystemRetrograde rocket system Communication SystemOAMS Environmental Control System (_C Rendezvous and docking light Guidance and Control SystemWater tank B Electrical Power System /-.

p I Time Reference System

Controls and displays> , ELSS _CS Section _')_1_ , -Rendezvous and recovery section (f)/ -rl " Parachute Sanding system _1I _ Rendezvous radarIll \ IP_ /" Docking baro ,-Adapterassembly

Reentry assembly Nose fairin

Figure 3.1-1. - Spacecraft arrangement and nomenclature, _F


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UNCLASSIFIEDNASA-S-66-6884UN

OAMShrustersQ Pitchpulator (_) (_ Pitch down

(_ (_) YawrightE-package 0 (_) Yawleft

A-package (_ (_ RollclockwiseB-package (_ (_ Rollcounterclockwise

Oxidizershutoff valve D-package (_ (_) Translateforward(_ (_ TranslateaftOxidizertan (_) Translateright

(_ TranslateleftC-package (_ Translateup

Fuel ,"" (_) Translatedown)ackage

cutter / sealers

12req'd)

OAMSreserve /fuel tank I J

Oxidizer \' /'

'/ /Equipmentection

Retrogradesection Cabinsection

Figure3. 1-2.- Orbital AttitudeandManeuverSystem.

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UNCLASSIFIED >__

Figure 3.1-3. -Reentry Control System.

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3-24 UNCLASSIFIED


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UNCLASSIFIEDNASA-S-66-6890 JUN

ExtravehicularifeSupportSystemstowage- _Aft stowagebox(left)

.BiomedicalrecorderRightstowagebox l no. 2Blood pressurebulbstowagearea-Right sidewall stowage _ j/

Medical kit _,._._11i

Rightstowage pouch- 11/Utility stowage pouch- --_'-_ - _

k'\ ,,s>/, x ,x X" ,

i "

_ pilot ejectionseat removed for clarityht side dry stowage bags

pedestal pouchPlott ing board stowage area

(b) View looking into pilot_ side.

Figure 3.1-5.- Concluded.

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NASA-S-66-6985 JUN L no.3 on-off-gndswitch __/ $ /_ _o.= __t ou_ , mea__rl Squib batt -- ISquib batt no. 1 I'l'

off-on-gnd _ mno. i switch _,ommo_Ground controlpower bus

Squib batt Squib batt no. 2off-on-gnd _'no. 2 switch v, __

Figure 3.7-7 . - ATDA power and power distribution.


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NASA_S-66-6927 JUN

C Red CZ Z('_ Green- ('__> _rj_ ARMED"1"1 -rlI"11 I-r

Not operational onATDA _mber

GOIFigure 3.7-8. - Status display panel. ,_


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3-56 UNCLASSIFIED


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UNCLASSIFIED 4-14.0 MISSION DESCRIPTION

4.1 ACTUAL MISSION

The Gemini IX-A mission was initiated with the lift-off of theTarget Launch Vehicle/Augmented Target Docking Adapter (TLV/ATDA) onJune i_ 1966. The TLV sustainer engine operated for a longer durationthan on any previous Atlas flight_ and the ATDA was inserted into anear-circular orbit with an apogee of 161._ nautical miles and a peri-gee of 158.5 nautical miles_ referenced to the Fischer ellipsoid earthmodel of 1960. Telemetry data indicated that the protective shroud hadnot separated from the ATDA.

Problems in the T-3 minute launch-azimuth update to the spacecraftInertial Guidance System prevented the launch of the Gemini space ve-hicle on June i, 1966. The Gemini Space Vehicle was launched onJune 3, 1966. Although the T-3 update was again not received by thespacecraft_ a backup procedure_ developed during the two-day launchpostponement_ prevented a hold in the countdown.

At 4 hours 15 minutes ground elapsed time (g.e.t.), the crew re-ported that the M= 3 rendezvous was complete and that they were stationkeeping with the ATDA at a range of 60 feet. The crew also reportedthat the shroud was still attached to the ATDA_ and they were able tomaneuver close enough to the ATDA to describe the shroud in detail.After two attempts to release the shroud by ground commands were un-successful, the alternate flight plan was placed in effect. (See fig-_re 4.1-1.) The alternate flight plan had been developed immediatelyafter the first telemetry data indicated that the shroud might not havejettisoned and docking would not be possible. This plan was formalizedprior to lift-off of the Gemini Space Vehicle. Because the shroud wasstill attached_ docking could not be accomplished and the spacecraftmoved away from the ATDA at 5 hours i minute g.e.t, to get into posi-tion for the equi-period rendezvous. The first equi-period rendezvousmaneuver was initiated at 5:45:20 g.e.t._ and the rendezvous was suc-cessfully completed at 6 hours 36 minutes when the crew reported sta-tion keeping with the ATDA at a range of 60 feet. At 7:14:58 g.e.t.,the spacecraft separated from the ATDA to get into position for thethird rendezvous (rendezvous from above). This sequence of events wasnecessary to complete the three rendezvous operations and avoid stationkeeping during a night period. The rendezvous from above and ahead ofthe ATDA was to simulate conditions which would result if the ApolloCommand Module were required to rendezvous from above with a disabledLunar Module.

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UNCLASSIFIEDAfter eating and sleeping (the micrometeorite collector door was

opened during the sleep period), the crew initiated the third rendez-vous at 18:23:19 g.e.t., and the rendezvous was completed at 21 hours42 minutes g.e.t. Additional attempts to release the ATDA shroud byground command were not successful. The crew inspected the ATDA fromclose range and determined that an attempt to remove the shroud by anextravehicular pilot would not be practical.

Also_ the crew reported that they were fatigued and requestedthat extravehicular activities (EVA) be postponed until the next day.Ground control concurred with this request, and several experimentswere scheduled to be conducted in place of the EVA on the second dayof the flight. A decision was made to not attempt further operationswith the ATDA_ and at 22 hours 99 minutes g.e.t, the spacecraft movedaway from the ATDA.

After a three-hour rest period_ the crew conducted several experi-ment sequences during revolutions 17 through 21. The micrometeoritecollector door was opened at the start of the next sleep period andclosed at the end of the sleep period.

Preparations for EVA were started at 45 hours 30 minutes g.e.t, onrevolution 29 and were completed approximately 30 minutes ahead of sched-ule. The cabin was depressurized incrementally to zero, and the pilotopened the hatch at 49 hours 23 minutes. The extravehicular activitieswere proceeding according to plan until the pilot reached the adapterand started preparations for donning the Astronaut Maneuvering Unit (AMU).The pilot experienced difficulty keeping his body properly positioned inthe work area and_ because of this_ was working much harder than antic-ipated. After the pilot had been outside the spacecraft for one hourand five minutes, he reported that moisture had started to fog his pres-sure visor. When efforts to clear the fogging visor were not successful,the pilot was unable to continue with the AMU evaluation_ and furtherextravehicular activities were cancelled. After two hours and five min-utes of EVA_ the pilot was hack in the spacecraft.

After a sleep period_ the crew powered up the spacecraft and pre-pared for retrofire. Retrofire was initiated at 71:46:44 g.e.t, duringrevolution 45_ and the reentry was nominal. The spacecraft landed at72:20:50 g.e.t, within one mile of the target landing point and in vis-ual contact of the prime recovery ship_ U.S.S. Wasp. Pararescue menattached and inflated the flotation collar four minutes after landing,and the crew and the spacecraft were hoisted onboard the aircraft car-rier 53 minutes after landing.

The ATDA remained in orbit with an estimated lifetime of _3 days.The ATDA was monitored by remote sites until ATDA revolution 63 when

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UNCLASSIFIED 4-3all sites were released except the Rose Knot Victor tracking ship. TheRose Knot Victor monitored the ATDA from ATe& revolution 63 until theATDA was powered down to a minumumpower configuration on revolution 78.

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UNCLASSIFIED 4-74.2 SEQUENCE OF EVENTS

The times at which major events were planned and executed are pre-sented in tables 4.2-I and 4.2-II for the Gemini Space Vehicle space-craft. Table 4.2-III shows the sequence of events for the Target LaunchVehicle/Augmented Target Docking Adapter.

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4-8 UNCLASSIFIEDT/kBLE 4.2-1.- SEQEENCE OF EVENTS FOR GEMINI SPACE VEHICLE LAUNCH PHASE

Event Time from !i_t-off_ sec Difference_Planned Actual sec

Stage I engine ignition signal (87FSI) -3.40 -3.14 +0.26Stage I MDTCPS makes_ subassembly i -2.30 -2.32 -0.02Stage I MDTCPS makes, subassembly 2 -2.30 -2.30 0.00Shutdown lockout (backup) -0.i0 -0.09 +0.01Lift-off (pad disconnect separation) i3:39:33.335 G.m.t.Roll program start (launch azimuth = 87.4 deg) 18.48 18.42 -0.06Roll program end 20.48 20.42 -0.06PStch program rate no. i start 23.04 22.97 -0.07Pitch program rate no. i end_ rate no. 2 start 88.32 88.06 -0.26IGS update sent 105.00 InhibitedControl system gain c

Documents

Gemini Program Mission Report Gemini Ix-A