AEROSPACE 

LIBRARY 

Document No. 

Copy No 

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RELEASE 1 JULY 2015 TOR-469(5107)-10)-2 

19 October 1964 

3rd SSD/A Coordination Copy 

UNCLASSIFIED 

PERFORMANCE AND DESIGN REQUIREMENTS 

FOR THE 

MANNED ORBITING LABORATORY (MOL) SYSTEM 

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COMMANDER SPACE SYSTEMS DIVISION V.711/4 AIR FORCE SYSTEMS COMMAND \ 

LOS ANGELES AIR FORCE STATION 

Los Angeles, California 

AIR FORCE / AEROSPACE 

EYES ONLY 

SENSITIVE MATERft___- EROSPACE CORPORATION 

UNCLASSIFIED 

1111111111111111 
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UNCLASSIFIED 

TOR-469(5107-10)-2 

Specification No: (3rd Coordination Copy) 

Dated: 19 October 1964 

rcvs--- 003i 

PERFORMANCE AND DESIGN REQUIREMENTS 

FOR THE 

MANNED ORBITING LABORATORY (MOL) SYSTEM, 

GENERAL SPECIFICATIONS FOR 

Aid MU/ AEROSPACE 

EYES ONLY 

SENSITIVE MATEP1At 

Approved by: Approved by: 

(Preparing Activity (System Program Director) 

Date: Date: 

PRELIMINAR DOWNGRADED AT 3 YEAR INTERVALS; 

DECLASSIFIED AFTER 12 YEARS 

DOD DIR 5200.10 

UNCLASSIFIED 

This document contains information effecting the notional defense of the United States within the meaning of the Espionage Laws, Title 

18, U.S.C., Section 793 and 794, the tronsmission or revelotion of which in any manner to an unauthorized person is prohibited by law. 
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MOL SYSTEM PERFORMANCE/DESIGN REQUIREMENTS 

GENERAL SPECIFICATION 

INDEX 

Section Description ' Page 

1. 0 SCOPE 1 

1. 1 Descriptive Title .1 

1. 2 Purpose 1 

2. 0 APPLICABLE DOCUMENTS 2 

3. 0 REQUIREMENTS 3 

3. 1 Performance 3 

3.1.1 Performance Characteristics 5 

3.1. 1. 1 System Characteristics 5 

3.1.1.1 1 Pre-Launch Preparation 5 

3. 1. 1. 1. 2 Launch 5 

3. 1. 1. 1 . 3 Ascent 6 

3.1. 1.1. 4 On-Orbit 8 

3.1. h 1. 5 Re-entry 9 

3. 1.1. 1 . 6 Recovery 10 

3, 1. 1. 1. 7 Rendezvous and Docking 11 

3.1. 1. 1. 8 Evaluation of Performance 11 

3. 1. 1. I . 9 Operating Locations 11 

3.1. 1. 1.10 Mission Responsibilities 13 

3. 1. 1. 2 Logistics 15 

3.1. 1. 2. 1 Supply Support 15 

3.1. 1. 2. 2 Maintenance Support 15 

3. I .1. 2. 3 New Facilities NA 

3.1.1.3 Personnel and Training 16 

3, 1.1. 3. 1 Operational Personnel 16 

3.1.1. 3.2 Maintenance Personnel NA 

3. 1, 1. 3. 3 Organization Maintenance Personnel NA 

3. 1. 1. 3. 4 Total Personnel NA 
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Section Description Page 

3.1.1.3.5 

3.1.1.3.6 

3.1.1.3.7 

3.1.1.3.8 

Personnel Resources 

Special Features 

Training Time 

Training Facilities and Equipment 

NA 

NA 

NA 

NA 

3.1.2 System Definition 17 

3.1.2.1 System Engineering Documentation 17 

3.1.2. 1 . 1 System Level Functional Schematics 17 

3.1.2.1.2 Functional Flow Diagrams 17 

3.1.2.2 System Segment List 28 

3..1.2.3 Contract End Item List 28 

3.1.2.4 Interfaces 29 

3.1.3 Operability 29 

3.1.3.1 Effectiveness 29 

3.1.3.2 Maintainability 31 

3.1.3.3. Useful Life 31 

3.1.3.4 Environment - Natural and Induced 32 

3.1.3.5 Transportability and Handling 33. 

3. 1. 3.6. Human Performance 33 

3: 1: 3.7 Safety 34 

3.1.3.8 Dangerous Materials and Components 34 

3.1.3. 9 Noise and Vibration 35 

3.1.3-10 Life Support 35 

3.2' System Design and Construction Standards 36 

3.2. l' General Design and Construction Requirements 36 

3.2.1.1 Selection of Specifications and Standards 36 

3.2.1.2 Materials, Parts, and Processes 37 

3.2. I: 3 Standards and Commercial Parts 37 

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Section Description Page 

3.2.1.4. Moisture and Fungus Resistance 38 

3.2:1.5 Corrosion. of Metal Parts 38 

3.2.1.6 Interchangeability and Replace ability 39 

3.2.1.7 Workmanship 39 

3.2.1.8 Electromagnetic Interference 41 

3.2.1: 9 . Identification and Marking 41 

3.2.2 Design Disciplines 42 

3.2.2.1 Electrical 42 

3.2.2.2 Mechanical 42 

3.2.2.3 Hydraulic and Pneumatic 42 

3.2.2.4 Civil 42 

3.3 Performance Allocations 43 

3.3.1 Orbiting Laboratory. System Segment 43 

3.3.1.1 Allocated Performance 43 

3.3.1.2 Peculiar Performance and Design Requirements 46 

3.3.1. 2 1 Communications and Control 46 

3.3.1.2 2 Orbit Attitude Maneuvering'System 47 

3.3.1.2 3 Structural Design 48 

3:3:1:2.4 Crew Transfer 49 

3.3.1.2.5 Experiment Provisions 50 

3.3.1.2. 6 Orbital Operations 50 

3.3.1.2.7 Aerospace Ground Equipment (AGE) 51 

3.3.1.2.8 On-Orbit Monitoring and Checkout 52 

3.3.1.2.9 On-Orbit Maintenance 52 

3.3.1.2.10 Rendezvous and Docking 53 

3. 3. 1. 2.11 Laboratory Rendezvous Requirements 54 

3: 3:1: 2.12 Gemini B Rendezvous Requirements 55 

3.3.1.2.13 Transtage Rendezvous Requirements 55 
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Section Description Page 

3. 3. 2 Laboratory Vehicle System Segment 56 

3. 3. 2. 1 Allocated Performance and Design Requirements 56 

3. 3. 2. 2 Peculiar Performance and Design Requirements 58 

3. 3. 2. 2. 1 On-Orbit Maintenance 58 

3. 3. 2. 2. 2 On-Orbit Technical Data 58 

3. 3. 2: 2. 3 Docking Provisions 58 

3. 3. 2. 2. 4 Outgas sing and Venting 58 

3. 3.2.2. 5 Communications and Data Handling 59 

3. 3. 2. 2. 6 Environmental Control and Life Support 66 

3. 3. 2. 2. 7 Orbital Attitude Maneuvering System 73 

3. 3. 2. 2.. 8 Electrical Power, Supply 79 

3. 3.. 2. 2. 9 Structural Sub-system 83 

3. 3. 2. 2. 10 Crew Accommodations 85 

3. 3. 3 Gemini B System Segment 88 

3. 3. 3. 1 Allocated Performance and Design Requirements 88 

3. 3. 3. 2 Peculiar= Performance and Design Requirements 91 

3. 3. 3. 2.1 Spacecraft Requirements 91 

3: 3: 3:2. 2 Guidance and Control Requirements 92 

3. 3. 3. 2. 3 Instrumentation Requirements 92 

3. 3. 3. 2. 4 Environmental Control Requirements 93 

3. 3. 3. 2. 5 Propulsion Requirements 94 

3. 3. 3. 2.. 6 Electrical Power Requirements 95 

3. 3. 3. 2. 7 Time Reference Requirements 96 

3. 3. 3. 2. 8 Pyrotechnic Requirements 96 

3. 3. 3. 2. 9 Landing Requirements 96 

3. 3. 3. Z. 10 Post Landing and Survival Requirements 97 

3. 3. 3. 2.11 Backup Crew Transfer Requirements 97 
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Section Description Page 

3.3.3.2.12 Crew Equipment and Display Requirements 98 

3.3.3.2.13 Communications and Command Requirements 99 

3.3.3.2.14 Gemini B Peculiar Ground System 101 

3.3.3.2.15 Crew Safety Requirements 102 

3.3.3.2.16 Rendezvous 103 

3.3.4 Experiment System Segment 104 

3.3.4.1 Allocated Performance and Design Requirements 104 

3.3.4.2 Peculiar Performance and Design Requirements 106 

3.3.4.2.1 General 106 

3.3.4.2.2 Experiment Information System Data 106 

3.3.4.2.3 P-1 Acquiring and Tracking Pre-Assigned 

Earth Targets P-2 and P-3 108 

3.3.4.2.4 P -4 Electromagnetic Signal Detection 111 

3.3.4.2.5 P-5 In-Space Maintenance 113 

3.3.4.2.6 P-6 Extravehicular Activities 115 

3.3.4.2.7 P -7 117 

3.3.4.2.8 P-8 Autonomous Navigation and Geodesy 119 

3.3.4.2.9 P-10 Multiban Spectral Observations 122 

3.3.4.2.10 P-11 General Human Performance 125 

3.3.4.2.11 P -12 Biomedical and Physiological Evaluation 127 

3.3.4.2.12 P-13 Integrated Navy Experiments 130 

3.3.4.3 Experiments Peculiar Ground System 132 

3.3.5 ' Flight Crew and Crew Equipment Systems Segment 133 

3.3.5.1 Allocated Performance and Design Requirements 133 

3.3.5.2 Peculiar Performance and Design Requirements 134 

3.3.5.2.1 Flight Crew Complement 134 

3.3.5.2.2 Flight Crew Selection 136 

3.3.5.2.3 Flight Crew Training 136 

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Section Description Page 

3.3.5.2.4 Flight Crew Activity Programming 138 

3.3.5.2.5 Nutritional and . Metabolic Requirements 139 

3.3.5.2.6 Personal Hygiene 140 

3.3.5.2.7 Physiological Conditioning 140 

3.3.5.2.8 Medical Monitoring 141 

3.3.5.2.9 Pressure Suit and Associated Equipment 141 

3.3.5.2.10 Flight Crew Training Equipment 141 

3. 3. 6 Titan III System Segment 143 

3.3.6.1 Allocated Performance and Design Requirements 143 

3.3.6.2 Peculiar Performance and Design Requirements 146 

3.3.6.2.1 Malfunction Detection System (MDS) 136 

3.3.6.2.2 Transtage On-Orbit Characteristics 147 

3.3..6.2.3 ITL AGE 148 

3.3.7 Test Operations System Segment (TOSS) 149 

3.3.7.1 Performance Allocations 150 

3.3.7.2 Functional Requirements Allocations 151 

3.3.7.2.1 Launch Phase 151 

3.3.7.2.2 Ascent Phase 154 

a. 3.7.2.3 On-Orbit Phase 157 

3.3.7;2;4 ' Loiter and Re-entry Phase 161 

3.3;7;2;5 . Recovery Phase 163 

3.3.7.2.6 Rendezvous 164 

3.3;7;3 ' TOSS Design Requirements 166 

3.3;7.3;1 Mission Control Sub-Segment 166 

3.3.7.3.2 Test Support Sub-Segment 170 

3. 3. 7. 3. 3 Recovery Sub-Segment 177 

3.3.8 Facilities 178 

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Section Description Page 

4.0 PERFORMANCE/DESIGN VERIFICATION 

AND TEST 181 

4. 1 Ground Test Requirements 181 

4.1.1 Development Tests 181 

4.1.2 Qualification Tests 189 

4.1.3 Effectiveness (Reliability) Testing 192 

4.1.4 Acceptance and Flight Readiness Tests 193 

4.2 MOL System Flight Test Requirements 196 

4.2.1 Test Program Description 196 

4.2.2 Sub-Orbital Flight 196 

4.2.3 Orbital Flights 196 

4.2.4 Rendezvous Test Missions 198 

4.3 Engineering Changes 198 

5.0 PREPARATION FOR DELIVERY 199 

5.1 Packaging for Gemini B and Laboratory 199 

6.0 NOTES 200 

7.0 CONTRACTOR DATA AND REPORTS 200 

8.0 SPECIFICATION TREE 201 

10.0 APPENDICES 

10.1 Appendix A - Applicable Documents 

10.2 Appendix B CEI List 

10. 3 Appendix C - Interface Requirements 

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MOL. SYSTEM PERFORMANCE/DESIGN . REQUIREMENTS 

GENERAL SPECIFICATION 

1.0 Scope . 

This specification establishes the performance, design, development 

and test requirements for the Manned Orbiting Laboratory (MOL) System. 

All elements and contract end-items of the MOL System shall conform to 

the requirements delineated herein. 

1.1 Descriptive Title 

The descriptive title for the total system shall be the "Manned 

Orbiting Laboratory System" (or "MOL System"). 

1. 2 Purpose 

The primary objective of the MOL program is to provide an in-space 

testing capability which will qualitatively and quantitatively assess the 

military usefulness of man in space. 

In order to accomplish this objective it hasibeen necessary to 

define possible military tasks in space and to define a set of experiments 

which will qualitatively and quantitatively evaluate man's value in the 

accomplishment of these tasks. The mission of the MOL program is to 

supply the necessary means, - the plan, the system hardware, the 

operational flights, and the evaluation, - to determine what the role of 

man should be, through carrying out these experiments. Man's unique 

capabilities can then be integrated into military space systems of the 

future. 

This primary objective shall be accomplished as early as possible, 

with minimum cost, and with careful attention to safety. aspects. 

Minimizing cost and time for development and test, as well as enhancing 

safety and reliability, implies a minimum of innovations to be introduced 

or developed. Proven vehicle and ground hardware, procedures, and 

facilities, resulting from prior DOD and NASA programs, are to be 

employed as the rule. Exceptions must be completely justified. 

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A secondary objective is the accomplishnient of experiments and 

tasks less directly associated with potential military applications, - 

those which increase knowledge of the space environment, investigate 

longer range military problems for man in space, and improv. e 

operational capabilities in space. Such tasks shall not interfere with 

the primary objective, but may utilize payload allotments or time on 

orbit not otherwise required. 

2.0 Applicable Documents 

As listed in Appendix A, military specifications, standards, 

exhibits, manuals, regulations, publications, bulletins, pamphlets, and 

other documents are specified as appropriate to obtain first tier 

compliance for the MOL system. Only specifications affecting either 

the entire system or the whole of a system segment are included in this 

Specification and then are only applicable to the extent provided in the 

section in which they are called out. 

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3.0 Requirements 

The Manned Orbiting Laboratory (MOL) Program centers around 

an orbiting vehicle in which men will carry out military and scientific 

experimental programs for durations of thirty days. The orbiting 

system consists of a Laboratory, a modified Gemini spacecraft 

(Gemini B), and the transtage of Titan III. This will be launched by 

Titan III-C from Cape Kennedy. During the ascent to orbit the space 

crew will be in the Gemini B, transfer to the Laboratory for accomplishing the on-orbit tasks as programmed, and will return to earth in the 

Gemini B. The remaining portions of the orbiting system will be left 

in a. decaying orbit. 

The Manned Orbiting Laboratory System is specified in terms of 

eight system segments, as defined in Section 3.1.2.2. 

The basic MOL design will include the capability for in-space 

rendezvous. The rendezvous missions, to be conducted in the latter 

part of the program, shall use essentially the same integrally launched 

orbiting vehicle configuration with additional equipment to permit 

tail-to-tail docking of the two orbiting vehicles. The objectives of the 

rendezvous and docking mission shall be to provide for re-supply, a 

larger in-space testing capability, and to extend the duration up to 

60 days. 

3.1 Performance 

The MOL flights shall be conducted from the Titan III launch 

complex at Cape Kennedy. Upon achieving orbit, the flight crew who, 

during launch and insertion into orbit, are located in the Gemini B, 

will prepare to transfer to the laboratory vehicle by conducting a 

checkout of the essential laboratory subsystems from the Gemini B and 

by activation of those laboratory subsystems which must be in operation 

during the transfer. Upon entering the laboratory, the flight crew will 

proceed to activate the remaining laboratory subsystems and place the 

laboratory vehicle in a full-operating condition. The crew will be the 

primary source of on-orbit flight decisions. 
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Orbiting Vehicle operations involving orbital abort, attitude control, 

translational control, transtage engine manuevers, rendezvous, docking, 

separation of vehicle elements, retrofire, and re-entry shall be conducted 

with pilot control as the primary operational mode. All system designs 

and trade-offs shall reflect this primary mode of operation. 

Flight crew functions will include performance of prescribed 

experiments, observations, physiological and psychological testing, and 

the monitoring, controlling, and maintenance of vehicle and experiment 

subsystems. Status of subsystems in the Gemini B essential to safe 

return will be monitored. Data from experiments, as well as telemetry 

of orbiting vehicle condition and space crew physiological functions, will 

be transmitted from the orbiting vehicle to ground stations and/or 

recorded on board as appropriate for transfer to the Gemini B and return 

to earth. 

Communication with the on-orbit crew and mission control functions 

will be controlled from a mission control center. A network of tracking 

and data acquisition stations will provide world-wide communication 

coverage. Experiment data management and certain experiment 

functions will be accomplished by an on-board central general purpose 

digital computer. Over-all control of the various experiments will 

remain a crew function. Certain analyses shall be made during orbital 

flights, both on-board and on the ground; the remainder will be accomplished 

after recovery. 

For the rendezvous flights, the chaser vehicle will be launched 

15 to 30 days after the target vehicle. The chaser will be launched 

in an elliptical catch-up orbit and, at the appropriate time, will be 

injected into the orbit of the target vehicle by means of the transtage. 

Rendezvous will be effected by means of a Gemini radar. Docking will 

be manual control and visual reference. Interchange of one crew 

member between chaser and target will be accomplished and the one 

Gemini B returned to earth. The chaser vehicle and the Laboratory 

from the target will remain on orbit an additional full mission period. 

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Upon completion of the mission, the flight crew will perform 

final checks of the condition of the Gemini capsule and activate those 

systems required for crew transfer. They will then don their space 

suits, deactivate certain subsystems in the laboratory, and return to the 

capsule for separation and re-entry. Upon return of the crew to the 

capsule, checkout of subsystems associated with life support, .separation, 

control, and re-entry will again be made and verified by the ground 

network. 

Upon completion of all systems checkout and verification, separation 

will be effected and de-orbit and re-entry will be accomplished. Following re-entry into the atmosphere the Gemini spacecraft will deploy a 

parachute for descent to a water recovery site. A ship/plane recovery 

force will recover the crew, spacecraft, and experiment data in a 

primary recovery area in the Atlantic Ocean or in the event of an 

emergency a secondary recovery area in the Pacific Ocean. 

3. 1. 1 Performance Characteristics 

Performance characteristics of the MOL system are defined in 

terms of System Characteristics, Logistics, and Personnel and Training. 

3.1.1.1 System Characteristics 

The significant system characteristics are defined in terms of 

the various operational phases ranging from pre-launch through mission 

evaluation, the operating location at which these will be accomplished, 

and the responsibilities for the various portions of the mission. 

3. 1. 1. 1. 1 Pre-launch Preparation 

This phase covers the period from arrival of systems at 

Cape Kennedy to the "T-Hcount on the launch pad. Pre-launch preparation will follow normal Titan III ITL procedures, with assembly of the 

Orbiting Vehicle to the launch vehicle and checkout in the VIB and subsequent transport through the SMAB to the launch pad for final countdown. 

3. 1. 1. 1. 2 Launch 

This phase covers the period from initiation of It --It 

count on the launch pad through lift-off. The launch countdown shall be 

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initiated and conducted so as to provide the optimum opportunity for 

recovery in the event of a malfunction during ascent. 

3.1.1.1.2.1 Crew launch Occupancy 

The time to launch a MOL system after astronaut 

insertion in the Gemini B capsule shall be as short as possible, not 

exceeding 120 minutes, including scheduled automatic countdown sequence 

holds. 

3.1.1.1.2.2 Hold Time 

The system shall be capable of sustaining a three-hour 

unscheduled hold in addition to the maximum 120 minute countdown time 

after the crew enters the spacecraft. 

3.1.1.1.2.3 Crew Escape 

Prior to lift-off, escape from the spacecraft 'in the 

event of an emergency shall be by egress from the crew hatch or by means 

of the escape system. 

3.1.1.1.3 Ascent 

This phase covers the period from lift-off through final 

orbit insertion. 

5.1.1.1.3.1 Azimuth 

The system shall be capable of launching a mission 

from ETR on any azimuth from 90° to 108°. 

3.1.1.1.3.2 Trajectory Safety 

The ascent trajectory shall be such that in the event of 

mission abort at any time, the spacecraft will not exceed safe conditions 

for re-entry and recovery. 

3.1.1.1.3.3 Insertion Elements 

Initial orbit shall be approximately 80 n.'mi. perigee 

and 160 n. mile apogee, then circularized at 160 n.rni. Nominal orbit 

inclination shall be 32°. 

3.1.1.1.3.4 Communication 

The system shall provide communication between the 

crew in the spacecraft and the mission control center during all portions 

of powered ascent. 
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3. 1. 1. 1. 3. 5 Crew Escape 

A crew escape system shall be provided which will 

allow safe escape and recovery if any catastrophic malfunction occurs 

during the ascent phase. 
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3. 1. 1. 1. 4 On-Orbit 

This phase covers the period from final insertion into orbit 

until separation of Gemini B from the Laboratory prior to re-entry 

3. 1. 1. 1. 4. 1 Duration 

The nominal MOL System Orbiting Vehicle duration shall be 

30 days following the injection into a 160 n. mi. circular orbit. Duration of the 

rendezvous mission will range up to 60 days. 

3. I. 1. 1. 4. 2 Normal Vehicle Orientation 

The Vehicle shall be oriented such that the longitudinal 

axis lies in the orbital plane, perpendicular to the local vertical. 

3. 1. 1. 1. 4. 3 Orbital Decay 

The orbital altitude shall be no less than 140 n. mi. throughout the mission. 

3. 1. 1. 1. 4. 4 Abort 

The system shall be capable of retrieving the MOL crew 

from an on-orbit mission abort and of returning them to pre-selected water 

landing sites. The abort procedure shall be initiated and accomplished by 

the flight crew. The Gemini B shall be capable of sustaining the crew for 

14 hours on-orbit after separation from the Laboratory. 

3. 1. 1. 1. 4. 5 Checkout and Monitoring 

The Orbiting Vehicle System shall be capable of providing 

functional subsystems information to the ground and the flight crew for purpose 

of checkout of those parameters critical to crew safety, mission status, and 

system status. Crew safety parameters shall be available to the crew prior 

to the activation and occupancy of the Laboratory; conversely the Gemini B 

status shall be available to the crew during the on-orbit phase and prior to 

occupancy for mission termination. 

3. 1. 1. 1. 4. 6 Flight Crew Transfer 

Passage of the crew members between the Gemini B and 

the Laboratory shall normally be accomplished within a pressurized tunnel 

which provides protection from the space environment. Capability for extravehicular crew transfer, involving only the protection afforded by pressure 

suits will be used as a back-up mode for transfer operation. 

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3.1.1.1.4.7 Mission Experiment Operations 

The experiment equipment shall be operable by the crew 

members in conjunction with the Experiments Information System. 

3.1.1.1.4.8 Maneuvering 

The Orbiting Vehicle shall be capable of executing controlled 

maneuvers with six degrees for freedom. A capability for an on-orbit velocity 

increment of 50.0 feet per second is required, in a total of not less than ten 

thrusting periods. The velocity increment will be imparted by both of the transtage main propulsion engines. 

3.1.1.1.5 Re-entry 

Re-entry is defined as the period from separation of Gemini B 

from the laboratory through landing. 

3.1.1.1.5.1 Separation 

The Gemini B shall be capable of separation from the 

Laboratory Vehicle only by crew initiation. 

3.1.1.1.5.2 Alignment Reference 

Alignment of the spacecraft for retrofire shall normally 

be accomplished by use of a horizon sensor reference and gyro-compassing 

of the IMU as a primary mode. The secondary mode shall be through visual 

alignMent by the crew. 

3.1.1.1.5.3 Retrofire Orientation 

Re-entry and de-boost data shall be provided the Gemini B 

crew for proper retrograde attitude and timing of manually-initiated ignition. 

3.1.1.1.5.4 Return Maneuver Capability 

During re-entry the Gemini B shall have a minimum capability for maneuvering cross-range 40 nautical miles, and downrange 400 

nautical miles relative to the nominal touchdown point. 

3.1.1.1.5.5 Communications 

During descent, recovery aids, including a beacon, shall 

be provided in the Gemini B to facilitate tracking and impact prediction. 

voice communication link shall be provided. 
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3. 1. 1. 1. 6 Recovery 

Recovery is the period from landing through safe return of crew, 

data, and spacecraft to points designated by the Mission Director. 

3. 1. 1. 1. 6. 1 Flotation 

Following water impact, the Gemini B shall float in a commandastronaut hatch-up position. Provisions for additional flotation gear to be manually secured to the Gemini B by recovery force personnel shall be provided. 

3. 1. 1. 1. 6. 2 Recovery Support 

Recovery forces consisting of sea and air units equipped 

with proper gear to facilitate astronaut, capsule, and data recovery shall be 

provided. 

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3. 1. 1. 1. 7 Rendezvous and Docking 

3. 1. 1. 1. 7.1 General 

The objectives of the rendezvous and docking mission shall 

be the operation of a representative set of experiments for up to 60 days, and 

the extension of crew on-orbit duration up to 60 days. The MOL system shall 

have the capability of rendezvous and tail to tail do6king of two Orbiting 

Vehicles. The MOL configuration for rendezvous and docking shall be 

composed of two vehicles, namely a target and chase vehicles, that are 

minimum modifications of the basic integral launch configuration. Occupancy 

of both laboratories shall be possible after rendezvous. 

3. 1. 1. 1. 7.2 Launch Preparations 

Preparations for launch of a mission intended to rendezvous 

with a vehicle already in orbit shall be completed within 15 days after the 

target launch. 

3. 1. 1. 1. 7. 3 Maneuver s 

The chase vehicle will acquire the target by radar. 

Following acquisition, a series of fine maneuvers will be made to place the 

target and chaser vehicles in the appropriate relative position for commencement of docking maneuvers. Final docking maneuvers shall be by manual 

control using visual observations. 

3. 1..1. 1. 8 Evaluation of Performance 

Mission evaluation shall include: 

Evaluation of astronaut performance 

Evaluation of on-orbit equipment, both vehicle and 

experimental 

Evaluation of over-all mission operation. 

3.1.1.1.9 Operating Locations 

3. 1. 1. 1. 9.1 Segment Acceptance Tests 

Each system segment of the vehicle will be assembled and 

acceptance tested at the respective responsible contractor's facilities prior 

to shipment to either the CKAFS or to the Orbiting Vehicle contractor's 

facility as appropriate. Those system segments of the Orbiting Vehicle which 

are supplied to the Orbiting Vehicle contractor as GFE, will be assembled at 

the Contractor's facility in the on-orbit verification tests, the Orbiting Vehicle 

will be disassembled as required for transport and shipped to CKAFS. 
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3. 1. 1. 1. 9.2 Pre-Launch Integration, Checkout, and Launch 

Final assembly of the MOL system flight vehicle will be 

completed in the VIB, checked out, transported to the •launch pad, and 

launched at the Titan III ITL complex at CKAFS. 

3. 

mission evaluation during flight will be performed at the MCC. 

3. 1. 1. 1. 9. 3. 2 Tracking and Communication Sites 

Tracking and communication network stations are 

designated by the phase of the mission profile during which they operate. 

Subject to negotiations with the appropriate agency the stations tentatively 

chosen for each phase are as follows: 

3. 1. 1. 1. 9. 3. 2. 1 Ascent 

CKAFS 

Grand Bahama Island 

Grand Turk 

Bermuda 

Grand Canary Island 

Antigua 

Ascension 

Pretoria 

NRD Ships 

3.1. 1. 1. 9. 3. 2. 2 Circularization and Early Orbit 

Carnarvon 

Hawaii 

Vandenberg /Arguello 

CKAFS 

Antigua 

Okinawa 

Ascension 

Pretoria 

Grand Bahama 

Bermuda 

NRD Ship s 

1. 1. 1. 9. 3 Mission Operations 

3. 1. 1. 1. 9. 3. 1 Mission-Control Center 

The Mission Control Center shall be at CKAFS. Primary 
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3. 1. 1. 1. 9. 3. 2. 3 On-Orbit 

Okinawa 

Hawaii 

Vandenberg /Arguello 

CKAFS 

Antigua 

Carnarvon 

Voice Stations 

3.1.1.1.9.4 Recovery Forces 

Primary recovery forces shall consist of U. S. Air Force 

aircraft and Navy, MSTS or specially assigned ships and aircraft suitably 

deployed. 

3. 1. 1. 1. 9. 4. 1 Initial and Early Orbit 

During the first day there will be recovery provisions 

for each orbit. 

3. 1. 1. 1. 9. 4. 2 On-Orbit and Return 

After the first day there will be a limited number of 

recovery areas. The location and number of vehicles remain to be determined. 

3 1. 1. 1.10 Mission Responsibilities 

3. 1. 1. 1.10. 1 Over-all Responsibility 

Over-all responsibility for design, development, and 

operation of the MOL System is assigned to the Space Systems Division, AFSC. 

3. 1. 1. 1. 10. 2 Launch Operations 

Launch operations are the responsibility of the Space 

Systems Division, AFSC, supported by the DOD manager for Manned Space 

Flight Support and the National Range Division, AFSC. 

3. 1. 1. 1. 10. 3 On-Orbit Operations 

On-orbit operations of the orbiting vehicles and the crew 

shall be the responsibility of the Space Systems Division, AFSC. Operation 

of the worldwide tracki:•,g net and communications net are the responsibility 

of the DOD Manager for Manned Space Flight Support and the National Range 

Division. The Mission Control Center shall be operated by the Space Systems 

Division and supported by NRD. 

3. 1. 1. 1. 10. 4 Experiment Operations 

Experimental equipment, developmental simulators, 

procedures, and data analysis, shall be supplied by the Space Systems Division, 

AFSC, supported by the Navy and the Aerospace Medical Division and Research 

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and Technology Division of AFSC. The Aerospace Corporation is responsible 

for providing general systems engineering and technical direction for Space 

Systems Division Contractors, as well as for the coordination and integration 

task. Hardware integration of the experiments into the Laboratory System 

Segment shall be performed by the Laboratory Contractor under the direction 

of SSD/Aerospace. The on-board central data management system shall 

provide those computer and data processing functions to support the experiments 

and is the responsibility of the Space Systems Division/AFSC. 

3. 1. 1. 1. 10. 5 Recovery Operations 

Primary support in the area of recovery operations 

shall be provided by the DOD Manager for Manned Space Flight Support. 

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3. 1. 1. 2 Logistics 

• . 3.,1. 1. 2. 1 Supply Support 

3.1.1. 2.1.1 Spare parts support for the Laboratory Vehicle, Gemini B, 

Experiments, Crew Equipment, T-IIIC and attendant AGE shall be provided in 

accordance with AFSSD Exhibit 63-14. Spare parts requirements shall be based 

on a concept of minimum maintenance at launch site consisting primarily of component replacement. Spare parts support planning shall consider the requirement 

for prestoCking and control of "Critical to Launch" spares. Spares 

kits shall be developed as required to support the crew capability for "In 

Flight" or "On Orbit" maintenance. 

3.1.1. 2.1. 2 Spare parts for the VIB, ITL, MCC, Range Stations, Recovery 

Forces, and attendant facilities and AGE shall be provided as required from 

contracts under which such services and/or facilities maintenance are provided. 

3. 1. 1. 2. 2 Maintenance Support 

3.1.1. 2.2.1 Applicable documents for Maintenance Support are listed in 

Appendix A with the prefix letter MS. 

3.1.1. 2. 2. 2 The repair program shall be based on return of components to home plant and/or to associate, sub-contractors or vendors plants for 

repair and return. Prime Contractors shall not duplicate repair capabilities 

existing at associate, sub-contractors or vendors plants. Repaired components 

must meet the serviceability and reliability requirements established for 

acceptance of newly fabricated articles. 

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3.1.1. 2. 2. 3 Maintenance of the VIB, ITL, MCC, Range, Recovery 

Forces and attendant facilities and AGE shall be provided from contracts under 

which such services are provided. 

3.1.1. 3 Personnel and Training 

Personnel associated with the total MOL system fall into two basic 

categories: Space Crew and ground personnel. These are treated separately in 

this specification and throughout the program. 

The Space Crew, their flight equipment, and training requirements are 

described in Section 3. 3. 5. Ground personnel only are specified in the requirements of this section. 

3. 1. 1. 3. 1 Operational Personnel 

There are no Operational Personnel for MOL in the general military 

context except as included in the support functions. Support personnel associated 

with flight operations will be assigned and coordinated by the MOL Test Operations 

Office of SSD. Personnel required for the assembly checkout, maintenance, 

launch, and operations support shall be supplied by contractors concerned with 

the various system segments. 

3. 1. 1. 3. 1. 1 Personnel Specification 

The contractors shall specify to SSD the number, type, skill, 

and training requirements of personnel required for assembly, checkout, 

maintenance, launch, and operations support. 

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3. 1. 2 System Definition 

3. 1. 2. 1 System Engineering Documentation 

3. 1. 2. 1. 1 System Level Functional Schematics (Figure 3. 1. 2. 1. 1) 

3. 1. 2. 1. 2 Functional Flow Diagrams 

3. 1. 2. 1. 2. 1 MOL System Top Level Functional Flow Diagram ‘: 

(Figure 3. 1. 2. 1. 2. 1) 

3. 1. 2. 1. 2. 2 MOL System First Level Functional Flow Diagram 

"Perform MOL Evaluation" (Figure 3. 1. 2. 1. 2. 2) 

3. 1. 2. 1. 2. 3 MOL System First Level Functional Flow Diagram 

a. "Perform MOL Mission and Recovery Operations" 

(Figure 3. 1. 2. 1. 2. 3`a) 

b. "Perform MOL Rendezvous Mission and Recovery Opperations" (Figure 3. 1. 2. 1. 2. 3 b) 

3. 1. 2. 1. 2. 4 MOL System First Level Functional Flow Diagram 

"Perform MOL Launch Operations" (Figure 3. 1. 2. 1. 2. 4) 

3. 1. 2. 1. 2. 5 MOL System First Level Function Flow Diagram 

"Perform System Integration and Pre-Launch Operations" 

(Figure 3. 1. 2. 1. 2. 5) 

3. 1. 2. 1. 2. 6 MOL System First Level Functional Flow Diagram 

"Perform Acceptance of Vehicle System Segments" 

(Figure 3. 1. 2. 1. 2. 6) 

3. 1. 2: 1. 2. 7 MOL System First Level Functional. Flow Diagram 

"Perform Simulation System Development and.Accomplish 

Simulation Objectives" (Figure 3. 1. 2. 1. 2. 7) 

3. 1. 2. 1. 2. 8 MOL System First Level Functional Flow Diagram 

"Design, Develop and Test MOL Vehicle System Segments" 

(Figure 3. 1. 2. 1. 2. 8) 

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3. 1 . 2. 2 System Segment List 

The following eight system segments for MOL are identified. 

Necessary ground equipment, simulators, "soft-ware, " and other segment 

determined material, and activities are included under the appropriate segment. 

3. 1 . 2. 2. 1 Orbiting Vehicle System Segment 

This constitutes all segments and parts of segments which are 

in orbit. 

3. 1 . 2. 2. 2 Laboratory System Segment 

3.1.2.2.3 Gemini B System Segment 

3. 1 . 2. 2.4 Experiments System Segment 

This consists of a number of independent or inter-related 

experimental programs, each of which may be considered a sub-segment. 

Developmental simulators are included under each experiment. 

3.1.2.2.5 Flight Crew and Crew Equipment System Segment 

The complete mission simulator and certain other training 

simulators are included. 

3. 1 . 2. 2. 6 Titan III-C System Segment 

This segment includes the operation of the ITL. 

3. 1'. 2. 2. 7 Test Operations System Segment 

The following sub-segments are involved: 

Test Support System 

Mission Control System 

Recovery System 

3. 1 . 2. 2. 8 Facilities Segment 

This segment consists of new facilities and major modifications 

to be obtained from USAF MCP funds. 

3. 1 . 2. 3 Contract End Item List 

The list, given in Appendix B, calls out only the principal system 

CEI's. Reference will be made on the principal CEI's to other CEI lists 

covering the minor CEPs. 

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3. 1. 2. 4 Interfaces 

Interfaces between the various segments and their interfacing components 

are delineated in Appendix C. Interface Control Documents requirements shall be 

stated as needed in the outline format given. 

3. 1. 3 Operability 

3. 1. 3. 1 Effectiveness 

The goal of the MOL Program is the acquisition of experimental results; 

the reliability emphasis must, therefore, be in terms of mission accomplishment. 

In addition, since men are involved in the mission, specific attention must be paid 

to safety. 

3.1. 3.1.1 The methods by which the mission effectiveness can be increased 

include: 

a. Low Failure Rates 

Increased MTBF attained primarily through basic design, and through 

selection and qualification of components and parts shall be accomplished. 

b. Redundancy 

Where adequate reliability cannot be attained by means -of a single path 

or component, redundancy must be provided along with a highly reliable 

means of transferring to the alternate. 

c., Maintenance 

Although emphasis should be placed on i.nherent reliability for the entire 

mission time, the fact that a crew i.s on-orbit permits maintainability of 

certain elements. This is only possible if appropriate design measures 

have been taken for checkout, access, and replacement. Determination 

of the extent to which manned maintenance can contribute to reliable space 

-operations is a significant goal of the program. The design shall be such 

that maintenance capabilities learned on one flight can be instituted as 

planned, but not necessarily scheduled procedures for similar elements on 

the next flight. However, maintenance tasks should not intefer. with time 

• allotments for experimental tasks. 

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d. Alternate Mode Flexibility 

It will be essential to minimize the over-all effects of single failures-on 

mission accomplishments. Obtaining a significant amount of mission 

data in spite of failures should be,a prime consideration in task and time 

allotments. 

3. 1. 3. 1. 2 Program Effectiveness 

In order to insure attainment of experimental results, it is essential 

that basic experiments be scheduled on at least two flights and that programming of 

tasks on-orbit be timed to maximize the data obtained. Data readout to ground 

stations should be planned not only to provide monitoring as a basis for decision by 

the mission control center, but also to record information which might be lost due to 

subsequent malfunctions. 

3. 1. 3. 1. 3 Specific Mission Effectiveness 

Over-all program effectiveness shall be defined in terms of probabilities for mission success of individual flights. These shall be further identified 

in terms of required success probabilities for each system segment and the 

principal subsystems thereof. 

3.1.3.1.4 Data shall be developed to support a detailed apportionment of 

effectiveness to the various system segments. 

3.1.3.1.5 For each system segment, a plan shall be developed to show how sub'-. 

stantial compliance of the effectiveness allocations will be demonstrated prior to 

acceptance. 

3. I. 3.1. 6 For each system segment, a plan shall be.developed to show how 

actual compliance to the effectiveness allocations is judged based on the performance, 

as applicable, during mission events such as assembly, launch, flight, and recovery. 

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3..1..3. 2 Maintainability 

3. 1. 3. 2. 1 Maintenance Requirements 

3.1.3. 2. 1.1 Ground Maintenance Requirements 

Maintainability of launch.vehicle•AGE and flight systems 

shall conform to the. requirements of MIL-M-26512C with. the exceptions as 

specified in 'Attachment 1 to SSD Exhibit 62-126. 

The .design of the OV AGE shall use MIL-M-26512C as a 

guideline for .maintainability purposes. Maintenance at the launch site shall 

be restricted to major module/component removal and replacement. Module 

and component repair will be accomplished .at the point of manufacture. 

Spare modules will be stocked at the launch site as required based on detailed 

maintenance analysis. 

The AGE shall be designed such.that ease .of maintainability can be incorporated to minimize equipment down time in order that 

launch .schedules may be adhered to. AGE will be designed to have self-contained fault isolation and detection provisions. Preventative maintenance in 

terms of routine pre-planned tasks such as inspection, lubrication, and 

minor adjustment shall be included in all AGE designs to enable minimum 

equipment down time due to critical component malfunctions. 

3.1.3. 2. 1. 2 On-orbit Maintenance Requirements 

The scope of on-orbit scheduled and unscheduled maintenance and repair shall be established as a result of design optimization studies 

and tradeoffs. Quantitative maintainability requirements shall be established 

consistent with allowable element down times. Adequate accessibility shall 

be provided for the maintainable items. 

3.1. 3. 3 Useful Life 

This paragraph is not applicable in the weapon system sense to the 

MOL Program. 

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3. 1.. 3. 4 Environment - Natural and Induced 

,The environments applicable to the MOL Program are divided into 

the following general classifications: 

a. Prelaunch - (applicable to all segments) 

b. Launch/ ascent - (applicable. to Airborne Vehicle and pad) 

c. On-orbit - (applicable to Orbiting Vehicle) 

d. Descent and Recovery - (Applicable to Gemini. B) 

3.1.3. 4.1 $SD Exhibit 64- , "Environmental Criteria .Specification for 

the MOL System", which contains all details on the applicable environments 

other than launch and early ascent. 

3.1. 3. 4. 2 SSD Exhibit 62-116A, "Environmental Requirements Specification, Program 624A", Revision A, 1 July 1964, which covers the launch and 

early ascent phases. 

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3.1.3.5 Transportability and Handling 

3.1.3.5.1 General 

Existing transportation and handling equipment from military 

or commercial sources will be used in preference to the design of new 

equipment. Equipment shall conform to the requirements of MIL-S-8512 

and MIL..M-8090C as well as to the environmental requirements of this 

specification.. 

3.1.3.5.2 Transportability 

Transportation planning for all components of the MOL 

System shall be by air in accordance with Space Systems Division 

Exhibit 63-3 and MIL-A-8421B. However, other modes of transportation 

may be utilized. 

3.1.3.5.3 Handling 

The handling of ground equipment shall be in accordance 

with the general requirements of MIL-S-8512B. To facilitate the handling 

of ground equipment, the design shall incorporate the safety measures 

prescribed in AFSC Manual 80-5. 

Instrumentation or other indicators shall be affixed to all 

transport assemblies, as required, to record or indicate any out of 

tolerance environments which have been encountered during transport or 

handling of sensitive assemblies or components. 

3.1.3.6 Human Performance 

For this program the Flight Crew has been functionally separated 

from the Ground Crew and is treated in the Flight Crew and Crew Equipment 

System Segment, Section 3.3.5. All Ground Crew will be treated within 

their associated segments. 

Documents governing system development fall into two categories: 

(1) Those applicable or partially applicable for use as governing documents 

and (2) Those usually concerned with operational system development which 

may be used primarily for guidance as they are not totally applicable. The 

•

`

. 

documents concerned with human performance (both Flight Crew and Ground 

Crew) are listed in Appendix A with these prefixes: 

Applicable or partially applicable Prefix HP 

Guidance Prefix GP 

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3. 1. 3. 7 Safety 

3.1. 3. 7.1 Applicable Documents for Safety are listed in Appendix A with 

the prefix letters; SF. 

3. 1. 3. 7. 2 Mission Safety Criteria 

3.1. 3.7.2. 1 The equipment design shall, in general, include sufficient 

redundancy so that no single equipment failure shall cause the necessity for 

an abort. 

3. 1.3.7.2.2 The equipment design shall, in general, include such 

features that no single equipment failure shall be cause of a fatality. 

3. 1. 3. 7.2. 3 Adequate design measures shall be taken to either avoid 

the use of toxic fluids in manned segments or to prevent their coming in 

contact with personnel during normal breakdown modes. 

3. 1. 7. 3 General 

The safety requirements specified under this paragraph shall 

include all equipment and areas which the crew may be expected to contact, 

or be in the immediate vicinity of; incorporating design features to preclude 

all forms of chemical and physical injury. 

3. 1. 3. 8 Dangerous Materials and Components 

a. Acceptable concentrations of toxic compounds shall be 

determined both for short term and for continuous exposure. The primary 

exposure problem is related to toxic materials encountered by-fuel handlers. 

However, to the extent that these materials .are diffused into the atmosphere, 

there is a problem of exposure of persons not in the immediate area of the 

fuel handling operation, including civilian populations. 

b. Techniques and equipments shall be selected to ascertain 

that safe exposure levels are not exceeded. Storage containers and methods 

of handling toxic materials shall be specified. An investigation of available 

and appropriate types of protective clothing (impermeable, impregnated, 

etc. ), and respiratory masks (including those which permit the inhalation of 

outside air after filtration and those which contain a portable oxygen supply) 

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c. Special attention is required for problems concerning the OV 

and on-orbit operations. This should include materials failures or developed 

toxicity (due to outgasing, embrittlement, etc.) promulgated by radiation 

and/or high vacuum or low temperature condition exposure. 

3.1. 3. 9 Noise and Vibration 

(See Section 3. 1. 3. 4) 

3. 1. 3. 10 Life Support 

(See Section 3.3.5) 

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• 3.2 System Design and Construction Standards 

The System Design and Construction Standards contained herein shall 

be applicable to the performance, design, , development and test of the system 

equipment, as well as to the. Design Disciplines, such as Mechanical, Electrical, etc. Design requirements of this type shall be imposed .by specifying 

the incorporation of the established military standards and specifications as 

applicable in the individual contract Qnd item specifications. The documents 

listed in Appendix A with the prefix DG shall be used .as general guides in the 

design and construction of the MOL Program equipment. 

3.2.1 General Design and Construction Requirements 

Requirements specified herein shall apply to the design and construction of all system equipment. Those documents listed in Appendix A 

with the prefix letters DR form a part of this requirement. 

3.2.1.1 Selection of Specifications and Standards 

3.2.1.1.1 The selection of specifications and standards fora the. identification, control and procurement.of the commodities required to design and 

fabricate .the equipment under contract shall be .in accordance..with MIL-STD- 

•143 and the requirements. of this specification. Only those military documents 

listed in ANA Bulletin 400 and/or the DOD Index..of Specifications and Standards 

shall be.interpreted as being ;".I" documents •as defined in MIL-STD-143. 

Specifications .and Standards of Governmental Agencies .other than DOD 

(e. g. NASA, FAA, etc.) shall be interpreted as being Group III. documents 

as defined in MIL-STD-143. 

3.2.1.1.2 Specification control and/or source control drawing as defined 

in MIL-D-70327 shall be-used to modify or augment the requirements .and 

quality assurance provisions:of the documents available to the. contractor 

from Group I through IV inclusive ,of MIL-STD-143. In order of precedence 

this method is desired over the use _of Group V documents. Any Group III 

documents selected for use shall automatically necessitate the preparation 

of a specification control drawing and shall be so drafted to establish the 

specific document being referenced, its date of issue, and contractor control 

responsibility for, its use. 

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• 3. 2.1.1.3 Military Standards shall be employed to the maximum extent. 

(AFSSD Exhibit 61=81, Compliance Specification.) 

3. 2.1.1. 4 All standards or specifications-other.than those established and 

approved for use by the Air Force must be approved by the procuring agency 

prior to incorporation into the system specification. 

3. 2. 1.2 Materials, Parts and Processes 

Materials, parts and processes selected for this system shall be 

selected with attention being given to the stringent requirern.ents of temperature, temperature gradients, thermal conductivity, vibration, shock, loads, 

pressure, light weight construction, and simplicity of manufacture. To insure compliance with optimum utilization of procedures, processes, methods, 

etc. , the following shall be adhered to: 

3. 2.1. 2. 1 Attention shall be directed to prevent unnecessary use of 

strategic and/or critical materials. A strategic and critical materials 

list can be obtained from the procuring agency. 

3.,2. 1. 2. 2 The use of non-standard materials, parts and processes shall 

be justified as to the reason for their use in lieu of standards as well as substantiation of their suitability for the intended application by submittal of 

engineering analysis, test reports, etc. to, demonstrate that the replacement 

has satisfactory performance characteristics. 

. 3. 2.1. 2. 3 Those documents listed in Appendix A with the prefix letters 

MP apply to the Materials, Parts, and Processes requirements. 

3. 2.1.3 Standards and Commercial Parts 

MIL-HDB-300 shall be used to insure the use of standard and commercial parts and parts, listed in MIL-S-38000 Qualified Parts Lists. To comply with the requirements, .the following definitions and procedures are 

offered: 

3. 2.1.3. 1 Military Specified Parts, Military Standard Parts, and MILSpec Parts are interpreted as those parts controlled by, and procurable under 

the documents classed as Group I in MIL-STD-143. 

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• 3.2.1.3.2 Government Standard Parts are defined as those parts controlled 

by and procurable under the documents classed as Group II and III in MIL-STD143. 

3.2.1.3.3 Industry. Standard Parts shall be understood to be those parts 

controlled by and procurable under the,documents classed as Group IV in 

M1L-STD-143. 

3.2.1.3.4 Design Activity Standard Parts, Company Standard Parts and 

Commercial Parts shall be understood to be those parts controlled .by and 

procurable under the, documents classed as Group V in MIL-STD-143. 

3. 24:3 5 Full utilization shall be made of IDEP. 

3.2.1.4 Moisture and Fungus Resistance 

Materials shall be used which will resist damage from moisture 

and fungus.. Protective coatings will not be acceptable as moisture and 

fungus preventatives on parts which will lose the coatings during the normal 

course .of inspection, maintenance, and periodic testing. "Moisture" shall 

be considered as containing salt from marine atmosphere (MIL-STD-210, 

Climatic Extremes for Military Equipment). The tests necessary to satisfy 

this requirement are specified under MIL-STD-810 and MIL-E-5272C. 

3.'2.1.5 Corrosion of Metal Parts 

3.2.1.5.1 Electrolytic Corrosion of Metal Parts 

The use of dissimilar metals, in immediate contact which will 

tend- to accelerate electrolytic corrosion in the presence of moisture shall 

be avoided - as defined in MS 33586A. Where the use of such metals in immediate' .toritact cannot be avoided, proper protection or insulation of such parts 

shall be provided. Care should be taken to prevent equipment corrosion in 

the laboratory due to moisture .under zero g conditions. The moist salt atmosphere created by man's presence may increase such electrolytic problems. 

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3.2.1. 5.2 Stress Corrosion • . Materials techniques and processes shall be selected and employed with regard to heat treatment procedures, corrosion protection, .finish 

and assembly.and installation such that sustained/residual surface tensile 

stresses, stress concentrations and the hazard of stress corrosion, cracking 

and hydrogen embrittlement are minimized. 

3. 2. 1. 5. 3 Protective Methods 

Protective methods and materials for cleaning, surface treatment, and application of finishes and protective coatings shall be accomplished 

in accordance with MIL-F-7179. 

3. 2. 1. 6 Interchangeability and Replaceability 

3. 2.1. 6.1 Interchangeability and Replaceability in Terms of In-Flight 

Maintenance Requirements 

Insofar as possible, the design and manufacture .of all MOL 

subsystem and experimental equipment shall not preclude the using of common 

parts such as valves; or electronic components such as transistors, capa.ci-• 

tors,..or printed circuit modules; or equipment in which one unit or component can be ,utilized for several functions in many items of the same or different equipments. Connectors, fasteners, small tubing and piping, . etc. , 

should be. designed such that satisfactory interchangeability can be .accomplished for many of these common items in order to alleviate spare part 

requirements and variety of types ,of special tools required for• interchangeable, Or non-interchangeable but replaceable, parts.of a common nature. 

Therefore; appropriate attention should .be given toward's obtaining maximum 

Usage of common. devices .and component parts insofar, as possible•on all 

MOL subsystems and experimental equipment in the Orbiting Vehicle. Applicable documents are listed in Appendix A with the prefix letters IC. 

3. 2. 1. 7 Workmanship 

The equipment, including all AVE and AGE parts and accessories, 

shall be constructed and finished in accordance with.the detail requirements 

specified in the documents listed in Appendix A with the,prefix letters WK.. 

The workmanship requirements of MIL-E-5400F, Paragraph 3. 5, shall be 

implemented with the aid of written standards for workmanship. 

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3.2.1.7.1 Quality Assurance 

• This section covers the quality assurance requirements that 

must be implemented during the design and manufacturing phases to assure 

the timely implementation of adequate and appropriate controls in accordance with MIL-Q-9858A and USAF Specification Bulletin No. 515 to ensure 

that the materials, workmanship and performance are to specified standards; 

and components have been manufactured and tested to approved drawings and 

specifications; and the reliability and quality assurance requirements of 

SSD Exhibit 62-117 have been met. 

3. Z. 1. 7.2 Inspection and Test Equipment Selection 

Equipment required for performance of the necessary 

inspections and tests shall be determined. Planning shall include the 

calibration system requirements to conform to MIL-C-45662A. 

3.2.1.7.3 Material Review Engineering and Quality Assurance 

At the earliest practical point, the material review representatives shall be determined. The material review procedures shall be 

reviewed for conformance to USAF Specification Bulletin No. 515. 

3.2.1.7.4 Vendor and Subcontractor Selection and Control 

The Contractor shall have a system for supplier selection and 

control. The system shall provide for continued assessment of suppliers. 

Provisions shall exist for requiring quality control systems in the plants of 

suppliers and lower tier subcontractors in accordance with MIL-Q-9858A or 

MIL-I-45208A as appropriate. Specification control drawings shall be 

generated in accordance with MIL-D-70327. 

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3.2.1.8 Electromagnetic Interference 

The General Design and Construction Requirements for this subject 

have been prepared under SSD Exhibit 64- titled, Electromagnetic Interference Control Specification for Manned Orbiting Laboratory. Applicable 

Military Specifications are listed in Appendix A with the prefix letters EI. 

3.2. 1. 9 Identification and Marking 

Equipment, assemblies and parts shall be marked for, identification 

in accordance with SSD Exhibit 62181. Specific identification requirements 

include such conditions as: 

3.2. 1. 9. 1 Equipment which may be damaged by operation in excess of 

the rated duty cycle shall be so marked. 

3.2.1. 9. 2 Items with limited operating lifetime or shelf life shall be so 

marked and a log maintained which is attached to the subject item. 

3.2.1. 9. 3 Critical components, as defined by AFSCM 375-1 shall bear a. 

high visibility and unique marker, plaque or decal which will immediately 

identify these components. This identification shall not be used on any other 

type item, . other than those classified as critical. 

. 3.2. 1. 9. 4 Applicable documents relating, to Specification and Marking 

are listed in Appendix A with the prefix letters IM. 

3.2.1.10 Storage 

The system shall be designed .to minimize the degrading effects 

of storage environments. In the event unwarranted system, weight, bulk, 

environmental limitations,. etc. are involved in achieving storage protection, 

special protective containers, covers, etc. , may be used. Special design 

attention shall be devoted to critical items - per AFSCM 375-1. System design criteria relative to the in-orbit storage .of maintenance items needed 

during the orbital mission shall be established by design activities. This 

criteria shall be incorporated into CEI specification and critical component 

specifications. Applicable documents relating to Storage listed in Appendix A 

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3. 2. 2 Design Disciplines 

The .design criteria requirements listed shall be limited to specific 

design disciplines and/or types of equipment: 

.3.2.2.1 Electrical 

The electrical design discipline requirements have been prepared 

under SSD Exhibit4- , titled, General Specification, Wiring Harness. 

The -applicable do uments for this subject are listed in Appendix A with the 

prefix letters EE. 

3. 2. 2. 2 Mechanical 

Mechanical equipment design disciplines shall be applied to AVE, 

MGE and OGE and shall reference such documents as AFM 88-2, Definitive 

Designs for Air Force Structures. 

3. 2, 2. 3 Hydraulic and Pneumatic 

Applicable Hydraulic and Pneumatic reference documents are listed 

in Appendix A with the prefix letters HP. 

3. 2. 2. 4 Civil 

Applicable civil reference documents are listed in Appendix A 

with the prefix letters CV. 

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3. 3 Performance Allocations • 3. 3. 1. Orbiting Vehicle System Segment 

1. 1 Allocated Performance and Design Requirements 

3. 1. 1. 1 Mass Parameters 

3. 3. 1. 1. 1. 1 Weight Breakdown 

The gross weight of the Orbiting Vehicle shall be approxi3. 3. 

3. 

mately.19, 700 pounds, excluding the Transtage. 

3. 3. 1. 1. 1. 1. 

pounds. 

3. 3. 1. 1. 1. 1. • 

The Orbiting Vehicle (OV) shall be composed of the following system 

segments: the Gemini B; the Laboratory; the Experiments; and the Titan•III 

Transtages and flight crew and crew equipment. The rendezvous and docking 

aspect of the segment is treated in Paragraph 3. 3.1. 2. 12. 

1 Laboratory 

The Laboratory segment weight shall not exceed 9800 

2 Gemini B 

The allocated weight•of the Gemini B segment shall not 

exceed 6300 pounds, including crew and flight equipment. 

3. 3. 1. 1. 1. 1. 3 .Experiments 

The allocated weight of the Experiments segment shall 

not be less than 3600 pounds for a 30-day mission integral launch mission. 

3. 3. 1. 1. 1. 1. 4 Transtage 

The Transtage dry weight shall not exceed 5250 pounds. 

3. 3. 1. 1. 1. 2 Center of Gravity 

The center of gravity shall be established and controlled 

such that requirements for on-orbit attitude control, and Titan II1C launch 

phase control are not compromised. 

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3. 1. 1. 2 Electrical Power 

3. 3. 1. 1. 2. 1 Orbiting Vehicle 

The Laboratory central power system (CPS) shall provide 

the total'Orbiting Vehicle power requirement while on orbit. The power over 

the entire 30 days is 1. 8 KW with a peak of 3. 6 KW. Peak requirements for 

each .segment are identified in the appropriate segment sections. 

3. 3. 1. 1. 2. 2 Gemini B 

Electrical power allocation to the Gemini B shall be 200 

watts average. 

Power system monitoring functions of the Gemini B local 

power supply shall be located both within the Gemini B and the Laboratory. 

The total abort and re-entry power system requirements shall be provided by 

the local Gemini B power supply. 

3. 3. 1. 1. 2. 3 Laboratory 

The Laboratory shall be allocated an average power of 

1. 35 KW for its functions during all phases of the mission after transfer to 

internal power. 

3. 3. 1. 1. 2. 4 Experiments 

The Experiment System Segment shall. be provided an 

average power of 250 watts from the CPS. Experiments peculiarly, incompatible 

with the CPS shall be supplied from an Experiment-peculiar power supply. 

3. 3. 1. 1.2.5 Transtage 

The average power required from the Orbiting Vehicle for 

on-orbit operation of the Transtage shall be included in the power allocation 

for the Laboratory Segment. This allocation is 50 watts average power. 

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3. 3. 1. 1. 3 Leak Rate 

The leak rate on orbit, with all system segments normally pres.- 

surized, • shall not exceed approximately 4. 5 lb/day, of which approximately 

2. 5 lb/day, shall be allocated to the Gemini B (and transfer tunnel) and approximately. 2. 0 lb/day shall be allocated to the Laboratory. 

3. 3. 1. 1. 4 Effectiveness 

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3. 3. 1. 2 Peculiar Performance and Design Parameters • Certain Orbiting Vehicle requirements will be unique to particular 

flights. The following requirements are those which are common to all flight 

configurations. 

3. 3. 1. 2. 1 Communication and Control 

3.3. 1. 2. 1. 1 General 

The Communication and Control Systems located in the segments shall be capable of independent operation. Electromagnetic compatibility 

shall be demonstrated when systems located in the different segments are 

activated simultaneously. 

3. 3. 1. 2. 1. 2 Command-System' 

Isolation shall be provided between the Gemini B Command 

System and the Laboratory Command System to prevent inadvertent activation 

of either Command System. 

3. 3. 1. 2. 1. 3 Data Transmission System 

Sufficient isolation shall be provided between the Gemini B, 

Titan III and Laboratory Vehicle Data Transmission Systems to prevent interference between those systems when operating simultaneously. 

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• 3.3.1.2.2 Orbit Attitude Maneuvering System' (OAMS) 

3.3.1.2.2.1 Operational Modes 

The on-orbit attitude control shall be provided by the 

Laboratory. The OV shall be capable of on-orbit operation with or without 

the transtage attached. 

3.3.1.2.2.2 Orientation 

Maneuver capability to any attitude and the maintenance of 

this attitude in either inertial orientation or in a local vertical orientation 

shall be provided. Generation of disturbance torques by venting of stored 

material and by starting and stopping of rotating machinery shall be minimized. 

3.3.1.2.2.3 Remote Activation and Control 

Capability to control the transtage main propulsion engine 

ignition, thrust termination and gimbal system from the Laboratory shall be 

provided. The interface between the transtage propulsion system and the • Laboratory control system shall be at the gimbal servo valve and the propellant 

valve inputs. 

3.3.1.2.2.4 Maneuvering 

On orbit maneuvers requiring addition of velocities in excess 

of approximately 10 feet per second shall be accomplished with Transtage 

Propulsion. Maneuvers requiring lesser velocity additions shall be accomplished 

with the Laboratory propulsion system. 

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3. 3. 1. 2. 3 Structural Design Requirements 

3. 3. 1 . 2. 3. 1 General 

Sufficient strength and rigidity shall be provided to meet 

the maximum loading and/or environmental conditions within the envelope of 

missions requirements. The Orbiting Vehicle shall be compatible in terms 

of load transmission capability and mating at the interfaces- with the Gemini B, 

with Titan IIIC Transtage, and with the experiments. 

3. 3. 1. 2.3.2 • Separation 

The capability shall be provided for separation on orbit 

between the Gemini B and Laboratory System Segments and between the 

Orbiting Vehicle and Titan IIIC Transtage. 

3. 3. 1. 2. 3. 3 The rmos tructural 

The Orbiting Vehicle shall not adversely deform as a result 

of structural temperature gradients. 

3. 3. 1. 2. 3. 4 Aeroelasticity 

Flutter or other related dynamic instability shall be prevented 

on the orbiting vehicle system. 

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• 3.3.1.2.4 Crew Transfer 

3. 3. 1 . 2. 4. 1 Normal Mode 

An internal pressurized tunnel through the heat shield shall 

be provided to transfer the crew between Gemini B and the Laboratory. 

Movement through the hatches and tunnel shall be in vented pressure suits; 

however, emergency inflation of the suit shall not cause trapping in the tunnel. 

The Gemini B heat shield and pressure hatch shall remain open at all times 

when both crew members are not in the Gemini B. 

For the initial transfer to the Laboratory, one crewman 

shall transfer into the smaller Laboratory compartment prior to beginning 

transfer of the other. For final transfer from Laboratory to Gemini B, the 

first crewman shall verify that all Gemini B systems are operating satisfactorily prior to transfer of the second. 

3. 3. 1 . 2. 4. 2 Emergency Mode 

Provision shall be made for extravehicular egress/ingress 

and transfer of crew members between the Gemini B and the Laboratory 

vehicles. 

Extravehicular egress/ingress to Gemini B shall be via the 

regular Gemini B hatches and to the Laboratory through the extravehicular 

hatches. 

Emergency transfer capability shall be provided from all 

Laboratory Vehicle compartments to space for extravehicular transfer to 

Gemini B. 

The Laboratory vehicle shall provide umbilical lines and 

a one hour supply of metabolic oxygen for two crew members. Back-up 

emergency Environmental Control shall be provided by the portable system 

specified as part of Experiment P-6. (Ref. section 3. 3. 4.) 

3. 3. 1 . 2. 4. 3 Number of Transfers 

Several return trips may be made to the Gemini B during 

the mission. 

3. 3. 1 . 2. 4. 4 Parc el Transfer 

Small packages shall be required to be manually transferred between the Laboratory and Gemini B. 

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• 3. 3. 1. 2. 5 Experiment Provisions 

3. 3, 1. 2. 5'. 1 General 

Data packages containing film, magnetic tape, bio samples 

and other material shall be transferred to the Gemini B for return. 

3. 3. 1. 2. 5. 2 Modification Group List per Flight 

Modifications to the Orbiting Vehicle for each flight 

mission and the experiment payload configuration, with its allocated performance characteristics and requirements, shall be defined, in accordance with 

Appendix B. 

3. 3. 1. 2. 6 Orbital Operations 

3. 3. 1. 2. 6. 1 Laboratory Activation 

The orbit will be circularized at the operational altitude 

within the range of a ground tracking station, followed by laboratory segment 

subsystems activation and checkout. Pre-transfer actions shall be accomplished in such a manner that the first astronaut commences transfer to the 

Laboratory while the orbiting vehicle is within range of communication 

stations. Upon completion of laboratory activation, the second astronaut 

will begin the Gemini B shutdown and transfer to the Laboratory within 

range of a. communication station. Upon completion of Laboratory activation 

tasks, the Laboratory orbital configuration will be verified and a shirtsleeve environment utilized. 

3. 3. 1. 2. 6. 2 Experiment Operation 

The orbiting vehicle and mission requirements for the 

on-orbit operation of the experiments, such as jettisonable covers, sensor 

deployment, antenna erection, air locks, extravehicular activity, 

human factors, bioastronautic 

measurements, and observation locations are specified. 

Upon completion of the on-orbit test phase the Gemini B 

shall be checked out and activated and the crew transferred in sequence with 

data such as film, magnetic tape, bio and other test samples. The Laboratory 

shall be de-activated and separated in preparation for de-orbit and re-entry 

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3. 3. 1. 2, 7 Aerospace Ground Equipment (AGE) 

The OV AGE shall include all the integrated Gemini B, Laboratory and Experiments AGE which is necessary to transport, handle, mate, 

integrate, verify interfaces, calibrate, check out, isolate faults, monitor, 

record, service and control the OV as an independent system and the OV as a 

system mated with the Titan IIIC booster. This AGE shall be capable of providing a means of (1) verifying the proper operation of the OV systems during 

checkout, countdown and launch, (2) determining whether the fully assembled 

system is operable within the prescribed limits of each segment, (3) assuring 

that all interfaces (electrical, mechanical, and human) between OV segments 

or with external surfaces are proper, and (4) identifying to the segment (or in 

critical systems the sub-segment) level areas of failure or operation outside 

of prescribed operating limits. The OV AGE shall be designed for compatibility with the Titan IIIC AGE and the ITL facilities. The OV AGE in the ITL 

system and located at the launch pad and/or in the Vertical Integration 

Building (VIB) shall provide capability for checkout of the integrated OV in 

any cell of .the VIB and for launch from either pad of the ITL system with a 

minimum of facility down-time and duplication of equipment. The OV AGE to 

be utilized at the Integrating Contractor's facility shall be functionally 

identical to the AGE utilized at the ITL. Provisions for OV AGE self-check 

and verification shall be provided. 

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3. 3. 1. 2:8 On-Orbit Monitoring and Checkout 

Both ground telemetry data and in-flight monitoring panels 

shall be utilized for on-orbit monitoring and checkout. The parameters 

requiring checkout and the frequency of performing monitoring function's shall 

be specified for each orbiting vehicle subsystem. Orbiting vehicle checkout 

shall be performed prior to activation or initiation of any new phase of the 

mission, and during the first few orbits, to establish performance parameters 

of each subsystem. Functions shall be visually and audibly presented for 

critical subsystem malfunctions. 

3. 3, 1. 2.9 On-Orbit Maintenance 

Design for maintainability shall be incorporated for those 

components or system elements where tradeoff studies show that crew safety, 

mission completion, and/or design adequacy will be best improved by the 

provision: of a maintenance capability. Where design for ground maintainability, which includes accessibility and ease of removal and replacement of 

selected modules or components, does not degrade in-flight capabilities, it 

shall be incorporated into the design. Maintenance shall normally be limited 

to the interior of the Laboratory or Gemini B. 

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3.3.1.2.10 Rendezvous and Docking Missions - Orbiting Vehicle • 3.3.1.2.10.1 Payload Allocation 

3.3.1.2.10.1.1 The minimum experimental payload for the target 

vehicle shall be 3000 pounds. 

3.3.1.2.10.1.2 The maximum experimental payload in the chase 

vehicle shall be provided which will not compromise the rendezvous mission. 

3.3.1.2.10.2 Rendezvous Operations Requirements 

3.3.1.2.10.2.1 Pre-Docking 

3.3.1.2.10.2.1.1 The Gemini B rendezvous radar, computer, and 

displays shall provide the gross rendezvous guidance and control capability. 

3.3.1.2.10.2.1.2 Sufficient fuel to permit maneuvers of approximately 500 fps shall be provided in the transtage system of the chase vehicle. 

3.3.1.2.10.2.1.3 A velocity of approximately 50 fps shall be provided in the chase vehicle OAMS to permit terminal rendezvous and final 

docking. 

3.3.1.2.10.2.2. Post-Docking • 3.3.1.2.10.2.2.1 The environmental control and life support 

system of the target and chase vehicles shall operate as independent systems. 

It shall be possible to transfer environmental replenishment gases from one 

vehicle to the other. It shall be possible to transfer food and water between 

the two vehicles. 

3.3.1.2.10.2.2.2 After docking, the electrical power systems of 

the two vehicles shall be joined to permit power to be shared in a reasonable 

manner between the two vehicles. 

3.3.1.2.10.2.2.3 The OAMS of either the chaser or the target 

shall operate the completely docked configuration. 

3.3.1.2.10.2.2.4 The Laboratory communication systems shall 

be operable independently, but not simultaneously. 

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• 3. 3.11. 2. 11 Laboratory Requirements 3. 3.1. 2. 11. 1 The Laboratory shall provide structural, electrohnechanical, and space for the fitting of the rendezvous mission equipment. 

3. 3.1..2.11. 2 The target vehicle shall contain: a crew transfer tunnel 

assembly which connects the vehicle pressurized compartment to a mating 

face on the docking plane between the target and chase vehicles, a crew access 

hatch to be installed on the pressure compartment side of the tunnel, a compatible docking mechanism assembly located at the aft end which is exposed 

for operation following transtage ejection, and an umbilical assembly capable 

of effecting electrical power, signal flow, and some fluid transfer between 

docked vehicles. 

3. 3.1,. 2.11 . 3 The chase vehicle structure shall contain: a crew transfer 

tunnel assembly which connects the vehicle pressurized compartment to the 

mating face of the target vehicle at the docking plane, a crew access hatch to 

be installed on the pressure compartment side of the tunnel, a compatible 

docking mechanism assembly located at the aft end which is exposed for operation following transtage ejection, some additional electrical power system 

capability and tankage required for 60 day operation, and an umbilical assembly 

capable of effecting electrical power, signal flow, and gas transfer between the 

docked -vehicles. 

3. 3.1.. 2.11.4 The target vehicle, (including subsystems), and the target 

experimental payload shall be qualified for a minimum of 60 days. 

3. 3. 2. . 5 The chaser vehicle (including subsystems) and the chaser 

experimental payload shall be qualified for a minimum of 45 days. 

3. 3.1..2. 11. 6 The target vehicle shall incorporate radar transponder 

compatible with the Gemini B rendezvous radar. 

3. 3.1.. 2: 11. 7 Power Supply 

The power supply shall have the capability of an in-space 

shut-down after completion of the launch, rendezvous, and docking mission 

phases. It shall be capable of an in-space start after 15 days of on-orbit 

storage in the shut-down mode. 

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3.3.1.2.12 Gemini B Requirements 

3.3.1.2.12.1 The Gemini B shall be capable of storage on-orbit for 

45 days. 

3.3.1.2.13 Transtage Requirements 

Provision shall be made for full control of the transtage main 

propulsion unit from the Gemini B. 

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3.3.2 Laboratory Vehicle System Segment 

The Laboratory'Vehicle shall consist of two sections, one pressurized and 

one unpressurized.. The pressurized section shall consist of two compartments, 

for environmental control, life support, attitude control, power generation, 

communications, vehicle status monitoring, and Experiment operation. 

3.3.2. 1 Allocated Performance and Design Requirements 

3.3.2. 1. 1 Volume 

3.3.2. 1.1.1 Pressurized 

The. Laboratory Vehicle shall provide a pressurized volume 

of approximately 1200 cubic feet, divided into two compartments which shall 

permit emergency egress (extra-vehicular). 

3.3.2.1.1.2 Unpressurized 

The Laboratory Vehicle shall provide a usable unpressurized 

volume of approximately 600 cubic feet. 

• 3.3.2. 1. 2 Internal Arrangement 

The equipment in the Pressurized section shall be arranged to 

afford maximum free volume for crew mobility. Provisions for crew personal 

requirements shall be integrated into a specific area of the Section, and all 

manually-operated control functions shall be related for functional efficiency. 

. . 

Equipment shall be packaged for minimum crew interference and injury. The 

over-all internal arrangement shall provide for convenient and simple management of the vehicle by the crew. 

3.3.2.1.3 Crew Stay Time 

The Laboratory Vehicle shall provide for a nominal on-orbit 

stay time fora two-man crew of 30 days, plus a reserve time of three days. 

3.3.2.1.4 Launch Re-cycle Operations 

The MOL System must be capable of re-cycle following a postponed launCh so as to coincide with Titan IIIC requirements. 

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3. 3. 2. 1. 5 Effectiveness 

Data shall be furnished to support a detailed apportionment of 

effectiveness to the Laboratory Vehicle Segment. A plan shall be developed 

to show how substantial compliance of this effectiveness allocation will be 

demonstrated prior to acceptance and how actual compliance to this 

effectiveness allocation is judged during each mission. 

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3. 3. 2. 2 Peculiar Performance and Design Requirements 

3. 3. 2. 2. 1 On-orbit Maintenance 

Critical elements of the Laboratory shall be designed and arranged 

to facilitate on-orbit maintenance and repair operations. 

3. 3. 2. 2. 2 On-orbit Technical Data 

Technical data on each of the Orbiting Vehicle segments and 

their subsystems as required by the Flight Crew in the performance of their 

operational and.maintenance functions shall be provided in a convenient and 

easily accessible form. 

3. 3. 2. 2. 3 Docking Provisions. 

The external arrangement shall be such that docking to at 

least one end of the Laboratory shall be possible. 

3. 3. 2. 2. 4 Ou tgas sing and Venting 

The Laboratory shall be designed so that neither normal • venting nor normal leakage of the consumable stores shall impinge on the 

Transtage. 

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3. 3. 2. 2. 5 Communication and Data Handling Requirements • 3. 3. 2. 2. 5.1 Command System 

3. 3. 2. 2.5.1.1 Scope 

The ground-to-vehicle command link is required to transmit 

information which will control certain vehicle equipments or up-date subsystems 

such as the guidance subsystem or an on-board computer. A prime concern is that 

the command sent is received and translated into the proper command with maximum reliability and minimum error. 

3. 3. 2. 2. 5.1.2 System Description 

3. 3. 2. 2. 5. 1. 2. 1 General 

The MOL Command System shall consist of the ground 

equipment for sending the command, and the vehicle equipment for receiving and 

distributing the command. The command system will be from ground to vehicle 

(one way). 

3. 3. 2. 2. 5.1. 2. 2 Receiving 

Multiple receivers operating continuously in parallel 

will receive the RF signal from the antenna system interface. Each receiver will 

detect the carrier modulation information and provide this as an audio output to 

the decoder. 

3. 3. 2. 2. 5. 1. 2. 3 Decoder Type 

The command decoder shall be of the digital type. 

3. 3. 2. 2. 5. 1. 2. 4 Bit Rate 

The command system shall accommodate an information bit rate of 200 per second minimum. 

3. 3. 2. 2. 5.1.2. 5 Command Capacity 

The basic capability for the laboratory vehicle shall 

be: one (1) Vehicle Address, one (1) Real Time System Address, and four (4) 

Stored Program System Addresses. Consideration should be given to expansion 

of Real Time System Addresses and Stored Program Addresses. 

3. 3. 2. 2. 5:1. 2. 6 Number of RTC Channels 

A minimum of 32 RTC output channels shall be provided. 

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3. 3. 2. 2. 5.1. 2. 7 Error Probability 

The probability of the decoder accepting an invalid 

message shall be less than 1 x 10-6. The probability of rejecting a valid message 

shall be less than 1 x 10-3. Error detection codes may be considered as a means 

of trading RF bandwidths for lower probability of error. 

3. 3. 2. 2. 5. 1. 2. 8 Message Verification 

At the completion of a valid command sequence, a 

verification signal shall be sent to the telemetry data link. 

3. 3. 2. 2. 5.1. 2. 9 Invalid Message Reset 

Detection of an invalid command/message shall cause 

the decoder to reset and await the repeated or reset command. 

3. 3. 2. 2. 5. 1. 2. 10 Stored Program Command (SPC) Transfer 

Decoded SPC's will be stored in appropriate circuits 

and a ready pulse sent to the addressed system. Message transfer is accomplished 

on receipt of clock pulses to the decoder, reading out the message in the order 

received. New data will be inhibited until transfer of data or reset of the decoder. 

The decoder shall be reset after transfer of data or after an appropriate time 

interval has elapsed following message storage. 

3. 3. 2. 2. 5.1. 2. 11 Power 

Power leads shall be isolated from case ground. No 

false command execution outputs shall result from out-of-tolerance receiver operation, 'over-or-under voltage, or voltage transient conditions. 

3. 3. 2. 2. 5. 2 Data Acquisition System 

3. 3. 2. 2. 5. 2.1 Scope 

Data acquisition is part of the total communications and 

data handling system and must interface with voice transmission, command verifir 

cation, and intercommunication requirements. 

3. 3. 2. 2. 5. 2. 2 General 

The Data Acquisition Subsystem shall: 

1. Accept electrical signals from the flight crew and 

Experiments Information System. 

2. Provide equipment for signal conditioning, coding and 

multiplexing the instrumentation signals for telemetry and recording. 

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3. Provides tape recorders/reproducing equipment. 

• 4. Provide a video system for support of .vehicle 

status reporting. 

3.3.2.2.5.2.3 System Description 

3.3.2.2.5.2.3.1 General 

The major elements of the Data Acquisition System 

are the PCM telemeter, a large capacity magnetic tape recorder(s), and a 

wideband data system. 

The same basic equipments shall be us ed for 

both manned and unmanned flights. VHF FM/FM telemetry may be used to 

accommodate high frequency vibration and similar requirements. 

3.3.2.2.5.2.3.2 PCM Telemetry 

The Laboratory Vehicle telemetry system shall be 

as separate and operationally independent of Gemini B spacecraft telemetry as 

possible consistent with the requirement for the capability of monitoring and 

transmitting critical Gemini B parameters remotely in the Laboratory Vehicle. 

The PCM Telemetry must accept a variable mix of • analog, digital, and discrete data inputs. Depending upon the particular flight 

mission and the mission phase, telemetry demands may vary. The system shall 

be sized for 350 input channels maximum and 64 channels minimum. The PCM 

telemetry shall allow for expansion of the number of channel inputs to 600-700 

without major re-design. Analog inputs shall be both high level (0-5 watts) 

and low level (0-20 millivolts, approximately). The design must also provide 

for selection and format combination of a wide range of sampling rates. The 

system shall be capable of operating at a transmission rate of 51.2 kilobits/ 

sec minimum. The PCM format shall be compatible with Gemini PCM 

ground station decommutation and data handling equipment. 

An important aspect of the PCM telemetry system 

design is control integration with a compatible magnetic tape recorder(s). Continuous recording of a sub-frame(s) of vehicle and crew status data at a rate of 

approximately 5 kilobits/sec is required, which will be transmitted later at a 

high rate to primary MOL ground stations. Similarly and normally simultaneously, capability must be provided for recording of a sub-frame(s) of limited special 

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vehicle and experimental data. Telemetry dump of the two sets of recorded • data shall be independent. Channel inputs from both data sets shall be available 

for transmission via the Real Time Telemetry. 

3. 3. 2. 2. 5. 2. 3. 3 Magnetic Recording Equipment 

3. 3. 2. 2. 5. 2. 3. 3. 1 Digital Recording 

Vehicle and crew status data will be recorded on 

magnetic tape whenever the vehicle is out of range of an appropriate ground receiving station. High speed playback of the recorded data shall be provided upon receipt of a ground command, programmed signal, or decision by the crew. The 

tape recorder shall be sized to handle a data rate of approximately 5 kilobits 

status data and 5 kilobits other data for a duration of at least three hours. Playback will be based upon 100 minutes of telemetry dump per day. 

It is anticipated that certain experiments will 

require data storage capability at recording rates independent of telemetry. 

3. 3. 2. 2. 5. 2. 3. 3. 2 Video Recording 

The capability for wide band recording of video 

data up to approximately 6 Mc shall be provided. 

3. 3. 2. 2. 5. 2. 3. 4 Wideband Data System 

A potential requirement exists for a wideband data 

systrri capable of handling either high-speed digital data up to approximately 

10 megabits per second, wideband analog transmission of TV pictures with 4 to 

5 Mc video bandwidth, and 2 to 6 Mc/ s bandwidth experimental data. 

Some experiments may provide more than six hours 

of wideband data per 30-day mission. On-board editing of recorded wideband data 

will be required. Photographic and tape record of data is required for capsule return. RF transmission of edited data using the wideband or.PCM telemetry links 

is required. 

3. 3. 2. 2. 5. 3 Data Transmission System 

3. 3. 2. 2. 5. 3. 1 System Description 

The telemetry transmitters shall consist of: 

a. Real Time Transmitters 

b. Standby Transmitters 

c. Delayed Time Transmitters 

d. Wideband Transmitters 

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The transmitter selected for the Laboratory Vehicle 

shall be compatible with the Ground Operational Support System Segment. This 

system shall be active prior to launch for Laboratory Vehicle checkout purposes 

and during ascent and orbital phases of the mission. The system shall be designed to be activated from ground command, an on-board programmer, or 

manually. 

3. 3. 2. 2. 5. 3. 2 Transmitter Characteristics 

The Real Time, Standby, and Delayed Time Transmitters 

shall operate on preassigned frequencies in the 225 to 260 mc/s VHF band and 

conform to IRIG performance standards. Solid-state components shall be used 

for all active elements. 

The wideband link shall utilize direct analog wideband 

FM modulation of up to 5 megacycles bandwidth or binary PCM/PM of up to 

10 megabits bandwidth depending on the application. The carrier frequency 

shall be between 2.2 to 2.3 kmc/s. 

3. 3. 2. 2. 5. 4 Tracking System 

3. 3. 2. 2. 5. 4. 1 General 

The Laboratory Vehicle Tracking System consists of the 

Radio Frequency Beacons required to assist the Ground Orbital Support Segment 

in determining vehicle ephemeris data by ground tracking techniques. This system 

shall consist of a transponder radar-type beacon compatible with the tracking 

radars located at the designated global tracking sites and a CW type beacon to 

aid the ground in vehicle acquisition. This system shall be activated by ground 

command, an on-board programmer, or manually, and will normally be used 

only on-orbit when tracking is required. 

The radar transponder beacon shall operate on C-band 

and shall be compatible with the FPS-16 and FPQ-6 ground tracking radars. 

The VHF acquisition beacon shall operate between 215 to 260 Mc. 

3. 3. 2. 2. 5. 5 Voice System 

3. 3. 2. 2. 5. 5.1 Requirements 

The voice communications subsystem must provide twoway communications between ground and crew and intercommunication between 

the flight crew during laboratory and transfer operations. 

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3. 3. 2.. 2. 5. 5. 2 Equipment 

The laboratory communications equipment shall be compatible with the Gemini B voice communication equipment. 

3. 3. 2. 2. 5. 5.2. 1 Voice Control Center (VCC) 

The VCC consists of both a HF and VHF voice network 

and a common control panel. The two networks shall be capable of operating 

simultaneously during all phases of the laboratory mission. Each network has 

two identical audio systems. The VCC provides a distribution and control center 

for the voice and audio systems and shall be located in the pressurized section. 

Two identical audio systems s hall be provided for 

each crewman. The audio system shall consist of a microphone amplifier,, headset amplifier, voice-operated switching circuit, and an electrical matching and 

switching network to provide'HF/ VHF voice communications and intercommunications. A speaker shall be provided in the pressurized section to retain voice 

contact when helmets are removed. 

A common control panel shall be provided for use 

by the crew. The panel shall have individual mode selection switches and volume 

controls for each crewman. The controls for transmitter-receiver selection, 

squelch and keying shall be common to the crew. 

3. 3. 2. 2. 5. 5. Z. 2 Remote Control Panels 

The remote control panels shall be similar to the 

control panel, but located at points remote from the VCC. The remote control 

panel shall be, electrically connected to the VCC and have the capability of permitting control of the voice networks from the remote positions. 

3. 3. 2. 2. 5. 5. 2. 3 HF and VHF Voice Transmitter-Receivers 

The HF and VHF voice transmitter-receivers shall 

each consist of an AM voice transmitter and an AM receiver which provide twoway duplex crew-to-ground communication. Two HF and VHF transmitterreceivers shall be located in the laboratory. 

3. 3. 2. 2. 5. 6 Antenna System 

3. 3. 2. 2. 5. 6. 1 General 

The Laboratory Vehicle Antenna System shall consist of 

the components from the antenna to the Voice, Data Transmission, Command, 

and Tracking systems. The Antenna System will primarily be utilized when the 

Laboratory Vehicle is in orbit but design consideration shall be given to obtain 

antenna coverage during the ascent phase for the Data Transmission System. 

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3. 3. 2. 2. 5. 6. 2 General Requirements 

The Antenna System shall normally be operational 

during the orbital phase of the mission. 

The C-band, S-band (Wideband Data), and VHF 

(telemetry) antenna radiation pattern shall be essentially hemispherical. 

The command, voice, and acquisition antennas shall 

provide near-spherical coverage such that their associated communications 

functions can be maintained with the ground during spacecraft maneuvers or 

non-nominal attitude conditions. 

3. 3. 2. 2. 5. 7 Security Subsystem 

Capability shall be provided to encryptographically secure 

the VHF duplex voice and telemetry links. The non-secure or secure mode 

of operation for either service or both shall be an in-flight option. The voice 

encryption technique shall minimize vehicle/laboratory equipment size-weightpower and complexity. The telemetry security equipment shall be capable of 

operation with either the PCM telemetry or the wide band data. link. The maximum data rate requirement for the secure telemetry is one megabit/sec. 

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3. 3. 2. 2. 6 Environmental Control and Life Support 

3.3.2.2.6.71 Scope 

The environmental control and life support system shall 

consist of the following functional areas: 

a. Atmosphere Control 

b. Thermal Control 

c. Food Management 

d. Water Management 

e. Waste Management 

f. Crew Hygiene 

The specific requirements for each of the above subsystems are given below, together, with the overall requirements for the 

complete system. 

3, 3. 2. 2. 6. 2 Atmosphere Control 

3. 3. 2. 2. 6. 2. 1 General 

The atmosphere control subsystem of the Laboratory 

shall Maintain and control the pressure, composition, temperature and 

relative humidity of the atmosphere for the pressurized section. Provision 

shall be made for operation of the pressure suits. Means shall be provided 

to recharge the portable environmental control units used in extravehicular 

activities. 

3 3. 2. 2. 6. 2. 2 Atmosphere Pressure and Composition 

The atmosphere control subsystem shall possess the 

inherent capability to operate in either a single or dual gas mode, and shall 

provide for such capability to be responsive to on-orbit decision. Operation 

of the single gas mode shall be assured by complete separability of the dilutent 

gas supply and control from the dual gas provisions. Pressure in the single gas 

mode shall be 5 psia. In the dual gas mode, pressure may be as much as 

7.5 psia.' 

3.3.2.2.6.2.3 Pressure Control 

Provisions shall be made to control the pressure and 

composition for either the single gas or dual gas operational modes. 

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• 3.3.2.2.6.2.3.1 Single Gas Pressure Control 

A pressure regulation system shall control the 

total pressure for the single gas mode. Demand pressure regulation shall 

be provided to control the specified total pressure for pressure suit operation. 

3.3.2.2.6.2.3.2 Dual Gas Pressure Control 

The dual gas pressure system shall be designed 

to preclude flooding the pressure compartments with the dilutent gas and shall 

control oxygen based on total pressure. 

3.3.2.2.6.2.4 Metabolic Gas Flux 

The baseline caloric requirement of 2800 Kcal (based 

upon a 70 kg man) and composition noted in 3.3.5.2. 6. 2 leads to oxygen consumption of 1.87 lbs/(man)(day) and CO2production of 2.32 lbs. /(man)(day). 

Variations of approximately - 10 percent about these baseline quantitites 

are permitted. 

3.3.2.2.6.2.5 Environmental Temperature and Humidity 

The average temperature for the internal wall 

pressurized volume shall not significantly exceed the internal ambient 

atmosphere temperatures, nor be less than atmosphere dew point. Operating 

temperature for the vehicle atmosphere shall be 70° 4- 5°F. Vehicle 

atmosphere humidity shall fall within the range of 50 +- 10%. The specified 

limits shall be met under the worst combination of vehicle orientation, crew 

operational mode, atmosphere operational mode and equipment operation. 

3.3.2.2.6.2.6 Atmospheric. Storage Requirements 

The atmospheric storage shall provide for the 

following requirements: 

a. Oxygen to provide for crew metabolic requirements during Laboratory pressurized section occupancy, for Gemini B 

reactivation, and for extravehicular activities. 

b. Oxygen to provide for leakage make-up for the 

Gemini B. 

c. Oxygen and dilutent to provide for leakage 

make-up of the Laboratory pressurized section, one complete repressurization 

of the pressurized Section, and a number of repressurizations of the 

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pressurized section depending on the extravehicular experiment activity. 

d. A 10% margin on oxygen and dilutent requirements, over and above those allowances made for any purge and leakage. 

3.3.2.2.6.2.7 Oxygen Storage 

Oxygen and dilutent storage shall be supercritical 

cryogenic. The storage system shall be capable of a minimum 48 hour nonvent standby time prior to launch. Design of the system shall be such that 

normal venting will not occur during orbital operation. 

A measuring system shall provide a continuous 

measurement of cryogenic quantity remaining. Accuracy of measurement 

shall be within 2% of the full scale indication. 

3.3.2.2.6.2.8 Carbon Dioxide Control 

An: .abs orbe :shall,be .used-to....reindve -carbon dioxide'. 

Ajrade study shall establish, whether it should .be regene rable 

mental control system shall maintain nominal CO .levels below .0.08 psia. 

The' maximum permissible pressure for CO2 shall be 0.15 psia. 

3.3.2.2.6.2.9 Odor and Contaminant Control 

Activated charcoal shall be utilized in series with 

the lithium hydroxide absorber to provide partial odor and tract gas control. 

A catalytic burner shall be provided for supplementary and emergency use. 

Concentration limits for a preliminary set of possible 

contaminants shall be as specified in U.S. Navy Submarine Atmosphere . 

Habitability Data Book, #250-649-1, Revision 1, Navy Bureau of Ships. 

Positive control shall be exercised to identify 

contaminants, their sources, and to minimize their introduction into the 

laboratory atmosphere. 

3.3: 2.2.6.2.10 Minimum Pressure Maintenance 

The oxygen for the pressurized volume shall be 

maintained above 3.50 psia for a minimum of 10 minutes, in the event of a 

cabin puncture equivalent to a 0.50 inch diameter hole. One compartment of 

the pressurized volume shall be capable of maintaining normal pressure in the 

event of- a cabin puncture in the other: 

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3. 3. 2. 2. 6. 2. 11 Repressurization 

Repressurization time for the complete pressurized 

volume shall not be minimized, but in no case shall exceed 1 hour. 

Repressurization time for each compartment of the pressurized volume shall 

be on a pro rata basis.. Provision shall be made for the rapid dumping of the 

atmosphere in either compartment. 

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• 3. 3.2.2.6.3 Thermal Control 

3.3.2.2.6.3.1 General 

The thermal control subsystem of the LV shall provide 

for heat transfer from the vehicle interior to the heat sink devices. Heat 

transfer shall be effected by means of air-to-liquid heat exchangers and 

cold plates, utilized in combination with a circulating heat transport fluid 

loop. Heat sink devices shall consist of a space radiator and water 

evaporator. 

3.3.2.2.6.3.2 Space Radiator 

The space radiator shall form part of the external 

vehicle surface and shall meet the meteoroid criteria. The space radiator 

shall be designed and controlled to avoid freezing of the transport fluid under 

all operational conditions, including Laboratory Vehicle pre-activation. 

3.3.2.2.6.3.3 Water Evaporator 

The fuel cell excess water and the collected 

atmospheric condensate shall be utilized with the water evaporator. The 

water evaporator shall provide for supplementary and emergency cooling 

on-orbit, and during the launch environment. This technique shall be 

used only when the expulsion of such material is not deleterious to the 

function of sensors located on the external surface of the Orbiting Vehicle. 

Consideration shall be given to minimizing disturbances of vehicle attitude 

due to the use of the water evaporator. 

3. 3. 2. 2. 6. 3. 4 Vehicle Orientation 

The thermal control system shall be capable of 

maintaining required temperature limits, with the vehicle in any, orientation, 

for approximately one hour. 

3. 3. 2. 2. 6. 3. 5 Wall Temperature 

The temperature for the internal wall of the 

pressurized volume shall not exceed 120°F nor be less than atmosphere 

dew point when subject to the worst combination of vehicle orientation, crew 

operational mode, atmosphere operational mode and equipment operation. 

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3. 3. 2. 2. 6. 4 Food Management 

The food and feeding system shall be designed to maintain 

optimal nutrition and performance of the flight crew and shall emphasize 

simiplicity, palatability and minimum interference with on-orbit duties. 

Food storage shall be at nominal cabin temperature and shall be such as to 

protect the food supply from chemical and microbial spoilage. Surplus food 

residues and containers shall be collected and processed in the waste 

management system. 

3. 3. 2. 2. 6. 5 Water Management 

Water management shall be provided for the efficient 

utilization of the water consumed and produced within the Laboratory. Vehicle. 

The on-board source of potable water shall be the fuel cell electrical power 

system. Crew metabolic requirements shall be stored in a potable water 

tank. The excess fuel water shall be stored in a waste water tank, in which 

shall also be stored the collected atmospheric condensate. Waste water 

shall be utilized for .thermal control purposes. The potable water shall be 

made available to the pressurized section at temperatures of 155°F and 

55°F. Potability measurement shall be provided. 

3. 3. 2. 2. 6. 6 Waste Management 

Waste management shall be provided for the collection, 

transfer and storage of all crew and cabin wastes. The crew waste collection 

devices shall be convenient and comfortable to use, and shall require 

minimum maintenance to avoid unsanitary conditions. The pressurized 

section atmosphere shall not be contaminated by the use of these devices 

and any atmosphere used in the crew waste collection process shall be 

decontaminated before return. Containers impermeable to solids, liquids, 

gases and bacteria shall be provided for waste storage. Proper purification 

control of collected waste shall be effected.. 

Provisions shall be made for the management of daily 

urine volumes of 1800 + 700 ml per man to be collected as a total daily 

specimen. This volume (less a.50 ml aliquot for physiological tests) is to 

be delivered to and managed by the urine disposal system. 

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The daily fecal volumes of approximately 30 + 30 ml shall 

be collected in a special bag for subsequent lyophilization. 

3.3.2.2.6.7 Crew Hygiene 

Solid debris, such as hair, nails, stuffings, food particles, 

etc. , shall be trapped and processed into the waste management system. 

3.3.2.2.6.8 Overall System Requirements 

3.3.2.2.6.8.1 Prelaunch Operation 

During the prelaunch phase, the system shall have 

checkout capability to verify required performance and operational parameters. 

Atmospheric conditioning of the pressurized volume shall be effected by 

purging and filling with the specified atmospheric composition at in excess 

of sea-level pressure. Ground cooling of the Laboratory shall be provided. 

3.3.2.2.6.8.2 Launch Operation 

During the launch phase, the system shall have the • capability to furnish operational status determination via telemetry. The 

atmosphere of the pressurized section shall be relieved during ascent to 

maintain a pressure differential comparable to the specified orbital 

requirement. Cooling of the Laboratory Vehicle during ascent shall be 

provided by a water evaporator. 

3.3.2.2.6.8.3 Monitoring and Control 

Monitoring of the system shall be provided to furnish 

performance status and diagnostic data for on-orbit and ground control 

requirements. Control of the system shall be on-board. 

3.3.2.2.6.8.4 Safety Features 

All valves that connect the interior of the pressurized 

section to the space environment shall have manual closures and/or overides. 

Filters shall be provided to protect critical components such as pumps and 

compressors. Relief shall be provided to prevent overpressurization. Flow 

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3. 3. 2. 2. 7 Orbital Attitude Maneuvering System {DAMS) 

3. 3. 2/. 2. 7. 1 General 

This system shall control the vehicle attitude and provide translational velocity change capability while on-orbit. An on-off reaction jet attitude 

control system located in the Laboratory shall control the vehicle attitude and 

generate small velocity changes. The transtage main propulsion system shall 

be utilized, in conjunction with the control electronics located in the Laboratory, 

for large velocity changes. 

3. 3. 2. 2. 7. 1. 1 Operating Requirements 

The control system shall be capable of continuous operation in any,of the operating modes specified below for the entire mission. The 

translational modes must be available at any time during the mission. 

3. 3. 2. 2. 7. 1. 2 Limit Cycle Dead Band 

A fine limit cycle dead band of ± 0.2 degree and a coarse 

dead-band of - 3. 0 degree shall be provided. 

• 3. 3. 2. 2. 7. 1. 3 Body Rates 

Body axis rates shall be maintained below 0. 01 degree/ 

second during limit cycle operation. Vehicle attitude accuracy and translational requirements are presented below, 

3. 3. 2. 2. 7. 2 Operating Modes 

The following operating modes are required to provide automatic and manual attitude hold and maneuver capabilities, and translational 

acceleration to meet the MOL mission requirements. 

3. 3. 2. 2. 7. 2. 1 Horizon Scan Local Vertical 

In this mode the vehicle attitude shall be automatically 

maintained with the longitudinal axis normal to the local vertical and in the 

orbit plan to within 0.4 degree about the local vertical and O. 7 degree about 

the orbit plane. 

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Displays of attitude errors relative to the reference 

• system and body axis rates shall be available. 

3. 3. 2. 2. 7. 2. 2 Rate Stabilization 

The Rate Stabilization mode shall be used for manual 

maneuvers and for short term attitude hold. Maneuver rates shall be 

available up ,to 5. 0 deg/sec. 

The displays shall provide three Euler angles, which 

locate the body axis coordinate system relative to the local vertical and orbit 

plane (or to an alternate attitude to which, the body axis reference system has 

been aligned). The body axis rates and attitude errors shall also be displayed. 

The desired- Euler angles (relative to the local vertical reference system) will 

be inserted into the control system by the astronaut. 

3. 3. 2. 2. 7. 2. 3 Attitude Hold 

Automatic attitude hold and maneuver shall be provided 

in this mode. Automatic maneuver rates shall be available. 

3. 3. 2. 2. 7. 2. 4 Minimum Impulse 

This mode will be used .by the astronaut to provide 

precise open-loop ,attitude control. The attitude and rate accuracy shall be 

limited only.by the fuel consumption and the minimum rate achievable from 

the reaction control system. 

External-visual or attitude control system displays 

shall be used as the attitude reference in this mode. 

Display requirements are identical to those of the Rate 

Stabilization mode. 

3. 3. 2. 2. 7. 2. 5 Direct Control 

This mode will be used as a back-up in case of control 

system failures or where high maneuver rates are required. The reaction 

jets shall be controlled directly by the astronaut through a minimum amount 

of electronics to provide high reliability. 

The attitude reference in this mode shall be externalvisual or attitude control displays. 

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Display requirements are the same as those of the Rate 

Stabilization mode. 

3. 3. 2. 2. 7. 2. 6 Transtage Velocity Increment 

Control of the transtage main propulsion system.ignition 

and thrust termination shall be provided. The vehicle attitude shall be controlled through the use of the transtage main engine gimbal system while thrusting, 

and in the Attitude Hold mode before and after thrusting. The astronaut will 

be required to insert initial gimbal angles and Lv requirements into the 

control system. 

The transtage gimbal angles and the velocity-to-be 

gained shall be displayed to the astronaut. 

3. 3. 2. 2. 7. 2. 7 Transtage Ullage 

The mode provides the propellant settling for the main 

engine in the transtage. The astronaut will control this mode through the A V 

display panel. 

3. 3. 2. 2. 7. 2. 8 Translation Control 

The reaction jet system will be required to supply small 

velocity changes in six direction parallel to the vehicle control axes. Acceleration greater than 0.05 ft/sec2 shall be required. Translational control shall 

be manual and the Attitude Hold mode will be utilized to maintain vehicle 

attitude. 

3. 3. 2. 2. 7. 3 Control Electronics 

3. 3. 2. 2. 7. 3. 1 Reference System 

This system shall contain .the horizon sensors, integrating gyros, rate gyros, accelerometer, and Euler Angle Computer (EAC). 

3. 3. 2. 2. 7. 3. 2 Displays 

The displays shall include mode select, Euler angle 

set, deadband control, velocity control and reaction jet control panels.. Euler 

angles, body axis rates and attitude errors shall also be displayed. • 

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The mode select panel will allow any of the control 

system operating modes to be selected and indicate which mode •is currently 

operating. 

The Euler angle set panel shall permit the astronaut 

to insert the three Euler angles aryl the maneuver rate, as well as displaying 

the currently set valves. 

Find and coarse deadband .selection and the magnitude 

of the coarse deadband shall be controlled through the deadband control panel. 

The velocity-to-be-gained shall be set in the velocity 

control panel, as well as the initial Transtage gimbal angles required to align 

the thrust vector through the vehicle center of mass. 

The reaction jet control panel shall contain the malfunction detection system displays and the switching associated with the 

reaction jet system. 

The Euler angles, body axis rates and attitude errors 

shall be displayed in a manner which is most efficient for the astronaut. 

3. 3. 2. 2. 7. 4 Propulsion System 

The reaction jet propulsion subsystem consists of thrust 

chamber assemblies, mounted to give vehicle rotation and translation, and a 

propellant supply and distribution system. This subsystem responds to 

actuation commande from the control electronics. Redundancy shall be 

provided for jet or jet module failure. 

.3. 3. 2. 2. 7. 4. 1 Life 

The Subsystem must be capable of a minimum of 3000 

sec. operation at any time during the thirty-day on-orbit life of the orbiting 

vehicle system. Time periods of acceptance testing, pre-launch testing 

(e. g. on-pad checkout and loading) and all other durations of subsystem 

operation shall be considered in the total subsystem life. 

3. 3. 2. 2. 7. 4. 2 Thermal Considerations 

The subsystem design shall be consistent with requirements for temperature conditioning of the propellants and other components 

necessary to maintain subsystem or vehicle components within their operating 

• temperature range. 

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High and low temperature strength along with thermal 

shock properties shall be considered in the choice of thrust chamber 

materials. The temperature encountered should range from space temperatures to the combustion temperature of the propellant(s). 

3. 3. 2. 2. 7.4. 3 Minimum Impulse Bit 

The engine shall deliver a minimum impulse bit of 

less than 0.25 lb. sec. This minimum shall not vary by more than ±-0. 05 

lb. sec. The minimum impulse bit is defined as the area under the thrust 

time curve including buildup and decay transients. 

3. 3. 2. 2. 7.4, 4 ,Specific Impulse 

Steady state (pulses greater than 1.0 sec. ) specific 

impulse shall not be less than 250 seconds. Specific impulse for the minimum 

impulse bit shall not be less than 100 seconds. Specific impulse at small pulse 

widths (less than 1. 0 sec) is defined as the impulse bit (lb. sec. ) divided by 

the weight of propellant consumed per pulse (lb. ). 

3. 3. 2. 2. 7. 4. 5 Duty Cycle 

The duty cycle will be composed mainly of: 

a. Limit cycles which require short on 

periods (>0. 020 sec. ) 

b. Roll maneuvers which require on periods of 

approximately one to ten seconds at intervals 

of approximately sixty seconds. 

c. Translation maneuvers which require on 

periods of approximately five to ninety 

seconds at intervals of approximately five 

to two hundred seconds. 

3. 3. 2. 2. 7. 4. 6 Impulse Capability 

The stored impulse capability of the subsystem shall 

be determined from the requirements. Consideration shall be given to expulsion efficiency, leakage, and off-performance operation. 

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3. 3. 2. 2. 7.4. 7 Propellant Gaging 

The subsystem shall include a method to measure and 

display to the astronaut the amount of propellant remaining in the subsystem. 

3. 3. 2. 2. 7. 4. 8 Leakage and Permeation 

Subsystem design shall include considerations to 

eliminate or minimize the leakage and/or permeation of fluid to other parts 

of the subsystem or to enclosed compartments, modules or sections of the 

Orbiting Vehicle. 

3. 3. 2. 2. 7. 4. 9 Propellants 

The propellants shall by hypergolic bipropellants which 

are space storable and shall be selected considering thermal environment and 

minimization of ignition over-pressure transients. 

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3. 3. 2. 2. 8 Electrical Power Supply 

3. 3. 2. 2. 8. 1 General Requirements 

The Laboratory Vehicle Central Power System (CPS) shall 

provide the total laboratory subsystem power during launch and injection, lab 

activation, on-orbit, and emergency mission phases. 

3. 3. 2. 2. 8. 1. 1 Type of Power Source 

The generation of primary electrical power for the Lab 

CPS shall be accomplished with H2 -02fuel cell modules arranged in parallel, 

with automatic and manually actuated interconnections. 

3. 3. 2. 2. 8. 1. 2 Nominal Power 

The Lab CPS shall be a nominal 28 volt dc power system 

utilizing established design practices for subsystem compatibility. 

3. 3. 2. 2. 8. 1. 3 Overloads 

During the 30-day on-orbit phase the Lab CPS shall accommodate transients, intermittent peaks of 3. 6kw and shall remain within its 

performance specification. The maximum to average and maximum to minimum 

• power ratios imposed upon the CPS are nominally 2:1 and 4:1 respectively. 

3. 3. 2. Z. 8. 2 Specific Requirements 

3. 3. 2. 2. 8. 2. 1 Location 

The fuel cell powerplant shall be located in the unpressurized compartment of the Laboratory Vehicle. 

3. 3. 2. 2. 8, 2. 2 Life 

The fuel cell powerplant shall have a minimum life 

capability of 1, 000 hours and during this life shall remain within its performance specifications while providing the Laboratory CPS power requirements. 

3. 3. 2. 2. 8. 2. 3 Fuel Cell Standby Capability 

The Lab CPS shall have a minimum fuel cell 28 volt 

module standby capability of 40% of the modular configuration; The standby 

modules may be utilized from either a cold or operating status. 

3.3. 2. 2. 8. 2. 4 Parasitic Power 

Parasitic power generated and required by the fuel 

cell powerplant may be delivered to the main dc bus, but it shall not be 

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• included as part of the 1. 8 kw average power required to be delivered by 

the powerplant for the Lab CPS loads. 

3. 3, 2. 2. 8. 2. 5 Emergency Power 

Emergency battery power shall be readily available 

and capable of maintaining emergency load conditions of 1 kw for a duration 

adequate to determine criticality of malfunction, ground mission control 

center coordination, remedial action, or return to Gemini B. 

3. 3. 2. 2. 8..2. 6 Voltage 

During the mission phases, and for all combinations_ of 

loading within the mission power profile, including emergencies, the powerplant shall maintain 25 - 30 volts at the bus. 

3. 3. 2. 2. 8. 2. 7 Specific Reactant Consumption 

The total quantity of reactants including purge requirements needed by the fuel cell powerplant to provide the required electrical 

power for the mission duration shall be no greater than 0. 95 pounds per net 

kilowatt-hour. • 3. 3. 2. 2. 8. 2. 8 Water Removal 

The water transport system shall remove the product 

water from the fuel cell. The water shall be delivered to the life support 

interface as potable for human consumption. 

3. 3. 2. 2. 8. 2. 9 Waste Heat 

The waste heat generated by the fuel cells shall be 

removed by a coolant circulated through each fuel cell module. The coolant 

system shall be integrated with the EC/LS system and dissipate its accumulated 

heat through an external space radiator located on the surface of the Laboratory. 

3. 3. 2.2. 8. 2. 10 Power Source Failure 

Power distribution from the fuel cell modules shall 

be designedso that the failure of any module or modules does not adversely 

affect the operation of the remaining modules. Switch-out of the failed 

modules, loading of the stand-by modules, or start up of the redundant modules 

shall be automatically controlled with a remote manual override capability. 

individual control of each module shall also allow selective grouping of any • combination of fuel cell modules. 

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3. 3. 2. 2. 8. 3 Power Control and Monitoring 

Provisions shall be incorporated within the Laboratory for 

Monitoring and managing the CPS. Visual indications of electrical system 

events, conditions, outputs, and malfunctions shall be provided. 

The power control unit shall provide a distribution point 

for the major electrical power within the Lab, , a switching capability, circuit 

access for ground maintenance, and fault isolation and protection. • 

3. 3. 2. 2. 8. 4 Power Conditioning 

All laboratory equipment and experiments requiring power 

outside the characteristics of the fuel cell power- plant shall provide individual 

power conditioning equipment operated from the main bus. 

3. 3. 2. 2. 8. 5 Reactant Supply System 

The reactant supply shall be provided from a supercritical 

cryogenic storage system. A minimum of two tanks each shall be provided 

for the hydrogen and oxygen storage. 

3. 3. 2. 2. 8. 5. 1 Capacity 

The cryogenic storage system shall have adequate 

capacity to supply all of the reactants for the fuel cell power system to 

accomplish the 30-day on-orbit mission, plus 3 day margin, at an average 

net power level of 1. 8kw. 

3. 3. 2. 2. 8. 5. 2 Pressurization 

The cryogenic storage system shall be capable of a 

minimum 48 hour non-vent standby time prior to launch. Design of the 

tankage system shall be such that venting will not occur during normal 

orbital operation. The heater duty cycle shall be minimized by utilizing 

excess heat from the Environmental Control System. An electridal 

resistance heater shall be included to provide additional heat for presurization 

during initial pressurization or periods of high fluid withdrawal. 

3. 3. 2. 2. 8. 5. 3 Quantity Measurements 

A quantity measuring system shall provide a continuous 

measurement of cryogenic quantity remaining. Accuracy of measurement 

shall be within 2 percent of the full scale indication. • 

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3. 3. 2. 2. 8. 6 Mission Phase Requirements 

During the pre-launch phase the CPS shall have a check-out 

capability, so that performance parameters may be verified prior to launch. 

Performance parameters of the other Lab sub systems are also excercised, 

and the CPS shall sustain their launch mode power requirements upon transfer 

to internal power. 

During the launch and ascent phase, monitoring of the CPS 

shall be provided. 

3. 3. 2. 2. 8. 7 Laboratory Vehicle Equipment Power Requirements 

3. 3. 2. 2. 8. 7.1 Equipment Operating Voltage 

Laboratory equipment shall give specified performance 

when operated with 23 - 31 volts at the equipment power terminals. 

3. 3. 2. 2. 8. 7. 2 Under and Over-Voltage 

Laboratory equipment shall withstand, without damage, 

voltages from 21 - 34 volts at its power terminal s and shall immediately give 

specified performance upon return to the equipment operating voltage. 

3. 3. 2. 2. 8. 7. 3 Transients 

Laboratory ?quipment shall be capable of withstanding 

transients of - 100 volts with respect to nominal bus voltage for durations up 

to 20 microseconds. 

3. 3. 2. 2. 8. 7. 4 Electromagnetic Interference 

Electromagnetic Interference (EMI) of the Laboratory 

Vehicle shall be minimized consistent with weight and performance constraints. 

The subsystems shall neither generate excessive interference, nor shall 

they be excessively susceptible to radiated and conducted noise. 

3. 3. 2. 2. 8. 7. 5 Grounding 

The Lab CPS shall incorporate a single point ground 

system, compatible grounding network with the Gemini B launch vehicle, 

and Experiments. 

w 

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3.3.2.2.9 Structural Subsystem 

3.3.2.2. 9. 1 Design Environment Criteria 

The environmental criteria applicable to the Laboratory 

Vehicle structure are specified in SSD Exhibit 64- 

3.3.2.2.9.2 Structural Design Criteria 

The structural design criteria applicable to the Laboratory 

Vehicle are specified in SSD Exhibit 64- 

3.3.2.2.9.3 Limit Load 

Limit load is the maximum anticipated load, or combination 

of loads, which a structure may be expected to experience during the performance of specified missions in specified environments. 

The structure shall be designed to have sufficient strength 

to withstand simultaneously the limit loads, applied temperature and other 

accompanying environmental phenomena for each design condition without 

experiencing excessive elastic or plastic deformation. 

• 

a. 

3.3.2.2.9.4 Factors of Safety 

Flight Loads 

Limit Proof Ultimate Burst 

b. 

Manned Payloads 

Non-Flight Loads 

1.00 1.40 

(Other than Pressure 

Dangerous to Personnel 1.00 1.50 

c. 

Remote to Personnel 

Pressure Loads 

1.00 1.25 

Main Propellant Tanks 1.00 * 1.40 1.40 

Rocket Motor Cases 1.00 -4: 1.25 1.40 

Pneumatic Vessels 1.00 1.67 2.22 2.22 

(Including Accumulators 

and Pressurization 

Bottles) 

Manned Cabins 1.00 1.33 2.00 2.00 • - 83 - 
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3.3.2.2.9,4 Factors of Safety (Cont' d) 

Limit Proof Ultimate Burst 

Hydraulic Vessels 1.00 2.00 4.00 . 4.00 

(Including Assumulators 

and Pressurization 

Bottles) 

Hydraulic Vessels 1.00 1.50 2.00 2.00 

(Normally Under Oil 

Pressure Only) 

Hydraulic and Pneumatic 1.00 2.00 4.00 4.00 

(Lines, Fittings and 

Hoses) 

Main Propellant 1.00 1.50 1.88 1.88 

(Supply and Vent 

Components 

3.3.2.2.9.5 'Strength and Stiffness 

3.3.2.2.9.5.1 Structural failure shall not be precipitated at loads 

less than iultimate. 

3.3.2.1.9.5.2 The structure shall not experience deformations 

which impair functional performance at limit loads. 

3.3.2.2.9.5.3 The structure shall not experience deformations 

which impair peformance of function at loads less than limits. 

3.3.2.2.9.5.4 Structural deformations shall not precipitate 

structural failure at loads less than ultimate. 

3.3.2.2.9.5.5 Flutter or other dynamic instability shall not occur 

on the Vehicle at any condition within the design envelope. 

3.3.2.2.9.5,. 6 Structural materials utilized in the pressurized areas 

shall possess demonstrated crack resistance under the specified environments and operations, and shall be of conventional types. 

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3. 3. 2. 2. 10 Crew Accommodations 

3. 3. 2. 2. 10. 1 Furnishings and Equipment 

The pressurized section shall provide furnishings and equipments in functional groups for maximum efficiency and crew safety. 

3. 3. 2. 2. 10.2 Restraints 

Restraint devices shall be incorporated to facilitate safe and 

efficient crew movement and performance of tasks. 

3.3.2.2.10.3 Safety Devices 

Safety guards, safety shields, and locking devices shall be 

provided on or over appropriate rotating machinery, controls, and display faces. 

The interior of the laboratory shall be designed to contain 

collision protection on such furnishings and equipments where injury to crew 

could result from motion of the laboratory or crew activity. 

• 3. 3. 2. 2. 10. 4 Crew Transfer Provisions 

3. 3. 2. 2. 10. 4. 1 Normal Transfer 

The Laboratory Vehicle shall provide umbilical connections required for life support and communications under normal crew 

transfer operations. Such provisions shall be located in the immediate 

vicinity of ingress to the laboratory pressurized compartment. 

3.3.2.2.10.4.2 Emergencies 

Provisions shall be made for the storage of emergency 

transfer equipment, to be located adjacent to an extravehicular hatch. Such 

provisions shall consist of portable emergency oxygen packs, extravehicular 

restraint devices, and portable lamps. 

3. 3. 2. 2. 10. 5 Hatches 

Pressure tight hatches, capable of actuation from either 

side, shall be provided, at all ingress/egress portholes in the laboratory 

pressurized compartments. 

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3.3.2.2.10.6 Windows 

Viewing windows, as appropriate, shall be provided in the 

laboratory pressurized compartment to permit earth and star field viewing 

by the crew. Provisions shall be included for manual control of solar radiation 

and direct light emission through window areas. 

3.3.2.2.10.7 Gravity Countermeasures 

The MOL system configuration shall have the capability, 

without major changes, of providing for local countermeasures to the effects 

of zero gravity. These provisions shall include sufficient space for possible 

installation of an internal centrifuge. 

3.3.2.2.10.8 Experiment Provisions 

Installation space shall be provided in the Laboratory 

Vehicle which is compatible with the Experiment equipment requirements. The 

space allocated shall permit installation of support brackets, signal and power 

conductors, and coolant lines to any set of. Experiment equipments, as required. 

• 3.3.2.2.10. 9 Laboratory Peculiar AGE 

The Lab Segment peculiar AGE shall consist of Operating 

Ground Equipment and Maintenance Ground Equipment designed to support all

Lab Segment operations from after final acceptance at the contractor's facility through launch. This Laboratory peculiar equipment shall be designed for 

operability, maintainability and reliability per the requirements generated by 

this specification. Maximum utilization shall be made of existing equipment. 

The Laboratory Segment peculiar Operatin.g Ground Equipment at the Launch 

Pad shall be designed for inclusion in one GFE railroad adapted 40' x 10' van, 

to be shared with the Experiment Segments Operating Ground Equipment. Payload Control Room No. 2 in the VIE shall be utilized jointly by the Laboratory 

Segment Operating Ground Equipment, and the Experiment Segments Operating 

Ground Equipment. Data transmitted between the Laboratory and its Operating 

Ground Equipment, shall consist of signals compatible with the Data Transmission System of the ITL System. The Laboratory AGE utilized at ETR shall 

be functionally identical to the AGE utilized during factory acceptance of the 

Laboratory. 

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3.3.2.2.10.9.1 Performance 

The Laboratory Segment peculiar AGE shall include 

all the equipment necessary to transport, handle, store, verify, calibrate, 

checkout, monitor, record, and service the Laboratory Vehicle. This AGE 

shall be capable of providing a means of verifying the proper operation of 

the Laboratory Vehicle and identifying areas of failure or operation outside 

the prescribed limits. This AGE shall be capable of integration with the 

complete MOL system AGE at CKAFS. Fault isolation equipment at the 

launch site will be limited to that equipment necessary to, isolate faults to the 

black box or replaceable component level. Detailed fault isolation and 

failure analysis within black boxes and/or components will be conducted at 

contractor/subcontractor plants and/or at AF depots. 

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• 3. 3. 3 Gemini B System Segment 

The. Gemini B is .a modified NASA Gemini spacecraft consisting, of a 

. .re-entry. module, an adapter section, a crew escape system and the supporting 

ground_system. The spacecraft shall be capable of performing 30 .day earth 

orbital flights as an integral part of the orbiting vehicle and shall be capable 

of controlled earth orbit, re-entry and water landing as .an Autonomous spacecraft. The spacecraft shall be dependent on other system segments for performance of certain functions; the extent of this dependency upon other segments shall be- as specified herein and in other appropriate documentation. 

3. 3. 3. 1 •Allocated Performance and Design Requirements 

3. 3. 3. I . 1 Weights 

Nominal design launch weight of the Gemini B, including the 

complete re-entry module, the adapter section, escape system, crew, and 

flight equipment shall be 6300 pounds. This weight is distributed as follows: 

Re-entry Module 

Adapter Section 

4750 pounds 

1. 550 pounds 

A more detailed presentation of weight ranges associated with each phase of 

flight, to be used for analysis purposes, is given in the appropriate supporting documents. 

3. 3. 3. 1. 2 Electrical Power 

Electrical power for the Gemini B during the phases of flight 

of launch, on-orbit prior to crew transfer to the Laboratory Vehicle, post 

separation, de-orbit and re-entry shall be provided by Gemini. B systems. 

The Laboratory Vehicle shall supply the power for the on-orbit storage phase 

and the power prior to launch shall be supplied by AGE. 

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3. 3. 3. 1. 3 Effectiveness 

Data, shall be furnished to support a detailed apportionment of 

effectiveness to the Gemini 8 System Segment. A plan shall be developed to 

show how substantial compliance of this effectiveness allocation will be demonstrated prior to acceptance and how actual compliance to this effectiveness 

allocation is judged during each mission. 

• 

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3. 3. 3. 1..4 Crew Stay.Time 

The maximum total time the crew will be required to stay in 

the Gemini B is. 60 hours. This maximum crew .stay time is allocated to the 

mission. phases as follows: 

Pre-launch 5 hours 

Launch, until crew transfer 8 hours 

On-orbit, pre-separation 9. hours 

On-orbit, post-separation 14 hours 

(includes loiter time) 

Re-entry 1 hour 

Post-landing 36 hours 

. 3. 3. 3. 1. 5 Leak_Rate 

The Gemini B re-entry module leak rate, including the crew 

transfer tunnel, shall not exceed 2. 5 lbs/day. These leak rates are for a 

pressurization of 5.0 psi under orbit environmental conditions. • 

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3. 2 Peculiar. Performance and Design Requirements 

3. 3. 2.1 Spacecraft Requirements 

3. 3. 3. 2. 1. 1 General 

The design of the Gemini B shall be based on a service life 

of one mission. 

3. 3. 3. 2 I. 2 Re-entry Module 

The Gemini B re-entry module shall consist of a modified 

Gemini A re-entry module. This module shall provide protection for the crew 

from the environment of launch, space, re-entry and landing. Provisions shall 

be included for mounting and protecting the equipment necessary for meeting . 

the requirements .of the subsequent paragraphs. Capability shall be provided 

for -return. of experimental data. 

3. 3. 3. 2.1. 3 Adapter Section 

The conical adapter section shall consist of the structure 

required to transition from, the re-entry module to the. 120" diameter Laboratory Vehicle. The crew transfer tunnel shall be inCluded as part-of the ,adapter 

section. The tunnel attachment to the laboratory shall be .a rigid seal. The 

Gemini B shall have the capability of separating from the Laboratory at the 

Laboratory/Gemini B retrograde adapter separation plane. The Gemini B 

shall also have the capability of separating the re-entry module from the retrograde .adapter section. 

3. 3. 3. 2.1.4 Strength and. Rigidity 

The structure of the Gemini B shall be capable of sustain-. 

ing all loads and environments imposed during the MOL mission of ground 

handling and transportation, pre-launch, launch, on-orbit, retrograde, reentry, landing, and recovery. 

3. 3. 3. 2.1. 5 Aerothermodynarnic 

The re-entry module center of gravity shall be located so 

that the re-entry module trims at an angle of attack capable of producing more 

than .40 nautical miles crossrange and 400 n. mi. along the ground track. The 

maximum deceleration experienced by the crew during normal guided re-entry 

shall not exceed .10 g. 

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3. 3. 3. 2. 2 Guidance and. Control Requirements 

3. 3. 3. 2. 2. 1 General 

The Gemini B shall have the capability for re-entry control 

recovery of 8 nautical miles (3 dispersions) at 70,000 feet altitude. This 

control shall be obtained .by employing re-entry module atmospheric.maneuvers. 

3. 3. 3. 2. 2. 2 Re-entry Guidance and Control 

A guidance .capability shall be included to provide spacecraft 

attitude .reference in all attitudes about three .axes, control touchdown..points 

for normal and aborted missions, maneuver control logic_ required for re-entry 

touchdown control, and control function outputs. to applicable systems. An 

attitude control capability consistent with the guidance accuracy requirement 

shall. beprovided. This capability shall provide automatic attitude and attitude 

rate control signals, .automatic response to manually initiated inputs for attitude 

and the means for manual control of spacecraft attitude propulsion systems. 

Provisions shall be made for visual horizon reference during retrofire for all 

de-boost‘design altitudes by at least one crew member. 

3.3. 3. 2. 2..3 On-orbit Post Separation Control 

The capability shall be provided for both manual and automatic control of spacecraft attitude during on-orbit periods following separation from the Laboratory Vehicle. 

3. 3, 3: 2. 3 Instrumentation.Requirements 

. . The Gemini. B shall have the capability to sense, • condition..and 

. provide data appropriate to the particular flight phase. The instrumentation:of 

the Gemini B shall provide capability to. monitor critical spacecraft and launch 

vehicle- events , critical launch, vehicle parameters,.spacecraft system status 

and. certain critical laboratory status items during .all mission phases. 

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• 3. 3. 3.2. 4 Environmental Control Re uirements 

3. 3; 3; 2. 4.1 General 

The Gemini B shall provide the environmental control and 

life support for the crew members until crew transfer. The Gemini B shall 

again provide environmental control and life support for the, crew members 

after. the Gemini B is reactivated for mission termination. 

.• "..'• ' 

3. 3. 3. 2. 4. 2 Cabin Environmental Control 

The capability shall be provided for complete environmental 

life support while the spacecraft is manned. The crew pressure suits shall be 

considered .as an emergency backup capability for this phase. A potable water 

supply and a method for handling urine shall be provided. The cabin temperature shall be maintained within a range of 60°F. to 95°F. while occupied onorbit; diiring re-entry, the tempe rature shall not exceed 200°F. 

3. 3. 3. Z. 4. 3 Suit Environmental Control 

Metabolic oxygen, pressurization and ventilation shall be 

provided for the pressure suits. Individual oxygen supplies shall be provided 

for each creW-Inember for emergency use during high altitude seat ejection. 

The. capability shall be provided to allow the crew to perform the necessary 

operational functions in a closed loop suit with the cabin either 'pressurized 

:or depressurized. 

3. 3. 3. 2. 4. 4 Equipment Environmental Control 

Provisions shall be included for maintaining the Gemini B 

equipment within .the required temperature range for both operating. conditions 

and Ori-orbit dormant storage conditions. 

3. 3. 3. 2. 4. 5 Crew Transfer Environmental Control 

The Gemini B ECS will supply ventilation, breathing oxygen, 

-and emergency pressurization (if required) during transfer to the Laboratory. 

This same function shall be performed by the Laboratory ECS during transfer 

to the Gemini B. 

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• 3. 3. 2. 5 Prqpulsion Requirements 

3. 3, 3. 2. 5.1 General 

Sufficient propulsive capability shall be provided to permit 

attitude control of the Gemini B, separation of the Gemini B from the. Laboratory Vehicle and application of de-orbit velocity increment.. 

3. 3. 3. 2. 5. 2 Re..entry'Control 

The reentry control system shall provide control required 

to achieve,the required touch down accuracy, structural/temperature constraints 

and crew load factor constraints. 

3. 3. 3. 2. 5. 3 On-Orbit Post Separation Control 

Propulsive capability shall be provided for control of the 

attitude and attitude rates of the Gemini B for on-orbit loiter up to 14 hours 

after separation from the Laboratory Vehicle prior to de-orbit. 

3. 3. 3. 2. 5. 4 Launch Abort Separation 

Abort modes using the Gemini re-entry module shall use the 

retrograde propulsion to produce separation. In other modes the ejection seats 

shall be used. Provision for a shut-down signal to the Titan III from Gemini B 

shall be provided. 

3. 3. 3. 2. 5. 5 On-Orbit,Separation 

A propulsive capability shall be provided to separate the 

Gemini' B from the Laboratory Vehicle on-orbit. The separation propulsion 

shall not impose -detrimental effects on the Laboratory Vehicle. Sufficient 

. separation distance shall be developed to preclude imposing detrimental effects 

on the Laboratory Vehicle by the operation of the retrograde motors. The 

Gemini B shall be capable.of discarding the transtage when desired. 

3. 3. 3. 2. 5. 6 Retrograde 

The capability shall be provided of imparting the necessary 

retrograde impulse to the re-entry module for reentry from 16- n. mi. design 

orbit altitudes. The retrograde impulse timing, orientation and magnitude shall 

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• provide re-entry conditions which, considering all dispersions and re-entry 

bank angle.comrnand schedules, will not produce structural temperatures 

greater. than the design values at any time during re-entry or at water impact. 

3. 3. 3. 2. 6 Electrical Power Requirements 

3. 3. 3. 2. 6. 1 General 

The capability for supplying Gemini B electrical. power for 

the pre-launch,. launch, pre-laboratory activation on-orbit, post-separation, 

.de-orbit, re-entry and post landing phases shall be provided. Provisions 

shall be made .for utiliza.tion of ground power prior to pre-launch and for all 

ground checkout. Provisions shall be made for the ,Laboratory Vehicle to. 

supply power on orbit during Gemini B dormancy. 

3. 3. 3. 2.6.2Electrical Power Supply 

Electrical power supply shall consist of a D. C. power 

source, A. C. power, as required by specific systems, shall be supplied 

by inverters and regulators considered a part of the utilizing system. There 

shall be redundancy in .all power. sources. Re-entry power. sources must be 

active during the launch phase for abort purposes. Independent and redundant 

power sources shall be provided for pyrotechnic circuits. 

3. I. 3. 2. 6. 3 Electrical Power Distribution 

A capability for distributing the electrical power from the 

power supply to the using system shall be provided. The spacecraft.structure 

shall not be used as an electrical current path. The system negative shall be 

grounded at one point only in the spacecraft. A compatible grounding network 

between Gemini B, Laboratory, and Titan IIIC shall be designed to maintain 

this concept. 

3. S. 2. 6. 4 EMI 

Electromagnetic Interference (EMI) of the Gemini B Shall be 

minimized consistent with weight and performance constraints. The subsystems 

shall neither generate excessive interference, nor shall they be excessively 

susceptible to radiated and conducted noise. 

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• 3. 3.. 3. 2..7 Time Reference Requirements 

3. 3. 3. 2. 7. 1 Babic Time Reference 

An electronic capability shall be provided to furnish accurate accounting of elapsed time or time-to-go for the following types of events: 

during ascent; time-to-go retrofire; time-to-go to start of reentry; etc. A 

reset capability shall be included. 

3. 3. 3. 2. 7. 2 Event Timer 

A capability for providing short-term timing of functions 

shall be provided. 

3. 3. 3. 2. 8 Pyrotechnic Requirements 

3. 3. 3. 2. 8. 1 General 

The Gemini B shall have the capability for actuating, 

severing, separating, deploying, etc. , by utilizing pyrotechnic devices. 

3. 3. 3. 2. 8. 2 Safety 

Actuation .of pyrotechnic devices, shall not endanger the 

crew or damage adjacent systems. Installation of pyrotechnic devices shall 

be so designed that the hazard to launch crews is minimized during assembly 

and checkout of the Gemini B. 

3. 3. 3. 2. 8. 3 Reliability 

Al].functions requiring the use of pyrotechnic devices 

shall utilize either redundant devices or have an alternate mode of operation. 

3. 3. 3. 2. 9 Landing Requirements 

'3; 3. 3. ?. 9. 1 General 

The Gemini B re-entry module shall have the capability of 

return to earth's surface by deployment of recovery System after satisfactory 

retrograde and re-entry. Initiation of the landing system shall be manual with 

automatic backup. The capability shall be provided for seat ejection to permit 

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3. 3. 3. 2. 9. 2 Descent and Impact 

The rate of descent of the re-entry module shall be 30 

- 2 fps at sea level for a weight of 4400 pounds. 

The water and sea state impact loads on the re-entry 

module shall not exceed the deceleration levels in the following directions: 

Forward 30 g 

Aft 30 g 

Up II g 

Down 15 g 

Left 11 g 

Right 11 g 

•3. 3. 3. 2.10 Post Landing and Survival Requirements 

3. 3. 3.2.10.1 Location 

The means for location of the re-entry module and the 

crew members after landing shall be provided. This location and capability 

shall include visual devices for both day and night operation as well as HF 

and UHF capability. Location aids in the re-entry module shall be operable 

for a post landing period of 36 hours. 

3. 3. 3. 2.10. 2 Crew Safety 

Sufficient food and potable water shall be provided for 

a post landing, period of 48 hours. Equipment to permit crew survival outside the re-entry module either on water or land shall be provided. 

3. 3. 3.2. 11 Back-up Crew Transfer Requirements 

Back-up transfer shall be extravehicular via the regular 

Gemini,B hatches. These hatches shall remain closed after transfer of the 

last crewman. Provisions shall be made for opening and closing the hatches 

from inside and outside Gemini B while in a pressurized suit. 

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. 3. 3. 3. 2.12 Crew Equipment and Display Requirements 

3. 3. 3.2.12.1 General 

The design and arrangement of the crew station 

shall be based on seating two crew members of the 15th through the 75th 

percentile man size as defined in WADC TR 52-321 "Anthropometry of 

Flying Personnel, 1950", dated September 1954, in a side by side 

arrangement. The crew members shall be clothed in pressure suits. 

3. 3. 3. 2. 12. 2 Displays and Controls 

Provisions shall be included to allow the crew 

members to monitor and manually control desired functions; these 

provisions shall permit the crew members to be in either a pressurized 

or unpressurized suit. 

• 

3. 3. 3. 2. 12. 3 Crew Seating 

Provisions shall be included for seating of the two 

crew members in the proper position and with adequate restraint to 

minimize the effect of launch and re-entry acceleration forces. These 

seat provisions shall include the capability of ejecting the crew members 

from the re-entry module for certain modes of launch phase abort and 

for emergency landing. 

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• 3. 3..3. 2..13 Communications and Command Requirements 

3. 3. 3.2. 13. 1 General 

A capability for communication and command 

compatible with the Test Operations Support System Segment shall be 

provided. This shall include the capability for providing two way voice 

communications, providing spacecraft to ground telemetry, aiding 

tracking and recovery, accepting digital commands from the ground and 

providing intercommunication between the crew at all times. These 

functions shall be supplied only when the Gemini B is active. 

3. 3. 3. 2. 13.2 Voice Communications 

Both UHF and HF voice communication shall be 

provided. A capability for post landing operation as a primary voice 

communication mode and as a backup recovery aid shall be provided. 

3. 3. 3.2.13.3 A capability for spacecraft to ground real time 

telemetry shall be provided. This telemetry capability shall be 

continuously available during launch and re-entry phases. Provisions 

for accepting PCM-FM signals from spacecraft and other instrumentation 

shall be included. 

3. 3. 3.2. 13.4 Tracking and Recovery Location 

Aids for flight phase radar tracking and post landing 

recovery location shall be provided. Radar tracking aids shall be 

capable of continuous operation during launch and re-entry phases and 

shall be compatible with C-Band ground tracking stations. Post landing 

recovery location aids capable of operating on the international distress 

frequency of 243 megacycles shall be provided. 

3. 3. 3.2. 13. 5 Command 

The Gemini B, when activated, shall be provided 

with the capability of receiving digital command intelligence from any 

properly equipped ground station. 

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• 

3. 3. 3.2. 13. 6 Intercommunication 

The capability for intercommunication between the 

crew shall be provided during all mission phases. These phases shall 

include those times when both crew members are in the Gemini B, when 

• t, 

one crew member is in the Gemini B and the other crew member is in 

the crew transfer mode,,,and when one crew member is in. the Gemini B 

and the other crew member is in the Laboratory Vehicle. The system 

required for intercommunication shall be compatible with the systems 

required for spacecraft to ground voice communications. 

• 

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• 

3.3.3.2.14 Gemini B Peculiar Ground Systems 

3.3.3.2.14.1 Gemini B Peculiar AGE 

3.3.3.2.14.1.1 General 

The Gemini B Segment peculiar AGE shall be 

designectin accordance with the AGE System Criteria Section. 

3.3.3.2.14.1.2 Design 

The Gemini B Segment peculiar AGE shall consist 

of -OGE and MGE designed to support all Gemini B Segment operations from 

after final acceptance at the contractor's facility through launch. This 

Gemini B peculiar AGE shall be designed per the requirements established 

by this specification. Wherever possible, maximum utilization shall be 

made of existing or modified Gemini A design. The Gemini B AGE 

utilized at ETR shall be functionally identical to the AGE utilized at the 

Contractor's facility and the AGE utilized during factory acceptance. 

3.3.3.2.14.1.3 Performance 

The Gemini B Segment peculiar AGE shall include 

all the equipment necessary to transport, handle, store, verify, calibrate, 

checkout, monitor, record, service and control the Gemini B Segment. 

This AGE shall be capable of providing a means of (1) verifying the proper 

operation of the Gemini B Segment to assure successful operation of all 

systems during all Segment test and factory acceptance, (2) determining 

whether the Gemini B Segment is operable within prescribed limits, (3) 

identifying to the black box and/or replaceable component areas of 

failure or operation outside of prescribed limits. This AGE shall support 

the GSS AGE end-to-end systems test of the Gemini B Segment when 

integrated with the Laboratory Segment, Experiments and/or Titan III 

Segment (Transtage) . Fault isolation equipment at the launch site will 

be limited to that equipment necessary to isolate faults to the black box 

or replaceable component level. Detailed fault isolation and failure 

analysis within black boxes and/or components will be conducted at 

contractor/subcontractor plants and/or at AF depots. 

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3. 3. 3, 2. 15 Crew Safety Requirements 

The crew safety requirements for the Gemini B shall 

include the inherent safety of the Gemini B and the safety provided 

the crew by the crew escape system in the case of aborts. 

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3. 3. 3. 2. 16 Rendezvous 

After orbital catchup, the rendezvous of a chase and target 

Orbiting Vehicle shall be controlled from the Gemini B of the chase OV. 

Such capability shall include sensors, computation zapability, displays, 

and necessary control signals to the Transtage and OV attitude control 

systems. 

The Gemini B shall be capable of storage on-orbit for 

60 days and then reactivation for crew return. 

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3. 3. 4 Experiment System Segment • The experiment system segment consists of primary experiments to 

evaluate the effectiveness of man in space doing military tasks, secondary 

experiments to develop technology and acquire scientific knowledge, and an 

experiment information system to facilitate expeditious experiment accomplishment. 

3.3.4..1 Allocated Performance and Desi n Requirements 

Experiments shall be allocated to flights in such a manner to 

maximize the return of data within the cumulative payload capability of the 

program. The specific characteristics and requirements of the experiments 

are to be defined as part of the program. 

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3.3.4.1.1 Effectiveness Allocation 

Data shall be furnished to support a detailed apportionment 

of effectiveness to each of the experiments and to the experiments as a 

group aboard each Orbiting Vehicle. A plan shall be developed to show how 

substantial compliance of this effectiveness allocation will be demonstrated 

prior to acceptance and how actual compliance to this effectiveness allocation 

is judged during each mission. 

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3.3.4.2 Peculiar Performance and Design Requirements 

3.3.4.2.1 General 

3.3.4.2.1.1 Repair Requirement 

All experiment equipments except P-11 and P-12 shall 

have provisions for malfunction detection and on-orbit repair. 

3.3.4.2.2 Experiment Information System Data 

A general purpose, stored program computer shall be 

provided for experimental equipment operation and experimental data 

processing. The computer shall have provisions for malfunction detection 

and on-orbit repair. The computer shall be capable of continuous operation 

during the entire 30-day on-orbit period. 

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• -3. 3. 4. 2. 2. 1 Computer Control 

A combination of automatic and manual control functions 

shall be provided. The control functions shall allow the crew to initiate 

computation routines, and control display and transmission of selected portions 

of the computer output data. 

3. 3. 4. 2. 2. 2 Data Handling Provisions 

The experiment information system shall be capable of 

accepting input data from the various experiment sensors, converting to 

computer language, and performing computations and data reduction as 

required by the experiment. 

3. 3. 4. 2. 2. 3 Read-Out Capability 

The experiment information system output format and 

data rate shall be compatible with the laboratory vehicle to ground link. The 

capability for crew control for frequency of read-out shall be provided. 

3. 3. 4. 2. 2. 4 Data Storage Capability 

Adequate data storage shall be provided to prevent loss of 

data due to transmission failure and to provide permanent records for future 

analysis. 

3. 3. 4. 2. 2. 5 Data Transfer for Return 

The capability for data transmission continuously during 

a pass over the readout station shall be provided. This capability shall be 

under manual control of the crew. 

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3. 3.4. 2. 3 P.1 Acquiring and Tracking Preassigned Earth Targets; 

P-2 

P-3 Detecting and Tracking Ground Targets of Opportunity. 

3. 3.4. 2. 3. 1 Objectives 

P-1 (a) To evaluate man° s capability to acquire preassigned 

land targets and track them with an, accuracy compatible with precise IMC 

determination under various conditions of lighting and target type. 

(b) To assess the effects of reference material 

quality on the- astronaut's acquisition performance. 

P-2 

P-3 (a) To evaluate the astronaut's proficiency in 

detecting ground targets of opportunity under various conditions-of lighting, 

target type, and background. 

(b) To define scanning techniques to optimize 

percentage of-land area covered pass. 

3. 3. 4. 2. 3. 2 Equipment Requirements 

1111.11111111111=E111.111 *

3. 3. 4. 2. 3. 3 Experiment 12'_ocedure 

In the P-1 expriment the astronaut will scan. the general 

target area using the PTS. Reference material will be displayed to assist 

in .acquisition. Upon acquisition, the field-of-view will. bedecreased .and. th.e- 

• magnification increased. The at.,:b-c,naut will-center the. crosshairs.on target 

• and proceed with the traC?-ing z.1.1 by the tracking servo. During the 

.tracking run the couplc:d will. record the image, .including the croSshair 

•reference at periodic •intervals. 

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In the P-3 experiment.the astronaut. will. scan with. the PTS 

in both manual and automatic modes to eValuate.his. ability to assess targets 

of Opportunity. 

3. 3, 4. Z. 3. 4 Orbital 'Vehicle Design Requireinents 

Provie:L.n shall be made for. disabling:the vehicle 

attitude .control system. during i.:asking runs. 

b.; Provi it)A1 :shall. be.ma.de to protect external portions 

of. the PTS during vehicle ascent. A method for removing this protection 

.after attaining Orbit shall be provided. 

c.: An unobstructed view of a major portion of the space 

below the vehicle shall be required. 

a.: . A viewport is recuired in the. bottom of the vehicle 

adjacent.to the TS cont- ol.ccIni.;c1e. 

e Vehicle rigidity- shall be compatible-with precise 

optical alignments. 

f., Storage space shall be provided for film. magnetic 

tapes, punched card digital information and spares. 

. :• 

Exposed film and .data shall be transferable to. the 

Gemini vehicle for re-entry. 

Thermal control.of the MOLIenvironment shall. be 

'consistent with maintaining precise optical alignments and accurate 

operation of servos and computers. 

Outgassing during.tracking runs shall not cause 

attitude errors _or rates in,excess of those specified. 

j, Ejected contx-ol gas shall not enter the field-ofview. of the PTS. 

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3. 3. 4. 2. 3. 5 Evaluation Requirement 

In Experiment P-3, sufficient data shall be recorded and 

recovered to allow quantitative evaluation of the experiment. 

3. 3. 4. 2..3. 6 Simulation R..quirements. 

The d.evelom,r,.:.:?,r,t:simu.lator.s shall.be.capable of providing 

'visual and.Operating duplication space .operations in order to determine 

-and-.evaluate equipment. design parameters, detailed experiment. and evaluation 

procedures,, variance .between subjects, and provide .pre-and .postflight 

reference .data •on..the•astronauts. 

3. 3. 4. 2. 3. 7 Experiment Interactions Requirements 

The PTS shall be capable of operation with the star 

acquisition.and ranging equipine!..•i:.af Experiment P-8, providing angle data 

.for .the pointing and :tracking cf. the P-10 .collector•optics and pointing .of 

. selected .antennas. of P-4. 

3. 3. 4. 2. 3. 8 Setup and Calibration Requirements 

Provisions shall be made to perform on-orbit setup, and 

calibration, consistent with the evaluation requirements. 

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• 3. 3. 4. 2. 4 P-4 Electromagnetic Signal Detection 

3. 3. 4. Z. 4. 1 Objectives 

The objective is to evaluate the effectiveness of the crew 

in performing tasks associated with detection, processing, display, measurement, and recording of electromagnetic.signals. 

3. 3.4.2.4.2 Equipment Requirements 

EquipthentE.% to be supplied for the P-4 experiment are to 

include the antennas, receivers, processing gear,• display consoles, and 

recorders. to permit evaluation of the. astronaut's ability to process. signal 

. radiation from coordinated emitters in two or three separate frequency 

bands. This equipment .shall be.designed to provide a real-time• analysis 

and display capability for sophisticated signals and modulation .techniques. 

3.3.4.2.4. 3 Experiment Procedures 

As the orbital vehicle passes over preselected target 

areas. alerting .shall be accomplished by operator scanning, or through 

automatic preset alarm criteria. The operator will make the proper 

adjustment of controls to isolate the desired signals and display these in 

an optimal fashion for identification of signal characteristics. Tests will 

be performed to evaluate performance of the equipment. and the operator 

in low versus dense signal environments, simple -versus complex signal 

parameters,:- and maximum versus minimum preilistruction. 

3.3.4.2.4.4 Orbital Vehic:.e Design Requirements 

a: Vehicle stability during the equipment operation shall be 

to allow tracking of ground-based electromagnetic sources. 

b. Storage space shall be provided for film, magnetic tapes, 

and spares. Exposed film and tapes shall be transferable to 

the Gemini vehicle for re-entry. 

A tracking antenna shall be provided for weak signals as well 

as signal locating and shall be extendable from the unpressurized 

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d. Precaution shall be taken from EMI standpoint to avoid deleterious 

interference with vehicle subsystem functioning, medical monitoring gear, telemetry and communication gear. 

e. Antenna arrays external to the vehicle shall be suitably protected 

during ascent to preclude damage from the environment. Covers 

shall be ejected after commencing orbit operations. 

3. 3. 4. 2. 4. 5 Evaluation Requirements 

Data shall be recorded and recovered to determine quantitatively the ability of the astronaut to detect, analyze and identify sophisticated 

signals, the time required to optimally display the signals, and the distribution 

of functions accomplished by the operator. 

3. 3. 4. 2. 4. 6 Simulation Requirement 

The developmental simulations shall provide a means for 

synthesizing typical RF signal environments to allow for evaluation of the 

spaceborne processing and display equipment, developing and testing 

operating and evaluation techniques, establishing variance between operators, 

and providing pre- and post-flight baseline reference data. 

3. 3. 4. 2. 4. 7 Experiment Interactions 

P-4 equipment shall be compatible with operation of the P-13 

surveillance radar and display equipment. 

3. 3.4. 2.4. 8 Setup and Calibration 

Provisions shall be made to perform on-orbit setup and 

calibration, consistent with the evaluation requirements. 

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3. 3. 4. 2. 5 P-5 In-Space Maintenance . 

3. 3. 4. 2. 5. 1 Objectives 

To provide quantitative and qualitative measures of man's 

ability to perform maintenance, calibration and adjustment on complex orbital 

equipment on-orbit within the spacecraft on a preventative and emergency 

basis. 

3. 3. 4. 2. 5. 2 Equipment Requirements 

Equipments to be supplied for P-5 shall include fault detection gear, standardized tools, attachments for various work stations, and 

suitable audio and visual recording devices for evaluation. In addition, 

maintenance models are required for functions not to be covered by normal 

maintenance operations. 

3. 3. 4. 2. 5. 3 Experiment Procedures 

Data concerned with maintenance activities connected with 

both vehicle and experiment subEystems shall be collected. Particular attention shall be given to acquire data which can be utilized to evaluate tools, 

work positions, level of repair, time requirements, and types of tasks. In 

addition, maintenance models shall be used to gain data on malfunction, repair, 

calibration tasks not included in the basic maintenance requirements. Also to 

be considered and evaluated are advanced techniques and technologies which 

would have application to future maintenance requirements. 

3. 3. 4. 2. 5. 4 Orbital Vehicle Design Requirements 

Suitable attachment points within the vehicle shall be provided for each maintenance position. 

Storage provisions for tools, repair kits, malfunction 

detection equipment, and maintenance models shall be provided. 

3. 3. 4. 2. 5. 5 Evaluation Requirements 

Evaluation data shall be acquired to determine the effectiveness of various tools and attachments on different levels and types of maintenance. Of particular interest is the time required in space—rel-ativc to the 

same task on the ground. 

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3.3.4.2.5.6 Simulation Requirements 

Suitable development simulations will be devised to establish 

tool, malfunction detection, and attachment design characteristics, evaluate 

operating and evaluating procedures and provide pre- and post-flight reference 

data. 

3.3.4.2.5.7 Experiment Interactions 

Vehicle subsystem and all experimental equipments shall be 

designed for in-space maintenance of critical elements. 

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• 3,3.4.2.6 P-6 Extravehicular Activities 

3. 3. 4. 2. 6. 1 Objectives 

To provide a qualitative assessment of man's extravehicular 

capability, using .a maneuvering unit, for operations on the external surface 

of the vehicle and at a distance from the vehicle. 

3. 3. 4. 2. 6. 2 Equipment Requirements 

Equipment to be supplied shall include a.task panel, suitable 

attaching and ambulating devices for surface operations, and an maneuvering 

unit that can be attached to the crew member to provide attitude stabilization 

and maneuvering capability. The maneuvering unit shall have an integral life 

support capability including suit-cooling to sustain operation for periods of at 

least one hour. 

3.3.4.2. 6. 3 Experiment Procedure 

The crew member will don .the pressure suit and check it 

out in the air lock compartment and perform selected tasks. He will then • depressurize the lock and egress out to the surface of the vehicle and propel 

himself along with a variety of ambulation techniques and devices. He shall 

perform a number of tasks such as erecting vehicle appendages, applying 

patches to the skin of the vehicle, and replacing typical components using 

standard space maintenance tools. 

For extended operations he shall don the maneuvering unit 

in the pressure lock, depressurize, and test its operation. He will then 

egress from.the vehicle, first performing simple maneuvers to evaluate the 

equipment and techniques while in retrievable distance with the tether line. 

After satisfactory completion of this phase he shall maneuver out to a 

proportioned target and proceed to return it to the vehicle. 

3.3.4.2.6.4 Design Requirements 

a. The air lock compartment shall be of sufficient dimension to 

permit donning the suit and astronaut maneuvering unit. The 

hatch external to the vehicle shall be of sufficient size to 

• permit easy egress to or egress from the vehicle. 

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b. Provisions for attachments to the laboratory, vehicle shall be 

provided for surface operations. 

c. An umbilical shall be provided for life support and comrnunication for surface operations. 

d. The maneuvering unit shall be designed to. be refurbishable in 

order to allow at least three complete cycles of operation of 

the unit. Provision shall be provided in the laboratory vehicle 

for communication to the maneuvering unit. 

e. Storage of AMU expendables shall be provided for in the air lock 

compartment of the vehicle. 

f. A vehicle viewing port shall be positioned so that the astronaut 

can be immediately viewed after egressing from the air lock. 

g. External illumination shall be provided. 

3. 3. 4. 2. 6. 5 Evaluation Requirements 

Evaluation shall be accomplished primarily through audio and 

video recordings made during operations and by debriefing. The astronaut 

shall describe his progress and time tones shall be superimposed on the 

record for time line analysis purposes. Extended operations shall be recorded 

by other astronaut, using a hand held camera at a viewing port or other suitable camera or television device. 

3. 3. 4. 2. 6. 6 Simulation Requirements 

Developmental simulation shall be carried out to evaluate 

the design of the astronaut maneuvering unit and to develope techniques of 

maneuvering. The surface ambulation and attachment techniques shall be 

evaluated to determine their effectiveness, perfect techniques, and determine 

training requirements. 

3. 3. 4. 2. 6. 7 Experiment Interactions 

No other experiment shall be performed during extravehicular operations. 

3. 3. 4. 2. 6. 8 Setup and Calibration 

There shall be no calibration necessary for the equipment 

of this experiment. 

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• 3. 3. 4. 2. 8 P-8 Autonornos :::-vicration and Geodesy 

3. 3.4. 2. 8. 1 Objective 

The objecti7ie of Experiment P-8 is to evaluate the ability 

of man to act as spacecraft - avigator and to determine man's ability to 

perform geodetic survey of imcooperative targets through the acquisition of 

data for use in subsequent post-flight analysis. 

3. 3. 4. 2. 8. 2 Equipment Requirements 

EquipmeLts to be supplied for the P-8 experiment are an 

inertial measuring unit, two automatic star trackers, a horizon scanner, a 

precision time reference system, a photo-optical system, a ranging device, 

displays and various prepared re:vigational data. The pointing and tracking 

scope for use in this experiment shall be the PTS described in Experiments 

P-1, 2, 3. The digital computer used in this experiment shall be the 

experirrient information system central computer. 

3. 3. 4. 2. 8. 3 

• 

It is required that measurements be made of inertial and 

terrestrial references as fu)e;tionS of time. The spacecraft's inertial 

orientation .shall Nr. ptcvide(1 by the inertial measuring unit which is 

periodically up-dated by celestial sightings; an alternate operating mode 

shall be provided utilizing celestial sightings, with star trackers, to obtain 

the inertial reference without recourse to an inertial measuring unit. 

Terrestrial references shall be obtained through measurements of the 

earth's horizon or ace known.landmarks. Data filtering and 

smoothing techniques shall be applied tc the above measurements. 

The geodey portion of the experiment shall employ the 

pointing and tracking scope acquire the terrestrial feature to be surveyed. 

A ranging device such.as a laser shall be caved to the pointing.and tracking 

scope. Time shall be obtained-from the spacecraft time reference system. 

Spacecraft attitude shall be determined by the star tracker-inertial measuring unit cornbination.together with a photo-optical system. 

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3.3 4.2.8.4 Orbital Vehicle Design Requirements 

a. The star trackers shall be positioned to provide adequate tracking of stars during terrestrial pointing of the pointing and 

tracking scope. 

b. A theodolite slaved to the star-trackers shall be positioned 

such that the operating FOV is the same as that for the star. 

trackers. 

c. A sufficiently unimpeded visual path shall exist between the 

navigation 'MU and the star-trackers to accomplish optical 

alignment if necessary. 

d. The horizon scanner and ranging. device shall be located on 

the earth.-facing side of the vehicle. 

e. Storage space shall be provided for film and.prints as well 

as other data. EXposed film..and data shall be transferable 

to the Gemini vehicle for recovery. - 

f. Thermal control of the MOL environment shall be consistent 

with maintaining precise optical alignments and accurate 

operation o2 inertial components, servos and.computers. 

g. Outgasing during data acquisition runs shall not cause attitude 

errors or rate:, in excess of those specified. 

h. ...Ejected Con.trol gas shall not enter the fields-of-view of the 

star-trackers, horizon sensor or the theodolite. 

3.3.4.2.8.5 'Evaluation Requirements 

Sufficient data shall be recorded and recovered to allow 

quantitative evaluation of accuracy and efficiency of on-board orbit 

determination .ephemeris prediction and navigation problem solution and to 

allow quantitative evaluation of the astronaut's ability to obtain high precision 

geodetic information. 

3.3. 4.2.8.6 Simulation Requirements 

The development simulators shall be capable of providing 

.visual andeoperating duplication of space operations in order to determine 

and evaluate equipment design parameters, detailed experiment and 

evaluation procedures, variance between .subjects, and provide pre- and postflight reference data on the astronauts, 

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• 3. 3. 4. 2. 8. 7 Experiment Interaction Requirements 

Compatible operation with the PTS and the experiments 

information system shall be provided. 

3. 3. 4. 2. 8. 8 Setup and Calibration 

Provisions shall be made to perform on-orbit setup and 

calibration, consistent with the evaluation requirements. 

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• 3.3.4.2.9 P-I 0 Multiband Spectral Observations 

3.3.4.2. 9. 1 Objectives 

The primary objective of the rnultiband spectral experiment is to evaluate man's ability to operate specialized radiometric and 

related equipment as aids in the following military mission and related 

scientific activities: 

a. Collection of a wide range of background measurements and 

sky background data which will be used to design advanced 

sensing systems. 

b. Acquisition and tracking of orbiting objects and/or ballistic 

missiles during boost, midcourse and re-entry phases. 

c. Determination of temperature distribution of ground and sea, 

and of orbiting targets. 

d. Detection and identification of camouflage in .both day and 

night observations. 

e. Collection of data essential to the design of improved horizon 

sensors from which advanced attitude control subsystems may 

be derived. 

f. Detection of high-flying aircraft in clear weather or against 

cloud background. 

3.3.4.2.9.2 Equipment Requirements 

Equipments to be supplied for Experiment P-I0 shall 

include an IR/UV multiband scanning radiometer capable of measuring 

radiation from cooperatively launched missiles, orbiting objects, high 

.flying aircraft and from. adverse earth background. The pointing and 

tracking scope (PTS) shall be used as an optical director. 

3.3.4.2.9. 3 Experiment Procedure 

The astronaut's activities shall include pointing of optics 

in the direction of phenomena or.targets using the PTS or other controls, 

selection of area for measurement, selection of detectors,. selection of 

scanning mechanisms and associated equipment, selection of filters, adjustments and. calibrations, preliminary evaluation, recording of data, verbal 

descriptions, and coordination with the ground, 

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• 

3. 3. 4. 2. 9. 4 Orbital Vehicle Design Requirements 

a. The optical system shall be mounted on the earth-facing side of 

the laboratory so that any portion of the earth observable from 

the satellite may be brought into the field-of-view. 

b. The laboratory vehicle shall provide adequate protection to 

maintain the mechanical and electrical integrity of P- 10 

equipment. 

c. The laboratory shall provide the necessary means of housing the 

P-10 equipment either in the air lock compartment with a special 

mounting hatch or a radiometer bay located. in the unpressurized 

compartment and contiguous with a portion of the pressure module. 

Provisions for an environmental door allowing pressurization.of 

the bay shall be included. 

d. Access with a pressurized environment shall be provided to the 

P-10 equipment when retracted in order to effect changes of 

filters and sensors, and to permit maintenance. 

e. P-10 equipment shall be effectively protected from any source 

of heat. 

f. Ejected control gas shall not enter the field-of-view of the 

optics. 

3. 3. 4.2. 9. 5 Evaluation Requirements 

In Experiment P-10 sufficient data shall be recorded and 

recovered to allow quantitative evaluation of the astronaut's performance in 

detecting, acquiring, tracking and interpreting multiband spectral signals. 

3. 3. 4. 2. 9. 6 Simulation Requirements 

The development simulators shall be capable of providing 

operating duplication of space operations in order to determine and evaluate 

man-machine design parameters, detailed experiment and evaluation procedures, variance between subjects and provide pre- and post-flight 

reference data on the astronauts. • 

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3. 3. 4. 2. 9. 7 Experiment Interactions 

The P-10 equipment shall be compatible and slaved to 

the Pointing and Tracking Scope. 

3. 3. 4. 2. 9. 8 Setup and Calibration 

Provisions shall be made to perform on-orbit setup and 

calibration, consistent with the evaluation requirements. 

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• 3. 3. 4. 2. 10 P-11 General Human Performance 

3. 3. 4. 2. 10. 1 Objective 

The objective of this experiment is to measure space crew 

performance on a standardized basis in order to detect changes in performance 

as a function of the environment or the conditions under which the performance 

occurs. 

3.3. 4. 2. 10. 2 Equipment Requirements 

The equipment to be utilized in this experiment consists of 

a control-display panel which presents tasks to the crew member as tests of 

various aspects of his performance capability. The panel displays shall be controlled by the experiment information system programmed to present the task 

stimulii. 

3. 3. 4. 2. 10. 3 Experiment Procedures 

a. Each space crew member shall perform the test sequence twice 

during every other day.. 

b. The test sequence consists of the crew member's starting the 

test, observing the display panel and responding by utilizing 

the panel controls in a previously learned manner. 

c. The experiments information system, central computer shall, 

in addition to controlling the panel displays, accept the responses made on the panel controls, and process this information for recording and transmission. 

3.'3. 4. 2. 10. 4 Design Requirements 

The display control panel shall be mounted so that a 

strained crew member can view the panel and. operate the controls. 

3.3. 4. 2. 10. 5 Evaluation Requirements 

The results of this experiment shall be compared with extensive ground-gathered, baseline data, and correlated with biomedical data to provide 

an evaluation of the effects of the MOL environment and conditions on man's 

general performance capability. 

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3. 3. 4. 2. 10. 6 Simulation Requirements 

A program of research utilizing simulations of the human 

performance tests to be used on P-11 shall be conducted in order to specify 

the detailed performance and statistical characteristics of the P-11 test 

battery and to minimize on-orbit testing time requirements. 

A program of testing on the total potential space crew 

population shall be conducted utilizing an exact copy of the P-11 test battery 

and, where possible, a simulation of test conditions in order to train the 

space crew sufficiently to remove learning effects during testing, and to 

establish baseline data against which orbital data will be compared, 

3. 3. 4. 2. 10. 7 Setup and Calibration 

There shall be, as a portion of the P-11 control program 

utilized by the MOL experiments information system computer, a brief 

checkout and calibration program which shall be initiated and used immediately 

prior to each P-11 test session. 

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3. 3. 4. 2. 11 P-12 Biomedical and Physiological 

3. 3. 4. 2. 11. 1 Objectives 

The primary objectives are the quantitative measurement 

and evaluation of the following physiological aspects of the weightlessness 

environment: 

a. Effects on gravity-dependent functions as modified by 

countermeasures. 

b.. Providing sufficient data to make plausible extrapolations 

for longer duration flights. 

c. Compare the physiological results with related aspects of 

human performance. 

Environmental parameters of the mission other than weightlessness shall also 

be evaluated; these include the effects of launch, re-entry, and recovery, as 

well as the total environment on orbit. 

3. 3. 4. 2. 11. 2 Equipment Requirements 

The test equipment shall be designed to: 

a. Make a series of physiological measurements while operating 

in the weightlessness environment. 

b. Provide, either continuous or on-demand measurements of 

certain vital functions, e.g. cardiac and respiratory, for 

medical monitoring purposes. 

c. Allow non-medical crew members to perform the tests with 

acceptable precision after an appropriate interval of training. 

d. Provide chemical analysis, e.g. mass spectrometer, shall 

have the capability for manual analysis of the atmospheric 

constituents, i. e. He,N2, 0

2' CO2, H2O and at least gross 

estimate of contaminates. 

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3.3.4.2.11.3 Experiment Procedures 

The measures ,to be used are classified into five categories 

as follows: 

a. Those requiring the space crew member to don one of the special 

garments containing sensors and to establish appropriate links 

with automatic processing or recording equipment. 

b. Those requiring the space crew member to perform a task for a 

period of time on one of the pieces of equipment designed to measure 

specialized aspects of his output and to, provide or establish the 

resultant data input into processing or recording equipment. 

c. Those requiring one space crew member to perform a measurement procedure on the other, recording the results appropriately. 

d. Those requiring one or both of the space crewmen to perform 

detailed analyses procedures utilizing specialized analytical 

equipment and to record the results for processing or recording. 

e Those requiring the space crewmen to measure, identify and 

record their own metabolic intakes and to collect, process and 

identify samples of their own metabolic products. 

The space crew shall ccllect, transfer and return samples to the earth for 

processing after recovery. 

3.3.4.2.11.4 Evaluation Requirements 

Evaluation shall be against the following requirements: 

a. Certain data shall be examined on areal-tune or near real-time 

basis so that medical decisions may be made for mission safely. 

b. Certain of the data shall be analyzed in an ongoing or sequential 

manner in order to detect trends requiring changes in the 

experimental data requirements or mission operations. 

c. The remaining data shall be evaluated in comparison with groundbased data and correlated with other orbital data in order to 

satisfy the objectives of the experiment. 

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3.3. 4.2.11.5 Simulation Requirements 

Simulation of equipment items shall be conducted throughout 

the program with increasing sophistication, beginning with simple mock-ups of 

sensors, test panels and procedures and culminating in actual hardware 

utilization in appropriate space environment simulators. 

3.3.4.2.11.6 Setup and Calibration Requirements 

Setup and calibration shall be designed into the test 

equipment and procedures. For clirdcal analyses the standard gas and 

liquid samples shall be packaged to allow direct insertion into the analytical 

equipment. 

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• 3.3.4.2:12 P-13 Integrated Navy Experiments 

3.3.4.2.12.1 Objective 

The objective is to evaluate the capability of the astronaut 

to control, coordinate, and utilize a number of sensors to detect, track, 

classify, and catalog sea targets. 

3.3.4.2.12.2 Equipment Requirements 

The equipment requirements of this experiment shall be 

the same as the equipment requirements for P-1, P-4 and 13,10. In addition 

to these equipments, an ocean surveillance radar (OSR), display equipment 

for correlation of data, and low-light level television (LLTV) to be used in 

conjunction with P-10 shall be provided. The digital computer used in this 

experiment shall be the experiment information system, central computer. 

3.3.4.2.12.3 Experiment Procedure 

Under normal operation the first detection of a sea surface 

target shall be made by the electromagnetic signal detector sensor (P-4). 

Upon alarm and identification of the target radiated signal, the characteristics 

shall be measured and recorded. The OSR shall scan for additional targets 

not identified by the electromagnetic signal detection sensor. During daylight 

operation, the astronaut shall track selected targets through the PTS to 

determine the proper image motion compensation and obtain photographs for 

classification. During night operation the low-light level TV sensor shall be 

used and the display recorded. 

3.3.4.2.12.4 Orbital Vehicle Design Requirements 

The LLTV and OSR shall be oriented to look in the forward 

down direction. 

Provision shall be made to provide an ascent protective 

cover for the ocean surveillance radar antenna and a mechanism for ejecting 

this cover. 

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3.3.4.2.12.5 Evaluation Requirements 

Sufficient data shall be recorded and recovered to allow 

quantitative evaluation of the astronaut's performance in detecting, acquiring, 

classifying, and determining concentrations of sea targets. 

3.3.4.2.12.6 Simulation Requireirents 

The development simulators shall be capable of providing 

visual and operating duplication of space operations in order to determine and 

evaluate equipment design parameters, detailed experiment and evaluation 

procedures, variance between subjects and provide pre- and post-flight 

reference data on the astronauts, 

3.3.4.2.12.7 Experiment Interaction Requireme nts 

The experiment interaction requirements shall include 

those of experiments P-1, P-4, and P-10. 

3.3.4.2.12.8 Setup and Calibration Reciuirements 

Provisions shall be made to perform on-orbit setup and 

calibration consistent with the evaluation requirements. 

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3.3.4.3 Experiments Peculiar Ground System 

3.3.4.3.1 Experiments Peculiar AGE 

3.3.4.3.1.1 Design 

The AGE peculiar to the various experiments shall consist of 

both the OGE and the MGE designed to support all Experiment operations following final acceptance at the contractor's facility through launch. This Experiments peculiar equipment shall be designed for operability, maintainability, 

reliability, etc. , per the requirements generated by this specification .and the 

Experiment contract end item specifications. Where compatible, common 

usage shall be made of the AGE to support the requirements of several Experiments. The Experiments OGE required .at the launch pad shall be designed for 

inclusion in. one GFE railroad adapted .40' x 10' van to be shared with the Laboratory OGE. Payload Control Room No. 2 in the VIB shall be utilized jointly 

by the Experiments fixed OGE and the Laboratory fixed OGE. Data transmitted 

between Experiment peculiar OGE and the VIB shall consist of signals compatible 

with the Data Transmission System of the ITL System. As far as possible, the 

Experiment AGE utilized at ETR shall be functionally identical to the AGE utilized 

at the Laboratory Vehicle contractor's facility. 

3.3.4.3.1.2 Performance 

The Experiments peculiar. AGE shall include all the equipment 

necessary to transport, handle, store, verify, calibrate, checkout, monitor, 

record, and service .the various Experiments. The AGE shall be capable of proiridifig a means of (1) verifying the proper operation of each Experiment to assure 

successful operation within prescribed limits of all systems, and (2) identifying 

to the black-box and/or replaceable component levels of failure operation outside 

of prescribed limits. Detailed fault isolation and failure analysis within black boxes 

and/or components will be conducted at contractor's/subcontractor's plants and/or 

at Air Force depots. 

3.3.4.3.2 In-flight Maintenance 

In-flight maintenance shall be performed on all experimental equipment 

where such maintenance, either preventative or repairative, may improve the 

possibility of mission success and completion. The maintenance guidlines as outlined in this specification shall be followed in establishing such Experiment 

equipment maintenance, 

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3.3.5 Flight Crew and Crew Equipment System Segment 

This system segment defines, the Flight Crew and crew equipment 

requirements for performance of the /VIOL mission. 

3.3.5.1 Allocated Performance and. Design Requirements 

3.3.5.1.1 Effectiveness Allocation 

The human performance requirements shall be generated and 

specified according to each explicit task element for MOL mission operations. 

These human performance requirements will form the basis for the training 

criteria and mission evaluation. The following criteria applies to the laboratory 

segment. 

3.3.5.1.2 Weight 

Crew members shall weigh 138-192 lbs. Individual space suits 

and portable environmental control sybsystem will weigh approximately 85 lbs. 

per man. This total weight of crew and flight crew equipment is contained in 

the Gemini weight. Back-up suit units, portable oxygen units, "shirt-sleeve" 

clothing, medical (first-aid) kit and personal items, weight - approximately 

300 lbs. total - shall be included in the Lab. Weights for remaining crew 

accommodations items are included in the Gemini B and Laboratory System 

Segments. 

3.3.5.1.3 Volume 

Baseline functional volumes for laboratory vehicle design for the 

human operator will be base upon anthropomorphic data using 10-90 percentile 

men by weight and 10-90 percentile by height. Both shirt sleeve and suited 

mode, pressurized and unpressurized, will be considered. Storage volume 

for back-up suits, clothing, medical treatment and personal items shall be 

provided. The baseline design of the laboratory vehicle shall provide a 

minimum of 200 cu. ft. per man of free volume. The total free volume in the 

final design will be based upon the optimal design. for man system effectiveness in the laboratory vehicle. • 

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3. 3. 5. 2. Peculiar Performance and Design Requirements 

3. 3. 5. 2. 1 Flight Crew Complement and Performance Allocation 

3. 3. 5. 2. 1. 1 Orbital Vehicle Crew Performance 

Functional areas of the Orbital Vehicle System Segment to 

which the flight crew shall contribute are: 

a. Laboratory activation and checkout 

b. Transfer locomotion and control 

c. Gemini B reactivation and checkout 

d. Gemini B - Laboratory separation 

e. Extravehicular activity 

3. 3. 5. 2. 1. 2 Gemini B Crew Performance 

Functional areas of the Gemini B system segment performance 

to which the flight crew shall contribute are: 

a. Launch monitoring and backup control of 

sub-systems. 

b. Launch abort monitoring and control 

c. On-orbit shutdown of Gemini B 

d. On-orbit checkout of Gemini B and preparation 

for re-entry. 

e. Re-entry Control 

3. 3. 5. 2. 1. 3 Laboratory Crew, Performance 

Functional areas of laboratory system performance to 

which man as a flight crew member shall contribute are: 

a. Monitoring and primary or backup control of 

subsystems 

b. Personal maintenance including monitoring 

and maintenance of crew health 

c. Maintenance of essential systems 

d. Laboratory vehicle data management 

e. Communication 

f. Mission control decisions 

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• 3.3.5.2.1.4 Experiments Crew Performance 

The flight crew shall perform the following functions in 

the accomplishment of the experiments mission of the MOL: 

a. Operation and maintenance of experimental 

equipment 

b. Experiments data management 

c. Communication concerned with experiments 

d. Control and perfOrmance of the experimental 

observations 

e. Experimental subject. 

3.-3.5.2.1.5 Crew Performance, Data 

The exact human performance (tasks) to be utilized in the 

various system segments will be defined as a result of engineering studies to 

optimize the man-machine relationships and to develop the procedures to be 

used in the operation and maintenance of the system segments. These human 

S 

performance requirements shall be documented in task and time line analyses. 

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3. 3. 5.2.2 Flight Crew Selection 

The Air Force will have primary responsibility and control of 

flight crew selection from qualified military personnel, according to specific 

mission., medical, and psychological criteria. 

3. 3. 5.2. 3 Flight Crew Train.in. 

The Air Force shall have primary responsibility for flight 

crew training. This training shall be controlled and coordinated by the 

'Training Director in• the MOL SSD system program office. 

3. 3. 5. 2. 3. 1 Training Stages 

After flight crew candidates are selected, training shall 

take place in three major stages. After each stage general evaluation of the 

training program and students shall take place in order to adjust the program 

onto provide additional training in any areas which are considered necessary. 

3. 3. 5. 2. 3. 1. 1 Stage 1 Preliminary General Training 

This stage of training shall consist of six months of 

postgraduate training at the Aerospace Research Pilot School, Edwards Air 

Force Base, California. This course shall be specifically designed for the 

MOL program and shall include advanced academic training, simulation 

(including environmental familiarization), bioastronautics training, site and 

contractor field trips, flight training and a physical fitness program. 

3. 3. 5. 2. 3. 1. 2 Stage 2 Engineering Development and Crew Training 

During this stage flight crew candidates shall be 

attached to the MOL program office and participate in certain aspects of the 

development program including serving as subjects in developmental simulation, participating in design reviews, mockup inspections, and design 

inspections. In addition, they shall receive more intensive training and 

familiarization on MOL systems undergoing development and continue their 

physical fitness and flight training programs. During this stage the more 

intensive and specialized experiments training which will be required for 

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specific•flights will be initiated.. In addition, contingency training shall be 

initiated during this stage. 

3. 3. 5. 2. 3. 1. 3 Stage 3 - Preflight Training 

The preflight training phase shall begin approximately 

six months prior to a scheduled launch. By this date the primary and 

secondary crew members will have been designated as well as the specific 

spacecraft with specific mission objectives for this launch date. These 

crew members shall then begin a detailed training program designed especially 

for their particular spacecraft, equipment, mission objectives, and mission 

profile. Spacecraft checkout and acceptance testing of the particular spacecraft will involve the assigned crew members. The training shall include parttask simulation of boost and ascent, attitude control, orbit modification, 

reentry retrofire and reentry control, and launch vehicle abort; simulation of 

experiments; whole mission rehearsal of the Gemini profile; and whole mission 

rehearsal of the MOL spacecraft mission, including ground support operations. 

Refresher training shall be given in the areas of environment, egress, contingency, and extravehicular activity. 

Toward the latter part of pre -flight training, simulation of all aspects of each experiment will be required. Baseline data shall be 

gathered on the crew after proficiency is obtained in the experimental routines 

for the particular flight. This baseline data shall cover crew participation 

in the integrated system over a representative period of time. 

Crew member capabilities for inflight maintenance 

will need to be .evaluated during preflight training for comparison with inflight performance. 

3. 3. 5. 2. 3. 2 Training and Proficiency Data 

Detailed training requirements and proficiency criteria 

shall be developed on the basis of the Space Crew performance required to 

meet the task and time line analyses. 

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During development simulation and all stages of training, 

crew proficiency data shall be gathered, analyzed and stored in a systematic 

manner in order to provide a training and human performance data base for 

the MOL and future programs. 

3. 3. 5. Z. 4 Flight Crew Activity Programming 

The activities of the Flight Crew required for vehicle operations, 

for performance of the array of experiments on a given flight and for personal 

maintenance - eating, sleeping, hygiene, etc. - shall be programmed for 

each MOL flight in order to achieve maximum mission success. Such 

programming shall contain alternate paths, and the capability for reprogramming 

crew time should contingencies arise requiring a reordering or reallocation 

of crew activities. The Flight Crew activity programs shall contain designated 

points or junctures wherein the crewmen will participate in selecting or 

deciding upon the alternative sequence of activities to pursue. 

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3.3.5.2.5 Nutritional and Metabolic Requirements 

3.3.5.2.5.1 Caloric Needs 

Firm energy requirements for activities in the weightless state cannot be specified until orbital data is secured. Estimates of 

energy allocations are as follows: 8 hours sleep, 500 + 90 kcal; 14 hours 

duty, 1600 kcal; 2 hours exercise, 700 kcal. 

3.3.5.2.5.2 Food Composition 

The 2800 kcal diet will consist of a minimum of 70 g 

of protein, (carbohydrate and fat to be defined) and fortified with vitamins 

and minerals and having a calcium content less than 500 mg. 

A major part of the diet will be administered in liquid 

form utilizing approximately 1500 ml water per day. Weight and volume 

requirements are not firm but can be based on isocaloric equivalents of 

freeze-dehydrated diets established for the NASA Gemini program. 

• 3.3.5.2.5.3 Water Requirements 

Total water intake is expected to be 3000 + 300 g per man 

day, including the water used to reconstitute the food for the liquid diet. 

Potability standards and associated control measures will be established for 

water use during the entire rnissio:n.. 

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• 3. 3. 5. 2. 6 Personal 1-Tgi.eal. 

General skin hygiene to be preserved by simplified system of 

moist skin scrubbing; non-aqueous materials of questionable use. Oral 

hygiene by water and brush without dentifrice. Beard clipping aspirated 

and filtered to eliminate debris from cabin atmosphere. 

3. 3. 5. 2. 7 ElLiy_sioloLical Conditioning • 'Combination of dynamic muscular exercise, peripheral 

vascular "exercises", such as lower body negative pressure, and skeletal 

loading will constitute the basic regime. The free volume of the laboratory 

is to be used for conditioning exercises.. 

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3. 3..5. 2. 8 Medical.Monitoring an.1 1.....aippat 

The baseline scheme for monitoring during launch and re-entry 

will consist of the basic NASA Gemini monitoring scheme. This includes 2 

leads of EKG, blood pressure, respiration profile and oral temperature. 

3. 3. 5. 2. 9 Pressure Suit and Associated Equipment 

The latest version of the NASA/Gemini 4-C, extravehicular 

space suit shall be modified as necessary to meet the requirements for the 

MOL space suit. In particular, the extravehicular transfer mode shall be a 

basic capability -- including the life support subsystem. 

Additional modifications shall be made for tethering, tool 

storage and other mission requirements. 

3. 3. 5. 2. 10 Flight Crew Training Equipment 

The flight crew training requirements are set forth earlier in 

this section. In accordance with. these requirements, five major classes of 

flight crew training equipment may be defined. It will be noted in the paragraphs which follow that certain of those devices shalt provide static representations of MOL subsystems, operations, or equipments. Certain devices 

will provide dynamic simulation of the operating situation and others will 

provide both static and dynamic simulation for training the flight crew in MOL 

operations and maintenance. 

3. 3. 5. 2. 10. 1 Function Trainers 

Training aids, as warranted, shall be developed for use 

in the study or demonstration of structure, function or operation of a single 

system or subsystem of a major segment of the MOL system, e.g. , device 

representing the ECS of the Gemini-B. 

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3.3.5.2.10.2 Part Task Trainers 

Training devices as warranted shall be developed for 

use in practice of a selected function or functions of the MOL operation, 

where a specific critical skill or skills is required, e. g. , manned re-entry 

simulation. 

3:3.5.2.10.3 System Trainers 

Training devices shall be developed in which simulated 

operation, including operation under contingency conditions, of an entire 

segment of the MOL system can be conducted. These procedures, trainers 

(simulators) shall include training devices for the Gemini-B, Laboratory, 

and Experiments system segments. These trainers shall incorporate high 

fidelity simulation of the physical layout. 

3. 3. 5.2. 10.4 Mission Trainer 

A mission training simulator, consisting of the system 

trainers:insofar as possible, shall be developed to provide an integrated 

simulation of all segments of the MOL system. This shall include interacting 

.ground support facilities through which full mission operations can be practiced, developed, and rehearsed. 

3. 3. 5.2. 10. 5 Environmental Trainers 

Training equipments. shall be provided for use in part 

task training in special environments such as acceleration (centrifuges), 

weightleSsfieSs (zero-g aircraft), and reduced pressures and special atmospheric compositions (space cha.mbers). 

3. 3. 5. 2. 10. 6 Development Simulators 

Development simulators for experiment equipments shall 

be used in the training program to minimize the number and types of trainers. 

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3.3.6 Titan ,III System Segment 

The Titan IIIC launch vehicle consists of Stage 0 (solids), Stage I, 

Stage II and transtage, and the flight control, electrical, pressurization, 

propulsion, inertial guidance, tracking and flight safety, instrumentation, 

and malfunction detection system. Basic requirements for performance 

and reliability are specified hereunder. 

3.3.6.1 Allocated PerformancL and Design IIssuirements 

3.3.6.1.1 Minimum Payload Performance 

The minimum on-orbit payload„ including all elements of the 

laboratory and Gemini B shall be as defined in the following for launch from 

ETR: 

• 

Orbital Inclination Altitude N. Mi.. Payload lb. 

28.4° 100 

160 

250 

23,000 

22,400 

21,500 

22,800 

22,200 

21,300 

22,500 

21,900 

21,000 

3.3.6.1.2 Degradation of Performance vs. Diameter 

The performance degradation which results from laboratories 

in excess of 10 feet shall be as follows: 

Payload degradation, lbs. Payload diameter, It. 

0 10 

140 12 

350 13 

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160 

250 

36° 100 

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3.3.6.1.3 Propellant Capacity 

The payloads given previously are for no remaining useful propellant on-orbit. The specific impulse for calculation of available velocity 

which can be gained by adding propellant shall be 305 seconds. The useful 

propellant which can be added in the tanks to provide orbital maneuver propulsion at the expense of payload is defined in .the following ,table: 

Launch Inclination Altitude N. M. Propellant Capacity, lb. 

100 4700 

160 4100 

250 3200 

100 4600 

160 3900 

250 2900 

100 4300 

160 3500 

250 2600 

28. 4° 

32° 

36° 

• 3. 3. 6. 1. 4 Injection Accuracy. 

The required injection accuracy from the nominal injection 

altitude circular orbit shall be as follows: 

Nominal Altitude at 

Circular Orbit 

100 n. m.rn. 1. rr 10 r ----237C1.m. 

± 

± ± Inclination ± 0. 12° 0. 12° O. 12° 

Altitude, ft. 3,000 + - 21,000 ± 22,000 

Eccentricity 0.4x10-3 3. Oxl 0-3 3.0x10-3 

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3.3.. 6.. 1.. 5 Reliability 

The following are predicted values for the booster and transtage: 

1. Countdown 0.87 

2. Boost 0,908 

3. Transtage (to inject) 0.915 

4. Transtage (30 days on-orbit) 0.864 

3.3.6.1.6 Constraints 

3.3.6.1.6.1 Length and Diameter 

The Titan IIIC is required to accept laboratory diameters 

between 10 and 13 feet. It shall accept laboratory lengths falling below a 

straight line on -a plot of payload length versus diameter. The plot is defined 

by the following points: 

Payload Length, Feet Payload Diameter, Feet 

48 10 

29 13 

Payload length is defined as the distance from launch vehicle station 77 to 

the top of the Gemini B without tower. Diameter is the outside diameter of 

the laboratory. 

3.3.6.1.6.2 Center of Gravity Location 

The launch vehicle shall be capable of accepting laboratories with C. G. location between 30 and 60 percent of the laboratory length, 

measured from the transtage interface, launch vehicle station 77. 

3.3.6.1.6.3 Weights 

The above payload length, diameter and C. G. requirements 

shall be met with payload weights between 15,000 pounds and 25,000 pounds. 

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3.3.6.2 Peculiar Performance and Design Requirements 

3.3.6.2.1 Malfunction Detection S stern (MDS) 

The MDS shall be provided to allow man-rating. The MDS shall 

sense potentially catastrophic malfunctions, and either provide cockpit displays 

(slow malfunctions) to the Gemini B, or initiate an abort sequence (fast 

malfunctions). 

3.3.6.2.1.1 Abort Logic 

The MDS shall be.capable of accepting-engine shut-down 

commands. The MDS shall include the capability of initiating thrust termination in Stage.0 flight, and initiating engine shutdown in those-cases where safe 

abort is achievable. The MDS shall be compatible .with the Flight Safety.and 

Tracking System. The MDS system shall be active during the ascent phase. 

3.3.6.2.1.2 Displays 

Signals indicating potentially catastrophic booster or transtage failures shall be provided as displays in the Gemini B and/or laboratory. 

3.3.6.2.1.3 Safety' Criteeia 

The probability that the booster will.function properly.or 

• that a timely_ abort signal will, be generated shall be 0.998 minimum,. The 

probability that. the MDS will-not generate a•false,abort shall be 0.994 minimum. 

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3. 3. 6. 2. 2 Transtage On-Orbit Characteristics 

The transtage shall be available for 30 days on-orbit for sustenance 

propulsion, orbital correction, and either backup or alternate attitude control. The 

propellants are nitrogen tetroxide and a 50-50 blend of hydrazine and unsymmetrical 

dimethylhydrazine (UDHM) for both systems. Nitrogen is the pressurant for the 

attitude control system, helium for the main engines. 

After injection and stabilization, the booster guidance and control 

system shall be made inoperative. The tra.nstage engines and attitude control system 

(ACS) modules shall then be available for use on orbit, and shall have capabilities as • 

defined hereunder. The main transtage engines are currently started after application of a settling impulse from the ACS modules. 

The vehicle-laboratory interface is at vehicle and transtage station 77. 

3.3.6.2.2.1 Main Engines 

Two engines having a nominal vacuum thrust of 8, 000 lb each are 

gimballed by mechanical feedback actuators to provide pitch, yaw, and roll control, 

as well as forward thrust. 

3. 3. 6. 2. 2. 1.1 Number of Restarts 

After injection into orbit the main engines shall be capable of 

at least 10 restarts, depending on the duty cycle and propellant available. 

3. 3. 6. 2. 2. 1. 2 Servo Interface 

On-orbit the effective gimbal actuator electrical interface with 

the laboratory is at the gimbal servo valve. 

3. 3. 6. Z. 2. 1. 3 Propellant Settling 

Propellant settling impulse required for restart of the main 

engines on-orbit shall be provided by the ACS engines. Alternatively, a laboratory 

system may be used to prbvide• the settling impulse. 

3. 3. 6. 2. 2. 2 Attitude Control System (ACS) 

The attitude control and propellant settling system modules consist of the following: 

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a. Four fixed thrust chambers directed aft for pitch 

and yaw control at Station 133.6, 63 inches from the transtage centerline, 

having a nominal vacuum thrust of 45 pounds each. 

b. Four fixed thrust chambers directed tangentially, 

providing couplers for roll control at the same station and radius, having 

a nominal vacuum thrust of 25 pounds each. 

3.3. 6. 2.2.3 Retrorocket System 

Transtage retrothrust shall be provided on the transtage 

for separation. 

3. 3. 6. 2. 2. 4 Telemetry 

Excess channels are available from the transtage for use 

in the boost and orbital phase. Due consideration shall be made to the use .of 

this capability. Primary use of this system. shall be for instrumentation .of 

the Titan.III vehicle during boost and orbital phases. The PCM transmitter 

operates in the 225 and 260 MC band, with an output power of 50 watts. 

3. 3. 6. 2. 3 ITL AGE 

AGE provided for the Gemini B and laboratory shall be compatible with the Integrate-Transfer-Launch AGE at the Eastern Test Range, 

and shall be integrated with existing Titan III equipment. Titan III AGE is 

designed in accordance with SSD Exhibit 62-128. The ITL concept provides 

for build-up of the launch vehicle in buildings away from the launch areas and 

transport of the assembled vehicle to the launch pad in a ready condition requiring only a combined system test and a discrete vehicle cheLkout. Before 

mating of the orbiting vehicle to Titan III all subsystems must have,been 

accepted and checked. An end-to-end. check must be performed after transport to the Eastern Test Range. 

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3. 3. 7 Test Operations System Segment (TOSS) 

The Test Operations System Segment (TOSS) shall consist of the 

launch environment, remote station network,control centers, recovery forces, 

equipment, communications, computer programs, perSonnel, techniques, 

Range support,and procedures necessary for test operation and mission 

control of the MOL system from the initiation of the launch countdown through 

MOL crew recovery and data retrieval. The segment also shall include provisions for integration, simulation, training, and system exercising. 

The TOSS shall function as a total operational system segment with 

functional performance during each operational phase as appropriate for test 

operations and mission control. The TOSS shall be designed, implemented, 

tested, and operated as a system and shall have integral system validation 

capability. 

The TOSS is composed of three sub-segrre nts; Mission Control, 

Test Support, and Recovery. The Mission Control sub-segment shall include 

the Launch and Mission Control Centers and their interfaces with the Test 

Support and. Recovery sub-segments, the mission-peculiar computer programs, 

the ground system simulation equipment and computer programs, and the 

mission operations personnel techniques and procedures. The Test Support 

sub-segment includes a worldwide network of telemetry, tracking and 

command (TT&C) stations, an interstation communications network, extensive worldwide meteorological support, instrumentation, post-flight data 

handling and computation, optical and photographic support, and all Range 

support services necessary to support MOL launch and flight coverage. The 

Recovery sub-segment includes land, sea, and air units deployed to support 

planned, contingency and emergency recovery modes as well as pad and 

ascent aborts. 

The Test Operations function shall be under•the direct control of 

the MOL System Program. Office (SPOT, SSD. The nominal point of control 

shall be located at CKAFS, 

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• 3. 3. 7. 1 Performance Allocations 

3. 3. 7. 1. 1 Effectiveness 

The effectiveness of the Test Operations System Segment shall 

be developed to the highest level consistent with maximum MOL Program 

cost effectiveness (Reference 3. 1.3. 1). That effectiveness shall be not less 

than 98 percent unless the models and procedures developed per paragraph 

3. 1. 3. 1 indicate that a lesser level will benefit program cost effectiveness. 

Should such a situation arise, a request for adoption of a lesser level 

together with the supporting analysis shall be submitted to SSD/Aerospace 

for review and SSD approval. Overall segment mission availability shall be 

not less than .999. 

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3. 3. 7. 2 Functional Re uirements Allocations 

3. 3. 7. 2. 1 Launch Phase 

This phase shall extend from the initiation of terminal countdown 

to the point of lift-off. 

3. 3.7. 2. 1. 1 Initial Conditions 

At the initiation of the terminal countdown the integration, 

assembly, and checkout of the complete MOL vehicle has been completed. 

Within the preceeding 24 hours, the instrumentation network, recovery force 

system, mission control center, and its supporting centers will have been 

checked out individually and,when inter-connected, will have been checked out 

on an end-to-end system basis. Other supporting services, such as weather 

forecasting and launch range materials handling services will have been 

active during previous operations and are on-line as required. MOL vehicle/ 

AGE/instrumentation/MCC interfaces have been validated. 

• 3. 3. 7. 2. 1.2 Mission Control 

Throughout all phases the mission control function shall 

have available the MOL Mission Control Center and the worldwide facilities 

for range support and recovery support which have been assigned to the 

program. The overall function shall be considered as a number of sub-functions 

plus a number of closely interfaced. supporting functions described as follows: 

. 3. 3. 7. 2. 1. 2. 1 Launc:h Control 

Prior to lift-off, all launch control capability will be 

contained within the ITL/T-111 (LCC) complex at Cape Kennedy. Decisions 

as to readiness of the tes`; vehicles from an equipment standpoint shall be 

made there with readiness decisions being monitored by the MCC. From the 

-countdown until the instrumentation systems normally used during. ascent 

become primary, the LCC shall function as an arm of mission control. 

During the countdown all LCC interfaces with the MCC are revalidated and the 

required display/control functions activated. 

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• 3. 3. 7. 2. 1. 2. 2 Vehicle/Crew Control 

This function shall be physically loca.ted in the MCC and, 

for all intents and purposes, is.the prime function for mission control from 

lift-off until re-entry, crew recovery, and data retrieval. This Vehicle-Flight 

Crew Control. Center shall be located at Cape Kennedy. Since the responsibilities of this control are exercised for the duration of the complete mission, 

means must be. available for insuring readiness of the worldwide TT&C 

network, the flight vehicle, the MCC and the crews that man these resources. 

During the countdown all displays and control capabilities are brought on line 

. and checked out with the data handling and instrumentation elements. 

• 3. 3. 7. 2. 1: 2. 3 Network Control 

Launch area and worldwide instrumentation data 

handling and. communications support shall be controlled during .all phases 

by a network or range control function which shall be represented.in .the MCC 

by a summary status and control element. During the countdown all network 

control. functions are .validated and brought on-line. 

3. 3. 7. 2. 1. 2. 4 Range Safety 

Range Safety control is exercised at the ETR Range 

Safety. Control Center. 

3: 3. 7. 2. 1. 2. 5 Recovery Control 

This function shall.be physically centralized.in the 

MCC and shall include the capability for deployment and _control of. forces 

for planned, contingency. and. emergency recovery support. The time constraints.associated with this function are extreme for aborts on-pad and.during 

.early powered flight. Pad _recovery iorces.are expected to be under.the direct 

control of an. appropriately located field commander. During the countdown, 

Recovery forces are brought to the appropriate state of readiness. 

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3. 3. 7. 2. I. 3 Instrumentation and Communications Network 

During the countdown the ETR instrumentation systems.are 

exercised and brought on-line by a combination of closed-loop and RF radiation 

..techniques. Actual vehicle frequency and other signal checks are made and 

. last minute corrections transmitted to the world-wide network. All stations 

.are brought on line and exercised using tapes and simulation equipment on a 

complete system basis, in which:the MCC data processing and display functions 

participate. 

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3.3.7.2.2 Ascent Phase 

The ascent phase extends from lift-off until injection into final orbit. 

3.3.7.2.2.1 Mission Control 

During early powered flight, mission control displays augment 

the crew displays and are concerned with trajectory and impact location. in the 

event of abort. During coast a detailed assessment is performed of the vehicle 

and crew's performance during powered flight and a baseline established for decision purposes. Necessary modifications to the planned final injection (circularization) maneuver are determined. During this maneuver, which occurs in range 

of a remote-site tracking station in. Australia, mission control is essentially on 

line. 

• 

3. 3. 7. 2. 2. 2 Tracking 

The tracking systems ;shall derive position information adequate 

for the control functions, i:acluding range and crew safety, during ascent. • Data 

derived from combinations of range, range rate, and interferometry systems at 

uprange ETR shall be used fro alignment and calibration of vehicle systems as 

required. During the later phases of burn, the ground-derived tracking data 

shall be used to verify achievement of orbital insertion and orbit life and to make 

alternate control decisions. Tracking data shall be obtained in real time after 

transtage shutdown for sufficient time to provide for smoothing data and verifying 

first insertion into orbit. 

For the coast phase the tracking systems at selected remote 

sites shall derive position information which is adequate to assist in deterinining 

malfunction of the vehicle guidance and control system and upon which to base 

corrective action for the injection burn. Tracking requirements during the injection 

. burn shall be those necessary to determine a catastrophic malfunction. Tracking 

. immediately after burn shall be adequate to derive an initial ephemeris for control 

purposes. 

3. 3.7.2.2. 3 Telemetry Acquisition 

Continuous telemetry data shall be obtained at downrange ETR 

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successful first insertion into orbit. Telemetry data shall be obtained during 

coast on a selected basis. Extensive telemetry service shall be used during 

circularization. All data shall be recorded on site and selected data shall be 

transmitted to the MCC in real time and near-real time. Data shall be selected 

locally as required. 

3. 3. 7. 2. 2. 4 Commanding 

Commands to the Gemini B shall up-date displays, guidance 

systems, and other vehicle systems as required. The commanding system also 

shall provide the necessary range safety destruct commands for the launch 

vehicle. 

3. 3. 7. 2. 2. 5 Communications 

Reliable communications shall be provided from the MCC to 

all remote sites for tracking, telemetry, and command data. Voice communications with the flight crew and with flight control personnel at the remote sites 

shall be provided. Administrative :ind range control communications shall be 

provided separately in cases where interference with mission requirements 

would result. 

3. 3. 7. 2. 2. 6 Data Flow, Computation and Display 

Tracking data and selected booster guidance telemetry data 

shall be furnished to the ETR Real Time Computer Center in. real time and used 

directly for trajectory, lIP, crew safety, and related calculations. .The outputs 

of these processes shall be displayed at the MCC and, in certain cases, at the 

Range Safety Control Center. Certain outputs may be used directly in the commanding process. Selected OV and crew telemetry data shall be converted to 

engineering units and displayed in real time at the MCC. Selected launch vehicle 

telemetry data shall be displayed in real time at the MCC and Range Safety 

Control Center. A large amount of telemetry data shall be collected, processed, 

and stored or displayed at the MCC in near-real time in order to establish a 

performance baseline.for later decisions and to aid in verification of the eventual 

OV status. Commands shall be initiated directly by the Range Safety Officer, by 

the Computer Center, as programmed, and from MCC. 

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3. 3. 7. 2. 2. 7 Coverage 

Coverage of the ascent phase shall be continuous, using 

selected downrange sites and ships as required, with adequate overlap and 

acquisition aids to assure against loss of data or track. 

As a minimum one full station pass exceeding 5 minutes in 

duration shall be obtained during the coast phase. 

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3. 3. 7. 2. 3 On-Orbit Phase 

This phase shall be considered in two sub-phases; early orbit 

and orbit. The early orbit sub-phase shall extend from final injection 

through lab activation, crew transfer, and verification of a satisfactory 

orbit operational configuration. The orbit sub-phase extends throughout 

the 30-day mission and ends as Gemini B separation from the Laboratory. 

The requirement to support on-orbit emergencies shall be considered. 

3. 3. 7. 2. 3. 1 Mission Control 

During the critical early orbit sub-phase, the mission 

control function enters directly-into a large number of decisions. The 

function includes a detailed analysis of the OV and crew telemetry data to 

establish the validity of the orbit configuration and provide malfunction 

detection and remedial action. Updating or modification to the system 

operations plans based on the actual orbit and vehicle/crew condition shall be 

performed. 

During the orbit sub-phase mission. control primarily 

performs detailed analysis, failure prediction, fault location and remedial 

planning as well as systems operational planning. The flight crew is. expected 

to achieve a high degree of self-sufficiency for routine operations. Close 

crew/mission control interaction shall be required during emergencies and 

during performance of certain types of experiments. The•mission control 

function is expected to achieve. a high degree of centralization, particularly 

during later flights. 

3. 3. 7. 2. 3. 1. 1 Experiment Control 

This function shall be exercised at the MCC. The 

possibility of subsidiary control points for specific experiments exists. 

Little or no experiment control is expected during the early orbit sub-phase. 

During the orbit sub--phase experiment analysis and control will cover a 

broad technical and operational spectrum and includes deployment of 

surface resources in. the atmosphere and in space. The time constraints 

associated with the experiment control function are only critical with regard 

to scheduling; other functions normally operate in a. control cycle on the order 

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3. 3. 7.2. 3. 2 Tracking 

At least three valid tracking passes are required to 

establish the orbit for control purposes. Thereafter, the nominal ephemeris 

accuracy requirements are expected to be achievable with 2-4 tracking 

passes per day. Special experiment tracking requirements may necessitate 

extensive tracking (up to one pass per revolution) and optical tracking. Callup tracking to support emergencies is a consideration. In the case where 

velocity changes are applied to the OBI for orbit phase changes or maneuvers, 

three valid tracking passes shall be required to re-establish the ephemeris. 

3. 3. 7. 2. 3.3 Telemetry Acquisition 

During early orbits telemetry data shall be obtained from 

transtage, laboratory, and Gemini B at all sites and recorded on site. At 

all primary stations throughout the mission, it shall be possible to select a 

set of data from any link and display in real time. It shall be possible to 

select a different set or the same set of data, edit or summarize and 

transmit to the MCC in real time. During the early orbit phase it shall be 

possible to perform this process on both the Gemini B and Laboratory real 

time links simultaneously. During routine on-orbit operations, time 

sharing of status and experiment data dumps and selection in real time of 

a limited amount of received data for transmission to the MCC shall be 

normal modes of operation. Additional requirements derived from the 

experiments in the combinations of extra links or special formats on the 

vehicle status links shall be processed, both in real time and near-real 

time modes. The requirement to support special wide band experiment links 

at selected remote sites is expected. 

3. 3. 7. 2. 3. 4 Commanding 

Commanding of the Laboratory shall update displays, the 

guidance system, and other vehicle systems as required. The commanding 

system shall be capable of providing ephemeris information, pointing 

instructions, and other.information to the Experiments Subsystems. The 

vehicle data system shall routinely be controlled.from the ground. All 

primary sites shall have the ca.pability to command the Gemini B systems 

required for reentry. 

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3. 3. 7. 2. 3. 5 Communications 

Communications requirements are generally the same as 

those for ascent. In view- of the practical limitations of achieving reliable 

wide band data over the early orbit sub-phase, it is expected that the discrimination, interpretation, and compression ability of mission trained 

personnel will be used at certain remote sites. During routine on-orbit 

operations, temporary restrictions in the rate capability of communications 

to the control center may be tolerated, provided that transmission of critical 

data is not interrupted. 

3. 3. 7. 2. 3. 6 Data Flow, Computation and Display 

During the early orbit sub-phase, tracking data shall be 

processed in real time at the central computer complex until the final 

ephemeris is established and verified. A large amount of telemetry data 

will be processed in real time and displayed to the mission control elements. 

Telemetry data also shall be collected and filed for use-in later trend 

analysis. Transmission of complex digital command loads from remote sites 

is expected to be limited to quasi-real time, in which data is transferred to 

the remote site at a reduced rate and stored for re-transmission to the 

vehicle. 

During on-orbit operations, the average data handling 

load .is expected to decrease significantly from that of the early orbit 

phase. However, the peak load may increase due to certain experiments 

which may require high rates and special data processing. The requirements 

to process different formats, information rates, and quantities of multiplexed vehicle and experiments data, together with the requirement to store 

data for trend analysis purposes shall require flexibility in the remote site 

and MCC data handling and display systems. In addition, the continuous 

. capability shall exist to compute the impact point based upon a tracking pass 

after retrofire or after receipt of the information of the time of retrofire. 

Command data flow shall be a real time function for passes over the MCC, 

Antigua and possibly the West Coast site.. 

3. 3-7. 2. 3. 7 Coverage 

• 

Extensive coverage, comprising two to four passes per 

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orbit and relatively continous coverage over the continental United States 

shall be available during the critical early orbits. 

On-orbit coverage for telemetry and command shall be 

nominally a minhnum of once per orbital revolution. Extensive coverage 

shall be provided .for orbits covering the continental U.S. Gaps in telemetry, 

and command coverage occurring shall be backed up by voice. During later 

MOL flights the coverage requirement for telemetry and command during 

normal modes of operation shall be decreased to a minimum network configuration involving coverage as•little as once per three or four orbits except for 

those orbits in which contact is made with the MCC directly. Tracking 

coverage after deboost is required in case of planned recovery, and is 

desired .in case of contingency recovery. 

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& Re-entry Phase 

The Loiter & Re-entry Phase extends from separation of 

Gemini B and Laboratory to water impact 

. 3. 3. 7. 2. 4. 1 Mission Control 

The mission control function during this phase is concerned 

primarily with providing maximum support to crew and vehicle. Close .crew/ 

mission control interaction also shall be. required for the, initiation of the reentry sequence. This may require use of local.flight control personnel. on site 

for. the planned de-orbit sequence. As a result of the limited loiter time capability and back-up capability of. the Gemini B, the recovery system assumes a 

critical operational mode during this phase. 

3. 3. 7. 2. 4. 2 Tracking 

Tracking requirements shall be of sufficient. coverage to 

establish the new ephemeris 'for - the Gemini B after separation from the Lab. 

More extensive support for. the Gemini B may be required of the worldwide 

tracking system to handle emergency as well as planned. de-orbit during this 

phase. 

For the primary recovery area in the West Atlantic, radar 

tracking shall-be provided almost continuously from..shortly after deboost until 

water landing. In case of other types of recovery, radar tracking will be 

- utilized where available. The primary, tracking system after emergency.from 

the ionization blackout shall be UHF direction finding equipment on aircraft 

and ships. 

3. 3. 7. 2. 4. 3 Telemetry Acquisition 

Telemetry acquisition requirements shall. support the 

• Gemini B only. Support should be the maximum achievable with the primary 

network. Call-up of additional stations is a possibility. The primary method 

of retrieval of data during deboost and. re-entry will be by recording type from 

.. the capsule. 

Commanding of -the Gemini B shall update displays, the 

guidance system, and other vehicle systems as. required. Ground.command 

control shall provide retrofire times and segments for both planned recovery 

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3.3.7.2.4.5 Co: imunications 

Communication requirements shall support the Gemini B 

only. More extensive support will be required of the worldwide comrnunication.system to handle emergency as well as planned de-orbit during this phase. 

Relatively continuous voice coverage-will be provided. Recovery communications shall generally be a separate net from the normal TT&C network, however, the hard wire capability of the latter shall supplement recovery communications as applicable. 

3.3.7.2.406 Data Handling, • Computation, and Display 

Gemini.13 telemetry and tracking data shall-be processed 

in real time-and near-real. time and displayed at. the MCC. Data displays 

may be utilized at remote•-sites which are required for backup support and 

are not part of primary MOL ground network support. Commanding from 

the remote sites shall be.limited to quasi-real time. 

3.3.7.2.4.7 Coverage 

Extensive instrumentation and. voice coverage shall be 

planned to support the Gemini B during loiter. time for both emergency and 

planned de-orbit. 

Emergency recovery coverage shall be available for all 

areas covered by the MOL orbit. Contingency coverage shall be a.limited 

number of areas based upon trade-off studies of abort modes, area size, 

force deployment, • access time requirements, daylight and weather constraints, and techniques. The planned landing area is in the West Atlantic. 

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3.3.7.2.5 Reccvery Phase • The recovery phase extends from water impact to retrieval 

of crew, spacecraft,and data. 

3.3.7.2.5.1 Track/Search 

The track/search operations will make use of aircraft 

and ship DF equipment compatible with the Gemini B UHF and HF recovery 

aids. A flashing light and sea marker will be used as optical search aids. 

It is expected that electronic buoys will be dropped to augment the capsule 

aids after it is first located. 

3. 3. 7. 2. 5. 2 Access and Retrieval 

Access time is defined from impact to that time when 

either flotation gear is rigged in a safe sea state (4 or less), or the spacecraft and crew are received on deck or the crew and data have been retrieved 

from the spacecraft. Access time varies during mission phases as a result 

of crew safety criteria. 

• 3. 3. 7. 2. 5. 3 Recovery Demands 

The Recovery Forces shall effect safe retrieval of the 

crew, spacecraft, and experiment data it. accordance with the following 

schedule: 

Crew 

Recover 

Experiment Data 

Reentry 

Module 

1. Pad Abort Yes No No 

2. Ascent Abort Yes No Desired 

3. Mission Termination Return Yes Yes Yes 

4. Contingency Return (with delay) Yes Yes Yes 

5. Emergency Return (immediate) Yes Yes Desired 

3.3.7.2.5.4 Post Recovery 

Post recovery operations include crew medical care and 

debriefing, and safe packaging of experiment data. Data and crew shall be 

returned to locations to be specified. 

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• 3. 3. 7. 2.. 6 Rendezvous 

The support and control of rendezvous flights places an 

additional requirement upon all aspects of TOSS during all mission phases. 

3. 3. 7. 2. 6. 1 Mission Control 

The mission control function includes an analysis of the 

target vehicle and crew telemetry data to establish the validity of the on-orbit 

configuration for rendezvous plus the generation of mission data necessary 

to solve the intercept-rendezvous problem. Up-dating of this mission 

data is required for all mission phases of the chaser vehicle prior to the 

successful intercept and rendezvous with the on-orbit target vehicle. 

For rendezvous mission control is responsible for two vehicles and crews 

through the start of terminal count on the chase vehicle until recovery of 

one Gemini B. 

3. 3. 7.2. 6. 2 Tracking 

The tracking requirements shall be that of sufficient 

coverage to establish the position and ephemeris for mission control of both 

the on•-orbit target vehicle and the chaser vehicle, which may be in any 

mission phase prior to successful intercept and rendezvous with the target 

vehicle. Extensive tracking support for the chaser vehicle shall be required 

after on-orbit phase and altitude changes. The possibility of maneuvers by 

both O.V. 's complicates the tracking procedures. The worldwide tracking 

system also shall meet o, requirement to support emergency abort of the 

chaser vehicle and emergency de-orbits of both the chaser vehicle and 

target•vehicle during the pei.:.)d before rendezvous and after separation of -

the space vehicles for a crew return. 

3. 3. 7. 2. 6. 3 Telemetry Acquisition 

The world wide network shall provide simultaneous 

telemetry support for both the target vehicle and the chaser vehicle. 

Telemetry acquisition requirements for the target vehicle shall be as 

described for the on-orbit phase; requirements for the chaser vehicle shall 

be as described according to the mission phase in progress. 

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• 3. 3..7..2.6.4 Commanding 

The world wide network shall provide simultaneous 

command support for both the target vehicle and the chase vehicle. Command 

requirements for the target vehicle shall be as described for the on-orbit 

phasee requirements for the chaser vehicle shall be as described - according 

to the mission phase in progress plus those commands necessary to solve 

the intercept-rendezvous problem. 

3. 3. 7.2. 6. 5 Comminnications 

Communication requirements for both vehicles shall. be 

.in.accordance with the mission phases in progress. 

3. 3. 7.2. 6. 6 Data.Handling, Computation, and Display 

Data handling, Computation, and Display shall provide 

simultaneous support for both vehicles in accordance with the mission phases 

in progress. This function also shall generate the mission data necessary 

to solve the interce-ot-rendezvous problem and provide control of the chaser 

vehicle and the •target vehicle prior to rendezvous.. 

1. 3. 7.2. 6. 6 Coverage 

Coverage requirements for both vehicles shall be in 

accordance with the mission phases in progress. More extensive coverage 

for. the :chaser vehicle shall be required for intercept-rendezvous control. 

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3. 3. 7. 3 TOSS Design Requirements • 3. 3. 7. 3. 1 Mission Control Sub-Seinaent 

The Mission Control Sub-Segment shall be provided by SSD and 

shall be under the direct control of the MOL System Program. Office, SSD, 

operating through appropriate agencies. The nominal point of control shall 

be located at Cape Kennedy (CKAFS). 

3. 3. 7.3. 1. 1 Mission Control Center. 

The Mission Control Center shall provide the following 

capabilities: 

a. Display and control consoles i:or launch, powered flight, 

life support, biomedical monitoring,. OV subsystems, 

experiments control. 

b. Display and control capability for recovery and range 

control. 

c. Working areas for analysis, control, orbit planning 

and biomedical staffs. • d. Experiments analysis and control staff working 

areas. 

e. Display subsystem providing a limited number of 

large screen display for special events, displays 

for control consoles and supporting staffs. 

f. Data buffering storage and retrieval subsystem for 

formatting, buLet.ing , filing, retrieval and outputting 

telemetry data. 

g. Interfaces with the launch and checkout complexes. 

h. Command storage and processing. subsystem. 

The following supporting elements shall be required, 

suitably interfaced with or incorporated in the MCC: 

a. Real time computer complex. 

b. Communications !>witching terminal. 

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Major computational and data handling functions shall be 

performed by a large computer center operated as part of or in direct support 

of MOL Mission Control operations. This computer center may be provided as 

part of test support or may consist of mission-dedicated equipment with test 

support equipment as a backup. On-line telemetry processing, buffering, 

filing and display driving shall be allocated to the computer center or to small 

buffer computers located within the MCC. Remote site data processing functions shall be allocated to available remote site computers. 

3.3.7.3.1.2 Operational Computer Program System Element 

The. Operational Computer.Program System Element shall 

consist of all mission-peculiar computer programs required for the entire 

MOL mission integrated into a compatible system. Computer program 

functions include: 

Input tracking sensor data 

Edit & condition tracking data 

Trajectory computation 

Orbit computation (life, ephemeris) 

Impact prediction 

Ascent abort timing 

Recovery instructions (per area) 

Acquisition 

Ship position 

Drive tracking, trajectory, and orbit displays 

Telemetry strip out 

Telemetry convert and format 

Drive telemetry displays 

Telemetry alarms and checks 

Data correlation 

Data file for retrieval 

Data trend analysis 

Compute and format updated IOU 

Compute and format stored program functions 

Compute and format orbit changes 

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Crew operations scheduling 

Vehicle operations scheduling 

Ground support scheduling 

Experiment guidance computations 

Experiment acquisition - Earth related (stationary 

and moving) 

Space related 

Experiment force deployment 

Experiment scheduling 

Experiment data analysis 

Experiment space simulation 

Rendezvous-intercept instructions 

3. 3. 7. 3. 1. 3 Ground System Simulation Element 

The Ground System Simulation Element shall provide the 

capability to simulate all mission phases and operations, including rendezvousintercept, to the degree that the real time data system, including operational 

computer programs, ana the flight control crews are exercised in a valid 

manner. This element shall make use of the Gemini/MOL Orbiting Vehicle 

Simulator. Simulation modes shall include both open loop and closed loop 

with various configurations of the total segment. This element shall be used 

to develop and test operational procedures, as well as for training and 

exercising. 

The various modes can be described as follows (in all 

cases the operational. MCC computer is driven as if the data were received 

from the the remote sites: 

a. MCC open loop - the simulation computer (with its 

data tapes) simulates the OV and remote sites, 

generating all required tracking and telemetry data. 

b. MCC closed loop - the MOL Orbiting Vehicle 

Simulator provides all necessary OV data (primarily 

telemetry data) to drive the simulation computer 

and MCC operational computer; the simulation computer.generates all tracking and other data required 

to exercise the MCC facility. 

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c. Station open loop - this mode provides limited 

simulation of remote sites. In this mode, the 

simulation computer (and its tapes) simulates 

the OV, driving (limited) simulated station display. 

In some instances, tapes generated using this 

technique or the OV simulator will be used at the 

actual remote sites for training. Fly-by aircraft 

may be used. 

d. Station/ship closed loop - this mode is similar 

to the open loop mode, except that the MOL 

Orbiting Vehicle Simulator will be used to provide OV data. In addition, actual remote sites 

may be integrated into the simulation, using flyby aircraft equipped with a partial OV simulator, 

including a simulated flight crew. 

e. System exercise this mode provides exercise 

of the complete TOSS as an integrated system. 

The MOL Orbiting Vehicle Simulator provides 

OV data to drive the MCC telemetry interface while 

the remote sites use tapes and voice patch; the 

simulation computer integrates these elements 

to provide the mcst practicable realistic overall 

mission simulation. 

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3.3. 7. 3. 2 Test Support Sul-Ssirnent. 

The Test Support Sub-Segment shall provide .the worldwide 

network which supports on-board MOL vehicle TT&C systems. Other elements 

include ground system communications, meteorological support, and all Range 

support necessary to accomplish launch and flight coverages. 

• 

3. 3. 7. 3. 2. 1 Network Support Element. 

Network Support Element shall provide remote site tracking, 

telemetry, command, and voice functions which support on-board MOL Vehicle 

. , . . 

TT&C Systems. Site capabilities shall include data acquisition, data handling, 

display and'intra-iintere site- Each Site-shall becapable inaa 

specified time of verifying subsystem performance of an individual basis as 

well as verifying the total site configuration and.ability to support the MOL 

mission. Validation of two-way interchange of data with the Mission Control 

Center shall be possible. The extent to which the site remains fixed in the MOL 

support configuration depends upon.the time required .and. confidence achieved 

in the checkout and .verilication process. 

3. 3. 7. 3. 2.1.1 . Coverage 

The ground.network shall be capable of providing the 

required, instrumentation coverage for vehicles launched in orbital planes 

between 28. and.36°. In addition.the ground network shall be capable of 

providing telemetry, tracking, and. command.-data from launch through final 

injection of the lvIOL orbiting vehicle at selected.remote sites and shall assure 

validation of the orbiting vehicle operational capabilities during early orbits 

.and.crew transfer. On-orbit coverage then shall. he a .minimum of once per 

orbit. Extensive coverage shall be provided for orbits within the continental 

U.. S. Also, the ground network shall be capable of updating .the orbiting 

vehicle on-board systems with ephemeris and re-entry data at least four. times 

per day. 

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3. 3.7.3.2.12 Meteorological Support Element. 

The Meteorological Support Element shall provide weather 

data obtained from va.ricus reporting and forecase sources necessary to 

support the MOL mission. 

3; 3. 7. 3. 2.1. 3 Loading 

The ground network shall be required to provide support 

for two MOL orbiting vehicles in various flight phases conducting an on-orbit 

rendezvous .mission. Consideration shall be given to the. fact that certain 

remote sites may be involved in other multi-mission support operations. 

3. 3.7.3.2. L 3.1 Ground TT&C Capabilities 

a. The acquisition of mission data and control of the MOL 

orbiting vehicle by the ground network shall be achieved by the use of: 

radar tracking systems for determining position and velocity, telemetry 

SYStems for ground monitoring of systems performance.in.real.time and by 

•the reception of on-board stored.data, ground command systems for updating on-board systems, and voice communications between the vehicle 

flight crew and the flight control personnel through the groundJaetwork. 

b. C-band radar tracking systems shall be employed by the 

ground network for tracking acquisition, launch. trajectory, and orbit updating. 

Identification of orbiting, vehicles shall be through the use of vehicle code 

addresses. Where feasible, skin tracking of the orbiting vehicle shall be 

employed. 

c.. VHF telemetry systems operating in .the R-F frequency 

band of 225-260 Mc shall be employed by the.ground.network for telemetry 

data acquisition. PCM-FM modulation will.be employed by the orbiting 

vehicle data transmission system. Ground telemetry and.data handling systems 

shall be capable of simultaneously receiving and recording all real time and 

stored .data transmitted from the orbiting vehicle. Telemetry dump schedules 

shall_ provide maximum use of the continental U. S.. stations to assure minimum 

logistics and communications problems, in handling the ,data. Depending upon 

mission phase, selected data. shall be transmitted to the MCC in real time or 

.near real time for analysis. Pro-visions for real time displays at selected 

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d. A digital command system compatible with the orbiting . 

vehicle shall be employed for ground-to-vehicle data transmission operating in 

the R-F frequency band of 406 to 450 Mc. Specific word format, the number of 

real time and.stored program commands, plus the transmission modes required 

will be determined. 

e. Voice transmission and reception in the R-F frequency 

band of 225 - 300 me using AM modulation shall be required at specific remote 

sites, 

f. Special telemetry links for experiment. data in the 2200 - 

2300 megacycle R-F band shall he supported at the. west coast, CKAFS,. and 

possibly downrange ETR up to a maximum of one megabit. A wide band data 

link having 5 Mc .analog or 10 megabit digital data capability shall be supported 

at Vandenberg Tracking Station and at least the analog signal. shall be 

supported at CKAFS. Ground display and recording equipment for such a link • 

shall be supplied by the TOSS or Experiment Segments., as applicable. 

g. In additicn, the design of the Test Support Sub-segment 

and its technical and operational interfaces widathe Mission Control Sub"- 

segment shall.consider.the ,expected evolution to a standard instrumentation 

system for support of DOD space program development. .This development will 

involve the use .of a minimum number of remote stations and a standardized 

integrated S..band TT&C system such as the AFSSD Space-Ground Link Subsystem (SGLS). 

3. 3. 7. 3. 2. 1. 4 Network Stations 

The network stations tentatively selected.on remote 

sites necessary for mission data acquisition. and.control of the MOL orbiting 

vehicle are listed .as follows: 

3. 3. 7. 3. 2. 1. 4. 1 Cape Kennedy (CKAFS) 

The employment of the resources at CKAFS shall 

include all the instrumentation necessary for the launch-and ascent phases of 

of the flight. Cape Kennedy also shall be utilized as a primary on-orbit station 

having telemetry reception, radar tracking, command transmission, and airto-ground voice capabilities. In addition, a secure capability shall be implemented for telemetry reception and air-to-ground voice communications when 

required by mission operations. 

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3. 3. 7. 3. 2.1. 4. 2 Grand Bahama Island, Grand Turk, Antigua, ETR 

Ship(s), Ascension, Pretoria, Bermuda, and 

Grand Canary Islands 

These ETR and NASA downrange stations shall 

provide support for missions with launch azimuths passing over their locations. 

An ETR ship or ships shall be positioned to provide coverage for the first 

transtage shutdown due .to the lack •of land-based stations in the area. For the 

ascent phase of the flight, command and air-to-ground voice functions shall be 

routed from the MCC and Range Safety through Grand Bahama Island, Grand 

Turk, Antigua, the ETR ship(s), Bermuda, and Grand Canary Islands depending 

.upon the launch azimuth. Selected telemetry functions shall be transmitted .to 

the MCC in real time or near real time from these stations, and all stations 

shall provide C-band tracking data in real time to. the MCC and Range Safety. . 

Antigua also shall be utilized as a primary on-orbit 

station having TT&C and air to-ground voice coverage netted with the MOL MCC 

at CKAFS. •A secure capability shall be implemented for telemetry reception 

.and-air-to-ground voice communications when required by mission operations. 

3. 3. 7. 3. 2. 1. 4. 3 Carnarvon, Australia 

Carnarvon shall be utilized for the ascent and 

circularization phases of the flight. This station provides TT&C and air-toground voice coverage during transtage re-burn. Since this station is essential for circularization coverage, mission personnel may be deployed at this 

site. Further netting of this station for on-•orbit support may be required 

depending upon mission requirements.. 

3. 3. 7. 3. 2, 1. 4. 4 Okinawa Area 

A new station .or ship in the Okinawa area shall be 

.implemented to provide primary on-orbit TT&C and air-to-ground voice . 

coverage netted with the MOL MCC at CKAFS. This station.also will provide 

coverage after the retrofire sequence prior to the communications blackout 

for. the secondary Midway and South Pacific (Tahiti) recovery areas. 

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3. 3. 7. 3. 2. 1. 4. 5 Hawaii Area 

An existing station in the Hawaii area shall provide 

primary on-orbit TT&C and air-to-ground voice coverage. Stations under 

consideration are Kaena Point and Kokee Park, A secure capability shall be 

implemented for telemetry reception and air-to-ground voice. communications 

when required by mission operations. The Hawaii,area station .also will provide coverage after retrofire sequence prior to the communications blackout 

.• for the primary West. Atlantic/ETR recovery area. 

3. 3. 7. 3. 2. 1. 4. 6 West Coast Area 

An existing station in the West Coast area shall 

-provide primary on-orbit TT&C and air-to-ground voice coverage. Stations 

under consideration.are Point Arguello and th.e Vandenberg Tracking Station. 

A secure capability shall be implerniented for telemetry reception and air-toground voice communications when required by mission operations. The 

West Coast area station also will provide coverage prior. to the communications 

blackout for. the primary West Atlantic/ ETR recovery area. 

• 3. 3. 7„ 3. 2. 1. 4. 7 Wake, Suva (Voice only) 

New air-to-ground voice .only communication 

stations 'shall be implemented at Wake and Suva .to fill gaps in primary station. 

coverage. The NASA station in the Grand Canary Island also shall be utilized 

for this purpose. 

3. 3. 7. 3. 1. 4, 8 White Sands, Eglin. 

These two stations shall be used .as back-up for 

C-band.radar tracking for early orbital ephemeris determination.and for 

Support of planned recovery. 

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3.3.7.3.2.1.5 Network Communications 

The ground communications network for MOL mission 

support shall use existing and planned DOD and commercial networks. 

Channel capacity and reliability to support flight crew-to-MCC voice, station 

control voice, telemetry data transmission, command control, and tracking 

data transmission at all stations in the network shall be provided. Where 

feasibile, all primary on-orbit stations shall be netted with .the MCC at 

CKAFS utilizing hardwire or equivalent circuits. Requirements for the 

communication support functions are described as follows: 

3.3.7.3.2,1.5.1 Flight Crew-to-MCC Voice 

Full duplex voice circuits from the remote sites 

to the MCC shall be employed for orbiting vehicle-to-ground voice relay. 

The capability for remote site keying. of the ground-to-air transmitters from 

the MCC shall be implemented for all remote sites netted for MOL network 

support to allow direct communications between the MCC and. the orbiting 

vehicle. 

3.3.7.3.2.1.5.2 Station Control Voice 

Full duplex voice circuits from the remote sites 

netted via the appropriate remote site control centers to the RCC shall be 

employed for remote site control and administration by the Test Support 

Sub-segment. Full duplex 100 wpm•teletype circuits also shall be utilized. 

3.3.7.3.2.1.5.3 Telemetry Data Transmission 

Telemetry data for the ascent phase of the mission 

shall be transmitted to the MCC for real time control from the remote stations 

utilizing 40,800 bps and/or 2,400 bps High Speed Data (HSD) lines to the 

extent possible. 

Both 100 wpm teletype-and 600-1.200 bps HSD 

lines shall be employed at the Ce.rnarvorn- Australia site. All primary stations 

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within the continental - U. S. , i.. e. , Cape Kennedy, Antigua, and the West Coast 

area, shall be netted with the -MCC for telemetry transmission utilizing. 

40,800 bps HSD lines and a hack-up 100 wpm teletype mode. 

Other stations required for on-orbit telemetry 

support, i.e. , Hawaii area, Okinawa area, and possibly Grand Canary Island, 

shall employ 100 wpm teletype. with growth to 600-2,400 bps HSD lines. 

3.3.7.3. Z. 1.5.4 Command Control 

Command control during. the mission flight phases 

shall be achieved through the use of HSD lines, 600-2,400 bps, for command 

transmission directly from the MCC via the remote Bite and through the use of. 

pre-stored commands sent by 100 wpm- teletype to the remote site to be initiated 

under MCC and mission personnel control. 

3.3.7.3.2.1.5.5 Tracking Data Transmission 

Tracking data for the ascent phase of the mission 

shall be transmitted to th.e MCC for real time control from the remote stations 

utilizing HSD lines to the extent. 

Special early orbit considerations may require 

real time transmission of tracking data over HSD lines. 

Routine on-orbit tracking for ephemeris updating 

shall utilize 100 wpm teletype where HSD lines are not conveniently available. 

3.3.7.3.2.1.5.6 Security 

In addition, the ground. communication network 

shall provide for secure transmission of experiment data and voice from the 

Okinawa. area, Hawaii area, West Coast area, and Antigua. 

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3.3. 7.3.3 Recovery Sub-segment 

The recovery system shall make maximum use of those 

equipments, techniques, and procedures developed for Gemini/Apollo 

recovery support which are appropriate for MOL. Support will be obtained 

through the DOD Manager for Manned Space Flight Support Operations. 

3. 3.7.3.3.1 Recovery Force 

The recovery force shall be comprised of sea, land, and 

air units, associated crews and specialist teams as necessary to meet the 

performance requirements of recovery. Such resources shall be provided 

from existing government sources, wherever possible and practicable. 

The recovery forces shall include the 11C-130 airplane 

equipped with HF and UHF /DI-equipment and carrying a pararescue crew. 

Such aircraft shall be continuously -deployed in the planned recovery areas 

during periods of planned recovery. At other times and areas, the aircraft 

shall be on strip alert foa immediate take-off in the event landing is made 

in one of the contingency areas or at any other place along the ground track. 

The surface recovery force shall include a Navy 

Destroyer modified for spacecraft pick up by the installation of special davit 

and winch equipment as provided under the NASA Gemini Program. Where 

possible, identical ships shall be used for both programs. 

Aircraft arid ships shall be provided in such quantities 

and at such locations in the recovery areas or appropriate bases as is 

necessary to effect retrieval of the spacecraft and. crew. 

Special high density recovery forces shall, be provided 

in the immediate area of the launch pad and down-range along the ground 

track to a distance of 70 n. m. to insure recovery of the crew following launch 

phase abort. These forces shall be comprised of fixed and rotary wing 

aircraft, land and amphibious vehicles and high-speed sea-going vessels and 

shall be capable of immediate 7i-ea.etion in case crew abort is initiated. 

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3.3.8 Facilities 

Design and construction of new and/or modified existing facilities 

shall be .under the direction of the Civil Engineering Office of SSD and shall 

satisfy the requirements of the total system as defined in this specification 

.and in..applicable Facilities Criteria Documents. 

The facilities covered in. this section encompass those facilities 

necessary to support the MOL development program and MOL operations 

from receipt of the segments at ETR through launch of the MOL and recovery of the Gemini B capsule. New facilities shall.be-provided.only as 

required; maximum use shall be made of existing facilities modified as 

required,. 

3.3.8.1 ITL System 

The MOL system will be integrated and launched from the Integrate 

Transfer Launch (ITL) system at the Eastern Test Range (ETR). Modification to the ITL shall Only be made if essential to operation. 

3.3.8.1.1 Launch Pad 

Modifications to the existing Pad 40 facilities shall be accomplished 

to provide an environmental enclosure for the entire Orbital Vehicle (OV) while 

.on the launch vehicle, suitable parking areas for the OV AGE rail vans and fluid 

.servicing units, and adequate services for the support of OV launch .operations. 

Means shall-be provided to effect the safe removal.of the flight crew to at least 

800 feet from the spacecraft within seconds in the .event a potentially dangerous 

condition arises between the time of flight crew insertion and lift-off. Existing 

facilities shall be removed or relocated as necessary to provide a clear landing 

area for the flight crew in case of on-paid abort. 

For the rendezvous mission, it may be necessary to also modify 

the existing Pad 41 facilities. 

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3. 3. 8, 1. 2 Vertical Integration Building_ 

Orbital vehicle integration with the TIII core shall be accomplished 

in .the Vertical Integration Building (VIB). The VIB shall be modified to provide 

an environmental enclosure for the OV while -on.the launch. vehicle, suitable 

.parking areas for necessary OV AGE rail vans, and adequate .services for. the 

support of the TIIII0V integration arid checkout. 

The VIB launch control center and. connecting cableways and 

.ducting between the -AGE vans and.the launch control center. shall be modified as 

required for spacecraft AGE'. installations. Existing areas shall_be.utilized 

with modifications, where required. The GEEIA communication lines, which 

connect the launch cos.aplex and the launch .control- center,. shall be modified 

.to satisfy MOL system requirerraants. 

3. 3.8.2Industrial Area 

Portions of the orbiting vehicle shall be integrated in the Industrial 

Area at Cape Kennedy prior to entering the VIB. New facilities or modifications 

to existing facilities shall be provided as follows: 

3. 3. 8. 2. 1 Assembly Facilities 

A clean room asserobly.area shall be provided for the receipt 

and inspection of the individual segment portions .of the MOL system and.the integration.and checkout Of the MOL flight vehicle. Sufficient area .shall be provided 

for all AGE and personnel necessary to perform systems tests required and to 

align., calibrate, or adjust the appropriate systems. Area .shall be provided for 

the storage of critical spare nomponents and. elements as required. 

A pyrotechnic installation facility shall be provided for the 

Gemini B at the location. remote from the Industrial Area. The possible use .of 

the. solid motor Receiving ins?ecaiion and Storage (IRS) building in the ITL 

system shall be considered for this function. 

3. 3. 8. 2. 2 Simulator Facilities 

Facilities shall. be provided as required..to operate Mission 

Simulator in. conjunction with the Mission Control Center and the world wide 

tracking net. 

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• 3. 3. 8. 2. 3 ]Engineering and Administration Facilities 

An Engineering and•Administration area shall be provided 

.for the individual segment contractors, and Air Force and Aerospace personnel. 

3. 3. 8. 2. 4 Mission Control Center 

Facilities' shall be provided. for mission control and shall 

include provisions for housing all Mission Control Center equipment for 

display and control, data retrieval- and storage, computation, on-orbit flight 

planning .and.changes, mission analysis, and biomedical. support. Facilities 

necessary for. the interconnection of the Mission Control Center with the ITL 

Launch Control Center, telemetry receiving stations, Mission Simulation 

Facility, Range Safety and Range Control, and range tracking station communications nets shall be installed. 

3. 3.8. 3 Telecommunications, Tzacking.and Control Facilities 

Additional. facilities shall-be provided as required to house and 

.otherwise -support the .worldwide TT&C requirements specified in the TOSS 

Segment Section. Examples. of such additional facilities are the Okinawa Station, 

and .the voice communication stations at Wake and Suva Islands. 

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• 4. 0 Performance/Desirification and Test 

This section specifies the formal tests and verification methods 

required to demonstrate compliance of the MOL system. In addition, the 

test operations of the developed MOL system required to fulfill the MOL 

mission are specified. 

The tests and verification demonstrations specified herein are those required 

at the overall system and major system segment levels and/or the general 

requirements which must be recognized in preparing Part I, section 4 of 

each contract end item specification. 

4. 1 ci,round Test Requirements 

4. 1. 1 Development Tests. 

4. 1. 1. 1 General :Requirements 

Design developrrr nt tests shall be performed to determine design 

feasibility, functional parameters, thermal and structural data, packaging 

and fabrication techniques, and environmental limitations. The majority of 

these tests shall be performed prior to design freeze; however, some tests 

are continued throughout the program. 

4. 1. 1. 2 Overall System. Requirements 

No "full scale" ground development tests at the overall system 

level are required. Subscale model wind tunnel tests of the TIIIC-Orbiting 

Vehicle shall be conducted to determine aerodynamic characteristics of 

the combined vehicle. 

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4.1.1.3 Orbiting Vehicle (OV) Requirements 

4. 1. 1. 3. 1 Space Simulation Test 

The orbit ing vehicle shall be tested to a thermal and 

vacuum space simulation for 30 days to demonstrate the environmental and 

thermal control subsystems, the tunnel development, and the orbiting 

vehicle functional characteristics. The laboratory and Gemini B shall be 

used for this test. Other segments of the OV may be simulated. During 

this test specific performance of the normal and emergency crew transfer 

shall be accomplished. Contaminant measurements shall be made during 

this test. 

4. 1. 1. 3.2 Compatibility Test 

Tests shall be conducted on the orbiting vehicle to demonstrate physical, functional and EMI compatibility. 

"Li. 1. 3. 3 Rendezvous and Docking Test 

Simulations shall be performed to demonstrate the 

ability of the chase OV to perform the necessary rendezvous maneuvers. 

Docking tests shall be conducted for development and demonstration of 

the Rendezvous and Docking s'ystem, plumbing and electrical connections, 

and crew passage. Post-docking tests of all critical (e. g. ECS, power) 

' subsystems shall be conducted. 

• 4.1.1.3.4 Attitude Control Simulations 

Appropriate air-bearing simulations to verify the control 

electronic and propulsion subsystem capab ility shall be performed for all 

control modes. 

4. 1. 1. 3. 5 Antenna Tests 

Complete antenna patterns of the laboratory and experiment segments shall be obtained with the simulated Gemini B and transtage 

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4.1.1.4 Laboratory Vehicle Requirements 

4: 1. 1: 4:1 Structural Tests 

Static tests shall be performed to limit and ultimate loads 

for the article design conditions to the.soecified structural criteria. 

Consideration shall be given to the thermal environment . Deformations 

shall not exceed the specified requirements. 

Shock and vibration tests shall be performed with 

appropriate simulation of Gemini B, transtage and experiments. 

4.1.1. 4. 2 A;roustic Test 

The laboratory vehicle (or sections thereof) including 

mass simulated components shall be subjected to acoustic testing to determine the acoustic and vibration environments imposed on the lab vehicle 

subsystems and components. Laboratory subsystem prototypes shall 

be installed. 

4.1. 1. 4, 3 Subsystem•Tests 

Separate subsystem development tests shall be made to 

verify design adequacy. 

4.1.1. 4, 4 'Meteoroid and Particle Radiation Test 

The a.bility of the lab vehicle to withstand meteroid impact 

and particle radiation shall be demonstrated by subjecting lab structural sections to simulated rneteroid and particle radiation environment. 

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• 4. 1.1. 5 Gemini B Requirements 

4: 1: 1:-5::1 General 

The Gemini B vehicle shall make maximum use of 

equipment and components developed and qualified for NASA Gemini. 

The requirements for Gemini B development testing shall be determined, 

based on an analysis of the changes to the NASA Gemini configuration 

and equipment necessary to meet the MOL environment and mission requirements. Two critical environments imposed on the Gemini B, not 

encountered by.the NASA Gemini, are the TIII-C launch environment 

and the 30-day on-orbit standby. All components common to Gemini B 

and NASA Gemini shall be analyzed to determine the effects of these 

environments and. the requirement for development and requalification testing. New and significantly modified components shall be designed to 

Gemini B criteria and shall undergo •a, complete development test program. 

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4. 1. 1. 5. 2 Wind Tunnel Tests 

Static force, moment and pressure wind tunnel tests shall 

be performed on the Gemini B configurations where NASA Gemini data does 

not exist. These tests include those cases where the external configuration 

or flight parameters are significantly changed. 

4.1.1. 5. 3 Space Environmental Tests 

The effects of a prolonged period of inactivity and exposure to the space environments shall be determined by a thermalvacuum space simulation test on the Gemini B system segment. Test of 

individual critical components shall be performed to assess the impact of 

the activation following a 30-day space standby environment. Component 

tests shall include environmental control, communication, electrical 

power, guidance and control, etc. 

4.1.1. 5. 4 Shock and Vibration 

Tests shall be performed for any shock and vibration 

criteria that is found to be in excess of NASA Gemini 

4.1.1. 5. 5 Acoustic Noise 

An acoustic noise test shall be performed on the Gemini B 

vehicle or vehicle section to determine the Gemini B vibration and acoustic 

criteria found to be in excess of NASA Gemini criteria. 

4. 1.1. 5. 6 Separation Tests 

Staging separation tests shall be performed on the Gemini 

B, simulating on-orbit separation from the transtage. 

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4. 1; 1. 5. 7 Crew Transfer Tests 

Tests shall be performed to demonstrate and verify the 

feasibility of the normal and emergency crew transfer between the Gemini B 

and the laboratory. Inflated suit and an incapacitated crewman in an 

emergency situation shall be simulated. 

4.1. 1. 5. 8 Abort: Tests 

Additional testing of the seat ejection system and the abort 

rockets shall be accomplished as necessary where changes .are made from 

NASA Gemini environment and/or design to determine crew safety. 

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4.1.1. 6 Experiments Requirements 

Developmental simulations shall be required for all experiment 

sub-segments. 

Complete development tests shall be performed for performance, temperature, shock, noise, vibration, strength, rigidity, 

EMI, maintainability, distortion, operability, etc. 

Man-machine performance parameter shall be obtained where 

applicable. 

4.1.1. 7 Titan IIIC Requirements 

Titan III-C vehicle shall be used for the MOL mission with 

minimum modifications .as necessary to fulfill the MOL mission. Requirements for development testing shall be determined based on an analysis of 

Titan III changes required to meet the environments imposed by the MOL 

mission which exceed the present Titan III design requirements. The 

requirement for the t:ranstage to perform for 30 days on-orbit, will require analysis and demonstration in a simulated thermal-vacuum environment. Additional restarts may require developmental testing. 

4.1.1. 8 Flight Crew and Crew Equipment Requirements 

Maximum use shall be made of NASA Gemini Flight Crew 

equipment. Such equipment, as well as new and/or significantly modified 

Flight Crew equipment shall undergo comblete.development testing to 

demonstrate capability to meet MOL environmental storage, crew transfer, 

extravehicular, and other mission requirements. 

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4.1. 1. 9 Test Operational Support Segment (TOSS) Requirements 

Development testing shall be conducted to demonstrate proper 

operation and compatibility of the TOSS with the Orbital Vehicle System 

Segment with which TOSS interfaces. Maximum use of simulation techniques such as computer mission simulation, data transfer runs, mockflights, etc. , shall be made for training and for developing early confidence 

in the performance of TOSS equipment and personnel for all phases of the 

MOL operations. 

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4.1.2 Qualification Tests • 4.1.2.1 General Requirements 

Qualification tests shall be performed to verify design adequacy 

and to demonstrate a minimum level of equipment performance and reliability.• 

The test conditions shall be the design requirements and consist of time 

and stress level safety factors on the anticipated environments. Full 

qualification tests, including all applicable environments, shall be performed at the component or subsystem level. Limited qualification tests, 

such as thermal-vacuum and EMI, shall be performed at the system segment 

level. Appropriate qualification tests must be completed prior to the 

applicable flight. 

4.1.2.2- Over-all System Requirements 

Due to the size and complexity of the over-all MOL system, there 

are no qualification test requirements at this level. of assembly. The 

qualification of the various system segments will constitute the qualification of the over-all system. 

4.1.2.3 Orbiting Vehicle Requirements 

An electro-magnetic interference qualification test shall be 

performed at CKAFS on the orbiting vehicle system as a complete systerri 

under conditions simulating pre-launch, launch, and on-orbit operations. 

Due to the size and complexity of the over-allflightivehicle.thexe .are. no 

additional qualification test requirements at this level of assembly. 

4.1.2.3.1 Mission Life Requirements 

The system segments comprising the rendezvous mission 

orbiting vehicles and their subsystems shall be qualified for a life of 

sixty days on orbit. Integral launch mission orbiting vehicle segments and 

their subsystems shall be qualified for on-orbit life of thirty days. 

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4.1.2.4 Laboratory Vehicle Requirements • 4.1.2.4.1 General 

The laboratory vehicle system segment shall be qualified 

both at the system segment level and at the component/subsystem level. 

These requirements will be detailed in an AFSSD environmental requirements 

specification exhibit for the laboratory vehicle and components. These 

environments will be based on the environments defined in Section 3.1.3.4, 

Environments (Natural and Induced). .In general, the components and/or 

subsystems will be tested to all applicable environments while the laboratory 

vehicle will be subjected to thermal-vacuum and EMI tests. 

The crew transfer shall be qualified to the specified 

environmental recuirements. The qualification tests of the laboratory shall 

be performed when possible on the laboratory, crew equipment,- and experiments 

system which comprise the laboratory vehicle segment. The tests shall 

establish the capability of maintaining the required environment, electrical 

power, leakage rate, communication and. data handling for the mission. 

4.1.2.4.2 Rendezvous.antDocking_Equiment 

The rendezvous and docking equipment, including the coupling 

mechanism, crew paaPagee tunnel, electrical connections, and plubbing, shall 

be qualified to the specified environmental requirements including the 

ability to properly function for a period of sixty days on orbit. 

4.1.2.5 Gemini B Repairements 

The Gemini B system segment shall be oualified per the requirements of the Environmental Specification. Components and/or subsystems qualified for NASA Gemini shall not be arbitrarily requalified but 

shall be analyzed from previous testing and flight test history. In addition;. 

the Gemini B System segment shall be subjected to a thermal vacuum and EMI 

qualification test, This test shall include, as a minimum,.the sequence oC 

operation on orbit, shut down and/or standby for an extended period of time 

and re-start and operation for re-entry. 

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The experiments shall be qualified at the subesegment or 

component level using as a basis the environmental requirements specified 

in SSD Exhibit 64-XX. 

4.1.2.7 T--III Requirements 

The T-III system segment shall be qualified per the requirements of AFSSD Exhibit 62-166A. "Environmental Requirements Specification, 

Program 624A", Rev. A, dated 1 July, 1964. The applicable subsystem of 

Titan III transtage shall be qualified for 30 days on orbit. 

4.1.2.8 Space Crew and Crewment Requirements 

Crew equipment qualified for NASA Gemini shall not be arbi 

trarily requalified but shall be analyzed on a basis of environmental 

exposure from previous testing flight test history and contemplated usage 

in the MOE system. environment. The crew system segment equipment shall be 

subjected to a qualification test including the sequence of mission 

operations from launch, oneorbit .including extra-vehicular activities, • 

re entry and recovery. 

Training equipment and simulatorssshall be qualified to requirements consistent with their ap.21ication and interfaces with other equipment as specified in the contract end items s,oecifications. 

4.1.2.9 Test 0erational Support(SLEOSSIlliquirements 

icormal qualification of the overall TOSS segment (equipment, 

personnel and procedures) shall be dem=strated by successful completion, 

of the functional development testing and compatibility testingccalled out 

in Section 4.1.1.9. Qualification tests are required on new equipment and 

significantly modified equipment to demonstrate proper performance in the 

environment in which the equipment is normally required to function. 

Experiment support equipment such as ground targets and special 

receiving facilities shall to qualified to meet the functional requirements 

of the experiment, the loca installation environment and. the operational 

life requirements specified in the e::;:perItment. 

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Effectiveness (Reliability) T2 lin • All testing performed on the MOL program is considered a part 

of the reliability effort. However, certain tests such as extended time 

tests, stress limit tests, and reliability tests are considered effectiveness tests. Extended time tests consist of cycling the component or subsystem to the critical environments such as vibration, temperature and 

altitude, to determine the safety margin of the equipment with respect to 

time. Stress limit tests consist of increasing the qualification test 

level until failure occurs, thereby determining the margin of safety with 

respect to stress level. Extended time and stress limit tests shall be 

phased in with the qualification test program. 

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• 4. 1.4 Acceptance and Flight Readiness Tests 

4. 1. 4. 1 Acceptance Test Requirements 

Acceptance tests shall be performed to improve equipment 

reliability by disclosing workmanship defects in time to permit corrections 

prior to end use of the equipment. These tests are applicable to all 

contract end items and deliverable equipment. The test conditions shall 

be comparable to end use environments and severe enough to detect and 

eliminate early-life failures bu: not so severe as to cause fatigue or 

wear out. A thermal-vacuum and a vibration acceptance test shall be 

conducted on the component or subsystem level. Other tests shall be 

required if the equipment is sensitive to other environments and workmanship errors are not readily detected by normal inspection methods. A 

thermal-vacuum acceptance test shall be performed at the system segment 

level where applicable. Acceptanee Tests will be sufficient to assure 

Flight readiness test integration. 

4. 1. 4. 2. MOL System Flight Readiness Test Requirements 

EMI, electrical and mechanical compatibility tests, functional 

operations and electrical and mechanical compatibility tests, functional 

operations and readiness tests performed at the launch site will constitute 

Flight Readiness Tests. Flight Readiness will be determined by these 

tests, plus the acceptance of the various system segments based on their 

acceptance tests. 

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4.1.4.3 Orbiting Vehicle Requirements 

The acceptance of the laboratory, crew equipment and experiment 

system segments for the particular flight mission. objectives together with 

a simulated Gemini B,transtage shall be based on mechanical, electrical, 

thermal, electromagnetic interference, and functional operational tests 

performed after integration of these segments to form the complete orbiting 

vehicle. 

4.1.4.3.1 Rendezvous Mission VehicleS 

The chase and target orbiting vehicles shall be acceptance 

tested at the system segment level with the mission peculiar equipment 

accepted at the subsystem and/or component level. In addition, a physical 

mating and separation. of the orbiting vehicles shall be accomplished to 

• demonstrate compatibility and proper functioning of all mechanical, plumbing and electrical connections, 

4.1.4.4 Laboratory'Vehicle Requirements 

The laboratory vehicle system segment shall be acceptance tested 

at the system segment level. 

4.1.4.5 Gemini B Requirements 

The Gemini B system segment shall be acceptance tested similar 

to the acceptance tests performed for NASA. Gemini but modified where necessary 

by MOL environmental requirements. In general, all components and/or subsystems shall have a vibration and a thermal-vacuum test performed as part 

of the acceptance test. In addition, the Gemini B system segment shall be 

acceptance tested to thermal-vacuum conditions. 

4.1.4.6 Experiments Requirements 

The experiments shall be. acceptance tested at the sub-segment 

level using as a basis the environmental requirements. 

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• 4.1.4.7 Titan III Requirements 

The Titan III system segment shall be acceptance tested to the 

requirements of ARSSD Exhibit 62-166A, "Environmental Requirements 

Specification, Program 624A", Revision.A dated 1 July 1964. The Titan III 

transtage acceptance tests shall be modified. for the on-orbit functions and 

the environments. 

4.1.4.8 Crew and Crew Equipment Requirements 

The 3C-,T c, i crew equipment shall be acceptance tested 

at the component and/or subsystem level. These requirements will be 

detailed in as. AFAKIO/AFEFTC environmental requirements specification exhibit 

for the crew and crew equipment. In general, the components and/or subsystems will be acceptance tested to vibration and thermal-vacuum conditions 

while the system segment will be tested to thermal-vacuum conditions only. 

Training equipment and simulators shall. be acceptance tested to 

requirements of the contract end item s-cecification and by complete functional 

operation. Compatibility with other subsystem and segments shall be demonstrated in all planned sequences and modes of operations. 

4.1.4.9 221LC2perational EkpoortSegmenTOSS)11quirements 

Formal. acceptance of the overall TOSS shall be based on the 

successful completion of the functional development testing and compatibility testing called out in. this section- Formal acceptance of individual 

new equipments is required and shall normally occur following installation 

of the equipment - in its use location and functional testing to verify 

specified performance .has been conducted. 

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• 4. 2 MOL System Flityht Test Requirements 

4. 2. 1 Test Program Description 

The complete MOL System Flight Test and Evaluation consists,of formal 

testing ,and evaluation spanning the integration of all system segments into a.cornplete system in the final operational configuration.and environment. All MOL 

System Flights shall be.launched from ETR with suitable instrumentation employed. 

to determine the, system functional-performance, operability,. and compatibility of 

the system segments. During the conduct of this phase of testing, system performance shall be compared to paragraph 3.0 Requirements of Part I of CEI 

Specifications, where .test/veeifications must be•accomplished during system 

flight testing. 

4. 2. 2 Sub-orbital Flight 

The first flight shall be unmanned and sub-orbital. The Gemini B 

employed shall have .operab?..e .subsystems, but.the Laboratory shall be only 

structurally complete. The Gemini B shall be separated from the .laboratory 

for retro, reentry, and recovery downrange. The primary. objective of this test 

is to evaluate the initial performance of the MOL system, in relation to the-requirements and. operability goals, under. conditions and .environments closely 

approximating those of an actual mission. :[n particular, the. test objectives 

should include: verification.of the.aeromechanics and launch environments of the 

Titan-IIIC, Laboratory and Gemini B combination; as well as safety of flight; 

laboratory -subsystems. op,.?;ration; and.operational readiness of the ground and 

flight systems„ 

4. 2.3 Orbital Flights 

The second MOL flight (first orbital. flight) shall be -either ..unrnanned.or 

manned with orbital- characteristics corresponding to the mission. The Laboratory 

shall incorporate critical subsystems for initial.evaluat4on.and a Gemini B with 

.fully operable subsystems. Tree .flight shall be of filloi° t o r bital duration. The 

mission duration .shall be dependent upon Laboratory Subsystem status. The 

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Gemini B shall be separated for retro, reentry, and recovery in a primary 

recovery area. This effort shall demonstrate the.initial orbital capabilities .of 

the Gemini '13 and Laboratory •systems and initially demonstrate the Test Operational 

Support system. As a manned mission, the flight will also allow a.preliminary 

check oforbital.capability.of the crew, crew transfer to the Laboratory,. and the 

laboratory subsystems. Verification. of Gemini B Subsystems will be 

accomplished for launch, a .short duration.on.-orbit mission, reentry, and recovery. 

The third flight shall be manned and programmed for a 30-day orbital 

flight for demonstration.of the Orbiting Vehicle system, as.well as the capability 

of the -TOSS to support a .sustained orbital operation. This flight will incorporate 

primarily biomedical, human performance experiments,. image velocity compensation, and target observation experiments, with other.experiments..on-noninterference and .schedule permitting:bases. 

Subsequent manned flights shall. include the. complete experiment. payload 

required for demonstration of mission objectives. Because .of payload limitations, 

all primary experiments cannot be carried on.any one flight. One.of the .scheduling 

.objectives shall-be to install each primary experiment aboard at least two flights. 

Secondary •technclogy experiments shall be programmed so as .to 

utilize .the available factors of weight, volume, power, schedule, and .crew duty 

cycles, .in substantial accordance with.their priority assigrunents. 

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4. 2. 4 Rendezvous Test Missions 

The rendezvous mission shall be accomplished late in the flight 

test program with a target orbiting vehicle and a chase orbiting vehicle. 

The experiment payload and equipment will be compatible with the vehicle 

capability and generally•consist of biomedical monitoring, human performance, extravehicular activity, vehicle and experiment maintenance, 

electromagnetic monitoring and observation of ground targets. These experiments may satisfy the objectives of the Navy integrated ocean surveillance experiment. The objective of the mission is to remain on orbit 

up to sixty days after exch2mging one crew member, and transferring expendables such as atmosphere gas and electric power as required, while 

docked with the target orbiting vehicle. 

The chaser orbiting 'vehicle shall be launched 15 to 30 days after 

the target vehicle. A tail to tail docking shall be accomplished, after 

which one crewman from each shall exchange positions. Connections 

shall be made for transfer of expendables and power and monitoring and 

signal circuits. The chaser orbiting vehicle normally shall remain docked 

with the target for the remaining time on orbit. The returning crew shall 

return with accumulated data parcels in one of the Gemini B' s, leaving 

both orbiting vehicles to be operated by one crew consisting of an "old" 

and "new" member, who will return in the remaining Gemini B. 

4. 3 Engineering Changes 

• Deficiencies encountered during the system tests shall be 

completely detailed and Engineering Change Proposals (ECP's) or System 

Change Notices (SC 3's) shall be issued, approved and accomplished for 

appropriate corrective action, 

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5.0 PREPARATION FOR DELIVERY 

This section covers requirements for the preparation for delivery 

which are peculiar to the system (other than standard practice). Specific 

requirements for such non-standard practices shall.be.contained in appropriate 

Contract End Item Specifications. These shall, nclude _unusual. requirements 

for: 

. a. Special pressure, thermal, .or other environmentaLcontrol 

required during transportation, 

b. Peculiar hoists, handling dollies, containers, and/or 

protective covers. 

C, Safety devices for ordna.ncetigniters. 

d. Special methods , load, shock, , etc. ,.limitation during,the 

handling proce s s. 

5. 1 Paclasta.g for Gemini B.and Labor.aloa. 

P..ecommendations shall be made for. the preservation, .packaging, 

packing,. marking, and. etc rage/ stowage requir ernents..for the life supporteitems, 

, equipment, :experiments.. and equipment. spares for Gemini B (See 3. 3. 3), . and 

. for both.the pressurized and the unpressurized•.sections .of the.Laboratory 

(See .3. 3. 2). .The recommendations. shall- reflect investigation for possible use 

of Space Packaging studies. and techniques developed in connection.with.other 

.manned programs. Environmental criteria, and packaging, hazards peculiar 

.to each .environment shall.be .defined„ .and testing programs, as required..shall 

be outlined to, as sui eretripatilility•of the packaging.materials•and methods that 

• are recommended with .thce environments, Consideration shall .be given .to 

compatibility•of•the packaging•wtth the crew handling restraints.imposed.by 

protective .clothing,. etc. alternative utilization..of packaging materials., disposition of packaging waste, dimensional definition of each storage space, the 

limitations imposed on individual package. design by.storage considerations 

such.as special. racks, and measures for package restraint within the storage 

space. 

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6.0 NOTES 

7. 0 CONTRACTOR DATA AND REPORTS 

Acquisition of data and reports will be in accordance with 

AFSCM 310-1/AFLCM 310-1. 

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8.0 SPECIFICATION TREE 

The MOL Specification Structure shall be depicted in.the form of a 

Tree. The following convention shall, apply for the construction of the 

Specification Tree. 

A CEI. Specification shall be _shown by a solid,box.for each CEI 

Specification to be prepared. (A CEI Specification is normally prepared for 

each piece of hardware or equipment which is accepted by the Air Force on a 

Form DD-250.) 

Under the AFSCIVI 375.-1 Specification System,. functional, type specifications will not be prepared.. The information which would have been. in. this 

.type of. specification will now be included in. the next higher. level CEI Specification or. the top system. specification. 

An example of a functional specification as used in.the past would 

be a specification describing all AGE. Since -AGE is accepted by'the Air Force 

.piece by piece on.s. Form .DD-250, a -CEI Specification will be required for 

. each piece of AGE accepted on a DD-250, and a .functional specification is no 

longer required. 

To assist in.rieveloping., an organization and structure to the Specification Tree (Once a long row of CEI specifications all on the same level is.not 

very meaningful), a dotted box .will be usedwhere-a. •document does not actually 

exist but. where it is desired to establish another. structured level to the Tree. 

As a general rule, a dotted box should be used wherever a functional 

subsystem can be identified which does not require ..a CEI Specification (i. e. , 

is not accepted. on a Form DD-250). 

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10.1

S 

APPENDIX A 

APPLICABLE DOCUMENTS 

FOR THE 

MOL SYSTEM PERFORMANCE/DESIGN REQUIREMENTS 

GENERAL SPECIFICATION • 

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PREFIX KEY FOR APPENDIX A 

CV Civil 

DA 

- 

Data and Reports 

DG Design and Construction 

DR Design and Construction Requirements 

EE 

- 

Electrical 

EI Electromagnetic Interference 

GP Human Performance (Guidance) 

HP Human Performance (Applicable) 

HY Hydraulic 

IC 

- 

Interchangeability 

IM Identification and Marking 

MA Maintainability 

MP 

- 

Materials, Parts and Processes 

MS Maintenance Support 

SE System Effectiveness 

SF 

- 

Safety 

SS Supply Support 

ST 

- 

Storage 

TR Transpo:qability 

WK Workmanship 

A -2 
murimuffigninawassimarimengtes 

APPENDIX B 

• 
Only the Principal 

System CEIs will be 

called out here and 

references will be 

made to other CEI 

lists covering the 

minor CEIs 

P-3, and P-8 CEI (Typical) 

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10.2 

Appendix B 

3. 1. 2. 3 Contract End Item List 

3.1.2.3.1 Standard Flight 

3.1.2.3.1.1 MOL Flight Vehicle CEI 

3.1.2.3.1.2 Laboratory Vehicle CEI 

3.1.2.3.1.3 Gemini B CEI 

3. 1.2.3. 1. 4 Flight Crew Equipment CEIs 

3. 1. 2.3.1.5 MOL Experiment CEIs 

3. 1. 2.3.1.5. 1 MOL Experiments P-1, P-2, 

3. 1.2..3. 1. 5.2 MOL Experiment P-4 

3.1.2.3.1.6 

3. 1. 2.3.1.7 

3. 1. 2.3.1.8 

3.1. 2.3.1.9 

MOL Test Operations System CEIs 

MOL Facilities CEIs 

Lab Vehicle AGE CEI4 

Gemini B AGE CEIs 

3.1.2. 3. 1. 10 Experiments AGE CEIs 

3. 1. 2.3.1.11 TOSS AGE CEIs 

3. 1. 2. 3.2 Special for Flight 

3.1.2.3.2.1 

3.1.2.3. Z. 2 

3. 1. 2.3. Z. 3 

3.1.2.3.2.4 

3.1.2.3.2.5 

3.1.2.3.2.6 

3.1.2.3.2.7 

3.1.2.3.2.8 

Modification Group 

Modification Group 

Modification Group 

Modification Group 

Modification Group 

Modification Group 

Modification Group 

ModificatIcn Group 

List for Flight 1 

List for Flight 2. 

List for Flight 3 

List for Flight 4 

List for Flight 5 

List for Flight 6 

List for Flight 7 

List for Flight 8 
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10. 3 

• 

3. 3..1. 3 Interface Requirements 

3. 3. 1. 3. 1 Scope 

Only the major inter-contractor physical,. functional, and procedural. interface s. will be identified .and . controlled within. the ICD (Interface 

Control Document) system indicated in this section. The minor inter-contractor 

:interfaces will, be identified .and. controlled by a subordinate document which will 

be. called out within. each of the identified ICD Areas. An associate .contractor's 

internal interfaces (with his own or his subcontractor's interfaces) which .do not 

affect. another, associate .contractor will not be covered by this 1CD system. 

Such internal interfaces will be included in the individual associate contractor's 

CEI specifications and will be controlled by that contractor's internal interface 

control system, 

3. 3. 1. 3. 2 General 

Each Interface Control Document Area shown in this Appendix 

represents a .category of interfaces .within .which separate Interface Control 

Documents will be prepared, negotiated, approved, and enforced for each 

interface involving more than one associate contractor. 

3. 3.1. 3. 3 Outline 1___u_ILLrnerits 

The groupings in the list of ICD Areas which follow are in the 

general.order,of the principal associate contractor involved in. the interface. 

This specification will contain. only a description of the general nature of the 

interface and an outline of the document contents for each interface .area 

identified. A typical example of such an outline follows: 

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1CD Area 1: Gemini B/Laboratory Interface 

(Applicable Interface Control Documentation No. 

1. Scope 

1.1 General Description of Interface Area 

1.2 Intended Usage 

1.3 Contractor Responsibilities and Role 

1,4 Interface Drawings 

1.5 Changes to Specifications 

2. Applicable Documents 

2.1 Subordinate ICDs 

3, Interface Requirements 

3.1 General 

3.2 Mechanical Interface 

3.3 Electrical/Electronic Interface 

3.4 Environmental Control 

3, 5 Crew Interacticns 

3.6 Aerospace Ground Equipment Interface 

3.7 Data Transfers 

3.8 erodynanics 

3.9 Mass Property Data 

3.10 Effectiveness Apportionments 

3.11 Interchangeability 

3.12 Special Features 

3. 12. 1 Adapters 

4. Test Criteria and Interface Inspection Requirements 

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3 3 1.3.4 ICD Area List 

ICD Area 1: 

ICD Area 2: 

1CD Area 3: 

ICD Area 4: 

ICD Area 5: 

ICD Area 6: 

ICD Area 7: 

ICD Area 8: 

ICD Area 9: 

ICD Area 10: 

ICD Area 11: 

ICD Area 12: 

1CD Area 13: 

ICD Area 14: 

ICD Area 15: 

ICD Area 16: 

ICD Area 17: 

1CD Area 18: 

ICD Area 19: 

ICD Area 20: 

1CD Area 21: 

ICD Area 22: 

ICD Area 23: 

IC:D Area 24: 

ICD Area 25: 

Laboratory/ Ear,e rim ents 

Laboratory/Space Crew 

Laboratory/ T -IIIC 

Laboratory/Modification 

Laboratory/Modification 

Laboratory/Modification 

Laboratory/Modification 

Laboratory/Modification 

Laboratory/Modification 

Laboratory/Modification 

Laboratory/Modification 

Laboratory/ TOSS 

Group List Per Flight 1 

Group List Per Flight 2 

Group List Per Flight 3 

Group List Per Flight 4 

Group List Per Flight 5 

Group List Per Flight 6 

Group List Per Flight 7 

Group List Per Flight 8 

Gemini 

Gemini 

Gemini 

Gemini 

Gemini 

Gemini 

Gemini 

Gemini 

Gemini 

Gemini 

Gemini 

Gemini 

CE-nini 

B/Laboratory 

B /Experiments 

B /Modification Group 

B/Modification Group 

B /Modification Group 

13/Modification Group 

B/Modification Group 

B/Modification. Group 

B /Modification Group 

B /Modification Group 

B/Space Crew 

B/TOSS• 

B/ T -IIIC 

List 

List 

List 

List 

List 

List 

List 

List 

Per 

Per 

Per 

Per 

Per 

Per 

Per 

Per 

Flight 1 

Flight 2 

Flight 3 

Flight 4 

Flight 5 

Flight 6 

Flight 7 

Flight 8 

ICD Area 26: 

ICD Area 27: 

lCD Area 28: 

:LCD Area 29: 

1CD Area. 30: 

1CD Area 31: 

ICD Area 32: 

1CD Area 33: 

1CD Area. 34: 

ICD Area 35: 

ICD Area 36: 

ICD Area 37: 

11.CD Area 38: 

Expel Iments 

.,E).rpe riments 

Expe rim ent s 

Experiment/ 

'E xpee im ents 

Expe:irnents 

Expe irnents 

Experiments 

E e r im exits 

Experiment 

Experiments 

Experiments 

Ex-p e im en t 3 

(Space Crew 

/ TOSS 

/Data Management 

Experiments 

/ T -MC 

/Modification Grthip 

/Modification Group 

/Modification Group 

/Modification Group 

/Modification Group 

/Modification Group 

/Modification Group 

/Modification Group 

List Per Flight 1 

List Per Flight 2 

List Per Flight 3 

List Per Flight 4 

List Per Flight 5 

List Per Flight 6 

List Per Flight 7 

List Per Flight 8 

ICD Area 39: Data Management System/Laboratory 

ICD Area 43: Space Crew/TOSS 

1CD Area 41: Space Crew/Modification Group List Per Flight 1 

ICD Area '1.2: Space Crew/Modification Group List Per Flight 2 

1C:ID Area Space Crew/Modification Group List Per Flight 3 

£01) .•-,.rea 44: Space Crew/Modification Group List Per Flight 4 

ICD Area '15: Space Crew/Modifica,tion Group List Per Flight 5 

ICD Area 45: Space Crew/Modification Group List Per Flight 6 

ICD Area 47: Space: Crew/Modification Group List Per Flight 7 

ICO Area /:P: Space CrewlivIodification Group List Per Flight 8 

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fir 

1CD Area. 4 TOSS T 

ICD Area 50: TOSS/Modification Group List Per Flight 1 

ICD Area 51: TOSS/Modification Group List Per Flight 2 

lOT) Area 5: TOSS/Modification Group List Per Flight 3 

ICD Area 53: TOSS/Modification Group List Per Flight 4 

ICD Area 54: TOSS/Modification Group List Per Flight 5 

ICD Area 55: TOSS/Modification Group List Per Flight 6 

1C1) Area 56: TOSS) Modific,ation Group List Per Flight 7 

10D Area 57: TOSS/Modification Group List Per Flight 8 

1C1) Area 58: TOSS/Data Management System 

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