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PRELIMINARY PERFORMANCE/ 

DESIGN REQUIREMENTS 

FOR THE 

MANNED ORBITING LABORATORY SYSTEM 

(MOL) 

GENERAL SPECIFICATION FOR 

NOVEMBER 1964 

HEADQUARTERS 

SPACE SYSTEMS DIVISION 

AIR FORCE SYSTEMS COMMAND 

UNITED STATES AIR FORCE 

SPECIAL HANDLING REQUIRED 

NOT RELEASABLE TO FOREIGN NATIONALS, 

DOWNGRADED AT 12 YEAR INTERVALS. 

NOT AUTOMATICALLY DECLASSIFIED 

DOD DIR 5200.10 

ATTACHMENT 

-.L1S1) -6; -1;1 -E0+4FIDE414146- SSM 

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TABLE OF CONTENTS 

Section Pa ge 

1. 0 SCOPE 1-1 

1. 1 Descriptive Title 1- 

1. 2 Purpose 1-1 

2. 0 APPLICABLE DOCUMENTS 2-1 

2. 1 Specifications and Standards 2- : 

2. 1. 1 MIL Specifications 2- 

2. 1. 2 Air Force BMD/BSD/SSD Exhibits 2-4 

2. 1. 3 Federal Standards 2- 5 

2. 2 Manuals, Regulations, Publications 2-5 

2. 2. 1 SSD Documents 2-5 

2. 2. 2 Air Force Regulations (AFR) 

2. 2. 3 Air Force Manuals (AFM) 

2. 2. 4 Air Force Procurement Instructions (AFPI) 2-o 

2. 2. 5 Air Force Pamphlets (AFP) 2-o 

2. 2. 6 AFSC Regulations (AFSCR) 2- 7 

2. 2. 7 AFSC Manuals (AFSCM) 2- 7 

2. 2. 8 Bulletins 2- 7 

2. 3 Other Documents 

3. 0 REQUIREMENTS 3-1 

3. 1 P-rformance 3-1 

3. 1. 1 Performance Characteristics 3-5 

3. 1. 1. 1 System Characteristics 3-5 

3. 1. 1.2 Logistics 3-14 

3. 1. 1. 3 Personnel and Training 3-15 

3. 1. 2 System Definition 3-17 

3. I. 2. 1 System Engineering Documentation 3-17 

3. 1. 2. 2 System Segment List 3 - 2 

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TABLE OF CONTENTS (Cont) 

Section Page 

3. 1. 2. 3 Contract End Item List 3-29 

3. 1. 2. 4 Interfaces 3-30 

3. 1. 3 System Effectiveness 3-31 

3. 1. 3. 1 Effectiveness Measures 3-31 

3. 1. 3. 2 Maintainability 3-36 

3. 1. 3. 3 Useful Life 3-37 

3. 1. 3. 4 Environment - Natural and Induced . . 3-38 

3. 1. 3. 5 Transportability and Handling 3-38 

3. 1. 3. 6 Human Performance 3-39 

3. 1. 3. 7 Safety 3-40 

3. 1. 3. 8 Dangerous Materials and Components 3-41 

3. 1. 3. 9 Noise and Vibration 3-41 

3. 1. 3. 10 Life Support 3-41 

3. 2 System Design and Construction Standards 3-43 

3. 2. 1 General Design and Construction Requirements . 3-43 

3. 2. 1. 1 Selection of Specifications and 

Standards 3-43 

3. 2. 1. 2 Materials, Parts, and Processes 3-44 

3. Z. 1. 3 Standard and Commercial Parts 3-45 

3. 2. 1. 4 Moisture and Fungus Resistance 3-45 

3. 2. 1. 5 Corrosion of Metal Parts 3-46 

3. 2. 1. 6 Interchangeability and Replaceability . 3-46 

3.2. 1. 7 Workmanship 3-47 

3. 2. 1. 8 Electromagnetic Interference 3-48 

3. 2. 1. 9 Identification and Marking 3-48 

3.2. 1. 10 Storage 3-49 

3. 2. 2 Design Disciplines 3-51 

3. 2. 2. 1 Electrical 3-51 

3. 2. 2. 2 Mechanical 3-51 

3. 2. 2. 3 Hydraulic and Pneumatic 3- 51 

3. 2. 2. 4 Civil 3-51 • 

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3. 3 Performance Allocations 3-5 s 

3. 3. 1 Orbiting Vehicle System Segment 3-5 , 

3-5 

3-5 - 

.3. 3. 2 La...oratory Vehicle System Segment 3 - 

3. 3. 2.. Allocated Performance and Design 

Requirements 3-t 

3. 3. 2. 2 Peculiar Performance and Design 

Requirements 

3. 3. 2. 3 Functional Interfaces 

3. 3. 2. 4 Contract End Items 

3. 3. 3 Gemini B System Segment 

3. 3. 3. 1 Allocated Performance and Design 

Requirements 3-99 

3. 3. 3. 2 Peculiar Performance and Design 

Requirements 3-100 

3. 3. 3. 3 Functional Interfaces 3- 11.: 

3. 3. 3. 4 Contract End Items 3-112 

3. 3. 4 Experiment System Segment 3-113 

3. 3. 4. 1 Allocated Performance and Design 

Requirements 3-11 ' 

3. 3. 4. 2 Peculiar Performance and Design 

Requirements 3- 113 

3. 3. 4. 3 Functional Interfaces 3-13c. 

3. 3. 4. 4 Contract End Items 3- 1 3i=, 

3. 3. 4. 5 Experiments Peculiar Ground System 3-137 

3. 3. 5 Flight Crew and Crew Equipment Systems 

Segment 3-139 

3. 3. 5. 1 Allocated Performance and Design 

Requirements 3-139 

3. 3. 1. 1 Allocated Performance and Design 

Requirements 

3. 3. 1. 2 Peculiar Performance and Design 

Requirements 

3. 3. 1. 3 Functional Interfaces 

3. 3. .. 4 Contract End Items 

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TABLE OF CONTENTS (Cont) 

Section Section 

3. 3. 3. 5. 2 3. 5. 2 Peculiar Performance and Design Peculiar Performance and Design Peculiar Performance and Design 

Requirements Requirements 

3. 3. 3. 5. 3 3. 5. 3 Functional Interfaces Functional Interfaces 

3. 3. 3. 3. 5. 4 3. 5. 4 Contract End Items Contract End Items Contract Endd Items 

3. 3. 3. 8. 1 3. 8. 1 ITL, System ITL, System 

3. 3. 3. 8. 2 3. 8. 2 Industrial Area Industrial Area 

3. 3. 8. 3 Telecommunications, 

Control Facilities 

3. 3. 8. 3 Telecommunications, Tracking & 

Control Facilities 

Tracking & 

4. 1 Ground Test Requirements 4-1 

4. 1. 1 Development Tests 4-1 

4. 1. 2 Qualification Tests 4-7 

4. 1. 3 Effectiveness (Reliability) Testing 4-11 

4. 1. 4 Acceptance and Flight Readiness Tests 4-13 

4. 2 MOL System Flight Test Requirements 4-17 

A tch. 6 CONFIDENTIAL 

 8 Facilities System Segment 3-195 

3-195 

3-196 

3-197 

4. 0 PERFORMANCE/DESIGN VERIFICATION AND TEST 4-1 

4. 2. 1 Test Program Description 4-17 

4. 2. 2 Sub-Orbital Flight 4-17 

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TABLE OF CONTENTS (Cont) 

Section Pa zE 

4. 2. 3 Orbital Flights 4- 1 

4. 2. 4 Rendezvous Test Missions 4-1 , 

4. 3 Engineering Changes 4-21 

PREPARATION FOR DELIVERY 5-1 

5. 1 Packaging for Gemini B and Laboratory 5-1 

NOTES 6-1 

CONTRACTOR DATA AND REPORTS 7-1 

SPECIFICATION TREE 8-1 

APPENDICES 10-1 

10. 1 Appendix A - Interface Requirements 10-2 

10. 2 Appendix B - Environmental Criteria Specification 

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5. 0 

6. 0 

7. 0 

8. 0 

10.0 

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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 has been 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 accomplishment 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 improve 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. 

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2 0 APPLICABLE DOCUMENTS. 

Military specifications, standards, exhibits, manuals, regulations, publications, bulletins, pamphlets, and other documents are herein 

specified as appropriate to obtain first tier compliance for the MOL System. 

Only specifications affecting either the entire system or the whole of a syster-. 

segment are included in this specification and then are only applicable to the 

extent provided in the section in which they are called out. 

A two letter prefix cod, is provided to assist in associating 

those documents which are applicable to a particular type of specification 

requirement. This prefix code is indicated in the applicable sections of this 

specification, such as Safety, General Design and ConstructionRequirements. 

Workmanship, etc. The key to the prefix code follows: 

CV Civil 

DG Design and Construction (Guidance only) 

DR Design and Construction Requirements 

EE Electrical 

EI Electromagnetic Interfe rence 

GP Human Performance (Guidance) 

HP Human Performance (applicable) 

HY Hydraulic 

IM Identification and Marking 

MP 

- 

Materials, Parts, and Processes 

MS Maintenance Support 

SF Safety 

ST Storage 

WK 

 

Workmanship 

2. 1 SPECIFICATIONS AND STANDARDS. 

2.1.1 MIL Specifications. 

MIL-A-8421B General Specification for Air 

Transportability Requirement, 

5 May 1960 • -C-GRFIDERTIAL Atch. 

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4 

MIL-F-7179 

HY - MIL-H-25475A 

HP - MIL-H-27894A 

Connectors, Electric, AN Type 

Control Configuration and Markings 

Colors, Aero Lignts and Lighting 

Equipment, General Specification 

for 

Connectors, Electric, Circular, 

Miniature Quick Disconnect, 

10 Aug 1962 

Calibration of System Requirements 

Safety Hazard Analysis 

Drawings, Engineering Assoc. 

Lists 

Data, QQPRI 

Electronic Equipment, Ground, 

General Requirement for 

Environmental Testing, Aeronautical and Assoc. Equipment, 

General Specification for 

Electronic Equipment, Airc raft, 

General Specification for 

Electro-Electronic System Compatibility and Interference Control 

Requirement 

General Specification for Electronic Modules 

Electrical and Electronic Equipment and Systems, Guided Missiles, Installation, General Specification for 

Finishes and Coatings, Gene ral 

Specifications for Protection of 

Aerospace Weapons Systems, 

Structures and Parts 

Hydraulic Systems, Missile, 

Design, Installation Test and 

Data Requirement, General Requirement for 

Human Engineering Required for 

Aerospace Systems and Equipment 

EE - MIL-C-5015 

IM - MIL-C-18012 

IM - -25050 

EE - MIL-C-26482 

(Suppi 1) 

MS - MIL-C -45662A 

SF - MIL-D-9310 

MIL-D-70327 

HP - MIL-D-26239A 

EE - MIL-E-4158E 

MIL-E-5272C 

DR - MIL-E- 5400F 

EE - MIL-E-6051C 

EE - MIL-E-19600 

EE - MIL-E-0025366B 

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Technical Information File of 

AGE for Air Weapon System 

Inspection System Requirement 

Interference Control Requirements Aircraft Equipment 

Interchangeability and Replaceability of Component Parts 

Int.:rference Control Requirement, Aeronautical Equipment 

Mooility Requirement, Ground 

Support Equipment, General 

Specification for 

Missiles, Guided: Design and 

Construction, General Specification for 

Maintainability Requirement for 

Aerospace System and Equipment. 

with Exceptions as Specified in 

Attachment 1 to SSD Exhibit 62 -

170 

Nomenclature and Nameplates for 

Aeronautical Electronic and Associated Equipment 

Preservation, Methods of 

Pneumatic Systems, Aircraft, Design, installation and Data Requirement for 

Packaging, Air Weapon Systems. 

Specification and General Design 

Requirement for 

Quality Control System Requirements 

Handling Ground Equipment, General Requirements for 

Support Equipment, Aeronautical, 

Special General Specification for 

the Design of 

Qualified Parts Lists 

Safety Engineering of Systems, 

and Associated Subsystems and 

Equipment 

• MIL-HDBK-300 

WK - MIL-I-4520B 

EI - MIL-I-6181B 

MIL-1-8500/3 

EI - MIL-I-26600 

DR - MIL-M-8090C 

DR - MIL-M-8555 

GP - MIL-M-26512C 

• IM - MIL-N-18307 

ST - MIL-P-116C 

HY - MIL-P-5518C 

(Suppi. 1) 

DR - MIL-P-9024B 

MS - MIL-Q-9858A 

DR - MIL-5-852B 

MIL-S-8512B 

MIL-S-38000 

SF - MIL-S-38130 

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IM - MIL-STD-130A Identification Marking of U.S. • 

Military Property 

DG - MIL-STD-143A Specifications and Standards, 

Order of Precedence for the 

Selection of 

IM - MIL-STD-195 

MIL-STD-210 

MIL-STD-447 

Marking of Connections for Electric Assemblies 

Climatic Extremes for Military 

Equipment 

Definition of Interchangeable Substitute and Replacement Items, 

29 May 1962 

IM - MIL-STD-795 Colors 

GP - MIL-STD-803 Human Engineering De sign C rite ria 

for Aerospace Systems and Equipment 

MIL-STD-810 Environmental Test Methods for 

Aerospace and Ground Equipment 

El - MIL-STD-826 Electromagnetic Interference Test 

Requirement and Test Methods 

IM - MIL-STD-1247 Identification of Pipe, Hose, and 

Tube Lines for Airc raft, Missiles, 

Space Vehicles, andAssociated 

Support Equipment and Facilities 

HP - MIL-T-27382 Training Equipment, Subsystem, 

Technical Data, Preparation of 

EE - MIL-W-8160D Wiring, Guided Missiles, Installa- 

(Amend. 1) tion of, General Specification for 

DG - MIL-W -9411A System Classification of Critical 

Characteristics 

IM - MS-24123A Plate Identification 

MP - MS-33586A Metals, Definition of Dissimilar 

Air Force BMD/BSD/SSD Exhibits. 

IM - BMD 58-20A Gas, Fluid Line Identification 

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Training Equipment Procurement for AFBM and Military 

Space Systems 

Color Requirement for Space System Ground Equipment and Facility Items 

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GP - BMD 59-17C 

IM - BMD 59-31 

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GP - BMD 60-1 

GP - BSD 61-99 

GP - BSD 63-19 

IM - SSD 61-70A 

SSD 61-81 

WK - SSD 62-117 

SSD 62-128 

SSD 62-130 

GP - SSD 62-131 

GP - SSD 62-162 

SSD 62-166A 

ST - SSD 62-181 

SSD 63-14 

DR - SSD 63-3 

PSS Testing for Ballistic. NlissiI, 

and Space Systems 

Human Engineering, General 

Specification 

PSS (Personnel Subsystem) 

Identification Requirements 

Compliance Specification 

Reliability and Quality Assurancf. 

Program Required 

Titan IL AGE Design Req. 

Facilities Requirement, General 

Specification 

PSS Requirement, General Specification 

Basic Data for PSS Development 

Specification 

Environmental Requirement 

Specification Rev. A, 1 July 1964 

Preservation to Packaging, Packing and Container Marking of 

Equipment, and Spare Parts for 

Shipment and Storage for Space/ 

Satellite Systems 

Spare Parts Provisioning Requirem' 

Engineering for Transportability 

2. 1. 3 Federal Standards. 

IM - FED-STD-5 

IM - FED-STD-595 

Standard Guides for Preparation of 

of Item Identifications by Government Suppliers 

Colors 

a. a MANUALS, REGULATIONS, PUBLICATIONS. 

2. 2. 1 SSD Documents. 

WK - SSD Pamphlet 

375-1-1 

Quality Assurance 

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2.2 Air Force Regulations (AFR). 

HP - AFR 30-8 Development of a Personnel Subsystem for Aerospace Systems 

SF - AFR 32-20 Responsibilities for Explosive 

Safety Program 

HP - AFR 50-19 Management of Training Equipment 

IM - AFR 71-6 Preservation, Packaging, Packing, and Marking Policy 

DG - AFR 73-1 Defense Standardization Program 

IM - AFR 74-2 Identify Calibrations Requirements 

of Systems, Subsystems & Equipment 

HP - AFR 84-7 Requirements for Contractor 

Operating Procedures and Flight 

C rews 

SF - AFR 160-3 Hazardous Noise Exposure 

2.2,3 Air Force Manuals (AFM). 

SF - AFM 32-3 

SF - AFM 32-6 

SF - AFM 71-4 

CV - AFM 8o-8 

AFM 88-2 

SF - AFM 127-201 

Accident Prevention Handbook 

Explosives Safety Manual 

Packaging and Handling of 

Dangerous Materials for Transportation by Military Aircraft 

Airfield and Airspace Criteria 

Definitive Designs of Air Force 

Structures 

Accident Prevention Handbook 

2.2.4 Air Force Procurement Instructions (AFPI). 

SF - AFPI 7-4047 Safety and Accident Prevention 

SF - AFPI 7-4048 Safety Precautions for Dangerous 

Mate rials 

2. 2.5 Air Force Pamphlets (AFP). 

Atch. 6 

NIP - AFP 88-002-1 Evaluation of New Materials and/ 

or Methods of Construction for Air 

Force Facilities • 

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• CV - 68-00a- i NI:s.,:ellau,...ous truLtio:Is and 

Criteria for Design and Constru, - 

tion of Air Force Facilities 

2. b AFSC Regulations (AFSCR). 

HP - AFSCR 80-16 Personnel Subsystems Program 

for Aerospace, Support & Command & Control Systems 

MP - AFSCR 400-3 Joint Use of Contractors' InProduction Support Materials and 

Operational Support Spares in 

Selected Missile Programs 

2.2.7 AFSC Manuals (AFSCM). 

• 

DR - AFSCM 80-1 Handbook of Instructions for Aircraft Designers, Vol I, II, III 

DR - AFSCM 80-3 Handbook of Instructions for Aerospace Personnel Subsystem Designers (NIAPSD) 

DR - AFSCM 80-5 Handbook of Instruction for Ground 

Equipment Designers (HIGED) 

DR - AFSCM 80-6 Handbook of Instructions for AGE 

Designers (HIAGED) 

DR - AFSCM 80-7 Handbook of instructions for Aer,)- 

space Vehicle Equipment Design 

DR - AFSCM 80-8 Handbook of Instructions for Missile Designers 

DR - AFSCM 80-9 Handbook of Instructions for Aerc)- 

space Systems Design 

DG - AFSCM 81-1 Specifications and Standards 

Manual 

AFSCM 310-1 Vol I and II - Management of 

(AFLCM 310-1) Contractor Data and Reports 

AFSCM 375-1 Configuration Management Durint! 

(All) Phase 

2.2.8 Bulletins 

ANA Bulletin 400T Electronic Equipment, Aircraft is 

Guided Missiles, Applicable Documents, Mar 1963 • 

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USAF Bulletin No. 515 Mate rial Review Proct•du res • 

MS - T.O. 33-1-14 

WADC TR 52-321 

Source and Maintenance Coding 

USAF Aeronautical and Supporting 

Equipment 

Material Inspection and Receiving 

Report "DD Form 250" 

Weapon System/Equipment Operations and Maintenance Records 

Defense Standardization Manual 

Requirements for Transport of 

Explosives 

NASA Life Science Data Book 

National Electric Code -1959 

General Safety Procedures for 

Chemical Guided Missile Propellants 

Repair, Calibration and Certification of Precision Measurement 

Equipment 

Anthropometry of Flying Personnel, 1950 dated Sept. 1954 

2. 3 OTHER DOCUMENTS. 

IM - AFLCM 65-3 

(Part IV) 

MP - ASPR 7-105.7 

MS - DCAS Checklist 

61-87 

DG DOD Manual 200A 

SF ICC Tariff No. 15 

EE NEC 

SF T.O. 00-11C-1-6 

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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 

Vehicle consists of a Laboratory, a modified Gemini spacecraft (Gemini B), 

and the transtage of Titan IIIC. This will be launched by Titan IIIC from 

Cape Kennedy. During the ascent to orbit the flight crew will be in the 

Gemini B, will 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 inspace 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-totail 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 flight 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 maneuvers, 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 1.2. essential to safe return 

will be monitored. Data from experiments, as well as telemetry of Orbiting 

Vehicle condition and flight 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 flight crew and mission 

control functions will be controlled from a mission control center (MCC). A 

network of tracking and data acquisition stations will provide world-wide 

communications 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 

flight 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 chase vehicle will be 

launched 15 to 30 days after the target vehicle. The chase vehicle 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 he by 

manual control and visual reference. Interchange of one flight crew member 

between chase and target Orbiting Vehicles will be accomplished and one 

Gemini B will return to earth. The two Laboratory Vehicles and a Gemini B 

will remain on orbit an additional full mission period. 

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a Upon completion of the mission, the flight crew will perior 

final checks of the condition of the Gemini capsule and activate those syste:-.1- 

required for flight 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 flight crew to the Gemini P. 

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 flight crew, Gemini B, and experiment data in a primary 

recovery area in the Atlantic Ocean or in the event of an emergency a sec - 

onclary recovery area in the Pacific Ocean. 

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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. L. 1 1. 1 Pre -Launch Preparation. 

This phase covers the period from arrival of systems at 

Cape Kennedy to the T - count on the launch pad. Pre -launch preparation 

will follow normal Titan Ill 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 T - count on 

the launch pad through lift-off. The launch countdown shall be 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 Flight Crew Launch Occupancy. 

The time to launch a MOL system after flight crew insertion 

in the Gemini B 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 flight crew enters the Gemini B. 

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3.1.1.1.2.3 Flight Crew Escape. 

Prior to lift-off, escape from the MOL Vehicle in the event 

of an emergency shall be by egress from the flight 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. 

3.1.1.1.3.1 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 Gemini B 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. M. perigee and 

160 N. M. apogee, then circularized at approximately 160 N.M. Nominal 

orbit inclination shall be 32°. 

3.1.1.1.3.4 Communication. 

The system shall provide communication between the flight 

crew in the Gemini B and the mission control center (MCC) during all portions of powered ascent. 

3.1.1.1.3.5 Flight Crew Escape. 

A flight crew escape system shall be provided which will 

allow safe escape and recovery if 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. M. circular orbit. Duration of 

the rendezvous mission will range up to 60 days. 

3. 1. 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. M. throughout the mission. • 

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

The system shall be capable of retrieving the MOL flight 

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

water landing sites. The abort procedure shall he 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. Flight 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 flight crew during the on-orbit 

phase and prior to occupancy for mission termination. 

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

Passage of the flight crew 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. 

3. 1. 1. 1. 4. 7 Mission Experiment Operations. 

The experiment equipment shall be operable by flight 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 of freedom. A capability for an on-orbit 

velocity increment of 500 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 flight 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 flight crew. 

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3.1.1.1.5.3 Retrofire Orientation. 

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

flight 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 N. M. , and downrange 400 N. M. 

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. A 

voice communication link shall be provided. 

3. 1. 1. 1. 6 Recovery. • 

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

Following water impact, the Gemini B shall float in a 

command-flight crew 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 flight crew, Gemini B, and data recovery shall be 

provided. 

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3.1.1.1.7 Rendezvous and Docking. S 

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 flight crew on-orbit duration up to 60 days. The MOL 

system shall have the capability of rendezvous and tail-to-tail docking of two 

Orbiting Vehicles. The MOL configuration for rendezvous and docking shall 

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

minimum modifications of the basic integral launch configuration. Occupancy 

of both laboratories shall be possible after rendezvous. 

3.1.1.1.7. Z 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 Maneuvers. 

The chase vehicle will acquire the target by radar. Following acquisition, a series of fine maneuvers will be made to place the 

target and chase vehicles in the appropriate relative position for commence - 

ment 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 flight crew performance 

Evaluation of on-orbit equipment, both vehicle and 

experimental 

Evaluation of over -all mission operation. 

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111 3. 1. 1. 1. 9 Operating Locations. 

3. 1. 1. I. 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 Laboratory Vehicle contractor's 

facility as appropriate. Those system segments of the Orbiting Vehicle 

which are supplied to the Laboratory 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. 

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. 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 

mission evaluation during flight will be performed at the MCC. 

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 

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Grand Turk 

Bermuda 

Grand Canary Island 

Antigua 

Ascension 

Pretoria 

NRD Ships 

3.1.1.1.9.3.2.2 Circulation and Early Orbit. 

Carnar von 

Hawaii 

Vandenberg/Arguello 

CKAFS 

Antigua 

Okinawa 

Ascension 

Pretoria 

Grand Bahama 

Bermuda 

NRD Ships 

3 1 1 1.9.3.2.3 On -Orbit. 

Okinawa 

Hawaii 

Vandenberg/Arguello 

CKAFS 

Antigua 

Carnarvon 

Voice Stations 

5. 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. 

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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 recol:- 

cry 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 (SSD), 

AFSC. 

3.1.1.1.10.2 Launch Operations. 

I Launch operations arc the responsibility of SSD, 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 flight 

crew shall be the responsibility of SSD. Operation of the worldwide tracking 

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 (MCC) shall be operated by SSD and supported by NRD. 

3.1,1,1.10.4 Experiment Operations. 

Experiment equipment, developmental simulators, procedures, and data ;Analysis, shall be supplied by SSD, and the U. S. Navy. Th, 

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Aerospace Corporation is responsible for providing general systems engineering and technical direction for SSD Contractors, as well as for the 

coordination and integration task. 

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. 

3. 1. 1.2 Logistics. 

3. 1. 1. 2. 1 Supply Support. 

3. 1. 1. 2. 1. 1 Sparc parts support for the Laboratory Vehicle, Gemini B, 

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

provided in accordance with SSD Exhibit 63-14. Spare parts requirements 

shall be based on a concept of minimum maintenance at launch site consisting 

primarily of component replacement. Sparc 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 flight 

crew capability for on-orbit maintenance. 

3. 1. 1.2.1.2 Spare parts for the V113, 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 arc 

provided. 

3. 1 . 1 .L. 2 Maintenance Support. 

3.1.1.2.2.1 Applicable documents for Maintenance Support are listed in 

paragraph 2.0 with the prefix letter MS. 

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3. 1. 1. 2. 2. 2 The repair program shall be based on return of component:- 

to home plant and/or to associate, sub-contractors or vendors plants for 

repair and return. Repaired components must meet the serviceability and 

reliability requirements established for acceptance of newly fabricated 

articles. 

3.1.1.2.2.3 Maintenance of the VIB, 1TL, 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: Flight Crew and Ground Crew. These are treated separately in this specification and throughout the program. 

The Flight Crew, their flight equipment, and training 

requirements are described in Section 3.3. 5. Ground Crew only, are speci- • fied in the requirements of this section. 

3. 1. 1. 3. 1 Operational Personnel. 

There arc 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, typo, 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. I. 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. I. 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 

Operations" (Figure 3. 1. 2. 1. 2. 3. b) 

3. 1. 2. 1. 2. 4 MOL System First Li• vcl 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. I. 2. 7). 

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) 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). 

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. 

so 

3. 1. Z. 2. 1 

are in orbit. 

3.1.2.2.2 

3.1.2.2.3 

3.1.2.2.4 

Orbiting Vehicle System Segment. 

This constitutes all segments and parts of segments which 

Laboratory System Segment. 

Gemini B System Segment. 

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. 

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0 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. 

(See appropriate paragraph in each system segment section.) 

3.1.2.3.1 Special Flight CEI's. 

3. 1. 2. 3. 1. 1 Modification Group List for Flight 1. 

6 

3.1.2.3.1.2 Modification Group List for Flight 2. 

3.1.2.3.1.3 Modification Group List for Flight 3. 

3.1.2.3.1.4 Modification Group List for Flight 4. 

3.1.2.3.1.5 Modification Group List for Flight 5. 

3. 1.2. 3.1.6 Modification Group List for Flight 6. 

3. 1.2. 3. 1.7 Modification Group List for Flight 7. 

3. 1. 2. 3. 1. 8 Modification Group List for Flight 8. 

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3.1.2.4 Interfaces. 

Interfaces between the various segments and their inter -

facing components are delineated in Appendix A. Interface Control Documents requirements shall be stated as needed in the outline format given. 

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• 3. 1. 3 System Effectiveness. 

3. 1. 3. I Effectiveness Measures. 

3. 1. 3. 1. 1 General. 

System effectiveness is defined as the probability that a system will accomplish a specified mission. The measure of MOL Program 

effectiveness shall be the extent to which the primary experiments and the 

required data retrieval are accomplished. Since, however, the experiments 

are many and varied, and since there is duplication on different flights, the 

"mission" is not a unique event. 

Factors included in system effectiveness are reliability, 

maintainability, quality assurance, human engineering, and permeating all 

these, safety. Although a high inherent reliability level for MOL is essential, 

presence of the flight crew may permit maintenance on orbit if appropriate 

design measures are taken to allow checkout, access, and replacement. 

Determination of the extent to which manned maintenance can contribute to 

reliable space operations is a goal of the program. Contractor shall minimize the effects of single failures on mission accomplishments, for example, 

through the flexibility of alternate modes, even if degradation results. 

3. 1. 3. 1. 2 Total Program Effectiveness. 

In order to assure the highest probability of obtaining the 

experimental results, basic experiments shall be programmed on at least 

two flights, flight crew tasks on orbit shall be scheduled to maximize data 

output, and recording and transmission shall optimize data retrieval. Flight 

crew safety on individual flights shall not be compromised. The primary 

MOL Program objective, for purposes of this requirement, is defined as: 

a. Completion of the total of the orbital man-hours activity 

for a single performance of all primary experiments 

including such checkout, alignment, calibration, repair, 

preparation, execution, processing, examination, communications, and similar tasks which are an integral 

part of, or are in direct support of, the experiments; 

and 

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b. Return Return to designated ground stations of the specified 

types, quantities, and qualities of data including that 

delivered by the astronauts in person; and 

c. Provision of environmental conditions, life support, 

performance capabilities, and ground support for the 

duration of the missions as required to sustain the system and to perform the experiments. 

3. 1. 3. 1. 3 System Capability. 

System capability, in essence operational effectiveness, is 

composed of both engineering performance and operational availability as 

these combine relative to mission requirements. Engineering performance 

requirements have been stipulated under segment 3.3. The capability of the 

system to sustain this performance level for the duration of its prescribed 

mission shall be determined. 

Performance requirements may vary for different missions 

or may be fixed for all missions. For any particular function, a criterion 

shall be established for determining whether the system is in an acceptable 

state. The acceptable risk of not meeting requirements on a particular mission must be determined in order to predict and verify whether the system 

involved meets its performance requirements. With the aid of such criterion 

the acceptable system states shall be determined. 

3. 1. 3. 1. 4 Effectiveness Apportionment. 

Effectiveness is to be apportioned by parameter among and 

within the system segments consistent with their mission requirements in 

a manner which will maximize MOL program cost effectiveness. The models 

and procedures for accomplishing the apportionment and for maximizing 

MOL program cost effectiveness will be developed by the contractors within 

guidelines provided by SSD/Aerospace. These models and procedures will 

be subject to the approval of the Air Force. 

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• The parameters to be considered in effectiveness shall include the following: 

a. Crew Safety - The probability that no crew casualties 

will be experienced in either normal or emergency 

operations during the period in which the crew constitutes a segment of the MOL System. That period extends 

from the time during the Pre-launch Phase at which the 

crew enters the Gemini B, through the completion of the 

Recovery Phase. A casualty, for purposes of the MOL 

mission, is defined as a fatality or an injury which renders the flight crew incapable of further services in the 

mission. Any lesser injury shall be considered to constitute a performance degradation. 

b. Mission Completion - The probability that no failures 

occur during the mission which result in major damage/ 

destruction or which require abandonment of the launch 

vehicle, laboratory, and/or re-entry vehicle. 

c. Design Adequacy - The probability that no failures occur 

during the mission which result in a reduction of performance capabilities such that mission objectives 

are compromised. 

d. Availability - The probability that a specified element 

will be capable of performing a specified function at a 

given point in time. 

3. 1. 3. 1. 4. 1 Orbiting Vehicle System Segment. 

The allocation of effectiveness assigned to the Orbiting Vehicle segment will involve the time period from injection into orbit to separation of the Gemini B, and return of the flight crew from orbit. This, 

therefore, involves the success of Gemini B in maintaining its required 

operating characteristics during the entire orbital mission, the satisfactory 

performance of the Laboratory during the on-orbit portion, operation of the 

Transtage as required, satisfactory accomplishment of experiments (including data retrieval), satisfactory crew performance, and appropriate operation of the crew equipment. Since the Orbiting Vehicle system combines 

portions of a number of other segments, values will be assigned under the 

other segments. 

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3-33 
3. 1. 3. I. 4. 2 Laboratory System Segment. 

The Laboratory Vehicle Systems, after having been placed 

into orbit, shall be capable of satisfactorily operating and sustaining the 

crew for 30 days with a probability of at least 0.96, including on-orbit maintenance. 

3. 1. 3. 1. 4. 3 Gemini B System Segment. 

The MOL Gemini B problems of launch and re-entry are 

similar to those of the NASA Gemini Program. However, the boosters are 

different, the requirement for loiter of 14 hours on-orbit, and a higher altitude for Gemini B are additional impositions. For launch and re-entry, it 

is required that Gemini B have at least as high a probability of accomplishment as does the NASA Gemini. For on-orbit operations, Gemini B must be 

capable of enduring the space environment for at least 30 days (60 days for 

rendezvous mission), and of complete reactivation for the re-entry phase 

with a probability of at least 0.97. The probability that successful re-entry 

(after separation from the Laboratory) is attained shall be at least 0. 998. 

3. 1. 3. 1. 4. 4 Experiment System Segment. 

Conduct of each experiment shall not affect the survivability 

of the Orbital Vehicle. Allocations for each experiment are dependent on 

such factors as priorities for results, detailed equipment characteristics, 

and capability for maintenance. Allocations shall be made when more details have been developed for these factors. 

3. 1. 3. 1. 4. 5 Flight Crew and Crew Equipment System Segment. 

Since a major aspect of MOL is the evaluation of flight crew 

capabilities, this will develop as crew is selected, simulations carried out, 

and tests conducted. However, it is essential that crew equipment operate 

satisfactorily. The probability of crew equipment to support the mission 

shall be at least 0. 98 without emergency back-up and 0. 998 including available emergency modes. 

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3.1.3.1.4.6 Titan III System Segment. 

Predicted reliability of Titan ILIC to injection is 0.869 and 

for 30 day orbital operation of the Transtage is 0.864. These shall be considered as minima and any modifications shall not decrease these estimates. 

3.1.3.1.4.7 Test Operations System Segment. 

Adequate maintenance and/or redundancy are assumed to 

exist in control, communications and recovery so that no significant deterioration of system effectiveness will be experienced here. The probability 

that TOSS operates satisfactorily shall be at least 0.999. 

3.1.3.1.4.8 Facilities Segment. 

Effectiveness allocations are not made directly for the Facilities Segment. 

3.1.3.1.5 Reliability Apportionment. 

• Quantitative reliability requirements to support the overall 

system effectiveness shall be established in accordance with the requirement 

of MIL-R-27542A and MIL-STD-721 dated 15 October 61. Reliability values 

for the entire system shall be apportioned from the system to system elements as a basis for design methods, parts application and testing. Apportioned objectives shall be used in design, test planning, evaluation, trade-off 

studies and identifying problem or risk areas in consideration of complexity, 

effects of failure and degree of importance to their mission. The selection 

of parts shall be in conformance with the requirements of MIL-R-38100A. 

3.1.3.1.6 Determination of Compliance. 

Compliance with the allocated values for mission success is 

difficult to measure in a program in which the number of flights is so limited. 

Compliance will therefore be evaluated in terms of the following: 

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a. Analysis. 

Utilizing the best possible methods of reliability analysis and introducing basic experimental evidence as 

appropriate, the value of the probability for mission 

success for the particular segment involved shall be 

greater than the number specified. Methods of analysis shall be approved by SSD/Aerospace in order to 

assure consistency, acceptability of data, appropriate 

inclusion of all significant factors, and utilization of 

the best available techniques. 

b. Tests. 

Appropriate qualification, acceptance, and reliability 

tests of both subsystems and system segments shall be 

identified for purposes of mission success evaluation. 

Results of test evaluations shall indicate effectiveness 

values not less than those specified in the preceding 

sections. Appropriate measures in design, quality 

control, fabrication, or procedures shall be taken, and 

tests repeated until satisfactory results are obtained. 

The criteria, environment, number and nature of tests 

shall be presented to SSD for approval and tests shall 

be conducted in accordance with such agreements. 

Specific review of all failures occuring during such 

tests shall be conducted to determine corrective 

actions. Based directly on observed results, models 

shall be developed for the measurement of MOL system 

effectiveness during flight tests. Results incorporated 

in the models shall emphasize percentages of experiments completed and percentage of required data 

retrieved, with necessary weightings. 

3. 1. 3. 2 Maintainability. 

To assure that maintainability objectives are achieved, a 

maintainability program must be implemented to run concurrent with equipment design, development, production and system operation. Such a program is established to meet the requirements of military specifications 

calling for maximum equipment availability and reduced.maintenance costs. 

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• 3. 1. 3. 2. 1 Maintenance Requirements. 

3. I. 3.2.1.1 Gound 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. Adaquate 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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S 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 Airborne Vehicle and pad) 

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

3. 1. 3. 4. 1 Appendix B, "Environmental Criteria Specification for the 

MOL System", contains all of the details on the applicable environments for 

the Prelaunch and On-orbit general classifications. 

3. 1. 3. 4. 2 SSD Exhibit 62-166A, "Environmental Requirements Specification, Program 624A", Revision A, 1 July 1964, covers the Launch and 

Early Ascent phases. The Laboratory Vehicle and Gemini B shall meet the 

applicable requirements of this Exhibit as modified to incorporate the changes 

in the environment at various station levels. 

3. 1. 3. 4. 3 The Gemini B shall meet, as a minimum, the descent and 

recovery environments imposed on the NASA Gemini. 

I 

3. 1. 3. 5 

3. 1. 3. 5.1 

Transportability and Handling. 

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. 

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i 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-851213. 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 Para. 2.0 with these prefixes: 

Applicable or partially applicable Prefix HP 

Guidance Prefix GP 

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3. 1. 3. 7 Safety. 

with the prefix leAtpteprlisc 

3. 1. 3. 7. 1 

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

SF. Documents for Safety are listed in Paragraph 2 

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 corning in contact 

with personnel during normal breakdown modes. 

3. 1. 3. 7. 3 General. 

The general safety engineering requirements specified 

under this paragraph shall include design efforts to preclude the inadvertent destruction of the system or injury to the crew and operating personnel. 

The requirement includes all possible hazardous interactions of facilities, 

equipment, procedures and personnel, either singularly or in combination. 

The possible sources of system destruction or degradation which shall be 

covered by the requirement shall include but not be limited to: 

(1) High pressure 

(2) Explosive 

(3) Combustive 

(4) Accelerative 

(5) Corrosive 

(6) Electrical 

(7) Radiative 

(8) Vibrative 

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(9) Stress 

(10) Fatigue 

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) shall be made. 

c. Special attention is required for problems concerning 

the Orbiting Vehicle 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 exposures. 

d. Dangerous materials and components will be prepared 

for delivery in accordance with Section 5 hereof, with 

special reference to paragraph 3f of SSD Exhibit 62-181. 

3.1.3.9 Noise and Vibration. 

(See Appendix B for Environmental Criteria) 

3. 1. 3. 1 0 Life Support. 

(See Appendix B for Environmental Criteria) 

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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 end item specifications. The documents listed in paragraph 2. 0 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 paragraph 

2. 0 with the prefix letters DR form a part of this requirement. 

S 3. 2. 1. 1 Selection of Specifications and Standards. 

3. 2. I. 1. 1 The selection of specifications and standards for the identification, control and procurement of the commodities required to design and 

fabricate the equipment under contract shall be in accordance with MILSTD-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 • 

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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. 

3. 2. 1. 1. 3 Military Standards shall be employed to the maximum extent. (SSD 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 requirements 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 paragraph 2. 0 with the prefix 

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

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• 3. 2. 1. 3 Standard 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. 

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-STD-143. 

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 MIL-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. 2. 1. 3. 5 

3. 2. 1. 4 

Full utilization shall be made of IDEP. 

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 (MILSTD-210, Climatic Extremes for Military Equipment). The tests necessary 

to satisfy this requirement are specified under MIL-STD-810 and MIL-E5272C. 

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3. 2. 1. 5 

3. 2. 1. 5. 1 

Corrosion of Metal Parts. 

Electrolytic Corrosion of Metal Parts. 

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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 contact 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. 

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. 

Interchangeability and Replaceability. 

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, 

capacitors, or printed circuit modules; or equipment in which one unit or 

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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 towards 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 paragraph 2. 0 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 paragraph 2. 0 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. 

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. 2. 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. 

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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. 

3. 2. I. 8 Electromagnetic Interference. 

The General Design and Construction Requirements for this 

subject have been prepared under SSD Exhibit 64-4 titled, Electromagnetic 

Interference Control Specification for Manned Orbiting Laboratory. Applicable Military Specifications are listed in Paragraph 2. 0 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 62-181. 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. 

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• 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 related to Specification and Marking 

are listed in Paragraph 2.0 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 

40 activities. This criteria shall be incorporated into CEI specification and 

critical component specifications. Applicable documents relating to Storage 

listed in Paragraph 2.0 are preceded with the prefix letters ST. 

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6 3. 2. 2 Design Disciplines. 

The design criteria requirements listed shall be limited to 

specific design disciplines and/or types of equipment: 

a 

3. 2. 2. 1 Electrical. 

The electrical design discipline requirements have been 

prepared under SSD Exhibit 64-5, titled, General Specification, Wiring 

Harness. The applicable documents for this subject are listed in Paragraph 2. 0 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 Paragraph 2. 0 with the prefix letters HV. 

3. 2. 2. 4 Civil. 

Applicable civil reference documents are listed in Paragraph 2. 0 with the prefix letters CV. 

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3. 3 PERFORMANCE ALLOCATIONS. 

3. 3. 1 Orbiting Vehicle System Segment. 

The Orbiting Vehicle shall be composed of the following 

system segments: the Gemini B; the Laboratory; the Experiments; and the 

Titan III Transtage and Flight Crew and Crew equipment. The rendezvous 

and docking aspect of the segment is treated in Paragraph 3. 3. 1. 2. 10. 

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

3. 3. 1. 1. 1 Mass Parameters. 

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

The gross weight of the Orbiting Vehicle shall be approximately 19, 700 pounds, excluding the Transtage. 

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

The Laboratory segment weight shall not exceed 9800 

pounds. 

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

The allocated weight of the Gemini B segment shall not 

exceed 6300 pounds, including flight 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 integral launch mission. 

I 

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

3. 3. 1. 1. 1. 2 

CONFIDENTIAL 

Transtage. 

The Transtage dry weight shall not exceed 5250 pounds. 

Center of Gravity. 

The center of gravity shall be established and controlled 

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

phase control are not compromised. 

3. 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. Z Gemini B. 

Electrical power allocation to the Gemini B shall be ZOO 

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. 

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110 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. 

3. 3. 1. 1. 3 Leak Rate. 

The leak rate on orbit, with all system segments normally 

pressurized, 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. 

As discussed in Section 3. 1. 3. 1. 3. 1 the apportionment of 

effectiveness for the Orbiting Vehicle involves a number of factors. Since 

the Orbiting Vehicle will contain different payloads and tasks for various 

• flights, separate analyses shall be made for each flight. Effectiveness 

considerations shall be included in determining experiments to be carried 

on each flight. 

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. 

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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. I. 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. 

3. 3. I. 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 Orbiting Vehicle 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. Capability to control the transtage ACS from the Lab shall be 

provided. The interface between the transtage propulsion systems and the 

Laboratory control system shall be at the gimbal servo valve and the propellant valve inputs. 

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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. 

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 Laboratory Vehicle shall be compatible in 

terms of load transmission capability and mating at the interface 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. Z. 3. 3 Thermostructural. 

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 Flight Crew Transfer. 

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

An internal pressurized tunnel through the heat shield shall 

be provided to transfer the flight 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 flight 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. ) 

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• 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 Parcel Transfer. 

Small packages shall be required to be manually transferred 

between the Laboratory and Gemini B. 

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 and/or to an information recovery capsule for return and recovery. 

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. 

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 flight crewman commences 

transfer to the Laboratory while the Orbiting Vehicle is within range of 

communication stations. Upon completion of Laboratory activation, the 

second crewman will begin the Gemini B shutdown and transfer to the 

Laboratory within range of a communication station. Upon completion of 

3. 3. 1. 2. 5. 2 

• 

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Laboratory activation tasks, the Laboratory orbital configuration will be S 

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, deployment of targets and remotely controlled units, 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 flight 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 of the Gemini B. 

3. 3. 1. 2. 6. 3 Data Recovery Capsule. 

Provisions shall be made for the incorporation of the necessary equipment for a recoverable data capsule aboard any desired flight. 

Such provisions shall include: access for placing data into the capsule in an 

environmentally controlled atmosphere; means of adjusting and measuring 

any required ballast; means of deploying the capsule without adverse effects 

on the Orbiting Vehicle; and means of controlling the attitude and time of 

release, and adjusting the retrograde impulse. 

3. 3. I. 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 

system during checkout, countdown and launch, (2) determining whether the 

• 

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• 

• 

CONFIDENTIAL 

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 or 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. 

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 functions 

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 flight 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 

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capabilities, it shall be incorporated into the design. Maintenance shall 

normally be limited to the interior of the Laboratory or Gemini B. 

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. 

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• 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. 

3.3.1.2.10.2.2.3 The OAMS of either the chase 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. 

3. 3. 1. 2. 10. 3 Laboratory Requirements. 

3.3. 1. 2. 10. 3. 1 The Laboratory shall provide structural, electro/ 

mechanical, and space for the fitting of the rendezvous mission equipment. 

o 

3.3.1. 2. 10. 3. 2 The target vehicle shall contain: a flight 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 

flight 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. 10. 3. 3 The chase vehicle structure shall contain: a flight crew 

transfer tunnel assembly which connects the vehicle pressurized compartment to the mating face of the target vehicle at the docking plane, a flight 

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. 

• 

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RELEASE 1 JULY 2015 -C-E*FEEFEt+T-I*L3.3. 1. 2. 10. 3. 4 The target vehicle, (including subsystems), and the target 

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

3.3. 1. 2. 10. 3. 5 The chase vehicle (including subsystems) and the chase 

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

3.3. 1.2. 10. 3. 6 The target vehicle shall incorporate radar transponder 

compatible with the Gemini B rendezvous radar. 

3.3. 1. 2. 10. 3. 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. 

3. 3. 1. 2. 10. 4 Gemini B Requirements. 

3.3. 1. 2. 10. 4. 1 The Gemini B shall be capable of storage on-orbit for 60 

days. 

3. 3. 1. 2. 10. 5 Transtage Requirements. 

Provision shall be made for full control of the transtage 

attitude control main and propulsion system from the Gemini B. 

3. 3. 1. 3 Functional Interfaces. 

(The contractor shall identify the functional interfaces 

between his system segments and other MOL system segments. ) 

3. 3. 1. 4 Contract End Items. 

(The contractor shall provide for incorporation in this 

paragraph a list by contract end item number, nomenclature and the CEI to 

which it installs, all contract end items included in his system segment. ) 

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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 flight 

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 flight crew 

interference and injury. The over-all internal arrangement shall provide for 

convenient and simple management of the vehicle by the flight crew. 

• 

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40fififfEttitt 

S 3. 3. 2. 1. 3 Flight Crew Stay Time. 

The Laboratory Vehicle shall provide for a nominal on-orbit 

stay time for a two-man flight 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. 

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. 

3. 3. 2. 2 

3. 3. 2. 2. 1 

Peculiar Performance and Design Requirements. S 

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 Data Recovery Capsule. 

The laboratory shall be designed to incorporate provisions 

for recovery of experimental data via a capsule delivery system. 

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3. 3.2. 2. 4 Outgassing and Venting. 

The Laboratory shall be designed so that neither normal 

venting nor normal leakage of the consumable stores shall impinge on the 

Transtage. 

3. 3. 2. 2. 5 Communication and Data Handling Requirements. 

3. 3. 2. 2. 5. 1 Command System. 

3. 3. 2. 2. 5. 1. I 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. 

1111 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. 

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3.3.1.1.5.1.2.4 Bit Rate. S 

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. 

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 

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 

S 

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• order received. New data will be inhibited until transfer of data or reset 01 

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 

verification, and intercommunication requirements. 

• 

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

The Data Acquisition Subsystem shall: 

a. Accept electrical signals from the flight crew and 

Experiments Information System. 

b. Provide equipment for signal conditioning, coding and 

multiplexing the instrumentation signals for telemetry 

and recording. 

c. Provides tape recorders/reproducing equipment. 

d. 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. • 

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The same basic equipments shall be used for both manned 

and unmanned flights. VHF FM/F, 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 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 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. 

S 

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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 

type 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 system 

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. 

• 

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3. 3. 2. 2. 5. 3 

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

Data Transmission System. S 

The telemetry transmitters shall consist of: 

a. Real Time Transmitters 

b. Standby Transmitters 

c. Delayed Time Transmitters 

d. Wideband Transmitters 

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 s.videband 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 

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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 voic.; communications subsystem must provide two-way 

communications between ground and crew and intercommunication between 

the flight crew during laboratory and transfer operations and extravehicular 

excursions. 

• 

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 shall 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 

• 

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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 flight crew. 

3.3.2.2.5.5.2.2 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 

Sys tern. 

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

The Antenna System shall normally be operational during 

the orbital phase of the mission. 

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• 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 Orbiting Vehicle maneuvers or nonnominal 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 sizeweight-power and complexity. The telemetry security equipment shall be 

capable of operation with either the PCM telemetry or the wideband data 

link. The maximum data rate requirement for the secure telemetry is one 

megabit/sec. 

• 3.3.2.2.6 Environmental Control and Life Support. 

3.3.2.2.6.1 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. Flight Crew Hygiene 

The specific requirements for each of the above sub-systems 

are given below, together with the overall requirements for the complete 

system. 

• 

SSMD-30-6 CONMENTRE Atch. 6 

3-75 
3. 3. 2. 2. 6. 2 

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

Atmosphere Control. 

General. 

• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CONFIDENTIAL 

The atmosphere control subsystem of the Laboratory shall 

maintain and control the pressure, composition, and temperature 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 unit 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 diluent 

gas supply and control from the dual gas provisions. An independent oxygen 

partial pressure indicator shall be provided. The partial pressures of the 

various atmospheric components shall be controlled to assure alveolar oxygen pressure between 60 and 175 mm Hg under all conditions. The normal 

operating level for alveolar oxygen pressure shall not be less than 100 mm 

Hg. 

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. 

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 pressure for pressure suit operation. 

• 

-CitiFI9ENT-1* SSMD-30-6 

Atch. 6 

3-76 
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0 3.3.2.2.6.2.3.2 Dual Gas Pressure Control. 

An oxygen partial pressure sensor shall be used to maintain 

the composition for the dual gas mode. Redundant partial pressure oxygen 

sensors shall be provided. A pressure regulation system shall control the 

total pressure for the dual gas mode and shall be designed to preclude flooding the pressure compartments with the diluent gas. 

3.3.2.2.6.2.3.3 Metabolic Gas Flux. 

A nominal oxygen consumption of 2.00 lbs/man/day and CO2 

production of 2. 32 lbs/man/day shall be utilized for system designs. 

3.3.2.2.6.2.4 Environmental Temperature and Humidity. 

The average temperature of the atmosphere shall be capable 

of control to ± 3.0°F of set point temperature over the range of 600F to 900F. 

The average atmosphere water vapor partial pressure shall be capable of 

control to t 3.0 mm Hg of set point over the range of 5.0 mm Hg to 15 mm 

Hg. The actual design temperatures and water vapor partial pressures are 

to be selected within these ranges to assure optimum crew comfort under all 

predictable environmental conditions. 

requirements: 

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

Gemini B reactivation. 

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

c. Oxygen and diluent 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 pressurized section depending on the extravehicular experiment activity. 

d. A 10% margin on oxygen and diluent requirements, over 

and above those allowances made for any purge and • 

SSMD-30-6 -C-ONFIRENTialeakage. 

Atch. 6 3-77 

3.3.2.2.6.2.5 Atmospheric Storage R.equirements. 

The atmospheric storage shall provide for the following 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.3.2.2.6.2.6 Oxygen Storage. 41 

Oxygen and dilutent storage shall be supercritical cryogenic. 

The storage system shall be capable of a minimum 48 hour non-vent 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. 

3.3.2.2.6.2.7 Carbon Dioxide Control. 

A non-regenerable CO2 absorbent system will be used until 

a trade study shall establish whether it should be regenerable. 

The environmental control system will maintain nominal CO2 

levels within 5 ± 3 mm Hg. 

3.3.2.2.6.2.8 Odor and Contaminant Control. 

Equipment shall be provided for the control of odor and trace 

gases. Atmospheric debris traps will be provided. 

Concentration limits for a preliminary set of possible contaminants shall be as specified in U.S. Navy Submarine Atmosphere Habitability Data Book, No. 250-649-1, Revision 1, Navy Bureau of Ships, corrected to the design atmosphere. 

Positive control shall be exercised to identify contaminants, 

their sources, and to minimize their introduction into the laboratory 

atmosphere. 

3.3.2.2.6.2.9 Pressure Maintenance. 

One compartment of the pressurized volume shall be capable 

of maintaining normal pressure in the event of a cabin puncture in the other. 

Atch. 6 

3-78 SSMD-30-6 

• 
NRO APPROVED FOR 

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• 3.3.2.2.6.2.10 Repressurization. 

Repressurization time for the complete pressurized volume 

shall 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. 

3. 3. 2. 2. 6. 3 Thermal Control. 

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

The thermal control subsystem of the Laboratory Vehicle 

shall provide for heat transport between the vehicle interior and the vehicle 

heat sinks. No critical equipment shall depend on the conditioned atmosphere for cooling. 

The thermal control system shall be capable of removing the 

heat generated under the most unfavorable combination of flight crew opera- 

• tional mode and atmospheric operational mode. 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 • 

SSMD-30-6 -C-ONFIDENTIA- Atch. 6 

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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. 

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 

simplicity, 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. Flight 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 

• 

• 

SSMD-30-6 Atch. 6 

3-80 
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• 

CONFIDENTIAL 

shall be made available to the pressurized section at nominal temperatures 

of 155°F and 55°F. Potability assurance 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 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 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 t 700 ml per man. This volume (less a 50 ml aliquot for 

physiological tests) is to be delivered to and managed by the urine disposal 

system. The collection and handling system shall provide for determination 

of urinary output volume. 

The daily fecal volumes of approximately 100 t 100 ml shall 

be collected in a special bag for subsequent lyophilization and storage for 

subsequent return to earth for analysis. 

3.3.2.2.6.7 Overall System Requirements. 

3.3.2.2.6.7.1 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 an excess of sealevel pressure. Ground cooling of the Laboratory shall be provided. 

• 

SSMD-30-6 CONFIDENTIAL Atch. 

3-81 
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CONFIDENTIAL 

3.3.2.2.6.7.2 Launch Operation. 

During the launch phase, the system shall have the capa nay 

to furnish operational status determination via telemetry. The atmosphere 

of the pressurized section shall be relieved during ascent to maintain 

pressure differential compatible with the specified orbital requiremen 

Cooling of the Laboratory Vehicle during ascent shall be provided by a 

water evaporator. 

3.3.2.2.6.7.3 On-Orbit Operation. 

Instrumentation of the system shall be provided to furni h 

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

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

3.3.2 .2 .6 .7 .4 Safety Features . 

All valves that connect the interior of the pressurized section 

to the space environment shall have manual closures and/or overrides}. 

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

compressors. Relief shall be provided over-pressurization. Flow limiting 

1 

This system shall control the vehicle attitude and provi e 

translational velocity change capability while on-orbit. An on-off rca tion 

jet attitude control system located in the Laboratory shall control the chicle 

attitude and generate small velocity changes. The transtage main pro•ulsion 

system shall be utilized, in conjunction with the control electronics lo ated in 

the Laboratory, for large velocity changes. 

devices shall be provided to prevent excessive use of gas supplies. 

3.3.2.2.7 Orbital Attitude Maneuvering System (DAMS). 

3.3.2.2.7.1 General. 

S 

• 

Atch. 6 

3-82 -C-GRFENTIAL- SSM -30-6 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 LUNt WIN I IAL 

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. 

• 

SSNID - 30 -6 GONFIDESTIAL- Atch . 

3-S \ 
NRO APPROVED FOR 

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CON1IDENTIAL 

40 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 0.7 degree about the orbit plane. 

Displays of attitude errors relative to the reference system 

and body axis rates shall be available. 

3. 3. 2. 2. 7. a. 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 flight crew. 

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 flight crew 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. 

• 

SSMD-30-6 CONFIDENTIAL 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 flight crew through a minimum amount of 

electronics to provide high reliability. 

The attitude reference in this mode shall be external-visual 

or attitude control displays. 

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 flight crew will 

be required to insert initial gimbal angles and AV requirements into the control system. 

The transtage gimbal angles and the velocity-to-be gained 

shall be displayed to the flight crew. 

3.3.2.2.7.2.7 Transtage Ullagc. 

The mode provides the propellant settling for the main engine 

in the transtage. The flight crew will control this mode through the AV 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. 

Atch. 6 

3-84 CONFIDENTIAL-, 

S 

SSMD-30-6 

S 

S 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

Acceleration greater than 0.05 £t/sec t 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. 

The mode select panel will allow any of the control system 

operating modes to be selected and indicate which mode is currently 

ope rating. 

The Euler angle set panel shall permit the flight crew to 

insert the three Euler angles and the maneuver rate, as well as displaying 

the currently set valves. 

Fine 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 flight crew. 

• 

SSMD -30 -6 C-OWIDENTIAL Atch. 6 

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3.3.2.2.7.4 Propulsion System. 4 

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 commands 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. 

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 temperature 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. . 

Atch. 6 

3 -86 -C-CiNfIDENTIAL- SSMD-30 -6 

...• • •,••.- • • •, •• ••••••••••••,. ••••••■•‘•• • ■ • 1.1"••••t •.••• ^ ••• ■ •••••, • •6• u•• ha w. 
NRO APPROVED FOR 

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• 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. 

3. 3. 2. 2. 7. 4. 7 Propellant Gaging. 

The subsystem shall include a method to measure and display 

to the flight crew 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. 

• 

SSMD -30 -6 -EitiFfEt11+14- Atch. 6 

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NRO APPROVED FOR 

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3. 3. 2. 2. 7. 4. 9 Propellants. 

The propellants shall be hypergolic bipropellants which are 

space storable and shall be selected considering thermal environment and 

minimization of ignition over-pressure transients. 

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, 

Laboratory 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 Laboratory CPS shall be accomplished with H2-02 fuel cell modules arranged in 

parallel, with automatic and manually actuated interconnections. 

3. 3. 2. 2. 8. 1. 2 Nominal Power. 

The Laboratory 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 Laboratory 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. 

S 

S 

-CONFIRENT SSMD-30 -6 

Atch. 6 

3 -88 
NRO APPROVED FOR 

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• 3.3.2.2.8.2 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 Laboratory 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 included 

as part of the 1.8 kw average power required to be delivered by the powerplant for the Laboratory 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. • 

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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 designed so 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. 

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. 

S 

• 

Atch. 6 3 -90 SSMD -30-6 
NRO APPROVED FOR 

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—eatiFfaEtiffklThe power control unit shall provide a distribution point for 

the major electrical power within the Laboratory, 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 electrical resistance heater shall be included to provide additional heat for pressurization during initial pressurization or periods of high fluid withdrawal. 

• SSMD -30 -6 -C-ONMENfbi-E Atch. 6 

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• 

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Atch. 6 4 

3 -92 -e0NROTRE SSMD-30 -6 

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. 

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 exercised, 

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 terminals and shall immediately give 

specified performance upon return to the equipment operating voltage. 

3. 3. 2. 2. 8. 7. 3 Transients. 

Laboratory equipment shall be capable of withstanding 

transients of ± 100 volts with respect to nominal bus voltage for durations up 

to 20 microseconds. 

4 

4 
NRO APPROVED FOR 

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• 

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 Laboratory CPS shall incorporate a single point ground 

system, compatible grounding network with the Gemini B launch vehicle, and 

Experiments. 

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 Appendix B. • 

3.3.2.2.9.2 Structural Design Criteria. 

The structural design criteria applicable to the Laboratory 

Vehicle are specified in attachment 1, Annex A, Phase I Work Statement. 

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. 

• 

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-E6tiFiEtifttit3. 

a. 

3. 2. 2. 9. 4 Factors of Safety. 

Limit Proof Ultimate Burst 

Flight Loads 

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 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 

Hydraulic Vessels 1.00 2.00 4. 00 4. 00 

(Including Accumulators 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 

ultimate. 

3. 3. 2. 2. 9. 5. 2 The structure shall not experience deformations which impair functional performance at limit loads. 

I 

I 

CONFIDENTIAL SSMD -30 -6 

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CONFIDENTIAL 

• 3.3.2.2.9.5.3 The structure shall not experience deformations which impair performance 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. 

3.3.2.2.10 Flight Crew Accommodations. 

S 

3.3.2.2.10.1 Furnishings and Equipment. 

The pressurized section shall provide furnishings and equipments in functional groups for maximum efficiency and flight 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 flight crew activity. 

• 

SSMD-30-6 C-GPIRENT-14- Atc. 3-95 

• 
3. 3. 2. 2. 

3. 3. 2. 2. 

10.4 Flight Crew Transfer Provisions. 

10. 4. 1 Normal Transfer. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

The Laboratory Vehicle shall provide umbilical connections 

required for life support and communications under normal flight 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. 

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 flight 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. 

Atch. 6 

3-96 -€ONFREtiflitt- SSMD-30-6 

.1"•••••.1 ..`P U^ '1,4 S, Vet •.••■• ••- ■••,,ne, hg....Intiq• 1 ■■•• ■ 

I 
NRO APPROVED FOR 

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10 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 Laboratory 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 Operating 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 VIB 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. 

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 

SSMD-30-6 -C-ONMENT-bit Atch. 6 

3-97 
NRO APPROVED FOR 

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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. 

3. 3. Z. 3 Functional Interfaces. 

(The contractor shall identify the functional interfaces between his system segments and other MOL system segments. ) 

3. 3. 2. 4 Contract End Items. 

(The contractor shall provide for incorporation in this paragraph a list by contract and item number, nomenclature and the CEI to which 

it installs, all contract and items included in his system segment. ) 

GONRENTIA SSMD-30-6 

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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 flight crew escape 

system and the supporting ground system. The Gemini B 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 Gemini B 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. 1. 1 Weights. 

Nominal design launch weight of the Gemini B, including the 

complete re-entry module, the adapter section, escape system, flight crew, 

and flight equipment shall be 6300 pounds. This weight is distributed as 

follows: 

Re-entry Module 4750 pounds 

Adapter Section 1550 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 flight 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. 

SSMD-30-6 -C-OfififftlfthE Atch. 6 

3-99 

00,00,0 01 I.■ P 11”,••1 ;.•■■ •■ ".•■•••• •■ •• ,1"1,1`1.1,1. 111.1. 
NRO APPROVED FOR 

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3. 3. 3. 1. 3 Effectiveness. 

Data shall be furnished to support a detailed apportionment 

of effectiveness to the Gemini B 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. 

3. 3. 3. 1. 4 Flight Crew Stay Time. 

The maximum total time the flight crew will be required to 

stay in the Gemini B is 64 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 

Total time in 

these categories will 

not exceed 14 

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. 

3. 3. 3. 2 

3. 3. 3. 2. 1 

3. 3. 3. 2. 1. 1 

Peculiar Performance and Design Requirements. 

Gemini B Requirements. 

General. 

The design of the Gemini B shall be based on a service life 

of one mission. 

Atch. 6 

3-100 -C-ONMENTIAL- SSMD-30-6 

•.1••••,..1 ..• ..... not ttrtrnsv ,ke tl••• ■ ••1 `0•,••• ■ w••.••••• In •••••• ■ •••••• ■ . •••••• I ,1 • •••• ■ 1.1...t 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

a 3. 3. 3. 2. 1. 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 

flight 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 a 56" long 

structure required to transition from the re-entry module to the 120" diameter Laboratory Vehicle. The flight 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 sustaining 

all loads and environments imposed during the MOL mission of ground 

handling and transportation, pre-launch, launch, on-orbit, retrograde, 

re-entry, landing and recovery. 

3. 3. 3. 2. 1. 5 Aerothermodynamic. 

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 N. M. crossrange and 400 N. M. along the ground track. The 

maximum deceleration experienced by the crew during normal guided reentry shall not exceed 10g. 

SSMD- 30 -6 CONFIDENTIAL Atch. 6 

3-101 

r •• • •• ! tat 
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3. 3. 3. 2. 2 Guidance and Control Requirements. 

3. 3. 3. 2. 2. I General. 

The Gemini B shall have the capability for re-entry control 

recovery of + 8 N. M. (3 sigma 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 reentry touchdown control, and control function outputs to applicable systems. 

An attitude control capability consistent with the guidance accuracy requirement shall be provided. 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 flight 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 Gemini B 

and launch vehicle events, critical launch vehicle parameters, Gemini B 

system status and certain critical Laboratory status items during all mission 

phases. 

Atch. 6 

3-102 -eNFIRENTIAL-- SSMD-30-6 

..••■ •••• st.. •••■ Ir 1.1,.% 
3. 3. 3. 2. 4 

3. 3. 3. 2. 4. 1 

Environmental Control Requirements. 

General. 

0 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CONFIDENTIAL 

The Gemini B shall provide the environmental control and 

life support for the flight crew members until crew transfer. The Gemini B 

shall again provide environmental control and life support for the flight crew 

members after the Gemini B is re-activated for mission termination. 

3. 3. 3. 2. 4. 2 Cabin Environmental Control. 

The capability shall be provided for complete environmental 

life support while the Gemini B is manned. The flight 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 on-orbit; during re-entry, the temperature shall not exceed 

200°F. 

• 

3. 3. 3. 2. 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 member for emergency use during high altitude seat ejection. 

The capability shall be provided to allow the flight 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 on-orbit dormant storage conditions. 

4111 

SSMD-30-6 CONFIDENTIAL 6 

3-103 
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-C-ORFEFERML-- 

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. 

3. 3. 3. 2. 5 Proplulsion 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 re-entry 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 

Atch. 6 

3-104 404FIDERA-L

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- SSMD-30-6 

S 

S 
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• 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 re-entry from 160 NM design 

orbit altitudes. The retrograde impulse timing, orientation and magnitude 

shall provide re-entry conditions which, considering all dispersions and 

re-entry bank angle command 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 utilization 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. 2 Electrical 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. 

• 

SSMD-30-6 

Atch. 6 

3-105 

• '•• •• /•• • , : • r I • • 
3. 3. 3. 2. 7 

3. 3. 3. 2, 7. 1 

Time Reference Requirements. 

Basic Time Reference. 

S 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 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 Titian IIIC shall be 

designed to maintain this concept. 

3. 3. 3. 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. 

• 

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 re-entry; 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. I General. 

The Gemini B shall have the capability for actuating, severing, separating, deploying, etc. , by utilizing pyrotechnic devices. 

Atch. 6 

3-106 -C-ONFIDENTI4 S 

SSMD-30-6 

■ •1 ,Iylynsy .. r. 10■■■ hd Ohi A•0••h 't •-reh,n., •hr sp..ouvir tn.s. 

• r.•• ■ I •• ■ e•Il by 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

--C-WIDENTIAL0 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 ground crews is minimized during 

assembly and checkout of the Gemini B. 

3. 3. 3. 2. 8. 3 Reliability. 

All functions requiring the use of pyrotechnic devices shall 

utilize either redundant devices or have an alternate mode of operation. 

Landing Requirements. 

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 emergency landing. 

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 11 g 

Down 15 g 

Left 11 g 

Right 11 g 

0 

SSMD-30-6 

Atch. 6 

3-107 

3. 3. 3. 2. 9 

3. 3. 3. 2. 9. 1 
3. 3. 3. 2. 10 

3. 3. 3. 2. 10. 1 

Post Landing and Survival Requirements. 

Location. 

S 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-ffitiFfEtifift 

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 Flight Crew Safety. 

Sufficient food and potable water shall be provided for a 

post landing period of 48 hours. Equipment to permit flight crew survival 

outside the re-entry module either on water or land shall be provided. 

3. 3. 3. 2. 11 Back-up Flight 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. 

3. 3. 3. 2. 12 Flight Crew Equipment and Display Requirements. 

3. 3. 3. 2. 12. 1 General. 

The design and arrangement of the flight 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 flight crew 

to monitor and manually control desired functions; these provisions 

S 

k!1}0% --€43NMENTIAL SSMD-30-6 
NRO APPROVED FOR 

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• shall permit them to be in either a pressurized or unpressurized 

suit. 

3. 3. 3. 2. 12. 3 Flight Crew Seating. 

Provisions shall be included for seating of the two man flight 

crew 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. 

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. 

• 

SSMD-30-6 -C-ONFIDEtiffki- Atch. 6 

3-109 

• 
NRO APPROVED FOR 

R EASE 1 JULY 2015 

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. 

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 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 

vehicle to ground voice communications. 

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 designed in 

accordance with the AGE System Criteria Section. 

gi 

Atch. 6 

3-110 SSMD-30-6 

•..., •. ••• ■■ •••■,t1 ..••• I )0.4.4 %,-e••• ■ 'kr In.I. 
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RELEASE 1 JULY 2015 

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. Whenever 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. 

S 

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-toend 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. 

3. 3. 3. 2. 15 Flight Crew Safety Requirements. 

The flight crew safety requirements for the Gemini B shall 

include the inherent safety of the Gemini B and the safety provided by the 

flight crew escape system in the case of aborts. 

• 

SSMD-30-6 CONFIDER-T-11k Atch. 6 

3-11 I 

.., .• • .• • •• 4•Irn■ •• •••• •■••• en^0'..) ht...”0,,, 
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CONFIDENTIAL 

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 Orbiting 

Vehicle. Such capability shall include sensors, computation capability, 

displays, and necessary control signals to the Transtage and Orbiting Vehicle 

attitude control systems. 

3. 3. 3. 3 Functional Interfaces. 

(The contractor shall identify the functional interfaces 

between his system segments and other MOL system segments. ) 

3. 3. 3. 4 Contract End Items. 

(The contractor shall provide for incorporation in this 

paragraph a list by contract and item number, nomenclature and the CEI to 

which it installs, all contract and items included in his system segment. ) 

Atch. 6 

3-112 SSMD-30-6 

,01 efrl,n,. n 11, U0.001 '11-110,1 /11,1, fh* fn11n.ne) 01 'he 1 t0.000/1. 

, 0, .s i.,..4,•••••■ In* 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CONFIDENTIAL 

O 3. 3.4 Experi:r.?nt System Segment. 

The Experiment system segment consists of primary experiments to evaluate the effectiveness of man in space doing military tasks, 

secondary experiments ts, develop technology and acquire scientific knowledge, and an experime:-.t :n:crrnation system to facilitate expeditious experiment accomplishment. 

3. 3. 4. 1 Allocato: Performance and Design 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 par: of the program. 

3. 3. 4. 1. 1 Effecti%eness Allocation. 

S 

Data shn.i be furnished to support a detailed apportionment 

of effectiveness to each cf the experiments and to the experiments as a group 

aboard each Orbiting Vu.:ole. A plan shall be developed to show how substantial compliance of effectivenss allocation will be demonstrated prior 

to acceptance and how actual compliance to this effectiveness allocation is 

judged during each mission. 

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. 

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3.3.4.2.2 Experiment Information System Data. • 

3.3.4.2.2.1 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. 

3.3.4.2.2.2 An Information Recovery Capsule shall be provided for the 

recovery of experimental data. The capsule shall contain a payload compartment, a retrograde and parachute recovery system, and flotation and 

communication gear which will permit recovery by sea and air units. 

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 flight 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. 

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a 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 flight crew. 

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 per pass. 

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3.3.4.2.3.2 Equipment Requirements. 

Equipments required for P-1, P-2, and P-3 experiments 

are a Pointing and Tracking Scope with variable magnification, manually 

adjustable crosshairs, a tracking servo, a coupled camera, a film processor, and film viewing and analysis equipment. The acquisition and tracking 

data shall be provided by the experiment information system. 

3.3.4.2.3.3 Experiment Procedure. 

In the P-1 experiment 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 be decreased and the 

magnification increased. The flight crew will center the crosshairs on target and proceed with the tracking run aided by the tracking servo. During 

the tracking run the coupled camera will record the image, including the 

crosshair reference at periodic intervals. 

In the P-3 experiment the flight crew will scan with the PTS 

in both manual and automatic modes to evaluate his ability to assess targets 

of opportunity. 

3.3.4.2.3.4 Orbital Vehicle Design Requirements. 

a. Provision shall be made for disabling the vehicle 

attitude control system during tracking runs. 

b. Provision shall be made 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. 

d. A viewport is required in the bottom of the vehicle 

adjacent to the PTS control console. 

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• e. Vehicle rigidity shall be compatible with precise optic_a. 

alignments. 

f. Storage space shall be provided for film magnetic tapes, 

punched card digital information and spares. 

g. Exposed film and data shall be transferable to the 

Gemini vehicle for re-entry. 

h. Thermal control of the MOL environment shall be consistent with maintaining precise optical alignments and 

accurate operation of servos and computers. 

i. Outgassing during tracking runs shall not cause attitude 

errors or rates in excess of those specified. 

.i• Ejected control gas shall not enter the field-of-view of 

the PTS. 

3. 3. 4. 2. 3. 5 Evaluation Requirement. 

In Experiments P-1 and P-2, sufficient data shall be recorded and recovered to allow quantitative evaluation of the times of acquisition, tracking errors versus time in the image plane and the over-all 

smoothed tracking rate data for various target types, visual conditions and 

initial errors. 

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 Requirements. 

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 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 equipment of Experiment P-8, providing angle data for P-7, 

the pointing and tracking of the P-10 collector optics and pointing of selected 

antennas of P-4. 

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3. 3. 4. 2. 3. 8 Setup a ..,1:bration Requirements. 

Provis: hall be made to perform on-orbit setup and 

calibration, consistent %, :Ile evaluation requirements. 

3. 3. 4. 2. 4 P-4 EL ::agnetic Signal Detection. 

3. 3. 4. 2. 4. 1 Objecti% 

The objcz:...- e is to evaluate the effectiveness of the flight 

crew in performing tasks associated with detection, processing, display, 

measurement, and recor of electromagnetic signals. 

3.3.4.2.4.2 Equips„, 

Equiprrc 

include the antennas, re -

recorders to permit evz• 

radiation from coordin,71. 

bands. This equipment 

and display capability for 

.',equirements. 

to be supplied for the P-4 experiment are to 

as, processing gear, display consoles, and 

ca of the flight crew ability to process signal 

.nitters in two or three separate frequency 

11 be designed to provide a real-time analysis 

s3phisticated signals and modulation techniques. 

3.3.4.2.4.3 Experin t Procedures. 

As the c: ::al vehicle passes over preselected target areas 

alerting shall be accomi... cd by operator scanning, or through automatic 

preset alarm criteria. operator will make the proper adjustment of controls to isolate the desire.: signals and display these in an optimal fashion for 

identification of signal c:. Acteristics. Tests will be performed to evaluate 

performance of the equip . nt and the operator in low versus dense signal 

environments, simple versus complex signal parameters, and maximum 

versus minimum preinstruction. 

3. 3. 4. 2. 4. 4 Orbital Vehicle Design Requirements. 

a. Vehicle stability , during the equipment operation shall be 

to alloy.,tracking of ground-based electromagnetic 

sources. 

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b. Storage space shall be provided for iilm, magnetic 

tapes, and spares. Exposed film and tapes shall be 

transferable to the Gemini vehicle for re-entry. 

c. A tracking antenna shall be provided for weak signals 

as well as signal locating and shall be extendable from 

the unpressurized portion of the MOL. 

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 Laboratory 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 subsystems 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. 

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3.3.4.2. 5. 5 Evaluation Requirements. 

Evaluation data shall be acquired to determine the effective - 

ness of various tools and attachments on different levels and types of maintenance. Of particular interest is the time required in space -relative to the 

same task on the ground. 

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. 

3.3.4.2.6 P-6 Extravehicular Activity. 

3. 3. 4. 2. 6. 1 Objective. 

To determine man's extravehicular capability and the equipment necessary to perform effective 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 pressure suit, an 

astronaut maneuvering unit (AMU), a separate portable ECS, standard type 

tools, zero reaction tools (ZERTS), cameras, task panel, various devices 

for extravehicular traversing along the MOL surface, such as handholds, 

foothold, etc. , plus a tether line. The AMU will provide the crew member 

attitude stabilization and maneuvering capability and shall have an integral 

life support capability including suit-cooling. 

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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 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 traverse away from the 

vehicle and perform selected tasks and maneuvers. 

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 from or ingress to 

the vehicle. 

b. Provisions for attachments to the Laboratory Vehicle 

shall be provided for surface operations. 

c. An umbilical shall be provided for life support and 

communication 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. AMU refurbishment expendable storage shall be provided for and shall be accessible from 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. 

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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 flight 

crewman shall describe his progress and time tones shall be superimposed 

on the record for time line analysis purposes. Extended operations shall 

recorded by the other crewman, using a hand held camera at a viewing poi: 

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 flight crew maneuvering unit and to develop 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. 

41110 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. 

3.3.4.2.7 P -7 

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3.3.4.2.7.5 Evaluation Requirements. 

Records of display data and flight crew control shall be 

recorded and recovered. Measures shall be developed for rating flight crew 

proficiency in performing predefined maneuvering tasks. 

3.3.4.2.7.6 Simulation Requirements. 

Development simulation shall be carried out to provide verification and evaluation of the Developmental simulators shall be provided to determine the optimum control 

procedure and display equipment and modes, to measure flight crew variance, 

to determine training requirements, and develop pre- and post-flight reference data. 

3.3.4.2.7.7 Experiment Interactions. 

experiment shall be designed 

to be visible to the PTS. • 

3.3.4.2.7.8 Setup and Calibration. 

shall be designed for ground 

alignment and calibration and shall require no on-orbit calibration. 

3.3.4.2.8 P-8 Autonomous Navigation and Geodesy. 

3.3.4.2.8. 1 Objective. 

The objective of Experiment P-8 is to evaluate the ability of 

man to act as spacecraft navigator and to determine man's ability to perform 

geodetic survey of uncooperative targets through the acquisition of data for 

use in subsequent post-flight analysis. 

3.3.4.2.8.2 Equipment Requirements. 

Equipments to be supplied for the P-8 experiment are an 

inertial measuring unit, two automatic star trackers, a horizon scanner, a • 

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precision time reference system, a photo-optical system, a ranging device, • 

displays and various prepared navigational 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 experiment information system central computer. 

3. 3. 4. 2. 8. 3 Experiment Procedures. 

It is required that measurements be made of inertial and 

terrestrial references as functions of time. The spacecraft's inertial 

orientation shall be provided 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 

the sighting of known landmarks. Data filtering and smoothing techniques 

shall be applied to the above measurements. 

The geodesy portion of the experiment shall, employ the 

pointing and tracking scope to acquire the terrestrial feature to be surveyed. 

A ranging device such as a laser shall be slaved 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 combination together with a photo-optical system. 

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. 

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c. A sufficiently unimpeded visual path shall exist between 

the navigation IMU 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. 

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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 B for recovery. 

f. Thermal control of the Orbital Vehicle environment 

shall be consistent with maintaining precise optical 

alignments and accurate operation of inertial components, servos and computers. 

g. Outgasing during data acquisition runs shall not cause 

attitude errors or rates in excess of those specified. 

h. Ejected control 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, ephermeris prediction and navigation problem solution and to 

allow quantitative evaluation of the ability to obtain high precision geodetic 

information. 

3.3.4.2.8.6 Simulation Requirements. 

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 flight crew. 

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-10 Multiband Spectral Observations. 

3.3.4.2.9.1 Objectives. 

The primary objective of the multiband 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 

ballistic missiles during boost, midcourse, and reentry phases. 

c. Determination of temperature distribution of ground and 

sea, 

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-10 shall include 

an IR/UV multiband scanning radiometer capable of measuring radiation from 

cooperatively launched missiles, 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 flight crew 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 

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mechanisms and associated equipment, selection of filters, adjustments and 

calibrations, preliminary evaluation, recording of data, verbal descriptions, 

and coordination with the ground. 

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 Orbiting Vehicle 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 flight crew 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 

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man-machine design parameters, detailed experiment and evaluation procedures, variance between subjects and provide pre- and post-flight reference 

data on the flight crew. 

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. 

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 flight 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 flight 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 flight 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. 

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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 restrained flight crew member can view the panel and operate the controls. 

3. 3. 4. 2. 10. 5 Repair Requirements. 

The equipment provided for this experiment shall be designed for minimum on-orbit maintenance, e. g. , light bulb replacement. 

3. 3. 4. 2. 10.6 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. 

3. 3. 4. 2. 10. 7 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 flight 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 flight 

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. 8 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 

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checkout andnd calibration program which shall be initiated and used immediately prior to each P-11 test session. 

3.3.4.2.11 P-12 Biomedical and Physiological Evaluation. 

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 flight 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, 02, CO2 , 

H2O and at least gross estimate of contaminates. 

e. Provide radiation measurements to ascertain crew 

member status and safety and to provide information for 

extrapolation to future manned missions. 

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0 3.3.4.2.11.3 Experiment Procedures. 

The measures to be used are classified into five categories 

as follows: 

• 

a. Those requiring the flight 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 flight 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 crew member to perform a 

measurement procedure on the other, recording the 

results appropriately. 

d. Those requiring one or both of the flight crewmen to 

perform detailed analyses procedures utilizing specialized analytical equipment and to record the results 

for processing or recording. 

e. Those requiring the flight crewmen to measure, identify 

and record their own metabolic intakes and to collect, 

process and identify samples of their own metabolic 

products. 

The flight crew shall collect, transfer and return samples to the earth for 

processing after recovery. 

3.3.4.2.11.4 Repair Requirements. 

The equipment for P-12 shall be designed for minimum onorbit maintenance and shall contain sufficient spares of non-reusable items. 

3.3.4.2.11.5 Evaluation Requirements. 

Evaluation shall be against the following requirements: 

a. Certain data shall be examined on a real-time or near 

real-time basis so that medical decisions may be made 

for mission safety. 

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 

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c. The remaining data shall be evaluated in comparison 

with ground-based 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. 6 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. 11.7 Setup and Calibration Requirements. 

Setup and calibration shall be designed into the test equipment and procedures. For clinical analyses the standard gas and liquid 

samples shall be packaged to allow direct insertion into the analytical 

equipment. 

3.3.4.2.12 P-13 Ocean Surveillance. • 

3.3.4.2.12.1 Objective. 

The objective is to evaluate the capability of the flight crew 

to control, coordinate, and utilize a number of sensors and associated displays etc. , to detect, locate, track, classify, and catalog sea targets. 

3.3.4.2.12.2 Equipment Requirements. 

The equipment requirements on three of the sensors for this 

experiment shall be met by the equipment requirements for P-1, P-4, and 

P-10. In addition to these equipments, an ocean surveillance radar, display 

equipment for correlation of data, and low-light level television (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. 

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-eetifleiffkl3.3.4.2.12.3 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 character - 

istics shall be measured and recorded. The radar shall scan for these 

radiating targets as well as additional targets not identified by the electromagnetic signal detection sensor. During daylight operation, the flight crew 

shall track selected targets through the optical sensor of P-1, P-2, and P-3 

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. The optics and LLLTV shall be 

assisted in acquiring the target by radar localization through the experiment 

information system. 

3.3.4.2.12.4 Orbital Vehicle Design Requirements. 

The television and radar sensors shall be designed so as to 

• 

operate with the Orbiting Vehicle's longitudinal axis tangent to its orbital 

path. 

The television sensor shall have approximately the same 

area coverage as the P-1 optical system. 

Provision shall be made to provide an ascent protective 

cover for the ocean surveillance radar antenna and a mechanism for ejecting 

this cover. 

The radar antenna location must be such that electromagnetic interference from and with other equipments is not deleterious. 

Storage space for film and prints shall be provided. Film 

and data should be recoverable. 

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-C-641FifrERfitit3.3.4.2.12.5 Evaluation Requirements. 

Sufficient data shall be recorded and recovered to allow 

quantitative evaluation of the astronaut's performance in detecting, locating, 

tracking, classifying, and cataloging sea targets. 

3.3.4.2.12.6 Simulation Requirements. 

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 Requirements. 

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 Requirements. 

Provisions shall be made to perform on-orbit setup and 

calibration consistent with the evaluation requirements. 

3.3.4.3 Functional Interfaces. 

(The contractor shall identify the functional interfaces between his system segments and other MOL system segments.) 

3.3.4.4 Contract End Items. 

(The contractor shall provide for incorporation in this paragraph a list by contract and item number, nomenclature and the CEI to which 

it installs, all contract and items included in his system segment.) 

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• 3.3.4. 5 Experiments Peculiar Ground System. 

3. 3. 4. 5. 1 Experiments Peculiar AGE. 

3. 3. 4. 5. 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 inclusions 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 the ETR 

shall be functionally identical to the AGE utilized at the Laboratory Vehicle 

contractor's facility. 

3.3.4.5.1.2 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 providing 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. 

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3. 3.4. 5. 2 3. 4. 5. 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 

guidelines 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 MOL 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 elements 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 Vehicle segment. 

3.3.5.1.2 Weight . 

Flight crewman shall weigh 138-192 lbs. Individual space 

suits and portable environmental control subsystem will weigh approximately 

• 

85 lbs. per man. This total weight of flight crew and flight crew equipment 

is contained in the Gemini B 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 Laboratory. 

Weights for remaining flight crew accommodations items are included in the 

Gemini B and Laboratory Vehicle System Segments. 

3.3.5.1.3 Volume. 

Baseline functional volumes for Laboratory Vehicle design 

for the human operator will be based 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 

3.3.5.2.1 

3.3.5.2.1.1 

Peculiar Performance and Design Requirements. 

Flight Crew Complement and Performance Allocation. 

Orbital Vehicle Flight Crew Performance. 

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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 Flight 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 Vehicle Flight Crew Performance. 

Functional areas of Laboratory Vehicle 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 Flight 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 Flight 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 performance requirements shall be documented in task and time line • analyses. 

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 Training. 

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 

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training program and students shall take place in order to adjust the program 

or to 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 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 

flight crew members will have been designated as well as the specific spacecraft with specific mission objectives for this launch date. These flight 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 space-

: raft will involve the assigned flight crew members. The training shall 

include part-task simulation of boost and ascent, attitude control, orbit 

modification, reentry retrofire and reentry control, and launch vehicle abort; 

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-C-ORRENTAsimulation of experiments; whole mission rehearsal of the Gemini B 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 flight 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. 

Flight 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 flight crew performance required to meet 

the task and time line analyses. 

During development simulation and all stages of training, 

flight 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. 

3.3.5.2.4 Flight Crew Activity Programming. 

The activities of the flight crew required for Laboratory 

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 

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participate in selecting or deciding upon the alternative sequence of activities 

to pursue. 

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 administed 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 freezedehydrated 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 mission. 

3.3.5.2.6 Personal Hygiene. 

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. 

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• 3.3.5.2.7 Physiological 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 Laborator, 

is to be used for conditioning exercises. 

3.3.5.2.8 Medical Monitoring and Operational Support. 

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 shall 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. 

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--E6NROL-N-11A3. 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. 

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), weightlessness (zero-g aircraft), and reduced pressures and special atmospheric 

compositions (space chambers). 

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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. 

3.3.5.3 Functional Interfaces. 

(The contractor shall identify the functional interfaces between 

his system segments and other MOL system segments. ) 

3.3.5.4 Contract End Items. 

(The contractor shall provide for incorporation in this paragraph a list by contract and item number, nomenclature and the CEI to which 

it installs, all contract and items included in his system segment. ) 

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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. 

Allocated Performance and Design Requirements. 

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. M. Payload lb. 

• 

28. 4° 100 23, 000 

160 22, 400 

32° 100 22, 800 

160 22, 200 

3.3.6.1.2 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: 

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160 4100 

32° 100 4600 

160 3900 

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3.3.6.1.3 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. 160 N. M. 

Inclination ±0. 12° ±0. 120 

Altitude, ft. ± 3, 000 ±21, 000 

Eccentricity O. 4x10-3 3. 0x10-3 

3.3. 6.1.4 Reliability. 

The following are predicted values for the booster and 

transtage: 

1. Countdown 0.87 

2. Boost 0. 908 

3. Transtage (to inject) O. 915 

4. Transtage (30 days on-orbit) 0. 864 

3.3.6.1.5 Constraints. 

3.3.6.1.5.1 Length and Diameter . 

Payload Length, Feet Payload Diameter, Feet 

48 10 

Payload length is defined as the distance from launch vehicle station 77 to 

the top of the Gemini B Re-entry Module. The above payload length constraint 

of 48' is based on a Gemini B configuration with an escape tower. Diameter 

is the outside diameter of the laboratory. 

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3.3.6.1.5.2 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. 3.6.1.5. 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. 

3.3.6.2 Peculiar Performance and Design Requirements. 

3.3.6.2.1 Malfunction Detection System (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 sal, 

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 Band/or Laborator 

3. 3.6.2.1. 3 Safety Criteria. 

The probability that the booster will function properly or that 

a timely abort signal will be generated shall be 0.998 minimum. The proba- 

• bility that the MDS will not generate a false abort shall be 0. 994 minimum. 

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--C-ONFiREKKE3. 3.6.2.2 Transtage On-Orbit Characteristics. 

The transtage shall be available for 33 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 transtage 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 interf ace 

with the laboratory is at the gimbal servo valve. 

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3.3.6.2.2.1.3 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 provide 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: 

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 

for separation. 

3.3.6.2.2.4 

Retrorocket System. 

Transtage retrothrust shall be provided on the transtage 

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 

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transport of the assembled vehicle to the launch pad in a ready condition 

requiring only a combined system test and a discrete vehicle checkout. 

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. 

3.3.6.3 Functional Interfaces. 

(The contractor shall identify the functional interfaces 

between his system segments and other MOL system segments. ) 

3.3.6.4 Contract End Items. 

3.3.6.4.1 A. C. Spark Plug CEI's: 

Nomenclature Specification No. 

1. Inertial Measurement Unit ES 8499 

MX-6478 / DJQ- 1 

2. Computer, Missile Guidance 

CP-781 /DJQ- 1 

3. Controller, Pressure-Thermal ES 8497 

C-6281/DJQ-I 

4. Signal Conditioner ES 8484 

MX-6479/DJQ- 1 

5. Modulator, Pulse Code ES 8498 

MID-588/DJQ-1 

6. Reducer, Video Bandwidth ES 8529 

MX-6480/ DJQ- 1 

7. Alignment-Checkout Group ES 8403 

Missile Guidance AN/GJQ-26 

8. Console Guidance Monitor ES 8469 

9. Electrotheodolite Set, Azimuth ES 8509 

Alignment, Lg Rng, AN/GVQ-7 

10. Test Set, Missile Guidance System ES 8471 

AN/DJM- * 

11. Electrotheodolite Set, Azimuth ES 8489 

Alignment, Short Range AN/ 

• 

SSMD- 30-6 .itch. 6 

154 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

• 

--C-ONRENTIA 

Nomenclature Specification No. 

12. Battery-Power Supply Assembly ES 8476 

PP-4116/DJQ-1 

13. Shipping & Storage Container ES 8511 

Missile Guidance Computer 

CY-4432/DJQ-1 

14. Test Set, Video Bandwidth ES 8483 

Reducer AN/DJM-22 

15. Simulator, Pulse Code 

Modulator Input AN/ * 

16. Test Set, Telemetry AN/ * 

17. Monitoring Set, Telemetric 

Data AN/DKM-11 

18. Filler & Bleeder, Missile ES 8490 

Guid Coolant Sys HD-666/DJQ-1 

19. Coolant Fluid Tank * ES 8550 

20. Power Elec Cable Assys * 

21. Spec Purpose Cable Assys 4, 

22. Hoses, Extension, FC-75 ES 8555 

23. Distribution Box * 

24. Cable Assy, Power, Elec * ES 8541 

25. Voltage Regulator 4' ES 8542 

26. Carrier, Electronic Equip 4, 

27. Truck, Hand, Shelf a:, 

28. Scale, Beam, Indicating * 

ES 8540 

29. Sump- Vacuum Pump * 

30. Coller, Liquid Refrigerative 3:e 

31. Test Set, Signal Conditioner * 

32. Telemetry Mon-Recorder Gp * 

33. Monitor Group, Telemetric Data ES 8456 

0A-6835/DJM-11 

34. Distrib-Indicator Gp, Telemetric ES 8457 

Data 0A-6836/DKM-11 

3.3.6.4.2 Aerojet Gen. CEI's: 

1. Engine Rocket Liquid AGC40173 

• Propellant, YLR87-AJ-9 

• 

Atch. 6 

-eetflieffia- 3-155 SSMD- 30-6 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-e0t4fIEN-}14- • 

10.2 

APPENDIX B 

ENVIRONMENTAL CRITERIA SPECIFICATION 

• FOR THE 

MOL SYSTEM PERFORMANCE/DESIGN REQUIREMENTS 

GENERAL SPECIFICATION 

• 

SSMD -30 -6 Atch. 6 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-CONFIDER* 

ICD Area 35: 

ICD Area 36: 

ICD Area 37: 

ICD Area 38: 

ICD Area 39: 

ICD Area 40: 

ICD Area 41: 

ICD Area 42: 

ICD Area 43: 

ICD Area 44: 

ICD Area 45: 

ICD Area 46: 

ICD Area 47: 

ICD Area 48: 

ICD Area 49: 

ICD Area 50: 

ICD Area 51: 

ICD Area 52: 

ICD Area 53: 

ICD Area 54: 

ICD Area 55: 

ICD Area 56: 

ICD Area 57: 

ICD Area 58: 

Experiments /Modification Group List Per 

Flight 5 

Experiments/Modification Group List Per 

Flight 6 

Experiments/Modification Group List Per 

Flight 7 

Experiments/ Modification Group List Per 

Flight 8 

Data Management System/Laboratory 

Flight Crew/ TOSS 

Flight Crew/Modification Group List Per 

Flight 1 

Flight Crew/Modification Group List Per 

Flight 2 

Flight Crew/Modification Group List Per 

Flight 3 

Flight Crew/Modification Group List Per 

Flight 4 

Flight Crew/Modification Group List Per 

Flight 5 

Flight Crew/Modification Group List Per 

Flight 6 

Flight'Crew/Modification Group List Per 

Flight 7 

Flight Crew/Modification Group List Per 

Flight 8 

TOSS/ T -IIIC 

TOSS/Modification Group List Per Flight I 

TOSS/Modification Group List Per Flight 2 

TOSS/Modification Group List Per Flight 3 

TOSS/Modification Group List Per Flight 4 

TOSS/ Modification Group List Per Fligh:: 5 

TOSS/Modification Group List Per Flight 6 

TOSS/Modification Group List Per Flight 7 

TOSS/Modification Group List Per Flight 3 

TOSS/Data Management System 

--eetiFIDENNAt- - _6 Atch. 6 

10-4 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

C3. 3. 

-CONFIDENTIAL53. 

54. 

55. 

56. 

Nomenclature Specification No. 

Tank Alcohol 

Pump, Reciprocating 

Power Driven 

Test Set, Rocket Engine 

Test Set Electrical Circuit 

AGC40169 

AGC40169 

AGC40177 

AGC40178 

57. Tool Kit, Turbopump AGC40172 

58. Test Set, Facility Syst. AGC40198 

59. Rocket Engine AGC40197 

60. Nozzle Extension Kit RED 

61. Shipping Container AGC40199 

62. Stand, Maintenance AGC40193 

63. Adapter, Maint. Stand AGC40201 

64. Test Kit, Pressure AGC40202 

65. Transport and Installation AGC40199 

Kit, Nozzle Extension 

66. Test Set, Functional AGC40194 

67. Cleaning & Purging Equip 

68. Adapter Kit, Cleaning System AGC40200 

69. Pump, Reciprocating 

70. Cleaning & Purging Equip 

71. Connecting Kit, Purge Set AGC40200 

7Z. Test Set, Electrical AGC40195 

73. Alignment Tool AGC40196 

74. Purge Set, Portable 

75. Connecting Kit, Purge AGC40200 

76. Connecting Kit, Purge Set AGC40200 

77. Link, Restrainer, Gimbal AGC40199 

6.4. 3 Martin Denver CEI's: 

1. Detail Spec for Standard Space D-SLV/1A010 

Launch Vehicle (SSLV) 

2. Detail Spec for Flight Control D-SLV/01D110 

Adapter - Programmer 

3. Identification Spec for Standard SSS- TIII-ID-SLV 

Space Launch Vehicle 

-C-OtiffEtifikE SSMD- 30-6 

Atch. 6 

3-158 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

—eetiFIDENTIALNomenclature Specification No. 

4. Air Scoop and Nut Catcher ID-SLV/01K000 

5. Attachment Kit, Rocket Motor ID-SLV/02K000 

Boosters 

6. Dummy Payloads ID-SLV/O1K100 

7. Adapters, Dummy Payloads ID- SLV/ 01K200 

8. Connector, Electrical-Rocket ID-SLV/02L003 

Motor Ground Power 

9. Cable Assembly Set, Electrical- ID-SLV/ 02 L002 

Rocket Motor Staging Disconnect 

10. Fairing, Payload ID-SLV/01K300 

11. Detail Spec for Hold-down Set, D-OGE/01B581 

Explosive 

12. Detail Spec for Stray Voltage D-OGE/01B583 

Detector 

13. Detail Spec for Propellant D-OGE/01C101 

Loading Unit, Fuel 

14. Detail Spec for Propellant D-OGE/01C102 

Loading Unit, Oxidizer 

15. Detail Spec for Propellant D-OGE/01C109 

Servicing Unit 

16. Detail Spec for Nitrogen D-OGE/01C401 

Pressure Controller 

17. Detail Spec for Pumping Unit, D-OGE/01C601 

Hydraulic Mobile 

18. Detail Spec for Vehicle Air D-OGE/01C703 

Conditioner (P-20) 

19. Detail Spec for Water Chiller D-OGE/01C705 

(Guidance Package) 

20. Detail Spec for Air D-OGE/01C706 

Conditioner (Vehicle) 

21. Detail Spec for Van Power D-OGE/01 EAAO 

Distribution Control 

22. Detail Spec for Control Center D-OGE/O1EABO 

Power Distribution Control 

23. Detail Spec for Power Supply D-OGE/01 EACO 

24. Detail Spec for Launch Pad D-OGE/ 01 EAEO 

Power Distribution Control 

• 

Atch. 6 

SS:v1D- 30-6 —C-CORDENTRE-- 3- 15') 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

ittettetttAt 

Nomenclature Specification No. 

25. Detail Spec for Vehicle D-OGE/O1FBOO 

Checkout Set 

26. Detail Spec for Propellant Transfer 

and Pressurization Control Set 

D-OGE/01FC00 

27. Detail Spec for Data Transmission D-OGE/01FDA0 

Group I 

28. Detail Spec for Data Transmission D-OGE /0 1 FDBO 

Group II 

29. Detail Spec for Data Recording Set D-OGE/01FBOO 

30. Detail Spec for Combined System D-OGE/OIFFOO 

Test Simulator Set 

31. Detail Spec for Solid Booster D-OGE/O1FGOO 

Simulator 

32. Detail Spec for Launch Control D-OGE/OIFJO0 

Console 

33. Detail Spec for Control Monitor D-OGE/O1FLOO 

Group 

34. Detail Spec for Recorder- D-OGE/01GC00 

Reproducer Set, Voice 

35. Detail Spec for Flight D-OGE/ 01JAA0 

Safety Checkout CMG 

36. Detail Spec for Pulse Tracking D-OGE /01JABO 

CMG 

37. Detail Spec for Tracking and D-OGE/O 'JACO 

Flight Safety Monitor Group 

38. Detail Spec for Frame, 

Transporter, SSLV 

D-OGE/01N032 

39. Detail Spec for Launch Mount, 

SSLV Transporter 

D- OGE /01 N033 

40. Detail Spec for Umbilical Masts, 

SSLV 

D-OGE/01N034 

41. Detail Spec for Cable Support D-OGE/01N035 

42. Detail Spec for Frame Support, 

Solid Motor 

D-OGE/01N036 

43. Detail Spec for Undercarriage D-OGE/01N043 

Assembly, SSLV Transporter 

44. Detail Spec for Space Vehicle D-OGE/01N571 

Checkout - Launch Control 

Equipment, Rail Van Mounted 

• 

• 

Atch. 6 

-COMMENT-Kt SSMD- 30-6 

;-160 
NRO APPROVED FOR 

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-feRFRENT-thi- 

• 

• Nomenclature 

45. Detail Spec for Space Vehicle 

Checkout - Instrumentation 

Equipment, Rail Van Mounted 

46. Detail Spec for AGE Van 

47. Detail Spec for Air Conditioner 

AGE Van 

48. Detail Spec for Dehumidifier, 

AGE Van 

49. Detail Spec for Trailer, SSLVStage I; & Trailer, SSLV, Transtage 

& Interface Section or Stage II 

50. Identification Spec for Operating 

Ground Equipment (OGE) 

51. Propellant Ready Storage Vessel, 

52. 

53. Tank, Storage, Gaseous Helium 

54. Ordnance Items Test Set 

55. Countdown Readout 

56. Bolt and Nut Set, Static 

57. Ladders, Personnel 

58. Net, Safety, Maintenance 

59. Service Platform - SSLV, 

Internal Access 

60. Crane, Floor, Portable 

61. Platform Set, Service 

Engine Compartment, Stage II 

62. Launch Mount (P-20) 

63. Erector Weather Protection 

Curtains (P-20) 

64. Service Platform Set, SSLV 

Transporter 

65. Net Set, Safety, SSLV 

Transporter 

66. Guard Set, Sill, Access Door 

67. Servicing Platform Set -

Adapter, Payload Fairing, MST 

Specification No. 

D-OGE/01N572 

D-OGE/01N573 

D-OGE/01N575 

D-OGE/01N576 

D-OGE/01P102/4 

SSSID-OGE/01C104 

ID-OGE/01C410 

ID -OGE/01FNO0 

ID-OGE/01FNO0 

ID-OGE/01N523 

ID-OGE/01N524 

ID-OGE/01N525 

ID-OGE/01N526 

ID-OGE/01N527 

ID-OGE/01N528 

ID-OGE/01N530 

ID-OGE/01N532 

ID-OGE/01N554 

ID-OGE/01N555 

ID-OGE/01N561 

ID-OGE/01N562 

• 

SSMD- 30-6 -C-OtifiRENTIAL- Atch. 6 

3-16I 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-C-OffilktittAt 

Specification No. e Nomenclature 

68. Servicing Platform Set -

Adapter, Payload Fairing, UT 

69. Servicing Platform Set -

Adapter, Payload Fairing, VIB 

70. Test Stand Service Platform 

Set (P-20) 

71. Servicing Platform Set (P-20) 

72. Crane, Floor, Portable 

73. Thrust Mount Tool Kit (P-20) 

74. Ring, Handling, SSLV - Forward 

(Stage I, Stage II and Transtage) 

75. Ring, Handling SSLV -

Aft, (Stage II) 

76. Breather, Propellant Tank, 

Stage I 

77. Breather Set, Propellant Tank, 

Stage II 

78. Breather Set, Propellant Tank, 

Transtage 

79. Cover, Protective, SSLV - Stage I 

80. Cover, Protective, SSLV - Stage II 

81. Cover, Protective, SSLV 

Propellant Tank Dome, Stage I 

82. Deleted 

83. Erection Fixture, SSLV - 

Stage I and Stage II 

84. Cover, Protective, SSLV -

Transtage and Interstage 

85. Transport Adapter, Transtage 

and Interstage 

86. Restraining Fixture, MST 

87. SSLV Positioning Set, (P-20) 

88. Positioning Set, SSLV (MST) 

89. Tool Kit, Handling Equipment (MST) 

90. Tool Kit, Launch Mount 

91. Positioning Set, SSLV - Stage I, 

Stage II and Transtage, VIB 

ID-OGE/01N563 

ID-OGE/01N564 

ID-OGE/01 N565 

ID-OGE/01N567 

ID-OGE/01N569 

ID-OGE/01P101 

ID-OGE/01P110 

ID-OGE/01P111 

ID-OGE/01P112 

ID-OGE/01P113 

ID-OGE/01P114 e 

ID-OGE/01P115 

ID-OGE/01P116 

ID-OGE/01 P119 

ID-OGE/01P120 

ID-OGE/01P122 

ID-OGE/01P123 

ID-OGE/01P124 

ID-OGE/01P126 

ID-OGE/01P127 

ID-OGE/01P133 

ID-OGE/01P139 

ID-OGE/01P140 

fb-OGE/01P142 

-C-ONFIDERA-L- SSMD- 30-6 Atch. 6 

3-162 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-6ANfIBENTItE 

92. 

93. 

94. 

Nomenclature Specification No. 

Tool Kit, Launch Nut 

Carrying Case, Ordnance Items 

Deleted 

ID-OGE/01P148 

ID-OGE/01P149 

ID-OGE/01P150 

95. Payload Fairing Positioning ID-OGE/01P151 

Set (P-20) 

96. Positioning Set, Payload ID-OGE/01P152 

Fairing (MST) 

97. Positioning Set, Payload ID-OGE/01P154 

Fairing VIB 

98. Platform Set, Space Vehicles ID-OGE/01P156 

99. Alignment Kit, Solid Rocket Motors ID-OGE/01P157 

100. Accessory Set - Dew Point ID-OGE/01P202 

Indicator 

101. Adapter, Torque Wrench - ID-OGE/01P208 

Retro Motor 

102. Detector, Helium Tracer Gas ID-OGE/015910 

103. Handling Set, Solid Rocket Motor ID-OGE/02P155 

104. Detail Specification for Test Stand, 

Hydraulic System Components 

D-MGE/01C602 

105. Detail Specification for Space D-MGE/01C603 

Vehicle Hydraulic Servicing Unit 

(P-20) 

106. Detail Specification for Test Stand, 

Pneumatic Components 

D-MGE/01N310 

107. Detail Specification for Hydraulic D-MGE /0 INBOO 

Control Unit 

108. Identification Specification for SSS- TIII-ID-MGE 

Maintenance Ground Equipment 

109. Decontamination Apparatus, Bench ID-MGE/01N304 

110. Decontamination Apparatus, 

Stationary, Tank 

ID-MGE/01N305 

111. Heater, Nitrogen ID-MGE/01N31 1 

112. Maintenance Equipment Test Set ID-MGE/01NFO0 

3.3.6.4.4 United Technology Co. CEI's: 

1 Rocket Motor 

2. Tank Assembly, Thrust 

Vector Control 

-CONFIDENTIAL4MDSE03101 

4TDSE51714 • 

SSMD- 30-6 

Atch. 6 

3-16i 

• 

e 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-C-OtifiERT-14- 

Nomenclature Specification No. 

3. Nozzle and Thrust Vector 4MDSE71601 

Control Assembly 

4. Electrical Cable Set, 

Rocket Motor 

4AISE60901 

5. Battery Assembly - ISDS 4MISE53501 

6. Battery, Wet, Primary - TVC 4MISE53501 

System 

7. Battery, Storage - Instrumentation 4MISE53501 

8. Loaded Closure, Forward Assembly 

of 

4MISE63201 

9. Loaded Segment 4MISE63201 

10. Loaded Aft Closure - Assembly of 4MISE63201 

11. Safety and Arming Device - TT 

and Destruct 

4MISE63001 

12. Safety and Arming Device - Igniter 4MISE63001 

13. Igniter - Rocket Motor 4MISE63001 

14. Ordnance Set, Thrust Termination 4MISE63001 

15. Ordnance Set, Destruct System 4MISE63001 

16. Mechanical Hardware Set, Forward 4AISE63301 

Closure Sub Assembly 

17. Mechanical Hardware Set, Aft 4AISE63301 

Closure Sub Assembly 

18. Mechanical Hardware Set, 

Rocket Motor 

4AISE63301 

19. Mechanical Hardware Set, 

Rocket Engine Attachment 

4AISE63301 

20. Mechanical Hardware Set, 

TVC Tank Assembly 

4AISE63301 

21. Mechanical Hardware Set, 

Instrumentation Raceway 

4AISE63301 

22. Mechanical Hardware Set, Section 4AISE63301 

23. Mechanical Hardware Set Staging 4AISE63301 

Rockets 

24. Fairing, Nose Section, Rocket 4AISE63301 

25. Fairing, Cluster, Rocket Motor - 4AISE63301 

Staging, Forward 

26. Insulated Cover - Thrust Termination 4AISE63301 

• 

• 

CONRENT4AL SSMD-30-6 

Atch. 6 

164 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Nomenclature Specification No. 

51. Fixture, Handling, Nozzle- 4GISE81-05 

Nozzle Exit Cone Extension 

52. Beam, Hoisting, Segment- 4GISE81-05 

Closure 

53. Fixture, Hoisting, Segment, 

Aft Closure Sub-Assembly 

4GISE81-05 

54. Fixture, Support, Aft Closure 4GISE81-05 

55. Fixture, Support, Segment 4GISE81-05 

56. Stand, Inspection-Subassembly, 

Segment-Closure 

4GISE81-05 

57. Ring, External, Segment-Forward 4GISE81-05 

Closure 

58. Ring, External, Segment-AFT 4GISE81-05 

Closure 

59. Fixture, Inverting, Segment- 4GISE81-05 

Closure 

60. Beam, Hoisting-Segment, Closure 4GISE81-05 

Container 

61. Fixture, Hoisting, AFT Closure 4GISE81-05 

62. Funnel, N204 Drain 4GISE81-05 

63. Beam, Hoisting-TVC Tank 4GISE81-05 

Assembly Trailer 

64. Fixture, Hoisting-Forward Closure 4GISE81-05 

65. Adaptor, Hoisting-Forward 4GISE81-05 

Closure Subassembly 

66. Beam, Hoisting, Nozzle Container 4GISE81-05 

67. Installation Kit - Nozzle 4GISE81-05 

68. Adapter, Closure 4GISE81-05 

69. Installation Kit-Nozzle Exit 4GISE81-05 

Cone Extension 

70. Guide-Support Skirt Installation 4GISE81-05 

71. Fixture, Hoisting, Vertical-TVC 4GISE81-05 

Tank Assembly 

72. Fixture, Handling-Injectant 4GISE81-05 

Transfer Tube 

73. Wire Rope Assembly, Single Legs 4GISE81-05 

• 

• 

:ch. 6 -C-OffileffItct SS NA D- 30-6 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

• 

• 

-EONFWE-tifttcl-- 

Nomenclature Specification No. 

74. Fixture, Handling, Igniter 4GISE81-05 

Cartridge - Igniter Case 

75. Fixture, Hoisting-Igniter Closure 4GISE81-05 

76. Plate, Retaining-Igniter Cartridge 4GISE81-05 

77. Installation Kit-Igniter 4GISE81-05 

78. Adaptor, Hoisting - TT Port 4GISE81-05 

79. Installation Kit - TT Port Cover 4GISE81-05 

80. Fixture, Hoisting-Nose Section 4GISE81-05 

Support Skirt 

81. Wrench, Safety and Arming Device 4GISE81-05 

Plug 

82. Cover, Protective, SRM 4GISE81-05 

Components 

83. Cover, Protective, SRM 4GISE81-05 

Components 

84. Rack, Pallet Storage 4GISE81-05 

85. Pallet, Material Handling 4GISE81-05 

86. Pin, Straight, Headless 4GISE81-05 

87. Maintenance Kit, Tank Pressurization Control System 

4GISE81-06 

88. Recorder, Temperature-Humidity 4GISE81-06 

89. Recorder, Shock 4GISE81-06 

90. Recorder, Temperature 4GISE81-06 

91. Chamber, Explosion Proof 4GISE81-06 

92. Kit, Leak Detection, TVC Tank 4GISE81-06 

Assembly 

93. Lead, Electrical 4GISE81-07 

94. Cable Assembly, Power, Electrical 4GISE81-07 

95. Cover, Protective, Propellant, 

Segment-Closure 

4GISE81-08 

96. Cover, Protective, Nozzle Flange 4GISE81-08 

97. Hose, Airduct, Temperature 4GISE81-08 

Control Unit 

98. Cover, Protective-Aft Closure Port 4GISE81-08 

99. Cover, Protective, TT Port 4GISE81-08 

Atch. 6 

SSMD- 30-6 —eettftlIENT-t* 3-167 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-CONFIN-t+TiklNomenclature Specification No. 

100. Cover, Protective-Igniter Port 4GISE81-08 

101. Maintenance Platform, Portable 4GISE82-01 

102. Press, Forcing, Hydraulic 4GISE82-01 

103. Stand, Maintenance-Igniter 4GISE82-01 

104. Adapter, Installation-Removal 4GISE82- 01 

Quick Release Pin 

105. Maintenance Kit, Environmental 4GISE82-01 

Control System 

106. Removal Tool, Pin, Straight, 

Headles s 

4GISE82-01 

Atch. 6 

3-168 -C-ENIFIDERkl-- SSMD- 30-6 

• 

• 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CONFIDENTIAL 

• 

• 

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-segments; 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, postflight 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 (SPO), SSD. The nominal point 

of control shall be located at CKAFS. 

• 

SSMD- 30-6 -CONFIDER.* Atch. u 

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—C-effEtifitcE3.3.7.1 Performance Allocations. 

3.3.7.1.1 Effectiveness. 

Although redundancies and maintenance permit high system 

effectiveness of TOSS in control, communication, and recovery modes, it is 

also essential that all aspects of range support attain a high effectiveness. 

A specific value of 0. 999 has been assigned. However, as a result of task 

identification and breakdown, it may become desirable to negotiate a lower 

level to 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. 

3. 3.7.2 Functional Requirements 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 

e 

• 

4 

-eeNFRENfitrE SSMD-10-6 

Atch. 6 

- 170 
NRO APPROVED FOR 

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range support 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. 

3.3.7.2.12.1 Launch Control. 

Prior to lift-off, all launch control capability will be contained within the ITL/T-III (LCC) complex at Cape Kennedy. Decisions as to 

readiness of the test 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. 

3.3.7.2.1.2.2 Vehicle/Crew Control. 

This function shall be physically located in the MCC and, for 

all intents and purposes, is the prime function for mission control from liftoff 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 recources. 

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. 

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3.3.7.2.1.2.4 

Control Center. 

3.3.7.2.1.2.5 

Range Safety. Safety. 

Range Safety control is exercised at the ETR Range Safety 

Recovery Control. 

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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 forces 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. 

3.3.7.2.1.3 Instrumentation and Communications Network. 

During the countdown the ETR instrumentation systems are 

e x ercised 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. 

3.3.7.2.2 

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 vehicle and crew status, and 

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 

Ascent Phase. 

The ascent phase extends from lift-off until injection into 

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I 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, including range and crew safety, during 

ascent. Data derived from combinations of range, range rate, and interferometry systems at uprange ETR shall be used for 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 deter- 

• mining 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 sites from launch vehicle; OV and crew from before lift-off to the 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. 

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3.3.7.22.4 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 and 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, IIP, 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 nearreal 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 powered flight phases 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. 

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 at 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. 

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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, including deployment of forces on 

the geoid, in the atmosphere, and in space. The time constraints associated with the experiment control function arc. only critical with regard to 

scheduling; other functions normally operate in a control cycle on the order 

of several hours to several days. 

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. Call-up tracking to 

support emergencies is a consideration. In the case where velocity changes 

are applied to the OV for orbit phase changes or maneuvers, at least 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 it in real time. It shall be possible to 

select a different set or the same set of data, edit or summarize it and transmit it 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 

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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 capability to command the Gemini B systems 

required for re-entry. 

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 expecte, 

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. 

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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 

orbit and relatively continuous 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 minimum 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. 

3.3.7.2.4 Loiter & Re-entry Phase. 

The Loiter & Re-entry Phase extends from separation of 

Gemini B and Laboratory to water impact. 

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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 tape 

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 

and emergency contingency areas during this phase. 

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3.3.7.2.4.5 Communications. • 

Communication requirements shall support the Gemini B 

only. More extensive support will be required of the worldwide communication 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. 

3.3.7.2.4.6 Data Handling, Computation, and Display. 

Gemini B 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. 

3.3.7.2.5 Recovery Phase . 

The recovery phase extends from water impact to retrieval 

of crew, spacecraft, and data. 

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3.3.72.5.1 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 in 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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-CetiftfrEtifhtt3. 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-oribt 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 onorbit phase and altitude changes. The possibility of maneuvers by both 

0. V. 's complicates the tracking procedures. The worldwide tracking system 

also shall meet a requirement to support emergency abort of the chaser 

vehicle and emergency de-orbits of both the chaser vehicle and target vehicle during the period 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 chaser vehicle. Telemetry 

acquisition requirements for the target vehicle shall be as described for the 

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• 

on-orbit phase; requirements for the chaser vehicle shall be as described 

according to the mission phase in progress. 

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 phase; 

requirements for the chaser vehicle shall be .ts described according to the 

mission phase in progress plus those commands necessary to solve the 

intercept-rendezvous problem. 

3.3.7.2.6.5 Communications. 

Communication requirements for both vehicles shall be in 

accordance with the mission phases in progress. 

411 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 intercept-rendezvous problem and provide control of the chaser 

vehicle and the target vehicle prior to rendezvous. 

3. 3. 7. 2. 6. 7 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. 

3.3.7.3 Functional Interfaces. 

(The contractor shall identify the functional interfaces 

between his system segments and other MOL system segments.) 

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3.3.7.4 Contract End Items. 

(The contractor shall provide for incorporation in this paragraph a list by contract and item number, nomenclature and the CE1 to which 

it installs, all contract and items included in his system segment. ) 

3.3.7.5 

3.3.7.5.1 

TOSS Design Requirements. 

Mission Control Sub-Segment. 

• 

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). 

3.3.7.5.1.1 Mission Control Center. 

The Mission Control Center shall provide the following 

capabilities: 

a. Display and control consoles for 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. 

1. Data buffering storage and retrieval subsystem for 

formatting, buffering, filing, retrieval and outputting 

telemetry data. 

11. Interfaces with the launch and checkout complexes. 

h. Command storage and processing subsystem. 

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• The following supporting elements shall be required, suitably interfaced with or incorporated in the MCC: 

a. Real time computer complex. 

b. Communications switching terminal. 

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. 

3.3.7.5.1.2 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 

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Data correlation 

Data file for retrieval 

Data trend analysis 

Compute and format updated IGU 

Compute and format stored program functions 

Compute and format orbit changes 

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. 3.7.5.1. 3 Ground System Simulation Element. 

The Ground System Simulation Element shall provide the 

capability to simulate all mission phases and operations, including 

rendezvous-intercept, to the degree that the real time data system, including 

operational computer programs, and 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 

clement 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 remote sites): 

a. MCC open loop - the simulation computer (with its 

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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. 

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 techniques 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 fly-by 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 most practicable realistic overall mission simulation. 

3. 3.7.5.2. 1.2 Loading. 

The ground network shall be required to provide support for 

two MOL orbiting vehicles in various flight phases conducting an on-orbit 

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rendezvous mission. Consideration shall be given to the fact that certain 

remote sites may be involved in other multi-mission support operations. 

3.3.7.5.2.1.3 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 system, and voice 

communications between the vehicle flight crew and the 

flight control personnel through the ground network. 

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. 

Provisions also for real time displays of the selected 

data or different data at primary remote sites shall be 

included. During the early orbit phase, simultaneous 

selection of data from both the Gemini B and Laboratory 

real time links for local site display and transmission 

to the MCC shall be required of the primary remote 

sites. 

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 

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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 - 400 me using AM modulation shall be 

required at specific remote sites. 

f. Special telemetry links for experiment data in the 

2200 - 2300 megacyle R-F band shall be 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. 

In addition, the design of the Test Support Sub-segment 

and its technical and operational interfaces with the 

Mission Control Sub-segment shall consider the expected evolution of a standard instrumentation system for 

support of DOD space program development. This 

development will involve the use of a minimum number 

of remote sites and a standardized integrated S-band 

TT&C system such as the AFSSD Space-Ground Link 

Subsystem (SGLS). 

3.3.7.5.2.1.4 Network Stations. 

The network stations tentatively selected as remote sites 

necessary for mission data acquisition and control of the MOL orbiting vehicle are listed as follows: 

3.3.7.5.2.1.4.1 Cape Kennedy (CKAFS). 

The employment of the resources at CKAFS shall include 

all the instrumentation necessary for the launch and ascent phases of the 

flight. Cape Kennedy also shall be utilized as a primary on-orbit station 

having telemetry reception, radar tracking, command, transmission, and 

air-to-ground voice capabilities. In addition, a secure capability shall be 

implemented for telemetry reception and air-to-ground/ground-to-air voice 

communications when required by mission operations. 

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capability shall be implemented for telemetry and air-to-ground voice reception when required by mission operations. 

3.3.7.52.1.4. 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 and air-to-ground voice reception 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. 

3.3.7.5.2.1.4.6 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 

considieration are Point Arguello and the Vandenberg Tracking Station. A 

secure capability shall be implemented for telemetry and air-to-ground 

voice reception 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. 

3.3.7.5.2.1.4.7 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. 

3.3.7.5.2.1.4.8 White Sands, Eglin. 

These two stations shall be used as backup for C-band radar 

tracking for early orbital ephemeris determination and for support of planned recovery. 

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3.3.7.5.2.1.5 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 

feasible, all primary on-orbit stations shall be netted with the MCC at 

CKAFS utilizating hardwire or equivalent circuits. Requirements for the 

communication support functions are described as follows: 

3.3.7.5.2.1.5.1 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. The local site controller shall have patch-in capability. 

3.3.7.5.2.1.5.2 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. 

3.3.7.5.2.1.5.3 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 Carnarvon, Australia site. All primary stations within the 

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-C-OtiFfEttihtlcontinental U. S., i. e. , Cape Kennedy, Antigua, and the West Coast area, 

shall be netted with the MCC for telemetry transmission utilizating 40,800 

bps HSD lines and a backup 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. 

3.3.7.5.2.1.5.4 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 site 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. 

3.3.7.5.2.1.5.5 Tracking Data Transmission. 

Tracking data for the ascent phase of the mission shall be 

transmitted to the MCC for real time control from the remote stations 

utilizing HSD lines to the extent possible. 

Special ascent and early orbit considerations will require 

real time transmission of tracking data over HSD lines. 

Routine on-orbit tracking for ephemeris up-dating shall 

utilize 100 wpm teletype where HSD lines are not conveniently available. 

3.3.7.5.2.1.5.6 Security. 

In addition, the ground communication network shall provide 

for secure transmission of telemetry data and voice from the Okinawa area, 

Hawaii area, West Coast area, and Antigua. 

3.3.7.5.2.2 Meteorological Support Element. 

The Meteorological Support Element shall provide weather 

data obtained from various reporting and forecast sources necessary to 

support the MOL mission. 

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3.3.7.5.3 Recovery Recovery Sub- s egment. 

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. 

3.3.7.5.3. 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 HC-130 airplane 

equipped with HF and UHF/DF 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 for 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 and 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 reaction in case crew abort is initiated. 

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-CONFIfftifht-L3.3.8 Facilities Systems Segment. 

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. 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 1TL 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 Orbiting 

Vehicle while on the launch vehicle, suitable parking areas for the Orbiting 

Vehicle AGE rail vans and fluid servicing units, and adequate services for 

the support of Orbiting Vehicle launch operations. Means shall be provided 

to effect the safe removal of the flight crew to at least 800 feet from the 

Gemini B 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-pad 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 VIE shall be modified 

to provide an environmental enclosure for the Orbiting Vehicle while on the 

launch vehicle, suitable parking areas for necessary Orbiting Vehicle AGE 

rail vans, and adequate services for the support of the TIII/Orbiting Vehicle 

integration and checkout. 

The VIE launch control center and connecting cable ways and 

ducting between the AGE vans and the launch control center shall be modified 

as required for spacecraft AGE installation. Existing areas shall be utilized 

with modifications, where required. The GEM communication lines, which 

connect the launch complex and the launch control center, shall be modified 

to satisfy MOL system requirements. 

3.3.8.2 Industrial 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 ag.sernbly 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 components 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 Inspection and Storage (RIS) building in the ITL 

system shall be considered for this function. 

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3.3.8.2.2 Simulator Facilities. 

Facilities shall be provided as required to operate an Orbiting Vehicle Mission Simulator in conjunction with the Mission Control Center 

and the world wide tracking net. 

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, Missile Simulation 

Facility, Range Safety and Range Control, and range tracking station communications nets shall be installed. 

3.3.8.3 Telecommunications, Tracking 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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—eetiFIE}Etifia4. 0 PERFORMANCE/DESIGN VERIFICATION AND TEST. 

This section specifies the formal tests and verification method,' 

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 GROUND TEST REQUIREMENTS. 

4. 1. 1 Development Tests. • 

4. 1. 1. 1 General Requirements. 

Design development 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 TIJ1C-Orbiting 

Vehicle shall be conducted to determine aerodynamic characteristics of the 

combined vehicle. 

4. 1. 1. 3 Orbiting Vehicle Requirements. 

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4.1.1.3.1 Space Simulation Test. 

The Orbiting 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 Orbiting Vehicle may be simulated. During 

this test specific performance of the normal and emergency crew transfer 

shall be accomplished. Contaminant measurem,!.nts 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. 

4.1.1.3.3 Rendezvous and Docking Test. 

Simulations shall be performed to demonstrate the ability of the 

chase Orbiting Vehicle to perform the necessary rendezvous maneuvers. 

Docking tests shall be conducted for development and demonstration of the 

Rendezvous and Docking system, 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 capability 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 

attached. 

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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 specified 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 Acoustic 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 ability of the Laboratory Vehicle to withstand meteroid 

impact and particle radiation shall be demonstrated by subjecting Laboratory 

structural sections to simulated meteoroid and particle radiation environment. 

4.1.1.4.5 Atmospheric Contaminant Test. 

A materials atmospheric contaminant test shall be conducted on 

the pressurized atmospheric environment of the Laboratory in a thermalvacuum space simulation chamber for a time period sufficient to identify 

contaminants and predict 30 day contaminant concentrations. Broad 

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spectrum measurements by infra-red gas chromatrographic and/or mass • 

spectrophotometric techniques will be used to determine significant toxic 

contaminants. Such tests to be defined to Phase I and performed in Phase II. 

4.1.1.5 Gemini B Requirements. 

4.1.1 . 5.1 General. 

The Gemini B 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. 

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 thermal-vacuum 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. 

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. 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. 

4.1.1.5.7 Flight Crew Transfer Tests. 

Tests shall be performed to demonstrate and verify the feasibility 

of the normal and emergency flight crew transfer between the Gemini B and 

the Laboratory. Inflated suit and an incapacitated flight crewman in an 

emergency situation shall be simulated. 

4.1.1.5.8 Abort Tests. 

Additonal 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 flight crew safety. 

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. 

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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 transtage 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 complete development testing to demonstrate 

capability to meet MOL environmental storage, flight crew transfer, extravehicular, and other mission requirements. 

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, mock-flights, 

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 system 

under conditions simulating pre-launch, launch, and on-orbit operations. 

Due to the size and complexity of the over-all flight vehicle there 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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4-0NFRENTIAL4.1.2.4 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 SSD 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 flight crew transfer shall be qualified to the specified environmental requirements. The qualification tests of the Laboratory shall be 

performed when possible on the Laboratory, flight 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 and Docking Equipment. 

The rendezvous and docking equipment, including the coupling 

mechanism, flight crew passage tunnel, electrical connections, and plumbing, shall be qualified to the specified environmental requirements including 

the ability to properly function for a period of sixty days on orbit. 

-1.1.2.5 Gemini B Requirements. 

The Gemini P system segment shall be qualified per the requirements of the Environmental Specification. Components and/or sub-systems 

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 of 

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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4.1.2.6 Experiments Requirements. 

The experiments shall be qualified at the sub-segment or component level using as a basis the environmental requirements specified in 

Appendix B. 

4.1.2.7 T-III Requirements. 

The T-III system segment shall be qualified per the requirements 

of SSD Exhibit 62-166A, "Environmental Requirements Specification, Program 624A", Rev. A, dated 1 July 1964. The applicable sub-system of 

Titan III transtage shall be qualified for 30 days on-orbit. 

4.1.2.8 Flight Crew and Flight Crew Equipment Requirements. 

Flight Crew equipment qualified for NASA Gemini shall not be 

arbitrarily requalified but shall be analyzed on a basis of environmental 

exposure from previous testing flight test history and contemplated usage in 

the MOL system environment. The flight crew system segment equipment 

shall be subjected to a qualification test including the sequence of mission 

operations from launch, on-orbit including extra-vehicular activities, 

re-entry and recovery. 

Training equipment and simulators shall be qualified to requirements consistent with their application and interfaces with other equipment 

as specified in the contract end items specifications. 

4.1.2.9 Test Operational Support Segment (TOSS) Requirements. 

Formal qualification of the overall TOSS segment (equipment, 

personnel and procedures) shall be domonstrated by successful completion of 

the functional development testing and compatibility testing called 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. 

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Experiment support equipment such as ground targets and special 

receiving facilities shall be qualified to meet the functional requirements of 

the experiment, the local installation environment and the operational life 

requirements specified in the experiment. 

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4.1.3 Effectiveness (Reliability) Testing. 

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 sub-system 

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 are intended to be more severe than field conditions, but are not 

intended to exceed reasonable safety margins or to excite unrealistic modes 

of failure. Extended time and stress limit tests shall be phased in with the 

qualification test program. 

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0 4.1.4 Acceptance and Flight Readiness Tests. 

4.1.4.1 Acceptance Test Requirements. 

Acceptance tests shall be conducted to demonstrate that the 

required design, performance, and reliability levels have been achieved on 

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 but 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 sub-system 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. Acceptance 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. 

4.1.4.3 Orbiting Vehicle Requirements. 

The acceptance of the Laboratory, flight 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. 

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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 sub-systems 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. 

4.1.4.7 Titan III Requirements. 

The Titan LLI system segment shall be acceptance tested to the 

requirements of SSD 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. 

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4.1.4.8 Flight Crew and Flight Crew Equipment Requirements. 

The flight crew and flight crew equipment segment shall be 

acceptance tested at the component and/or sub-system level. These requirements will be detailed in an AFAMD/AFEFTC environmental requirements 

specification exhibit for the flight crew and flight crew equipment. In 

general, the components and/or sub-systems 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 specification and by complete functional operation. Compatibility with other sub-system and segments shall be 

demonstrated in all planned sequences and modes of operations. 

4.1.4.9 Test Operational Support Segment (TOSS) Requirements. 

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 

equipment 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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-e9tifiDENT-ht4.2 MOL SYSTEM FLIGHT 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 complete 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/ 

verifications 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 operable sub-systems, but the Laboratory shall be only 

structurally complete. The Gemini B shall be separated from the laboratory 

for retro, re-entry, 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. In 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 sub-systems operation; and operational 

readiness of the ground and flight systems. 

4.2.3 Orbital Flights. 

The second MOL flight (first orbital flight) shall be either unmanned or manned with orbital characteristics corresponding to the mission. 

The Laboratory shall incorporate critical sub-systems for initial evaluation 

and a Gemini B with fully operable sub-systems. The flight shall be of short 

orbital duration. The mission duration shall be dependent upon Laboratory 

Sub-system status. The Gemini B shall be separated for retro, re-entry, 

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and recovery in a primary recovery area. This effort shall demonstrate the 

initial orbital capabilities of the Gemini B and Laboratory systems and 

initially demonstrate the Test Operational Support system. As a manned 

mission, the flight will also allow a preliminary check of orbital capability 

of the flight crew, crew transfer to the Laboratory, and the critical Laboratory sub-systems. Verification of Gemini B Sub-systems will be accomplished for launch, a short duration on-orbit mission, re-entry, 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 non-interference 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 technology experiments shall be programmed so as to 

utilize the available factors of weight, volume, power, schedule, and flight 

crew duty cycles. 

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. The objective of the 

mission is to remain on orbit up to sixty days after exchanging one crew 

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member, and transferring expendables such as astmosphere gas and electric 

power as required, while docked with the target Orbiting Vehicle. 

The chase 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 chase 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. 

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4.3 Engineering Changes. 

Deficiencies encountered during the system tests shall be 

completely detailed and Engineering Change Proposals (ECP's) or System 

Change Notices (SCN'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 include unusual requirements for: 

a. Special pressure, thermal, or other environmental control 

required during transportation. 

b. Peculiar hoists, handling dollies, containers, and/or protective covers. 

c. Safety devices for ordnance/igniters. 

d. Special methods, load, shock, etc., limitation during the 

handling process. 

5.1 PACKAGING FOR GEMINI B AND LABORATORY. 

Recommendations shall be made for the preservation, packaging, 

packing, marking, and storage/stowage requirements for the life support 

items, 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 the 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 assure compatibility of the packaging materials and methods that are recommended with these environments. Consideration shall be given to compatibility of the packaging with 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. 

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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 AFSCM 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 a 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 developing an organization and structure to the 

Specification Tree (since a long row of CEI specifications all on the same 

level is not very meaningful), a dotted box will be used where 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 

APPENDIX A 

S INTERFACE REQUIREMENTS 

FOR THE 

MOL SYSTEM PERFORMANCE/DESIGN REQUIREMENTS 

GENERAL SPECIFICATION 

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10.1 INTERFACE REQUIREMENTS. 

10.1.1 Scope. 

Only the major inter-contractor physical, functional, and procedural interfaces will be identified and controlled within the ICD (Interface 

Control Document) system indicated in this section. The minor intercontractor interfaces will be identified and controlled by a subordinate document which will be called out within each of the identified ICD Areas. An 

associated 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 ICD 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. 

10.1.2 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. 

10.1.3 Outline Requirements. 

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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10.1.4 'CD Area List 

ICD Area 

ICD Area 

1: 

2: 

Gemini B/Laboratory 

Gemini B/Experiments 

ICD Area 3: Gemini B/Modification Group List Per Flight 1 

ICD Area 4: Gemini B/Modification Group List Per Flight 2 

ICD Area 5: Gemini B/Modification Group List Per Flight 3 

ICD Area 6: Gemini B/Modification Group List Per Flight 4 

ICD Area 7: Gemini B/Modification Group List Per Flight 5 

ICD Area 8: Gemini B/Modification Group List Per Flight b 

ICD Area 9: Gemini B/Modification Group List Per Flight 7 

ICD Area 10: Gemini B/Modiiication Group List Per Flight 8 

ICD Area 11: Gemini B/Flight Crew 

ICD Area 12: Gemini B/TOSS 

ICD Area 13: Gemini B/T-IIIC 

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ICD Area 14: 

ICD Area 15: 

ICD Area 16: 

ICD Area 17: 

ICD Area 18: 

'CD Area 19: 

ICD Area 20: 

ICD Area 21: 

ICD Area 22: 

ICD Area 23: 

ICD Area 24: 

ICD Area 25: 

Laboratory/Experiments 

Laboratory/Flight Crew 

Laboratory/ 

Laboratory/Modification 

Flight 1 

Laboratory/Modification 

Flight 2 

Laboratory/Modification 

Flight 3 

Laboratory/Modification 

Flight 4 

Laboratory/ Modification 

Flight 5 

Laboratory/Modification 

Flight 6 

Laboratory/Modification 

Flight 7 

Laboratory/Modification 

Flight 8 

Laboratory/ TOSS 

Group List Per 

Group List Per 

Group List Per 

Group List Per 

Group List Per 

Group List Per 

Group List Per 

Group List Per 

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Expe rim ents / Flight Crew 

Experiments/ TOSS 

Experiments/Data Management 

Experiment/Experiments 

Experiments/T-IIIC 

Experiments/Modification Group List Per 

Flight 1 

Experiments/Modification Group List Per 

Flight 2 

Experiments/Modification Group List Per 

Flight 3 

Experiments/Modification Group List Per 

Flight 4 

ICD Area 26: 

ICD Area 27: 

ICD Area 28: 

ICD Area 29: 

ICD Area 30: 

ICD Area 31: 

ICD Area 32: 

ICD Area 33: 

ICD Area 34: 

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Per Flight 

Per Flight 

Per Flight 

Per Flight 

Per Flight 

Per Flight 

Per Flight 

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4 

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ICD Area 35: 

ICD Area 36: 

ICD Area 37: 

ICD Area 38: 

ICD Area 39: 

ICD Area 40: 

ICD Area 41: 

ICD Area 42: 

ICD Area 43: 

ICD Area 44: 

ICD Area 45: 

ICD Area 46: 

ICD Area 47: 

ICD Area 48: 

ICD Area 49: 

ICD Area 50: 

ICD Area 51: 

ICD Area 52: 

ICD Area 53: 

ICD Area 54: 

ICD Area 55: 

ICD Area 56: 

'CD Area 57: 

ICD Area 58: 

Experiments/Modification Group List Per 

Flight 5 

Experiments/Modification Group List Per 

Flight 6 

Experiments/Modification Group List Per 

Flight 7 

Experiments/Modification Group List Per 

Flight 8 

Data Management System/Laboratory 

Flight Crew/ TOSS 

Flight Crew/Modification Group List Per 

Flight 1 

Flight Crew/ Modification Group List Per 

Flight 2 

Flight Crew/Modification Group List Per 

Flight 3 

Flight Crew/ Modification Group List Pe r 

Flight 4 

Flight Crew/Modification Group List Per 

Flight 5 

Flight Crew/Modification Group List Per 

Flight 6 

Flight'Crew/Modification Group List Per 

Flight 7 

Flight Crew/Modification Group List Per 

Flight 8 

TOSS / T -ILIC 

TOSS/Modification Group List 

TOSS/Modification Group List 

TOSS/Modification Group List 

TOSS/Modification Group List 

TOSS /Modification Group List 

TOSS/Modification Group List 

TOSS/Modification Group List 

TOSS/Modification Group List 

TOSS/Data Management System 

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