MOL SYSTEMS OFFICE 

LOS ANGETRA AIR FORCE STATION 1.71-*Zr.11AL FIANDLING REQUIRED NOT RELEASABLE TO FOREIGN NATIONALS 

The information contained in this document wilt disclosed not he to foreign nations or their representatives. 

SPECK ACCESS REQUIRED 

SENSITIVE AREA d, GRAD' IDENTITY. }9 

DOWNGRADED AT 12 YEAR 

INTERVALS; NOT AUTOMATICALLY 

DECLASSIFIED. DOD DIR 5200.10 

This materiel contains inbnration effecting the 

national clasps* of elo t11,11:s witliin• the 

ovtar.inc cf s: 1.1w1,111!is 13, 

Sections 793 ;:n..1 ih•J :ratozonisshm or revels. 

tion of which in any msnnor to an unauthorized 

person is prohibited by 

1 

-us • %A 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

40 

(U) PRELIMINARY PERFORMANCE/ 

DESIGN REQUIREMENTS 

FOR THE 

MANNED ORBITING LABORATORY SYSTEM 

(MOL) 

GENERAL SPECIFICATION FOR 

January 1966 
• INCLUDING GENERAL SYSTEM SPECIFICATION 

FOR 

PERFORMANCE AND.DESIGN REQUIREMENTS FOR THE DORIAN 

PHOTOGRAPHIC RECONNAISSANCE SATELLITE SYSTEM 

January 1966 

Approved: 

B. F. Knolle, Jr. 

Approved: 

S. S. Strong 

ii-th' L ING 

NRO APPROVED FOR 

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R N RA A P aEAto iR5 HANDLING 

FOREWORD 

This advance rough draft of the proposed MOL/Dorian Integrated 

System Specification was prepared based on the so-called manned/unmanned 

concept. The manned version presented herein assumes automatic operation 

of the mission payload with manual•override capability. 

Recent guidelines issued by MOri program management directed discontinuance of the acronym "MUM" and the verbage "manned/unmanned." 

Instead the following terminology is to be used: 

1) Manual 

2) Automatic 

3) Manned - Automatic 

Present plans envisage seven (7) sets of orbiting vehicle hardware 

to be built and delivered in the manned-automatic configuration. It is 

also planned to develop and build three (3) kits which will enable conversion from the manned-automatic configuration to a completely automatic 

configurations• 

The issuance of this draft has not been delayed to reflect the above 

changes. Prior to promulgation of the approved document, references to 

the "Manned Version", will be changed to read "manned-automatic." 

Similarly, references to the "Unmanned Version" will be changed to read 

"automatic." 

Another significant difference between this advance rough draft of 

the Integrated System Specification and SS-N011-1 dated 3 December 1965, 

is that this draft makes the Mission Module structure part of the Mission 

Payload System Segment, whereas SS-MOL-1 states that the Mission Module 

structure is part of the Laboratory Vehicle System Segment. In a few other 

areas the white pages also differ somewhat from SS-NOL-1. Until officially 

superceded, SS-NOL-1 is the approved "white" system specification. 

SPECIAL liANDalt 
DitfiCtiAlwuNG CONTENTS 

1.0 SCOPE 1-1/2 

1.1 Descriptive Title 1-1/2 

1.2 Purpose 177,1 

1.3 Mission 1-3 

1.3.1 Descriptive Title 1-3 

2.0 APPLICABLE DOCUMENTS 2-1 

2.1 Specifications 2-2 

2.1.1 MIL Specifications 2-2 

2.1.2 Air Force BMD/BSD/SSD Exhibits 2-5 

2.1.3 Federal Standards 2-6 

2.2 Manuals, Regulations, Publications 2-6 

2.2.1 Air Force Regulation 2-6 

2.2.2 Air Force Manuals 2-7 

2.2.3 Air Force Procurement Instructions 2-7 

2.2.4 Air Force Pamphlets 2-7 

2.2.5 AFSC Regulations 2-8 

2.2.6 AFSC Manuals 2-8 

2.2.7 Bulletins- 2-9: 

2.3 Other Documents 2-9 

2.4 Dorian Exceptions to Applicable Documents Listing 2-11 

3.0 REQUIREMENTS 3-1 

3.0.1 General 3-1 

3.0.2 Performance 3-1 

3.0.3 Growth Considerations 3-3 

3.0.4 Mission Requirements 3-4 

3.0.4.1 Photographic Resolution 3-4 

3.0.4.2 Target Access 3-4 

3.0.5 Secondary Mission Requirements 3-4 

3.1 Performance Characteristics 3-5 

3.1.1 Performance Characteristics - General 3-5 

3.1.1.1 System Characteristics 3-5 

3.1.1.2 Logistics 3-13 

3.1.1.3 Personnel and Training 3-14 

3.1.1.4 Mission Characteristics 3-16.1 
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3.1.2 

3.1.3 

CONTENTS (Continued) 

Page 

System Definition 

3.1.2.1 System Engineering Documentation 

3.1.2.2 System Segment List 

3.1.2.3 Contract End Item List 

3.1.2.4 Dorian Functional Flow Diagram 

System Effectiveness 

3-17 

3-17 

3-28 

3-28 

3-28.1 

3-29 

3.1.3.1 Effectiveness Measures 3-29 

3.1.3.2 Maintainability 3-31 

3.1.3.3 Useful Life 3-‘32 

3.1.3.4 Environment-Natural and Induced 3-32 

3.1.3.5 Transportability and Handling 3-33 

3.1.3.6 Human Performance 3-33 

3.1.3.7 Safety 3-34 

3.1.3.8 Dangerous Materials and Components 3-35/36 

3.1.3.9 Noise and Vibration 3-35/36 

3.1.3.10 Life Support 3-35/36 

3.2 System Design and Construction Standards 3-37 

3.2.1 General Design and Construction Requirements 3-37 

3.2.1.1 Selection of Specifications and Standards 3-37 

3.2.1.2 Materials, Parts, and Processes 3-38 

3.2.1.3 Standard and Commercial Parts 3-38 

3.2.1.4 Moisture and Fungus Resistance 3-39 

3.2.1.5 Corrosion of Metal Parts 3-39 

3.2.1.6 Interchangeability and Replaceability 3-40 

3.2.1.7 Worklanship 3-40 

3.2.1.8 Electromagnetic Interference 3-41 

3.2.1.9 Identification and Marking 3-42 

3.2.1.10 Storage 3-42 

3.2.2 Design Disciplines 3-42 

3.2.2.1 Electrical 3-43/44 

3.2.2.2 Mechanical 3-43/44 

3.2.2.3 Hydraulic and Pneumatic 3-43/44 

vi 

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CONTENTS(Continued 

3.2.2.4 

3.2.2.5 

3.2.2.6 

3.2.2.7 Maintenance Support and Spares Provisioning 3-43/44 

1 . , 3.2.2.8 Environmental Criteria 3-43/44 

3.2.3. Dorian Exceptions 3-44.1 

3.3 Performance Allocations 3-45 

3.3.1 Orbiting Vehicle System Segment 3-45 

3.3.1.1 Allocated Performance and Design Requirements 3-45 

3.3.1.2 Peculiar Performance and Design Requirements 3-47 

3.3.1.3 Functional Interfaces 3-52 

Nt Contract Items 

Peculiar Requirements, Orbitinf'Xiicle 3-52.1 

3.3.2 Laboratory Vehicle System Segment 3-53 

3.3.2.1 Allocated Performance and Design Requirements 3-53 

3.3.2.2 Peculiar Performance and Design Requirements 3_55 

3.3.2.3 Functional Interfaces 3-85/86 

3.3.2.4 Contract End Items 3-85/86 

3.3.2.5 Mission Peculiar Requirements, Laboratory 3-86.1 

Vehicle 

3.3.3 Gemini B System Segment 3-87 

3.3.3.1 Allocated Performance and Design Requirements 3-87 

3.3.3.2 Peculiar Performance and Design Requirements 3-88 

3.3.3.3 Functional Interfaces 3-102 

3.3.3.4 Contract End Items 3-102 

3.3.4 Mission Payload System Segment 3-103/104 

3.3.4.1 Allocated Performance and Design Requirements 3-103/104 

3.3.4.2 Mission Payload Performance and Design 3-104.1 

Requirements 

3.3.4.3 Mission Module Section 3-104.7 

3.3.4.4 Data Re-entry Vehicle Section 3-104.16 

3.3.4.5 Photographic Section 3-104.24 

3.3.4.6 Aerospace Ground Equipment Requirements 3-104.35 

3.3.4.7 Mission Payload Functional Interfaces 3-104.36 

3.3.4.8 Contract End Item List (CEI) 3-104.36 

4 

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Page 

Civil 3-43/44 

Human Engineering 3-43/44 

Safety 3-43/44 
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CONTENTS (Continued) 

Page 

3.3.5 Crew Equipment System Segment 3-105 

3.3.5.1 Allocated Performance and Design Requirements 3.-105 

3.3.5.2 Peculiar Performance and Design Requirements 3-108 

3.3.5.3 Functional Interfaces 

3.3.5.4 Contract End Items 

3.3.6 Titan III System Segment 

3.3.6.1 Allocated Performance and Design Requirements 3,-113 

3.3.6.2 Peculiar Performance and Design Requirements 3-115 

3.3.6.3 Functional Interfaces 

3.3.6.4 Contract End Items 

3.3.7 Facilities System Segment 

3-117/118 

3-117/118 

3-119 

3.3.7.1 Allocated Performance and Design Requirements 3.-119 

3.3.7.2 Peculiar Performance and Design Requirements 3-119 

3.3.7.3 Functional Interfaces 3-122 

3.3.7.4 Contract End Items 3-122.1 

3.3.7.5 Mission Payload Facility Requirements 3-122.1 

3.3.8 Launch Operations System Segment 

3.3.8.1 Pre-launch Operations 

3.3.8.2 Launch Operations 

3.3.8.3 Functional Interfaces 

3.3.8.4 Contract End Items 

3-123 

3-123 

3-123 

3-124 

3-124 

3.3.8.5 Mission Payload Launch Operations Support 3,-124.1 

3.3.9 Flight Operations and Support System Segment 3-125 

3.3.9.1 Mission Control Operations 

3.3.9.2 Flight Operations Support 

3.3.9.3 Functional Interfaces 

3-125 

3-132 

3-138 

3.3.9.4 Contract End Items 3-138 

3.3.9.5 Payload Operations Control Requirements 3.140:1 

3-141 

3-141 

3-141 

3-142 

3-142 

3.3.10 Recovery System Segment 

3.3.10.1 Recovery Operations 

3.3.10.2 Recovery Force 

3.3.10.3 Access and Retrieval 

3.3.10.4 Post Recovery 

, \ 

viii 

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CONTENTS (Continued) 

3.3.10.5 Payload Recovery Requirements 3-142.1 

3.3.11 Test Support System Segment 3-143 

3.3.11.1 Pre-launch Support 3-143 

3.3.11.2 Launch and Ascent Support 3-143 

3.3.11.3 On-Orbit and Recovery Support 3-144 

3.3.12 Flight Crew System Segment 3-147 

3.3.12.1 Allocated Performance and Design Beqpimg06 3-147 

3.3.12.2 Peculiar Performance and Design Requirements 3-147 

3.3.12.3 Functional Interfaces 3-149/150 

3.3.12.4 Contract End Items 3-149/150 

3.3.12.5 Flight Crew Dorian Support Requirements 3-150.1 

4.0 PERFORMANCE/DESIGN VERIFICATION AND TEST 4-1 

4.1 Ground Test Requirements 4-1 

4.1.1 Development Tests 4-1 

4.1,1.1 General Requirements 4,1 

4.1.1.2 Over-all System Requirements 4-1 

4.1.1.3 Orbiting Vehicle Requirements 4-1 

4.1.1.4 Laboratory Vehicle Requirements 4-2 

4.1.1.5 Gemini B Requirements 4-4 

4.1.1.6 Mission Payload Segment Requirements 4-5 

4.1.1.7 Titan III Requirements 4-5 

4.1.1.8 Crew Equipment Requirements 4-5 

4.1.1.9 Operations Compatibility Requirements 4-5 

4.1.1.10 Aerospace Ground Equipment RequirementE4-5 

4.1.1.11 Orbiting Vehicle Mission Simulator ,45 

Requirements 

4.1.2 Qualification Tests 4-6 

4.1.2.1 General Requirements 4-6 

4.1.2.2 Over-all System Requirements 4-6 

4.1.2.3 Orbiting Vehicle Requirements 4-6 

4.1.2.4 Laboratory Vehicle Requirements 4-7 

4.1.2.5 Gemini B Requirements 4-7 

4.1.2.6 Mission Payload Requirements 4-8 

4.1.2.7 Titan III Requirements 4-8 

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CONTENTS (Continued) 

Page 

4.1.2.8 Flight Crew Equipment Requirements 4-8 

4.1.2.9 Launch Operations, Flight Operations, 

Recovery and Test Support Equipment 

4-8 

Requirements 

4.1.2.10 Aerospace Ground Equipment Requirements 4-8 

4.1.2.11 Mission Simulator Requirements 4-9 

4.1.3 Effectiveness Testing 4-9 

4.1.4 Acceptance and Flight Readiness Tests 4-9 

4.1.4.1 Acceptance Test Requirements 4-9 

4.1.4.2 Flight Readiness Test Requirements 4-10 

4.1.4.3 Orbiting Vehicle Requirements 4-10 

4.1.4.4 Laboratory Vehicle Requirements 4-10 

4.1.4.5 Gemini B Requirements 4-10 

4.1.4.6 Mission Payload Segment Requirements 4-10 

4.1.4.7 Titan III Requirements 4-11 

4.1.4.8 Flight Crew Equipment Requirements 4-11 

4.1.4.9 Launch Operations, Flight Operations, 4-11 

Recovery and Test Support System 

Segment Requirements 

4.1.4.10 Aerospace Ground Equipment (AGE) Requirements 4-11 

4.1.4.11 Mission Simulator Requirements 4-12 

4.2 NOL System Flight Test Requirements 4-12 

4.2.1 Test Program Description 4-12 

4.2.2 Titan III Development Flight Test (MOL Flight #1)4-12 

4.2.3 MOL Development Flight Test (MOL Flight 42) 4-13 

4.2.4 MOL Flight Tests (MOL Flight 43 and Subsequent) 4-13 

4.3 Dorian System Flight Certification Testing 4-15 

4.3.1 Qualification Testing 4-15 

4.3.2 Acceptance Testing 4-15 

5.0 PREPARATION FOR DELIVERY 5-1/2 

5.1 Packaging 5-1/2 

GLOSSARY 

VEHICLE COORDINATE SYSTEM DEFINITION A-1 

Attachment 1 - Method for Statistical Analysis of Attitude Control 

System Accuracy 

Attachment 2 - Mission Payload Performance Prediction 

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SPECIAL HANDLING 

SPECIAL liA;:DLINO 

FIGURES 

3-1 MOL Orbiting Vehicle Segment Orbit Altitude Constraint 3-15/16 

3-1.1 Orbit Envelope 3-16.3 

3-1.2 Nadir Resolution vs Sun Angle 3-16.4 

3-1.3 Across the Format IMC 3-16.5 

3-2 MOL System Top LeveLTunctional Flow Diagram 3-20 

3-3 MOL System Flow Diagram Code 3-21 

3-4 MOL System Flow Schematic 3-22 

3-5 Manned Dorian System Integration Functional Flow 3-28.2 

3-6 Unmanned Dorian System Integration Functional Flow 3-28.3 

3-7 Dorian System (Manned - Automatic Configuration) 3-104.2 

3-8 Dorian System (Automatic Configuration) 3-104.3 

3-9 Optical Sensor Basic Configuration 3-104.25 

3-10 Resolution Versus Contrast 3-104.29 

3-11 Dorian System Specification Tree (Manned Automatic) 3-104.37 

3-12 Dorian System Specification Tree (Automatic) 3-104.38 

SPECIAL HANDLING 

SPECIAL HANDLING 
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APPENDIX A 

VEHICLE COORDINATE SYSTEM 

DEFINITION 

A-1 
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' RELEASE 1 JUL`;' 2015 

anotaumkati" 

MOL STA (REF. ) 

500.00 

420.0" (REF) 

A 

+ y 

IV 

II III 

A 

Z 

TIII STA 

222.44 

SECTION A-A 

(MOL ORBITING VEHICLE AXES NOTATI 

Z 

y 

II 

/// 

SECTION B-B 

(TITAN III VEHICLE AXES,NOTATION 

ru /,,heys, ;elcr r s e 50' •?) AW-01/Or-ti 

*MOristatiOn tumbers increase going forward. 
(Use right hand rule for p

o

d'rtive r

otation

s) 

0 H 

En 

1 

A 

Order

ed Rotations 

0 H 

0 Cl) 

.---I r-1 

o -P -P 0 -P -P -e- ;-1 c, A 

+) tIO +) 0 tO 

+ 

--3- 

F-4 vi 

T4 

+-I 

til 

O 

• 

-P (1.) 0 +) a) +-I 

ra I 

O cia 0 C/) co 4 r 

satip...• 

I i LIg +i 0 

0 C> - - 

ular Rates 

Pitch about +Y 

Yawabo

ut +Z 

ki A 0 

4., 

pq 0 

Cd •■••1 

F-i 0 

0 0 

...1 6 14 

Ro

ll about +X 

A-3 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

ATTA.CIEvIT71 1 

METHOD FOR STATISTICAL ANALYSIS OF ATTITUDE CONTROL SYSTEM ACCURACY 

(Later) 
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, ^ 

ATTAMENT 2 

MISSION PAYLOAD PERFORMANCE PREDICTION 

Modulation Transfer Function (NIF) techniques are used to predict 

Photographic system performance. The parameters which affect resolution 

are: operating altitude; target position and contrast; lens parameters 

(focal length, aperture, semi-field angle, percent obstruction, and transmission); optical quality factor; focus; residual image motion; shutter 

efficiency; wavelength of light; and.average minimum scent luminance. 

The MTF of the lens is computed for the selected lens parameters 

and then multiplied by the optical quality factor. A transfer function is 

computed for the combination of shutter efficiency and residual image. motion. 

Target modulation resulting from the contrast of a standard tri-bar test 

object (in accordance with Figure 1 of NIL-STD-150A) is multiplied by the 

above X2F's to obtain an image modulation curve. This curve represents the 

total modulation of the image at the film plane versus spatial frequency, 

and its intersection with the aerial image modulation curve gives the threshold lens-film resolution of the system. The threshold resolution is given 

in lines/mm at the film plane and must be combined with focal length to 

obtain angular resolution. The relationships between film resolution, 

angular resolution, and ground resolution are as follows: 

Film resolution: 1/Rf = F a 

Ground resolution: Rs = h 0 (cosf cos12)-32 

where Rf = film resolution in cycles/linear distance 

Rg = Ground resolution in linear distance 

o = Angular resolution in radians 

F = 'Focal length 

h. = Altitude 

= Stereo angle 

52 = Obliquity angle 
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r • 

Mission average angular resolution is used to estimate average 

system performance over the ranges of expected operating conditions. The 

within-mission random variables included are obliquity aim angle, focus 

variations, deviation from nominal exposure conditions, and residual image 

motion. 

Monte Carlo techniques are used to determine mission average 

angular resolution. A computer program has been written for this purpose. 

The computer selects a value from each of the four random distributions 

(random smear rate, exposure, focus, and obliquity) and calculates the 

corresponding angular resolution and ground resolution. This selection 

of a set of random variables and the calculation of resolution is repeated-

"N" times for each set of fixed input variables. Mission average angular 

resolution is then the 'average of the individual angular resolutions, and 

the individual ground resolutions can be used to plot cumulative resolution 

probability. 

This approach to determining average resolution is based on the 

central limit theorem which says that if a sufficient number of samples are . 

chosen at random from an infinite population, the average of the samples 

approaches the average of the population. A statistical evaluation of trial 

cases indicated that a sample size of N = 100 is required to determine 

mission average performance for the specified manned photographic system. 
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CONTENTS 

1.0 SCOPE 

1.1 Descriptive Title 

1.2 Purpose 

2.0 APPLICABLE DOCUMENTS 

2.1 Specifications, Standards, and Exhibits 

2.2 Manuals, Regulations, Publications 

2.3 Other Documents 

3.0 REQUIREMENTS 

3.0.1 

3.0.2 

3.0.3 

General 

Performance 

Growth Considerations 3-3/4 

3-1 

3-1 

3.1 Performance Characteristics 3-5 

3.1.1 Performance Characteristics 

General 3-5 

3.1.1.1 System Characteristics . . . 3-5 

3.1.1.2 Logistics 3-13 

3.1.1.3 Personnel and Training . . . 3-14 

3.1.2 System Definition 3-17 

3.1.2.1 System Engineering 

Documentation 3-17 

3.1.2.2 System Segment List 3-28 

3.1.2.3 Contract End Item List . . . . 3-28 

3.1.2.4 Deleted 3-28 

3.1.3 System Effectiveness 3-29 

3.1.3.1 Effectiveness Measures . . . 3-29 

3.1.3.2 Maintainability 3-31 

3.1.3.3 Useful Life 3-32 

3.1.3.4 Environment - Natural and 

Induced 

3.1.3.5 Transportability and 

Handling 
CONTENTS (Continued) 

3-33 

3-34 

3-35/36 

3-35/36 

3-35/36 

3. 2 System Design and Construction Standards . . . . 3-37 

3. 2. 1 General Design and Construction 

Requirements 3-37 

3-37 

3-38 

3-38 

3-39 

. 3-39 

3-40 

3-40 

3-41 

3-42 

3-42 

3-42 

3-43 /44 

3-43/44 

. . . 3-43/44 

3-43 /44 

3-43 /44 

3-43/44 

3. 2. 2 Design Disciplines 

3. 2. 2. 1 Electrical 

3. 2. 2. 2 Mechanical 

3. 2. 2. 3 Hydraulic and Pneumatic 

3. 2. 2. 4 Civil 

3. 2. 2. 5 Human Engineering 

3. 2. 2. 6 Safety 

3. 2. 1. 1 Selection of Specifications 

and Standards 

3. 2. 1. 2 Materials, Parts, and 

Processes 

3. 2. 1. 3 Standard and Commercial 

Parts 

3. 2. 1. 4 Moisture and Fungus 

Resistance 

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

3. 2. 1. 6 Interchangeability and 

Replaceability 

3. 2. 1. 7 Workmanship 

3. 2. 1. 8 Electromagnetic 

Interference 

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

3. 2. 1. 10 Storage 

3. 1. 3. 6 Human Performance 

3. 1. 3. 7 Safety 

3. 1. 3. 8 Dangerous Materials and 

Components 

3. 1. 3. 9 Noise and Vibration 

3. 1. 3. 10 Life Support 

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vi 
• 

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CONTENTS (Continued) 

3.2.2.7 Maintenance Support 

3.2.2.8 Environmental Criteria. 

3.3 Performance Allocations 

3-43/44 

3-43/44 

3-45 

3.3.1 Orbiting Vehicle System Segment . . • 3-45 

3.3.1.1 Allocated Performance and 

Design Requirements 3-45 

3. 3. 1. 2 Peculiar Performance and 

Design Requirements 3-46 

3. 3. 1. 3 Functional Interfaces 3-52 

3. 3. 1. 4 Contract End Items 3-52 

3. 3. 2 Laboratory Vehicle System Segment . . 3-53 

3. 3. 2. 1 Allocated Performance and 

Design Requirements 3-53 

3. 3. 2. 2 Peculiar Performance and 

Design Requirements 3-55 . 

3. 3. 2. 3 Functional Interfaces 3-85/86 

3. 3. 2. 4 Contract End Items 3-85/86 

3. 3. 3 Gemini B System Segment 3-87 

3. 3. 3. 1 Allocated Pe'rformance and 

Design Requirements 3-87 

3. 3. 3. 2 Peculiar Performance and 

Design Requirements 3-88 

3. 3. 3. 3 Functional Interfaces 3-102 

3. 3. 3. 4 Contract End Items 3-102 

3. 3: 4 Mission Payload System Segment • • . 3-103/104 

3. 3. 4. 1 Allocated Performance and 

Design Requirements 3-103/104 

3. 3. 4. 2 Peculiar Performance and 

Design Requirements 3-103/104 

3. 3. 4. 3 Functional Interfaces . . . . 3-103/104 

3. 3. 4. 4 Contract End Items 3-103/104 

3. 3. 5 Crew Equipment System Segment . . . 3-105 

3. 3. 5. 1 Allocated Performance and 

Design Requirements 3-105 

vii • 
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CONTENTS (Continued) 

3. 3.5.2 Peculiar Performance and 

Design Requirements 3-108 

3. 3. 5. 3 Functional Interfaces 3-111/112 

3. 3. 5. 4 Contract End Items 3-111/112 

3. 3. 6 Titan III System Segment 3-113 

3. 3. 6. 1 Allocated Performance and 

Design Requirements 3-113 

3. 3. 6. 2 Peculiar Performance and 

Design Requirements 3-115 

3. 3. 6. 3 Functional Interfaces 3-117/118 

3. 3. 6. 4 Contract End Items 3-117/118 

3. 3. 7 Facilities System Segment 3-119 

3. 3. 7. 1 Allocated Performance and 

Design Requirements 3-119 

3. 3. 7. 2 Peculiar Performance and 

Design Requirements 3-119 

3. 3. 7. 3 Functional Interfaces 3-122 

3. 3. 7. 4 Contract End Items 3-122 

3. 3. 8 Launch Operations System Segment. . . 3-123 

3. 3. 8. 1 Pre-launch Operations . . 3-123 

3. 3. 8. 2 Launch Operations 3-123 

3. 3. 8. 3 Functional Interfaces 3-124 

3. 3. 8. 4 Contract End Items 3-124 

3. 3. 9 Flight Operations and Support System 

Segment . . 3-125 

3. 3. 9. 1 Mission Control Operations . 3-125 

3. 3. 9. 2 Flight Operations Support . . 3-132 

3. 3. 9. 3 Functional Interfaces 3-139/140 

3. 3. 9. 4 Contract End items 3-139/140 

3. 3. 10 Recovery System Segment 3-141 

3. 3. 10. 1 Recovery Operation 3-141 

3. 3. 10.2 Recovery Force 3-141 

3. 3. 10. 3 Access and Retrieval 3-142 

• •7--7', 
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RELEASE 1 JULY 2015 

CONTENTS (Continued) " 

3-142 

3-143 

3-143 

3-143 

3. 3. 10. 4 Post Recovery 

3.3. 11 Test Support System Segment 

3. 3. 11. 1 Pre-launch Support 

3. 3. 11.2 Launch and Ascent Support. 

3. 3. 11.3 On-Orbit and Recovery 

Support 

3. 3. 12 Flight Crew System Segment 

3. 3. 12. 1 Allocated Performance and 

Design Requirements 

3. 3. 12. 2 Peculiar Performance and 

Design Requirements 

3. 3. 12. 3 Functional Interfaces 

3. 3. 12. 4 Contract End Items 

4. 0 PERFORMANCE /DESIGN VERIFICATION AND TEST. 

4. 1 Ground Test Requirements 

4. 1. 1 Development Tests 

5. 0 PREPARATION FOR DELIVERY 

5. 1 Packaging 

GLOSSARY 

3-144 

3-147 

3-147 

3-147 

3-149/150 

3-149/150 

4-1 

4-1 

4-1 

4-6 

4-9 

4. 1. 2 Qualification Tests 

4. 1. 3 Effectiveness Testing 

4. 1. 4 Acceptance and Flight Readiness 

Tests 

4. 2 MOL System Flight Test Requirements 

4. 2. 1 Test Program Description 

4. 2. 2 Titan-III Development Flight Test 

(MOL Flight No. 1) 4-12 

4. 2. 3 MOL Development Flight Test 

(MOL Flight No. 2) 4-13 

4. 2. 4 MOL Flight Tests (MOL Flight No. 3 

and Subsequent) 

' 4-9 

 4-12 . 

4-12 

ix 
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FIGURES 

3-1 MOL Orbiting Vehicle Segment Orbit Altitude 

Constraint 3-15/16 

3-2 MOL System Top Level Functional Flow Diagram. 3-20 

3-3 MOL System Flow Diagram Code 3-21 

3-4 MOL System Flow Schematic 3-22 
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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 (CEI) of the MOL System shall 

conform to the requirements delineated herein. (U) 

1.1 DESCRIPTIVE TITLE 

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

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

1.2 PURPOSE 

A primary objective of the MOL Program is development of 

technology to improve capabilities for manned and unmanned operations of 

.military significance. * This may include intermediate steps toward operational 

systems.. 

This objective shall be accomplished as early as possible, with 

minimum system cost and with careful attention to safety aspects. Minimizing 

cost and time for development and test, as well as enhancing system effectiveness 

implies a minimum of innovations. Proven vehicle and ground hardware, procedures, and facilities resulting from prior DOD and NASA programs will be. 

employed to the greatest extent practicable. 

Additional objectives are: 

(a) Quantitative determination of man's military usefulne,ss in space 

(b) Scientific and technological experiments of 

national importance 

(c) Determination of the biological responses of man 

in orbit for 30 days or more 

(d) Investigation of the possibility of operation in an 

unmanned mode 

*Where no heading appears with material herein defining its applicability 

to manned or unmanned versions, the material shall be applicable to both. 

As additional material within a paragraph is required for either version, 

a heading is provided defining!: the appropriate version. 

1-1/2 
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1.3 Mission 

The primary mission of the MOL System shall be to conduct photographic intelligence (Dorian) gathering against specific targets of interst. 

This MOL/Dorian system shall be herein referred to as the Dorian System. 

Requirements stated herein will include performance, design, development, 

and test. The Dorian System shall be capable of obtaining high resolution 

stereographic photography of specified targets. All elements and contract 

end items of the Dorian System shall, as a minimum, conform to the requirements delineated herein. 

1.3.1 Descriptive Title 

Dorian High Resolution Reconnaisance Satellite 

System (Dorian System). 

SPECIAL HANDLING 

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2. 0 APPLICABLE DOCUMENTS (U) 

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. 

The following list of applicable documents is presented for purposes 

of guidance. Applicability of the listed documents shall be to the extent 

called out in this General Specification. In cases where the requirements 

of the following documents are in conflict with the requirements stated 

in this General Specification, the General Specification shall take 

precedence. 

A two-letter prefix code is provided to assist in associating those 

documents which are pplicable 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 Construction 

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

CODE Paragraph Reference 

CV - Civil 

DG - Design and Construction 

(Guidance only) 

DR - Design and Construction 

3. 2. 

3.2 

2.4 

Requirements 3. 2. 1 

EE - Electrical 3. 2. 2. 1 

EI - Electromagnetic Interference 3. 2. 1. 8 

EV - Environmental Criteria 3. 2. 2. 8 

GP - Human Pe rformance.(Guidanc e) 3. 2. 2. 5 

HP - Human Performance (applicable) 3. 2. 2. 5 

HY - Hydraulic . 3. 2. 2. 3 

IC - Interchangeability 3. 2. 1. 6 

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

'MP - Materials, Parts, and Processes 3. 2. 1. 2 

MS - Maintenance Support 3. 2. 2. 7 

SF - Safety 3. 2. 2. 6 

ST - Storage 3.2.1.10 

WK -Workmanship 3. 2. 1. 7 
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2.1 SPECIFICATIONS, STANDARDS, AND EXHIBITS 

2.1.1 MIL Specifications 

EE - MIL-C-5015 

IM - MIL-C-18012 

IM - MIL-C-25050 

EE - MIL-C-26482 

(Suppl 1) 

DR - MIL-D-70327 

EE - MIL-E-4158E 

DR - MIL-E-5400G 

EE - MIL-E-19600 

EE - MIL-E-0025366B 

MP - MIL-F-007179B 

General Specification for Air 

Transportability Requirement, 

5 May 1960 

Bonding, Electrical Lightning 

Protection for Aerospace Systems 

Connectors, Electric, AN Type 

Control Configuration and Markings 

Colors, Aero Lights and Lighting 

Equipment, General Specification 

for 

Connectors, Electric, Circular, 

Miniature Quick Disconnect, 

10 Aug 1962 

Drawings, Engineering and 

Associated Lists 

Electronic Equipment, Ground, 

General Requirement for 

Electronic Equipment, Aircraft, 

General Specification for 

General Specification for 

Electronic Modules 

Electrical and Electronic Equipment 

and Systems, Guided Missiles, 

Installation, General Specification 

for 

Finishes and Coatings, General 

Specifications for Protection of 

Aerospace Weapons Systems, 

Structures and Parts 

MIL-A-8421B 

(Para 3. 1.3.5.2) 

EI - MIL-B-5087B 

2-2 
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HY - MIL-H-25475A 

HP - MIL-H-27894A 

MIL-HDBK-300 

(Para 3. 2. 1. 3) 

IC - MIL-I-8500B 

- MIL-M-8090C 

(Para 3. 1. 3. 5. 1) 

DR - MIL-M-8555 

GP - MIL-M-26512C 

Hydraulic Systems, Missile,. Design, 

Installation Test and Data Requirement, General Requirement for 

Human Engineering Required for 

Aerospace Systems and Equipment 

Technical Information File of AGE 

for Air Weapon System 

Interchangeability and Replaceability of Component Parts 

Mobility Requirement, Ground 

Support Equipment, General 

Specification for 

Missiles, Guided: Design and 

Construction, General Specification 

for 

Maintainability Program Requirement for Aerospace Systems and 

Equipment, with Exceptions as 

Specified in Attachment 1 to SSD 

Exhibit 62-170 

- MIL-M-38310 Mass Properties Control Require- 

(Para 3. 3. 1. 1. 1. 1) ments for Missile and Space 

Vehicles 

IM - MIL-N-18307 

ST - MIL-P-116C 

HY - MIL-P-5518C 

(Suppl 1) 

DR - MIL-P-9024B 

DR - MIL-Q-9858A 

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 

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DR - MIL-S-852B 

- MIL-S-8512B 

Para 3.1.3.5.1 

EE - MIL-R-38100 

SF - MIL-S-38130 

IM - MIL-STD-130A 

DG - MIL-STD-143A 

IM - MIL-STD-195 

EV - MIL-STD-210 

IC - MIL-STD-447 

WK- MIL-STD-454 

Handling Ground Equipment, 

General Requirements for 

Support Equipment, Aeronautical, 

Special General Specification for 

the Design of 

Reliability Assurance Program for 

Established Reliability Parts 

Safety Engineering of Systems, and 

Associated Subsystems and 

Equipment 

Identification Marking of U. S. 

Military Property 

Specifications and Standards, Order 

of Precedence for the Selection of 

Marking of Connections for 

Electric Assemblies 

Climatic Extremes for Military 

Equipment 

Definition of Interchangeable 

Substitute and Replacement Items, 

29 May 1962 

Standard General Requirements for 

Electronic Equipment 

DR - MIL-STD-785 Requirements for Reliability. 

Program (for Systems and 

Equipments) 

IM - MIL-STD-795 k., Colors 

HP MIL-STD-803A-1 Human Engineering Design Criteria 

for Aerospace. System Ground 

Equipment 

HP MIL-STD-803A-2 Human Engineering Design Criteria 

for Aerospace System Facilities and 

Facility Equipment 

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GP MIL-STD-803A-3 

EV - MIL-STD-810A 

IM - MIL-STD-1247 

GP - MIL-T-27382 

EE - MIL-W-8160D 

(Amend. 1) 

IM - MS-24123A 

MP - MS-33586A 

Human Engineering Design Criteria 

for Aerospace Vehicle Equipment 

(AVE). (If available) 

Environmental Test Methods for 

Aerospace and Ground Equipment 

Identification of Pipe, Hose, and 

Tube Lines for Aircraft, Missiles, 

Space Vehicles, and Associated 

Support Equipment and Facilities 

Training Equipment, Subsystem, 

Technical Data, Preparation of 

Wiring, Guided Missiles, Installation of, General Specification for 

Plate Identification 

Metals, Definition of Dissimilar 

2.1.2 Air Force BMD/BSD/SSD Exhibits 

IM - BMD 58-20A 

GP - BMD 59-17C 

IM - BMD 59-31 

SSD Ex 61-47A 

(Para 3. 3. 9. 2. 2) 

Gas, Fluid Line Identification 

Training Equipment Procurement' 

for AFBM and Military Space 

Systems 

Color Requirement for Space 

System Ground Equipment and 

Facility Items 

Computer Program Subsystem 

Development Milestones 

EI - SSD 64-4 Electromagnetic Compatibility 

SF Requirements for Manned Spacecraft, General Specification for 

EE - SSD 64-5 General Specification for Wiring 

Harness in Manned Spacecraft 

GP - BMD 60-1 PSS Testing for Ballistic Missile 

and Space Systems 

IM - SSD 61-70A Identification Requirements 

SSDL-70-1 - Deleted 
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WK - SSD 62-117 

DG - SSD 62-128 

DG- SSD 62-130 

GP - SSD 62-131 

GP - SSD 62-162 

EV - SSD 65-7 

ST - SSD 62-181 

MS - SSD 63-14 

DR - SSD 63-3 

2. 1. 3 Federal Standards 

IM - FED-STD-5 

FED-STD-222 

(Para 3. 3. 2. 2. 5. 15) 

IM - FED-STD-595 

Reliability and Quality Assurance 

Program Required 

Titan III AGE Design Requirements 

Facilities Requirement, General 

Specification 

PSS Requirement, General 

Specification 

Basic Data for PSS Development 

Specification 

Environmental Criteria for the 

MOL System 

Preservation to Packaging, Packing 

and Container Marking of Equipment, 

and Spare Parts for Shipment and 

Storage for Space/Satellite Systems 

Spare Parts Provisioning 

Requirements 

Engineering for Transportability 

Standard Guides for Preparation of 

Item Identifications by Government 

Suppliers 

Title (To be provided) 

Colors 

2. 2 MANUALS, REGULATIONS, PUBLICATIONS 

2. 2. 1 Air Force Regulations (AFR) 

GP - AFR 30-8 

SF - AFR 32-20 

HP - 50-19 

Development of a Personnel 

Subsystem for Aerospace Systems 

Responsibilities for Explosive 

Safety Program 

Management of Training Equipment 

paragraphs 1, 2, 4a(1), 5, 6, 10; 

all other paragraphs are GP. 

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IM - AFR 71-6 

DG - AFR 73-1 

IM - AFR 74-2 

HP - AFR 84-7 

Preservation, Packaging, Packing, 

and Marking Policy 

Defense Standardization Program 

Identify Calibrations Requirements 

of Systems, Subsystems and 

Equipment 

Requirements for Contractor 

Operating Procedures and 

Flight Crews 

SF - AFR 160-3 Hazardous Noise Exposure 

2.2.2 Air Force Manuals (AFM) 

SF - AFM 32-3 Accident Prevention Handbook 

SF - AFM 127-100 Explosives Safety Manual 

SF - AFM 71-4 Packaging and Handling of 

Dangerous Materials for Transportation by Military Aircraft 

CV - AFM 86-8 Airfield and Airspace Criteria 

DR - AFM 88-2 Definitive Designs of Air Force 

Structures 

SF - AFM 127-201 Accident Prevention Handbook 

2.2.3 Air Force Procurement Instructions (AFPI) 

SF - AFPI 7-4047 Safety and Accident Prevention 

SF - AFPI 7-4048 Safety Precautions for 

Dangerous Materials 

2.2.4 Air Force Pamphlets (AFP) 

MP - AFP 88-002-1 

CV - AFP 88-009-1 

Evaluation of New Materials and/or 

Methods of Construction for Air 

Force Facilities 

Miscellaneous Instructions and 

Criteria for Design and Construction of Air Force Facilities 

'2-7 
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2.2.5 AFSC Regulations (AFSCR) 

HP - AFSCR 80-16 

MP AFSCR 400-3 

2.2.6 AFSC Manuals (AFSCM) 

Personnel Subsystems. Program for 

Aerospace, Support and Command 

and Control Systems (Paras. 1, 

5-a-D. All other paragraphs are 

GP). 

Joint Use of Contractors' InProduction Support Materials and 

Operational Support Spares in 

Selected Missile Programs 

DR - AFSCM 80-1 

DCA - AFSCM 80-3 

DR - AFSCM 80-5 

DR - AFSCM 80-6 

DR - AFSCM 80-7 

DR - AFSCM 80-8 

DR - AFSCM 80-9 

DG - AFSCM 81-1 

AFSCM 375-5 

Handbook of Instructions for 

Aircraft Designers, Vol I, II, III 

Handbook of Instructions for 

Aerospace Personnel Subsystem 

Designers (HIAPSD) 

Handbook of Instructions for Ground 

Equipment Designers (HIGED) 

Handbook of Instructions for AGE 

Designers (HIAGED) 

Handbook of Instructions for 

Aerospace Vehicle Equipment Design 

Handbook of Instruction for 

Missile Designers 

Handbook of Instructions for 

Aerospace Systems Designers 

Specifications and Standards 

Manual 

Deleted 

Configuration Management 

During (All) Phase 

Deleted 

AFSCM 310-1 

(AFLCM 310-1) 

AFSCM 375-1 

2-8 
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PH - AFSCM 95-1 Deleted 

2.2.7 Bulletins 

EE - ANA Bulletin 

400T 

Electronic Equipment, Aircraft & 

Guided Missiles, Applicable 

Documents, March 1963 

DR - USAF Bulletin Control of Non-Conforming Supplies 

No. 515 

2.3 .OTHER DOCUMENTS 

IM - AFLCM 65-3 

(Part IV) 

Source and Maintenance Coding 

USAF Aeronautical and Supporting 

Equipment 

MP - 'ASPR 7-105.7 Material Inspection and Receiving 

report "DD Form 250" 

MS - DCAS Exhibit Weapon System/Equipment. 

61-87 Operations and Maintenance Records 

DG - DOD Manual 200A Defense Standardization Manual 

SF - ICC Tariff 

No. 15 

Requirements for Transport of 

Explosives 

CP -- NASA Life Science Data Book 

EE - NEC National Electric Code - 1959 

MS - T. O. 33-1-14 Repair, Calibration and Certification of Precision Measurement 

Equipment 

GP - WADC TR52-321 Anthropometry of Flying Personnel, 

1950 dated Sept. 1954 

DG Department of Defense Index of 

Specifications and Standards, 

Parts 1, 2 and 3 
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RELEASE 1 JULY 2015 

DG Meteorological Note No. 2, • 

Atmospheric and Wind Design 

Criteria for PMR, Titan IIIX/Agena, 

by Martin Company/Denver, 

dtd 7 August 1964 

Structural Criteria for the Manned 

(Para 3. 3. 2. 2. 9. 2) Orbiting Laboratory (MOL) 

Laboratory Vehicle System 

SSBD 65-22 Titan HIM System Performance/ 

Design Requirements, General 

Specification 12 November 1965 

No. 250-649-1 U. S. Navy Submarine Atmosphere 

(Para 3.3.2.2.6.2.8) Habitability Data Book, Rev 1, 

Navy Bureau of Ships 

AFWTR 550-2 WTR Range Safety Handbook 

SSDM 80-1 Flight Test Documentation Manual 

AFBSD TR62-2 Storable Propellants Handbook 

SSMD-77 Government Plan for Program 

(Security Control No. Management for the MOL 

only) Para 3.1.1.1.10 

2-10 
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SPECIAL *.i,:DLING, LIM 

2.4 Dorian Exceptions to Applicable Documents Listing 

The following additions/deletions comprise exceptions to the 

foregoing list of documents applicable to the Dorian mission payload. 

a. Additions 

NEIL-STD-150A Photographic Lens 

b. Deletions 

SPECIAL HANDLING 

2-11 
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3.0 

3. 0. 1 

REQUIREMENTS1 

General 'Ss3 SAR) 

The Manned Orbiting Laboratory (MOL) Program centers 

around an orbiting vehicle used to carry out military and scientific programs 

for durations of 30 days. The Orbiting Vehicle (OV) shall be launched by a 

MOL Titan III from Vandenberg Air Force Base (VAFB). 

The on-orbit tasks for the MOL system shall provide for both 

manned and unmanned operation of the Laboratory Vehicle and the MisSion 

Payload Segments. During manned operations, equipment in general will be 

operated automatically with crew monitoring and manual- override capability: 

Provisions shall be made for conversions of the Orbiting Vehicle for complete 

unmanned operation within a 4-month pre -launch period, utilizing appropriately 

packaged hardware and software elements. Provisions shall be made for 

disposal of the Laboratory and Mission Payloads upon completion of the mission. 

The MOL System is specified in terms of system segments as 

defined in paragraph 3. 1. 2.2. 

Manned Version 

The Orbiting Vehicle (OV) consists of a Laboratory Vehicle, 

a Mission Payload and a modified Gemini spacecraft (Gemini B). During 

the ascent to orbit, the flight crew will be in the Gemini B. After achieving 

orbit, the crew will transfer to the Laboratory Vehicle to perform the onorbit tasks as programmed. Orbital operations shall be planned to enable 

evaluation of the relative performance and effectiveness of the automatic and 

manual modes of operation. At the end of the mission, the crew will return 

to the Gemini B, separate the Laboratory Vehicle from the Gemini B, de-orbit 

and re-enter, and be recovered. 

Unmanned Version 

When configured for unmanned operation, the Gemini B will 

be replaced with a nose cone housing a support module. 

3. 0. 2 Performance X-3 SAR) 

The MOL flights shall be conducted from a Titan III Initial 

Launch Capability (ILC) at VAFB. Orbiting Vehicle operations involving 

attitude control, translational control and separation of vehicle elements shall 

be capable of being conducted either with crew or automatically. Retrofire and 
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re-entry shall be performed under pilot control. All system designs and tradeoffs shall reflect both modes of operation. The Basic MOL design decisions 

should not preclude possible extension of stay in orbit, using integral launch. 

The basic MOL design decisions should not preclude in-space rendezvous. 

Manned Version 

Upon achieving orbit, the flight crew (located in the Gemini B 

during launch and injection into orbit) will pre pare to transfer to the Laboratory 

Vehicle by conducting a checkout of the essential Laboratory subsystems from 

the Gemini B. Upon entering the Laboratory, the flight crew shall activate, the 

remaining Laboratory subsystems to place the Laboratory Vehicle in a fulloperating condition. The flight crew shall be the primary source of on-orbit / 

flight decisions. 

Flight crew functions will include performance of prescribed 

mission tasks, observations, physiological testing, and the monitoring , 

controlling, and maintenance of vehicle and mission subsystems. Status of 

subsystems in the Gemini B essential to safe return will be monitored. Mission 

data, as well as telemetry of OV condition and flight crew physiological functions, 

shall be transmitted from the OV to ground stations and/or recorded on board 

as appropriate for transfer to the Gemini B and return to earth. Data return 

by capsule shall be used as appropriate. 

Communications with the on-orbit flight crew, and mission 

control functions will be performed from Mission Control. A network of 

tracking and data acquisition stations will provide world-wide communications 

coverage. Certain mission functions will be accomplished by an on-board 

central general-purpose digital computer. Over-all control of the various 

tasks will remain a flight crew function for manned operations. Automatic 

control will be exercised by the AVE Computer and MissionControl as 

appropriate. Provision shall be made for flight crew override for flight or 

mission emergencies. Certain analyses shall be made during orbital flights 

both on-board and on the ground, additional analysis will be performed after 

data recovery. 

Upon completion of the mission, the flight crew shall perform 

final checks of the condition of the Gemin B spacecraft and activate those 

systems required for flight crew transfer. The crew shall deactivate certain 

subsystems in the Laboratory Vehicle and return to the Gemin B for separation 

3-2 
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and re-entry. Upon return of the flight crew to the Gemini B, checkout and 

activation of subsystems associated with life support, separation, control, 

and re-entry will be completed and verified by the ground network. 

Upon completion of all systems checkout and verification, 

separation shall be effected and de-orbit and re-entry accomplished. Following 

re-entry into the atmosphere, the Gemini B will display a parachute system 

for descent to a water recovery site where shipJaircraft recovery forces will 

recover the flight crew. Gemini B, and mission data. The planned and 

alternate end-of-mission recovery areas will be located near the continental 

U.S., and all contingency recovery areas will be located as close as possible 

to the U.S. or to U.S. controlled territories. 

Provision shall be made for continued operation of the 

Laboratory and Mission Payload Segments in the unmanned mode after separation 

of the Gemini B for crew return.• Disposal of the laboratory and mission 

payload segments will be accomplished from Mission Control upon the cornletion of operations. 

Unmanned Version , 

On-orbit operations will be controlled by the AVE computer 

and mission control. 

3. 0. 3 Growth Considerations 

(later) 

3-3 
NRONTROVEDFO, 

Sra ityLy 2011 irti 

3.0.4 Mission Requirements 

3.0.4.1 Photographic Resolution 

It is required that a resolution of be 

obtainable with the Dorian System. Consideration must also be given to 

growth to advanced optical systems, so that resolutions on the ground 

may be obtained. 

Unless otherwise noted in this specification, a statement of ground 

resolution shall be under the following conditions: Type SO-362 film, 

on-axis, nadir position, 2-sigma focus and smear, 2:1 contrast ratio at 

the vehicle, 890 foot-lamberts scene luminance, 80 n.mi. altitude. The 

Dorian System shall be capable of resolution under 

these conditions for launches between 21 March and 22 August for targets 

at latitudes as high as 50°N and for mission durations of 30 days. 

For design purposes, a minimum of 1500 eland-free targets per 

30-day mission shall be considered the requirement for the Dorian System, 

for a cloud-cover of 604ereent- 60- percent of prospective targets 

are cloud-covered during the 30-day mission). 

3.0.4.2 Target Access 

It is a design goal that complete photographic access shall be 

provided above 30°N latitude at least four times during a 30-day mission. 

Access shall not require an obliquity angle greater than ± 40 degrees. 

The system shall be capable of photographing any cloud-free location in 

the world having a sun angle greater than 5 degrees while the vehicle is 

traveling on either a northbound or southbound orbital pass. 

3.0.5 Secondary Mission Requirements 

Development and demonstration of other military applications of 

the Dorian System are to be considered as secondary mission requirements 

of the system. To achieve secondary mission requirements, vehicle design 

parameters shall not be prescribed in such a way as to compromise the 

primary mission requirements. 

SPEUP11. ligiDLitsa 
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3.1 PERFORMANCE CHARACTERISTICS 

3.1.1 Performance Characteristics - General (U) 

Performance characteristics of the MOL system are defined 

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

3.1.1.1 System Characteristics (U) 

The significant system characteristics are basically defined 

in. terms of the various phases ranging from pre-launch through mission 

evaluation, the location at which these shall be accomplished, and the responsibilities for the various portions of the mission. 

3.1.1.1.1 Pre-launch Phase -4) 

This phase covers the period from arrival of systems at the 

MOL Launch Site (NLS) to the start of countdown on the launch pad. Assembly of the OV to the Launch Vehicle will take place at the launch pad for 

checkout and final countdown. The segments of the Launch Vehicle will also 

be brought to the launch pad for assembly and checkout prior to being mated 

to the OV. The system shall be capable of meeting a launch frequency requirement of one flight every. ' months. The system shall be designed so 

that conversion from manned to unmanned or.from unmanned to manned versions 

shall not require moresthan-four. months. 

3.1.1.1.1.1 Launch Window Ns3 SAR) 

The MOL System shall be capable of launching within a one 

hour window on a day specified two weeks in advance with a probability of 0.75 

for that day and for each of the two following days. This probability value 

does not include delays resulting from non-technioal..constraints...... 

Placement of the over-all launch window within a 24 hour period shall be' 

determined by: 

1) Mission requirements and priorities -- 

2) Vehicle constraints 

3.1.1.1.1.2 Solar Angle S3 SAR) 

The solar angle (p).shall be between -60 deg and +60 deg. 

The angle beta is defined as the angle between the earth-sun line and the 

orbital plane. 
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3. 1. 1. 1. 2 Launch Phase (U) 

This phase covers the period from initiation of countdown on the launch 

pad through lift-off. 

3. 1. 1. 1. 2. 1 Flight Crew Launch Occupancy \-4) 

The time to launch a Flight Vehicle after the flight crew enters the 

Gemini B shall be as short as possible, not exceeding 120 min, including scheduled countdown sequence holds other than the 60-min 

hold at T-10 min of paragraph 3.1. 1. 1.2..2 below. 

3. 1. 1. 1. 2. 2 Hold Time (Ns4) 

Holds may be used to meet an optimum launch time, within the specified window, dependent upon: 

1) Mission : requirements and priorities 

2) Evaluation of the confidence in ability to hold 

for the required time. 

The MOL System shall provide for up to a 1-hr hold at T-10 min. 

3. 1. 1. 1. 2. 3 Flight Crew Pre-Launch Egress \4) 

Prior to lift-off, escape from the Flight Vehicle in the event of an 

emergency shall be by egress from the flight, crew hatch or by means 

of the pad abort escape system at the discretion of the crew or by 

pre-arranged procedures. 

3. 1. 1. 1. 2. 4 Turn-Around Time Following Scrub\-4) 

Following a scrub during the countdown, the MOL System shall be 

capable of launch at the opening of the launch window on the next day 

with the only deviation being the repair time on failed non-replaceable 

subsystems/components. (Subsystems/components are not considered 

replaceable for the purposes of this requirement if de-fueling is 

required prior to replacement. ) If de-fueling is required to repair/ 

replace a failed subsystem/component, the MOL system shall be 

capable of launch within the launch window on the third day following 

the scrub. 

3-6 'MET- 

•Ihis document contains information affecting the not onal defense of the United States within the inclining of the Espionage L0.1. 

Tole I& U.S.C... Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by taw 
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3. 1. 1. 1. 2. 5 Back-up Launch Capability ( -4) 

Design of the Launch Operations, Facilities, Flight Operations, and 

Test Support Segments of the over-all MOL system shall not be such 

as to preclude the future incorporation of capability to achieve a 

back-up launch within a 30-day period following determination of the 

requirement for such a launch. Design considerations to support the 

requirement shall be based upon the assumption that flight hardware 

can be made available for launch site integration and checkout in time 

to support the back-up launch. 

3. 1. 1, 1. 3 Ascent PhaseX-4) 

This phase covers the period from lift-off through insertion into an 

initial sustainable orbit and confirmation thereof. 

3. 1, 1. 1. 3. 1 Azimuth 154s3 SAR) 

, • 

The system shall be capable, as a minimum, of launching a missionfrom 

Vandenberg Air Force Base (VAFB) at launch azimuths such as to 

achieve any orbit inclination between 80 and 100 deg, as specified in 

paragraph 3. 1. 1. 1. 3. 3, including the use of yaw maneuvers if required by range safety regulations. Launch azimuth capability compatible with the 65 to 125 deg orbital inclination stated in paragraph 

3. 1. 1. 1. 3. 3 is also a design goal herein. 

3. 1. 1. 1. 3.2 Trajectory Safety \-4) . 

The ascent trajectory shall be such tha;t, in the event of mission abort 

at any time, the Gemini B will not exceed safe conditions for re-entry 

and recovery or the Gemini B will be in an orbit from which normal 

re-entry can be made at a later time. 

3. 1, 1. 1. 3. 3 Orbital Inclination ( 3 SAR) 

Operation in all orbital inclinations between 65 ddg and 125 deg shall 

be achievable as a design objective for the OV. Inclinations between 

80 deg and 100 deg shall be achievable as a basic requirement. 

3-7. 

This document contains information affecting the national defense of the United States within the rneontng of the EN:now:19e lows. 

Title 18, U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by lees 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.1.1.1.3.4 Insertion Conditions\-3 SAR) 

Insertion shall be performed by the Launch Vehicle into an initial 

orbit with a minimum perigee of 70 n. . mi. located between 30

o - 50° N 

latitude. 

It shall be possible to alter insertion parameters as late as three days 

prior to a scheduled launch, provided the changes do not exceed the 

redeployment capability of the downrange elements. 

3. 1. 1. 1. 3.5 Communication Ns4) 

The system shall provide voice communication between the flight crew 

in the Gemini B and Mission Control during all portions of powered ascent. 

3. 1. 1. 1. 3. 6 Flight Crew SafetyX4) 

Crew safety during the ascent phase shall be provided by the inherent safety 

..of the MOL Flight Vehicle and the abort/escape system of Gemini B. The 

probability of a crew fatality during powered ascent shall be no great er 

than 0.0003. 

3.1. 1. 1. 4 Early Orbit Phase 

This phase begins after insertion and ends when the flight crew has shut 

down the Gemini B and has transferred to the Laboratory Vehicle . 

3.1.1. 1. 4.1 Orbit AdjustSs...3 SAR) 

Orbit adjust is the transfer from the initial sustainable orbit , or any 

orbit, to any subsequent orbit. Orbit adjust shall be accomplished by providing the required V from the Laboratory Vehicle Attitude Control Translation . 

System (ACTS). See • 3.-3.2-.2.7N-473- - 

3.1.1.1.4.2 Orbital Altitude 13s3 SAR) ,

The MOL system shall be capable of achieving any orbit, circular or elliptical, 

within the limits defined in Figure 3-1. The extreme boundariesof the required operating altitudes and required inclinations shall be achievable from 

the combination of the booster velocity and the velocity achieved from ACTS 

operation.. 

3.1.1.1.4.3 Flight Crew TransferNc4) 

Passage of the flight crew between the Gemini B and the Laboratory Vehicle 

shall normally be accomplished within a pressurized tunnel., Capability for 

extravehicular crew transfer will be provided as a back-up mode. 

3-8 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 iqt.,c 

r • r]: 

3.1.1.1.5 On-Orbit Phase (U) 

This phase covers the period from insertion until separation of the 

Gemini B from the Laboratory prior to the in itiation of re-entry. 

3.1.1.1.5.1 Duration <1) 

The nominal MOL System OV mission duration shall be 30 days. 

3.1.1. 1. 5. 2 Nominal Orbiting Vehicle OrientationX-4) 

• The OV shall be nominally oriented such that the longitudinal axis is 

aligned with the orbital plane, with Gemini B forward, and perpendicular 

to the local vertical. As an alternate mode, the longitudinal axis will be 

aligned with the relative velocity vector (Ref. Paragraph 3.3.2.2.7.2. 1) 

and the local vertical. 

3. 1. 1. 1. 5. 3 Orbit Maintenance J1■iQ SAR) 

The perigee shall be no less than 70 n. mi. throughout the on-orbit phase 

of the mission. 

3.1.1.1.5.4 Abort€4) 

The system shall be capable of evacuating the MOL flight crew in the event 

of an on-orbit mission abort and of returning the crew to preselected water 

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

flight crew. 

3. 1. 1. 1. 5. 5 Checkout and Monitoring (U) 

The Orbiting. Vehicle shall contain equipment capable of providing information relative to the operation of vehicle systems and well-being of the flight 

crew. These data shall be available to the flight crew on-orbit and to the 

Mission Control via the ground network. The data available on-orbit shall be 

of a form that allows easy recognition of parameters critical to flight crew 

s afety, mission status, and Orbiting Vehicle equipment status. Recognizable 

visual and auditory warning devices shall be provided for critical parameters. 

The status of critical Gemini B subsystems shall be available to the flight 

crew during the on-orbit phase . 

3. 1. 1. 1.5.6 Flight Crew Transfer 

(now Paragraph 3.1.1.1.4.3) 

3.1.1.1.5. 6 Mission Operations SAR) 

The equipment shall be operable by flight crew members. The equipment . 

design for the segments listed below shall be such that the crew time allocations 

shall not be exceeded in normal operations. 

ratv 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 it 'et; a 

QI7 kz.:1; 

Maximum Average 

Hr/Day 

Mission Payload 

Laboratory Vehicle 

Gemini B (Monitoring) 

Crew (Eat/Sleep/Arousal/ 

Conditioning/Personal/ 

Equipment) 

16.0 

4..0 

0.25 

24.0 

TOTAL initial Allocation 44.25 

The equipment shall be designed for remote operation 

from Mission Control with provisions for monitoring both 

by Mission Control and by the flight crew during automatic 

operation. For automatic operation, mission vehicle 

operations may be programed for duty cycles in excess of 

t hose given in the above table to provide additional data. If 

this is done, crew activities may be appropriately scheduled 

to Permit operation (monitoring) in accordance with that 

schedule. 

3.1.1.1.5.7 Maneuvering4) 

The OV shall have three axis attitude control and attitude maneuver capability. 

It shall also have the capability of providing linear acceleration in the 

direction of the longitudinal axis. 

3.1.1.1.6 Re-entry Phase (U) 

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

from the Laboratory and ending with landing. This phase 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

includes loiter time, retro-fire, de-orbit, parachute deployment, and 

touchdown. Loiter is defined as a mode during which the Gemini B 

operates as an autonomous spacecraft separated from the Laboratory; 

this separation is required in the event of a failure of a critical Laboratory system. 

3. 1.1.1.6. 1 Separation (U) 

The Gemini B shall be capable of separation from the Laboratory 

Vehicle only by flight crew initiation from the Gemini B. 

3. 1. 1. 1. 6. 2 Communications (U) 

During re-entry, recovery aids (including a beacon) shall be provided 

in the re-entry module to facilitate tracking and touchdown prediction. 

A voice communication link shall be provided. 

3. 1. 1. 1. 7 Retrieval Phase (U) 

Retrieval operations start with the re-entry module touchdown prediction and end when the crew, data, and re-entry module are recovered • 

and returned to predetermined locations for the initiation of post-flight 

analyses. Retrieval includes location of the re-entry module, physical 

recovery of the re-entry module, crew, mission data, an initial 

medical examination, and initial de-briefing of the crew. Communications and location aids shall be provided for use during this phase. 

3.1.1.1.7. 1 Recovery Support (U) 

Recovery forces consisting of land, sea, and air units equipped with 

proper gear to facilitate recovery of the flight crew, re-entry module, 

and data shall be provided. 

3. 1. 1. 1. 8 Performance Evaluation (U) 

Mission performance evaluation shall include: evaluation of flight 

crew performance, evaluation of on-orbit equipment (both vehicle and 

mission equipment), and evaluation of over-all mission operation including pre-launch and launch operations. 

SSD AFARr2 20B 
I 

Operating Locations 

Acceptance TestsX4) 

All contractor AVE equipment shall be assembled and acceptancetested at the respective responsible contractors' facilities prior to 

shipment to either VAFB or to the Laboratory Vehicle contractor's 

facility, as appropriate. Those system elements of the Orbiting 

Vehicle which are supplied to the Laboratory Vehicle contractor as 

GFE shall be installed at the Laboratory contractor's facility for in- 

.., 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 1. 1. 1. 9 

3. 1. 1. 1. 9. 1 

tegration tests. 

3. 1. 1. 1. 9. 2 

(See Fig. 3-4..) 

Pre-Launch Integration, Checkout, and Launch ():Sci) . 

Following receiving, inspection; and assembly of various equipment 

items at the OV Assembly Building, final assembly of the MOL System 

Flight Vehicle will be completed at the launch area. The Flight Vehicle 

will be checkout out and launched from the Western Test Range. • 

3.1.1.1.9.3 Mission Operations 

3. 1. 1. 1. 9. 3. 1 Mission Control \-4) 

Mission Control shall be at the Satellite Test Center in Sunnyvale, 

California, and will exercise centralized control over all aspects of 

the mission. 

3. 1.1. 1. 9. 3. 2 Tracking and Communication Sites X-4) 

Tracking and communication network stations are designated by the 

phase of the mission profile during which they operate. The stations 

chosen for each phase are as follows: 

(1) Ascent 

WTR/Point Arguello 

PMR/San. Nicholas 

PMR/Point Mugu 

NRD Ships 

SCF/VAFB 

3-12 

FORM This document contains .information affecting the notional defense of the United Stores within the mooning of the Espionage Lows. 

SSD AUG 62 20B title 16, U.S.C.. Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by low 
SCF stations 

Selected NASA stations 

Selected ETR stations 

Selected WTR stations 

(2) Early Orbit 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 1. 1.1.9.4 

(3) On-Orbit 

SCF stations 

Selected NASA and ETR stations 

Recovery Areas 0•s=1) 

Recovery ships and aircraft will be placed in areas so located as to 

provide a number of supported recovery opportunities each day. There 

will be a supported recovery capability for each of the first three 

orbits (in addition to launch abort recovery zones) and a supported 

recovery capability for about once every 12 hours thereafter. All 

recovery areas will be near the continental U. S. or U. S. controlled 

territories. 

3.1.1.1.10 Mission Responsibilities (U) 

Mission responsibilities are as defined in the Government Plan for 

Program Management for the MOL, SSMD-77 (Security Control number 

only). 

3.1.1.2 Logistics 

3.1.1.2.1 Supply Support (U) 

Spare parts support for the Laboratory Vehicle, Gemini B, Mission 

Payloads, and associated AGE shall be provided in accordance with 

SSD Exhibit 63-14 dated 15 Nov 63 and its Amendment #1 dated 14 Apr 

65. Spare parts requirements shall be based on a concept of mini, 

mum maintenance at launch site by component replacement. 

3.1.1.2.2 Maintenance Support (U) 

All levels of maintenance for the Laboratory Vehicle, Mission Payload, 

_Gemini B, and associated AGE shall be vested with the respective . - 

--CONFIDE:441AL-- 3-13 

FORM This document contains information - affecting the notional defense of the United 'states within the meaning of the Espionage Lows. 

SSD AUG 62 20B Title 18, U.S.C., Section 793 and 794, the, transmission of which in any monner to an unauthorized person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-10NRIEMAL--- 

responsible contractors. Maintenance considerations in support of 

the Laboratory Vehicle,, Gemini II,' and its -AGE should be principally 

confined to the removal and replacement of modules/components. 

Maintenance facilities available at the launch site will.not be duplicated when existing facilities can be made available for progi•am 

utilization. 

3. 1. 1. 3 

Deleted 

3. 1, 1. 3. 1 

Personnel and Fraining 

Operational Personnel 

There are no Operational Personnel for MOL in the general military 

sense except as included in the support functions. Support personnel 

asrsociated with flight operations will be assigned and/or coordinated 

by the MOL System Program Office. Personnel required for the assembly, checkout, maintenance, launch, and operations support shall. 

besupplied and trained by contractors concerned with the various -system segments. 

3-14 

This document contains information affecting the notional defense of the United States within the meaning of the Espionn91 ;Ws. 

SSD a7.13Rld2 208 Title la, U.S.C., Section 793 and 794, the treinunission of which in any manner to art unauthorised person is prohrhited by la. 
0 

co 

.r• 

VEHICLELIMITS NOT/NCLUPEO 

W 

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NN tv co (NI 

7W ,201W17v •Rpsociv 

• . 3-15/16 

This document contains informolion affecting the notional ddense of the Undid Stems within the meaning of the tsp.:maw tows. 

7

tfle le, U.S.C.. &Knan 793 and 794, the transmission of which in any manner to on unauthonted person is pichihtd by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SIECREI, SPECIAL HANDLING 

3.1.1.4 Mission Characteristics 

3.1.1.4.1 Target Selection Capability 

Target selection shall be made by command decision and ground data 

processing considering priority of targets, weather, and the time required 

to complete a given target relative to accessibility of succeeding targets. 

During manned operations, the crew will have the capability of making final 

target selection (e.g. select an alternate target rather than a primary 

target because of weather considerations). It is desirable that ground 

data processing have the capability of minimizing photography of cloud 

obscured (in preference to cloud free) targets. 

3.1.1.4.2 Data Retrieval 

nzokmu-lomtomatic Configuration 

The system shall be capable of processing and returning data 

from the exposed film and returning the exposed film itself. Three methods 

of data retrieval shall be used: (1) Data selected by the astronauts, 

processed and transmitted over a widehand readout link to the ground 

facilities. Security considerations dictate a cryptographic link for this 

data transmission. (2) Exposed film returned by a Data Re-entry Vehicle. 

(3) Exposed film returned with the astronauts in the Gemini B. 

Automatic Configuration 

Film will be returned periodically by Data Re-entry Vehicle. 

3.1.1.4.3 Command and Control 

The system shall have the command and control capability required to obtain photographs of the maximum number of clear targets from 

the target list. Radio contact with the ground is permitted as a portion 

of the command and control, as well as for purpose of tracking and telemetry. 

- Automatic Configuration 

The command and control capability shall use a crew of two 

astronauts in a manner consistent with the requirement to reserve the 

--sinET_SPECIALHANDUNG 
NRO APPROVED FOR 

RhirtAtik*410 A.2015 MI ia ffi E L 

astronauts for functions for which they are especially and uniquely qualified. 

The system shall be capable of operation by a single astronaut with minimum 

degradation to system performance. 

3.1.1.4.4 Mission Orbital Envelope 

The Orbiting Vehicle must be capable of operating over the apogee 

and perigee intervals for the orbital inclinations shown in Bigure 3.1-1. The 

maximum altitude for photography shall be 230 n.mi. 

Photography will be conducted over the area of interest at sun 

elevation angles at the target (eta) as small as five degrees. Sun illumination required for high quality photography defined by this specification is 

890 ft lamberts, which corresponds to a sun angle of approximately 40 degrees. 

Orbital parameters for the Dorian mission shall optimize the 

optical resolution and target access as given in Section 3.0.4.2, within the 

sun angle constraints as stated above and in Section 3.1.1.1.1.2. 

3.1.1.4.5 Quick Launch Reaction 

The capability shall exist to launch within the orbit envelope 

shown in Figure 3-1.1, with notice of nominal lift-off time and selected 

orbit parameters for the given mission days prior to this nominal liftoff time. The system shall have the capability of responding to a new target 

list, based on unchanged orbital parameters, as late as hours prior to 

launch. 

3.1.1.4.6 Resolution 

The resolution achievable at zero stereo angle by the system as a 

function of obliquity and illumination must be no worse than that shown in 

Figure 3-1p. The specified ground resolution includes the dynamic resolution 

loss due to all contributions to smear. 

Across-the-format INT corrections shall be provided so that the 

loss in resolution anywhere within 0.8° diameter circle about the center of 

format from the resolution achievable at the center for format shall be no 

greater than that given by Figure 3-1.3. 

--sEr6RET, 
z 

110 

240 

100 

APOGEE ALTITUDE 

160 

140 

1s 

110 

Figure 3-1.1 Orbit.:Envelpve 

SPECIAL ,IDUNG 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

TO*PERIGEE ALTITUDE= 65 N.M. 

I 

110 TO to HO 

ORBIT INCLINATION 'IDIOMS/ 

3-16.3 
SPECIAL HANDLING 

w 
RES - ii-V215 6ratilik 

NvApply9F0R, 

Figure 3-1.3 

Across the Format IMC 

(later) 

SPECIAL hANDLING 

3-16.5 
R 

PM 

NatAWR 

J 15 

3 .1.1.4.7 Smear Limits 

In addition to the resolution specification, it is required that 

the amount of smear appearing on the format be limited to a maximum acceptable 

value. 

--Automatic Configuration 

It is assumed thatthe astronaut contribution to rate control 

will allow the system to meet this value. However, in order for the astronaut 

to perform properly in this function within reasonable time constraints, the 

smear contribution provided by the system exclusive of the astronaut participation in rate control must also be limited. The total smear contribution 

to dynamic resolution loss in terms of angular rate shall not exceed the 

following values at the center of formats 

greater than 

a. With astronaut participation in rate control: 

radians/second (2 o-) 

b. 1k:elusive of astronaut participation in rate control: 

radians/second (2e) 

The uncompensated image smear due to vibration shall be no 

radians/second (247-). 

Automatic ConfigiTation, 

The total smear contribution to dynamic resolution loss in terms 

of angular rate shall not exceed radians per second. The uncompensated 

image smear due to vibration shall be no greater than radians per 

second. 

3.1.1,4.8 Data Reconstruction 

For reconstruction of ground detail and object location it is 

required that altitude and time information be included on the film edge, 

Edge data are discussed in detail- in section 3.3.4.5.6. 

3.1.1.4.9 Orbital Reaction Times 

While in orbit, the system shall be capable of reacting to 

changes in the target list received by the Satellite Test Center at Sunnyvale, 

California, one-half hour or more before a command loading opportunity where 

these changes do not require a change in orbit parameters. 

SPECIAL iihil!DUK6 3-16.6 
SPECIAL HANDLING 

3.1.1.4.10 Astronaut Requirements cAutomatic Configuration) 

The major astronaut contributions required for commands and 

control consist of: 

a. Selection of Targets 

In the presence of cloud cover which is not 100 percent, 

the astronauts will select the least obscured target from the primary and 

alternate targets. 

b. Reduction of Tracking Error 

Two acquisition and tracking scopes will be provided.. 

By acquiring and tracking the next target while photography of the current 

target is occurring and being monitored (or controlled) by one of the two 

astronauts, the other astronaut will observe that the tracking error for 

the next target is reduced to a minimum by the time the target becomes 

current. At the time a target becomes current, the tracking mirror will be 

slewed to the target. One astronaut may then observe that the tracking error 

is milled in position and rate while observing the target through the main 

optics. 

e. Cluster Photography 

The capability shall be provided to photograph the targets 

of a cluster in the following manner. The first target will be acquired at 

a forward stereo angle and the image motion will be stopped by the astronaut. 

The camera will then automatically step through the other targets of the 

cluster, taking one photograph of each at a forward stereo angle. The. 

computer will provide precise angle rates for succeeding targetst based on 

the astronaut-controlled rates obtained for the first target. This entire 

procedure will be repeated to provide one photograph of each target at an 

aft stereo angle. (See 3.5.3.4.7) 

d. Photographic Results 

The astronauts will compile information on the results of 

the photography for each target. This information will be furnished to the 

ground facility controlling target selection. 

e. Data Readout Editing 

Generally, only a portion of selected photographic frames 

will be read out. The astronauts will select that portion. 

f. Verbal reporting of visual observations or photographic 

interpretation of selected high priority target information. 

--sECREL SPECIAL HANDLING 

1-16.7 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 
NRIgaljEA 1HANDLING IMe*- 

3.1.1.4.11 De-orbit Dorian System Hardware 

A capability to de-orbit the Dorian System hardware into 

designated water impact areas at termination of orbital operations shall 

be provided. 

3.1.1.4.12 Security of Operations 

Provisions shall be made for interfacing technical personnel 

(e.g., EK personnel) in support of checkout, launch, and orbital operations 

so that maximum support can be provided without compromising Dorian security 

requirements. In addition, the ground-vehiCle communication system must be 

designed for efficient communications without compromising Dorian security 

requirements. 

SPECIAL HANDLING 

3-16.8 
NRO APPROVED FOR 6 

RELEASE 1 JULY 2015 

3. 1.2 System Definition 

3. 1. 2. 1 System Engineering Documentation 

3. 1. 2. 1. 1 MOL System Top Level Functional Flow, Diagram 

The MOL System Top Level Functional Flow Diagram (Fig. 3-2) 

contained in this System Specification is the starting point for system 

engineering of the MOL System and is arranged to facilitate integration 

of system engineering activities. Each block of the diagram represents 

a functional area which has special interest to one of the Associate* 

(contractors or participating government agencies). This contractor/ 

agency (in parentheses just above each block of the Top Level F1011 ,

Diagram) is assigned responsibility for intermediate integration of 

'system engineering data of Associates making contributions to the 

functions contained in the block. 

Intermediate integration is accomplished by first .developing?in 

cooperation with the contributing Associate contractors/agencies, the 

necessary lower level flow diagrams for the functions .of the block 

which clearly divide the task responsibilities among the Associates, 

and supplying them to the Contributing Associates. Each Contributing 

contractor/agency then prepares the system engineering data for his 

part of the system and delivers it to the designated Intermediate 

Integrator for integration to assure compatibility. The data packages 

which result from this process are then integrated for over-all system 

compatibility by the Laboratory Vehicle Contractor acting as the 

Over-all System Integration Contractor. All steps in this process will 

be monitored by the MOL SPO and periodic formal reviews will be held 

to determine status and progress. 

3. 1. 2. 1. 2 MOL System Flow Diagram Code 

The code system for identification of the blocks in the MOL system 

functional flow diagrams is shown in Figure 3-3. Each block designator consists of an alpha-numeric code which identifies: (1) the 

3-17 
NRO APPROVED FOR 

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1 mission, (2) the participating Associate responsible for preparing the 

block, and (3) the area in which the activity is conducted. In addition, 

each block will contain an identification number as shown in Fig. 3-2; 

3. 1. 2. 1. 3 MOL System Segment Flow Schematic 

A representation of the MOL System Segment hardware flow between 

the principal Associates and the MOL Launch Site (MLS) is shown in 

Fig. 3-4. Factories and other facilities are shown in enclosed 

dashed-line blocks. The movement of a hardware item (AVE, AGE, 

AAE) is shown by a dash-dot-dash line. The DAC area for integration 

and test is shown as a separate facility only for clarity. Over-all 

grouped facilities (e. g. , the SCF or MLS) are enclosed by heavy solid 

lines. Light solid lines on the schematic indicate a hard-line connec- 

•r 

tion (cable or microwave link) between points. 

3.1.2.1.4 Top Level Function Flow Descriptions 

The functions included within each block of the Flow Diagram 

(Fig. 3-2) and their starting and stopping points are defined below. 

3. 1. 2. 1. 4. 1 Block 1. "Evaluate MOL System" 

The functional objective of this effort is to achieve a qualitative 

appraisal of the performance of the various elements comprising the 

MOL System and of the System as a whole. This appraisal shall 

facilitate: (a) management cognizance of important milestones both 

during and following each flight which will enable decisions to be made 

on a timely basis in regard to changes of in-flight programming and to 

future flights, (b) detection of deficiencies so that required corrective 

actions may be implemented, (c) determination of additions or changei 

which could improve future capabilities for manned or unmanned 

operations of military significance. 

Each of the Associates will determine the data items he requires for 

this appraisal effort as a part of his participation in the analysis of 

3-18 
NRO APPROVED FOR 

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requirements for the assigned functions derived from the Top Level 

Flow Diagram (Fig. 3-2). These will include:the types and quantity of 

required data items to be recorded, transmitted by telemetry, retrieved, measured prior to launch or after recovery; evaluation 

criteria; and the equipment, personnel, and facility requirements for 

processing and reducing the data. Tradeoff studies shall be made as 

necessary to ascertain the data requirements. The Laboratory 

Vehicle Contractor will collate and intermediately integrate these 

requirements. He will also review the over-all system requirements 

to see that the data necessary for evaluation can indeed be obtained 

from all parts of the program. 

An appraisal of the performance of the MOL System will be made after 

.r. 

each flight and will include all of the required data items enumerated 

in this analysis, including such possible items as: test, transport, 

maintenance, training, simulation, installation, checkout, control, 

transfer, on-orbit operations, de-orbit, recovery, and post-recovery 

analysis. 

• 3. 1. 2. 1. 4. 2 Block 8. "Test, Accept, and Deliver MOL System" 

The functions to be analyzed for requirements start with the completion of fabrication of the MOL AVE and supporting ground equipment, 

and proceed through evaluation tests, acceptance tests, qualification 

tests, shipment to the test range (or other location, in the instance of 

certain AGE), receipt. and inspection at the MOL Launch Site (MLS) 

and checkout of ground equipment at the contractor 'receiving and 

maintenance area. The functions of this block terminate with delivery 

to the ILC for assembly and integration. 

Each Associate responsible for-contributing equipment or software to 

the MOL program will analyze his own area of responsibility to define 

his equipment, test, personnel, and facility requirements. The 

Laboratory Vehicle Contractor will collate and perform intermediate 

3-19 
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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

C 

FIRST DESIGNATOR 

MISSION CODE 

,SECOND DESIGNATOR 

ASSOCI E CODE 

THIRD DESIGNATOR 

AREA CODE 

K MOL 10. Laboratory Vehicle Contra, tor AA Contractor Factory Area 

KA' . (Douglas) AB Douglas 

KB 11. Gemini B Contractor ABC IBM 

KC (McDonnell) AC McDonnell 

KD 12. Mission Payloads AD Martin 

KE 13. Flight Crew Equipment AE GE 

KF Agency (MOL SPO) BA Government Agency Area 

KG 14. Titan III Agency (T-III SPO) BB MOL Launch Site (MLS) 

14.2 AC Electronics BBA ILC 

14.3 Martin Company BBT Launch Pad in ILC 

14.5 Aerojet-General BBW Receiving Inspection and 

14.6 UTC Maintenance Areas 

15. Deputy for Civil Engineering BBX Ordnance Areas 

(SSD) BBY Propellant Storage Area 

15.1 Stearns-Roger (ILC) BC Satellite Control Facility 

15.2 Daniel, Mann, Johnson and BCC Satellite Test Center 

Mendenhall CA Transport 

16. Launch Operations Agency CB Factory to Factory 

(65- - AT W) CC Factory to Governivient 

17. Flight Operations Agency Area 

(SCF) CD Govt Area to Govt Area 

18. Recovery Agency DA In-Flight 

(DOD Manager) DB Ascent 

19. Test Support Agency DC Injection 

20. Overall Systems Integrator DD On-Orbit (OV) 

(Douglas) DE On-Orbit (Loiter) 

X Plurality of Contractors 

and/or Agencies 

DF 

DO 

Re-Entry 

Descent 

(-) Designation Pending EA Recovery 

EB Planned Recovery Area 

EC Contingency Recovery 

Area 

ED Emergency Recovery 

Area (MLS) 

EE Emergency Recovery. 

Area (Other) 

FA 

XX Plurality of Areas r: 

(—) Designation Pending 

Figure 3-3. • 'MOL System Flow Diagram Code 

3-21 
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integration of these requirements to ensure over-all system assembly 

test program, handling, and receiving compatibility. It is expected 

that the required intermediate integration will be minimal since, in 

the performance of these functions, the inter-contractor interfaces 

are limited. 

3. 1. 2. 1. 4. 3 Block 7. "Perform Installation, Checkout, 

Pre-Launch Operations, and Launch" 

The Laboratory Vehicle Contractor will perform the intermediate 

integration of all of the requirements of these functions which 

start at the receipt of flight hardware at the ILC and terminate 

at lift-off. Also to be included in the requirements analysis are 

the installation and checkout of the ground systems equipment 

used at the ILC (excluding NRD and SCF equipment which are 

covered in Block 12), and accomplishment of a launch complex demonstration. As a result of this intermediate integration, the requirements for the launch operations are to be collated and integrated. 

Branches of these functions covering the normal modes of operation 

are to be analyzed for requirements for such items as pad receipt, 

pad checkout, positioning for assembly and readiness operations, interAssociate communications, and launch countdown. Also included shall 

be the installation and checkout operations at the pad, Launch Control 

Center, and. propellant and hazardous-commodities storage areas. ' 

Branches of these functions, covering refurbishment and non-normal 

modes of operation (such as equipment recycling after a hold or a 

scrub, or after an abort where damage is limited) shall be analyzed 

for requirements. 

3. 1. 2. 1. 4. 4 Block 6. "Perform Boost, Insertion, and Separation" 

These functions start at lift-off and terminate when successful insertion 

into an initial orbit has been achieved and the Orbiting Vehicle has been ; 

separated from the final Launch Vehicle stage. 

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Boost, insertion, and separation under both normal and various contingency modes are to be branches of these functions analyzed for requirements for both personnel and equipment. The Launch Vehicle 

Contractor is responsible for the intermediate integration of all of the 

requirements of these functions. The Laboratory Vehicle contractor 

shall be responsible for the integration of requirements affecting the 

integrity of the OV. 

3. 1. Z. 1. 4. 5 Block 5. "Perform Initial Orbit Adjust and 

Transfer of Flight Crew into Laboratory" 

These functions start when a successful insertion and separation have 

been achieved and the flight crew can now prepare to perform the 

maneuver into another orbit and then to transfer from the Gemini B 

r• 

to the Laboratory Vehicle. Termination of these functions occurs when 

the second flight crew member completes his transfer, defined as the 

time at which he closes the tunnel door between the Laboratory 

Vehicle and the Gemini B. 

Normal, contingency, and emergency modes of these functions are to 

be analyzed to determine the requirements for both equipment and 

perSonnel. The Gemini B Contractor will perform the intermediate 

integration of the requirements for these functions. 

3. 1. 2. 1. 4. 6 Block 4. "Perform On-Orbit Objectives" 

These functions start when the second flight crew member arrives in 

the Laboratory Vehicle following transfer and closes the tunnel door 

and terminate with the opening of the tunnel door for the departure of 

the first flight crew member. 

Normal, contingency, and emergency modes of operation are to be 

branches of these functions. Laboratory Vehicle requirements, as 

well as payload requirements and procedures, and personnel requirements are to be detailed. The Mission Payload (Experiments 

Integration) Contractor will integrate the requirements for the payloads 

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0 and their operation, and will program the payloads by flight. The 

Laboratory Vehicle Contractor will perform the intermediate integration of all of the requirements for these functions. 

3. 1. 2. 1. 4. 7 Block 3. "Perform Transfer of Flight Crew, 

Separate, Loiter, and De-Orbit" 

These functions start when the first flight crew member opens the 

tunnel door preparatory to transferring from the Laboratory Vehicle 

to the Gemini B and terminate at earth touchdown. Both normal and 

emergency termination of the mission will be considered for flight 

crew departure from the Laboratory Vehicle. The Gemini B Contractor 

will perform the intermediate integration of the requirements for these 

functions. 

. r3. 1. 2. 1. 4. 8 Block 2, "Perform Retrieval Operations" 

These functions start with earth touchdown and include normal 

retrieval from plannedrecovery areas or from contingency recovery 

areas, as well as emergency retrieval operations. The function 

terminates with delivery of the flight crew and spacecraft to predetermined locations for initiation of post-flight analysis. The Gemini 

B Contractor will perform the intermediate integration of the requirements for these functions. 

3. 1. 2. 1. 4. 9 Block 9. "Define Requirements for Flight Crew 

Training and. Preparation" 

The functional objective of this block is to ensure, for each flight, a 

crew that is adequately and specially trained and prepared to accomplish the particular mission. All affected Associates will have inputs 

for the flight crew training requirements. Examples of such inputs 

are: training for Gemini B functions, Laboratory Vehicle operation 

and maintenance, communications operations, mission operations and 

maintenance of special payloads, data handling, reprogramming of . 

operations, housekeeping, emergency procedures, etc. 

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The Laboratory Vehicle Contractor as the intermediate Integrator will 

collate the separate requirements and integrate them into meaningful 

and compatible training requirements that, with optimum use of the 

simulators and trainers, will accomplish all of the objectives. Flight 

crew training will be accomplished by those Agencies assigned the 

actual training responsibility. . 

3.1.2.1.4.10 Block 10. "Perform Simulations" 

Each Associate will analyze the simulation requirements of his equipment and determine the performance and design requirements for 

simulation equipment, personnel, and facilities. The Laboratory 

Vehicle Contractor will assemble the contributions of individual 

Associates as well as define the integrated requirements for the 

Mission Simulator. 

3.1.2.1.4.11 Block 11. "Maintain System" 

The functions covered here include all preventative and corrective 

(both scheduled and unscheduled) maintenance of AVE, AGE, AAE, 

and facilities. Included are ground maintenance before and during 

flight, and on-orbit maintenance of the Orbiting Vehicle. RequireMents from each Contributing Contractor will be assembled by the 

Laboratory Vehicle Contractor acting as Intermediate Integrator. 

3.1.2.1.4.12 Block 12. "Perform Mission Control" 

This function is primarily centered in the time period starting with 

lift-off and terminating with recovery. However, certain closely 

related functional activities are also performed during the countdown, 

particularly during the period of the T-count. 

Each Associate will develop his mission control needs as part of his 

participation in the analysis of the other appropriate functions on the 

Top Level Flow Diagram (e. g. , "Perform Boost, Injection, and 

.Separation", "Perform On-Orbit Objectives", etc.) and their appropriate sub-functions. Included are Mission Control requirements for 

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all of the networks and stations involved in the processes of monitoring, 

receiving and/or transmitting information bearing on the flight or on 

the readiness to commence or terminate flight. Included are the 

requirements for control, communications, weather and sea condition 

forecasts, tracking, telemetry, data recording and reduction, and 

status reporting. The Laboratory Vehicle Contractor is the Intermediate Integrator for the requirements of these functions. 

3. 1. 2. 1. 4. 13 Block 13. "Pre-Launch or Ascent Abort" 

The functions in this block include all abort modes which can occur 

prior to injection of the Orbiting Vehicle into a sustainable orbit. The 

abort can occur any time starting with entry of the flight crew into the 

Gemini B prior to launch and ending with injection of the Orbiting 

.r. 

Vehicle into a stable orbit. The functions start with receipt of a 

signal in the spacecraft indicating an incipient failure and the need for 

emergency termination of the mission. These functions terminate upon 

earth touchdown. The Gemini B Contractor will perform the intermediate integration of the requirements of these functions. 
L. 

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3. 1. 2. 2 System Segment List 

The following MOL System Segments are identified. Necessary 

ground support equipment, simulators, software, and other segmentdetermined material and activities are included under the appropriate 

segment. 

LOCATION IN 

THIS DOCUMENT 

Orbiting Vehicle System Segment 3. 3. 1 

This constitutes all segments and parts 

of segments which are retained as. a 

unit in orbit. 

Laboratory Vehicle System Segment 

•r3. 3. 2 

Gemini B System Segment 3. 3. 3 

Mission Payload System Segment 3. 3.4 

Flight Crew Equipment System Segment 3. 3.5 

Titan III System Segment 3. 3. 6 

Facilities System Segment 3. 3. 7 

Launch Operations System Segment 3. 3. 8 

Flight Operations and Support System Segment 3. 3. 9 

Recovery. System Segment. .3. 3. 10 

Te.st Support System Segment 3. 3. 11 

Flight Crew System Segment 3. 3. 12 

3. 1. 2. 3 Contract End Item List 

See paragraph 3. 3. X. 4 under each system segment. 

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3.1.2.4 Doran Functional Flow Diagram 

Figures 3-5 and 3-6 illustrate the functional flow sequence 

for the major elements of the Manned automatic and automatic configurations, 

respectively, of the DOrian System (later). 

SidE.Ga tiWWIARG 

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MANNED AUTOMATIC DORIAN SYSTEM INTEGRATION FUNCTIONAL FLOW 

(later) 

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AUTOMATIC DORIAN SYSTEM INTEGRATION 

FUNCTIONAL FLaw 

(later) 

SPECIAL liANDLIIIG. 
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3. 1. 3. System Effectiveness 

3. 1. 3. 1 Effectiveness Measures 

3. 1. 3. 1. 1 General 4) 

System Effectiveness is defined as the probability that the 

system will accomplish a specified mission within a given period of time 

under the planned support and usage conditions. The measure of MOL 

effectiveness shall be the extent to which the mission and the required 

data retrieval are accomplished. 

In the MOL Program Safety, Reliability, Maintainability, 

Quality Assurance and Human Engineering shall be integrated in an Effectiveness program. This program shall be primarily directed to maximizing 

MOL program effectiveness consistent with the maximum cost effectiveneis. 

The scope of Orbiting Vehicle and payload on-orbit 

scheduled and unscheduled maintenance and repair shall be established as. 

a result of design optimization. The MOL system shall be designed to permit on-orbit maintenance by the crew to the greatest extent consistent with 

the required ability to operate in the unmanned mode under remote control. 

Adequate accessibility shall be provided for maintainable items and provisions shall be made for storage of spare parts and tools. 

The primary MOL Program objective, for purposes of this 

requirement, is defined as: 

(1) Completion of the total of the orbital man-hours 

activity for mission performance including such checkout, alignment, calibration, repair, preparation, execution, processing, examination, communica" 

tions, and similar tasks which are an integral part of, or are in direct 

support of, the mission 

(2) Return to designated ground stations of the specified 

types, quantities, and qualities of data including that delivered by the 

astronauts in person 

(3) Provision of environmental conditions, life support, 

perforinance capabilities, and ground support for the duration of the missions 

as required to sustain the system and to perform the missions. 

(4) Determination of the capability of the Manned Orbiting 

Laboratory to operate effectively in an automatic mode and to establish a 

basis for the evaluation of performance, reliability , and operational 

lithitations of unmanned operation relative to manned operation. 

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3.1.3.1.2 

La 

Effectiveness Apportionment Nc40 

The effectiveness of the MOL system segments shall be developed 

to the highest level consistent with maximum MOL program cost effectiveness. 

Assigned values are given in the following paragraphs; however, as a result 

of system analysis and optimization, it may become desirable to negotiate a 

different level to improve program cost effectiveness. Should such a situation 

arise, a request for adoption of a different level, together with the supporting 

analysis, shall be submitted to MOL SPO for review and approval. The mission, 

unless specified otherwise, extends from the initiation of the launch countdown, 

to the final cessation of use of the element in question including data re-

'trieval and, for the crew, recovery. 

3.1.3.1.2.1 Orbiting Vehicle System Segment IXO 

'r' The allocation of effectiveness assigned to the Orbiting VehiCle 

SegMent shall be for the time period from launch through 30 days of orbital 

operation to separation of the Gemini B. Since the Orbiting Vehicle segment 

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

. - 

the other segments. 

3.1.3.1.2.2 Laboratory Vehicle System Segment .t%s.?1.) 

The combined effectivene'ss of the.Laboratory Vehicle for the , 

total mission shall not be less than 0.97 in the manned mode and 0.90 in 

the automatic Mode. 

3.1.3.1.2.3 Gemini B System Segment NOSs ) 

The effeCtiveness of the Gemini B for its total mission shall 

be not less than 0.97. Gemini B. shall be capable of on-orbit storage for 30 

days, and re-activation shall not. degrade the probability of successful 

re-entry below 0.9997. 

3.1.3.1.2.4 Mission Payload System Segment X.3.skR) 

• 

The effectiveness of the Mirseion Payload Segment'including-the 

mission module structure for the total mission shall be shot less. than 0.95 

. for the manned version and for the unmanned version. 

3.1.3.1.2.5. Crew Equipment System Segment Nc9 

The effectiveness of the Crew Equipment, including backup 

modes, shall be not less than 0.999. 

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CONFIDENTIAL 

3.1.3.1.2A Titan III System Segment (D<4) 

The effectiveness of Titan III from final coUntdovn through 

insertion shall be not less than 0.90 for manned launches. 

3.1.3.1.2.7 Launch Operations, Flight Operations, Recovery, and Test. 

Support System Segments 1(`Igs) 

The composite effectiveness of these segments shall be at 

least 0.98 for manned operations and at least 10.80 forunmaruted operations. 

3.1.3.1.2.8 Flight Crew System Segment t‘q 14.) 

The mission effectiveness of the Flight Crew Segment shall 

be not less than 0.99. 

3.1.3.2 Maintainability (U) 

A maintainability program shall be ithillebented to inn concurrently with equipment design, development, production, and system operation. 

3.1.3.2.1 Maintenance Requirements. 

3.1.3.2.1.1 Ground Maintenance Requirements INs-10 

The maintainability program for Launch Vehicle AGE shall conform to the requirements of MIL-N-26512C with the exceptions as spetified in 

Attachment 1 to SSD Exhibit 62-126.' 

The requirements. of MIL-M26512C shall apply in the design and 

development of all OV AGE, unless. specifically exempted. Maintenance at the . 

launch site shall be restricted to major module/component removal and replacement. Module and component repair shall, in general, be accomplished at 

the point ofmanufacture. The items to be repaired at'the launch site shall be 

restricted to'.that equipment which can be repaired and revalidated at the 

launch fadility more economically than at the point of manufacture, and with 

no degradation of performance. 

Ground maintenance of flight equipment shall be restricted to 

major module/component removal and replacement and/or to any module/component 

-which 'is designed to be removed and replaced during on-orbit operation of 

the OV. Spare modules shall be stocked at the launch site as required. 

The AGE shall be designed for ease. of maintenance, and shall 

baVe features which will facilitate fault isolation and detection. • 

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3.1.3.2.1.2 On-Orbit Maintenance Requirements (.4) 

See Paragraph 3.1.3.1.1 

3.1.3.3 Useful Life (U) 

All equipment necessary for the MOL program shall have a 

minimum storage life to be specified by MOL SPO in the pre-launch and 

storage environment described in SSD Exhibit 65-7. The equipment shall 

have a minimum useful life to be specified by MOL SPO in the environment 

stated in SSD Exhibit 65-7. 

3.1.3.4 Environment - Natural and Induced (U) 

The environments applicable to the MOL Progiam are 

specified in SSD Exhibit 65-7 "Environmental Criteria for the MOL System. " 

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0 (1) Prelaunch - (Applicable to all segments) 

(2) LaunchiAscent - (A?plicable to Airborne Vehicle 

and ground environment) 

On-Orbit - (Applicable to Orbiting Vehicle) (3) 

Descent and Recovery - (Applicable to Gemini B) (4) 

Transportability and Handling 

3.1.3.5.1 General (U) 

Existing transportation and handling equipment .from_ governmental or 

commercial sources shall be used in preference to the design of, new 

equipment. Equipment shall conform to the requirements of MIL-S8512B and MIL-C-8090C. 

3.1.3.5.2 

. 

Transportability (U) 

Q 

Transportation planning for all components of the MOL System shall 

be by air in accordance with SSD Exhibit 63-3 and MIL-A-8421B. 

'However, other modes of transportation may be utilized where more 

effective or when disassembly is required for air transport. 

3.1.3.5.3 Handling (U) • 

The handling provisions for ground' equipment shall be in accordance 

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

handling of ground equipment, the design shall incorporate the safety 

provisions 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 (U) 

Documents governing system development for Human Performance 

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 

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guidance since they are not totally applicable. The documents concerned with human performance (Flight Crew and/or Ground Crew) 

are listed in Section 2.0 with these prefixes: 

Applicable or partially applicable Prefix HP 

Guidance Prefix GP 

3. 1. 3. 7 Safety 

3. 1. 3. 7. 1 General (U) 

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) Explosion 

(3) Combustion 

(4) Acceleration 

(5) Corrosion 

(6) Electrical Effects 

(7) Radiation 

(8) Vibration 

(9) Stress 

(10) Fatigue 

(11) Noise 

(12) Toxicants 

3.1.3.7.2 Ground Safety (U) 

Applicable documents for Ground Safety are listed in Section 2.0 

. with the prefix letters SF. 

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System design for safety shall be coordinated with maintainability design to optimize system maintainability characteristics, safety chatacteristics, and human factors characteristics consistent with the 

effectiveness analyses and optimization. 

In the event of conflict with the requirements resulting from the optimization of crew safety, crew safety requirements shall take ptecedence. 

3.1.3.7.3 Crew Safety (V) 

The flight equipment design and development process shall include the 

analysis, specification control, and review of parts, materials, and 

designs (including human engineering provisions) to assure the maxi- 

.r.mum protection for the crew consistent with cost effectiveness. 

The equipment design, where practicable, shall be such that no single 

failure shall be cause for a crew casualty or shall necessitate a mission abort. 

3.1.3.8 Dangerous Materials and Components (U) 

(1) Concentrations of toxic compounds shall be 

within acceptable limits both for short term 

and for continuous exposure. 

(2) Techniques and equipments shall be selected 

to assure that safe exposure levels are not 

exceeded. 

(3) 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 (U) 

(See SSD Exhibit 65-7 for Environmental Criteria. ) 

3.1.3.10 Life Support (U) 

(See Paragraph 3.3.12) 

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3. 2 SYSTEM DESIGN AND CONSTRUCTION STANDARDS 

The System Design and Const ruction 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 and electrical. Design requirements of this type shall be 

imposed by specifying the incorporation of the established military 

standards and specifications a as applicable in the individual contract 

end item (CEI) specifications. The documents listed in Section 2 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 

.rRequirements specified herein shall apply to the design and construc 

tion of all system equipment. Those documents listed in Section 2 

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

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

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 

MIL-STD-143A and the requirements of this specification. Only those 

military documents listed in ANA Bulletin 400T and/or DOD Index of 

Specifications and Standards shall be interpreted as being Group I 

documents as defined in MIL-STD-143A. 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-143A. 

Any Group III documents selected for use shall automatically necessitate the preparation of a specification control drawing and shall be so 

drafted to establish the specific document being referenced, its date 

of issue, and contractor control responsibility for its use. 

Military Standards shall be employed to the maximum extent. 

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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 given to the stringent requirements of temperature, 

temperature gradients, thermal conductivity, toxic contamination potential in crew atmospheric environments, vibration, shock, loads, 

pressure, lightweight construction, and simplicity of manufacture. To 

ensure compliance with optimum utilization of procedures; processes, 

methods, etc. , the following shall be adhered to: 

(a) 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. 

(b) The use of non-standard materials, parts, and 

processes shall be justified as to the reason 

for their use in lieu of standard items as well 

as substantiation of their suitability for the 

intended application by submittal of engineering 

analyses, test reports, etc. , to demonstrate 

that the replacement has satisfactory performance characteristics. 

(c) Those documents listed in Section 2 with the 

prefix letters MP apply to the Materials, 

Parts, and Processes requirements. 

3.2.1.3 Standard and Commercial Parts 

MIL-HDBK-300 shall be used to ensure the use of standard and commercial parts. Qualified parts shall be used. To comply with this 

requirement, the following definitions and procedures apply: 

(a) Military Specified Parts, Military Standard 

Parts, and MIL-Spec Parts are interpreted as 

those parts controlled by, and procurable 

under, the documents classed as Group I in 

MIL-STD-143A. 

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(b) Government Standard Parts are defined as 

those parts controlled by and procurable under 

the documents classed as Group II and III in 

MIL-STD-143A. 

,r3.2.1.4 

(c) Industry Standard Parts shall be understood to 

be those parts controlled by and procurable 

under the documents classed as Group IV in 

MIL-STD-143A. 

(d) 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-143A. 

(e) Full utilization shall be made of Inter-Service 

Data Exchange Program (IDEP). (U) 

Moisture and Fungus Resistance 

Non-nutrient 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 (see MIL-STD-210). The tests necessary to 

satisfy this requirement are specified under MIL-STD-810A. 

3.2.1.5 Corrosion of Metal Parts 

3.2.1.5.1 Electrolytic Corrosion of Metal Parts 

The use of dissimilar metals and protection against electrolytic cor- . 

rosion shall be controlled in accordance with MIL-E-5400G and 

MS 33586A. Care shall be taken to prevent equipment corrosion in 

the Laboratory due to moisture under zero g convitions. 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, 

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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 Method's 

Protective methods and materials for cleaning, surface treatment, 

and application of finishes and protective coatings shall comply with 

MIL-F- 007179B. 

3.2.1.5.4 Materials. Compatibility 

Materials and surfaces which may be exposed to contact with effluents 

shall be selected for compatibility with these effluents insofar as 

design considerations. permit. Suitable compatibility data are given 

in the Storable Propellants Handbook, AFBSD- TR-62-2. 

3.2.1.6 Interchangeability and Replaceability 

3.2.1.6.1 Interchangeability and Replaceability in Terms of 

In-Flight Maintenance Requirements 

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

and experimental equipment shall not preclude the use of: common 

parts such as valves; electronic components such as transistors, 

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

unit or component can be utilized for several functions in many items 

of the same or different equipments. Connectors, fasteners, small 

tubing, and piping shall be designed such that satisfactory interchangeability can be accomplished for many of these common items to 

alleviate spare part requirements and variety of types of special, tools 

required for interchangeable, or noninterchangeable but replaceable, 

parts of a common nature. Applicable documents are listed in 

Section 2 with the prefix letters IC. 

3.2.1.7 Workmanship 

The workmanship requirements of MIL-STD-454 shall be implemented 

with the aid of written standards for workmanship. 

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3. 2. 1. 7. 1 Quality Assurance 

Quality assurance requirements must be implemented during the 

design and manufacturing phases to assure timely implementation of 

adequate and appropriate controls in accordance with MIL-Q-9858A 

and USAF Specification Bulletin No. 515. This will ensure that the 

materials, workmanship, and performance comply with specified 

standards, and that components have been manufactured and tested to 

approved drawings and specifications. 

3. 2. 1. 7. 2 Inspection and Test Equipment Selection 

The calibration system requirements shall comply with 

MIL-Q-9858A. (U) 

'`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 comply 

with USAF Specification Bulletin No. 515. 

3. 2. 1. 7. 4 Vendor and Subcontractor Selection and Control 

The contractor shall have a plan and/or procedure 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. Specification 

control drawings shall comply with MIL-D-70327. 

3. 2. 1.8 Electromagnetic Interference 

The General Design and Construction Requirements for Electromagnetic Interference (EMI) shall comply with SSD Exhibit 64-4. 

Applicable specifications are listed in Section 2. with the prefix 

letters EI. 

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3. 2. 1.9 Identification and Marking 

Equipment, assemblies, and parts shall be marked for identification 

in accordance with MIL-STD-130A. Specific identification requirements include such conditions as: 

(a) Equipment which may be damaged by operation 

in excess of the rated duty cycle shall be so 

marked. 

(b) Items with limited operating lifetime or shelf 

life shall be so marked, and a log shall be 

maintained and, attached to the subject item. 

(c) Critical components, as defined by 

AFSCM 375-1, Exhibit VI, shall bear a high 

visibility and unique marker, plaque, or decal 

which will immediately identify these cornponents. This identification shall not be used 

on any other type item, other than those 

classified as critical. 

(d) Applicable documents related to Specification 

and. Marking are listed in Section 2 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 that 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 in 

accordance with AFSCM 375-1. System design criteria relative to the 

in:orbit storage of maintenance items needed during the orbital 

mission shall be established by design activities. These criteria 

shall be incorporated into CEI specification and critical component 

specifications. Applicable documents relating to Storage listed in 

Section 2 are preceded with the prefix letters ST. 

. 3. 2. 2- Design Disciplines 

The design criteria listed shall be limited to specific design disciplines 

and/or types of equipment. 

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Or 

3.2.2.1 Electrical 

The electrical design discipline requirements have been prepared 

under SSD Exhibit 64-5. The applicable document's for this subject 

are listed in Section 2.0 with the prefix letters EE. 

3.2.2.2 Mechanical 

The general mechanical design discipline requirements specified in 

AFM 88-2 shall be applied to AVE, MGE, and OGE. 

3.2.2.3 Hydraulic and Pneumatic 

Applicable Hydraulic and Pneumatic reference documents are listed 

in Section 2.0 with the prefix letters HY. 

Civil 

Applicable civil engineering reference documents are listed in 

Section 2.0 with the prefix letters CV. 

3.2.2.5 Human Engineering 

Applicable human engineering reference documents are listed in 

Section 2.0 with the prefix letters HP for directly applicable documents 

and the prefix letters GP for those considered as guidance. 

3.2.2.6 Safety 

Applicable safety reference documents are listed in Section 2.0 with 

the prefix letters SF. 

3.2.2.7 Maintenance Support and. Spares Provisioning 

Applicable maintenance support and spares provisioning reference 

documents are listed in Section 2.0 with the prefix letters MS or MP. 

3.2.2.8 Environmental Criteria 

Applicable environmental criteria reference documents are listed in 

Section 2.0 with the prefix letters EV.. 
AMOVED 

a oLijj~ t7 

3.2.3 Dorian Exceptions 

The following additions/deletions comprise exceptions to 

the foregoing Design and Contruction Standards as applicable to the 

Dorian Mission Payload. 

a. Additions 

(later) 

b. Deletions 

(later) 

SPECIAL HANDLING 
71' 

* Includes Mission Module Struttp. 

NRO APPROVED FOR 

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3. 3 PERFORMANCE ALLOCATIONS 

3. 3. 1 2 Sem(U) System 

The Orbiting Vehicle shall be composed of the following 

system segments: the Gemini B, the Laboratory Vehicle, the Mission 

Payload, which includes the mission module structural shell, and the 

Flight Crew and Flight Crew Equipment. 

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

3. 3.1.1.1 Mass Parameters 

3. 3. 1. 1. 1. 1 Weight Breakdown SAR) 

Within the Orbiting Ve hicle System Segment, the maximum 

design allocation of weights shall be as follows: 

.)tanned: 

Automatic 

Laboratory Vehicle Segment 11.42, - 

.), s,C Gemini B Segment or 4,(1.1 

Support Module Q. 

Mission Payload Segment * -4,330- - 

Crew Equipment Segment.s1,,t,o.---fal il 

Flight Crew Segment 360 

26,425 

Weight allocations shall be in accordance with the requirements of 

MIL-M- 38310. 

3. 3. 1. 1. 1. 2 Center of Mass • 

The OV center of mass shall remain within a cylinder 

whose centerline is coincident with the geometric centerline of the OV. 

The radius of the cylinder shall not exceed_ inches at launch and inches 

at any time during the flight. 

3. 3. 1. 1. 1. 3 Principal Axis Alignment 

The angular deviation of the OV principal axis of inertia 

about the center of mass and the OV Body Axis (Reference 3. 3. 2. 2. 7. 3) 

shall not exceed 1. 0. degree. 

Electrical Power 

Orbiting VehicleX4) 

The Laboratory Vehicle centeral power system shall provide 

the total Orbiting Vehicle power requirement during launch and injection 

and while on orbit prior to Gemini B separation. The power demand over 

the entire 30 days is a nominal 2. 0 kw with nominal peaks of 3. 6 kw. 

Co 

3. 3. 1. 1. 2 

3. 3. 1. 1. 2. 1 

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Peak power requirements which exceed the power supply capability 

shall be individually accommodated. 

3.3.1.1.2.2 Gemini B (U) 

Electrical power allocation to the Gemini B shall be a nominal 150 watts , 

40-r—normal-on--atibit-staraggt Nominal power levels of 480 watts for 

the launch and injection phase, 440 watts for the pre-orbital storage 

phase, and 570 watts for the pre-separation phase shall be provided 

from the Laboratory central power system. 

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 ( 4) 

The Laboratory Laboratory shall be allocated a nominal 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 Mission Payload \-4) 

A nominal watts will be available for the combined Mission Payload Segment. 

3. 3. 1. 1. 3 Leak Rate \-4) 

The over-all leak rate for the Orbiting Vehicle shall be based on the 

leak rate for the Gemini B and transfer tunnel (see paragraph 3. 3. 3.1..5), 

plus a leak rate of i. 5 lb/day for the degraded single gas mode (5 psia, 

100 percent oxygen) for the Laboratory Vehicle. Leak rate for the 

normal dual gas mode for the Laboratory Vehicle shall be ratioed from 

the single gas mode value according to pertinent parameters of the 

atmospheric composition selected. 

3. 3. 1. 1. 4 Effectiveness 

The Orbiting Vehicle System Segment combines a number of other 

segments, therefore values are assigned under the other segments. 

Crew safety probability for the 30-day orbital mission, including the 

time from insertion on-orbit to separation of the Gemini B, shall 'be 

at least 0.999. 

3-46 

FThis document contains information affecting the notional defense of the United Stares within the meaning of the Espionage tows, SSD AUTT2 20B 1..1. to. U.S.C.. Section 793 and 791. the transmission of which in any manner to an unauthorized person is prohibited by law. 

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3. 3. 1. 2 Peculiar Performance and Design Requirements 

The following requirements are common to all flight configurationti. 

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

3.3. 1. 2. 1. 1 General (U) 

The Communication and Control Systems located in the segments 

shall be capable of independent operation. Electromagnetic compatibility shall be demonstrated when systems located in the different 

segments are activated simultaneously. 

3. 3. 1. 2. 1. 2 • Command System (U) 

Isolation shall be provided between the Gemini B Command System. 

and the Laboratory Command System to prevent inadvertent activation 

or interference with either Command System. 

3. 3. 1. 2. 1. 3 Data Transmission System (U) 

Sufficient isolation shall be provided between the OV and Titan III and 

between the various portions of the OV to prevent interferenCe between those systems when operating simultaneously. 

3. 3. 1. 2. 2 Attitude Control Translation System (ACTS) 

3. 3. 1. 2. 2. 1 Operational Mode-§-(U) 

The on-orbit attitude control shall be provided by the Laboratory. 

3. 3. 1. 2. 2. 2 Orientation (U) 

Capability to attain any attitude and the maintenance of this attitude in 

_ an inertial 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 Maneuverability (U) 

Maneuvers shall be accomplished with the Laboratory ACTS. 

3 -47' 

This document contains information affecting the national defense of the United Sates within the meaning of the Espionage Lows, 

Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by los. 
NRO APPROVED FOR 

FgELEASE 1 JULY 2015 

3. 3. 1.2. 3 Navigation N\-4) 

Navigation data for the Orbiting Vehicle shall be derived by the SCF 

from ground tracking of the spacecraft. The SCF capability for 

orbit determination and orbit prediction shall be used to derive orbit 

parameters and/or time/position tables for execution of planned operations and/or data tagging. 

3. 3. 1. 2. 4 Computation and Data Processing 

Computation capability shall be provided within the Orbiting Vehicle 

as required to support Mission Payload operations and the Laboratory 

Vehicle. Computer system hardware and software requirements shall 

be defined by the Laboratory Vehicle and Mission Payload Integration 

contractors. Compatibility with a ground software system is required. 

.r. 

3. 3.1. 2. 5 Structural Design Requirements 

3.3.1.2.5.1 General (U) 

Sufficient strength and rigidity shall be provided to meet the maximum 

loading and/or environmental conditions within the envelope of mission requirements. The Laboratory Vehicle and . the mission 

module shall be compatible in terms of load transmission capability 

and mating at the interface with the Gemini B, with the Titan III, and 

the Mission Payload. 

3. 3..1 . 2. 5. 2 Separation (U) 

The capability shall be provided for separation on orbit between the 

Gemini B Segment and Laboratory System Segment, and between the 

Orbiting Vehicle and Titan III. 

3. 3. 1. 2. 5. 3 Thermostructural (U) 

During normal orbital operations (including solar angle variations, 

within the limits of -60 deg and +60 deg), axial deformation of the 

mission module structure due to thermal gradients (measured with 

reference to a set of axes defined by the mission module/laboratory 

module mating plane and the mission module center line perpendicular 

to that plane), shall not exceed a maximum of (to be supplied). 

3-48 --CONRIENTIAL, 

FORM This document contains information affecting the nof.000l tDAVISe of he United States within the meaning of the Espionage Laws, 

SSD AUG 62 20B Title 18, U.S.C., Section 793 and 794. the transmission of which in on manner to ln unauthorized person is prohibited by low. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 

3. 3. 1. 2. 5. 4 Aeroelasticity (U) 

Flutter or other related dynamic instability shall be prevented on the 

Orbiting Vehicle system. 

3. 3. 1. 2. 6 Flight Crew Transfer 

3. 3. 1. 2. 6. 1 Normal Mode (U) 

The Gemini B crew transfer hatches will remain open and the Laboratory crew transfer hatch closed while both crew members are in the 

Laboratory. These hatches shall be operable while the crew are in 

pressurized suits. 

3. 3. 1. 2. 6. 2 Backup and Emergency Modes (U) 

Provision shall be made for back-up extravehicular egress/ingress and 

transfer of flight crew members between the Gemini B and the Laboratory Vehicle. Extravehicular egress/ingress to Gemini B shall be via 

the regular Gemini B egress hatches and to the Laboratory through the 

extravehicular hatches. Extravehicular transfer capability shall be 

provided from all. Laboratory Vehicle pressurized compartments to 

permit extravehicular transfer to Gemini B. The Gemini B egress 

hatches shall be closed after transfer of the last crewman to the 

Laboratory. Provisions shall be made for opening and closing the 

Gemini B and Laboratory egress hatches from either inside or outside 

while in a pressurized suit. 

Emergency crew transfer from the Laboratory to the Gemini B shall 

include transfer through the internal tunnel in shirtsleeves (i. e. , without wearing the MOL basic pressure suit) or in the MOL pressure suit 

assembly without umbilical attached. 

3. 3. 1.2. 6. 3 Number of Transfers (U) 

Laboratory expendable capability shall be provided sufficient to permit 

two return trips to the Gemini B during the mission in addition to the 

final transfer. Return to the Gemini B shall be upon completion of the 

mission or under emergency conditions and not as a planned activity. 

3-49 
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3.3.1.2.6.4 Ground Communications Coverage 

Deleted. 

3.3.1.2, 7 Orbital Operations 

3. 3.1.2:7.1 On-Orbit Monitoring and Checkout (-4) 

Both ground telemetry data and in-flight monitoring panels shall be 

utilized for on-orbit monitoring and checkout. The parameters requiring checkout, the frequency of performing monitoring functions, and 

the locations of monitoring functions shall be specified for each Orbiting 

Vehicle subsystem. Orbiting Vehicle checkout shall be performed 

during the first few orbits and prior to activation or initiation of any 

new phase of the mission to establish performance parameters for each 

subsystem. Visual and/or audible signals shall be used to indicate 

existence of or impending malfunctions on selected items. Provisions 

shall be made for indication of subsystem or appropriate module level 

for malfunction detection. 

3. 3. 1. 2. 7. 2 On-Orbit Maintenance !;•<1) 

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 inflight capabilities, it shall be incorporated into the design. Maintenance shall normally be limited to the interior of the Laboratory. 

3. 3. 1. 2. 7. 3 . On-Orbit Extravehicular Capability (U) 

The OV shall be provided with the capability to support extravehicular 

operations, consisting of Emergency Extravehicular Transfer (as 

defined in paragraph 3. 3. 1. 2. 6. 2) and the requirement to umbilically 

support an inspection of any part of the OV exterior. Equipment to be 

utilized in such operation shall be as defined in paragraph 3. 3. 5. 1. 4. 

Duration of extravehicular operation shall be 2 hours nominal, 4 hours 

maximum. 

3-50 CONFIBENTIAL 

This document contains information affecting the notional defense of the United States within the meaning of the Espionage Laws. 

Title .111, U.S.C.. Section 793 and 794; the transmission of which in any manner to on unauthorised person es prohibited by law 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3-.1.1.2.7.4 • Automatic Operation 

Provisions shall be made in the orbiting vehicle to 

accomplish on-orbit operations in the automatic mode for up to 30 days. 

Automatic mode operation requires completely automated control of 

the vehicle„ Finduding malfunction detection and redundant component 

switching. On-board and/or on-ground support may be utilized for 

fault isolation and corrective action. In the manned version all automated subsystems shall provide for manual override or inhibit by the 

crew. 

3.3.1.2.8 Aerospace Ground Equipment (AGE) -4) 

The OV AGE shall include all the Gemini B, Laboratory Vehicle, 

and Mission Payload AGE 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 III Launch Vehicle. Thus AGE shall provide means of (1) verifying the proper operation of the OV system during 

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

assembled system is operable within the prescribed limits of each segment, (3) assuring that all interfaces (electrical, mechanical, and 

human) between'OV segments or with external surfaces are proper, and 

(4) identifying to the segment (or in critical systems, the subsegment) 

level areas of failure or operation outside of prescribed operating limits. 

The OV AGE shall be designed to support manned, unmanned, and the combined 

modes of operation. 

The. OV AGE shall be designed for compatibility with the Titan IIII/AGg, 

and the ILC facilities. The OV AGE at the ILC shall provide capability 

for checkout and for launch 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 VAFB. The OV AGE shall be designed for ease of maintainability and 

interchangeability and shall have features which will facilitate fault isolation 

and detection. All OV AGE shall be acceptance tested prior to being utilized 

for OV AGE ground operations. 

3.3.1. 2.9 Mission Simulator(s) (U) 

Mission simulators shall be provided to accomplish training in 

accordance with Paragraph 3.3.12.2: 1. 2.43. 

)4 • 

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3. 3.1. 3 Functional Interfaces (U) 

(Functional interfaces shall be listed here when defined by the cogni-. 

zant Interface Control Working Group-ICWG. ) 

3. 3. 1. 4 Contract End Items (U) 

(The contractor shall provide for incorporation in this paragraph a list 

of the Contract End Items by CEI specification number, nomenclature, 

and the CEI into which it installs. This paragraph shall list all end 

items being provided under these system segments. ) 

3-52 
rr NRTSPEZAt filiALING SLUM' 

3. 3. 1. 5 Mission Peculiar Requirements , Orbiting Vehicle 

3. 3. 1. 5. 1 Orbiting Vehicle Vibration Limitations 

During on-orbit mission payload operations,, the amplitude of 

vibration at station 500 shall not exceed 3.9 x 10-5 inches (vector sum 

of the lateral components) from 5 cps to 150 cps due to any orbiting vehicle 

equipment that can not be shut down for at least 20 minutes. 

3. 3. 1. 5. 2 Minimum Time Between Targets 

The time in seconds between adjacent targets achievable 

by the system shall be no greater than d e + 3 or 4 95 + 3 seconds, 

-6-- 

whichever is larger, where and4are the stereo and obliquity angle changes, 

respectively, in degrees commanded between targets. 

Manned Version 

The actual time between targets is increased over the 

above by the time required for the astronauts to null the tracking error and 

rate error. It shall be a design objective of the system to minimize the time 

required for the astronauts to acquire targets and reduce the rate error to 

acceptable levels. 

3. 3.1. 5. 3 Photographic Data Return 

3. 3.1. 5. 3.1 Data Re-entry Vehicles (DRrs) 

Sequentially following completion of one of the assigned 

blocks of photographic payload operations sufficient for one DRY, the specific 

DRV will be ejected from the Orbiting Vehicle and deboosted from orbit into the 

designated recovery area using its own deboost propulsion capability. Retrieval 

Of the DRV will be by air recovery as the primary method, with water recovery 

as backup. 

SPECIAL HANDLING 

3-52.1 
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RELEASE 1 JULY 2015 -sENTSPECIAL HANDLING 

Manned - Automatic Configuration 

Depending upon the design selected, the DRY film will be 

loaded automatically, or as a package by the astronauts. The capability 

shall exist to return 60 lbs. record in one to three DRY's. 

Automatic Configuration 

At least four DRV's will be provided. Each DRY will have a 

capability of returning 60 lbs. of record. The DRY', will be supported in 

a Support Module replacing the Gemini B system segment. 

3.3.1.5.3.2 Data Readout Subsystem (Manned - Flights Only) 

A capability shall exist to process selected photographic 

frames and transmit all or selected parts of the scene from the original 

negative to the ground over a wideband data link. The length of time required 

to transmit the scene from a 5 square-inch segment of the negative shall not 

exceed five minutes. It shall be a design objective not to lose more than 

20 percent of the resolution of the original negative in the processing, 

scanning transmission, and ground data recording process. 

3.3.1.5.3.3 Data Return Via Gemini B Manned Version Only 

The Gemini B System Segment will have the capability to 

return of the photographic record obtainable on the 30-day 

mission. 

3.3.1.5.4 Command and Control 

Manned - Automatic Configuration 

The cOMmand and control will be provided by an integrated 

system of astronaut, vehicle hardware, software, and ground support system. 

The capabilities of each contributor shall be used to maximize the number of 

targets photographed at high resolution. 

MMELSPECIAL HANDLING 3-52.2 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

Automatic Configuration 

The Command and Control will be provided by an integrated 

system of vehicle hardware, software and ground support system. The capabilities of each contributer shall be used to maximize the number of targets 

photographed at high resolution. 

3.3.1.5.4.1. Vehicle Hardware and Software Requirements 

The major vehicle hardware and software requirements for 

command and control consist of: 

a. Target and Orbit Data Processing 

b. Provision of Astronaut Controls and Displays (Manned 

Flights only) 

c. Cueing System Control (Manned Flights only) 

d. Acquisition Scope Control (Manned Flights only) 

e. Tracking Mirror Control 

f. Camera Control 

g. Instrumentation Control 

h. Communications Control 

i. Data Readout Control (Manned flights only) 

j. Target Photographic Qgality Information Processing 

Detailed requirements for the above command and control 

functions are given in Section 3.5.3.4 

3.3.1.5.5 Target Acquisition 

The target acquisition system (exclusive of the astronaut) shall 

be capable., with 95 percent probability, of automatically acquiring the 

target and holding the aiming error to less than 0.2° throughout the range 

of + 30° in track and + 40° cross track. Further, the system shall be 

capable of correcting the aiming error to 0.1° within two seconds under 

control of an astronaut. 

IMETSPECIAL HANDLING 3_52.3 
WEECULAANDLING 

3. 3. 1. 5. 6 Malfunction and Post-Gemini Separation Operations 

(Manned Rlightis only) 

To permit obtaining maximum useful performance data 

on the Dorian System under flight conditions, the Orbiting Vehicle shall be 

designed so that operation of the Dorian System hardware shall be possible: 

a. Even if the astronauts cannot enter the Laboratory 

Vehicle for safety or other reasons. 

b. Following separation of the Gemini vehicle. 

It is not intended that major design perturbations be required. 

to implement this requirement, nor that all Dorian systems be operable. For 

example, the above shall not require that unmanned operational capability 

be provided for hardware for which only manual operation by the astronauts 

is feasible. Return of useful photographic data shall not be a requirement 

under conditions a. and b. above. 

3.3.1.5.7 Miss ion Payload Ground Handling 

The mission module temperature, humidity, and dust 

control requirements, together with the necessity to maintain precise alignments within the orbiting vehicle must be considered in designing the ground 

handling equipment for use at the launch base. 

SPECK VtiVIDLING 
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3.3.2 Laboratory Vehicle System Segment Sk) 

The Laboratory Vehicle shall be approximately 10 feet 

in diameter and 20.5 feet long divided into :two sections, one pressurized 

and one unpressurized. The pressurized section will consist of two com- 

, partments to enclose and support the operation of environmental control, 

life support, attitude control, power generation, communications, vehicle 

status monitoring, and mission equipments. The pressuriZed section 

shall proVide'bOusing for service items and a crew transfer tunnel. 

3.3.2.1 Allocated Performance and Design Requirements 

Volume 

3.3.2.1.1.1 Pressurized \-4) 

The Laboratory Module shall provide a pressurized volume of 

approximately 1000 cu ft, divided between two compartments. The baseline 

design of the manned version of the Laboratory Module 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's effectiveness in the 

Laboratory Mbdule. 

3.3.2.1.1.2 Uhpressurized X-4) 

The Laboratory Module shall provide a usable unpressurized, 

volume of approximately 500 cu ft. 

3.3.2.1.2 Internal Arrangement N-4) 

The equipment arrangement in the pressurized section shall 

provide for maximum free volume for crew mobility. Provisions for flight 

crew personal requirements shall be integrated into a specific area of the 

pressurized 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 vehicle operational and main- , 

tenance tasks by the flight crew. Maintainability objectives shall'be adhered 

to in defining internal arrangement and equipment packaging. Prior to launch, 

isolation of faulty equipment at the black box level shall not require disassembly 

of laboratory pressure bulkheads for removal and replacement. Equipment 

packaging shall be compatible with ac(!omplishing the above corrective action 

through available hatc es.. 

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Location of the display and control subsystem consoles shall 

be compatible with the reach envelope and visual capabilities of .the crew. 

Means shall be provided to stabilize the crew's position to permit activation 

of controls under zero-g, permitting a fixed frame of reference. The layout 

shall be arranged such that, where necessary, a pressure-suited operation 

may be accomplished. 

The display and control subsystem shall provide necessary 

controls and displays to accomplish vehicle management functions, specific 

missions, and information management. The controls and displays shall be, 

integrated to the extent possible and multipurpose displays provided where 

effective. .ThiS subsystem shall be capable of varying flight requirements 

with. respect to mission accommodation. • 

Aft Pressurized.CompartmentN4) 

The equipment in the aft pressurized compartment (launch 

orientation) shall be arranged circumferentially on the vehicle inner wall 

to accommodate a "head-up" crew position in pre-launch and launch attitude. 

The arrangement shall afford maximum free volume for crew mobility and shall 

provide mutually independent but functionally integrated areas for vehicle 

operations, mission operations, technology operations, information management,': 

and food-exercise-hygiene center. The over-all internal arrangement shall 

provide for convenient and simple management of the vehicle by the flight 

crew'. 

3.3.2.1.2.2 Forward Pressurized Compartment T'ScY) 

The equipment.in the forward pressurized compartment shall be 

installed in console 'areas arranged to permit maximum freedom of movement by . 

the crew to and from Gemini B and the aft pressurized compartment. The compartment shall provide for extravehicular activity equipment, data re-entry 

. vehicle storage, maintenance and repair functions, permit two crewmen to 

simultaneously don pressure suits, and accommodate sleeping and recreation 

facilities. 

3.3.2.1.3 Flight Crew Stay Timelits4) 

The Laboratory Vehicle shall -2rovide for a nominal on-orbit 

stay time for a two-man flight crew of at least 30 days, plus a 10 percent 

reserve. 

3 
3.3.2.2 

3. 3. 2. 2. 1 

3. 3. 2. 2. 2 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 2. 1. 4 Effectiveness (U) 

Effectiveness requirements for the Laboratory Vehicle 

system segment are specified in paragraph 3. 1. 3. 1. 2. 2. 

Peculiar Performance and Design Requirements 

On-Orbit Maintenance (Deleted) 

On-Orbit Technical Data Z11/4-4) 

Technical data on each of the Orbiting Vehicle segments and 

their subsystems, as required by the flight crew in the performance of 

their operational functions, shall be provided in a convenient and easily 

accessible form and location. 

3.3.2.2.3 Data Re-entry Vehicle ISO) 

The Laboratory shall be capablecf incorporating the necessary 

equipment for recoverable data capsules aboard any designated flight. 

The capability shall permit: access for playing data into the capsules in 

an environmentally controlled atmosphere; means for adjusting and measuring 

any environmentally controlled atmosphere; means for adjusting and 

measuring any required ballast; means for deploying the DRV without 

adverse effects on the OV; and means for controlling the attitude and 

time of release. 

3. 3. 2. 2. 4 Outgassing, and Impingement 

The Laboratory shall be designed so that no effluents shall 

impinge deleteriously on the Orbiting Vehicle. Positive control will be 

exercised to minimize contaminant introduction into the Laboratory Vehicle 

atmosphere. 

• 

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• 

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3.3.2.2.5 Communications and Data Processing Requirements 

3.3.2.2.5.1. Communications 

'3• 3• 2.2• 5• l• General 

Laboratory Communications shall be compatible with the Flight Operations 

and Support System Segment and shall make primary use of the USAF Space 

Ground Link Subsystem (SGLS). Secondary systems include UHF voice, 375 

mc/s commanding, and a back-up telemeter. An S-band transmitter shall 

provide wideband data transmission. The Laboratory communications equipment shall be extendable directly, or by modular add-on, to at least the 

maximum performance limits of the SCF ground configuration specified herein. 

3.3.2. 2. 5. i. 2- Integrated Tracking, Telemetry, Command, 

and Voice (TTCV) Transponder 

The La1?oratory shall contain a transponder consisting of a receiver and trans.:. 

mitter which combines TTCV functions over single up and down radio links. 

Performance specification for the integrated functions are given in subsequent 

paragraphs of this section. 

The receiving portion of the transponder shall be activated either by the onboard computer stored program, or manually. The transmitter shall be capable 

of being energized by the command link, by use of a stored program, or by , 

manual switching. 

3.3.2.2.5.1.2.1 Tracking 

The SGLS-compatible phase coherent transponder shall provide, when used with 

an SCF SGLS ground station, on-orbit vehicle metric tracking data having lr 

accuracies as follows: 

Range 50 ft 

Range Rate 0.2 ft/sec 

Angles, Az & El 2 milliradian 

3. 3.2.2.5.1.2.2 PCM Telemetry Transmission 

The transponder shall be capable of transmitting separately or simultaneously, 

two digital data serial bit streams as provided by the PCM telemetry or data 

recorders. One digital data input shall have a data rate in the range of 4-128. . 

kilobits/second and the other ranging from 4-1024 kilobits/second. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• • is is 

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subcarrier which can accommodate IRIG FM/FM, PAM/FM, or other analog' 

data having a double-sided modulation bandwidth of 500 kilocycles/second or 

less. 

3.3.2.2.5.1.2.4 Voice 

The TTCV transponder shall provide primary Laboratory-ground duplex .voice 

link capability. The two-way channel shall accommodate nominal 3 kilocycle' 

bandwidth voice or 2400 kilobit/second digital voice at crew option. 

3.3.2.2.5-1 LS 375 Command Receiver 

Ari SCF compatible 375 me command receiver shall be provided as a back-up 

to SGLS 1 kilobit/second commanding. 

3.3.2.2. S. 1.4- Back-Up Telemetry Transmitter 

A back-up PCM telemetry transmitter shall be provided to enhance ground 

PCM telemetry support availability. Compatibility with an existing or a firmly 

planned SCF receiving system is an important selection criteria. 

3.3.2.2.5-. 1.5 Wideband Data Transmitter 

A wideband data transmitter shall be provided capable of transmitting digital 

data at rates as high as 20 megabit/second. The transmitter shall operate in 

the 2200-2300 Mc RF band. Modulation, specific frequencies, frequency 

stability, and other technical characteristics shall be compatible with the 

SCF S-band wideband data link. 

3.3.2.2.5.1.i UHF Voice Transceiver 

A Gemini-type simplex UHF voice Transceiver shall provide back-up to the 

SGLS voice link and shall provide contact capability with non-SGLS ground site's. 

3.3.2.2.5.1.7 Voice Control and Intercommunications 

A voice control center and remote control panels shall provide intercommunications functions and control for each set of voice receiving and transmitting 

equipment. It shall be possible for both crewmen to have simultaneous voice 

communications with the ground. Aural alarms of the monitor/alarm subsysteiii 

shall be broadcast via the intercom. . 

3.3.2.2.5. 8- Vo coder 

A vocoder shall provide voice transmission and reception via the TTCV transponder at the digital data rate of 2400 bits/.second. The vocoder shall be 

3.3.2.2.5.1.2.3 Analog Telemetry 

The SGLS compatible transmitter shall include, as a pre-flight option, a 

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3. 3. 2. 2., 5.•1•9 Communication Security_ 

Communication security shall be provided as an in-flight option for voice, 

PCM telemetry, commands and wideband data transmission. The security 

devices shall be GFE. 

3.3• 2.2• 5• 1• 10 Antennas and RF 

The antenna and RF subsystem shall consist of the TTCV transponder, wideband data (S-band), UHF voice and command, and secondary PCM telemetry 

antennas (as required) and their associated transmission lines, power dividers; 

RF multiplexers, and RF switches for antenna selection and AGE use.. The 

TTCV and UHF antenna system shall provide, at crew option, spherical or 

directive radiation coverage. The wideband data antenna shall provide earth 

coverage when the spacecraft is orbiting in its nominal attitude. The TTCV 

. transponder antenna system shall be capable of use during launch. 

3.3.2.2.-5.2 

3.3'.2.2.5.2.1 

Data Management 

Command 

The command subsystem accepts input signals in the SCF trinary format at a 

.1 kilobit/second transmission rate. Primary command validity checking and 

decoding functions and stored program functions shall bel,provided by the vehicle 

computer. A decoder shall provide real-time command back-up to the cornputer. Sizing of the decoder shall be based upon manned operation of the 

Orbiting Vehicle, less computer dependent experiment(s) for 30 days without 

the availability of a computer. 

3.3.2.2.5.2.1.1 Decoder 

• The decoder shall perform validity checks and logic operations and generate 

command outputs to controller switching/relay circuitry. Indication of command message validity checks shall be provided as an output available for 

telen-ietering to the ground. The decoder design shall provide for expansion by 

modular add-On. Power to the command decoder shall be controlled by internal 

logic, by a vehicle stored program, or manually. No false command execution 

outputs shall result from over-or-under voltage, turn ON or OFF, or other 

transient power conditions. 

3• 3.2.2.5. 2. 1.2 Command Controller 

The controller provides switching functions for various vehicle equipments. 

Solid state type switching of both latching and non-latching types shall be emr ' I• .4" 4,41'&8114 

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played as required. The controller circuitry shall incorporate manual reset 

and over-ride features. Signal pick-offs shall be provided for channel actuation 

verification and/or status indication to be transmitted to the ground via the 

vehicle status telemetry. The controller shall accommodate a minimum of 256 

channels and provide for expansion by modular add-on to 512 channels. 

3.3.2.2.5.2.1.3 Teleprinter 

The teleprinter shall provide hard-copy text of operational instructions, quantitative data for crew use, procedures and other similar comprehensive data 

transmitted via the command data link vehicle/mission module computer, 

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

3. 3. 2. 2. 5. 2. 2. 1 PCM Telemetry 

The PCM telemeter shall accept a variable mix of analog, digital and discrete 

data inputs, provide main data frame multiplexing, provide A-to-D conversion 

as required, generate appropriate timing signals for internal and external use, 

generate synchronization words, and combine data and sync into a serial, 

digital bit stream. These data shall then be provided as an input to the TTCV 

transmitter for real time data transmission or to a recorder for delayed data 

transmission. The real time data digital multiplexing shall be continuous 

during ascent and during station contacts on-orbit at a rate of 128 kilobit/sec 

or lower. The PCM telemetry shall accept primary mission module data from mission 

. • . 

module submultiplexers.. Telemetry timeline analyses shall provide for transmission 

availability of mission module data on each SCF station pass. Laboratory and 

mission module status and housekeeping data shall be multiplexed into a seria:. - 

bit stream Vial eh,-shall 'be tiine trans'-. - r i ';•111 - 

mitted each station pass (nominal) or recorded continuously or intermittently at 

crew option. Crew and other test data shall be intermittently multiplexed and recorded at rates up to 128 kb/sec for variable durations. Playback and telemetry 

dump of the recorded data shall use either the primary or secondary SGLS 

carrier at compatible transmission rates up to 1024 kilobit/sec. 

The PCM telemetry system shall accommodate greater than 1000 vehicle status 

measurements for a given mission. Sampling rates shall extend from 1 sample 

per 10 seconds to at least 512 samples per second. High• level (0-5,11olts) and 

low-level (0-20 millivorts) remote multiplexers shall be used where appropriate 
• I 

3.3.2.2.5.2.2.2 Analog Telemetry 

\ IRIG subcarrier oscillators, frequency multiplexers, etc., shall be provided 

as required to accommodate wideband instrumentation sensors such as vibra.! 

tion pick-ups required for Orbital Vehicle. structure test. 

3.3.2.2.5.2.2.1 Format Selection • 

The PCM main multiplexer design shall provide in-flight selection of any one 

of several pre-flight prepared digital telemetry formats and data rates. 

.3. 3. 2. 2. 5. 2. 2.4 Recorders 

Magnetic tape recorders shall be provided as follows: 

(a) Voice - Intermittent analog voice recording with 

total capability in excess of four hours. Two 

playback speeds shall be provided: one at the 

1:1 rate and the other at a fast rate consistent 

with transmission using the TTCV transponder, 

r. 

500 kilocycle, analog telemetry channel. The 

recorder shall provide for both manual and 

voice recording control, shall record signals for 

the time correlation, and shall contain fast data 

search and retrieval features. 

(b) Telemetry Recorder(s) - Continuous or intermittent recording of vehicle status data for a 

total single-channel recording period of three 

hours minimum; provides storage of mission 

module data; records crew and other test data; 

stores keyboard encoded operational messages. 

The nominal playback 

rate for stored telemetry is 128 kilobit/sec. 

Performance features to be considered shall include digital and analog record and reproduce, 

multiple recording channels, multiple tape 

speed, bi-directional record and reproduce, and 

provision for rapid search and retrieval. 

All recorders shall allow in-flight tape change; magnetic heads and other 

critical components shall be capable of being removed, serviced, and reinstalled 

or replaced. 

3.3.2.2.5.2.3 Timing 

The timing subsystem shall provide time signal generation for data handling 

equipment, synchronization and control, time correlation of data, two channel 

event timing, time words for computer use, and time displays. Clock synchronization shall be manually selectable from either an internal signal source or externally. 

The internal clock shall have a time reference stability of 10-7 per 30 days or better. 

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Initialization or up-date of the timing logic shall be accomplished via command 

(primary) or manually. Displays shall include Greenwich Mean Time (GMT), 

vehicle ela,psed time (VET), vehicle ground time difference (•&T), cOMpiiter 

• ,synchronization indication, two event elapsed time (EET) channels, 

and a mechanical clock. 

3. 3. 2. 2. 5. 2. 4 Data Computation 

3.3.2.2.5.2.4.1 Computer Hardware 

The computer subsystem shall consist of two identical computers, together with 

the peripheral units described below, and shall be capable of performing all onboard computations and data-handling functions not implemented by other sub= ' 

systems. It shall also provide the capability for performing command functions 

required to be initiated manually by the flight crew through the computer control unite-through the command link, or automatically through signals initiated 

by the monitor/alarm subsystem. The computer subsystem shall have the 

capability for executing all functions essential to Mission Module and Laboratory 

operation while utilizing only one of the computers and its associated peripheral 

units. 

3.3.2.2.5.2.4.2 Computer Subsystem Control Unit 

The computer subsystem control unit shall provide the capability for automatic ' 

control of the computer and data adapter units, either through the command link 

or upon a signal from the operating computer.. The control unit shall provide 

for manual override or control when the OV is manned. 

3. 3. 2. 2. 5. 2. 4. 3 Data Adapter Units 

The data adapter units shall provide all necessary signal conditioning, synchronizing, and buffering required between the computer and other orbiting vehicle subsystems. Separate adapter units'shall be provided for interfacing the computers 

with the laboratory subsystems and with the manual and automatic equipment 

within the mission module. Redundancy shall be provided for the two types of data 

adapter units, and each unit shall be capable of interfacing with either computer. 

3. 3. 2. 2. 5. 2. 4. 4 Display and Control 

The display and control unit provided with each computer subsystem shall provide

. 

all necessary capability for entering or requesting data from the. computer, and 

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shall provide all necessary capability for flight crew control of the computer 

subsystem. The computer display panel shall consist of all indicators and '- 

lights necessary for non-textual communications between the computer and 

the flight crew. 

3.3.2.2.5.2.4.5 External Storage 

External storage shall be provided to allow read-only storage of all computer 

programs required during the mission. The storage unit shall be addressable 

by either computer for access to stored programs. 

3. 3. 2. 2. 5. 2. 4. 6 Software 

Software provided for the vehicle-borne computer system shall be consistent 

with the need for optimizing storage and execution time requirements for those 

programs which are substantially unchanged from flight to flight, and with the 

need for facilitating changes in those programs which may change from flight 

to flight. Software 'languages shall be compatible with the types of functions 

for which they will be utilized, so that programming of vehicle-borne functions 

may be efficiently implemented. 

3. 3. 2. 2. 5. 3 Instrumentation and Display 

3. 3. 2. 2. 5. 3. 1 'Sensors 

Instrumentation sensors and accompanying excitation sources, etc., shall be 

provided for all Laboratory subsystems as required for vehicle displays, 

telemetry, and the monitor/alarm. 

3. 3. 2. 2. 5. 3. 2 Signal Conditioning_ 

Conditioning of signals shall be provided for all Laboratory Vehicle subsystems 

as required for interface with PCM telemetry, vehicle displays, and the vehicle 

monitor and alarm subsystem. Provision shall be made for in-flight change of 

signal conditioner and remote multiplexer•channels, adjustment of levels and 

calibration., 

3. 3. 2. 2. 5. 3. 3 Displays and Controls 

Provision shall be made for selection and operation of normal control and ba'.ok.- 

up modes as applicable for all vehicle subsystems. Displays shall, include 

vehiCle subsystem status and mode displays, those displays directly associated 

with subsystem control and operation, and certain critical parameter displays. 

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3.3.2.2.5.3.4 Monitor/Alarm 

The vehicle monitor and alarm subsystem shall be 

capable of continuously monitoring or sampling approximately 150 

critical vehicle subsystem 'parameters concerned with crew safety and 

with functions whose failure would jeopardize the mission. Points 

monitored shall be predicated on a maximum space-ground contact gap 

of 6 hours. Off-nominal performance which can persist for more than 

6 hours shall be diagnosed 'on the ground. Sampling rates range from 

approximately one sample per second and one sample per 10 seconds, as required. 

Both aural and visual signalling shall be provided for out-of-tolerance 

conditions. Approximately 25% of the function/measurement tolerances 

and points monitored shall be programmable while in flight. Immediate 

or rapid crew action is required when certain (approx. 50) of the total 

points are out of tolerance. Manual override and reset features shall be 

incorporated. Design shall provide for modular expansion. Monitor/ 

Alarm outputs shall be interconnected to the vehicle computer and directly 

to the controller(s) to provide automatic control of vehicle subsystems. 

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

3.3.2.2.6.1 Scope (U) 

The Environmental Cont rol and Life Support (EC/ZS) 

subsystem shall consist of the following functional areas: 

(a) Atmosphere Control 

(b) Thermal Control 

(c) Food Management 

(D) Water Management 

(e) Wast Management 

(f) Personal Hygiene 

The specific requirements for each of the above functiona 

areas are given below, together with the over-all requirements for the 

complete subsystem. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 3, 3. 2. 2, 6. 2 Atmosphere Control 

3. 3. 2. 2. 6. 2. 1 General (U) 

Atmosphere control for the Laboratory shall maintain and control the 

pressure, composition, and temperature of the atmosphere for the 

pressurized section. Provision shall be made for both shirtsleeve 

operation (normal activity) and pressure suit operation (special and 

emergency activity). Means shall be provided to support extravehicular activities, as defined in paragraph 3. 3.5.1. 4 and 

3.3.1.2.7.3. 

3. 3. 2. 2. 6.2. 2 Atmosphere Pressure and Composition 11S\-4) 

The atmosphere control provisions shall afford the inherent capability 

,rio operate in a normal dual-gas mode, with provisions for automatic 

degradation to a single-gas mode (5 psia - 100 percent oxygen). 

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 of alveolar oxygen pressure shall not be less than 100 mm Hg. 

3. 3. 2. 2. 6. 2. 3 Pressure Control (U) 

Provisions shall be made for both automatic and manual control of 

the atmospheric 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 (U) 

A pressure regulation system shall control the total pressure for the 

single-gas mode. For pressure suit operation, devices shall be 

employed to automatically assure a level that provides for the specified normal alveolar oxygen pressure.. 

CONFIIIENTIV 

IhtS document contains onformation affecting the notional defense 01 the ()mind States wortsm the meontno of the Espionage 

1.111 )8. U.S C Section 793 and 794. the tronsmossion of 'Much in any money to an ortouthotteed person rs otobtb.ted by low 

3-63 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.3.2.2.6.2.3.2 Dual-Gas Pressure Control (U) 

An oxygen partial-pressure sensor shall be used to maintain 

atmospheric 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. 

3.3.2.2.6.2.4 Shirtsleeve EnvironmentN, 

An environment shall be provided that will result in physioaogical responses within ranges compatible with human comfort as defined 

for. equivalent terrestial conditions and levels of metabolic activity. Due 

consideration shall be accorded to the effects of reduced atmospheric pressure, 

different atmoshperic composition, and elimination of natural convections. 

An optimum balance of atmoshperic temperature, ventilation velocity; water 

vapor, partial-pressure, and mean radiant temperature shall be established and 

maintained. Relative humidity shall be maintained at less than 60 percent. • ' 

Provisions for the control of shirtsleeve environment, based on nominal metabolic loadings (in the region of 400 to 800 BTU/hr) shall not require the 

utilization of active thermal cooling garment:;. 

3.3.2.2.6.2,5 Atmosphere Storage Requirements :(N-4) 

Atmosphere storage shall be based on the following requirements: 

(1) Oxygen to provide for crew metabolic require 

ments during occupancy of the Laboratory 

pressurized compartments, and for Gemini B 

reactivation as specified in paragraph 

3.3.1.2.6.3. 

(2) Oxygen to provide for the repressurization and 

leakage make-up for the Gemini B and transfer tunnel as specified in paragraph 3.3.3.1.5. 

(3) Oxygen and diluent to provide for'leakage 

makeup of the Laboratory pressurized section 

3-64 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 • 

• 

(including cE1.-bon &oxide desorption losses), 

one complete repreE.surization of the pressurized 

section, and a number of repressurizations as 

required of ,he pressurized compartment used 

for extravehicular :.gress. 

(4) Oxygen as required to provide for the support 

of extravehicular operations. 

The above requirements do not include allowances that may be 

necessary for storage purge and lea.cage. 

Oxygen and Diluen.: Storal;e \-4) 

The EC/LS oxygen requirements shLI1 be inzegrated with the electrical power supply oxygen requirements. Diluent supply shall be 

provided from a supercritical cryogenic storage system. Design 

requirements for the diluent storage system (including standby time, 

orbital operation, extended mission capability, quantity measurement, 

and pressurization) shall be identical to those specified for the 

oxygen storage system in paragraphs 3.3.2.2.8.5.1 and 

3.3.2.2.8.5.2. . 

3.3.2.2.6.2.7 Carbon Dioxide Control -4) 

A regenerable adsorbent system shall be 1.1.£ ed for carbon dioxide 

control. The environmental control system shall maintain nominal 

carbon dioxide levels. The emergency carbon 

dioxide level shall not exceed .15 mm Hg for 4 hr. 

3.3.2.2.6.2.8 Contaminant Control \-4) 

Equipment shall be provided for the control of odor and trace gases. 

Atmospheric debris traps shall be p;:ovided. 

Concentration limits for 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 and duration. 

• 

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Title 18. U.S.C.. Section . 798 and 794, the tionpatss.on of which in any manner to an onouthorreed person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 CO '1 

Positive control shall be exercised to identif:i contaminants, their 

ems 

sources, and to. Minimize their introduction into the Laboratbry atmosphere. 

Rigid control of contamination and contamination producing materials and conditions shall be exenised in part by: 

a. Contractor contamination control specifications(s), 

b. Thorough contractor surveillance and approval of 

purchased ("make.7or-buy) and laboratory installed contamination controlled 

components or parts. 

c. Installation of necessary diagnostic instrumentation 

and/or displays. 

3.3.2.2.6.2.9 Pressure Maintenance Ns!+) 

Each compartment of the pressurized section shall be capable 

of maintaining normal pressure in the event of loss of pressure in the other 

compartment. The pressurization system shall be capable of maintaining a 

level that provides minimum acceptable alveolar oxygen pressure in either . 

compartment for 5 minutes with a 1.0.in. diameter hole. 

3.3.2.2.6.2.10 Repressurization 

Repressurization time for either pressurized compartment 

to a.leveltthAt:pro-Vides normal alveolar oxygen pressure shall be five min 

maximum. Diluent makeup to the normal dual gas mode shall be one hr maximum. 

Provisions shall be made for the rapid depressurization of the atmosphere in 

either pressurized compartment. Repressurization time for the Gemini B and 

transfer tunnel to the level specified in paragraph 3.3.3.1.5 shall be one. 

minute maximum. 

3.3.2.2.6.3 Thermal Control 

3.3.2.2.6.3.1 General (U) 

Thermal control for 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 provisions shall be capable of removing 

the heat generated under the most unfavorable combination of crew operational 

mode and atmosphere operational mode. Capability shall be provided to 

accommodate the electrical loadings identified in paragraphs 3.3.1.162.1 and • 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 3. 3. 2. 2. 6. 3. 2 Space Radiator 

The space radiator shall form part of the external vehicle surface. 

Radiator tubing shall meet the meteoroid criteria specified in paragraph 3. 3. 2. 2. 9. 2. The space radiator shall be designed and controlled 

to avoid freezing of the transport fluid under all operational conditions, 

including Laboratory Vehicle pre-activation. The space radiator shall 

properly perform for the orbital conditions defined in paragraphs 

3. 1. 1. 1. 4. 2 and 3. 1. 1. 1. 1. 2. A single radiator failure shill not 

result in abort of the mission. 

3. 3. 2. 2. 6. 3. 3 Expendable Matter (U) 

The fuel cell excess water and the collected atmosphere condensate 

p.ball be utilized as expendable matter. This heat sink shall provide 

for supplementary and emergency cooling on-orbit, and for proper 

thermal control during the ascent environment. This technique shall 

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

the OV. Disturbances of vehicle attitude due to the use of the water 

evaporator shall be minimized. 

3. 3. 2. 2. 6. 3.4 Vehicle Orientation (U) 

The thermal control proVisions 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 (U) 

The temperature for the internal wall of the pressurized section shall 

not exceed 120 deg F, nor be less than atmosphere dew point, when 

subjected to the worst combination of vehicle orientation, crew operational mode, atmosphere operational mode, and equipment power 

loading. 

3. 3. 2. 2. 6. 4 Food Management /*Qc4) 

Food management for the Laboratory Vehicle shall emphasize simplicity, palatability, and minimum interference with on-orbit duties. 

Food storage shall be at nominal cabin temperature (extremes not to 

-CONFIDENTIAL-- 

Due document contoms Information offec/Ing the nenonol defense of the Unttat Slates within the meaning of the tiatonage snrs 

Title 18. U.S C . Section 783 and 794

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

exceed 0-100°

F) 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 as part of the waste management 

provisions. Provisions for measuring and recording actual food intake shall be provided. 

3.3.2.2.6.5 • Water ManagementX-4) 

• 

Water management shall provide for the efficient utilization of the 

water consumed and produced within the Laboratory Vehicle. The onboard source of potable water shall be the fuel cell electrical power 

supply. Potable water to meet crew metabolic requirements shall be . 

stored in a separate water tank. The excess fuel water shall be stored 

in a waste water tank, in which shall also be stored the collected atmospheric condensate. The potable water shall be made available to 

the pressurized section at nominal temperatures of both 155 deg F and 

55 deg F. Provisions for measuring and recording water intake and 

timing shall be provided. 

3.3.2.2.6.6 Waste Management (If) 

Waste management for the Laboratory Vehicle shall provide for the 

collection, transfer and storage of all crew and vehicle wastes. The 

crew waste collection devices shall be convenient and comfortable to 

use and shall require minimum maintenance to avoid unsanitary conditions. The vehicle atmosphere shall not be contaminated by the use 

of these devices and any airflow used in the waste collection process 

shall be decontaminated before return to the pressurized compartments. Containers impermeable to solids, liquids, gases and bacteria 

shall be provided for waste storage. Proper provisions shall be 

employed to ensure maintenance of putrefaction control of collected 

waste. 

Provisions shall be made for the management and measurement on an 

individual crew member time line basis of daily urine volumes of 1800 

± 700 ml per man. This volume (less a 100 ml aliquot for subsequent 

3-68 -CONFIDENtlitThis document contains "information affecting the notional defense of the United States wallas the meaning of the Esptonage Lows. 

Title I8, U.S C. Section 793 and 794, the transmission 'of which in any manner to on unauthotszed penal is woh.h.ted by law 
NRO APPROVED FOR 

RELEASE 1.JULY 2015 

lyophilization and returnto earthfor analysis) is to be delivered to and 

managed by the appropriate waste management equipment. 

The daily fecal volumes per man of approximately 100.± 100 ml shall 

.be collected for immediate lyophilization and stored for subsequent 

return to earth for analysis. 

3.3.2.2.6.7 Personal Hygiene (U) 

Personal hygiene for the Laboratory Vehicle shall provide for the convenient storage of all stores and devices used by the crew for skin • 

cleansing, oral hygiene, shaving, and hair and nail cutting, as required. 

Proper,provisions shall be employed to collect and process all debris' 

and wastes produced as a result of these operations. 

3.3.2.2.6.8 EC/LS Over-all System Requirements 

3.3.2.2.6.8.1 Prelaunch Operation (1J) 

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 sea-level pressure. Ground cooling of the Laboratory shall 

provide for pre-launch requirements as defined in paragraphs 3.1.1.1.1 

and 3.1.1.1.2.2. 

3.3.2.2.6.8.2 Launch and Ascent Operations (U) 

The atmosphere of the pressurized section shall be relieved during 

ascent to maintain a pressure differential compatible with the specified 

orbital requirement. 

3.3.2.2.6.8.3 Safety Features (U) 

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 to prevent over-pressurization. Flow limiting devices shall be provided to prevent excessive 

use of gas supplies. • Manual backup shall be provided to control repressurization. 

3-69 
NRO APPROVED FOR 

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3.3.2.2.7 Attitude Control and Traneation System (ACTS) 

3.3.2.2.7.1 Gene ral4) 

The ACTS shall provide, without dependence upon the 

Laboratory vehicle computation capability (paragraph 3.3. 2. 2.5. 23), the 

following functions: 

(1) automatic and manual. attitude control 

(2) orbit maintenance 

(3) separation from boost vehicle 

(4) vernier insertion capability 

(5) orbit adjust 

(6) Laboratory Vehicle disposal 

3.3. 2. 2. 7. 2 Functional Requirements tSs-4) 

The functional requirements of the following paragraph 

are those necessary to provide automatic and manual attitude hold and 

maneuver capabilities and translational acceleration to meet the MOL 

mission requirements. When. ACTS is used to assure initial orbit the 

remainder of the ACTS propellant will be reprogrammed for degraded 

on-orbit operation. 

Operating Modes1/4-3 SAR) 

(a) Local Vertical and Orbit Plane Mode - the 

vehicle attitude shall be automatically maintained 

relative to the local vertical and the orbit plane. 

(b) Local Vertical/Relative Velocity Vector Mode - 

the vehicle attitude shall be automatically maintained 

relative to the local vertical and the relative velocity 

vector. The relative velocity vector is defined 

as the vector sum of the vehicle velocity vector 

and the velocity vector of the earth directly 

under the vehicle, both taken with respect to an 

earth-centered reference frame. 

(c) Inertial Attitude Hold Mode - shall provide for 

attitude hold relative to an inertial coordinate 

system and for sequential single axis maneuvers.. 

Maneuvers may be commanded by the ground . 

command or the crew. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

(d) Rate Stabilization Mode - shall provide for 

automatic damping of vehicle rates and for rate 

maneuvers controlled by ground command or 

manually. Rate maneuvers shall not exceed 5.0 

deg/sec. 

(e) Direct Control Mode - Shall provide for manual 

high rates and manual emergency control. The 

reaction jets shall be controlled directly by the 

flight crew with a minimum amount of electronics 

to provide high reliability. 

(f) AV Mode - shall provide acceleration in the 

x direction. Capability shall be provided for 

ground or manual command of AV set and initiate. 

(g) )Low Power Mode - electrical power consumption 

shall be minimized and the vehicle shall be oriented 

to reduce aerodynamic drag. 

(h) Minimum Impulse Mode - shall be used by the 

flight crew to provide precise manual maneuvers. 

(1) Vertical Acquisition Mode - shall provide 

automatic acquisition of the local vertical. 

(j) Automatic 4 V Termination Mode - shall provide 

automatic initiation and termination of velocity changes 

in the x direction. 

3. 3. 2..2, 7. 2. 2 Rate Roof Operationl'1/43 SAR) 

Provisions shall be incorporated into the system for 

automatically maintiahing rates below the value specified in 3.3. 2.2. 7.4 

when utilizing the Local Vertical and Orbit Plane mode, Local Vertical/ 

Relative Velocity Vector mode, and the Attitude Hold mode. 

3.3.2.2.7.2.3 Limit Cycle Deadbandl'1/43 SAR) 

Two limit cycle deadbands shall be provided in each axis; • 

one narrow deadband, and the other a wide deadband. The magnitude of the 

wide deadband shall be manually variable between 0. 5 and 5.0 deg. The 

magnitude of the narrow deadband shall be selected to meet the requirements of 

item (2) of paragraph 3. 3, 2. 2. 7..4, 

3.3.2.-2.7.2.4 Inhibit Irss4) 

The ACTS shall be capable of accepting an inhibit signal 

from other systems. This signal will inhibit all reaction jet firing until 

removed. A manual override shall be provided, 

. r. 

F.Pg10„, 341 
NRO APPROVED FOR 

RELEASE 1 JULY 2015. 

3.3.2.2.7.2.5 Operating Life 1/44) 

The ACTS shall be capable of continuous operation in 

any of the operating modes at any time during the mission. Propellant and 

thrust chamber requirement s shall be Lased upon the operational mission 

profile. 

Rate and Attitude Information 

The ACTS shall be capable of providing body axis 

rate and attitude error signals to other OV subsystems. The probability 

of the error in analog rate signal exceeding 0.005 degree/second or 

the error in the analog attitude error signal exceeding 0.45 degrees 

shall be less than 0.997. 

3.3.2.2. 7.2.7 Attitude Acquisition 

,r_ The ACTS shall be capable of automatic acquisition of 

and orientation to the local vertical and orbit plane when loss of acquisition 

is sensed automatically or upon ground command. Acquisition time shall 

not exceed 30 minutes. 

3..3.2.2.7.3 Definition of Body Axes (U) 

The body axes are defined as: 

(1) Pitch axis (y-axis) - This axis completes a right 

hand set with the roll and yaw axes. 

(2) Roll axis (x-axis) - An axis parallel to the 

vehicle longitudinal axis with the positive direction 

toward the Gemini B. 

(3) Yaw" axis (z axis) - An axis normal to the vehicle 

longitudinal axis and parallel to a radius of the 

vehicle which is nominally earth-pointing. The 

positive direction is toward earth. 

3.3.2.2.7.4 Accuracy Requirements -3 SAR) 

The probability that the following angular deviations 

are not exceeded shall be greater than 0.997. (This is equivalent to a three 

sigma requirement for a normal statistical distribution). 

(1) Vehicle Attitude Reference - In the Local Vertical/ 

Orbit Plane moTg,ENTangular deviation of the • 

pitch or roll reference signals from the local 

vertical shall not exceed + 0.35 deg. 

In the Local Vertical/Relative Velocity. Vector . 

mode the angular deviations of the pitch or 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

roll reference signals from the local vertical 

shall not exceed + 0.3 deg and the angular 

deviations of the .yaw reference signals from the 

relative velocity vector shall not exceed + 0.45 deg. 

In the Inertial Attitude Hold mode the drift of the 

attitude reference signal shall not exceed three deg per 

hour. 

• 

3=72.1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SECF:ET 

(2) Vehicle Body Axes .- 

Narrow Deadband - In the Local Vertical/Orbit 

Plane mode, the angular deviation of the pitch 

or roll body axes from the local vertical shall 

not exceed ±0. 5 deg. The angular deviation of 

the yaw body axis from the orbit plane shall 

not exceed ±0. 5 deg. 

In the Local. Vertical/Relative Velocity Vector 

mode the angular deviation of the pitch or roll 

body axis from the local vertical shall not 

exceed ±0. 50 deg. The angular deviation of 

the yaw body axis from the relative velocity 

vector shall not exceed ±0. 60 deg. 

Wide Deadband - The deadbands shall be selected to minimize propellant requirements. 

In the Low Power mode the angular deviation 

of the body axis from the desired reference 

shall not exceed ± 4. 0 deg. 

Body Axis Rates - In the normal operating 

modes, rate control is not required. However, 

body rates shall be minimized to reduce propellant requirements. 

During rate roof operation, control logic 

shall be provided to prevent the body axis 

rates exceeding ± 0. 005 deg/sec for long periods of time. 

Performance Reouirement3 SAR) 

Translational Acceleration - The unidirectional I 

translational acceleration shall be greater than 

Gemini B Interfacess\-4) 

It shall be possible to control the ACTS from the Gemini B to separate 

the Orbiting Vehicle from the Launch Vehicle when initial orbit is 

achieved and for certain abort modes. 

Capabilities in the Gemini B shall include: 

(a) ACTS electronics control monitors 

(b) ACTS propulsion control monitors 

(c) Controls for manual operation of the ACTS. 

SECRET 

•The. document contains,information affecting the national• defense of the United States Within the meaning of the Espionage lows, 

•71the 18, U.S.C.. Section 793 and 794, the transmission of which in any manner lo an unauthorized person is prohrbtted by low 

werrenertrilF 

,r- 

(3) 

3. 3. 2. 2. 7. 5 

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

0.40 ft/ sect in the x direction, 

3-73 
NRO APPROVED FOR 

RELEASE 1 JULY 201.5 

-111NRDET111--- 

• The Gemini B reference system and displays shall be utilized for 

visual reference but shall not be integrated with the ACTS electronics 

located in the Laboratory Whit le. 

3. 3. 2. 2. 7. 7 Control Electronics Subsystem N\-4) 

This subsystem consists of the reference element, the control logic 

and drive electronics, and the display element of the ACTS required to 

. command the on-off reaction jet propulsion subsystem to control 

orbiting vehicle attitude and pi-oxide translational velocity changes 

while in orbit. 

3. 3. 2. 2. 7. 7. 1 Reference Element Ns-4) 

This element shall contain the horizon sensors, gyros, and accelerometers litcessary to provide vehicle linear acceleration, attitude, and 

angular rate sensing. It shall also include any other equipment neces-. 

sary to provide outputs suitable for linear velocity, attitude, and angular rate control and display. Ion sensors shall be included in the 

selection of the Low Power mode reference element. 

3. 3. 2. 2. 7. 7, 2 Display Element 

Deleted. 

3. 3. 2. 2. 7. 8 Propulsion Subsystem /1S.4) 

The propulsion subsystem consists of thrust chamber assemblies 

(mounted to give vehicle rotation and translation) and propellant supply 

and pressurization assemblies. This subsystem responds to actuation 

commands from the control electronics subsystem. The subsystem 

shall be designed to permit full operation with only minor degradation 

in the event of a single malfunction of a component. 

3. 3. 2. 2. 7. 8. 1 Subsystem LifeNO) 

The propellant supply and pressurization assemblies shall be capable 

of continuous operation during the on-orbit life of the Laboratory Vehicle. .The thrustors shall be capable of operation in a worst-case duty 

3-74 

This document contains information affecting the notionol defense of the United States ...thin the meaning .of the Espionnoe tows. 

Title le, U.S C.. Section 793 and 794. the tionsmission of which in any manner to on smouthorlied person is prohibited by law 
3-75 

This document contoins information affecting the notional defense of the United States within the meaning of the Espionage Lows, 

41111 IS, Section 793 and 794, the transmission of which in any manner to on unauthorized person is plohibtted by .law 

'n'tenett"997•99.114 

SSD APAR:2 208 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

cycle imposed by the mission requirements. Time periods of acceptance testing, prelaunch testing (e. g. , on-pad checkout and propellant 

handling) and all other durations of subsystem or component operation 

shall be considered when determining the life of the subsystem or any 

of its elements. 

3. 3. 2. 2. 7. 8. 2 Propellant GagingIV4) 

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. 8. 3 Propellant Requirements 4) 

The propellants shall be hypergolic bipropellants which are spacestorable and shall be selected with consideration of thermal environ- 

, 

Ment, minimization of ignition. over-pressure transients, and the 

thrust chamber assembly selection. 

The longitudinal translational velocity increment (AV) shall be 

ft/sec for orbit maintenance, 'separation, vernier insertion correction, 

orbit adjust, and de-orbit. Additional propellant shall be provided for 

attitude control, propellant utilization, and contingencies. 

3. 3. 2. 2. 8 Electrical Power Subsystem 

3. 3. 2. 2. 8. 1 General Requirements (U) 

The Laboratory Vehicle Central Power System (CPS) shall be activated 

during prelaunch operations and shall provide the total Laboratory 

subsystem power during launch, insertion, orbit adjust, Laboratory 

activation, on-orbit and emergency mission phases. 

3. 3. 2. 2. 8. 1, 1 Type of Power Sour ce (U). 

The generation of primary electrical power for the CPS shall be 
RO APPROVED FOR 

RE L iitt 1 JULY 2015 6 'CORRAL-. 

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 l'iS<4) 

The CPS shall be a nominal 28v dc power system utilizing established 

design practices for subsystem compatibility. 

3. 3. 2. 2. 8. 1. 3 Overloads 1€K4) 

During the 30-day on-orbit phase the CPS shall accommodate transients, intermittent and varying peak power levels and shall remain 

within its performance specification. Power requirements which 

exceed the specified capability of the CPS shall be supported 

separately. 

3. 3.• 2. 2. 8. 2 Specific Requirements 

3. 3. 2. 2. 8. 2. 1 Location (U) 

The fuel cell powerplant shall be located in the forward unpressurized 

compartment of the Laboratory Vehicle. 

3.3.2.2.8.2.2 Life 11S-s4) 

The fuel cell powerplant shall have a minimum life of 1000 hr and 

during this life shall remain within its performance specifications 

while providing CPS power requirements. 

3. 3. 2. 2. 8. 2. 3 Fuel Cell Redundancy 11Ss4) 

The CPS shall have a minimum fuel cell module redundancy of 33 percent of the required modular configuration. 

3.3.2.2.8.2.4 Parasitic Power 115.1/4-4) 

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 nominal 2. 0 kw of power required to be delivered by the 

power plant for the CPS loads. 

3-76 

SSD AUGr2 F 20B Title U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by low 

This document contains information affecting the notional defense of the United Sta:es within the meaning of the Espionage tows, 

"r"Wrrwl.'911rrilltrIPMFgellor•FIMPII.111180111.111/11 ,111,r-irr 

-GONFIDENflAr- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 2. 2. 8. 2. 5 Emergency Power llS4) 

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, Mission Control coordination, 

remedial action, and Flight Crew return to Gemini B. 

3. 3. 2. 2. 8. 2. 6 Voltage ls1) 

During the mission phases. and for all combinations of loading within 

the mission power profile, including emergencies, the power sources 

shall maintain 25-31 volts ;it the bus. 

3. 3. 2. 2. 8. 2. 7 Specific Reactant Consumption N4) 

The total quantity of reactants including purge requirements needed by, 

the fuel cell power plant 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 (U) 

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 per paragraph 3. 3. 5. 

3. 3. 2. 2. 8. 2. 9 Waste Heat(U)- 

• 

The waste heat generated by the fuel cells shall be removed by a circulating coolant system. The coolant system shall dissipate its accumulated heat through an external space radiator located on the surface of the Laboratory. The coolant system shall allow the Laboratory Vehicle CPS to have an independent checkout and test capability. 

3. 3. 2.2. 8. 2. 10 Power Source Failure (U) 

Power distribution from the fuel cell modules shall be designed so 

that the failure of any module or modules does not adversely affect. 

0 

3-77 

FORM This document contains information affecting the national defense of the United ,'aces within the meaning of the Espionage. Lows. SSD AUG 62 20B Title 18. U.S.C., Section 793 and 794, the transmission of which in any manner :o an unouthoficed omen is prohih•ted by to. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

the operation of the remaining modules. Switch-out of the failed modules 

shall be automatically controlled with a remote manual override capability. 

Individual control of each module shall allow selective grouping of any 

combination of fuel cell modules. 

3.3.2.2.8.2.11 In-Space Start (U) 

The fuel cell power supply shall have the capability of an 

in-space shut down after on-orbit operation and an in-space start after onorbit storage. 

3.3.2.2.8.3 Power Control and Monitoriqg (U) 

An automatic sensing and control system with a manual and 

remote command override capability shall be incorporated within the vehicle 

for monitoring and managing the CPS visual indications and status telemetry of 

electrical system events, conditions, outputs and malfunctions shall be 

provided. Manual and remote command control of load switching and reset of 

circuit breakers shall be provided. 

The 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 (U) 

All Laboratory and Mission Payload equipment requiring 

power outside the characteristics of the fuel cell power plant shall provide., 

individual power conditioning equipment. 

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 

hydrogen and oxygen storage. A redundant pressurization system shall be 

provided for each tank. 

3.3.2.2.8.5.1 Capacity 0 

The cryogenic storage system shall have adequate capacity. 

plus a 10 percent reserve to supply the EC/IS oxygen requirement and all of the 

j 

CONED NTlit 
NRO APPROVED FOR 

' RELEASE 1 JULY 2015 CONFIDENTIAL 

reactants for the fuel cell power system to accomplish the complete 

mission. The cryogenic storage system shall be capable of a minimum 

48 hr 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 cryogenic storage system shall not preclude provisions 

for an extended mission .duration capability. 

3.3.2.2.8.5.2 Quantity Measurements (U) 

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 (U) 

During the pre-launch phase, the CPS shall have a check-out capability 

to permit performance parameters to be verified prior to launch. Performance parameters of the other Laboratory Vehicle sub-systems 

also shall be exercised, and the CPS shall sustain their launch mode 

power requirements, and those of the Gemini B upon transfer to internal power. 

A capability shall be provided to monitor the CPS during all phases of 

a mission. 

3.3.2.2.8.7 Laboratory Vehicle Equipment Power Requirements 

3.3.2.2.8.7:1 Equipment Operating Voltage (V\-4) 

Laboratory equipment shall give specified performance when operated 

with 22-31 volts at the equipment power terminals. 

3.3.2.2.8.7.2 Under and Over-Voltage (6-4) 

Laboratory equipment shall withstand, without damage, continuous 

voltages from 20-33 volts at its power terminals and power interruptions up to one second and shall immediately give specified performance upon return to the equipment operating voltage. 

FORM This document contains information affecting the national' defense of the United States within the meaning of the Espionage Lows. 

SSD AUG 62 20B Title 18. U.S.C., Section 793 and 794, the transmission of which in any manner to o unauthorized person Js prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -SEW3.3.2.2.8.7.3 Transients l'Ic-4) 

Laboratory equipment shall be capable of withstanding transients of 

*100 volts with respect to nominal bus voltage for durations up to 10 

microseconds. 

3.3.2.2.8.7.4 Electromagnetic Interference (U). 

Electromagnetic Interference (EMI) control of the Laboratory Vehicle 

shall be as specified in SSD Exhibit 64-4. 

3.3.2.2.8.7.5 Grounding (U) 

The CPS primary power distribution shall incorporate a single point ' 

ground system and grounding network compatible with the Launch 

Vepicle, Gemini B, Laboratory Vehicle, and Mission Payload, Shield 

grounding shall be in accordance with SSD Exhibit 64-4. 

3.3.2.2.8.7.6 Bonding (U) 

The bonding requirements for the installation and interconnection of 

electrical and electronic equipment shall be as specified in SSD 

Exhibit 64-4 and MIL-B-5087B. 

3.3.2.2. 8. 7. 7 Electro-Explosive Device (EED) Installation (U) 

The installation of EED pyrotechnic devices or actuators shall be in 

compliance with the requirements of SSD Exhibit 64-4 and AFWMTR550-2. • 

3.3.2.2.9 Structural Subsystem (U) 

3.3.2.2.9.1 Design Environment Criteria (U) 

The environmental criteria applicable to the Laboratory Vehicle 

structure are as specified in SSD Exhibit 65-7. 

3.3.2.2.9.2 Structural Design Criteria (U) 

The structural design criteria applicable to the Laboratory Vehicle 

are specified in the "Structural Criteria for the Manned Orbiting 

Laboratory (MOL) Laboratory Vehicle System," Attachment No. 7 to 

Laboratory Vehicle Contractors Statement of Work. 

3-80 

This document document contains information affecting the notional defense of the United Stores within the ',waning of the Eipronnge Laws, 

Title IS. u S c . Section 793 and 794, the transmission of which in ony manner to on totototh0,oted oersnn is prohibited by tow 
.14.011.• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 

3.3.2.2.9. 3 Limit Load\-4) 

Limit load is the maximum anticipated load, or combination of loads, 

which a structure may be expected to experience during the performance of specified missions in specified environments. 

The structure shall be designed to have sufficient strength to withstand 

simultaneously the limit loads, applied temperature, and other accompanying environmental phenomena for each design condition without 

experiencing excessive elastic or plastic deformation. 

a. 

,r3.3.2.2.9.4 Factors of Safety (U) 

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. OCi 

(Normally Under Oil Pressure Only) 

Hydraulic and Pneumatic 1.00 2.00 4.00 - 4.00 

(Lines, Fittings and,Hcises) 

Main. Propellant 1.00 1.50 1.88 1.88 

(Supply and Vent Components) 

Cryogenic Tanks 1. 00 1.67 2.22. 2. 22 

* Proof pressure is defined as that pressure which is applied to a 

pressure vessel as a test at room temperature. (U) 

3-81 

fibs document contains micumoun effecting the nation& defenso of the United States within the meaning of the Espionage tows. 

lute '18. U.S C . Section 79.3 and 794. the tronsmission of which n ony ,manner to an unouth9"7ed person is plohibifed by low 

7717999,117. 
SSD Foam 

AUG 62 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 2. 2. 9. 5 Strength and Stiffness 11S.4) 

Structural failure shall not occur at loads less than ultimate. 

The structure shall not experience deformations which impair functional performance at limit loads. 

'.The structure shall not experience deformations which impair performance of function at loads less than limit. 

Structural deformations shall not cause structural failure at loads less 

than ultimate. 

Destructive flutter or other dynamic instability shall not occur at any 

condition within the design envelope. 

Structural materials' utilized in the pressurized areas shall possess 

demonstrated crack resistance under the specified environments and 

operations. 

3. 3. 2. 2. 9. 6 Hatches X-4) 

Pressure tight hatches, capable of actuation from either side, shall 

be provided at all ingress/egress hatches in the Laboratory pressurized compartments. 

3. 3. 2. 2. 9. 7 Windows X-4) 

Viewing windows, as appropriate, shall be provided in the Laboratory 

pressurized compartment to permit earth and star field viewing. 

Intra-Laboratory and transfer tunnel viewing shall be provided in the 

compartment bulkhead door. 

3. 3.'2. 2. 10 Flight Crew Accommodations (U) 

Provisions shall be made in the Laboratory for flight crew equipment, 

accessories, supplies, and test and monitoring as defined under 

• Section 3. 3.5. 

3-82 --.5NFIDENTIAL_ 

This document contains information affecting the national defense of the United States within the meaning of the Espionage Laws, 

208 Tale 18, U.S C., Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by low. 

IMemerfetteltrig 
tr 1-- NRO APPROVED FOR 

RELEASE 1 JULY 2015. CONFIDENTIAL 

3. 3. 2. 2. 10. 1 Furnishings and Equipment (U) 

or 

The pressurized•section shall provide furnishings and equipments in 

functional groups for maximum efficiency and flight crew safety. 

3. 3. 2. 2. 10.2 Flight Crew Test and Monitoring Subsystem 

3. 3. 2. 2. 10. 2. 1 Biomedical Test and Monitoring (U) 

Equipment shall be provided to accomplish the biomedical tests as 

presented in 3. 3. 5. 

3. 3. 2. 2. 10. 2. 2 Crew Performance Tests (U) 

Equipment shall be provided to 'accomplish the crew performance tests 

as presented in 3.3.5. 

3. 3. 2. 2. 1 O. 3 

.r. 

Extravehicular Operations (U) 

Extravehicular capability shall be provided to include restraint for the 

EV Crewman, umbilical Environmental Control System, visual monitoring equipment, effective illumination, and voice communications. 

3. 3. 2. 2. 11 Mission Provisions(U) 

Installation space shall be provided in the Laboratory Vehicle which 

is compatible with the mission equipment requirements. The space 

allocated shall permit installation of consoles, controls, displays, 

support brackets, signal and power conductors, and coolant lines to 

equipments, as required for a manned or unmanned operation. 

3. 3. 2. 2. 11. 1 Scientific and Technological Experiments (U) 

A further objective of the Laboratory Vehicle design shall be to provide a configuration which will not preclude the incorporation of 

military scientific and technological experiments. 

3. 3. 2. 2. 11. 1. 1 Space. Provisions (U) 

Any space not specifically required for primary purposes shall be 

evaluated for use by scientific and technological experiments. If 

feasible, any such space allocation should be consolidated to enhance 

its usefulness for experiments. 

• 

111 • 3-83 

FORM • This document contoms Atm-notion affecting the notional defense of the Unite•i Woes within the meaning of the Espionage Laws.. 

SSD AUG 62 20B title 18, U.S.C., Section 793 and 794, the transmission of which II any manner to an unauthorized person is prohibited by. law 

"ImlffmrFIRE 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 CONFIDENTIAL 

3.3.2.2.11.1.2 Support Provisions (U) 

Consideration shall be given to the provision of support to scientific 

and technological experiments which may be installed in the above 

spaces. This shall include consideration of power, cooling, interconnections, and display and control consoles. 

3.3.2.2.11.1.3 Mass Properties Provisions (U) 

Requirements for local attachment of scientific and technological 

experiment equipment and the mass properties effects of such equipment upon the over-all segment loads shall be considered. 

3.3.2.2.12 Flight Crew Training Equipment (U) 

Training equipment, as appropriate, shall be provided to accomplish 

F4ght Crew Training in accordance with 3.3.12. Portions of the 

Laboratory Vehicle procedures trainer shall be designed for integration into the MOL Mission Simulator. 

3.3.2.2.13 Laboratory Peculiar AGE 

3.3.2.2.13.1 Design /1\4) 

The Laboratory Vehicle System Segment peculiar AGE shall consist 

of Operating Ground Equipment (OGE) and Maintenance Ground Equipment (MGE) designed to support all Laboratory segment assembly 

and checkout ground operations at the Laboratory contractors' facility. 

Portions of this AGE will be utilized for OV integration at the OV . 

Integrating Contractor facility and at the launch site. Laboratory 

peculiar AGE shall be designed per requirements established in this 

specification, with maximum utilization of existing AGE. The Laboratory AGE utilized at the launch site shall be functionally identical 

to that AGE utilized at the contractor manufacturing facilities. The 

Laboratory peculiar AGE shall be designed for inclusion in GFE vans 

compatible with ILC, operations. Laboratory peculiar AGE may be 

integrated into a complete OV checkout system as dictated by detailed 

design requirements. The Laboratory peculiar AGE shall be designed 

3-84 

FORM This document contoins information affecting the national defense of the United St Ites within the meaning of the Espionage Laws, 

SSD AUG 62 LUB Tote i6, U.S C.. Section 793 and 794. the transmission of which in any manner to an unauthorized person is Prohtbfted by law 
NRO APPROVED FOR 

' RELEASE 1 JULY 2015 

for ease ease of maintainability, interchangeability, and shall have. features 

which will facilitate isolation and detection. All Laboratory AGE shall 

be acceptance tested prior to being utilized for AVE ground operations. 

Data transmitted between Laboratory and its peculiar AGE shall be 

compatible with the data transmission system of the ILC at VAFB. 

3.3.2.2.13.2 Performance ItS..4) 

The Laboratory Vehicle System 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 

.r. operation outside the prescribed limits. This AGE shall be capable 

of integration with the complete MOL system AGE at VAFB. 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. Portions of the Laboratory AGE shall support the Laboratory 

Vehicle System Segment end-to-end systems test when integrated into 

the OV checkout system. 

3. 3. 2. 3 Functional Interfaces (U) 

(Functional interfaces shall be listed here when defined by the cognizant Interface Control Working Group - ICWG. ) 

3. 3. 2. 4 Contract End Items (U) 

(The contractor shall provide for incorporation in this paragraph a list 

of the Contract End Items by CEI specification number, nomenclature, 

and the CEI into which it installs.. This paragraph shall list all end 

items being provided under these system segments.) 

3 -85 /6 

FORM This document contains information affecting the national defense of the United States within the meaning of the Espionage Laws. 

SSD AUG 62 20B Title l6, U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by low 
_ 

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3.3.2.5 Mission Peculiar Requirements, Laboratory Vehicle 

3.3.2.5.1 Space Allocation Requirements 

3.3.2.5.1.1 Consoles and Camera Equipment 

The Laboratory Vehicle shall provide for and accommodate 

consoles and camera equipment necessary for the operation, information 

display and processing activities for the mission payload. Console space 

requirements in the pressurized section of the laboratory module are as 

follows: 

Manned Automatic Configuration 

(later) 

Automatic Configuration 

(later) 

3.3.2.5.1.2 Data Re-entry Vehiclei:Section (Manned Flights only) 

The Data Re-entry Vehicle Section (DRVS) shall support, 

house, and protect up to three data re-entry vehicles (DRV), a launcher 

tank, auxiliary electrical and mechanical equipment required to control 

DRV separation.and DRVS environmental control. The DRVS shall be located 

in the Laboratory Module which shall provide the following space and 

orientation: 

(later) 
NRO APPROVED FOR 

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SPECIAL HANDLING 

3.3.2.5.2 Maneuvering Capability Requirements 

The Attitude Control and Translation System 'shall have the 

capability to orient the orbiting vehicle to any roll, pitch or yaw 

attitude as commanded for photography of objects of secondary interest, 

for orbit adjust, crab correction, and other purposes. The specification for attitude accuracy shall remain the same for yaw offsets up 

to 3° from the orbit plane, otherwise the roll and pitch accuracy shall 

be allowed to degrade in proportion to the angle commanded by 1% of the 

commanded angle. The system shall be capable of settling within 30 seconds 

from the end of a manuever down to within the specified photo period 

accuracies prior to an active photo pass. 

Not more than one second can be allowed for control system 

settling to within the above attitude and attitude rate specifications 

following a disturbance during an active photographic pass. 

3.3.2.5.3 Backup DRV Separation System (Automatic Configuration only) 

A backup stabilization subsystem and backup command subsystem 

are required in order that a satisfactory orbit ejection attitude for at 

least one DRV separation may be obtained even though a failure has been 

experienced in any combination of primary electrical power, command and 

control, and attitude control subsystems. 

3.3.2.5.4 Alignments 

(later) 

3.3.2.5. 5 Electrical Power 

(later) 

SPECIAL liAiCila 3-86.2 

IfeRET— 
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3.3.2.5.6 Command and. Control 

SPECIAL HANDLING 3_86.3 
,214.11110,14.64111110IMINNam.-40' 

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3. 3. 3 Gemini B System Segment (U) 

The Gemini B system segment shall consist of a re-entry module 

(REM), an adapter, and the supporting ground system. The Cti-nini B 

will be a NASA Gemini spacecraft with minimum modifications. The 

Gemini B shall be capable of performing 30-day earth orbital flights 

as an integral part of the OV and shall be capable of controlled 

earth orbit, loiter, re-entry, and water landing as an autonomous ' 

spacecraft. The Gemini B shall bey dependent on other system segments for performance of certain functions; the extent of this dependence upon other segments shall be as specified herein and in the CEI 

specifications. design criteria, and interface specifications. 

3.3. 3. I 

3. 3. 3. 1. 1 

Allocated Performance and Design Requirements 

Weights (U) 

Maximum design launch weight for the Gemini B, including the REM 

and adapter, shall be 5610 lb. 

3. 3. 3. 1. 2 Electrical Power (U) 

Electrical power requirements for Gemini B are given in paragraphs 3. 3.1.1.2.2 and 3.3.3.2.6. 1. 

3. 3. 3. 1. 3 Effectiveness (U) 

The Gemini B system segment requirements for system effectiveness 

are given in paragraph 3.1.3. 1. 2. 3. 

3. 3.3.1.4 Flight Crew Stay TimeS4) 

... - 

The maximum total time the flight crew will be required to stay in the 

Gemini B is 62 hours. Of this time, at least 14 hours shall be avail- • 

able for loiter as defined in paragraph 3.1.1.6. 

3. 3. 3. 1. 5 Leak Rate (4) 

The Gemini B REM leak rate, including the crew transfer tunnel) ._ 

shall not exceed 2. 5 lb/day.. The REM leak rate with crew 

transfer hatches closed shall not exceed 1.5 lb/day. These leak rates 

3-87 

FORM This document contains information affecting she notional defense of the United Slates within the meaning of the Espionage lost, 

SSD AUG 62 20B Tole 18, U.S.C. , Section 793 and 794. the transmission of which in any manner to an unauthorized person is prohibited by law_• 
mr.-•••••••■•■■■•••11 

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FtE EkSE 1 JULY 2015 

‘o,-V 

are for a pressurization of 5. 0 psi under orbit environmental conditions. • The leak rate at the orbital storage pressure of 0. 1 psi minimum shall not exceed 0. 05 lb/day. 

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

3.3. 3.2. 1 Gemini B Requirements 

3. 3.3.2. 1. 1 Re-entry Module \-4) 

The Gemini B re-entry module shall consist of a modified NASA 

Gemini re-entry module capable of re-entry from polar orbitg consistent with requirements of paragraph 3. 1. 1. 1. 3. 3. This module 

shall provide protection for the flight crew from the environment of 

launch, space, re-entry, and landing within the limits specified herein. 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 data within the 

Gemini B. 

3. 3. 3. 2. 1. 1. 1 Crew Transfer (U) 

Capability shall be provided to permit transfer of the crew members 

• through the Gemini B main pressure bulkhead and heat shield to an 

ii internal tunnel consistent with the requirements of paragraph 3. 3. 3. 2. 11. 

3. 3. 3. 2. 1. 1. 2 Data Package (?11/44) 

The Gemini B REM shall have the capability for return of data from 

orbit. The total weight and total volume available shall be a minimum 

of \--; lb and ) cu ft, respectively. 

3.3.3.2. 1.2 Adapter (U) 

The adapter shall consist of an approximately 56-in. long conical 

structure required to transition from the re-entry module to the Laboratory Vehicle. Provisions shall be included for mounting and protecting the equipment not required to be part of the re- entry module 

3-88 

FO RM This document contains information affecting the national defense of the United States within the meaning of the f suionale tnwt. 

SSD AUG 62 208 Title 18, U.S.C., Section 793 and 794, the transmission of which in any manner to an unauthorized person is p,ohihited by On 
.4 

it- 

, 

11' 

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`Cfttif-BENTIAL. 

but required to support the Gemini B. The Gemini B shall have the 

capability of separating from the Laboratory both the Laboratory/ 

Gemini B adapter separation plane and the adapter retrograde separilion 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 . 3 Strength and Rigidity (U) 

The structure of the Gemini It shall be capable of sustaining all loads 

and environments imposed during the MOL mission for ground handling 

and transportation. pre-lawn- h. launch, ascent, on-orbit, retrograde, 

re-entry. landing, retrieval, and abort modes. 

3.3.3.2.1. 4 Aerodynamic 1/44) 

re The re-entry module shall be trimmed by center-of-gravity position to 

proyide nominal open-loop re-entry touchdown variations of not less 

than 80 n mi right and left total crossrange. The conditions for which 

this design goal shall be met are: mass distribution existing at the 

end of powered flight, re-entry from all orbits as defined in paragraph 3, 1. 1. 1. 4. 2, nominal retro motor performance (six retrograde 

motors fired), and spacecraft minimum design weight. This capability 

shall be obtained only through the use of bank angle ((3) variations in 

the range of -90 °5_ p :5+90° where, for a zero value of f3, the lift vector is directed away.from the earth in the vertical plane. 

3.3.3.2.2 Guidance and Control Requirements 

3.3.3.2.2.1 General (U) 

The Gemini B shall hav,e - a guidance and control system which provides 

the functions of back-up inertial guidance during the ascent phase 

and re-entry guidance and attitude control during the period in which 

the Gemini is separated from the Laboratory Vehicle. 

INFBENTIAL-- 3-89 

FORM This document contains information affecting the national defense of the United States within the meaning of the Esornnage Lows. 

-1U AUG 62 2013 . Tule 18, U.SC., Section 793 and 794. the transmission of which in any manner toOn unauthorized person n nrohihrted by In.. 
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IONMENTRE 

3.3. 3.2. 2.2 Back-up Launch Guidance (U) 

The Gemini B inertial guidance system, when in the back-up launch 

guidance mode, shall provide the required steering and discrete signals to the Titan III flight control system throughout the entire launch 

and ascent phases. Switchover to the Gemini B back-up guidance will 

be initiated by the Titan III MDS, or by the crew. 

3. 3. 3. 2. 2. 3 Re-Entry Guidance and Control (U) 

The Gemini B guidance and control system shall provide these functions during retrofire and re-entry for both normal and aborted missions. Both automatic and manual re-entry control shall be provided; 

The guidance system shall provide an accuracy of ±4 n mi (2 sigma 

dispersions) about the 70, 000-ft altitude intersection point with the 

• 

nominal re-entry trajectory if no error is present in the pre-retro 

initial conditions provided to the guidance system. The system shall 

have the capability to guide to non-nominal points. 

3. 3. 3. 2. 2. 4 On-Orbit Post-Separation Navigation and Control (U) 

The Gemini B shall provide manual and automatic attitude control 

during this phase and, based on data transmitted from the ground 

directly or through the Laboratory Vehicle, shall provide a retrofire 

prediction navigation capability for up to 14 hr from receipt of data. 

3.3.3.2.3 Instrumentation Requirements (U) 

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 by the flight crew and, as required, by the ground during all 

mission phases while the flight crew is in the Gemini B. Suitable 

instrumentation capability shall be provided to permit display and 

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control of the Laboratory ACTS. Capability shall be provided for 

monitoring of Gemini B status by the ground and flight crew while the 

flight crew is in the Laboratory. The Gemini PCM digital telemetry 

format shall be used. Suitable interface modifications shall be provided for integrating and for establishing compatibility of SGLS with 

the Gemini PCM digital telemetry. 

3. 3. 3.2.4 Environmental Control Requirements 

3.3.3.2. 4. I General 

' The Gemini B shall provide the environmental control and life ,support (EC/LS) 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 reactivated for 

• 

mission termination. The atmosphere of the Gemini B, while 

occupied, shall be 5-psi pure oxygen. The Laboratory Vehicle shall 

provide pressurization gas to maintain a minimum pressure of 0. 1 psi 

in the Gemini B cabin and transfer tunnel during the on-orbit storage 

period. Breathing atmosphere, drinking water, and food shall be 

provided for the crew stay time in Gemini B compatible with the 

requirements of Paragraph 3.3..3.1.4. 

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 /VIOL pressure suit assembly shall be considered as an emergency back-up capability for this 

function. 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 

1 

temperature shall not exceed 150°F. 

3.3.3.2.4.3 Suit Environmental Control 

Metabolic oxygen, pressurization, and ventilation shall be provided to 

support the MOL pressure suit assembly. The capability shall be 

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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. 

3. 3. 3.2.4 5 Crew Transfer Environmental Control 

The Gemini B ECS will supply suit ventilation, breathing oxygen, and 

emergency pressurization (if required) during transfer to the Laboratory. This same function shall be performed by the Laboratory ECS 

durirrig transfer to the Gemini B. Capability shall be provided to 

permit extravehicular transfer between the Gemini B and the Laboratory as a back-up mode. 

3. 3.3.2. 5 Propulsion Requirements 

3. 3.3.2. 5. 1 General 

Sufficient propulsive capability shall be provided to permit attitude 

control of the Gemini B during normal re-entry, re-entry from aborts 

and on-orbit loiter, for 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 Gemini B re-entry control system (RCS) shall provide sufficient 

control authority over the entire.re-entry flight to achieve the attitude 

control necessary to permit the full effectiveness of the re-entry 

guidance system and prevent any structural/temperature and crew 

load factor constraints from being violated through uncontrolled 

attitude disturbances. 

( 

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3. 3. 3. 2. 5. 3 - On-Orbit Post-Separation Contri51' 

Propulsive capbility shall be provided for control of the attitude and 

attitude rates of the Gemini B for oniorbit loiter after separation from 

the Laboratory Vehicle prior to de-orbit. 

3. 3. 3. 2. 5.4 Launch Abort Separation 

Abort modes using- the Gemini li re-entry module shall be capable of 

using either the retrograde propulsion system or the on-orbit separation propulsion system to produce separation from a malfunctioning 

flight vehicle. 

3. 3. 3. 2. 5. 5 On-Orbit Separation 

A propulsive capability shall be provided to separate the Gemini B 

• r* from the Laboratory Vehicle on-orbit. The separation propulsion 

shall not impose detrimental effects on the Laboratory Vehicle. Sufficient separation distance shall be developed to preclude imposing 

detrimental effects on the Laboratory Vehicle by the operation of the 

retrograde motors. 

3. 3. 3. 2. 5. 6 Retrograde 

The retrograde system shall provide an impulse sufficiently large to 

provide safe re-entry conditions from the nominal orbit and any intermediate orbit with one motor not operating. 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 Gemini B shall have the capability for providing power for ascent - 

abort, on-orbit post separation, re-entry and retrieval. The Labor-- 

atory Vehicle shall supply Gemini B power as given in 

• 

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paragraph 3. 3. 1. 1. 2. 2. Provisions shall be made for utilization of 

ground power prior to launch and for all ground checkout. • 

3.3.3. 2. 6.2 Electrical Power Supply 

Electrical power supply shall consist of a dc power source; ac power, 

as required by specific systems, shall be supplied by inverters and 

regulators considered a part of the utilizing system. There shall be 

redundancy in all power sources.Re-entry power sources must be 

active during the launch phase for abort purposes. Independent and 

redundant power sources shall be provided for pyrotechnic circuits.. 

3. 3. 3. 2. 6. 3 Electrical Power Distribution 

A capability for distributing the electrical power from the power supply'tb the using system shall be provided. The spacecraft structure 

shall not be used as an electrical current path. The system negative 

shall be grounded at one point only in the spacecraft. A compatible 

grounding network between Gemini B, Laboratory, and Titan HI shall 

be designed to maintain this concept. 

3. 3. 3. 2. 6. 4 Electromagnetic Interference 

Electromagnetic interference (EMI) of the Gemini B shall be minimized 

consistent with the requirements of SSD Exhibit 64-4. Reference paragraph 4. 1. 2. 5. 

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

3. 3. 3. 2. 7. 1 Basic Time Reference 

An electronic capability shall. beprovided to furnish accurate accounting of elapsed time, time-to-go, and time correlation. A reset 

capability shall be included. 

3. 3. 3. 2. 7. 2 Event Timer 

A capability for providing short-term timing of function shall be 

provided. 

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3.3.3.2.8 Pyrotechnic Requirements 

3. 3. 3. 2. 8. 1 General (U) 

The Gemini B shall have the capability for actuating, severing, separating, deploying, sealing, and jettisoning by utilizing pyrotechnic 

devices. 

3.3.3.2.8. 2 Safety (U) 

Actuation of pyrotechnic devices shall not endanger the crew or damage 

adjacent systems. Installation of pyrotechnic devices shall be so 

designated that the hazard to launch ground crews is minimized during 

assembly and checkout of the Gemini la. All possible precautions 

shall be taken to preclude inadvertent initiation of pyrotechnic devices. 

E-lectromagnetic Compatibility requirements for these devices must be 

consistent with SSD Exhibit 64-4. The requirements of AFWTRM 

550-2 will be met by all pyrotechnic devices. 

3. 3. 3. 2. 8. 3 Effectiveness (U) 

All functions requiring the use of pyrotechnic devices shall utilize 

either redundant devices or have an alternate mode of operation. 

3. 3. 3. 2. 9 

3. 3. 3. 2. 9. 1 

Landing Requirements 

General (U) 

The Gemini B re-entry module shall have the capability to return to 

the earth's surface by deployment of recovery devices. The capability 

for seat ejection during descent shall be provided. 

3. 3. 3. 2. 9. 2 Descent and Impact \-4) 

The rate of descent of the re-entry module shall be 32 ± 2 fps at sea 

level for a weight of 4860 lb. 

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ksr) wet 111 

thts document contains information affecting the national defense of the United States within the meaning of the Espionoge Laws. 

_II 1.0. in ii s t•rt.ran 703 and 701 the transmission of which in any mem., N. net - • • - • • 
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CONFIDENTIAL 

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 1.1 g 

Down 15 g 

Left 11 g 

Right 11 g 

3.3.3.2.9.3 Flotation (1-1 ) 

Following water impact, the Gemini B shall float in a crew hatch-up 

position. Provisions for additional flotation gear to be manually secgred to the Gemini B by recovery force personnel shall be provided. 

3. 3. 3. 2. 10 Post- Landing and Survival Requirements 

3. 3. 3. 2. 10. 1 Location (U) 

The means for location of the re-entry module and 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 VHF voice and VHF recovery beacon capability. Location aids 

in the re-entry module shall be operable for a post-landing period of 

36 hr. 

3.3.3.2.10.2 Flight Crew Safety (U) 

Sufficient food and potable water shall be provided for a post-landing 

period of 48 hr. Equipment to permit flight crew survival outside the 

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

Gemini B shall be capable of floating in water while maintaining an 

interior environment permitting crew survival inside the crew compartment for a continuous period of not less than 36 hr after touchdown in water. 

• 

3-96 

FO F 4

This document contains information affecting the notional defense of the United States within the meoning of the Espionage Laws, 

SSD AUG 62 20B Title 16, U.S.C., Section 793 and 794: the transmission of which in any manner to an unauthorised person is prohihited by low 
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3. 3. 3. 2. 11 Flight Crew Transfer Requirement 

3. 3, 3. 2. 11. 1 Normal Mode (1!) 

Sufficient free volume shall be provided to permit either. crewman to 

open, stow,, and subsequently re-install and latch the transfer hatches. 

Hatch and tunnel size shall be large enough to preclude trapping of the 

crewman Ills emergency ,c)1 tt suit «, CCIRTS (luring transtfer. 

Positive stowage of the transfer hatches shall be provided to prevent 

damage during transfer and on-orbit storage. 

3. 3. 3. 2. 11.2 Back-up and Emergency Modes (U) • 

'rile regular 'egreSs hatches used for backup extravehicular transfer 

shall remain closed after transfer of the. last crewman. Provisions 

"gliall be made for opening and closing the hatches from inside and outside Gemini B while in a pressurized suit: Provisions shall be provided for handholds, etc. on the exterior of the Gemini B. 

3. 3.. 3. 2.. 12 FliEht Crew Equip:r.lent ar:1 Display Requirements 

3. 3. 3. 2. 12. 1 General (U) 

The design and arrangement of the flight crew station shall be based 

on seating two crew members of a size consistent with the requirements of paragraph 3. 3. 5 in a side by side arrangement. The crew. 

members shall be clothed in MOL pressure suit assemblies. 

3.. 3- 3. 2.. 12.2 Dis-pla-ys sm;'2. CrT., s1Etc`4)) 

Display and control capability shall be provided to permit the flight 

crew to monitor and manually control Gemini B functions consistent 

with the requirements stated herein. Display capability to satisfy 

the malfunction detection system (MDS) requirements (paragraphs 3. 3. 3. 2. 16 and 3. 3. 6) must be provided. Control provisions 

must be included to permit shutdown of the Titan III engines by the 

CO1111YENTAL- 3-97 

This document contotns rniormotton affecting the noifonol defense of The United Srotes within the znecaung of the Istrr-4sn'iff 

Tale 1$, U.S.C. Section 793 and 794, the itoninussion of which in ony manner to on unauthorized Person rs prohrhited by bu 
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flight crew while in the Gemini B. Capability to control the Laboratory Vehicle ACTS shall be provided. Pertinent Laboratory system 

status display capability and control of critical Laboratory functions 

shall be provided consistent with the requirements of paragraphs 3.1. 1. 1. 5. 5 and - 3..3.2. Control provisions for safety of flight 

functions shall be operable hv the crew in either vented or pressurized' suits . 

3. 3. 3. 2. 12. 3 Flight. Crew, Seating (U) 

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 

shell include the capability of successfully ejecting the crew members 

from the re-entry module for rertain modes of launch and ascent 

phase abort,. and for emergency landing. 

3.3.3.2.13 Communications and Command Requirements 

3.3.3.2.13.1 General (U) 

The AFSSD developed Space-Ground-Link System (SGLS) suitably 

modified for Gemini B shall be used to provide the main functions of 

two-way voice communications, spacecraft to ground telemetry. 

tracking, and digital command from the ground. These functions 

shall be supplied only when the Gemini B is active. Provisions shall 

be made for inter-communication between the crew at all times. 

Recovery aids shall be provided. 

3.3.3.2.13.2 Voice Communications (D) 

In addition to SGLS, one UHF and one HF two-way voice communication system shall be provided. A capability for post-landing 

operations with a primary voice communication mode and a back-up 

beacon mode shall be provided. 

3-98 --1111filEffflAtThis document contains information affecting the notional defense of the United Stoles within the meaning of the Esp.onneje flows: 

rale 19. U S C . Section 793 and 794. the•ttonsinission of which in any manner to an annuthni....4".,...:,- - • 
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3. 3. 3. 2. 13. 3 Telemetry 

A capability for spacecraft-to-ground real-time telemetry shall be 

provided. This telemetry capability shall be continuously available 

when in sight of a ground station during ascent, loiter, and re-entry 

phases. During the on-orbit phase, the telemetry capability shall be 

available on call.. The Gemini PCM format shall be used. Suitable 

interface modifications shall be provided for integrating and establishing compatibility of SGLS with the Gemini instrumentations. 

3. 3. 3. 2. 1 4 Tracking.and Recovery 

SGLS and additional aids for flight phase radar tracking and for postlanding 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 Unternational distress frequency of 243 Mc shall be provided. 

3. 3. 3. 2. 13. 5 Command 

A capability for ground to spacecraft command transmissions and 

receptions shall be provided. The Gemini command format shall be 

used. Suitable interface modifications shall be provided for integrating and establishing compatibility of SGLS with the Gemini digital 

commands. 

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 Laboratory 

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Vehicle. The system required for intercommunication shall be 

compatible with the systems required for vehicle to ground voice 

communications. 

3.3.3.2.14 Flight Crew Training Equipment 

Training equipment, as appropriate, shall be provided to accomplish 

Flight Crew Training in accordance with paragraph 3. 3. 12. Portions 

of the Gemini B procedures trainer shall be designed for integration 

into the MOL Mission Simulator. 

3.3.3.2,15 Gemini B Peculiar Ground Systems 

3.3.3.2.15.1 Gemini B Peculiar AGE 

3,3.3.3.2.15.1.1 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. Maximum utilization shall be made of existing or 

modified NASA Gemini designs. The Gemini B AGE utilized at VAFB 

shall be functionally identical to the AGE utilized at the contractor's 

facility and the AGE utilized during factory acceptance. 

3.3.3.2.15. 1.2 Performance 

The Gemini B segment peculiar AGE shall include all the equipment 

necessary to transport, handle, store, verify, calibrate, checkout, 

monitor, record, service and control the Gemini B segment. This 

AGE shall be capable of providing a means of (1) verifying the proper 

operation of the Gemini B segment to assure successful operation of 

all systems during all segment test and factory acceptance, (2) determining whether the Gemini B segment is operable within prescribed 

limits, and (3) identifying to the black box and/or replaceable component areas of failure or operation outside of prescribed limits. This 
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-11114f-ffrifflAt--- 

AGE shall form a part of the OV AGE and will also support the integration of the Gemini B with the other elements of the OV and the 

Titan III. 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. 

3.3.3.2.16 Flight Crew Safety Requirements 

3.3.3.2.16 1 General Nc4) 

The flight crew safety contribution of the Gemini B shall include both 

that provided by the inherent safety of the Gemini B design when the 

syttem is operated in a normal manner and by the crew escape/ 

mission abort systems and/or operating modes for abnormal system 

operation and malfunctions. Crew fatalities as defined here are those 

fatalities attributable to the mission phase prior to recovery and subsequent to SRM ignition. 

3.3.3.2.16.2 Inherent Safety X-4) 

Inherent safety is provided by ensuring the compatibility of the Gemini 

B system and spacecraft capabilities with the conditions and environments imposed by normal operation and by the effectiveness of the 

systems and subsystems. The probability that a crew fatality will 

result from any kind of failure .of the Gemini B shall not be greater 

than 0.001. 

3.3.3.2.16.3 Safety During Mission Abort \-4) 

When an abort is required, the use of the abort/escape systems combined with the inherent safety of the Gemini B shall allow a probability 

of crew fatality no greater than that called out in the table below. The 

table shows the maximum allowable probability of crew fatality as a 

function of flight phase in. situations in which an abort is required. 

-CONFIDENTIAL- 3-101 

This document contains information affecting the notional defense of the United Stoles within tht. inenntng of the Ittt■ ntinfiol tws 

ittio 18. U.S C Section 703 .and 794. the ttensnossion of which in any mann*, to on urovth,,• ∎ ced Pvion to t", 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Stage During Which Maximum Probability of Crew Fatality 

Abort Occurs If An Abort is Required 

Stage 0 Operation 

Any Other Launch Vehicle 

Stage Operation 

Orbital Operations 

0.100 

0.020 

0.001 

The probability that the Gemini B shall cause a mission abort shall 

not exceed 0.0001 for the entire mission. 

3. 3. 3. 3 Functional Interfaces(u) 

(Functional interfaces shall be listed here when defined by the cognizant Interface Control Working Group - ICWG) 

3.31.4 Contract End Items (u) 

(The contractor shall proVide for incorporation in this paragraph a list 

of the Contract End Items by CEI specification number, nomenclature, 

and the CEI into which it installs. This paragraph shall list all end 

items being provided under these system segments. ) 

3:-102 

--COMEIHAIE 11 4 -

MS document (ontten% informotton effecting the notional defense of the Untied Stoat %% ohm rho meomng of the Neonege 

Title le, U.S C.. Sechon 793 and 794. the tronsmtslion of which in any manner to on unaufhowert (teflon I% ntoatuted by Ina 
.*••••■■■•■•1•111■110. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CONFIDE: IAL 

3.3.4 . Mission Payload System Segment 11S..4) 

The Mission Payload System Segment shall utilize al-v 

Mission Module (unpressurized, ten feet in diameterand -aoximately:36'feet 

located aft of the Laboratory Module. Control and display consoles necessary 

to the operation of mission payloads will be accombtated itithin the pressurized 

section of the Laboratory.Module as stated in paragraph 3.3.2.2.11. 

The specifications of t4e Mission Payloads will be provided 

separately. 

3.3.4.1 Allocated Performance and Design Requirements 

3.3.4.1.1 Effectiveness 

Effectiveness requirements for this segment are specified in 

.rparagraph 3.1.3.1.2. 

3.3.4.1.2 Weight 

The weight allocation for this segment is specified in 

paragraph 3.3.1.1.1. 

3:3.4.1.3 Electrical Power 

The electrical power allocation for this segment is specified 

in paragraph 3.3.1.1;2.4. The allocation per referenced paragraph shall be 

supplied to the Mission Payload Segment by the Laboratory Vehicle Segment. 

Mission Payload power requirements in excess of the allocation of paragraph 

3.3.1.1.2.4 shall require a corresponding adjustment of the weights 

allocation given in paragraph' 3.3.1.1.1. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET SPECIAL HANDLING 

3.3.4.2 Mission Payload Performance and Design Requirements 

3.3.4.2.1 General 

The purpose of this section of the specification is to present a 

definition of the Dorian System by defining and describing the major subsystems 

and components; defining the system specification tree and system segment list; 

and listing the contract and items. 

Manned Flights 

The Orbiting Vehicle is composed of the Gemini B System Segment, 

the Laboratory Vehicle System Segment and the Mission Payload System Segment. 

Automatic Configuration 

The Orbiting Vehicle consists of the Laboratory Vehicle System 

Segment and the Mission Payload System Segment (which includes the DRV Section). 

3.3.4.2.2 Mission Payload System Segment Description 

The Mission Payload System Segment includes the Mission Nbdule 

Section, the Photographic Section, and the Data Re-entry Vehicle (DRV) Section. 

The Mission Module Section includes additional Dorian System equipment located 

in the Laboratory Module. The major Dorian System items are shown in Figure 

3-7 for the manned automatic configuration and in Figure 3-8 for the automatic. 

configuration. 

The Dorian System consists of a high resolution optical reconnaissance sensor and suitable control, recording, and processing equipment. 

The image recording equipment will be dual frame cameras capable of photo 

graphing the target image at approximately one frame/second. Upon being 

reflected by a tracking mirror, the ground target image will pass through the 

photographic optics, consisting of a primary mirror, two folding mirrors, and 

a Ross corrector assembly, into the camera located in the Laboratory Module. 

The ground target will be tracked by the tracking mirror, servo-controlled by 

an on-board command and control system. Latest ground computed ephemeris 

information will be continuously updated using an accelerometer. Vernier 

Control of the tracking mirror will be provided utilizing star tracker and 

rate gyro subsystem together with an image motion detector. The stereo angle 

range of the tracking mirror will be +300 to -400 with an oliquity angle range 

of 4- 400. 

Manned Automatic Configuration 

The astronaut will have the capability of overriding the automatic 

tracking mirror control to minimize image motion at the center of the format 

or to center the particular point of interest within a given target area. 

-steRESPECIAL HANDLING 

3-104.1 
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Normally„itarget photographic operations will be automatically controlled; 

however,-during manned flights, the astronaut will be able to acquire the 

target using an acquisition and tracking scope having a zoom lens. A 

target cue display will be available to aid in target recognition. The 

astronaut will also have the capability to monitor (and, if desired, control) 

final target centering and tracking rate error reduction using the primary 

optical system. 

The capability will be provided in the Laboratory Module for 

manned flights, to process selected indiVidual frames of photography through 

a readout system and relay selected portions of these frames to the ground. _-/ 

Recovery of the primary record will be by means of small Data Re-entry 

Vehicles (DRVi s) launched from the Laboratory Vehicle and the Gemini B 

spacecraft. A more complete description of the Photographic Section may 

be found in 3. . 

Automatic Configuration 4 

Data will be returned by means of four DRV's,(larger than -those 

of-the-manned_version). These DRVI s will be supported in and released from 

the Support Module which includes the nose cone of the vehicle. 

3.3.4.2.3 Weights 

The Mission Payload System Segment weight budget is as follows: 

Manned Automatic Automatic 

Photographic Section* 4800 

Data Re-entry Vehicle Section 380 

Peripheral Equipment*** 1020 

8330 

* Includes camera, visual optics, alignment and focus equipment, 

film transport, and film. 

** Includes weight of nose fairing and DRV launcher in Laboratory. 

*** Includes reconnaissance consoles (manned only) data readout 

system (manned only) acquisition and tracking system (manned 

only), star tracker and rate gyro subsystem, Image Lotion 

Detector and other miscellaneous payload support equipment. 

3.3.4.2.4 Electrical Power 

Electrical tower will be supplied by the laboratory fuel cells. 

The drubmic characteristics of the mission payload electrical system are 

(later). The on-orbit average power allocated for Mission Payload System 

Segment is watts. Allowable peak transient are (later) 

SPECIAL HANDLING 3-104.4 
NRO 

REL F1A,DLING SECRET _ 

3. 3. 4. 2. 5 Disturbances Due t o Mission Payload Equipment 

The torque disturbances due to outgassing, magnetic materials and other 

sources of external torque shall not exceed ft. lbs. or a 

total of ft lb sec for the 30-day mission. 

The torque disturbances due to internal moving parts shall be kept to a 

minimum. Examples of moving parts are the mirror, the film transport, 

the astronauts, doors and other pieces of equipment such as DRV's, tracking 

scopes, etc. The torque disturbances due to internal moving parts shall 

be kept to a minimum. Examples of moving parts are the mirror, the film 

transport, the astronauts, doors and other pieces of equipment such as 

DRV's, tracking scopes, etc. The changes in OV 'angular momentum required to put these devices into motion shall not exceed the following during 

the period beginning one minute before and ending-immediately after an active 

photographic pass: 

Yaw angular momentum 

Pitch angular momentum 

Roll angular momentum 

The total accumulated magnitude of angular momentum changes which exceed 

these values outside of the period of an active photographic pass shall not be 

more than the following: 

Yaw angular momentum 

Pitch angular momentum 

Roll angular momentum 

System Coordinates 

The Orbiting Vehicle coordinate system definiti-lans for the 

manned and unmanned versions, are given in Appendix A 

SPECIAL HANDLING 
SPECIAL HANDLING 

1-4.044 6C, 

%MARA tDLING 

3.3.4.2.7 Design Considerations 

Mission Payload design criteria shall be such as to minimize 

launch base test requirements and to maximize payload security. 

3.3.4.2.8 Flight Termination System 

There are no functional flight termination system requirements for the Mission Payload. Launch abort and equipment recovery will 

include security provisions for Dorian System equipments (e.g., target cues). 

3.3.4.2.9 Explosive Devices, Squib Simulator, etc. 

Chaptor 10 of AFWTRM 550-2 provides guidance to range users 

regarding design, installation, and checkout of ordnance items. Generally, 

explosive devices must be designed to permit installation as late as possible 

during the pre-launch phase. 

3.3.4.2.10 Launch Safety 

The design of the NM/Dorian System shall be such that hazards 

to personnel during the pre-launch, checkout, and launch operation is minimized. 

Applicable documents on ground safety are listed in Section 2.0 with the 

prefix letters SF. Particular attention is called to the WTR Range Safety 

Manual (AFWTRM 550-2). 

3.3.4.2.11 Umbilicals 

It shall be a design goal to minimize the use of umbilicals 

to the Mission Payload System Segment during launch pad integration and 

checkout. If possible, the Mission Module Segment power, instrumentation, 

air conditioning, and computer programming requirements will be provided via 

the Laboratory Vehicle AGE. Proper terminal equipment must be provided to 

maintain required mission security. 

3.3.4.2.12 Weight and Balance 

It shall be a design objective not to require weight and 

balance equipment at the launch base. Final weight and balance adjustment 

shall be performed during the mission module/laboratory module integration 

and checkout prior to shipment to the launch base. 

3.3.4.2.13 Alignment 

(later) 
NRO APPROVED 

SPECIALLYHANDLING 

3.3.4.3 Mission Module Section 

3.3.4.3.1 Mission Module Structure 

(later) 

3.3.4.3.2 Thermal Environment Control Subsystem 

(later) 

3.3.4.3.2.1 General 

It is required that the environmental control system not 

limit the photographic sensor operation. 

3.3.4.3.2.2 Ground Conditioning 

(later) 

3.3.4.3.2.3 Powered Flight 

(later) 

3.3.4.3.2.4 Orbital Flight 

(later) 

3.3.4.3.3 Command and Control Requirements 

3.3.4.3.3.1 General 

The Mission Control Subsystem (MCS) shall provide for the 

commanding of the cameras, optical equipment, and other mission module functions. 

The Satellite Control Facility shall be used to the maximum extent for the 

determination of the parameters used by the MCS. On-board data processing 

shall be used as required to meet performance objectives. The MCS shall be 

designed to support the Dorian System either manned or unmanned. 

3.3.4.3.3.2 Main Optics Tracking 

The MCS shall provide closed loop control of the tracking mirror. 

The accuracy and resolution of the digital interface with the motors and 

instruments shall be designed for compatibility with the mirror servomechanisms. 

The tracking equations and digital interface shall provide for control of the 

mirror with errors contributing no more than 0.07 percent to image motion. During 

a single forward to rearward track, the MCS shall provide for mono or stereo 

photography of a single target or a target cluster. Target cluster requirements 

are specified in Section 3.3.4.3.3.7. 

SPECIAL HANDLING 3-104.7 
SKEGKELTANDLING SECRET 

3.3.4.3.3.3 Orbital Position Determination 

The MCS shall determine the position of the vehicle on orbit 

by interpolating an ephemeris table. A description of the orbit spans required 

for photography shall be accepted from any SCF tracking station by the MCS. 

Without the use of on-board instrumentation, orbital positions as defined by 

the MCSAUting, the4hotograPhic-Spanb thailltave:the following two sigma 

accuracies 12 revolutions after the orbit definition has been loaded (22 

revolutions after the determination span): 

In-track 0.2 mile 

Cross track 0.1 mile 

Altitude 0.1 mile 

An in-track correction bias shall also be accepted from the tracking station. 

In addition, the output of an accelerometer shall be integrated to establish 

the in-track error resulting from drag. With proper accelerometer performance, 

the two sigma in-track error shall be no greater than 0.1 mile (22 revs after 

the determination span). 

Manned Automatic Configuration 

Manual hand controller inputs shall be accepted from the crewmen to correct the in-track and crosstrack reference. 

3.3.4.3.3.4 Image Motion Compensation 

By further processing theAprbit definition (3.3.4.3.3.3) and 

accelerometer inputs, the image motion shall be determined to sufficient 

accuracy to reduce the image rate at the center of the format to less than 

0.07 percent. An image motion detector shall be provided. The ICS shall 

provide information to the image motion detector equating to a V/h error no 

greater than one percent. The image motion detector shall return error signals 

or measurements. 

As an objective, the image motion detector shall measure both 

the in-track image motion error and the cross component resulting from yaw 

error. 

Manned Automatic Configuration 

Manual hand controller inputs shall be accepted from the astronaut 

to correct image rates. These corrections shall apply to the orbit reference, 

and affect following targets. The processing of image motion detector inputs 

to the MCS shall be an astronaut option. 

3.3.4.3.3.5 Payload Attitude Measurement 

Two or more star trackers shall be integrated into the mission 

module. The mounts for these trackers shall be positioned and designed for 

3-3JObr.8 
NRO APPROVED FOR 

RELEASE1JULY201 5pr,, 

os,PLILING SPECIAL- • • 

the maximum correlation between the_star tracker reference and the optics 

pointing reference. Two of the star trackers will normally be tracking 

during photographic operations. The specific stars to be tracked shall be 

determined by ground data processing. .A.ssuming an in-track error no 

greater than that specified in 3.3.4.3.33 nester tracker system, shall 

establish the attitude of their mounting axis with respect to the local 

vertical and the orbit plane with two sigma errors no greater than 1.5 

minutes. Prior to acquisition, the MCS shall point the axis of the tracker 

to the line of sight to the star with an error no greater than 2 degrees. 

The number and reliability of the star trackers shall assure 

that the probability of two or more trackers working at the end of the 

mission is 0.95. 

3.3.4.3.3.6 Camera Control 

The MCS shall provide open loop adjustments and commands, 

and off-axis image motion compensation servo control. The opin 

loop adjustments shall include exposure (slit control),focus (correction 

for slant range and focal length), and a cycle command. Either open loop 

or closed loop servo commands shall be provided to the platen and/or slit 

as required for across the format IMC. Calculations for this INC control 

shall be performed by the MCS. 

Error signals shall be accepted from a focus sensor and a 

boresight light tracker. The focus sensor shall provide signals correlating 

with the apparent error in focal length for the scene under observation. 

Open loop operations shall be provided by recording foCus error signals for 

ground analysis, and subsequent platen commands. In addition, the MCS shall 

provide for closed loop focus by filtering. .- the error signal to test suitability of the scene, and then by automatically commanding platen adjustments. 

The MCS shall accept error signals from the boresight light 

tracker for system alignment. When operating with a source of collimated 

light within the optical system, the MCS shall drive alignment servos to 

null the error. Both open loop and closed loop operation shall be provided. 

As an objective, the MCS also shall use the boresight light tracker to track 

a light source on the ground. Following ground processing of the. error 

signals, the MCS shall accept an alignment matrix from the ground relating 

the star tracker reference to the apparent optical axis reference. 

r+V. 

0,1 

t 1 1 

'Ast 

SP EMI. Mt:DUNG 
NRO APPROVED FOR 

RELEASE 1 JULY 201 v P 

SPEW_ ViggLAVA c-- 

The MCS shall provide information to the camera data lamps. 

This information shall include a convenient rev. and frame identifier, tine 

which can be correlated to within one millisecond of GMT (post flight), '. 

the exposure setting, and information allowing the determination Of the 

angle between the LOS to the target and the local vertical with an error 

no greater than 2 minutes of arc (2m). 

Unmanned Version 

The MCS shall provide a discrete to the camera system for 

looper replenishment. This discrete shall be issued at a time when the 

starting and stopping of the film cassettes does not adversely disturb 

system operation. Additional discretes shall be provided for film wrapup, 

cut, and seal. 

Manned Version 

The MCS shall provide' control signals to select the film 

to be positioned for each exposure or to tag the- frames to be processed 

on-board. 

3.3.4.3.3.7 Sequential Control 

The MCS shall provide for the sequential control of the 

Mission Payload Segment. This function shall include the execution of real 

time commands within one second of their receipt, and the execution of 

stored commands within 200 msec. of the time indicated by their associated 

time label. Stored commands shall be employed for housekeeping tasks not 

directly related to photography. 

During a single forward to rearward motion of the tracking 

mirror, the MCS shall sequence the events required to photograph a single • 

target, or a club-ter of targets. Nominally, a single target will be photographed in stereo with three different exposure settings. The various 

exposures will be taken to improve the resolution of both the highlights 

and the shadows. When photographing target clusters, the available time 

and camera cycle constraints may limit photography to the one exposure 

setting calculated by the MCS using sun angle and scenecontent informaiion. 

The cluster or target definition provided by the ground shall specify the 

exposure ground rule, stereo angle, and specific target for each frame. 

Clustered targets may be defined as.offsets to the first target in the 

cluster to be photographed. 

SPECIAL HANDLING 

3 P731Piv:34)o 
NRO APPROVED FOR 

OS? gj S 

RELEASE 1 JULY 2015 

a HP 3k 

• ••■• 

Manned .Version 

When photographing a target clustero manual hand controller input 

correcting position for the first frame shall apply to all targets in the cluster. 

Rate corrections shall be accepted throughout the sequence. 

3.3.4.3.3.8 Thermal Door Control 

The MCS shall control the thermal door servos. The dooi. 

positions shall be controlled to limit the heat energy entering the 

tracking mirror bay without obstructing the light from the target. The 

acceleration of the doors shall be controlled by the MCS to hold disturbance 

torques to an acceptable level. ,e 

3.3.4.3.3.9 Target Acquisition and Selection (Manned plights) 

Two acquisition and tracking scopes shall be provided to 

assist the astronauts in their selection of the target and tie reduction of 

pointing errors; The MCS shall provide for the closed loop control of these 

two optical devices using an:interface similar to that provided for the 

primary tracking mirror. Both astronaut stations shall have the capability 

to observe theiimagefrom either acquisition and tracking scope, or from 

the primary optics. Manual hand controller' inputs shall be accepted - f p= the , 

astronaut to perform the functions listed in 3.3.4.3.3.1=and3,3-.4;3.3.4 

and to slew the acquisition scopes in a manual search mode. The MCS 

shall store and process a matrix relating the axis of the main optical system 

to the axes of the two acquisition and tracking scopes. 

Alternate targets (or target clusters) shall be available 

to the astronaut to permit the circumvention of weather. The selection 

of options for the target or cluster following any given target or cluster 

shall be prepared at the Mission Control Center. Thettarget optionhshall 

be transmitted to the vehicle either as earth referenced coordinates, or 

as designators of targets stored in the vehicle. 

Controls shall be provided for the designation of targets 

by the astronauts and for their comments relating to the estimated quality 

of the photography. 

The MCS shall provide open loop commands to the astronaut 

cue system. These commands shall result in the automatic presentation of 

the target cueing aids required by the astronauts to center the targets 

or properly position the offset reference. 

SPECIAL .HANDLII. 
EtfAIFAANDLING 

3.3.4.3.3.10 MCS Telemetry 

Two data services shall be provided to the telemetry system 

from the MCS computer: real time diagnostic data and a stored mission 

reporting service. 

Real time diagnostic data shall be provided at a rate 

between one and five kilobits per second. These data shall contribute to 

the analysis of control system performance. This diagnostic data shall 

include all control signals interfacing with the computer software. 

The mission reporting service shall provide a summary of 

system operation during the photographic pass. This service shall be 

provided at a rate between 500 and 1200 bits per second to permit direct 

transfer to data lines between the tracking station and the Mission 

Control Center. Operational data on each photograph shall be included. 

In addition, critical instrumentation shall be reported as a backup to 

the vehicle telemetry recorder, the SGLS ground station, and the SCF 

data processing system. 

3.3.4.3.3.11 Reliability 

The MCS shall be designed to survive failure. After any. 

single failure, the MCS shall be capable of supporting a productive 

mission. The equipment shall be organized to support an efficient test 

of the redundancy. It shall be a design objective that this redundancy 

be achieved with a minimum of additional equipment configured so that 

failure may reduce capability but not abort the mission. 

:3.3.4.3.4 Electrical Power and Distribution Subsystem 

(later) 

SPECIAL HANDLING 

-33=afor4127 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET SPECIAL HANDLA 

3.3.4.3.5 Data Readout Subsystem (Manned Flights only) 

A readout subsystem shall be provided for the transmission of 

photographic information to the ground. The primary requirements for this 

system are quality and security. The secondary requirements are quantity, 

economy, astronaut convenience, and reliability. A standard SCF S-band data 

link operating at 20 MBPS shall be employed. 

3.3.4.3.5.1 Resolution 

As a design objective, the data readout subsystem shall scan 

and transmit pictures with no loss in resolution. It is required that the 

loss in photographic resolution due to scanning and digitizing shall be no 

greater than 20 percent. 

3.3.4.3.5.2 Quantity 

The readout subsystem shall read out the maximum area of photographic material consistant with the other requirements in Section 3.3.4.3.5. 

It shall be a design requirement to read out 5 square inches in 5 minutes, and 

a design goal to read out 100 square inches in 5 minutes. 

3.3.4.3.5.3 Operational Employment 

Operation of the readout subsystem shall require a minimum of 

the astronaut's time. The scanner shall accept portions of various pictures 

which have been edited by the astronaut. It shall be a design goal that the 

astronaut not be required to assist the scanning operation over a tracking 

station. 

The number of tracking stations equipped for readout will be 

a function of the ground equipment costs. Decryption and processing of data 

at the tracking station is not required) but may be performed if it contributes 

to quality or economy. 

3.3.4.3.5.4 Security 

Encryption equipment will be provided (Tit. 

--sEeREt- spun. mouNG 3-104.13 
OV UFOR 71(1 JU ,i ;Ss 

1'17, 7"12 

Acquisition and Tracking Scopes (Manned Flights Only):,_ 

Two acquisition and tracking scopes for redundancy and • 

efficiency of target acquisition shall be an objective. The optical 

axes of the scopes can be positionedfrom+70° to -40° in-track and 

+45° crosstrack. Position and tracking rate data from the scopes will 

be fed to the computer for main optics acquisition. 

3.3.4.3.4.1 Magnification Range 

The scope image will be a 5X magnification with a zoom 

capability to give 25X. It shall be a design objective to also provide, 

IX for wide field of view. 

.3.3.4.3.6.2 Field of View 

The apparent field of view will be 20°, but at the magnification of the eyepiece (5X) the astronaut will see a 40 field. 

3.3.4.3.-6.3 Alignment 

The scopes will have the capability of being boresighted 

with the main optics while on-orbit. 

3.3.4.3.6.4 Display 

The view from each scope will be available at both astronaut 

stations. A 

3.3.4.3.6.5 Scope Control 

The acquisition and tracking scopes will be servo driven 

using independently controlled positioning servo systems. The input signals 

will be supplied from the 14M- and from the controlling astronaut's handEcontro11 

motion. Each astronaut will have control capability for both scopes. The 

gimbal arrangement and optical-dynamical effects should be as close as 

possible to the Tracking Mirror Control. The torquer and equilization. 

design will give consideration to the astronauts abilities and should 

maximize efficient use of this capability. Consideration of a quickened 

reticle; wave form input spectrum and noise effects should be included' 

in order to simplify the tracking task; provide specified accuracy) damping 

and response for the overall subsystem. 

SPECIAL. HANDLING 
NRO APPROVED FOR 

SPtCJJ Cl 1ANDLING • 

3.3.4.3.7 

.7 

Astronaut Viewing Capability (Manned Configuration) 

A lookout capability will be provided, permitting the 

astronauts to scan the entire volume beneath the Orbiting Vehicle, 

360° in azimuth, at elevation angles up to and including at least 900. 

At a magnification of 1X, the field of view shall be at least 20°. 

The lens system will also have to capability to zoom to a Tagnification 

of 5X. The capability to determine the relative position ot:ob4eta 

within the field of view to within degrees in both azimuth and 

elevation is required. 

Consideration shall be given to providing the above 

capability in the Acquisition and Tracking Scope or with a separate 

instrument. (Also st462.43.2../aq.7)2,3, 2.7,/, ) 

SPECIAL HANDLING 

3.74410,6 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.3.4.4 

SEC K 11 SPECIAL HANDLING 

Data Re-entry Vehicle Section 

3.3.4.4.1 General Requirements 

Manned Automatic Configuration 

The Data Re-entry Vehicle Section (DRVS) shall include one to 

three Data Re-entry Vehicle (DRV's) and shall support, house, and protect the 

DRV's, a launcher tube, and auxiliary electrical and mechanical equipment 

required to control DRV separation. 

The DRVS launcher tube shall be adequate to contain one re-entry 

vehicle approximately 22 to 33 inches in diameter at its mounting base and 

130 lbs weight with 20 - 60 lbs of data capsule capacity. The data capsule is 

defined as the film container in the DRV. The launcher shall be located at 

the proper re-entry angle assuming a normal level attitude of the Orbiting 

Vehicle at separation. 

The DRVS shall be located in the Laboratory Module (LM) which 

shall provide the required space and the environmental control as specified 

herein. 

In the event a DRV does not eject from the DRVS launcher, the 

capability shall exist to retrieve the film and re-seal the DRVS launcher 

as required. 

Automatic Configuration 

The DRVS* shall include four DRV's and shall support, house, 

and protect the DRV's and auxiliary electrical and mechanical equipment to 

control DRV separation and provide environmental control. The DRYS shall 

also serve as the nose cone of the launch vehicle and shall be designed to 

withstand the launch and ascent environment. 

The DRVS shall be adequate to support four DRV's approximately 

33" in diameter, 43" long, and 374 weight (including film). The DRV's will 

be supported at the proper re-entry angle assuming the OV roll axis is normal 

to the local vertical at separation. 

3.3.4.4.2 DRVS Structure and Packaging. 

a. Accessibility 

(1) DRV Installation and Removal 

(Later) 

* In the automatic configuration the DRVS is contained in the Support Module. 

---SE-eRET--SPECIAL HANDL! 3-104.16 
. NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HAN OLING • (2) Retro-rocket Ignitor-installation 

The safety problem associated with the solid retrorocket will possibly require shipment of the assembled DRV prior to installation of the rocket ignitor or initiator. The design of the rocket 

ignitor shall be such as to allow shipment of a unit as completely asseMbled . 

as possible under air transport restrictions. However, if required because 

of shipping regulations, provisions shall be made to install the ignitors:, 

or initiators at the. pad without disassembling the DRV, and without invalidaVng any previous testing.. 

3.3.4.4.3 Pyrotechnics 

All pyrotechnic-operated devices will have redundant or backup pyrotechnics. Redundant pyrotechnics shall be fired from independent 

electrical circuits. All pyrotechnic devices shall be hermetically sealed 

and qualified to show no degraded'. performance afer 60 days under simulated 

orbital environmental conditions. 

3.3.4.4.4 • DRVS Environmental Control (Thermal) 

a. General 

The environmental control design shall maintain the DRV 

within the proper' temperature range. This will be accomplished, using both 

passive and active thermal control as required. 

b. Ground Conditioning 

• The ground temperature range and humidity limits are as 

per Section 3.4. The cleanliness limits are (later). 

c. Orbit 

The temperattre limits (later) shall be maintained. . 

Data Recovery Vehicle Subsystem Weight Budget 

The total weight of each DRV (exclusive of film) as defined 

herein shall not exceed 130 lbs for the manned version or 315 lbs for the 

unmanned version. 

3.3.4.4:6 Minimum Acceptable Reliability Level 

The DRVS equipment shall have a minimum acceptable.reliability 

level pf (later). 

3.3.4.4.7 Prelaunch Testing 

At the launch pad:, the DRVS will be capable of all necessary 

prelaunch tests as part of an overall system test while fully assembled 

sPECUkp ti r4Alk 1 

7 GA 
NROAPPROVEDFOR 

JUL D OR 

and mated' with the Laboratory Module. , CommandOf this testing will be 

through the vehicle command and control system and monitoring will be done 

via telemetry, The functions to be tested and the test procedure will 

be the, rsaue as those during the final acceptance tests at the factory. 

Data Re-entry Vehicle (DRV) 

DRV shall be completeede-orbiting re-entry vehicle. 

While in'orbit, it will maintain the proper environment for the film and 

will supply status data to the telemet'ry subsystem. Its capabilities (with 

manual assistance)* include: sealing as required; preparation for de-orbit 

and re-entry; and separation from the DRVS support structure. 

After separation from the DRVS support structure „the. DRV 

will transmit a radio frequency signal to provide re-entry status data and 

to act as a retrieval aid. During the atmospheric re-entry phase, the DRV 

will provide environmental protection of the film. After re-entry, the 

DRV will descend via a parachute designed for aerial retrieval. At parachute 

deployment, the DRV will provide the required lights to assure night retrieval. 

The DRV will survive water impatt and the retrieval aids will remain active 

until the sink subsystem is activated. 

' The DRV will contain a system for self-destruction if it i. 

not re-enter within a designated area. 

a. Detail Performance Requirements 

(1) General 

Mannedilutpaatie Configuration 

The DRV will be fully accessible while attached to the 

DRVS support structure. It will be capable of mechanical disassembly without 

demoting from the DRVS support structure and without disconnecting electrical 

circuits. The capability for replacement of any item or component while on 

the launch pad shall exist. The Uesign of pyrotechnic installations shall 

permit the verification of such installations without disassembly of the DRV, 

AutoMstic Confi4prstion 

The DRV will be fully accessible while attached to the 

Support Module structure: It will- be modulari-zdand designedfdr- Interchakgeability so that an unacceptable DRV can be replaced in the vehicle without 

detrimentally affecting the vehicle DRV performancef.separation, *weight, and, • 

balance constraints. The capability for replacement of any item or component 

* In -manned cortfzu:ratibiCs 

PECIAL HANDLING 

-37491M 4-8 
NRO APPROVED FOR 

RELEASE 1 LY2015 

irti iQL3WYU 

of the DRV in the OVAB shall exist. The deSign of pyrolectric installations 

shall permit the verification of such installations without disassembly of 

the DRV. 

(2) Ascent 

Manned..Wom4Iic ConfisUration 

During ascent, the DRV will maintain its interior 

pressure at or above the Laboratory Module level. 

AutomaticConfleuration 

During ascent the DRV will maintain its interior 

pressure at (later) 

(3) Orbit 

The DRV and its components will be designed and 

qualified to withstand at least 60 days in a vacuum space environment without degrading its subsequent operational capability or reliability. External 

surfaces of the DRV shall be capable of being treated with thermal paint. 

Manned-kutomatic ConfigUration 

While in the environment of the Laboratory Mbdule, 

the operational DRV will maintain its data capsule internal temperature within the range 75 + 15 degrees F. 

The DRV launcher will be pressure sealed so that in the 

event of loss of Laboratory Module pressure, the leak rate from the launcher 

will be less than 1%/day. Manual pressure relief shall be provided for 

controlled access to the DRV launcher. 

During orbit and all subsequent mission phases, the 

DRV will provide a light-tight container for the film. 

Au:tbmati4. Configuration 

The DRV and DRVS design shall be such that the film 

is maintained at a temperature of 75° + 15°F. The DRV and film chute shall 

be pressure sealed as necessary so that the Laboratory Mbdule pressure can 

be maintained at 1.5 psi. 

The DRV and film chute shall provide a light-tight 

environment for the film. 

(4) Preparation for Deboost 

The DRV will require no more than two electrical signals 

to prepare if for deboost. These two signals may be used for such purposes as 

activating re-entry batteries, starting timers, beacons, or arming programmers. 

Manned=Automatic Cotilsturkailon 343.04d4' 

The operations required for placing the data capsule 
NRO APPROVED FOR 

itatjUPtr TIVANa 

Automatic Confleguration 

The DRV and film chute design shall permit serial 

loading of the four DRV's without a requirement for film splicing. 

(5) Data Re-entry Vehicle Separation 

The DRV will be separated while the OV roll axis 

is aligned with the flight path within a tolerance of +2 degrees (three 

sigma) about the pitch, and yaw OV axes. The OV will have maximum 

rates of + .02°/second (three sigma) about all three axes. In an emergencymode, the OV attitude tolerance at DRV separation will be + 10° (three 

sigma) about each OV axis. 

Nanned=4utomatic Configuration 

The DRV separation and push-off subsystems are to 

be considered part of the launcher subsystem. The launcher subsystem shall 

spin the DRV as required for stabilization. 

Automatic Conftgurktion 

The DRV separation and push-off subsystem are to be 

considered part of the DRVS. Spin-up of the DRV will be provided by the 

DRV spin-de-spin system after separation of the DRV from the Orbiting Vehidle. 

(6) Deboost 

After separation and spin-up, the DRV will deboost 

itself from orbit by firing the retro-rocket, and de-spinning, if required, 

to a rate which will allow the proper re-entry angle and proper parachute 

deployment. The deboost operation shall result in no damage or detrimental 

effects to the Orbiting Vehicle, including the primary payload optics. 

Approximately at the time of separation, the DRV will commence transmitting 

an RF signal modulated to provide minimum operational decision data and which 

will act as a tracking and retrieval aid. This RF signal shall be of 

sufficient power and characteristics as to be received by existing tracking 

stations, ships, and recovery aircraft at a line-of-sight range. A 

redundant tracking aid shall be required. This deboost must be successful 

under worst case DRV unbalance. The deboost must also be successful from 

the emergency mode attitude limits, including both N-S and S-N re-entry. 

(7) Re-entry 

The DRV will provide thermal and environmental protection for the film during atmospheric re-entry. The DRV will be designed 

--70:17fteir----- : SPECIAL HANDLING 1-404,149 
SWPIRAffIRANDLING 

so that In-gassing will occur upon atmospheric re-entry and in such a... 

manner as to cause no damage to the film payload. The film will not be 

subjected to temperature in excess of 110°F. 

(8) Deboost and Re-entry Dispersions 

In the case of proper film handling and with. bhe 

OV under the control of the primary stabilization system at DRV separation, 

the impact point of the DRV will be wi,thin a rectangle + 75 nm in-track 

and +8 nm crosstrack (three sigma). Impact is defined as the:.latitUde and 

longitude of the DRV upon descending to 50,000 ft. In the case where the 

vehicle is in the emergency mode, the successful dispersion rectangle will 

be increased by a factor;. of 2 in each dimension. 

(9) DRV Destruction Subsystem 

In the event the DRV overshoots the predicted impact 

point, it will contain a mechanism for destroying itself and its data by . 

natural means so that:,.it'is beyond recognition upon reaching the earth. 

This destruction may occur upon recognition of the overshoot or at eventual 

orbit decay and re-entry. This destruction will not take place for an overshoot of the predicted impact point of less than 1400 nm and is mandatory 

in the event of an overshoot exceeding 2600 nm. 

(10) DRV Recovery 

(a) Primary Mode - Aerial Recovery 

Final descent will be controlled by a parachute. 

subsystem. This parachute will. provide a minimum of 20 minutes of descent, 

time on the parachute before water impact. The descent rate at 10,000 feet 

will not exceed 25 ft/sec under standard atmospheric conditions. The 

parachute system will be compatible with RCG aerial recovery gear. Night 

recovery capability is required. 

(b) Secondary Mode - Water Recovery 

Water recovery requires the radio retrieval 

aid and a flashing light system. If not covered in the air; the DRY will 

survive water impact and float such that the radio retrieval aid and the 

flashing light system are still effective. The radio frequency aid will 

be capable of operation for a minimum period of 24 hours after separation. 

The flashing light will continue to operate for approximately 12 hours after 

separation. 

SPECIAL HANDLING 3-?,) 
NROAPPROVEDFOR 

RELEV MAL HANDLAu 

(11) DRV Sink Subsystem '- 

The DRV will continue to float for a minimum of 

50 hours. The sink subsystem will flood and sink the capsule after a 

maximum of 90 hours in the ocean. A design requirement of this subsystem 

is simplicity and a negligible probability of premature operation. 

(12) Post Re-entry DRV Retrieval 

After aerial or water recovery, the US Government 

will provide shipment and control of the data capsule. A means of deactivating the DRY will be provided. A shipping container will be required 

to house the data capsule during shipment and handling after retrieval. 

The DRV design will be such as to facilitate removal of the film from.the 

DRVan'complete darkness. 

b. DRV Electrical Subsystem 

All power required in the DRAT will be supplied by the 

Laboratory Mbdule until receipt by the DAV(arthat signal which will be 

used to activate the DRV battery during the deboost sequence. 

The electrical design of the DRVS, consisting of harnessing 

and components to control and monitor the DRV status and separation, shall 

- meet the electrical design requirements of Section 3.4. 

c. Special Requirements ' 

(1) Supplemental Telemetry System 

(later) 

d. Orbit, De-orbit, and Re-entry Conditions 

The DRY shall be capable of being de-orbited properly, 

from. e.nyyposition on the following orbits. 

Orbit Perigee Altitude 70 nm to 90 nm 

Eccentricity 0 to 0.025 

DRV Orientation One optimum to be selected 

by DRV Contractor 

Orbit Plane Inclination From 65° to 125° 

. Orbit Duration 60 days 

SECRET SPECIAL HANDLINg7/01.24 
1! ' 

- ViV4DLING 

e. Data Re-entry- Vehicle Reliability Requirements 

The reliability design objectives are defined for 

operation during the period of time from launch vehicle liftoff through 

completion of recovery operations. Equipment design and component 

selection shall take cognizance of these reliability goals. The DRYS 

contractors shall consider reliability improvements through redundancy 

(and appropriate use of the astronaut in the manned version). 

The reliability goals demonstration requirements 

shall be as follows: 

(1) Reliability Goals 

Manned-Automatic Configuration 

(later) 

AutomaticConfipiation 

(later) 

Separation Subsystem 

The DRV shall be ejected so as to place it in the correct 

attitude and spin stabilized for ignition of the retro-rocket. 

SPECIAL HANDLING 

. A 

3.3.4.4.9 

RNRELogri, 
' 1112Riki 4 r 

VEDVOWSI 

LY 2015 

3.3.4.5 Photographic Section 

3.3.4.5.1 General 

The Photographic Section contains optical, mechanical, thermal, 

electrical, and structural components necessary to perform high quality, 

stereo, photographic reconnaissance. 

The available volume for photographic section use is 10 feet in 

diameter (to maintain structural continuity with the Titan booster) and 

16. , feet long. Local areas of protuberance may exceed this diameter. 

The optical system of the payload (see Figure .:71A9'. ) -- 7

consists of a 70 inch aperture, focal length Ross telephoto lens 

having a 0.54° semi-field angle. The optical axis is approtimately parallel 

to the longitudinal axis of the Mission Module which contains the payload. 

The Mission Module and payloadare unpressurized. A 70-inch diameter, circular, 

flat tracking mirror is located in:front of the lens at the forward end of the 

Mission Module. The tracking mirror is capable of pointing the line-of-sight 

+ 40° in roll (left and right of the X-Z plane), 30° forward in pitch and 400 

aft in pitch. The tracking mirror is gimballed in two axes and is servo 

driven to slew, to follow computed target tracking rates, and to respond to 

position and rate change inputs inserted by a ta°,rget 

tracker or by an astronaut. 

Frame cameras utilizing 92 inch wide film are lonated at the 

end of the Ross corrector barrel at the Laboratory Module side of the bulkhead. 

The cameras may take a sequence of up to ten photographs of each target, 

nominally within approximately +15 to -15 degrees fore and aft (stereo) angles. 

Three different exposure settings are planned for each target. The nominal 

sequence rate is 1 frame per second. The total primary camera film supply 

.shall be sufficient to obtain 15,000 frames of photography per 30-day mission. 

The 15,000 photographt may be apportioned by command between one photograph 

per target to 10 photographs per targgt. 

The Mission Module provides a viewport which allows the primary 

optical beam to be moved through the required obliquity and stereo angles 

for photography. Viewport doors are provided for thermal protection during 

non-photographic periods, 

Mhnned4utomotic Configuration 

The Ross corrector barrel of the optical system is above and 

parallel to the optical axis of the primary mirror. Light is diverted 

from the optical system into a visual optics barrel which is parallel to 

the Ross corrector barrel. A zotmleyepiece at the end of the visual optics and 

within the Laboratory Module allows the astronaut to observe and track the 

target during photography. Malnifinatia of are provided. 

li 3=9,0)01 4:P 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Figure 3-9 

OPTICAL SENSOR BASIC CONFIGURATION 

(Later) 

a 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

; 

Assemblies in the Laboratory Module which are required for 

the manned reconnaissance operation are the Pre-editor and Processor, Film 

Viewer and Editor, and the Film Scanner and Readout. Also essential to 

photography are the 2 astronaut. consoles with TV displays of the ac14isition 

telescope fields, target cue displays and:a hand'Controller for target 

centering and rate correction of the tracking mirror and acquisition scopes. 

Auxiliary photographic equipment includes a 16 mm sequence camera which 

looks through the primary optics. 

3.3.4.5.2 Operational Requirements 

The Photographic Section shall be capable of both northr.. 

bound and southbound photography during a single mission and shall meet 

the specified resolution and total smear limit under the specified conditions. 

'The altitude range for photography shall be 70 to 230 nni. Other aspects 

of the mission. orbital envelope for photography are specified in Section 

It shall be an operational recuirement to photograph as many 

targets as possible consistent with high quality stereo photography. 

"J. /.- 

. Camera 

The camera system consists of the mechanical, electrical, 

and optical elements necessary to position the film and properly expose it. 

The system shall consist of cameras capable of providing a circular image 

on 9.5" wide aerial film. The film shall be transported across the platen 

between exposures and held in place during exposure(or moved if across the 

Format „IMO is required). The film holding system shall be of such a design 

that systeM performance will not be degraded by film surface deformation. 

Film transport from the storage reels, positioning on the 

camera platen, and transport to the take-up reels shall be automatically 

initiated after each exposure. The time between completion of one exposure 

to the allowable start of another shall be 1.0 second or less. 

The local 'exposure time is defined as the time specified to 

expose a picture element. The frame exposure time is the time required to 

expose a photographic frame to all scene and data information. The nominal 

local exposure time will be 1/200 sec for SO-362 film. An exposure range 

will be provided for all sun elevation angles down to 5°. The nominal frame 

exposure time shall be 0.2 sec in accordance with the requirements on the 

nUmber of frame/target. 

or 45 7' 
NRO APPROVED FOR 

FtELEASESI JULYY2015,r 7' 

The Mission-ControlSubsystem. shall be capable of providing 

rare-programmed sequences of from one to ten or more photographs. These 

sequences shall be programmable as to exposure and may contain up to three 

exposure levels to obtain +1 stop exposure range. 

The position of the camera mount shall be controllable to 

provide inches of focus correction. The camera shall be designed to 

accommodate the equipment necessary for recording data on the 92 inch film. 

Manned-Automatic Configuration 

The system shall also be capable of providing and identifying 

one frame of photography target for. on-board processing with no loss of 

photographic information. 

3.3.4.5.4 Optical Design/Performance Requirements 

This section describes the requirements on the primary photographic and visual systems only. Performance requirements •ficiii" 

the sequence camera are contained in Section 3.34.5.7. 

3.3.4.5.4.1 Primary Optics 

The final image shall be photographic negative on type SO-362 

film. The orbital quality measurement method and quality requirements for 

the primary image are as follows: 

a. Measurement Method 

The quality of the primary image shall be measured by 

photographing during flight, one or more specifically prepared test targets 

having several tri-bar patterns of standard Air Force design and having a 

calibration gray scale of known reflectivity. During the performance check 

the brightness of the various areas of the target will be measured at the 

target with pre-calibrated instruments. Simultaneously with these measurements the optical sensor shall photograph the target 'from satellite altitude. 

Not less than four photographs shall be taken. 

Manned -Automatic Confivration 

Two of the latent images will be processed with on-board 

equipment according to specifications in Section 3..4.5.5. Two of the latent 

images will be returned to earth via a DRV Gemini B. Resolution 

readings and density measurements of the processed record shall be made by 

an astronaut and reported at the earliest opportunity. 

firs ..4 t 7 3-7.041.2'r 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

41." ti Li .3 

b. Quality Requirement. 

Analysis of the film records together with measured 

brightness values shall permit the calculation of apparent contrast at the 

entrance pupil. A calculated apparent> contrast between 1.5 and 3.0 shall 

imply acceptable test and atmospheric conditions for a quality check. 

Within this range on contrast, the system shall be capable of resolving 

tri bars as indicated in Figure 3-10. The conditions of this figure 

form a part of this specification. Performance tradeoffs for conditions 

outside this range shall be supplied by the photographic sensor contractor. 

3.3.4.5.4.2 Visual Optics (Manned ConfigurationA) 

The performance and testing requirements are as follows: 

a. Performance 

Magnification continuously variable 

Apparent Field 40° full field. 

Flight Transmission % for visual relay only 

Resolving Power lines/degree 

Central 10° lines/degree 

Rest of Field lines/degree 

Eye Relief nm 

b. Testing 

Magnification of the visual relay shall be checked before 

it is assembled to the primary optical system. It can be checked in a test 

fixture containing a reticle with known spacings. The angle subtended by 

these spacings can be measured with a clinometer looking through the eyepiece. The magnification of the telescope can be computed if the magnification of the visual relay and the focal length of the primary mirror 

are known. 

Apparent field can be measured on the same test fixture 

as used for magnification by having reticle marks to indicate the field size 

for a given magnification. 

Light transmission of the visual optics relay shall be 

measured with a photometer. 

Resolving power of the telescope shall be measured with 

the complete system correctly aligned. Since this only happens in orbit, 

, •b 

37191b4P2. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Figure 3-10 

RESOLUTION VERSUS CONTRAST 

(Later) 

-3,464.i0 
NRO APPROVED FOR 

(SefIT!)PLY2W) 

the performance test must be made bylooking at test charts on the ground. 

This can be done during the photographic testing. 

Eye relief shall be measured by attaching a pupilometer 

to the eyepiece to locate the exit pupil. 

3.3.4.5.5 Recordi-ng- Handling 

3.3.4.5.5.1 Film Requirement 

The nominal film width shall be 92 inches. The primary 

reconnaissance film shall be Kodak Special High-Definition Aerial Film 

(Estar Thin Base) Type SO-362. The vehicle shall carry 13,000 feet or 

230 lbs of this film for photographic operations exclusive of leader requirements and expected waste. 

3.3.4.5.5.2 Black and White 

Manned: tlonfiEuration 

The primary film S0-362 will be loaded into 5 supply reel 

cassettes and loaded into the camera manually and over operational lighting 

conditions. Each supply reel shall satisfy film requirements for 6 days 

operation. The number of targets acquired per pass shall not be limited 

by supply or take-up capacity. The exposed record shall be wound into 

take-up cassettes and manually removed from the camera under operational 

lighting. 

.ikutomgtie:CorifIguration 

The primary film, SO-362 will be loaded into one supply reel 

threaded, through the camera and into the multiple take-up cassettes. 

3.3.4.5.5.3 Color and Special Films (Manned configuration) 

The vehicle shall be capable of carrying additionaly supply 

cassettes of color, night, or special films. For use other than-_in•.main 

camera see Section 3.3.4.5.9. 

3.3.4.5.6 Photographic Format 

The photographic image shall be a 9.4 inch diameter circular 

format centered with respect to the edges of the film. The interframe 

spacing shall be 1 inch, giving a frame length of 10.4 inches. 
,NRPARPROVED FOR 

f. 

Areas outside the image, the four corners, are available 

for edge data recording on the film. Edge data to be recorded shall 

include the following: 

a. Binary Code 

(1) Greenwich Civil Time (accuracy +1 millisecond), 

(2) Vehicle Attitude (accuracy +3 minutes) 

(3). Tracking Mirror Stereo and Obliquity Angles 

(accuracy + 3 minutes) 

(4) Film Exposure - Tine (8 levels) 

(5) Revolution Number 

(6) Frame Sequence Number (begin with zero for 

each revolution) 

b. Alphanumeric Symbols 

(1) Revolution Number 

(2) Frame Sequence Number • 

All foregoing data will be recorded when the slit 

is in center format position. The binary data shall also be recorded on 

magnetic tape for transmission to ground. 

In addition to above data, other suitable exposures 

and markings will be made on the film to show: 

(a) Fiducial marks 

(b) Frame center mark 

(c) Interframe mark 

i• • 

(d) Revolution end mark 

(e) Frame vernier dots (1/200 sec spacing 

with motion of slit) 

(f) Mark or magnetic imprint for special frames 

3.3.4.5.7 Sequence Camera (Manned-Configurations) ) 

A motion picture camera shall be provided in the visual optics ' 

system. This sy+m will provide 16 frame/sec color motion pictures of 

the image displayed to the astronaut. The operational light for this camera 

shall be obtained without introducing any flicker into the astronaut's view, 

and it shall not limit the luminance of his visual image to less than 

 ft-laMberts at nominal scene brightness and to less than ftlamberts at any time during primary payload operations. 
NRO APPROVED FOR 

JUL* 

The camera shall provide sufficient film to provide coverage 

for 1500 targets during the mission. For each target, the sequence camera 

shall activate during primary off-on periods. Exposure control shall be 

automatic. 

The sequence camera shall provide feet coverage. with 

nominal ground resolution at nadir. The sequence camera 

format shall contain only data required for time correlation with the 

primary camera. 

Operation of the sequence camera outside of shutter actuation 

shall not require the attention of an astronaut at any time during a photographic pass, and the camera shall be designed to require as little attention 

as feasible from the astronaut. 

3.3.4.5.8 

3.3.4.5.8.1 

Film Processor (Manned Configuration) 

General 

The Laboratory Module shall be provided with an on-board 

processor which will process selected frames of SO-362 primary record for 

the purpose of on-board photographic reconnaissance and readout to the 

ground for quick access to reconnaissance information. 

3.3.4.5.8.2 Acquisition 

The primary record to be processed shall be obtained without 

endangering the continuity of primary record to be processed on the ground. 

Provision shall be made for identifying frames to be on-board processed 

and provisipn shall be made for removing these frames and transporting 

them to the processor without restriction to the lighting conditions in the 

Laboratory Module. 

3.3.4.5.8.3 Processor 

The on-board processor shall be capable of processing 50 pictures/ 

day with no more than 5 minutes/picture total processing time. The processor shall not degrade resolution by more than 15 percent of the resolution 

obtainable with optimum ground processing. Chemical contaminants shall not 

in any way affect the quality of the recovered_ primary record and shall in 

no way endanger the health, safety, or comfort of the astronauts. The 

processor shall be capable of operation in nominal Laboratory Module.lighting' 

conditions and shall produce a dry photograph suitable for viewing and 

readout. 

!C" t V. it-. t, 
• wwgpRoyEDFOR,- 

Q,J=104/04tALY2mq, , 

3.3.4.5.8.4 Viewer 

A viewer shall be provided to examine the on-board processed 

record. The viewer shall be large enough to accommodate two frames.of 

photography. The viewer shall be equipped with a binocular microscope of 

magnification range to capable of displaying the scene to its 

full resolution limit. The microscope shall be capable of scanning an 

entire image. 

3.3,4.5.9. Dual Camera System (Primary and Secondary) (Manned Version) 

It shall be a design objective to provide, in addition to the • 

primary camera, a secondary frame camera which uses the primary optics and ,-

has the Same image format as the primary camera. Simultaneous photography 

with both cameras is not a requirement. Photographs will be made with the. 

secondary camera by either diverting the light beam from the primary to 

secondary camera platen, or by replacing the primary camera with the 

secondary without a change in the light beam. The purpose of the secondary 

camera is to provide the capability of photographing the target with color 

and/or films other than that used for primary photography. Thus, the same 

target can be photographed with both the primary high resolution black 

and white film and a different film such as color. Astronaut access to 

the secondary camera is a requirement. 

The camera system shall be capable of changing films and , 

necessary filters with a loss of no more than one frame of photography/ 

change. 

i 

3.3.4.5.10 Environmental Control 

3.3.4.5.10.1 General 

The environmental control subsystem shall provide proper 

temperature control for the Photographic Section during all phases of 

vehicle operations. Passive thermal control shall be used to the greatest 

practical extent. Ground conditioning of the Photographic Section shall 

be performed by internal convective cooling and electric heating as required. 

3.3.4.5.10.2 Ground Conditioning 

Ground conditioning during all phases of ground test 

(including factory system test and pad operations) will employ an internal 

ducting system to maintain the required thermal control. 
-7 qhF,'RCNEDFCR--q -, -NR 

IR-ETS LEA k1/4 SLILY 

The temperature range and humidity limits are 

(later). The cleanliness limits are (later). 

The ground conditioning system shall provide an environment 

that will allow acceptable thermal conditions for payload operation within five hours after launch. 

3.3.4.5.10.3 Powered Flight 

The' temperature and humidity limits are as per Section 3.3.2.2.6.2.4. 

The. cleanliness requirements are (later). 

Vent paths shall be sized consistent with the design pressure 

differentials. The allowable pressure differentials on the aft laboratory 

bulkhead are +5 to X1/2 psi differential (P laboratory-P mission module). 

The allowable compartment pressures for the forward booster compartment' 

3.3.4.5.10.4 Orbit 

A passive system of environmental control shall be employed 

to the greatest practical extent. This system Shall utilize thermal 

control coatings, insulation, and component placement. Active environmental control shall be automatic. 

. The temperature and humidity requirements are as per 

3.3 , j 

Section 3.3.2.2.6.2 4. The cleanliness requirements are (later). 

Coating deterioration due to the space environement shall 

be minimized and must be compatible with the mission life and system 

performance requirements. 

The optical performance degradation with door open time shall 

be minimized. The design goal is to obtain no measurable degradation for 

10 minutes of active operation with the maximum sun angle ( p= 0, 21 June). 

3.3.4.5.11 Mechanical Mounting. 

3.3.4.5.11.1 General 

Suitable mechanical mountings for the Photographic Section 

shall be supplied for all phases of the payload operations. The mounting 

shall not in any way affect or alter the performance of the Photographic 

Section. 

r PVC* 

— J j L/, 
NR etemEvopti 1 1A) wig tiokuoil is s 

3.3.4.5.11.2 Ground Handling 

Mechanical mounting of the Photographic Section during testing 

shall be performed in such a way that the test results shall be independent 

of the test method. 

3.3.4.5.11.3 Powered Flight 

The Photographic Section shall be mounted in such a way that 

launch forces cannot endanger the Photographic Section or its subsequent 

performance. 

3.3.4.5.11.4 Orbit 

The mechanical mountings during flight must be such that 

no performance degradation results. The mountings shall allow strain free 

support of the payload at all times during the useful orbital life of the 

vehicle. The payload shall be aligned to within + degrees of the 

vehicle X axis before alignment and shall be held within + degrees 

after alignment. 

No focus shift of the image on the record and no alignment 

shift of any of the payload elements shall occur due to the payload mountings. 

3.3.4.5.12 Performance Prediction 

Performance prediction is a tool that is useful for design 

purposes. For the Dorian System, performance prediction shall be accomplished 

by the method described in Attachment 2. 

AtivtppOet-Gtoll= MtatTiment HeqUirementS 

3.3.4.6.1 In-Plant Test Equipment 

(later) 

3.3.4.6.1.1 Alignments 

(later) 

3.3.4.6.1.2 Special Purpose Testing 

(later) 

3.3.4.6.2 Handling and Transportation Equipment 

(later) 

3.3.4.6.2.1 Handling 

(later) 

3.3.4.6.2.2 Transportation 

(later) 

SPECIAL MaLING 

3 3-0- 
oviworz , 1% GI Juitritt 1)1.41 SFr" 

3.3.4.6.3 Launch Base Test Equipment 

(later) 

3.3.4.6.4 Ground Power and Electrical Distribution 

(later) 

3.3.4.6.5 Aerospace Vehicle Servicing Equipment 

(later) 

3.3.4.6.6 Ground Environmental Control Equipment 

(later) 

3.3.4.6.7 Launch Monitoring and Control Equipment 

(later) 

3.3.4.6.8 Safety Equipment 

(later) 

3.3.4.6.9 Miscellaneous Aerospace Ground Equipment 

(later) 

3.3.4.7 Mission Payload Functional Interfaces 

(Physical and functional interfaces shall be listed here 

when defined by the cognizant Interface Control Working Group - ICWG). 

Manned Version 

(later) 

Unmanned Version 

(later) 

3.3.4.8 Contract End-Item List (CEI) 

Figures and illustrate the top level 

specification trees for the major end items comprising the manned and unmanned 

versions, respectively, of the Dorian System. Detailed end-item critical 

lists shall be prepared and maintained by each applicable contractor in 

accordance with his contract. Detailed specifications shall also be prepared, 

submitted to the Procurement Agency for approval, and subsequently maintained 

by the contractor for each end-item to be furnished. 

The applicable CEI lists are as follows: 

3.3.4.8.1 Mission Module Section Breakdown (later) 

3.3.4.8.2 Photographic Section Breakdown (later) 

3.3.4.8.3 DRV Section Breaks. (later) 

SPECIAL HANDLING ti 

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• 

.,4111140111111138118481111.11Amedownwensuessw __ 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-11INFIDENTIAL,. 

3.3.5 Crew Equipment System Segment (U) 

This system segment defines the crew equipment requirements for 

performance of the MOL mission. 

This section covers equipment for both intravehicular and extravehicular tasks, performed both with and without a pressure suit (both 

pressurized and unpressurized) 

3.. 3.5. I Allocated Performance and Design Requirements 

3.3.5.1.1 Effectiveness (U) 

Effectiveness requirements for this segment are specified in paragraph 3.1.3.1.2.5. 

3., 3. 5.1.2 Weight Itvi) 

For Crew .Equipment design purposes, each crew member shall weigh 

138 - 192 lb. The basic flight suits, together with portable oxygen 

supplies and umbilicals, shall not exceed 94 lb. Extravehicular equipment, including spare suits and umbilicals, portable environment 

systems, tools, tethers, and portable illumination sources, shall, not 

exceed 220 lb. Flight crew test and monitoring equipment for both 

biomedical and human performance tests shall not exceed 520 lb, 

phasing down to a 95 lb weight target for later flights. Personal 

equipment, such as clothing and perSonal hygiene, shall not exceed 

75 lb. 

3.3.5.1.3 Volume (U) 

Baseline functional volumes for Laboratory Vehicle design for the 

human operator shall be based upon anthropometric data, using 

10-90 percentile men by weight and by height. Both shirtsleeve and 

-suited (pressurized and unpressurized) modes shall be considered. 

Storage volume for back-up suits, clothing, medical treatment, and 

personal items shall be provided. 

'CUNF1DtiflAtFORM This document contains information affecting the' notional defense of the United Stores within the 'meaning of the Espionage Lows. SSD AUG 62 208 Title 18, U.S.C., Section 793 and 794, the transmission of which in any manner to an unauthorized person is prohibited by Pow 
NRO APPROVED FOR 

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'1111ffEENTIM, 

Extravehicular Equipment 

Pressure Suit Assembly .(1.) 

The pressure suit assembly (PSA) includes ihe basic garment, with 

integral thermal and micrometeoroid protective provisions "anti-g" 

protection, helmet, gloves, communications, bioinstrumentation, 

plus recovery, flotation, survival and rescue equipment attached to 

the pressure suit. 

3. 3. 5. 1. 4 

3. 3. 5. 1. 4. 1 

During extravehicular operations. the PSA shall be provided with 

crew atmosphere control requirements through an umbilical and environmental control system components. 

The PSA shall provide adequate mobility in shoulders, arms, hands, 

•r• 

waist, hips, and knees to conduct all suited tasks planned for the 

MOL mission. The helmet shall provide undistorted visibility, portable illumination, protection from both ultraviolet and infrared radia..; 

tion by the use of a removable visor, and micrometeoroid protection. 

The PSA shall provide protection against both radiated and conducted 

.:heat from direct, reflected, and surface contact, between the limits 

of -100° F to +200°F. Micrometeoroid protection shall be provided 

integrally in the PSA. 

Each member of the primary and back-up crews shall be provided 

two PSA during each mission, one for primary and one for back-up 

use. Each PSA shall be custom-fitted to the individual flight crewman. 

3. 3. 5. 1. 4. Z Auxiliary Extravehicular Equipment (-4) 

The major equipment items to, be used in conducting the extravehicular operations, in addition to the PSA, are an umbilical type Environment Control System, personal VHF transceiver, and devices for 

traversing the OV surface such as handholds and tether belt. Capability for visually monitoring an extravehicular crew member shall 

be provided in the Laboratory. 

• 

3-106 ''CONFIBEKIAL 

FORM This doeurnent contains information affecting the notional defense of the United Stoles within the meaning of the Espionage Laws, 

SSD AUG 82 208 hit* 18, U.S.C. Section 793 and 794, the transmission of which in any manner to an unouthorised perion is prohibited by low 

. . . 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 5. 1. 5 Intravehicular Operations (Ul 

Basic operations in the Gemini B will consist of flight operations 

during ground checkout, launch, orbital injection and insertion, 

Laboratory activation, de-orbit and recovery and shall be conducted 

in an unpressurized suit during non-emergency operations. Emergency operations for the same profile may utilize a pressurized suit. 

Routine Laboratory operations shall be conducted in shirtsleeve protective clothing. 

3. 3. 5. 1. 5. I Intravehicular Operations Equipment (U) 

Restraining and locomotion devices shall be provided to permit the 

crew members to effectively operate at and move between various 

,work and living stations in the vehicle. Such devices shall employ both 

fixed base and moving base restraint concepts as required to facilitate all operations and maintenance tasks. Standard and special tools 

with tool and component support shall be provided for maintenance and 

repair tasks. Comfortable restraint devices for sleeping shall be 

provided that occupy minimum volume both in use and during storage. 

3.3.5.1.5.2 Flight Crew Clothing and Accessories (U) 

Personal equipment, other than the PSA, shall be provided for the 

flight crew (e.g. body covering, footgear, gloves, tethers, eye 

protection devices, shaver, personal hygiene gear and first aid 

equipment). The intravehicular shirtsleeve clothing shall allow for 

essential body functions (including proper thermal transfer properties), 

skin health and hygiene, and shall be constructed of materials and 

characteristics of no-lint, appropriate strength, appropriate moisture 

absorbance and transfer, and soil and fire resistance. All clothing 

and accessories shall be consistent with Laboratory Vehicle 

requirements. 

O SSD AUF GRM 

 2 20B 

3-107 
NRO APPROVED FOR 

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3.3.5. 2 

3.3.5.2.1 

3.3.5.2.1.1 

Peculiar Performance and Design Requirements 

Orbital Operations Aids 

On-board Technical Data (U) 

The flight crew shall be provided with readily accessible technical data 

on systems, equipments,, and procedures required to perform (e. g. 

using equipment. collecting data), in the operational and maintenance' 

functions. 

3.3.5. 2. 1. 2 Crew Activity Programing (U) 

The activities of the flight crew required for vehicle operations in 

performance of mission operations and tests on a given flight, and for 

personal maintenance (e. g. eating, sleeping, exercise) shall be progamed for each flight to achieve maximum mission effectiveness. 

Such programing shall contain alternative paths and the capability for 

reprograming crew time to accommodate alternate mission profiles or 

contingencies on a real or near real time basis with the crew participating in alternative sequence decisions. 

3.3.5.2.2 Nutritional and Metabolic Requirements (U) 

Atmosphere and thermal control requirements, together with water 

and waste management specifications,are included in the Environmental 

Control and Life Support Subsystem of the Laboratory Vehicle 

Segment. 

3.3.5.2.2.1 Crew Energy Outputs (U) 

A nominal energy output o 3.000 kilocalories (kcal) per man per 24 

hour cycle will be distributed as follows: 8 hr sleep at approximately 

75 kcal per hour per man; two 30-min periods per man of physical 

work and/or exercise at 600 kcal/hr; 15 hr of other duty functions at 

approximately 120 kcal/hr. The EC/LS system should be designed 

to accommodate these thermal loads without depending on positive man 

heat storage during work or exercise periods, nor depending upon 

negative man heat storage during sleep periods. The system should 

also normally limit evaporation from the crewman to nominal figures 

3-108 

SSD AFAR:2 20B 
NRO APPROVED FOR 

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of 45 cc/hr except during exercise periods when an evaporation rate of 

1000 cc/hr is allowable for a combined respiratory and skin water loss 

Of 500 cc during a 30 min exercise period. 

3.3.5.2.2.2 Food Composition 

The 3000 kcal diet shall 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. 

The food shall be carried in a dehydrated state; efficient, .zero.-g 

qualified food preparation, packaging, and dispensing procedures shall 

be provided. Food and water-handling systems shall provide for 

simple and effective means of recording specific food intake by nutri, 

.r- ent type and calories. 

3.3.5.2.2.3 Water Requirements (IJ) 

Total water provision shall be 3200 ± 300 g per man-day, including 

the water used to reconstitute the food for the liquid diet. Potability . 

standards, including U. S. Public Health Service requirements and 

associated control measures, shall be established for water use during 

the entire mission. Water for food preparation and drinking shall be 

provided at 155°F and 55°F, respectively. 

3.3.5.2.3 Personal Hygiene (U) 

General skin hygiene shall be preserved by a simplified system of 

moist skin scrubbing. Oral hygiene shall be accomplished by water 

and brush without dentifrice. Particulate matter (beard, nail clippings, 

etc.) shall be aspirated and trapped. 

3.3.5.2.4 Flight Crew Test and Monitoring 

3.3.5.2.4.1 Biomedical Tests (U) 

Equipment shall be provided to obtain in-flight data from both the 

flight crew and from the environment to which it is exposed. Prerequisites to the in-flight test program incinde acquisition of essential 

pre-flight and post-flight baseline data and extensive ground-based 

3-109 
NRO APPROVED FOR 

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testing to understand as fully as possible the physiological mechanisms 

of "simulated" weightlessness and the explicit parameters selected 

for in-flight measurement. 

Provision shall be made for measurement of the following functions 

considering the effects of weightlessness, environmental loads, and 

body demands: (1) blood volume, pressure and flow; (2) the 

electromechanical behavior of the heart; (3) fluid and electrolyte levels 

and balance: (4) gastro-intestinal function and nutritional status; (5) 

metabolism of selected body materials, e. g. , Calcium and protein; 

(6) respiratory mechanics and rate of energy metabolism; (7) nervous 

system functions; e. g. muscle strength and coordination, general 

mental status;(8) body mass. Important associated environmental 

parameters shall be measured, including physical and tissue equivalent radiation measurements. 

3. 3. 5. 2.4. 2 Biomedical Monitoring (U) 

The biomedical test equipment specified in 3. 3. 5. 2. 4. 1 shall contain 

biomedical monitoring equipment to be used for flight safety monitoring in the Laboratory during all flights. These measures shall include 

continuous heart rate plus EKG, blood pressure, temperature, and 

respiration rate on schedule and on demand. 

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. 

1' 3.3.5.2.4.3 • Crew Performance Tests (U) 

The flight crew shall be tested on a set of standardized tasks integrated into a computer-driven, control-display test console designed 

to assess human performances related to aerospace vehicle and payload operations. The test profile shall include memory, vigilance 

monitoring, intellectual processes, and sensory-motor performances. 

3-110 
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3.3.5.2.4.4 Man-Equipment Design Validation (U) 

Flight crew performance shall be validated by the use of direct (TV, 

voice, recordings, and photographs) and indirect (flight data analysis. 

logs, and debriefings) measures. 

3.3.5.Z. 5 AGE 

3. 3. 5. 2. 5. 1 Crew Support (U) 

Facilities shall be available at or near the launch and recovery areas 

to house and transport crew members and to provide the necessary 

medical support, including prelaunch and post-flight medical 

evaluations. 

•r3. 3. 5.2. 5.2 Pressure Suit (U) 

Ground support facilities shall be provided at locations wherever suit 

usage is contemplated. 

3.3. 5.2.5.3 Flight Crew Test and Monitoring (U) 

AGE shall be provided as required for crew test and monitoring 

equipment. 

3. 3. 5. 3 Functional Interfaces (U) 

(Functional interfaces shall be listed here when defined by the cognizant Interface Control Working Group-ICWG.) 

3. 3. 5. 4 Contract End Items (U) 

(The contractor shall provide for incorporation in this paragraph a 

list of the Contract End Items by CEI specification number, nomenclature, and the CEI into which it installs. This paragraph shall list 

all end items being provided under these system segments.) 

3-111/112 
I 

NRO APPROVED FOR 

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3. 3. 6 Titan III System Segment (U) 

The. Titan HI Launch Vehicle consists of two seven segment 120" dia 

solid rocket motors and a two stage core vehicle as defined in 

SSBD 65-22. Basic requirements for performance and reliability are 

specified in this section. 

3.3.6.1 Allocated Performance and Design Requirements 

3.3.6.1.1 Minimum Payload Performance Ns3 SAR) 

The Launch Vehicle shall be capable of launching a 32,000 lb Orbiting 

Vehicle into a reference 80.degree inclination 80/130 n mi elliptical orbit with 

perigee between 30°and 50°North latitude, without yaw steering 

from WTR. Payload decrements for greater inclination angles and 

.,paw steering to meet range .safety requirements should be subtracted 

from the above value. Estimates of such decrements associated with 

orbit inclinations other than 80°and/or yaw steering requirements 

are tabulated below. 

r) Orbit Inclination Payload Decrement 

*80° 4.30 

*82° 500 

*84° 620 

*86° 800 

88° 1020 

90° 1250 

95° 1790 

97° 1980 

100° 2230 

*Yaw steering predicated on estimated range restrictions. 

3-113 

This document contoms mf cumotioo oflycting the national defense of the United Stow within the meaning of the Espiannye Crows. 

Title IA. U.S C.. Section 793 and 794. the tronsrmition of which in any manner to an vnouthoected person is prohibited by to 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 'MET, 

3. 3. 6. 1. 2. Insertion Accuracy k‘k-3 SAR) 

The, required insertion accuracy from a reference 80/130 n mi orbit 

shall be as follows; 

30-Insertion Accuracy 

Primary Guidance Secondary Guidance 

Inertial Velocity (tangential 

velocity) 

Inertial Flight Path Angle 

Altitude 

Out-of-Plane Velocity 

Out-of-Plane Position 

12 fps 

0.05 deg 

1 n mi 

10 fps 

0.5 n mi 

20 fps 

0.1 deg 

2 n mi 

300 fps 

10 n mi 

3. 3, 6. 1. 3 Launch-on-Time Probability N-4) 

The Titan III system segment (AGE, Launch Vehicle, and facility) 

shall have a 0. 90 probability of meeting a one hour window on any one 

of three successive days specified two weeks in advance of the 

scheduled launch date. 

3. 3. 6. 1. 4 Effectiveness 11Ss-4) 

The Launch Vehicle shall have a probability of successfully accomplishing a launch countdown (Final 30 sec) of 0. 93. The probability of acacomplishing a successful launch through orbit insertion shall be 0. 97. 

3. 3. 6. 1. 5 Launch Restrictions (U) 

3. 3. 6. 1. 5. 1 The Flight Vehicle shall be capable of being launched 

in 99 percent winds aloft and ground winds at WTR as defined in 

Meteorological Note No. 2, Atmospheric and Wind Design Criteria 

for PMR, Titan IIIX/Agena, Martin Company/Denver, dated 

7 August 1964. 

3. 3. 6. 1. 5. 2 Visual Abort Mode (U) 

Visual monitoring of the Launch Vehicle, and abort warning during the 

lift off and clearing of the launch complex shall be provided. 

• 

3-114 

pus document contains information affecting the notional defense of the United States within the meaning of the Essaonage Laws, 

Title U S e . Section 793 and 794. she transmission of which .n any manner to on unouthortted person is prohibited -isy low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.3.6.1.6 System Monitoring During Ascent (U) 

A capability to monitor critical events and system status 

during ascent shall be provided to the Gemini B and mission control.' 

3.3.6.1.7 Orbiting Vehicle'Separation (U) 

The OV s.hall provide propulsive capability for the Stage II/OV 

separation. Redundant separation signals and separation devices will be 

supplied by the Launch Vehicle contractor. Backup will be provided by 

crew initiation capability. During separation, tip-off rates shall not exceed , 

2 deg per sec about any axis. The separation mechanism shall not induce 

deterimental shock or contaminants which could significantly degrade mission 

payload performance. 

Requirements for thermal protection of the Titan III/M Mission 

Module interface area from flight "termination exhaust plume impingement 

effects shall be determined. 

3.3.6.1.8 Tracjectory Constraints (U) 

The dispersed 3 sigma ascent trajectory shall not exceed MOL 

system constraints. 

3.3.6.1.9 Induced Oscillations (U) 

The Launch Vehicle longitudinal oscillations will not induce sustained oscillations in the OV/Booster Interface in excess of 0.25g peak-ti-peak 

in the frequency range of 5 to 30 cps. 

3.3.6.1.10 Yaw Steering 146-3) 

The Launch Vehicle shall be capable of being yaw-steered during 

the powered portion of flight to meet the requirements specified in Paragraph 

3.1.1.1.3.1. Pre-programed orbital inclination inputs shall be accepted up 

to 24 hours before launch. 

3‘. 3.6.1.11 Perigee Placement X3) 

The Launch Vehicle shall accept' a programmed positive insertion 

flight path angle ( ) up to 0.4 deg' with a granularity of no more than 0.05 deg. 

3.3.6.2 Peculiar Performance and Design Requirements 

3.3.6.2.1 Malfunction Detection System (U) 

A Malfunction Detection System (MDS) shall be provided to sense 

impending catastrophic or degrading failures. MDS paths and signals 

3-115 
=AMISINS 

NRO APPROVED FOR 

'RELEASE 1 JULY 2015 

shall be redundant. Escape shall be manually initiated; however, pro-. 

visions shall be made for both'automatic and manual thrust termination during Stage 0 flight. 

*3. 3. 6. 2. 1. 1 Abort Warning (U) , 

Sensors, logic, and displays Shall be provided to meet MOL system 

criteria for crew abort evaluation and decision. 

3. 3. 6. 2. 2 Backup Guidance and Control 

3. 3. 6. 2. 2. 1 Redundant Guidance System (U) 

The Gemini B IGS shall be used as a back-up to the Titan III system 

IGS for all stages of powered flight. Both automatic and manual 

switchover and switchback capability shall be provided. 

. f. 

3. 3. 6.'2. 2. 2 Redundant Flight Control Systems (U) 

Redundancy shall be provided in the flight control system. 

3. 3. 6. 2. 3 Safety Criteria X-4) 

The Launch Vehicle systems, including the airborne and ground (real 

time) malfunction detection systems, shall be designed to meet the 

following criteria: 

(a) Between solid motor ignition and orbit 

insertion, the probability of a failure with a 

warning time* less than 3.0 sec, plus undetectable failures, shall not exceed 1. 8 per 

thousand flights. 

(b) Between 40 and 90 sec of powered flight, the 

failure rate with a warning time* between 0.5 

and 6 sec shall not exceed 3.2 per thousand 

flights. 

(c) Verification of. anorbit lifetime of at least 

two orbits or generation of an abort signal or 

AV requirements shall be provided. 

*Warning time is defined as the time between signalling the' spacecraft 

of need to abort and either (1) start of structural breakup in the 

Launch Vehicle, or (2) exceeding ejection system or other spacecraft constraints. 

3-116 

this docvinent contains Information 'affecting the notional. defense of the United Stotts *Ain the meaning of the Espionage Oyes. • 

fide t6. U.S C . Section 793 and 794, the tronanistion of which in any rnonnw to an unouthoraed person ptoh.bdred by law 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

`SECRET-- 

(d) Autonomous detection of guidance malfunctions on board the Titan III shall be provided 

after loss of range tracking (elevation angle 

<5 deg). 

3. 3. 6. 2. 4 Performance Constraints (U) 

The L'aunch Vehicle shall be constrained to• the following nominals: 

(a) Maximum dynamic pressure shall not exceed 

900 psf 

(b) Maximum acceleration during Stage 0 shall 

not exceed 3. 29g 

(c) Maximum heating integral goal for critical 

Launch Vehicle stations shall be 

100 X 106ft-lb/ft2 

3c.3. 6. 3 Functional Interfaces (U) 

(Functional interfaces shall be listed here when defined by the cognizant Interface Control Working Group-ICWG) 

3. 3. 6. 4 Contract End Items (U) 

(The contractor shall provide for incorporation in this paragraph a 

list of the Contract End Items by CEI specification number, nomenclature, and the CEI into which it installs. This paragraph shall list 

all end items being provided under these system segments. ) 

"SEEL_ 3-1171118 

.This document contains Information affecting the notional defense of the united stores within the meaning of the Iscuono9. Laws. 

title 18. U.5 C.. Section 793 and 794. 'the transmission of which in any manner to an unauthorized Person is prohibited by low. 
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3. 3. 7 Facilities System Segment 

Design and construction of new and/or modified existing facilities 

shall satisfy the requirements of the MOL 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 VAFB 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. 7. I Allocated Performance and Design Requirements 

Required facilities for MOL System operations include the Initial 

Launch Capability (ILC), an Orbiting Vehicle Assembly Building (OVAB) 

an Engineering and Operation Facility, an Operational Readiness Unit, 

The Contractor Support Facility (CSF), Hazardous Handling Building, 

Pyrotechnic Storage Building, Miscellaneous Administration Building, 

and an Operational Training and Evaluation Facility, all to be located at 

VAFB. Facilities for storing and processing flight vehicle segments, 

components and spares, shall meet the requirements for function, safety and 

environmeit s including contamination control, as specified under the provisions 

of . In addition, Mission Control at STC Sunnyvale and 

appropriate communication networks and facilities are required. 

3. 3. 7. 2 Peculiar Performance and Design Requirements ' 

3. 3. 7. 2. 1 Initial Launch Capability 

The MOL system will be integrated and launched from the ILC 

system at the VAFB. 

3. 3. 7. 2. 1. 1 Launch Pad 

The MOL launch pad facilities shall provide an environmental, 

enclosure for the. entire Orbiting Vehicle while on the Titan III launch 

Vehicle, suitable parking areas for the Orbiting. Vehicle AGE 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 ft from the Gemini B in the 

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event a potentially dangerous condition arises between the time the 

flight crew enters the spacecraft and solid motor ignition. Facilities 

shall be located with consideration for the provision of a clear landing 

area as required for the flight crew in case of launch abort.. 

3.3.7.2.1.2 Launch Control Center 

The ILC Launch Control Center (LCC) and connecting cable ways and 

ducting between the AGE vans and the Launch Control Center shall 

accommodate the MOL System AGE installation. Communication lines 

connecting the launch complex and the Launch Control Center shall 

satisfy MOL system requirements. 

3.3.7.2.2 Industrial Area 

Use .of VAFB industrial area facilities by the Orbiting Vehicle prior to 

entering the ILC shall be minimized. New facilities or modifications 

to existing facilities shall be provided as follows: 

3. 3. 7. 2. 2. 1 Engineering and Operation Facility . 

Taigineering and Operation, and Contractor Support Facilities shall be 

provided for the individual segment contractors and Air Force and 

Aerospace personnel. 

3.3.7.2.3 Orbiting Vehicle Assembly Building 

A facility shall be provided for the receipt, inspection, assembly, and 

checkout of the OV. Provisions shall be made for vertical assembly 

and checkout of the OV, including the pre-launch installation of pyrotechnical and ordnance devices. Additional facilities shall be provided 

for the AGE required to conduct individual segment tests and to perform an integrated OV test. 

3.3.7.2.3.1 Receiving, Inspection and Storage Facilities 

A clean room area shall be provided in the Orbiting Vehicle. Assembly 

Building for the receipt and inspection of individual segment portions 

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-- COURDENTIAL, 

of the OV system, which will be subsequently integrated and checked 

out. Sufficient area shall be provided for necessary AGE and personnel to perform subsystem tests required to align, calibrate, or 

adjust the appropriate systems. Area shall be provided for the storage 

of critical space components and elements as required. 

3. 3. 7. 2. 3. 2 Orbiting Vehicle Subsystem Maintenance Area (U) 

An Orbiting Vehicle subsystem maintenance area shall be provided for' 

possible modifications and/or maintenance found necessary on subsystems that are removed from the OV. Areas in the existing OVAB 

buildings shall be used for this function, where possible. 

3. 3. 7. 2.4 Pyrotechnic Receiving, Test, and Storage Facilities (U) 

Agyrotechnic receiving3 test, and storage test facility shall be provided 

at a location remote from the OVAB for receiving and testing of Orbiting 

Vehicle explosive devices. Provision shall be made .for installation of 

explosive devices on the OV at the launch pad. 

3.3.7.2.5 Bench Support Areas (U) 

Bench support areas shall be provided for test equipment required to 

support design modifications, to determine the accuracy of spares, to 

detect malfunctions, and to support a limited maintenance and repair 

capability at VAFB: Areas in the ILC and/or existing VAFB buildings 

shall be used for this function, where possible. 

3. 3. 7. 2, 6 Mission Controlserbsi) 

Facilities shall be provided at the Satellite Test Center .(STC) at 

Sunnyvale, California for housing all powered flight and Mission Control equipment for display and control, data retrieval and storage, 

computation, on-orbit flight planning and changes, mission analysis, 

and biomedical support. Equipments necessary for the interconnection 

of the Mission Control with the LCC, telemetry receiving stations, 

mission simulation facility, range safety and range control, and range 

tracking station communications nets shall be installed, 

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FORM This document contains information affecting the national defense of the United Skies within the meoninp of the Espionage lows. 

SSD AUG 62 20B title 1$. U.S.C.. Section 793 and CM, the transmission of which in any manner to on unauthorized person is prohibited by low 
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--CONENTILL__ 

3.3.7.2.7 Operational Training and Evaluation Farility Irscrl) 

Facilities shall be proirided in the Operational Training and Evaluation 

Facility to house the necessary flight crew equipment, training equipment, physiological evaluation equipment, and a complete mission 

simulator which will operate in conjunction with Mission Control, the 

WTR, and the world-wide tracking network. 

3.3.7.2.8 Operational Readiness Unit (U) 

Facilities in the Operational Readiness Unit shall be provided at VAFB 

to furnish suitable living accommodations for primary and back-up 

flight crews, as well as key mission personnel. Space shall be provided for approximately eight flight crew members and 12 key personnel continuously on duty. This facility shall be located relatively 

close to-operational training and evaluation facility. 

3.3.7.2.9 Bioastronautic Operational Support Unit (Deleted) 

3.3.7.3 Functional Interfaces (U) 

(Functional interfaces shall be listed here when defined by the cognizant Interface Control Working Group-ICWG.) 

3.3.7.4 Contract End Items (U) 

(The contractor shall provide for incorporation in this paragraph a 

list of the Contract End Items by CEI specification number, nomenclature, and the CEI into which it installs. This paragraph shall list 

all end items being provided under these, system segments.) 

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ihis docyment contains information affecting the notional defense of the United States watin the meaning of the Espionage Lows. 

Title IS, U.S.C. Section 793 and 794. the transmission of which in any, manner to on uiiouthorized person is prohibited by low 
EtttiVIDLING 

3.3.7.5 Mission Payload Facility Requirements 

Adequate provisions shall be made in the checkout, maintenance and launch areas for Dorian environmental and special security 

requirements. The provisions of FED-STD-222 are applicable to areas 

provided for servicing the mission payload. 

3.3.7.5.1 Communications 

Peculiar Mission Payload launch base communications 

requirements shall be established in such a manner that all required pre-launch 

and launch operations can be conducted with required security. 

SPECIAL HANDLING 

3 ---;3f2 
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--CONFIDEVIAL--- 

3.3.8 Launch Operations System Segment (U) 

The Launch Operations System Segment essentially covers all functions, techniques, and procedures that take place in the immediate 

geographical area of. the launch site. It encompasses items involving 

the flight hardware and flight crew, and extends from their receipt at 

the launch site until lift-off of the Flight Vehicle from the launch site. 

In addition, the activities within this segment depend upon the completion of the design, construction, and acceptance of the launch base 

facilities described in the Facilities Systems Segment.. A further 

requirement is the design, installation, checkout, and acceptance 

of the AGE/OGE as an integrated system capable of performing prelnch and launch verification tests on both the integrated OV and the 

Flight Vehicle. 

3.3.8.1 Pre-launch Operations (U) 

Pre-launch operations include receipt, check-out, assembly, maintenance, modification, and launch-verification testing of all flight 

hardware at the launch site" It 

includes certain training and bioastronautic preparation and readiness 

of the flight crew at the launch site. Additionally, launch site ground 

crew training and preparedness is contained in this system segment. 

Pre-launch operations also encompass the necessary planning and 

management required to accomplish launch, both for the pre-launch 

operations themselves and the support requirements thereof. Control 

of all launch site facilities and equipments for launch operations is 

contained within this segment. 

3.3.8.2 Launch Operations /1-4) 

Launch operation shall begin with the start of readiness count (approx 

R-54 hr), proceed through T-count (approx T-300 min) and terminal 

count (approx T-32 sec) and .end at lift-off. Prior to lift-off, control 

of the countdown shall be exercised within the Launch Control Center 

-CONFIDENTIAL- 3-123 

.This document contains infwmotion affecting the notional defense at the United S,ates within the meaning of the Espionage Lows. 

Tide US, U.S.C.. Section 793 and 791, the transmission of which in ony manner to on unauthorized person is prohibited by low 
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(LCC) in the Launch Complex. Decisions as to readiness of the test 

vehicle and flight crew from an equipment and health standpoint shall 

be made there, with readiness decisions being monitored b y Mission 

Control at STC. From the start of countdown until the ground instrumentation systems used during ascent become primary, the LCC shall fum tion 

as an arm of Mission Control. During the countdown all Flight Vehicle/Test 

Support interfaces with Mission Control shall be revalidated. In general, 

the Launch Operations System Segment shall contain the necessary on-site 

planning and documentation effort which will assure support of the ascent 

operations requirements. These ascent operations requirements include 

instrumentation, data handling, abort-recovery, and post-launch data needs. 

3. 3. 8. 2.1 OGE Equipment and Computer Programs (U) 

.r. Special equipment and computer programs shall be furnished to 

achieve an integrated MOL Flight Vehicle system exercise, countdown, 

'• and launch only to the extent required by the specified system effectiveness 

(paragraph 3. 1. 3). 

3. 3. 8. 2. 2 Ground Wind Restrictions 

Maximum allowable ground wind speeds for transport of the 

complete orbiting vehicle shall be established by the Laboratory Vehicle 

contractor. Ground wind restrictions for launch pad mating and other 

pre-launch rad operations shall be established by the launch integrating 

contractor. 

3. 3. 8. 3 Functional Interfaces (U) 

(Functional interfaces shall be listed here when defined by 

the cognizant Interface Control Working Group - ICWG) 

3. 3. 8. 4 Contract End Items (U) 

(The contractor shall provide for incorporation in this 

paragraph a list of the Contract End Items by CEI specification number, 

nomenclature, and the CEI into which it installs. This paragraph shall 

list all end items being provided under these sys tern segments. ) 

In addition, the contractors shall define the range support -- 

requirements in sufficient depth to permit the extraction of those 

requirements as direct inputs to the appropriate range support documentation 

specified by SSDM 80-1. 

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L'2 

!NIG 

'VAA 01ini ULI 

3.3.8.5 Mission Payload Launch Operations Support 

(later) 

3.3.8.5.1 Contractor Support 

(later) 

3.3.8.5.2 Software Requirements 

(later) 

SPECIAL HANDLING 

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3.3. 9 Flight Operations and Support: System Segment Ns 4) 

Flight Operations and Support System Segment is concerned 

principally with Mission Control and includes all equipments, communications, 

computer programs, personnel, techniques, and procedures necessary to 

accomplish MOL Mission Control from start of launch, countdown to mission 

completion, including data retrieval, laboratory disposal, and crew recovery 

when applicable. The segment also includes appropriate provisions for 

integration, simulation, training, and over-all system exercising. This 

segment shall be designed, implemented, tested, and operated as a system 

and shall have an integral system validation capability. The nominal point 

of segment control will be at the Air Force Satellite Test Center (STC) at 

Sunnyvale, California. 

3.t 9.1 Mission Control Operations (`C4 

Throughout all phases, the Mission Control shall have available 

the worldwide facilities for range support and recovery support which have 

been assigned to the program. Launch range instrumentation and support • 

will be furnished jointly by the Western Test Range (WTR) and the Satellite 

Control Facility (SCF). The SCF will provide the on-orbit network, Mission 

Control and Data Re-entry Vehicle _recovery forces. Certain supplemental 

support will be provided by NASA (Goddard) and the Nat ional Range DiVision 

(NRD). Instrumentation ship support for injection coverage will be provided 

by the ship,pool under the operational direction of the NRD. Communication 

support will be obtained from existing SCF, NRD, and NASA Inetworks, with 

additional services obtained through established DOD channels. All recovery 

forces for the Gemini B and flight crew will he provided through the agency 

of the DOD Manager for Manned Space Flight Support. 

3.3.9.1.1 Initial Conditions 

Within the 24 hours preceding terminal countdown, the instrumentation network, recovery force system, SCF, and their supporting centers 

shall be checked out on an end-to-end system basis. Other supporting services, 

such as weather forecasting and launch range materials 

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handling services, shall be active during previous operations and shall 

be on-line as required. MOL vehicle/AGE/instrumentation/SCF/LCC 

interfaces shall have been established and validated prior to the initiation of the terminal countdown. 

3.3.9.1.2 Launch Control k4) 

Prior to lift-off, control of the countdown shall be exercised within the 

MOL LCC at VAFB. Decisions as to readiness of the test vehicles 

from an equipment standpoint 'shall be made there with cognizance of 

such readiness decisions being maintained by Mission Control. 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 final countdown, all Vehicle/Test Support interfaces with..M3.ssion Control shall be revalidated through the instrumentation networks and the required display/control functions activated at 

the STC. 

3.3.9.1.3 Vehicle/Crew Control (-4) 

This function shall be physically located in the STC and shall be the 

prime function of Mission Control from lift-off until re-entry, crew 

recovery, and data retrieval. During the countdown all display and 

control capabilities shall be brought on-line and checked out with the 

data handling and instrumentation networks. 

3. 3. 9. 1.4 Network Control Nc4) 

Launch area and worldwide instrumentation data handling and cornmunications support shall be controlled during, all phases by a summary 

status and control element at the STC. During the countdown all network control functions shall be validated and brought on-line. 

3. 3. 9. 1. 5 Recovery Control X4) 

This function shall be physically centralized at the STC and shall include the capability for deployment and control of, and continuous 

communication with, forces for planned, contingency, and emergency 

3-126 `CONRIENTAL_ 

RM .This document contains information affecting the national defense of the United States within the meaning of the Espionage laws. 

1 62 20 13 Title IS, U.S.C.. Section 793 and 794, the transmission of which in any manner to an unauthorized person is prohibited by low. 
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fl 

recovery support. During the countdown, recovery forces shall be 

brought to an appropriate state of readiness. 

3.3.9.1.6 ' Instrumentation and Communications Network fri-4) 

During launch preparations local launch area instrumentation systems 

shall be brought on-line. Final data acquisition parameters shall be 

transmitted to the worldwidw ground support network. All network 

stations shall be brought on-line and exercised on a complete system 

basis using, where appropriate, local simulation equipment and data 

tapes interconnected with the station instrumentation which shall supply data to the STC data processing and display equipment for system 

exercising. 

3.3.9.1.7 Ascent Phase 

3.3.9.1.7.1 Tracking Zt1/44) 

The ground tracking systems shall derive position information to assist 

in the Mission Control functions, 'including discrete commanding, slow 

malfunction detection, and crew safety when applicable. During the later 

phases of ascent, both on-board guidance data and ground-derived 

tracking data shall be used to verify achievement of an orbit having 

adequate life, to establish the initial ephemeris, and to make any alternate 

control decisions. For the manned flights, tracking of the Gemini B 

spacecraft and impact prediction are required after an abort during powered flight. 

3. 3. 9. 1. 7. 2 Telementry Ns4) 

Telemetry data from the Launch Vehicle, Gemini B, 

and Laboratory shall be obtained on a selected baSis from before lift-off 

to verification of initial orbit. 

3.3.9.1.7.3 Command. N1/4-4) 

Commands to the Gemini B shall up-date displays on 

the manned flights. The Gemini B command format and rate will be 

equivalent to NASA Gemini. The WTR command system shall provide 

the necessary range safety commands for the Launch Vehicle. 

3.3.9.1.7.4 Voice Communications ZIS1/4-4) 

Voice communications between Mission Control and 

flight Crew shall be continuous. 

--CORROHN , 

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3.3.9.1.7.5 Data Flow, Computation, and Display Ilr\-4) (Manned Flights) 

Metric tracking data and selected Launch Vehicle and 

orbiting vehicle telemetry data shall be used for trajectory, IIP, flight 

c rew safety, and related calculations. The outputs shall be displayed 

at Mission Control. Selected Gemini B, Laboratory, and flight crew 

telemetry data shall be converted to engineering units and displayed 

in real time at Mission Control. Launch Vehicle telemetry data shall be 

displayed, as well as used in computations related to slow malfunction 

detection. Commands shall be enabled directly from Mission Control. 

Mission Control shall have the capability to sense and analyze malfunctions 

and effect abort and switchover decisions with short time constraints. 

In those cases where the time constraint necessitates instantaneous decisions 

by the flight crew based on vehicle displays (i. e. , through the on-board 

malfunction detection system), Mission Control shall provide assistance 

and backup. Special provisions shall be made to optimize retrosequence in case of abort. A detailed assessment shall be made of the 

mission performance during powered flight and a baseline established 

for any later decisions. Necessary modifications to any planned maneuver 

shall be determined. 

3.3.9.1.7.6 Data Flow, Computation and Display 1S-4) .(Unmanned 

Flights) 

For unmanned flights metric data and selected telemetry 

data will be used for trajectory IIP and related calculations. The ground 

system shall comprise the applicable portions of the systerri utilized for • 

manned flights, and outputs, shall be displayed in real time at the Mission 

Control Center. 

Early Orbit Phase 

Tracking N-4) 

At least three valid metric tracking passes shall be 

obtained to establish the orbit for control purposes. 

3. 3. 9. 1. 8. Telemetry Wc4) 

For this flight phase, telemetry data shall be obtained from 

both the Laboratory and Gemini B.. Data from both sourcds shall be simul.! 

taneously selectable for retransmission to Mission Control. 

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3. 3. 9. 1. 8 

3. 3. 9. 1. 8. 1 
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SECRET 

3.3.9.1.8.3 Command%tk-3 SAR) 

Commands for the Laboratory and Gemini B shall update on-board 

displays, the guidance system, and other systems as required. The 

Mission Payload data system shall be capable of being loaded and controlled from the STC. Secure command capability shall be provided 

for the Laboratory Vehicle and Mission Payload Segments. 

3. 3. 9. 1. 8. 4 Voice Communications 11S4) 

Voice Communications capability between the flight crew and Mission 

Control shall be continuous during all passes over primary network 

stations and over certain supplemental stations to minimize gaps in 

coverage. 

'r`3. 3. 9. 1. 8. 5 Data Flow, Computation, and Display (15c4) 

Tracking data shall be processed without delay at the STC computer 

complex until the final ephemeris is established and verified. Telemetry data will processed in real time and displayed to the Mission 

Control elements. 

' The mission control function shall include a detailed analysis of all 

mission telemetry data to back up the flight crew during transfer and 

Laboratory activation, establish the validity of the orbit configuration, 

and provide malfunction detection and any remedial action.. The system operations plans shall be updated or modified on the basis of the 

actual orbit and vehicle/flight crew condition. 

3. 3. 9. 1. 9 

3. 3. 9. 1. 9. 1 

On-Orbit Phase Nc4) 

Tracking (\-4) 

Tracking shall be only that necessary to provide sufficient ephemeris 

accuracyfor control purposes. Supplemental tracking shall be called 

up to provide additional accuracy as required by the.mission. 

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.This document contains information affecting the notional defense of the Uniied States within the meaning of the isplooceoe Lows. 

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3. 3. 9. 1. 9. 2 Telemetry X-4) 

During routine on-orbit operations, time-sharing of status and payload 

data dumps and selection and compression in real time of a limited 

amount of received data for transmission to the STC shalLbe normal 

modes of operation. Additional requirements derived from mission 

data in combinations of extra carriers or special formats on the vehicle 

status telemetry systems shall be processed in both on-line and offline modes. 

3. 3. 9. 1. 9. 3 Command (*S.< SAR) 

Commands for the Laboratory shall be.the same as those for the early 

orbit phase with additional allowance for growth in mission information 

systenxrequirements. Secure commands shall be provided. 

3. 3. 9. 1. 9.4 Voice Communications Teszl) (Manned flights only) 

Voice communications capability between Mission Control and the 

flight crew shall be continuous during all passes over primary stations. 

Supplemental stations shall be called up for special events or 

emergencies. 

3. 3. 9. 1. 9. 5 Data Plow, Computation, and Display /V,1/4-4) 

The data handling system shall have the capability during-a mis sion.toadapt to and process different formats, information rates, and 

quantities of multiplexed vehicle and payload data, and to store data 

for trend analysis. The system shall have the capability to edit and 

strip-out mission data up to 1 mb/sec. Mission data in the 20 mb/sec 

range shall be presented to mission equipment in video form or down 

converted as appropriate. 

During the orbit phase, Mission Control shall perform detailed analysis, failure prediction, fault location, and remedial planning as well 

as mission operations planning. The• quality of mission data shall be 

evaluated in real time, or near real time, as appropriate. Detailed mission 

data analysis and evaluation shall function with time constraints appropriate 

to the mission and compatible in all cases with over- all mission control 

function. 

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TM* 111, U.S.C.. Section 793 and 794, the transmission of which in any manner to on onoothortted person is picshibtled by law. 
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t 

3.3.9.1.10 Re-entry Phase (Manned Flights Only) 

3.3.9.1.10.1. Tracking ttgc4) 

Metric tracking shall be of sufficient coverage to establish the new 

ephemeris for the Gemini B and Laboratory after separation. Supplemental support for the Gemini B shall be expected to handle emergency 

as well as planned re-entry. For the primary recovery area, metric • 

tracking shall be provided after retrofire to develop an accurate impact prediction. In case of recovery in a contingency area, metric, 

tracking shall be utilized as available. 

3.3.9.1.10.2 Telemetryl'ISs4) 

Telemetry capability will support the Gemini B. Support shall be the 

.r• maximum achievable with the primary network stations with voice 

coverage from additional stations. 

3.3.9.1.10. 3 Command t. k 3 SAR) 

Commands for the Gemini B will update displays, the guidance system, 

and other vehicle systems as required. Secure commands for the 

Gemini B are not required. Ground command control will provide 

retrofire times and sequence for both planned recovery and contingency 

areas. 

3.3.9.1.10.4 Voice CommunicationsNO) 

Communications capability shall be only with the Gemini B. Relatively 

continuous coverage will be provided. 

3. 3.9.1.10.5 Data Flow, Computation, and Display tc-4) 

Gemini B and Laboratory telemetry and tracking data shall be processed in real time and near real time as appropriate and displayed at 

Mission Control. AS a result of the limited loiter time and back-up 

capability of the Gemini B, the mission control function shall provideextensive support for the flight crew. Close flight crew/Mission. 

Control interaction shall be effected for the initiation of the re-entry 

sequence. 

'SEAL 3-131 

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Title 18, Section 793 and 794, the transmission of which in any manner to an unouthorited person is prohibited by taw 
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3. 3. 9. 2 Flight Operations Support tS-4) 

Flight Operations Support will be furnished for Mission: Control at the. 

STC and at remote stations of the SCF. This support encompasses 

interfaces with Test Support and Recovery, the mission-peculiar 

computer programs, the ground system simulation equipment and 

computer programs, and the mission operations personnel, techniques 

and procedures. This support also shall provide the capability for 

control of diverse cooperative mission support forces. 

3. 3. 9. 2. 1 Satellite Test Center \-3 SAR) 

The STC shall provide the following capabilities. with the manned functions 

deleted for the unmanned flights: 

(a) Control and display consoles for powered flight, 

:rte life support, biomedical monitoring, OV subsystems, mission payload monitoring and 

control 

(b) Control and display capability for ground support and recovery control 

(c) Working areas for operations planning, 

analysis, control, and biomedical staffs 

(d) Mission analysis and control staff working 

areas 

(e) Display subsystem providing a limited number 

of large screen displays for special events, 

displays for control consoles and supporting 

staffs 

(f) Data buffering storage and retrieval subsystem 

for formatting, buffering, filing, retrieval, 

and outputting telemetry data 

(g) Interfaces with the launch and checkout 

complexes 

(h) Command storage and processing subsystem 

(i) Mission security capability 

Real time computer complex for trajectory 

and orbit related computation 

(k) Communications switching, terminal, technical 

monitoring, and control facility 

3-132 SECIIEL 

..this document contains information affecting the notional defense of the United States within the weaning of. this Espionage lOwi. 

Title IL Section >93 and 794, the transmission of which .in any /manner to an ,,nouthonted person is piohibtled by law . 
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1SREL 

The major computational and data handling functions for powered flight, 

orbit and recovery shall be performed by a large computer center 

operated as part of or in direct support of Mission Control operations. 

On-line telemetry processing, buffering, filing, and display driving 

shall be allocated to small buffer computers .located within the STC. 

Remote, site data processing functions shall be allocated to available 

network station computers. 

3. 3. 9. 2. 2 Operational Computer Program Support 11S.c4) 

The Operational Computer Program support shall consist of all mission peculiar computer prograMs required for the entire MOL mission 

integrated into a compatible system (Reference SSD 61-47A). Major 

..computer program functions required of the large computer center 

shall include: 

(a) Tracking data editing and conversion 

(b) Trajectory calculations 

(c). Impact prediction (including abort AV and 

delay options, for manned flights. 

(d) Coordinate conversion of telemetered booster 

and Gemini guidance data for manned flights. 

(e) Orbit injection (including ACTS thruster and 

retro-rocket options'for manned flights) 

(f) Command synthesis 

(g) Orbit determination and related computations. 

(h) Injection burn-time and vehicle altitude • 

(1) Retrofire and recove vehicleslicableto Gemini 

B and Data Re-entry 

(j) Ephemeris-related computations 

(k) Network station acquisition tables 

(1) Mission Payload data processing 

(m) Mission Payload support -- orbit related 

(n) Telemetry and event processing and display 

(including post-event correlation) 

(o) Orbiting Vehicle status/malfunction monitoring 

(p) Orbiting Vehicle crew operations scheduling for 

manned flights. 

(q) Flight operations planning and scheduling 

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• 
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In addition a number of program components shall be provided to integrate and complete the above functions. The most significant of these 

is executive control, which will allow the execution of the program 

elements according to priorities that vary with the mission phase. 

Other routines required include the utility programs (compilers, 

assemblers, input/output routines, etc.), standard arithmetic routines 

(trigonometric, matrix operations, integration/differentation, etc.), 

and error detection and correction programs. Major computer program functions required of the small buffer computers include: 

(a) Network station prepass information 

(b) Data acquisition 

(c) Tracking sensor data input and conditioning 

r (d) Telemetry data conditioning and format 

conversion 

(e) Telemetry display 

(f) Telemetry alarms and checks 

(g) Telemetry data file for retrieval 

(h) Command execution and verification 

3.3. 9. 2.3 Ground System Simulation Support N4) 

The Ground System Simulation Support shall provide the capability to 

simulate all mission phases and operations and shall provide a means 

for training flight clews, flight directors and controllers, and support 

personnel located within the STC and related support areas including 

the network stations. In addition, the support shall provide a means 

of: (1) checking all operational Mission Control programs, (2) validating and accepting special MOL STC equipment, (3) training and rehearsing network station operational personnel, (4) validating cornmu.nications lines to remote areas and control centers prior to a 

mission, and (5) finally developing and validating Mission Control and 

payload control procedures. 

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Tole 111. U.S C.. Section 793 and 794, the tronsintssion of which in any manner to on unouthonted• person is prohibrted by law 
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3 -135 

This support shall make use of the Mission Simulator suitably interfaced 

to Mission Control. Simulation modes shall include both open-loop and 

closed-loop with various configurations of the total network. 

The modes of simulation with Mission Control shall include: 

(1) Powered flight simulation through the actual 

real time data handling and communications 

system developed for actual powered flight. 

Network Station simulation through a 2400 bit 

per second data line and other communications 

in the same format as used by the actual primary 

network stations. 

The generation of suitable simulation tapes for use 

by actual network stations. 

al 3. 9. 2.4 Network Support ? ? 

The Network Support shall provide remote site tracking, 

telemetry, command, and voice functions which support on-board OV 

Vehicle Communications and tracking systems. Site capabilities shall 

include data acquisition, data handling, display, and intra/inter-site 

communications. The SGLS will be operational at all SCF sites for the 

MOL flights. 

Primary SCF support locations shall include: (1) Guam; 

(2) Kaena Point, Hawaii; (3) Kodiak, Alaska; (4) New Boston, New Hampshire; 

and (6) Vandenberg, California. The SCF Indian 

Ocean Station will support early orbit and contingencies. Each site shall 

be capable of verifying, in a specified time, their subsystem performance 

on an individual basis as well as verifying the total site configuration 

and ability to support the MOL mission. Validation of two.-way interchange 

of data with Mission Control shall be possible. The extent to which the 

site remains fixed in the MOL support configuration depends upon the 

time required and confidence achieved in the checkout and verification process. 

For manned flights, supplemental coverage to that of 

the SCF will be required during early orbits an on an emergency call-up- 

(3) 
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ot72 

basis to improve crew safety and mission success probability. Such 

coverage shall be limited to UHF voice communications with the flight 

crew. Locations which provide coverage in early orbit and are capable 

of filling gaps in SCF coverage include the NASA installations at 

Carnarvon, Grand Canary, and Tananarive; such ETR installations 

as Antigua and Ascension; and the WTR installation at Midway. Present 

studies also consider the possibility of requesting early orbit, loiter, 

and special events. Metric C -band tracking data from these stations 

shall be routed to the STC on an off-line basis via teletype. 

For either manned or unmanned flights, skin track data 

from SPADATS shall be made available. 

3.3.9.2.4.1 Instrumentation X-3 SAR) 

,r. 

The acquisition of mission data and control of the 

'Launch Vehicle by the ground network shall be achieved by the use of 

C -band radar tracking supplemented by precision velocity measuring 

systems for determining position and velocity during powered flight, 

and by S-band telemetry systems for ground monitoring of system 

performance in real time. 

The requirement for mission data and control of the 

OV shall be met using the integrated telemetry, tracking, command, 

and voice (TTC V) capabilities of the S -band Space-Ground Link Subsystem 

(SGLS). 

The capability to simultaneously receive all SGLS 

telemetryiand voice information when applicable, from both the Gemini B 

and Laboratory shall be included at certain primary MOL network stations 

w hich are required for early orbit support; metric tracking and commanding, 

using SGLS, is required only of one link at any given time. Throughout 

the mission all primary network stations shill have the capability to 

select sets of data from any two .PCM telemetry information carriers 

and to display these data locally in real time; it shall also be possible 

to select different sets of data or the same sets of data tor transmission 

to Mission Control in real time. 

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All primary network stations shall provide support to the Orbiting 

Vehicle backup command and telemetry system. 

ror the manned flights only, support of the Orbiting 

Vehicle 20 mbs data link in the S-band (2200 - 2300 Mc RF band)shall 

be provided at four locations: Vandenberg .AFB, New Hampshire, Alaska, 

and a Pacific Island site. During tot-tine on-orbit operations, time 

sharing of status and payload data dumps and the selection and compression 

in real time of a limited amount of7received data for transmission to 

Mission Control shall be normal modes of operation. 

Voice transmission and reception in the RF band of • 

225-400 Mc, using AM modulation, shall be required as a minimum at 

all network stations for all manned flights. 

,e. Transmission of complex digital command loads 

from primary network stations shall be limited to quasi-real time in 

which commands are sent to the station prior to the pass and transmitted 

during the pass at the appropriate time. All primary network stations 

must have the capability to command and update the Gemini B systems 

as required for manned flight re-entry. 

For manned flights, the capability must exist continuously 

. to compute the impact point on the basis of a tracking pass after retrofire or after receipt of voice information of the time of retrofire, attitude, 

re-entry profiles, and on-board instrument readings. 

-addition,-:-sufficient DRV re-entry data must be provided to the 

SCF Recovery Con rol Group in time to permit location and air-snatch 

recovery. 

3. 3. 9. 2. 4. 2 Communications "3 SAR) 

The ground communications network shall use the 

existing and planned NRD, STC, and in some cases for maimed flights 

NASA networks. When applicable, sufficient channel capacity and 

reliability shall be provided to support flight crew-to-Mission Control 

voice, network stations control voice, telemetry data transmission, 

command control, and tracking data transmission. All launch network 

stations, including the, injection ship and the SCF on-orbit stations, 

shall be netted with the STC utilizing hardline or equivalent circuits. 

Communications satellites may be used where appropriate. 

3-137' 
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The use of encrypted space-to-ground, ground-to-space 

communications systems for both voice and data is required; encrypted 

circuits from and to the STC for all SCF network stations shall be provided. 

For the manned flights, full duplex voice circuits from the network stations 

to the STC shall be employed for OV-to-ground voice relay. The capability 

for remote site keying of the ground-to-space transmitters from the STC shall 

be implemented at all SCF stations todlow direct communications between 

Mission Control and the flight crew. This capability is desired from all 

other stations utilized for voice-only transmissions where communications 

circuits permit, but it is not mandatory. In all cases the local station 

controller shall have a patch-in capability for local transmissions. 

Certain SCF stations shall be equipped with secure systems for flight 

crew voice reception and transmission utilizing SGLS and shall be equipped 

with secure ground communications for direct relay of classified voice 

information to the STC. 

3.3.9.2.4.3 Data T ran smi s s iontru-..4-)-165.-- 3 54R) 

.ri en a e f to achieve real time control for manned flights, telemetry 

and metric tracking data for the powered flight phase of the mission shall 

be transmitted to the STC from the launch site area and down-range 

ships utilizing redundant wideband data lines for real time control. For 

all flights,at all primary SCF network stations, secure 2400 bps data 

lines shall be utilized for the real time interchange of telemetry, tracking 

and command data with the STC. The backup mode for all data during 

both powered and orbital flight shall utilize teletype circuits where data 

lines are not achievable due to communications or equipment limitations. 

3.3.9.2.4.4 Meteorological Support%tS-4) 

Meteorological Support shall provide weather data 

obtained from various reporting and forecast sow ces necessary to support 

the MOL mission. 

3.3.9.3 Functional Interfaces (U) 

(Functional interfaces shall be listed here when defined 

by the cognizant Interface Control Working Group - ICWG.) 

3.3.9.4 Contract End Items (U) 

The contractors shall define the range support requirements in sufficient depth to permit the extraction of those requirements 

as direct inputs to the appropriate range support documentation specified. 

in chapter 3 of SSDM 80-1. 

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3.3.9.5 Payload Operation Control Requirements 

3.3.9.5.1 Ground Support System Requirements 

The major ground support system requirements for command and 

control of the Dorian System consist of: 

a. Processing of tracking data and determination of orbit 

parameters. The orbit determination and ephemeris prediction shall have the 

following accuracy: The error in extrapolation of the position of the vehicle 

22 revs beyond the .1att set of tracking data shall not be greater (20-) than 

0.2 nautical miles in track, 0.1 nautical mile cross track, and 0.1 nautical 

miles in altitude with respect to the reference geoid (World Geodetic System 

1960). The capability to update the orbit determination and ephemeris prediction every orbit revolution shall exist in the software. 

b. Processing of target list data and orbit ephemeris data 

to accomplish target selection. The system shall be capable of accomplishing 

target selection within one-half hour of receipt of a changed target list 

and/or new target weather information. 

c. Transmission of orbit parameters and target information 

to the vehicle. During manned operations/ predicted weather for upcoming 

targets also will be furnished. The capability to transmit updated orbit 

parameters to the vehicle within one orbit revolution of receipt of the tracking 

data for the orbit update shall exist, provided an SCF tracking station is 

available. 

d. Recording and processing data transmitted from the vehicle 

(e.g., Data Readout System). 

e. Analysis of Dorian System performance and status from 

data (e.g., telemetry) transmitted from the vehicle. The ground system 

(including personnel) shall be capable of a complete status analysis .of- all 

Dorian System components within one-half hour of transmission of telemetry 

data to an SCF tracking station. A capability for preliminary status analysis 

of major Dorian subsystems while the transmission is taking place shall also 

exist. 

f. Computation of DRV re-entry parameters for control of 

DRV ejection. Pertinent data will be transmitted to the vehicle and used 

to control time of ejection. 

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3.3.10 Recovery System Sejment /•■cc

4) (Manned Flights Only) 

The Recovery System Segment includes those forces deployed to 

support planned, contingency, and emergency recovery modes as 

well as pad and ascent aborts. Although Recovery. Control shall be 

exercised as an element of Mission Control, this segment also 

includes those communication and control networks peculiar to the 

Recovery Operation. 

3.3.10.1 Recovery Operations X1/4-4) 

The recovery system shall make maximum use of those equipments, 

techniques, and procedures developed for Gemini/Apollo recovery 

support which are appropriate for MOL. The track/search operations will make use of aircraft and ship direction-finding (DF) equipment compatible with the Gemini- B HF and UHF recovery aids. A 

flashing light and sea marker will be used as visual search aids. 

Extensive support shall be required of the world-wide communication 

system to handle emergency as well as planned re-entry. Relatively 

continuous voice coverage should be provided. In general, recovery 

communications shall be by a network other than the normal tracking 

and communications network; however, the hardwire capability of the. 

tracking and communications network shall supplement recovery 

communications where applicable. 

3.3.10.2 Recovery Force X-4) 

The recovery force shall be comprised of sea, land, and air units, 

associated crews, and specialist teams as necessary to meet the, 

performance requirements 9f recovery. Such resources shall be 

provided from existing government sources wherever possible and 

practicable. Aircraft and ships shall be provided in such quantities 

and at such locations in the designated recovery areas or appropriate 

bases as is necessary to effect retrieval of the spacecraft and crew 

within the required access times. Special high-density recovery 

37141 • 

FORM This document contains information affecting the notional defense of the United Stoles within the.rniraning of the Espionage Lows, 

SSD AUG 62 20E3 Title I8„ U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthorized person is.prohibited by tow . 
NRO APPROVED FOR 

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--CORSENTIAL,_ 

forces shall be provided in the immediate area of the launch pad and 

downrange along the ground track to ensure recovery of the crew 

following launch phase abort. These forces shall be comprised of 

fixed (HC-130) and rotary wing (HH-3C) aircraft, land vehicles, 

amphibious vehicles, and sea craft, and shall be capable of immediate 

reaction in case crew abort is initiated. Recovery forces shall use 

both HF and UHF direction-finding equipment as the primary tracking 

system below the ionization blackout region and selected elements 

will be equipped to carry a para-rescue crew. Recovery aircraft 

and sea craft shall be deployed in the planned recovery areas during 

period of planned recovery. At other times and in other areas, 

recovery aircraft shall be in a location and'state of readiness to 

support contingency and emergency areas along the ground track. 

r3. 3. 10. 3 Access and Retrieval l‘g-4) 

Access time is defined as the time from determination of impact to 

the time when the flotation gear is rigged and first level medical 

assistance is provided to the crew. Access times vary during 

mission phases as a result of crew safety criteria and will be determined at a later date. 

3. 3. 10. 4 Post Recovery X-4) 

Post recovery operations include crew medical care and debriefing 

and safe packaging of Mission Payload data. Data and crew shall be 

returned to locations to be specified. 

• 

3-142 

This document contains information of feCting the national defense of the United States within the meaning of the Esp000go tows. 

Tole 111. U.S.C.. Section 793 and 794. the iransmis■ion of which in any manner to on vnouthotized person is plobiblsost by low 
MEMANDLING 

3.3.10.5 Payload Recovery Requirements 4Mannedladdathmattlid) 

3.3.10.5.1 General 

Photographic record will be returned by means of Data 

Re-entry Vehicles and in the manned version vitt Gemihif, B, as well. 

Recovery forces shall provide adequate security for recovered payload 

record until turned over to properly designated courier. 

3.3.10.5.2 DRY Recovery 

Data Re-entry Vehicles will be deorbited, re-enter and be 

air recovered in the Hawaiian area. Provision for backup water recovery 

will be provided. 

SPECIAL HANDLING 
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3. 3. I 1 Test Support System Segment (X-4) 

The Test Support System Segment consists of all 

requirements(over and above those support capabilities that exist as an 

integral part of the SCF) for support furnished the Launch Operations 

System Segment, the Flight Operations and Support System Segment. 

In particular, this segment includes support of pre-launch, launch, ascent, 

and any remote station support-as may be required especially for manned 

flights. Such support includes the planning for, acquisition of, and 

operation or control of the equipments, communications, computers, 

computer programs, personnel, techniques, and procedures necessary 

to support MOL operations. The segment also includes appropriate 

provisions for integration, simulation, training, and support exercising. 

-Pest Support shall function as an element of the total operational test 

system, with functional performance during each operational phase 

as appropriate. Pre- and post-test data are also included in this 

segment. 

3. 3. 11. 1 P.re -Launch Support (\-4) 

Support of pre-launch operations shall begin in the form 

of planning for integration of all operations-support elements external 

to that provided by the SCF. This planning must include: any remote site 

telemetry, tracking, command and/or voice supplemental requirements; 

interstation and center communications; extensive meteorological 

support; data handling and computation; and Range support for launch 

and ascent coverage. As operations progress towards launch, pre-launch 

support shall be more significantly involved in providing those services 

necessary to assure launch, and.will. include services for both flight 

hardware and flight crew. 

3. 3. 11. 2 Launch and Ascent Support 1'61/4-4) 

In addition to providing for smooth phase -over of support 

services from pre-launch to launch, the employment of the resources in 

-the launch site area shall also include all the ground instrumentation 

necessary for the initial powered flight phase. Ascent support downrange for all flights shall include one range instrumentation ship to 

achieve down-range coverage through insertion, plus approximately 30 secs. 
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7 d Is 

For manned flights, a range instrumentation ship 

having precise navigation, C -band tracking, multiple link PCM telemetry, 

voice, real time display and computation, and high-speed data communications capabilities is required for injection coverage. From the ship, 

reception of selected Gemini B and Laboratory SGLS telemetry, as well. 

as Launch Vehicle S-Band telemetry, will be required for real-time 

monitoring and control; the SGLS up-link capability is not mandatory. 

The ship. shall have reliable 1-...igh-speed data communications with 

C:ontrol, Tracking of the C_ and impac, is 

7'ec;:.;.:.red for an .a..1..-sc.ft during d 

-z. _ unmanned flign...s: instrurr..,..,:ion ship 

.6 minimum record all 1'v links 

perform predict on misslc.n. 

shic shall h..,72= relia:.)..e- C 01.n viith 

Con.trol 

- -On :bit and RecoverySupport Ns4) 

yr y .port for these phases includes supplemental 

world-wide remote es necessary 1.o sati,fy Orbiting '7.rehiciarequ.rernexi_ Se), EasLorn and West-4:m Test Range. 

(WTR) a prearranged ca;.1.!-1% - .i: 

basis laize coverage. In 

C-Banel -2adar tra.c.`ivng WTR, and NASA stations 

shall be provided, o on a :;rearranged basis for emergency 

or back-up support of either the Orbiting `..rehicle or Gemini B using 

the C -Band transponder located in ....he Gemini B. Metric .0 -Band • 

tracking data from these stations shall be routed to the STC on an 

off-line basis via teletype and the STC shall be equipped to accept those 

metric data and perform the data conversions necessary for STC 

orbital calculations. 

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1 

Any ships active in Test Support shall be on planned standby to support 

special events or emergencies. These ships shall be responsive to 

the Recovery Segment for possible supplementary support to operations 

requireMents. 

•fo 

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FORM This document contains information affecting the notional defense of the United Stores within the meaning of the Evil:swat Lows,. SSD AUG 62 208 Title tg, U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by law 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 12 Flight Crew System Segment 

3. 3. 12. 1 Allocated Performance and Design Requirements 

3.3.12.1. 1 Flight Crew Complement and Performance 

Allocation l'ess4) 

The flight crew shall perform vehicle control, monitoring, primary 

and back-up control of subsystems, maintenance of certain systems, 

mission operations, information management, certain mission control 

decisions, extravehicular activity, and personal maintenance together 

with monitoring and maintenance of crew'health. 

3. 3. 12. 1. 2 Crew Task Definition (U) 

Crew Tasks shall be defined by mission requirements and evaluated 

'by- functional time line analyses. 

3. 3. 12. 2 Peculiar Performance and Design Requirements 

3. 3. 12. 2. 1 Flight Crew Selection and Training 

3. 3. 12. Z. 1. 1 Flight Crew Selection (U) 

The MOL SPO shall have primary responsibility and control of flight 

crew selection. 

3. 3. 12. 2. 1. 2 Flight Crew Training (U) 

The MOL SPO shall have primary responSibility for flight crew training. The training will consist of briefings on MOL operations, mission 

plans, communications, data.handling, experiments, and other related 

technical areas. In addition, this training will cover static representation of MOL subsystems, operations or equipments, dynamic simulations of the operating situations, and combined static and dynamic 

simulations as described below. 

3. 3. 12. 2. 1. 2. 1 System Function Training (U) 

System training shall cover the study or demonstration of design 

function or operation of a single system or subsystem of a major ' 

segment of the MOL. 

3-147 

this document contains information affecting the notion, defense of the United Stoles within the meamng of the Espionage taws. 

Tide IS. U.S.C., Section 793 and 794, the transmission of which m any manner to an unouthorited person is prohibited by law 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3.12.2. 3.12.2. 1. 2. 2 1. 2. Part-Task Training (U) 

Part-task trainers shall be used in training for selected function or 

functions of the MOL mission operation where specific critical skill(s) 

is required. 

3. 3. 12.2. 1. 2. 3 Procedures Training (U) 

Procedures training simulates an operation of an entire segment of 

the MOL system, including operation under contingency conditions 

for the Gemini B and Laboratory System Segments. The Laboratory 

procedures trainer must incorporate major operational systems as 

warranted. The trainers needed for this purpose shall incorporate 

the fidelity required for realistic and meaningful simulation. 

3. 3. .

r

12. 2. 1. 2. 4 Mission Simulation (U) 

Two complete mission training simulators, incorporating the procedures trainers insofar as possible, shall be developed to provide for 

both separate and integrated simulation of all whole mission and 

system segments of the MOL. This shall include interacting ground 

support facilities with which full mission operations can be planned, 

developed, validated, and rehearsed. 

3. 3. 12. 2. I. 2. 5 Environmental Training (U) 

Training shall be provided in special environments involving positive 

acceleration (centrifuges), weightlessness (zero-g aircraft), and 

reduced pressures and special atmospheric compositions (space 

chambers). 

3.3. 12.2.1.2. 6 Engineering Development Simulation (U) 

Simulation of selected system elements will be provided on engineering development simulation equipment to provide early crew inputs for 

the design phase and to familiarize the crew with equipment and 

operating problems. 

3-148 CONFIDENTIAL— 

This document contains informotion allotting the notional defense of the United States w•thin the meaning of the Espionage Lows. 

Title la, U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthorised person is prohibited by law 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 12. 2. 2 Training and Proficiency Data (Deleted) 

3. 3. 12. 2. 3 Man-Equipment Design Validation (Deleted) 

• r•

3. 3. 12. 3 Functional Interfaces (U) 

(Functional interfaces shall be listed here when defined by the cognizant Interface Control Working Group - ICWG. ) 

3. 3..12. 4 Contract End Items (U) 

(The contractor shall provide for incorporation in this paragraph a list 

of the Contract End Items by CEI specification number, nomenclature, 

and the CEI into which it installs. This paragraph shall list all end 

items being provided- under these system segments. ) 

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FIRMLY ;SI D — C; 11, SECRET 

3'.3.12.5 Flight Crew Dorian Support Requirements (Manned Version only) 

3.3.12.5.1 General 

(later) 

3.3.12.5.2 Training 

(later) 

3.3.12.5.3 Target Acquisition and Tracking 

(later) 

3.3.12.5.4 Film Handling 

(later) 

3.3.12.5.5 On-orbit Optics Alignment 

(later) 

3.3.12.5.6 Data Readout Support 

(later) 

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4.0 PERFORMANCE/DESIGN VERIFICATION AND TEST 

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. (U) 

The basic document specifying the external environment 

to which the MOL shall be exposed is SSD Exhibit 65-7, Environmental 

Criteria for the MOL System. 

4. 1 GROUND TEST REQUIREMENTS 

4. 1. 1 Development Tests 

44, 1. 1 General Requirements 

Design development tests: shall be performed to determine 

design feasibility, design adequacy, equipment performance, effectiveness, 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 teats are continued throughout the program. 

4.1. 1.. 2 Over-all System Requirements 

No full scale ground development tests at the Flight 

Vehicle system level are required. Sub scale model wind tunnel tests 

of the MOL Flight Vehicle shall determine aerodynamic characteristics of 

the combined vehicle. 

4. 1. 1.3 Orbiting Vehicle Requirements 

4.1.1.3.1 Antenna Tests (U) 

Complete antenna patterns of all flight antenna subsystems 

shall be obtained using sub scale and/or full scale models. 

4. 1. 1. 3. 2 Compatibility Test 

• Tests shall be conducted on the Orbiting Vehicle System 

Segments to demonstrate physical, functional, and EMI compatibility. 

CONFIDENT:1AL 

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4.1.1.4.. Laboratory Vehicle Requirements 

4.1.1.4.1 Structural Tests (U) 

A static test to ultimate loads shall be performed on the 

primary shell structure of an assembled Laboratory Vehicle 

In addition static ultimate load tests shall 

be performed on all major structural assemblies not tested in the shell 

structure test. Ultimate load factors are given in the Laboratory Vehicle 

System Structural Criteria. The thermal environment shall be simulaed 

or the loads shall be increased to account for reduced allowables under 

operating temperature. 

The Laboratory Vehicle (or sections thereof) shall be 

subjected to pyrotechnic shock excitation by discharge of the pyrotechnic 

r. 

devices to determine the shock excitation imposed on the Laboratory 

Vehicle subsystems and components. 

A vibration survey shall be performed on the Laboratory.' 

Vehicle with adjacent segments simulated. The dynamic properties 

of all significant subsystems and components not available for 

the teat shall be simulated. 

4. 1. 1.4.2 Leak Test • 

After the static test article of the above section has 

been tested to limit load, the load shall be removed and a leak test run. 

Comparison shall be made with a leak test performed before the load 

is applied. All sealing must be complete for the test. 

4. 1. 1. 4. 3 Acoustic Test (U) 

The Laboratory Vehicle (or sections thereof) shall be 

subjected to acoustic testing to determine the acoustic and vibration • 

response imposed on the Laboratory Vehicle subsystems and components. 

Laboratory subsystem prototypes shall be installed,..and if not..availabler, ' 

mass simulated components will be used. 

4. 1. I. 4. 4. Subsystem Tests (U) 

Separate subsystem development tests shall be made 

to verify design adequacy. Such tests shall include demonstration of onorbit and critical ground maintenance tasks. 

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4.1.1:4.5 Attitude Control Simulations (U) 

Appropriate air-bearing or servo-driven table 

simulations to verify the control electronic and propulsion subsystem 

capability shall be performed for all control modes. 

4.1.1.4.6 Meteoroid and Particle Radiation Test (U) 

Adequacy of the Laboratory Vehicle structure to withstand 

meteoroid impact shall be established by-analysis based on test results 

simulating meteoroid impact on representative structure and on appropriate 

theory of meteoroid impact. 

4. 1. 1. 4. 7 Atmospheric Contaminant Test 16.4) 

A materials atmospheric contaminant test shall be 

conducted on the pressurized atmospheric environment of the Laboratory 

in a thermal vacuum space simulation chamber for a time period sufficient 

to identify contaminants and establish 30-day contaminant concentrations.' 

Broad spectrum measurements by infrared gas chromatographic and/or 

mass spectrophotometric techniques will be used to determine significant 

toxic contaminants. 

4. 1. 1. 4. 8 Space Simulation Test (U) 

The Qualification Test Vehicle (laboratory module) shall 

be tested in a thermal vacuum space simulator to verify design adequacy 

of the environmental control/thermal control system and to determine the 

thermal characteristics of the vehicle. 

The mission module Qualification Test Vehicle shall be 

.• 

tested in a thermal vacuum space simulator to determine the thermal 

characteristics of the vehicle. 

For both of these tests the Qualification Test Vehicles 

need not have all flight equipment installed as long as all thermal 

characteristics are simulated. 

Also, in both tests segments affecting the thermal balance 

shall be used or simulated to provide valid thermal interfaces. 

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CONFIDENTIAL 

4.1.1.5 Gemini B Requirements 

4; 1.1.5.1 General (U) 

The requirements for Gemini B development testing 

shall be based on an=: analysis of the changes to the NASA Gemini 

configuration and equipment necessary to meet the MOL environment and 

mission requirements. New and significantly modified components 

shall be designed to Gemini B criteria and shall undergo a complete 

development test program. Tests shall be made to demonstrate the 

physical and functional compatibility, and EMI. 

4.1.1.5.2 Wind Tunnel Tests (U) 

Static force, moment and pressure wind tunnel tests 

0141 be performed on the Gemini B configurations where NASA Gemini 

data do not exist. These tests include those cases where the external 

configuration or flight parameters are significantly changed or where 

present test datakite inadequate or inaccurate. 

4.1.1.5.3 Space Environmental Tests \-4) 

The effects of a prolonged period of inactivity and 

exposure to a 33 day space environment shall be determined by a 

thermal-vacuum.space simulation test on the Gemini B system. Tests 

of individual critical components shall be performed to assess the 

impact of the activation follbwing a 33-day space sta.ndby environment. 

4.1.1.5.4 Structural Tests (U) 

Static tests shall be performed to verify the capability 

of the modified and new portions of the Gemini B spacecraft to meet 

the re quirements of the structural design criteria. Shock and vibration 

tests shall be performed in accordance with environmental criteria. 

4.1.1.5.5 Separation Tests.(U) 

Staging separation tests shall be performed on the 

Gemini B to simulate Laboratory, retrograde, and re-entry module/ 

adaptor separation. 

4.1.1.5.6 Flight Crew Transfer Tests (U) 

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. Transfer with inflated suit and transfer 

of an incapacitated flight crewman in an emergency situation shall be 

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4. 1. 1. 5. 7 Abort Tests (U) 

Additional testing of the spacecraft escape system, 

seat ejection, system and the abort/retrograde rockets; -shall be 

accomplished as necessary. 

4. 1. 1. 6 Mission Payload Segment Requirements 

Developmental simulations shall be required for all 

Mission Payload sub-segments. Complete development tests shall be 

performed to demonstrate performance, and physical and functional 

compatibility, including EMI. 

Man-machine performance parameters shalLbe 

obtained where applicable. 

4. 1. 1. 7 Titan III Requirements 

Requirements for development testing shall be determined 

based on an analysis of Titan III changes required for the MOL mission. 

4.1. 1. 8 Crew Equipment Requirements 

New and/or significantly modified NASA 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 Operations Compatibility Requirements 

Development testing shall b conducted to demonstrate 

proper 'operation and compatibility.of. the:Orbiting Vehicle System, the 

Launch Operations, Flight Operations, Recovery, and Test Support 

System Segments. 

4. 1. 1. 10 Aerospace Ground Equipment Requirements 

Design development testing for Orbiting Vehicle and 

Laboratory Vehicle AGE shall be conducted to verify the design, to 

determine equipment compatibility,•to evaluate performance, and to 

develop procedures. 

4. 1. 1. 11 Orbiting Vehicle Mission Simulator Requirements 3 5419 

Design development of the Orbiting Vehicle mission 

simulator shall be conducted to verify the design, to determine equipment 

,4-5 
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compatibility, to evaluate performance, and to develop procedures. 

Tests shall also be conducted to demonstrate proper operation and 

compatibility of the OV mission simulator interface with the SCF and 

Test Support System Segment. 

4. 1.2 Qualification Tests 

4. 3. 2. 1 General Requirements (U) 

Qualification tests shall be performed to verify 

design adequacy and to demonstrate equipment performance. The test 

conditions shall be determined by the design requirements and consist 

of time and stress level factors on the anticipated environments. 

Qualification tests to all applicable environments shall be performed at 

the,„component and/or subsystem level. In addition thermal-vacuum 

and EMI qualification tests shall be performed separately on the 

laboratory module and mission module Qualification Test Vehicles. 

Qualification tests shall be completed and qualification test reports 

approved on all equipment prior to the flight on which the equipment 

is used. 

4. 1. 2. 2 Over-all System Requirements (U) 

Due to the size and complexity of the Flight Vehicle and . 

OGE Systems, there are no qualification test requirements except 

electromagnetic compatibility at this level of. assembly. Exceptfor 

electromagnetic compatibility and the qualification of the various system 

segments will constitute the qualification of the over-all system. 

The flight vehicle will be qualified for electromagnetic compatibility 

under conditions simulating pre -launch and launch operations 

4. 1. 2. 3 Orbiting Vehicle Requirements (U) 

An electromagnetic interference (EMI)' qualification test 

shall be performed at VAFB on the Orbiting Vehicle system as a complete 

system under conditions simulating pre -launch, launch, and on-orbit 

operations. 

4.1. 2.3. 1 Mission Life Requirements X-4) 

Orbiting Vehicle elements and their subsystems shall be 

qualified for on-orbit life of 33 days. 

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4.1.2.4 Laboratory Vehicle Requirements 

4.1.2.4.1 General s Ss4) 

The Laboratory Vehicle System segment shall be 

qualified both at the module level and at the component/subsystem level. 

These requirements shallibe detailed in the Environmental specification 

and Test Requirements for the MOL System and the Electromagnetic 

Compatibility Requirements Specification (SSD Exhibit 64-4.) 

In general, the components and/or subsystems will 

be tested to all applicable environments whereas the laboratory module and 

the mission module Qualification Test Vehicles shall be performed with 

flight crew equipment and mission equipment installed. The Laboratory module 

thermal vacuum tests shall be the final qualification tests of the EC/LS 

Subsystem, the electrical power subsystem, and the communication and 

data handling subsystem. In addition, the tests shall establish the 

capability of electro/mechanical control functions originating in the 

laboratory module to be properly transmittedtto and executed in the 

mission module and the Gemini B. Segments or modules adjacent 

to those under test shall be simulated electrically, Imeaa.nically, and 

thermally as required for a valid test of each module. After subsystem 

and safety checks have been performed unmanned in the laboratory 

module thermal vacuum test, contractor personnel shall be used to 

represent the crew segment. • 

4. 1. 2. 5 Gemini B Requirements . (U) 

The Gemini B spacecraft shall be qualified to the 

requirements of SSD Exhibit 65-7 Environmental Criteria Specification 

and SSD Exhibit 64-4 Electromagnetic Compatibility requirements. 

Specific Gemini B components and/or subsystems which are new or 

modified items shall be qualified. Components and/or subsystems 

qualified for NASA Gemini shall not be arbitrarily requalified but the 

necessary testing shall be determined from previous testing and flight 

test hiStory. These tests shall include, as a minimum, the sequence 

of operations during launch, on-orbit, shutdowr and/or standby for an 

extended period of time and re-start and operation for re-entry. 

8 

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4.1.2. 6 Mission Payload Requirements ISs3 SAR) 

The Mission Payload segment shall be qualified at 

the sub-segment or component level using as a basis the environmental 

requirements specified in the SSD Exhibit 65-7 Environmental Criteria 

Specification and the SSD Exhibit 64-4 Electromagnetic Compatibility 

Requirements Specification. 

4.1.2.7 Titan III Requirements (U) 

The Titan III System Segment shall be qualified per 

the requirements of SSD Exhibit 65 -7, "Environmental Criteria for the 

MOL System. " 

4.1.2.8 Flight Crew Equipment Requirements (U) 

Flight crew equipment qualified for NASA Gemini shall 

I.. 

not be arbitrarily requalified, Selective qualification requirements 

shall be determined on a basis of previous flight test history and 

contemplated usage in the MOL system environment. The flight crew 

equipment shall be subjected to a qualification test including the sequence 

of mission ope rations from launch, on-orbit including extravehicular 

activities ?re-entry, and recovery. 

Training equipment and simulators shall be qualified 

to requirements consistent tvith their application and interfaces with 

other equipment as specified in the contract end items specifications. 

4.1.2. 9 Launch Operations, Flight Operations, Recovery, 

and Test Support Equipment Requirements (U) 

Formal, qualification of the over-all operation of 'the 

equipment and procedures for these segments shall be demonstrated 

by successful completion of the functional development testing and 

compatibility testing. 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. 

4.1.2.10 Aerospace Ground Equipment Requirements (U) 

Most of MOL System AGE shall be qualified by acceptance 

test specified in paragraph 4.1.4, Acceptance and Flight Readiness Tests, 

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Ao 

of this specification. Separate qualification tests are required on 

selected AGE items. The list of AGE items to be qualification tested 

shall be submitted to the MOL SPO for approval. 

4. 1. 2. 11 Mission Simulator Requirements (U) 

The Orbiting Vehicle mission simulator shall be 

qualified as specified in Acceptance Tests and Mission Simulator 

Requirements of this specification. 

4. 1. 3 Effectiveness Testing (U) 

All testing performed on the MOL program is considered 

to be a part of the effectiveness effort. Certain tests, such as extended 

time tests, stress limit tests; human factors, and maintainability 

demonstration tests, are to be considered as basic effectiveness tests. 

Extrided time tests consist of cycling the items to the critical 

environments such as vibration, thermal and vacuum, to determine the 

safety margin of the equipment with respect to time. Stress limit tests 

consist of increasing the qualification test levels until failures occur, 

thereby determining the margin of safety with regard to stress. 

Wherever practicable, effectiveness tests shall be phased in with other 

development or proof tests such as the qualification test program. 

4. 1. 4 Acceptance and Flight Readiness Tests 

4. 1. 4. 1 Acceptance Test Requirements (U) 

Acceptance tests shall be conducted on all contract 

end items and deliverable equipment. Deviations on specific items may 

be granted by the MOL SPO. The test conditions shall be comparable 

to end-use environments and severe enough to detect and eliminate discrepancies in 

workmanship and substandard manufacture but not so severe as to cause 

fatigue or wear out. A thermal-vacuum and a vibration acceptance test 

shall be conducted on selected components or subsystems. The ACTS/ 

propulsion shall be static fired in lieu of an operating vibration test. 

A thermal-vacuum acceptance test shall be performed at the module 

or system segment level where applicable. 
NRO APPROVED FOR 

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4. 1. 4. 2 Flight Readiness Test Requirements (U) 

Electromagnetic, 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 (U) 

The acceptance of the Laboratory Vehicle, Flight Crew 

Equipment, and. Mission Payload Segments for the particular flight mission 

objectives, together with a Gemini B, shall be based on mechanical, 

electrical, electromagnetic compatibility, and functional operational .r. 

tests performed after integration of these segments to form the complete 

Orbiting Vehicle. 

4.1.4.4 Laboratory Vehicle Requirements (U) 

All componenets and/or subsystems shall have a 

vibration and a thermal-vacuum test performed in accordance with 

the Environmental Specification and Test Requirements document. 

Deviations on specific items may be granted by the MOL SPO. In addition, 

the Laboratory module shall be subjected separately to thermal-vacuum 

acceptance tests. 

4. 1. 4. 5 Gemini B Requirements (U) 

The Gemini B system segment shall be acceptance 

tested to meet MOL requirements as specified in the approved CEI 

specifications. 

4. 1. 4. 6 Mission Payload Segment Requirements ('S‹ SAR) 

The Mission Payload Segment shall be acceptance 

tested at the segment level. All components and/or subsystems shall 

have a vibration and thermal-vacuum test performed in accordance 

• with the Environmental Criteria for the MOL System. 

_ 

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SECRET 

4. 1. 4. 7 Titan III Requirements (U) 

The Titan HIM Systeria Segment shall be acceptance tested to the provisions of the applicable CEI Specification. 

4. 1. 4. 8 Flight Crew Equipment Requirements (U) 

The flight crew equipment shall be acceptance tested at the component 

and/or subsystem level. In general, the components and/or subsystems will be acceptance tested to vibration and thermal-vacuum conditions while the system flight equipment will be tested to thermalvacuum conditions only. 

zrw 

Training equipment and simulators shall be acceptance tested to requirements of the contract end item specification and by complete 

functional operation. Compatibility with other subsystems and segments shall be demonstrated in all planned sequences and modes of 

operation. (U) 

4. 1. 4. 9 Launch Operations, Flight Operations, RecoveryL 

and Test Support System Segments Requirements (U) 

Formal acceptance of the equipments required for these segments 

shall be based on the successful completion of the functional develop, 

ment testing and compatibility testing. Formal acceptance of individual new equipment is required and shall normally occur following 

installation of the equipment in its location of use and funct1onal testing 

to verify specified perforniance has been conducted. (U) 

4. 1. 4. 10 Aerospace Ground Equipment (AGE) Requirements 

Nfc<i) 

Orbiting vehicle segment AGE.shall be acceptance tested at the contract end item level. Initial acceptance shall be at the manufacturerls 

facility and shall include a thorough physical examination to verify 

4-11 

.This document contains information affecting the national defense of the United Stoles within the Meaning of the EsPiona9e tows. 

'title 18, U.S.C.. Section 793 and 794, the tionsmission of which in any manner to on unauthorized person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

conformance to the specified level of quality as well as functional tests. 

Further acceptance testing shall be conducted at the location of use to 

verify the installation and the ability of combined end items to perform 

their intended function. Complete mechanical and electrical compatibility (including electromagnetic interference) shall be demonstrated. 

Final acceptance of the AGE shall be accomplished during the premission support tasks associated with the first VAFB launch of a complete OV. 

4. 1. 4. 11 Mission Simulator Requirements (U) 

The mission simulator shall be acceptance tested at the contract end 

item level. Initial acceptance shall be at the manufacturer's facility 

and shall include a thorough physical examination to verify conformance torthe specified level of quality as well as functional tests. Further acceptance testing shall be conducted at the location of use to verify the installation and the ability of combined items to perform their 

intended function. Complete, mechanical and electromagnetic interference compatibility shall be demonstrated. Compatibility with other 

subsystems and segments shall be deinonstrated in all planned sequences and modes of simulation. 

4.2 MOL SYSTEM FLIGHT TEST REQUIREMENTS 

4. 2. 1 Test Program Description (3c4) 

The complete MOL System Flight Test and Evaluation consists of formal testing and evaluation including the integration of all system segmer into a complete system in the final operational configuration and 

environment. All MOL System Flights shall be launched from VAFB 

with suitable instrumentation employed to determine the system functional performance, operability, and compatibility of the system segments. 

4. 2. 2 Titan-III Development Flight Test (MOL Flight No. 1) 

Nc4) 

This flight shall be unmanned and orbital. The Titan-III Launch Vehicle shall have modifications incorporated to accommodate the seven 

4-12 '• -101iRDENTIAL, 

FORM This document contoihs information affecting the notional defense of the United States withi, the meaning of the Espionage Lows. 

UG 62 208 Tm. is. U.S.C., Section 793 and 794. the transmission -of which in any manner to an unowhorized person is piohtbited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

segment solid motors, crew safety, mission success, and performance improvement changes. 

The Laboratory section shall be only structurally complete. A boilerplate Gemini shall be used for this flight. Instrumentation shall be included for temperature, acoustic, vibration, pressure, and buffet 

measurements. The primary objectives of this flight are to demonstrate the structural integrity of the Titan III with the MOL-type payload', collect data on the launch and Titan III, demonstrate compatibility of the MOLrtype configuration with ILC concept at VAFB, and 

exercise selected segments of the MOL System. 

4. 2. 3 MOL Develo ment Flight Test (MOL Fli•ht No.2) (U) 

This second MOL flight shall be unmanned. This flight shall be suborbital. The Gemini B shall employ operable subsystems, but the 

Laboratory Vehicle shall be only structurally complete. The Gemini 

B shall be separated from theLaboratory for retro, re-entry, and 

recovery. The primary objective of this test is to evaluate the launch, 

ascent, and re-entry 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 III, Laboratory Vehicle and 

Gemini B combination; re-entry environment and heat shield, and operational readiness of the groUnd and flight systems. Recovery of 

Gemini B shall be accomplished. 

4. 2. 4 MOL Flight Tests (MOL Flight No. 3 and Strbs-eqnetst) 

'15%3 SAR) 

4-46,4fth 

The thirdA MOL Flight,shall be manned with orbital characteristics 

corresponding to the mission. The Laboratory Vehicle shall incorporate all subsystems for system evaluation and a Gemini B with fully 

operable subsystems will be used. The mission duration requirement 

shall be 30 days. The gemini B shall be separated for retro, re-entry, 

"-SEER, 4-13 

• document 'contains information affecting the notional defense of the United Stoles within the meaning of the Espionage Laws, 

I,r!e 18, U.S.C., Section 793 and 794, the fronsmission of which in any monitor to an unouthatized person is prohibited by low. 
,NRO APPROVED FOR 

„:104ELEASE 1 JULY 2015 . 

-SEM, 

and recovery in a primary recovery area. This effort shall demonstrate the orbital capabilities of the Gemini B and Laboratory Vehicle 

systems and demonstrate the Launch Operations, Flight Operations, 

Recovery and Test Support System Segments. As a manned mission, 

the flight will also allow a preliminary check of the biomedical and 

human performance capability of the flight crew on orbit, crew transfer to the Laboratory, the operation of Laboratory Vehicle subsystems, 

and controlled disposal of the Laboratory Vehicle. Verification of 

Gemini B subsystems will be accomplished for launch, on-orbit mission operations, re-entry, and recovery. This flight is a back-up for 

Flight No. 2. 

The fourth las-equent fligitti-eitall be manned and operated for a 

30'-day orbi6,1 flight for operational demonstration of the MOL. System 

in both the manned and automatic modes-.----Theselflight0 shall include the 

mission payload system segment required for demonstration of mission 

objectives. 

2.s mot_ r2../6/y7 rr NO F ./ C ay 75 A NO 5q Watt:riff), 

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4-14 

This document contains information of fatting the notional defense of the United States within the meaning of the Espionoge laws. 

Title 18. U.S.C.. Section 793 and 794.. the transmission of which in any manna, to an unauthorized person is prohibited by low. 
NRO APPROVED FOR 

4".+Y 20,15 ;;: 

ahl ULING 

4.3 L9RIAN SYSTEM FLIGHT CERTIFICATION TESTING 

(Later) 

4.3.1 Qualification Testing 

(Later) 

4.3.2 Acceptance Testing 

(Later) 

SPECIAL HANDUNG 
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5.0 PREPARATION FOR DELIVERY (U) 

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 

This section covers the preservation, packing, packaging, marking 

and storage requirements for all items of equipment required for the 

MOL system. Requirements for subsystems, Gemini B, Laboratory, ' 

Orbiting Vehicle and AGE shall be included in specifications prepared 

by the segment contractors and approved by the MOL SPO. These 

specifications shall be based on methods of space packaging studies 

and techniques developed in connection with other manned programs, 

and include environmental, criteria and packaging hazards peculiar to 

each environment. The testing programs shall insure compatibility 

of the packaging materials and methods with these environments. 

5-1/2 

• 

• • 
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GLOSSARY 

Aerospace Ancillary 

Equipment 

ACTS Attitude Control and 

Translation System 

A-to-D Analog to Digital 

(Conversion) 

AGE Aerospace Ground 

Equipment 

AVE Aerospace Vehicle 

Equipment 

BECO Booster Engine Cutoff 

BOSU Bioastronautics Operational Support Unit 

ILC Initial Launch Capability 

IRIG Inter-Range Instrumentation Group 

ITL Integrate-TransferLaunch (Facility) 

LCC Launch Control Center 

MDS Malfunction Detection 

System 

MGE Maintenance Ground 

Equipment 

MLS MOL Launch Site 

MM Mission Module 

• r• 

National Range Division 

Operational Ground 

Equipment 

Office of the Secretary 

of the Air Force 

Orbiting Vehicle 

Orbiting Vehicle 

Assembly Building 

CEI Contract End Item NRD 

CIP Central Information 

Processor OGE 

CPS Central Power System 

CSF Contractor Support OSAF 

Facility 

OV 

DF Direction-Finding OVAB 

Equipment 

EC/LS Environmental Control/ PBS 

Life Support 

ECS Environmental Control 

System RCS 

EED Electro-Explosive Device REM 

EET Event Elapsed Tithe 

EKG Electrocardiogram SCD 

EMI Electromagnetic 

Interference SCF 

EVA Extravehicular Activity SGLS 

FAA Federal Aviation Agency SRM 

STC 

GSE . Ground Support Equipment 

ICD Interface Control Drawing 

ICWG Interface Control Working 

Group TTCV_ 

IDEP Inter-Servic.e Data 

Exchange Program 

IFS Interface Specification VET 

IGS Inertial Guidance System VOX 

IIP Instantaneous Impact Point 

Program Breakdown 

Structure 

Re-Entry Control System 

Re-Entry Module 

Specification Control 

Drawings 

Satellite Control Facility 

Space-Ground Link 

Subsystem 

Solid Rocket Motor 

Satellite Test Center 

Vehicle Elapsed Time 

Voice 

T-Count Terminal Count' 

TTC Tracking, Telemetry, 

and Command 

_Tracking, _Telemetry, 

Command, and Voice 

This document contains inhumation affecting the national defense of the United States within the insanity of the. Espionage tows. 

Tine 18. U.S.C., Section, 793 and 794. the nenunission of which in any manner to on unauthorised person is prohibited by low.