• • • .-. , 4. a •. 

FOR THE 

MANNED ORBITING LABORATORY SYSTEM 

(MOL) 

• • 

PECat '17e/Mts-m0i,1 

p. 

•. • , . • • • 

PRELIMTNARY PE7MINANCE/ • . 

DESIGN REQUIRFMTTTS 

GENERAL SPECIFICATION FOR 

3 December 1965 

• ' , 

, • ' 

XIAL HAN rt.A. I N CZ

' 

 % 

NOT RELEASABLE TO FOREIC': *NATIOt'!ILDS 

errs-dosed to foreign nations or their reprosentathies. 

; 

DOWNGRADED AT 12 YEAR 

MOL SYST:eMS 0: ?ICE INTERVALS NOT AUTOMATICALLY 

LOS ANGELES AIR F.' STATION DECLASSIFIED. DOD DIR 5200.10 

Thet information contained in this document 

This material contains infmiration affecting tho 

national dr.kiv,z. cf :!1!7.s the 

ti..* U.S.C., 

Scy'iions 793 c.v.: 7:y2 :roirrsi.in or reveta. 

ticn of whin in any inannor to an unauthorized 

person is prohibited by law. 

• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• • „ 

eft 

4 
JOHN L. MARTIN, JR. 

Brig Gen, USAF 

Director for Special Projects, OSAF 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL 

FOREWORD 

The green pages of this Specification provide the additional 

MOL System performance and design requirements which come under 

DORIAN Security procedures for their statement. 

The MOL System must conform to the requirements as 

specified in the combined document consisting of both white and green 

pages. 

RUSSELL A. BERG 

Brig Gen, USAF 

Deputy Director for MOL 

, 
--Let 

R SSE . BERG 

Brig Gen, USAF 

Deputy Director for MOL 

SPECIAL HANDLING 

WO APPROVED FOR 

RELEASE 1 JULY 2015 

• SPECIAL HANDLING 

Specification No. SS-MOL 1 

3 December 1965 

FOREWORD 

Based upon the results of the System Engineering Analysis 

effort to date, various technical reviews, and numerous discussions 

between the MOL Participants, some revisions or changes have 

been recommended and accepted. 

For convenience purposes, these revisions or changes have 

been incorporated into a revised MOL System Specification, 

SS-MO.L 1. 

Changes or revisions to the original MOL System Specification 

are identified by lines or bars inserted in the outside margin 

adjacent to each affected sentence or paragraph. In addition, 

where complete paragraphs .have been relocated within the text, 

the old paragraph number is indicated in the margin. 

All MOL Program participants will insure that their individual 

and consolidated efforts are properly oriented to.comply with the 

requirements included in this Specification. 
A:-.()I• 20 Jan_66___ 

SPECIFICATION CHANGE LOG 

:;!,1 (Incrcrict: No SS- MOL- 1 

PAGI7S 

SCN NO. FCP NO SCN DATE AFrEcTin i'vEm rrIT:crF:n 

0 0 o 0 

N.A. 20-1-66 1-1/2 

2-6 

),. 3-1 

3-2 

3-3/3-4 

3-6 

3-9 • 

3-10 

3-11 

3-13 

3-29 

3-30 

3-31 

3-32 

3-45 

3-46 

3-49 

3-51 

3-55 

3-56 

3-37 

3-58 

3-59 

3-. 61 

3-62 

3-71 

3-77 

3-78 

3-79 

3-83 

3-125 

3-19 6 

3-127 

3-128 

3-1.29 

3-130 

3-132 

3-133 

T 

MOL SYSTEM 

SPECIAL HANDLING A 

.1' 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 6111 .spicApcmatiNG 
O CD 

SPECIAL HANDLING 

As or 20 Jan 66 

SPECIFICATION CHANGE LOG 

SPECIFICATION NO. SS - MOL- 1 

14.7, 

NRO APPROVED FOR 

RELEASE 1 -JULY 2015 

GC iv N‹.). CCP NO SON DATE AFFECTED EF'r r.CTED 

20-1-66 3-135 

3-137 

3-138 

3-141 

3-144 

4-5 

4-6 

4-13 

4-14 

NA 

• . • 

SUPERSEDING • 

MOL SYSTEM 

Cg 

t. 

SPECIAL ANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ME_ SPECIAL HANDLING 

SPECIFICATION 

SPECIFICATION NO. SS 

AS OF 15 Wrch 66 

CHANGE LOG SUPERSEDING 

-MOL-1 

SCN NO. ECP NO SCN DATE 

PAGES 

AFFECTED ITEM EFFECTED 

0 0 0 0 0 

2 0001 15-3-66 3.2 MOL SYSTEM 

3.5 

3.7 

3.8 

3.9 

3.10 

3.12 

3.13 

3.30 

3.45 

3846 

3.47 

3.48 

3.49 

3,51 

3.52 

3.60 

3.62 

3.63 

3.64 

3.67 

3.68 

3.69 

3.73 

3.79 

3.84 

3.85/86 

3,87 

3:88 

'3.89 

3.90 

3.91 

3.92 

3.93 

3.94 

3.95 

3.96 

3.98 

3.99 

3.100 

3.101 

3.102 

3.105 

3.106 

SEEC1AL HANDUNG 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

SPECIFICATION 

SPECIFICATION NO. SS 

AS OF 15 March 66 

CHANGE LOG SUPERSEDING 

-MOL-1 

PAGES 

SCN NO. ECP NO SCN DATE AFFECTED ITEM EFFECTED 

0-. 

(I) 0) 0 0 1) 

2 0001 15-3-66 3.107 MOL SYSTEM 

3.110 

3.111/11; 

3.116 

3.117/11E 

3.120 

3.121 

3.122 

3.123 

3.124. 

3.131 

3.139/14k 

3.144 

3.149/15C 

4.5 

4.6 

4.7 

Glossary 

"tEeRE-T--- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIFICATION 

SPECIFICATION ',. 

AS OF 25 April 1966 

CHANGE LOG SUPERSEDING 

SCN NO. ECP NO SCN DATE 

,',:-. -.,t..;, 

AFFECTED ITEM EFFECTED 

0 (i) 

3 NA 25-4-66 2-3 MDL SYSTEM 

2-6 

2-9 

3-1 

3-5 

3-8 

3-10 

3-31 

3-45 

3-46 

3-62 

3-65 

3-66 

3-77 

3-88 

3-103/4 

3-113 

3-114 

3-117/8 

3-119 

3-120 

3-124 

3-130 

3-137 

• 

-SEW- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 snag SPECIAL HANDLING 

CONTENTS 

1.0 SCOPE 1-1/2 

1.1 Descriptive Title 1-1/2 

1.2 Purpose 1-1/2 

2.0 APPLICABLE DOCUMENTS 2-1 

2.1 Specifications, Standards, and Exhibits 2-2 

2.2 Manuals, Regulations, Publications 2-6 

2.3 Other Documents 2-9 

3.0 REQUIREMENTS 3-1 

3.0.1 General 3-1 

3.0.2 Performance 3-1 

3.0.3 Growth Considerations (Deleted) 3-3 /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 

3.1.2 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 3-32 

3.1.3.5 Transportability and 

Handling 3-33 

• - • 

IBREL SPECIAL HANDLING 
--IT_ SPECIAL HANDLING vi 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 ----SECREF SPECIAL HANDLING 

CONTENTS (Continued) 

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 

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 

3.2.1.1 Selection of Specifications 

and Standards 3-37 

3.2.1.2 Materials, Parts, and 

Processes 3-38 

6 

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 

Replace ability 3-40 

3.2.1.7 Workmanship 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 

3.2.2.4 Civil 3-43/44 

3.2.2.5 Human Engineering 3-43/44 

3.2.2.6 Safety 3-43/44 
3. 2. 2. 7 Maintenance Support 

3. 2. 2. 8 Environmental Criteria . 

3. 3 Performance Allocations 

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

3. 3. 1. 1 Allocated Performance and 

Design Requirements 

3. 3. 1. 2 Peculiar Performance and 

Design Requirements 

3. 3. 1. 3 Functional Interfaces 

3. 3. 1. 4 Contract End Items 

3. 3. 2 Laboratory Vehicle System Segment . 

3. 3. 2. 1 Allocated Performance and 

Design Requirements 

3. 3. 2. 2 Peculiar Performance and 

Design Requirements 

3. 3. 2. 3 Functional Interfaces 

3. 3. 2. 4 Contract End Items 

3. 3. 3 Gemini B System Segment 

3. 3. 3. 1 Allocated Performance and 

Design Requirements 

3. 3. 3. 2 Peculiar Performance and 

Design Requirements 

3. 3. 3. 3 Functional Interfaces 

3. 3. 3. 4 Contract End Items 

3. 3. 4 Mission Payload System Segment . . . 

3-43/44 

3-43/44 

3-45 

3-45 

3-45 

3-46 

3-52 

3-52 

3-53 

3-53 

3-55 

3-85/86 

3-85/86 

3-87 

3-87 

3-88 

3-102 

3-102 

3-103/104 

3-103/104 

3-103/104 

3-103/104 

3-103/104 

3-105 

3-105 

vii 

3. 3. 4. 1 Allocated Performance and 

Design Requirements 

3. 3. 4. 2 Peculiar Performance and 

Design Requirements 

3. 3. 4. 3 Functional Interfaces 

3. 3. 4. 4 Contract End Items 

3. 3. 5 Crew Equipment System Segment . . 

3. 3. 5. 1 Allocated Performance and 

Design Requirements 

PICO ///f/l/S/N1 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• CONTENTS (Continued) 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CONTENTS (Continued) 

3. 3. 5. 2 Peculiar Performance and 

Design Requirements 

3. 3. 5. 3 Functional Interfaces 

3. 3. 5. 4 Contract End Items 

3-108 

3-111/112 

3-111/112 

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

3. 3. 6. I. 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 
NRO APPROVED FOR 

41 RELEASE 1 JULY 2015 

411111 CONTENTS (Continued) 

3. 3. 10.4 Post Recovery 3-142 

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 Requirements 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 

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. 2 Qualification Tests 4-6 

4. 1. 3 Effectiveness Testing 4-9 

4. 1. 4 Acceptance and Flight Readiness 

Tests 4-9 

4. 2 MOL System Flight Test Requirements 4-12 

4. 2. 1 Test Program Description 4-12 

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) 4-13 

5. 0 PREPARATION FOR DELIVERY 5-1/2 

5. 1 Packaging 5-1/2 

GLOSSARY 

15? 
NRO APPROVED FOR 

RELEASE 1 JULY. 2015 

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 

osi 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL 

SUPPLEMENTAL CONTENTS 

1.3 

2.4 

TITLE PAGE 

FOREWORD 

Mission 

Additions to Applicable Documents Listing 

Page 

1-3 

2-11 

3.0.4 Mission Requirements 3-4.1 

3.0.4.1 Photographic Resolution 3-4.1 

3.0.4.2 Target Access 3-4.1 

3.0.5 Secondary Mission Requirements 3-4.1 

3.1.1.4 Mission Characteristics 3-16.1 

3.1.1.4.1 Target Selection Capability 3-16.1 

3.1.1.4.2 Data Retrieval 3-16.1 

3.1.1.4.3 Command and Control 3-16.1 

3.1.1.4.4 Mission Orbital Envelope 3-16.2 

3.1.1.4.5 Quick Launch Reaction 3-16.2 

3.1.1.4.6 Target Acquisition 3-16.2 

3.1.1.4.7 Smear Limits 3-16.2 

3.1.1.4.8 Data Reconstruction 3-16.3 

3.1.1.4.9 Orbital Reaction Times 3-16.3 

3.1.1.4.10 Flight Crew Requirements 3-16.4 

3.1.1.4.11 Security of Operations 3-16.5 

3.3.1.5 Mission Peculiar Requirements, Orbiting Vehicle 3-52.1 

3.3.1.5.1 Orbiting Vehicle Vibration Limitations 3-52.1 

3.3.1.5.2 Malfunction and Post-Gemini Separation Operations3-52.1 

3.3.1.5.3 Mission Payload Ground Handling 3-52.1 

3.3.2.5 Mission Peculiar Requirements, Laboratory Module 3-86.1 

3.3.2.5.1 Space Allocation Requirements 3-86.1 

3.3.2.5.2 Maneuvering Capability Requirements 3-86.1 

3.3.2.5.3 Alignments 3-86.1 

3.3.2.5.4 Electric Power 3-86.2 

3.3.2.5.5 Mission Module Structure 3-86.2 

xi 
NRO APPROVED FOR 

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SUPPLEMENTAL CONTENTS (continued) 

Page 

3.3.3.5 Mission Peculiar Requirements, Gemini B Module 3-102.1 

3.3.3.5.1 Gemini Film Data Return 3-102.1 

3.3.4 Mission Payload System Segment 3-104.1 

3.3.4.1 Mission Payload System Segment Components 3-104.1 

3.3.4.2 General Performance Allocations 3-104.2 

3.3.4.2.1 Weights 3-104.2 

3.3.4.2.2 Disturbances Due to Mission Payload 

Equipment 3-104.2 

3.3.4.2.3 Design Considerations 3-104.2 

3.3.4.2.4 Flight Termination System 3-104.2 

3.3.4.2.5 Explosive Devices, Squib Simulator 3-104.2 

3.3.4.2.6 Launch Safety 3-104.3 

3.3.4.2.7 Weight and Balance 3-104.3 

3.3.4.2.8 Alignment 3-104.3 

3.3.4.2.9 Minimum Time Between Targets 3-104.3 

3.3.4.3 Mission Module Section 3-104.4 

3.3.4.3.1 Mission Module Structure 3-104.4 

3.3.4.3.2 Thermal Control Subsystem 3-104.4 

3.3.4.3.3 Navigation and Control Requirements 3-104.4 

3.3.4.3.4 Electrical Power and Distribution 

Subsystem 3-104.10 

3.3.4.3.5 Data Readout Subsystem 3-104.11 

3.3.4.3.6 Acquisition and Tracking Scopes 3-104.12 

3.3.4.4 Data Re-entry Vehicle Section 3-104.13 

3.3.4.4.1 General Requirements 3-104.13 

3.3.4.4.2 DRVS Structure and Packaging 3-104.13 

3.3.4.4.3 DRVS Environmental Control 3-104.13a 

3.3.4.4.4 Minimum Acceptable Reliability 

Level 3-104.13a 

3.3.4.4.5 Prelaunch Testing 3-104.14 

3.3.4.4.6 Data Re-entry Vehicle (DRV) 3-104.14 

3.3.4.5 Photographic Section 3-104.17 

3.3.4.5.1 General 3-104.17 

3.3.4.5.2 Operational Requirements 3-104.19 

SPEP 

xii 
NRO APPROVED FOR 

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SUPPLEMENTAL CONTENTS (continued) 

Page 

3.3.4.5.3 Camera 3-104.19 

3.3.4.5.4 Optical Design/Performance 

Requirements 3-104.20 

3.3.4.5.5 Record Handling 3-104.24 

3.3.4.5.6 Photographic Format 3-104.26 

3.3.4.6 Mission Payload Peculiar AGE Requirements 3-104.31 

3.3.4.7 Functional Interfaces 3-104.33 

3.3.4.8 Contract End-Item List (CEI) 3-104.33 

3.3.7.5 Mission Payload Peculiar Facility Requirements 3-122.1 

3.3.7.5.1 Communications 3-122.1 

3.3.8.5 Mission Payload Peculiar Launch Operations Support 3-124.1 

3.3.8.5.1 Contractor Support 3-124.1 

3.3.9.5 Mission Payload Peculiar Operations and Support Requirements 3-140.1 

3.3.9.5.1 Ground Support System Requirements 3-104.1 

3.3.10.5 Mission Payload Peculiar Recovery Requirements 3-142.1 

3.3.10.5.1 General 3-142.1 

3.3.10.5.2 DRV Recovery 3-142.1 

3.3.12.5 Mission Payload Peculiar Flight Crew Support Requirements 3-150.1 

3.3.12.5.1 General Training Requirements 3-150.1 

3.3.12.5.2 Simulator Requirements 3-150.1 

4.3 Mission Payload Peculiar Flight Certification Testing 4-15 

4.3.1 Qualification Testing 4-15 

4.3.2 Acceptance Testing 4-16 
NRO APPROVED FOR 

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S 

LS 

FIGURES 

3-5 Optical Sensor Basic Configuration 3-134.18 

3-6 Across-The-Format IMC Requirement 3-104.21 

3.7 Static Resolution Versus Contrast 3-104.23 

xiv 
GP-MIL-STD-410 - 

Systems & Ecui=ents). ( u) 

Maintainability Program Ro::;uirements (for 

.NRO APPROVED FOR 

RELEASE 1 JULY 2015 

- - Conyof S5S233-1 

PRELIM:NARY 

• 2 FINAL

o. 

SUPERSEDIY.G 

EC? NO. 2. CONTNR.:n.C.31' CND 1TE. NO. 3. SPEC. NO. 

YLL System 

4. CONTRACT 5. C ON TR ACT I.. 'JT FILE OP.OiJiTC SPEC. PACE NO. 

67,)!!.. 2.03 

6. EFFECTIVITY 

MOL Z-Ogram 

7. TEXT CHANCE. 

Chanze applicable document Paragraph 2.1.1 as follows: 

a. Delete GP-MIL-M-26512C - Maintainability Program ReciT,:lrement 

for Aerospace Systems & Ecuipment. (U) 

b0 AL the following: 

- 1 • e ; 

DAT-, „. • I. 

GP-IN77,-SD-471 Maintaimbility Demonstration (-U) 
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RELEASE 1 JULY 2015 - 

Lt.) 1I1 Li LtiVU 

4. r ra utfULASSINED 

C3 PRELIMINARY pAct- 2 OF 52 

SPECIFICATION CHANGE NOTICE 

NO. 1 

DATE 20 Jan 66 

FINAL SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

2 -6 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Change. Applicable Document Paragraph 2.1.2 as follows: (U) 

a) Change MS-SSD-63-14 - Spare Parts Provisioning Requirements to read: 

"MS-SSD-63-14A Spare Parts Provisioning Requirements" 

(T -IIIM Associates) 

b) Add the following: 

MS-SSD-62 -13A - Spare Parts for Support of Contractors engaged in 

(14 Jan 64) Development and Feasibility Demonstration of Test 

(OV Associates) Systems. 

17,1r.4 rkrt7r-fr-r-it I ' 

• A,o1,;?::s 

SPECiAL 0— 
. , 

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SSS-233-1 

PRIELIVIINARY 

I. EC? NC. 

r 

NC. 3 

9 . CONTRACT END :TEM NO. 

I • YOL Syste 

„ . 

SPEIC. 

4. CONTRACT 15. CONTRACTUAL Aumoa= 

2roGram 632A CCN 

OPPOSITE S:-')E.C.. PAGE NO. 

I '2-6 

6. EFFECTIVITY 

Por:o•:an -

7. TtXT ChANOE 

Par,zraph 2.1.3 Federal Standards (13) 

YD-SID-222 

(a) Delete "Title (to be nrovided)li 

(b) Aaa title "Radiation Standards for. Cc=aunications and other 

2n2omtion ProcesCin Ecrai.oment." 
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SSS-233-1 

IMINARY 

:NAL 

ECP NO. 

NA 

4. CONTRACT 

Program 632A 

6. EFFECTIVITY 

1'V:0fl Pro=73., m 

7. TEXT CHANCE 

PACE 

C:-:ANC5 

NG. 3 sij,,,E=Q:70TvG 

(2. CONTRACT END ITEM NO. 3 . SP NC.. 

XIT, System 

5 . CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

CON 1 C, 

Pa-f.agrapn 2.3 Other Decurrahts (U) 

Change MS-DOAS Exhibit 61-87 - Weapon Systcm/Ecuipraent Operations 

and Maini„enance Records to read: 

MS-SSD aenibit 66-1 - Instructions for Initiation and Updating 

0o,;ration, and Maintenance Records. 
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• SECRE1 574n Fo " ..

0/ 

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. 

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

documents which are applicable to a particular type of specification 

requirement. This prefix code is indicated in the applicable sections 

of this specification, such as Safety, General Design and Construction 

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

Code Paragraph Reference 

CV - Civil 3. 2. 2. 4 

DG - Design and Construction 

(Guidance only) 3.2 

DR Design and Construction 

Requirements 3. 2. 1 

EE Electrical 3.2.2.1 

EI - Electromagnetic Interference 

EV Environmental Criteria 

GP - Human Performance (Guidance) 

HP - Human Performance (applicable) 

HY Hydraulic 

IC Interchangeability 

IM Identification and Marking 

MP Materials, Parts, and Processes 

MS Maintenance Support 

SF Safety 

ST Storage 

WK Workmanship 

3. 2. 1. 8 

3. 2. 2. 8 

3. 2. 2. 5 

3. 2. 2. 5 

3. 2. 2. 3 

3. 2. 1. 6 

3. 2. 1. 9 

3. 2. 1. 2 

3. 2. 2. 7 

3. 2. 2. 6 

3. 2. 1. 10 

3. 2. 1 . 7 

2 - 1 

SEbilLik 

nnry all101■"' 
EE - MIL-E-0025366B Electrical and Electronic Equipment 

and Systems, Guided Missiles, 

Installation, General Specification 

for 

MP - MIL-F-007179B Finishes and Coatings, General 

Specifications for Protection of 

Aerospace Weapons Systems, 

Structures and Parts 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

2. 1 SPECIFICATIONS, STANDARDS, AND EXHIBITS 

2. 1. 1 MIL Specifications 

MIL-A-8421B General Specification for Air 

(Para 3. 1. 3.5,2) Transportability Requirement, 

5 May 1960 

EI - MIL-B-5087B 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 

DR - MIL-D-70327 Drawings, Engineering and 

Associated Lists 

EE - MIL-E-4158E Electronic Equipment, Ground, 

General Requirement for 

DR - MIL-E-5400G Electronic Equipment, Aircraft, 

General Specification for 

EE - MIL-E-19600 General Specification for 

Electronic Modules 

EE - MIL-C-5015 

IM - MIL-C-18012 

IM - MIL-C-25050 

EE - MIL-C-26482 

(Suppl 1) 
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SPECIAL HANDLING 

HY - MIL-H-25475A Hydraulic Systems. Missile, Design, 

Instailation Test and Data Requirement, General Requirement for 

!IR- MIL-H-27894A Hul-in Engineering Required for 

Aerospace Systems and Equipment 

MIL-HDBK-300 Technical information File of AGE 

(Para 3. 2. 1. 3) for Air Weapon System 

IC - MIL-I-8500B Int changeability and Replaceabi ty of C,, c.....ponent Parts 

- MIL-M-8090C M,. ;ity Req.airenaent, Ground 

(Para 3. 1. 3. 5. t) Ski7nort Ecuinm9nt, General 

Specificati.o.,-. • 

DR - MIL-M-8555 Missiles, Design and 

Construction, Gc.1:.,ral Specification 

for 

V13( MIL-M-26512C' — 

va 

- • 

,•/ 

Maintainability- 

.:or Aerospace S s and 

E1 - —,:ceptions 

r. Attachment 1 to SSD • 

- MIL-M-38310 Mass Pi•operties Control-Require- 

',Para 3. 3. 1. 1. 1. 1) marlts fol. Missile and Space 

IM - MIL-N- 18307 Iss...i...aenclature and Nameplates for 

Aeronautical Electronic and 

A.isccia.:ec.. Equipment 

ST - MIL-P- 1 16C Methods of 

H•Y - MT.L-P-551PC, pn e-m;_.tic. Systems, Aircraft 

(Suppl 11 1.1-.staflation and Data 

--.:,.ireinent for 

DR - MIL-P-9024E Pa.:.1.:a.ging, Air Weapon Systems, 

Spr:cification and General, Design 

Requirement for 

DR - MIL-Q-9853A Quality Control System Requireent s 

if GP - MIL - STD - 470 

`)P it 

OP - MIL - STD 

• \k!.1 2-3 

"111T".• 
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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 

Handling Ground Equipment. 

General Requirements for 

Support Equipment, Aeronautical, 

Special General Specification for 

the Design of 

Reliability Assurance Program for 

Established Reliability Pa its 

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 

r. 

HP - MIL-STD-803A-2 

Standard General Requirements for 

Electronic Equipment 

Requirements for Reliability 

Program (for Systems and 

Equipments) 

Colors 

Human Engineering Design Criteria 

for Aerospace System Ground 

Equipment 

Human Engineering Design Criteria 

for Aerospace System Facilities and 

Facility Equipment 

WK - MIL-STD-454 

DR - MIL-STD-785 

IM .- MIL-STD-795 

HP - MIL-STD-803A-1 
IM - BMD 58-20A 

GP - BMD 59-17C 

IM - BMD 59-31 

SSD Ex 61-47A 

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

EI SSD 64-4 

SF 

EE - SSD 64-5 

GP - BMD 60-1 

IM - SSD 61-70A 

SSDL- 70-1 

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 

Electromagnetic Compatibility 

Requirements for Manned Spacecraft, General Specification for 

General Specification for Wiring 

Harness in Manned Spacecraft 

PSS Testing for Ballistic Missile 

and Space Systems 

Identification Requirements 

Deleted 

TECIAL hANDLIK 

2-5 

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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 
MS - SSD 63-14 

DR - SSD 63-3 

2. 1. 3 Federal Standards 

IM - FED-STD-5 

SPECIAL 1-11-4.'Srbiliia 

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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 

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 

T--i+i-c 

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 Preservation, Packaging, Packing, 

and Marking Policy 

DG - AFR 73-1 Defense Standardization Program 

IM - AFR 74-2 

HP - AFR 84-7 

Identify Calibrations Requirements 

of Systems, Subsystems and 

Equipment 

Requirements for Contractor 

Operating Procedures and 

Flight Crews 

SF - AFM 32-3 

SF - AFM 127-100 

SF - AFM 71-4 

Accident Prevention Handbook 

Explosives Safety Manual 

Packaging and Handling of 

Dangerous Materials for Transportation by Military Aircraft 

A 2.2.4 Air Force Pamphlets (AFP) 

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 

MP- AFP 88-002-1 

CV - AFP 88-009-1 

2-7 

% ■; A NG 

Ci 1.711- SECRETS

SPECIAL 

SF - AFR 160-3 Hazardous Noise Exposure 

2.2.2 Air Force Manuals (AFM) 

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 
HP - AFSCR 80-16 

MP- AFSCR 400-3 

2.2.6 AFSC Manuals (AFSCM) 

DR AFSCM 80-1 

DG - 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 310-1 

(AFIJCM 310- 1) 

AFSCM 375-1 

AFSCM 375-5 

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 

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 

2-8 

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2.2.5 AFSC Regulations (AFSCR) 
Department of Defense Index of 

Specifications and Standards, 

Parts 1, 2 and 3 

DG 

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PH - AFSCM 95-1 

2. 2. 7 Bulletins 

EE - ANA Bulletin 

400T 

DR - USAF Bulletin 

No. 515 

2. 3 OTHER DOCUMENTS 

IM - AFLCM 65-3 

(Part IV) 

Deleted 

Electronic Equipment, Aircraft & 

Guided Missiles, Applicable 

Documents, March 1963 

Control of Non-Conforming Supplies 

Source and Maintenance Coding 

USAF Aeronautical and Supporting 

Equipment 

Material Inspection and Receiving 

report "DD Form 250" 

MP - ASPR 7-105. 7 

G6e. MS - DCAS Exhibit Weapon System/Equipment 

61-87 Operations and Maintenance Records 

DG DOD Manual 

SF - ICC Tariff 

No. 15 

.1 

CP --

EE - NEC 

MS - T. O. 33-1-14 

200A Defense Standardization Manual 

Requirements for Transport of 

Explosives 

NASA Life Science Data Book 

National Electric Code - 1959 

Repair, Calibration and Certification of Precision Measurement 

Equipment 

GP - WADC TR52-321 Anthropometry of Flying Personnel, 

1950 dated Sept. 1954 
SPECIAL HANDLING 

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. Z. 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 

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2.4 Additions to Applicable Documents Listing 

The following comprise additions to the foregoing list of 

documents applicable to the MOL mission payload. 

a. Additions 

MIL-STD-150A Photographic Lens 

-SECRET-- SPECIAL HANDLING 2-11 
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3. 2 SYSTEM DESIGN AND CONSTRUCTION STANDARDS 

The System Design and Consi 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 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 

Requirements specified herein shall apply to the design and construction 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 . 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 coinImercial 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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3-39 

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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. 

(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) 

3.2.1.4 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 corrosion 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 ernbrittlement are 

minimized. 

3. 2. 1. 5. 3 Protective Methods 

Protective methods and materials for cleaning, surface treatment, 

and application of finishes and protective coatings shall 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 

44 ^ 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. 
SPECIAL HANDLING 

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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 

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4 

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 components. 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. 
3-43/44 SPECIAL HANDLING 

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3.2.2.1 

I 

Electrical 

„=1 

The electrical design discipline requirements have been prepared 

under SSD Exhibit 64-5. The applicable documents 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. 

3.2.2.4 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 ;,.lidance. 

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. 
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NC. --: 

C 

;". 

_ 

_ . 

7. 

1.::oon Syoco:1 

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4.4 L.) 1.-• 
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(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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3. 3. 4 Mission Payload System Segment 

("' The specifications of the Mission Payloads will be provided under 

separate cover. 

3.3.4.1 Allocated Performance and Design Requirements 

3.3.4.1.1 Effectiveness 

Effectiveness requirements for this segment are specified in paragraph 3 . 1. 3 . 1 . 2 . 

3.3.4.1.2 Weight 

The weight allocation for this segment is specified in paraIrsis 1,L.)efl 

3.3.4.2 Peculiar Performance and Design Requirements 

3.3.4.2.1 Flight Crew Training Equipment 

Training equipment, as appropriate, shall be provided to accomplish 

Flight Crew Training in accordance with 3.3.12. Portions of the 

Mission Payload procedures trainers shall be designed for integration 

into the MOL Mission Simulators. 

• 

3.3.4.3 Functional Interfaces 

(Functional interfaces shall be listed here when defined by the cognizant Interface Control Working Group-ICWG. ) 

3. 3.4.4 Contract End Items 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL 611..9 `e,;" 4. 

3. 3. 4 Mission Payload System Segment 

(Note: the green pages under paragraph 3. 3.4 supersede the 

white pages under paragraph 3.3.4). 

3.3.4.1 Mission Payload System Segment Components 

The Mission Payload System Segment consists of three 

sections as follows: 

a. Mission Module Section 

This section includes the following major subsystems: 

(1) Thermal Control 

(2) Tracking Mirror Drive 

(3) Acquisition and Tracking (Manned-Automatic only) 

(4) Navigation and Control 

(5) Electric Power and Distribution 

(6) Data Editor, Scanner, and Digitizer (MannedAutomatic) 

(7) MP consoles and Displays 

(8) Terrain Camera 

b. Photographic Section 

This section includes the following major subsystems: 

Camera 

Image Motion Detector 

Primary Optics (Camera Optical Assembly and 

Tracking Mirror) 

Film Handling 

Film Processor (Manned-Automatic only) 

c. Data Re-entry Vehicle Section 

This section includes the following major subsystems: 

( 1) Launch Mechanisms and Support 

( 2) Data Re-entry Vehicle 

3-104.1 
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3.3.4.2 General Performance Allocations 

3.3.4.2.1 Weights 

TLe Mission Pay-load System Segment budget is as follows: 

Manned-Automatic Automatic 

Mission Module Section 2840 

Photographic Section 5203 

Data Re-entry Vehicle Section 390 

8433 lb. 

3.3.4.2.2 Disturbances Due to Mission Payload Equipment 

The torque disturbances due to outgassing, magnetic 

materials and other sources of external torque shall not exceed 0.25 ft. 

lbs. or a total of 5 x 104 ft. lbsec for the 30-day mission. The torque 

disturbances due to internal moving parts shall not cause changes in OV 

angular momentum which exceed the following during the period beginning 

one minute before and ending immediately after an active photographic pass: 

Yaw angular momentum + 25 ft.lb.sec 

Pitch angular momentum + 25 ft.lb.sec 

Roll angular momentum + 25 ft.lb.sec 

3.3.4.2.3 Design Considerations 

Mission Payload System design criteria shall be such as to 

minimize launch base test requirements and to maximize payload security. 

3.3.4.2.4 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 Mission Payload System equipments (e.g., target 

cues). 

3.3.4.2.5 Explosive Devices, Squib Simulator, etc. 

Chapter 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. 

47 

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3.3.4.2.6 Launch Safety 

The design of the Mission Payload 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. 

3.3.4.2.7 Weight and Balance 

There shall not be a requirement for weight and balance 

equipment at the launch base. Final weight and balance adjustment shall 

be performed during the Mission Payload/Laboratory Vehicle integration 

and checkout prior to shipment to the launch base. 

3.3.4.2.8 Alignment 

There shall not be a requirement for alignment equipment 

at the launch base. Final alignments and adjustments shall be performed 

during the Mission Module/Laboratory Module integration and checkout 

prior to shipment to the launch base. 

After insertion into orbit and activation, provision shall be 

made for the crew to perform precision alignments and adjustments as 

required. 

As a design objective for the automatic mode, provision shall 

be made to check alignment via telemetry and make corrections by ground 

command. 

It shall be a design requirement for both modes that precision 

alignment and adjustment of the main optics and camera be capable of being 

performed automatically in orbit. 

3.3.4.2.9 Minimum Time Between Targets 

The time in seconds between adjacent targets achievable by 

An- the system shall be no greater than + 3 or + 3 seconds, 

whichever is larger, whereoel and 4-C1- are the stereo and obliquity angle 

changes, respectively, in degrees commanded between targets. 

SPECIAL 3-104.3 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL 

3.3.4.3 Mission Module Section 

3.3.4.3.1 Mission Module Structure 

The mission module structure shall support the mission 

payload and protect it from deleterious shock and vibration during powered 

flight. It shall also, during orbital flight, maintain vibration at a level 

which will not degrade mission performance below specification requirements. 

Separation devices for items such as the structural door, 

when actuated, will not cause damage to the payload and peripheral equipment, misalign equipment outside adjustment capability, or cause contamination of sensitive equipment to occur. 

3.3.4.3.2 Thermal Control Subsystem 

3.3.4.3. 2. 1 General 

It is required that the thermal control system not limit the 

photographic sensor operation. 

3.3.4.3.2.2 Ground Conditioning 

Immediately prior to launch (T-48 hours), the ground 

conditioning system, in conjunction with the AVE temperature control 

system, shall provide on orbit temperature conditions. The requirement 

shall be that the internal temperatures on the ground shall be within the 

expected orbital flight tolerances. Prior to this time, the limits may be 

extended provided no irreversible affects occur. (See 3.3.4. 6. 4 for 

AGE requirements) 

3.3.4.3.2.3 Powered Flight 

The thermal control subsystem shall be activated prior to 

launch to achieve and maintain optics temperatures at orbital design values. 

3.3.4.3.2.4 Orbital Flight 

The thermal control system shall maintain the photographic 

section equipment at a temperature that will provide specified system 

performance. Gradients shall be controlled so that resolution of the image 

will not be degraded below specification performance. 

3.3.4.3.3 Navigation and Control Requirements 

3.3.4.3.3.1 General 

The Navigation and Control Subsystem (NCS) shall provide 

for the control of the cameras, optical equipment, and other mission 

SPE2Jr 3-104.4 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

payload functions. The Satellite Control Facility shall be used to the 

maximum extent for the determination of the parameters used by the NCS. 

The NCS shall employ the computer subsystem specified in paragraph 

3.3.2.2.5.2.4. The NCS shall receive an ephemeris table and the position 

of the targets as earth referenced coordinates for calculation of pointing 

angles. The NCS shall be designed to support the Mission Payload System 

Segment in either the manned-automatic or automatic modes. The NCS shall 

be capable of servicing a tracking station pass coincident with photographic operations. 

3.3.4.3.3.2 Main Optics Tracking 

The NCS 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. During a single forward to rearward track, the 

NCS 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. 

3.3.4.3.3.3 Orbital Position Determination 

The NCS shall determine the position of the vehicle on 

orbit by interpolating an ephemeris table furnished by the SCF. A 

description of the orbit spans required for photography shall be accepted 

from any SCF tracking station by the NCS. Orbital position as defined by 

the NCS during the photographic spans shall have the following two sigma 

accuracies 1-1/2 revolutions after the orbit definition has been loaded 

(2-1/2 revolutions after the determination span): 

In-track 0.3 n m 

Cross-track 0.1 n m 

Altitude 0.1 n m 

As an objective the two sigma in-track error shall be no greater than 

0.1 n m (2-1/2 revs after the determination span). 

SPECIAL HANDLINU 

3-104.5 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDL NG 

Manned-Automatic Configuration 

Manual hand controller inputs shall be accepted from the 

crewmen to correct the in-track and cross-track reference. 

3.3.4.3.3.4 Image Motion Compensation 

By further processing the orbit ephemeris information 

(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 that required by 3.1.1.4.7. An image motion detector shall be provided. 

The NCS 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 NCS shall be a crew option. 

3.3.4.3.3.5 Payload Attitude Measurement 

A star acquisition and tracking system (SATS) shall be 

integrated into the mission module. The mounts for this system shall 

be positioned and designed for the maximum correlation between the 

SATS reference and the optics pointing reference. The specific stars to 

be tracked during photographic operations shall be determined by ground 

data processing. Assuming an in-track error no greater than that 

specified in 3.3.4.3.3.3, the SATS shall establish the attitude of its 

mounting axes with respect to the local vertical and the orbit plane with 

two sigma errors no greater than 1.5 minutes. Prior to acquisition, the 

NCS shall point the axis of the tracker to the line of sigh to the star with 

an error no greater than 2 degrees. The reliability of the SATS for the 

mission duration shall be 0.95. 

SECRET SEECIAL 1-1A WLINE 3-104.6 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

4EGRET.._ SPECIAL HANDLIN 

3. 3. 4. 3. 3. 6 Camera Control 

The Navigation and Control System (NCS) shall provide open 

loop adjustments and commands, and off-axis image motion compensation 

control. The open loop adjustments shall include exposure, slit control, 

focus (correction for slant range), and a cycle command. Commands 

shall be provided to the platen and/or slit as required for across-the-format 

IMC. Calculations for this IMC control shall be performed by the NCS. 

The focus sensor shall provide signals correlating with the 

apparent error in focus for the scene under observation. Open loop 

operations shall be provided by recording focus error signals for ground 

analysis and subsequent platen commands in all modes. In addition, the 

manned-automatic mode shall have open loop focus capability which can be 

controlled by the crew. 

The NCS shall provide information to telemetry and the 

camera data lamps. This information shall include a convenient rev. and 

frame identifier, time of exposure of the center of the frame, which can 

be correlated to within one millisecond of GMT, 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 (2o- ). 

Manned-Automatic Version 

The NCS shall provide control signals to select the film to 

be positioned for each exposure. 

3. 3. 4. 3. 3. 7 Sequential Control 

The NCS shall provide for the sequential control of the 

Mission Payload System 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. 

SFCIA 3-104.7 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

'Lijkt1 l

During a single forward to rearward motion of the tracking 

mirror, the NCS shall sequence the events required to photograph a single 

target, or a cluster 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 NCS using sun angle and scene content information. 

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. 

Manned-Automatic Version 

When photographing a target cluster, 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 NCS shall control the thermal door servos. The door 

positions shall be controlled to limit the heat energy entering the tracking 

mirror bay without obstructing the light from the target by more than 2 %. 

3.3.4.3.3.9 Target Acquisition and Selection (Manned-Automatic) 

Two acquisition and tracking scopes shall be provided to assist 

the crew in their selection of the target and the reduction of pointing 

errors. The NCS 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 crew stations shall have the capability to observe 

the image from either acquisition and tracking scope, or from the 

primary optics. Manual hand controller inputs shall be accepted from 

the crew to perform the functions listed in 3.3.4.3.3.3. and 3.3.4.3.3.4 

3-104.8 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

and to slew the acquisition scopes in a manual search mode. The NCS 

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 crew 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. The target options shall 

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 crew and for their comments relating to the estimated quality 

of the photography. 

The NCS shall provide open loop commands to the target 

cue system. These commands shall result in the automatic presentation 

of the target cueing aids required by the crew to center the targets or 

properly position the offset reference. 

3. 3. 4. 3. 3. 10 NCS Communications 

Two data services shall be provided to the telemetry 

system from the NCS 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 data shall be reported as a backup to the vehicle 

telemetry recorder/SGLS ground station/SCF data processing system. 

3-104.9 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 Re 

The NCS shall accept data from the MCC (via tracking 

stations) as specified in Section 3.3.2.2.5.2. Data required by the NCS 

shall be organized into words and blocks of words. Both the words and 

blocks shall be tested for validity. 

For all possible conditions of communications noise, the 

coding shall assure that distorted data is not acted upon by the NCS. As 

a secondary requirement, the coding shall assure efficient information 

transfer with any bit error rate less than 10

-3. Coding used for command 

feedback (telemetry verification) shall permit continuation of a block after 

experiencing a temporary loss of telemetry reception. The NCS shall 

extract portions of data and circulate these data through government 

furnished decryption equipment. 

As a design objective the NCS shall accept data at a rate 

of ten kilobits per second. Coincident photographic operations are not 

required when accepting data at 10 kbps. Efficient operation of 10 kbps 

is not required at bit error rates greater than 10-5

. 

3..3.4.3.3.11 Reliability (U) 

The NCS shall be designed to survive failure such that 

after any single failure, the NCS shall be capable of supporting a productive 

mission. Redundancy shall be utilized and 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. 

The design of the NCS and the arrangement of the 

equipment shall be such that each of the redundant elements will be able 

to be tested and checked individually. 

3.3.4.3.4 Electrical Power and Distribution Subsystem 

The Mission Payload equipment shall be designed to the 

same requirement specified for the Laboratory in paragraph 3.3.2.2.8.7 

except that relative to paragraph 3.3.2.2.8.7.2, specified performance 

shall be achieved within 30 seconds after a power interruption of up to one 

second, provided the timing signal is restored/retained correctly. 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. 

3-104.10 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 CI 

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, crew 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 consistent with the other requirements in 

Section 3.3.4.3.5. The subsystem shall scan and transmit 5 square 

inches in 4 minutes. 

3.3.4.3.5.3 Operational Employment 

Operation of the readout subsystem shall require a minimum 

of the crew's time. The scanner shall accept portions of various pictures 

which have been edited by the flight crew. 

Crew assistance shall not be required during the 

readout station pass. Readout will be performed only at stations equipped 

with advanced SGLS. Stations equipped for readout shall be the 

New Hampshire Station, the Vandenberg Station, the Hawaii Station and 

the Station. It shall be a design objective to record 

data in encrypted form at the tracking station, and process the encrypted 

data at user facilities. 

cr. 3-104.11 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.3.4.3.6 Acquisition and Tracking Scopes (Manned-Automatic) 

Two acquisition and tracking scopes for redundancy and 

efficiency of target acquisition are required. The optical axes of the 

scopes shall be capable of being trained from +70° to -40° in-track 

and + 45o cross-track. Position and tracking rate data from the scopes 

will be fed to the computer for main optics acquisition. 

3.3.4.3.6.1 Magnification Range 

The scope image will be a 5X magnification with a capability 

to change to 25X. It shall be a design objective to also provide 1X 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 crew will see a 4° 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 stations. 

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 NCS and from the controlling crewman's handcontroller motion. Each crewman 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 crewman 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. The slew rate capability of the 

acquisition and tracking scopes shall be at least 20 degrees per second 

in both pitch and roll. 

Fr. 

3-104.12 
NRO APPROVED FOR . 

? 17 

RELEASE 1 JULY 2015 

.16.4 SPEC 

3.3.4.4 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 

Data Re-entry Vehicle (DRV) with provisions for a second DRV, DRV 

structural supports, launcher tube assembly, release mechanism, and 

auxiliary electrical and mechanical equipment required to evaluate DRV 

status, and to control DRV release and separation. 

The DRVS shall be located in the Laboratory Module (LM) 

which shall provide the required space and environmental control. The 

DRV launcher tube shall be adequate to contain and support one DRV in 

the launch, ascent, orbit, and deboost environments; and its centerline 

shall be oriented 90 degrees to the orbiting vehicle (OV) roll axis. In the 

event a DRV does not eject from the DRV launcher, the capability shall 

exist to retrieve the DRV film and reseal the DRV launcher tube as required. 

Automatic Configuration 

The Gemini B will be replaced by a Support Module (SM). 

The Support Module shall serve as the nose fairing of the flight vehicle, 

and shall be designed to withstand the launch and ascent environment. 

The DRVS shall include six DRV's and shall support, 

house, and protect the DRV's and film transport and chute assembly, and 

auxiliary electrical and mechanical equipment required to evaluate DRV 

status, to control DRV release and separation, and to provide environmental 

control. 

3.3.4.4.2 DRVS Structure and Packaging 

a. DRV Installation and Removal 

The DRV will be fully accessible while attached 

to the DRVS support structure. 

SECRET SPECL.,.., A,JhtL.7 3-104.13 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPEC1 

b. Retro-rocket Ignitor-installation 

If required because of shipping regulations, provisions 

shall be made to install the ignitors or initiators at the Launch Complex 

without disassembling the DRV, and without invalidating any previous testing. 

3.3.4.4.3 DRVS Environmental Control 

General 

The environmental control shall maintain the internal DRV 

0 temperature within 70o +20 0F. This will be accomplished, using both -30 

passive and active thermal control as required. 

The DRV and film chute (automatic mode) shall provide 

a light tight contamination free environment for the film. 

Manned-Automatic Configuration 

The DRV and/or launcher tube shall have provisions for 

controlled venting so that DRV internal pressure does not exceed the 

external pressure by more than 5 psi when separated from the OV or in 

the event of loss of Laboratory Module pressure. Manual pressure 

relief shall be provided for controlled access to the DRY launcher tube. 

Automatic Configuration 

The DRV and film chute shall be pressure sealed as 

necessary, so that the Laboratory Module pressure can be maintained 

at 5.0 psia. Pressure makeup shall be provided to maintain the DRV and film 

chute internal pressure at 5 + 0.5 psia. 

3.3.4.4.4 Minimum Acceptable Reliability Level 

The DRVS shall have a minimum acceptable reliability 

level of: 

Manned-Automatic Configuration 

DRVS reliability - 0.97 

3-104. 13a 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Automatic Configuration 

DRVS reliability 

a. Return of the first DRV - 0.95 

b. Return of all six DRV's - 0.75 

3.3.4.4.5 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 

and mated with the Laboratory Module. 

3.3.4.4.6 Data Re-entry Vehicle (DRV) 

The DRV shall be the Mark V, modified as necessary to 

withstand a pressure differential of 5 psi. 

a. General 

(1) 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. 

The DRV shall not significantly contaminate the Laboratory Module liveable 

environment with toxic products. Contamination shall be avoided by the 

proper selection of DRV materials or prevention of outgassing of toxic 

materials. The DRV will provide thermal and environmental protection for 

the film during launch, orbit, and re-entry operations; and will supply 

status data to the telemetry subsystem. Its capabilities (with or without 

manual assistance) shall include: preparation for de-orbit, and re-entry 

and separation from the DRVS support structure. 

(2) After separation and spin-up, the DRV will 

deboost itself from orbit by firing the retro-rocket, and despinning, 

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. A redundant tracking aid shall be required. This deboost must also be 

successful from the emergency mode attitude limits, including both N-S and 

S-N re-entry. 

CP-. 

3-104.14 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIr 

(3) After re-entry, the DRV will descend via a 

parachute designed for aerial retrieval. The descent rate at 10,000 feet 

will not exceed 25 ft/sec, under standard atmosphere conditions. DRV 

primary and secondary recovery modes shall be aerial and water, respectively. 

(4) The DRV will survive water impact, and the 

retrieval aids will remain active until the sink system is activated, i.e. 

the DRV will continue to float for a minimum of 50 hours, with the sink 

system flooding and sinking the capsule after a maximum of 90 hours in the 

ocean. 

(5) The DRV will contain a system for self-destruction if it does not re-enter within a designated area. 

b. Data Re-entry Vehicle Separation 

The DRV separation and push-off subsystem are to be 

considered part of the DRVS. The DRV shall be ejected so as to place it 

in the correct attitude, and then spin stabilize prior to ignition of the 

retro-rocket. 

c. Deboost and Re-entry Dispersions 

In the case of proper film handling and with the OV 

under the control of the primary stabilization system at DRV separation, 

the impact point of the DRV will be within 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. 

d. DRV Electrical Subsystem 

All power required in the DRV will be supplied by the 

Laboratory Module until receipt by the DRV of that signal which will be 

used to activate the DRV battery during the deboost sequence. The DRV 

will require no more than two electrical signals to prepare it for deboost. 

-SECRET- SPE\ 

3-104.15 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 3.2. 

e. Telemetry 

The DRV shall provide monitors for battery voltages 

and temperature, heat shield temperature and loop continuity. DRV 

sequencing and discretes will be monitored by beacon modulation after DRV 

separation. 

f. Orbit, De-orbit, and Re-entry Conditions 

The DRV shall be capable of being de-orbited properly 

from any position on the following orbits. 

Orbit Perigee Altitude - 70 nm to 90 nm 

Eccentricity - 0 to 0.025 

DRV Orientation - Manned-Automatic: 

900 to OV roll axis 

TI TI - Automatic: 

later 

Orbit Plane Inclination From 65° to 125° 

Orbit Duration - 60 days 

g. 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 requirements. The DRVS contractors 

shall consider reliability improvements through redundancy (and appropriate 

use of the crew in the manned version). 

The DRV reliability demonstration requirements shall 

be 0.98. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

3.3.4.5 Photographic Section 

3.3.4.5.1 General 

The photographic section shall contain optical, mechanical, 

thermal, electrical, and structural components necessary to perform high 

quality, stereo, photographic reconnaissance. 

The available volume for photographic section use shall be 

feet in diameter (to maintain structural continuity with the Titan 

booster) and 36 feet long. Local areas of protuberance may exceed this 

diameter. 

The optical system of the payload (See Figure 3-5)shall 

consist of a 70 inch aperture, focal length Ross telephoto lens 

having a 0.54° semi-field angle. The optical axis shall be approximately 

parallel to the longitudinal axis of the Mission Mbdule which contains the 

payload. The Mission Module and payload shall be unpressurized. A 70-inch 

diameter, circular, flat tracking mirror shall be located in front of the 

lens at the forward end of the Mission Mbdule. The tracking mirror shall 

be capable of pointing the line-of-sight + 400 in roll (left and right of 

the X-Z plane), 30° forward in pitch and 400 aft in pitch. The tracking 

mirror shall be gimballed in two axes and be servo driven to slew, follow 

computed target tracking rates, and respond to position and rate change 

inputs inserted by an image motion detector or.by a member of the crew, 

A frame camera utilizing 4 inch wide film shall be located 

at the end of the Ross corrector barrel at the Laboratory Mbdule side of 

the bulkhead. The camera may take a sequence of up to ten photographs of 

each target, nominally within approximately ÷ 15 to -15 degrees fore and aft 

(stereo) angles. Normally, three different exposure settings shall be 

used for each target. The nominal sequence rate shall be 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 photographs may be 

apportioned by command between one photograph per target to 10 photographs 

per target. 

SPECIAL HANDLDIG 3-104.17 
SPECIAL HANDLING FIGURE 3-5 OPTICAL SENSORBASIC CONFIGURATION 

SPECIAL HANDLING 3-1o4.18 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

!n •

Ly 

The Mission Module shall provide a viewport which will allow 

the primary optical beam to be moved through the required obliquity and 

stereo angles for photography. Viewport doors shall be provided for 

thermal protection during non-photographic periods. 

Manned-Automatic Configuration 

The Ross corrector barrel of the optical system shall be 

above and parallel to the optical axis of the primary mirror. Light shall 

be diverted from the optical system into a visual optics barrel located 

parallel to the Ross corrector barrel. A zoom eyepiece at the end of the 

visual optics and within the Laboratory Nbdule will allow the crew to 

observe and track the target during photography. Magnifications of 11IX to 

1000X shall be provided. 

Assemblies in the Laboratory Module which will be required 

for the manned reconnaissance operation are the Pre-editor and Processor, 

Film Viewer and Editor, and the Film Scanner and Readout. This equipment 

shall not significantly contaminate the LM liveable environment with toxic 

products. Also essential to photography are the 2 reconnaissance consoles 

with TV displays of the acquisition telescope fields, target cue displays 

and a hand controller for target centering and rate correction of the 

tracking mirror and acquisition scopes. 

3.3.4.5.2 Operational Requirements 

The Photographic Section shall be capable of both northbound 

and southbound photography during a single mission and shall meet the 

specified conditions. The altitude range for photography shall be To to 

230 nm. Other aspects of the mission orbital envelope for photography are 

specified in Section 3.1.1.4.4 

It shall be an operational requirement to photograph as 

many targets as possible consistent with high quality stereo photography. 

3.3.4.5.3 Camera 

The camera system shall consist of the mechanical, electrical, and optical elements necessary to position the film and properly 

expose it. The system shall include a camera 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. 

The film holding system shall be of such a design that system performance 

will not be degraded by film surface deformation. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

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 shall be defined as the time 

specified to expose a picture element. The frame exposure time shall be 

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 a film 

having the resolution of Type 3404 but a speed of 6. 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 frames/target. 

The position of the camera platen shall be controllable, 

on-orbit, to provide 0.1 inches for 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 secondary 

records, one type of which is suitable for on-board processing, by means 

of interposing a second film platen at the image plane in place of the 

primary film. Introduction of the second platen in place of the primary 

platen shall be done automatically and shall not take longer than 1 second. 

The secondary platen shall use the same film format and data imprinting, 

shall utilize the same shutter and shall employ means for holding the film 

during exposure to minimize film surface deformation. 

3.3.4.5.3.1 Across-the-Format IMC 

Across-the-format IMC shall be provided which, when used, 

shall insure that the average geometric mean performance at the film plane 

anywhere within a 0.8° diameter circle about the center of the format will 

be greater than that given by Figure 3-6. Across-the-format IMC shall be 

used only for the primary record. 

3.3.4.5.4 Optical Design/Performance Requirements 

This section describes the requirements on the primary 

photographic and visual systems only. 

SPECIAL h 

3-104.20 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLIN4 

0° (on axis) performance without 

X-Format it 100% 

Q 

H 

fc3 +' 0c .3 

• E U 

• C, 

O 

P4 

O ( 

• C3-1 

0.) V

.H 

SEMI-FIELD ANGLE (DEGREES) 

(DEGREES) 

FIGURE 3-6. ACROSS-THE-FORMAT 

IMC REQUIREMENT 

SPECIAL HANDLING 3-104,21 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING SECRET 

3.3.4.5.4.1 Primary Optics 

The final image shall be a photographic negative on a film 

having the resolution of Type 3404 but a speed of 6. 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 Configuration 

Two of the latent images will be processed with on-board 

equipment according to specifications in Section 3.3.4.5.7. Two of the 

latent images will be returned to earth via a DRV or in te Gemini B. 

Resolution readings and density measurements of the processed record shall 

be made by an astronaut and reported at the earliest opportunity. 

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 3-7. 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-4utomatic) 

The performance and requirements are as follows: 

SECRET SPECIAL HANDLING 3-104,22 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 4Eurf ET- SPECIAL HANDLING 

FIGURE 3-7 

STATIC RESOLUTION VERSUS CONTRAST 

SPECIAL HANDITIM 3-104.23 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

a. Performance of Primary Visual Optical System 

Magnification 111X to 1000X continuously variable 

Apparent Field 40° full field 

Light Termination 35% for visual relay only 

Resolving Power 

Central 10° 30 lines/degree 

Rest of field 15 lines/degree 

Eye Relief (min.) 40 mm 

b. Performance of Secondary Visual Optical System 

The secondary visual optical system shall have the same 

characteristics as the primary as a goal. However, the performance may 

be degraded as far as the following in order to save weight: 

Magnification 111X to 1000X 

Apparent Field 40° Full Field 

Light Termination 30% 

Resolving Power 

Central 10° 25 lines/degree 

Rest of Field 15 lines/degree 

Eye Relief (min) 40 mm 

3.3.4.5.5 Record Handling 

3.3.4.5.5.1 Film Requirement 

The nominal film width shall be 9-i inches. The primary 

reconnaissance film shall be black and white film having the resolution 

of Type 3404 but a speed of 6. Secondary reconnaissance films shall be 

provided. The secondary records shall also have a 92 inch nominal film 

width. The vehicle shall carry a nominal film load of 13,000 ft. including 

both primary and secondary records. Consideration shall be given to protecting 

the film from excessive radiation damage. 

3.3.4.5.5.2 Black and White 

Manned-Automatic Configuration 

The primary film will be loaded from one (1) supply reel. 

The exposed record shall be wound into take-up cassettes and manually 

removed from the camera under operational lighting. 

_SPECIAL I-IANbLi,NG 3-104.24 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-SECRET- SPECK p 

L.1 li;)! 

Automatic Configuration 

The primary film will be loaded into one supply reel, 

threaded through the camera and into multiple take-up cassettes. 

3.3.4.5.5.3 Color and Special Films (Manned-Automatic Configuration) 

The vehicle shall be capable of carrying additional supply 

cassettes of color, night, or special films for use with the secondary 

platen (see 3.3.4.5.3) 

3.3.4.5.5.4 Data Return Capsules (Manned-Automatic only) 

3.3.4.5.5.4.1 General 

Three (3) Data Return Capsules (DRC's) shall be utilized 

as takeup cassettes for the primary record during photographic operations. 

Each DRC shall have a capability of returning 60 pounds of film, for a 

total of 180 pounds of primary record, in the Gemini. 

A fourth DRC (or secondary package) shall be utilized to 

return 60 pounds of secondary record and cues in the Gemini. This latter 

data will be enclosed in sealed canisters, installed and secured in the 

fourth DRC. The DEC's shall have flotation capability. 

3.3.4.5.5.4.2 Environmental Control 

The DRC design shall minimize the possibility of film 

damage due to (a) handling, (b) contamination, (c) light leaks, and 

(d) excessive temperature excursions. The film records shall be 

+20 

maintained at a temperature of 70 °F. However, the sealed film canisters -30 

are permitted to approach a maximum temperature of 120°F for a period not 

exceeding one hour. 

3.3.4.5.5.4.3 Alignment/Adjustment 

The design of the DRC's containing the primary record 

in association with the Laboratory Module DRC support equipment, shall 

incorporate provisions for takeup cassette/film alignment and adjustment 

during photographic operations. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

3.3.4.5.5.4.4 DRC Film Weight Breakdown 

The DRC Film weight breakdown shall be as follows: 

Data DEC's Weight (pounds) 

Primary Record 3 18o 

Secondary Record/Cues 1 60 

Total 240 

The Secondary Record/Cues weight breakdown shall be as 

follows: 

Data Canisters Weight (pounds) 

Processed 2 20 

Color 1 10 

Infra-Red 1 10 

High Speed 1 10 

Cues 1 6 

Terrain 1 

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. 

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 and Numeric Data 

(1) Revolution Number 

(2) Frame Number 

(3) Vehicle Time 

(4) Exposure Start and Exposure Finish Times 

(5) Vehicle Attitude 

(6) Tracking Mirror Position 

(7) Exposure Slit Number 

(8) Exposure Slit Orientation 

(9) Vehicle Identification Number 

SPECIAL HANDLING 3-104.26 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECI k .. s; s 

b. Special Markings 

(1) Fiducial Marks 

(2) Interframe Marks 

(3) Special Frame Marking (Auxiliary platen only) 

3.3..5.7 Film Processor (Manned-Automatic' Configuration) 

3.3.4.5.7.1 General 

The Laboratory Mbdule shall be provided with an on-board 

processor which will process groups of selected frames of black and white 

primary or secondary record for the purpose of on-board photographic 

reconnaissance and/or quality information and readout to the ground for 

quick access to reconnaissance information and photographic quality 

information. 

3.3.4.5.7.2 Acquisition 

There shall be supply cassettes of secondary record 

available for on board processing. One of these cassettes shall be mounted 

on the secondary camera prior to those photographic passes where output 

for flight crew photographic viewing and readout is needed. The secondary 

takeup cassette containing the exposed film which is to be processed shall 

be removed and transferred to the processor as required. 

It shall be possible to process a limited amount of primary 

camera record for monitoring performance of the primary camera. Removal 

of primary camera record for processing shall be limited to a few frames 

taken from the standard primary camera take-up cassette prior to the photographic mission and to frames taken between the removal of a full cassette 

load and the start of the next regular cassette load. 

3.3.4.5.7.3 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. All chemical contaminants shall be identified and controlled in such a manner that they will 

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 flight crew. The 

processor shall be capable of operation in nominal Laboratory Module lighting 

conditions and shall produce a dry photograph suitable for viewing and readout. 

(71- p 

7-Y5 SPECr C1,!) 1 

 

3-104.27 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECREI SPEC t.4 

3.3.4.5.7.4 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. 

3.3.4.5.8 Environmental Control 

3.3.4.5.8.1 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. 

3.3.4.5.8.2 Ground Conditioning 

The temperature and humidity limits shall be established 

such that no moisture condensation shall occur on any portion of the camera 

or optical assembly. Cleanliness conditions shall meet the requirements 

of paragraph 3.3.4.6.3. 

3.3.4.5.8.3 Powered Flight 

The temperature and humidity limits shall be established 

such that no moisture condensation shall occur on any portion of the COA. 

In addition, the ascent heating load shall be attenuated to an extent that 

will allow acceptable thermal conditions for payload operation within five 

hours after launch. Cleanliness requirements are the same as those given 

in Section 3.3.4.6.3. 

3-104.28 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 tTff- SPECIAL HANDLING 

3.3.4.5.8.4 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. 

Temperature requirements for the Photographic Section shall 

be determined by the optical performance requirements. 

Coating deterioration due to the space environment and 

those environments encountered prior to and during powered flight 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 (0 = 0, 21 

June) and nominal albedo (.38). 

The cleanliness requirement shall be such that the particle 

count shall not exceed 2,000 particles per liter in the Mission Module. 

3.3..5.9 Mechanical Mounting 

3.3.4.5.9.1 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. 

3.3.4.5.9.2 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. 

3.3.4.5.9.3 Powered Flight 

The Photographic Section shall be mounted in such a way 

that launch forces cannot endanger the Photographic Section or its subsequent performance. 

3.3.4.5.9.4 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 

SECRET SPECIAL 

3-104.29 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET, SPECIAL HAND 1NG. 

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. 

firqr7 

p • s, 3-104.30 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 _SEE- SfECIAL hANDLING 

3.3.4.6 Mission Payload Peculiar AGE Requirements 

The MPSS AGE will conform to the general design and performance 

requirements given for the Orbiting Vehicle in 3.3.1.2.8, and those for the 

Laboratory Vehicle in 3.3.2.2.13. Requirements for MPSS alignment, special 

purpose and handling equipment are given below. 

3.3.4.6.1 

3.3.4.6.2 

Alignment Equipment 

a. Mission Module Section 

AGE shall be provided for alignment of the optical and 

star acquisition and tracking equipments with reference to 

the mission module principal axes. The AGE shall also be 

capable of measuring these alignments to within one minute of 

arc. 

The alignment of the tracking mirror assembly and its 

measurement shall also be provided for. 

A structure representing the Camera Optical Assembly (COA), 

will be utilized with the MPSS to aid in these alignments. • 

b. Photographic Section 

Special equipment for optical and mechanical alignment of 

components shall be designed and utilized to validate optical 

and mechanical dimensions of the optical sensor, to align 

the navigation and control reference with the optical sensor, 

and to align automatic film handling equipment as necessary. 

Special Purpose Equipment 

a. Mission Module Section 

AGE shall be provided which will allow for testing of the 

MPSS consoles. This AGE will provide stimuli for exercising the 

displays and simulated MPSS equipment to test responses from 

operation of the consoles. 

SPECIAL H„NbL“ 

3-104.31 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

In addition, special power supplies stimulating the Laboratory 

Module CPS will be provided for testing the MPSS. Fixtures for 

vibration testing will also be provided. 

Special test equipment for thermal-vacuum testing of 

the MPSS will be provided. 

b. Photographic Section 

Special purpose equipment shall be designed and 

utilized by the Photographic Section Contractor at his 

facility during manufacture and sub-assembly build-up 

operation and through assembly and acceptance of the 

Mission Payload System Segment. 

3.3.4.6.3 Handling and Transportation Equipment 

a. Mission Module Section 

AGE shall be provided for handling and transporting 

the MM and other MPSS equipments within the payload integrating contractor's plant, between contractors' plants, 

from the contractor's plant to the launch site, and at the 

launch site. It is a design requirement that this AGE 

protect the MPSS AVE and control the AVE environments to 

levels below those the AVE is expected to experience 

while on the pad, at launch, during power flight, and inorbit. Specifically, the following guidelines apply: 

Shock and Vibration - isolation to levels below those 

expected during launch and powered 

flight. 

Temperature Limits - within those specified for the design. 

Cleanliness within those limits specified by 

Federal Standard 209, class 10,000 

(internal) and class 100,000 (external), 

plus elimination of oils and volatiles 

in the atmosphere. 

SECRET SPECIAL .FIANDL j.3 

".-104.32 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL 

b. Photographic Section 

Suitable handling equipment for the COA interface 

substitute shall be provided to implement vertical and horizontal lifting, 

erection to a vertical attitude, and in-plant transport in a horizontal 

attitude. Equipment for assembly of the COA interface substitute into a 

mission module shall be limited to that equipment directly associated with 

handling of the optical sensor. 

Necessary handling equipment for installation of the 

Photographic Section laboratory module components shall be provided. 

Photographic Section items shall be packaged in 

suitable containers which hold the contents within the environmental limits 

established for the hardware. 

3.3.4.6.4 PAD Environmental Control Equipment 

The AGE shall provide for control of the environment inside 

the MPSS as follows: 

Temperature - 70°F + 5

o normal requirement 

70°F + 1o starting 48 hours before launch 

Cleanliness Federal Standard 209 class 10,000, plus 

elimination of oils and volatiles in the 

atmosphere. 

3.3.4.7 Functional Interfaces 

(Functional interface documents shall be listed here when 

defined and approved in accordance with IFS-MOL-100001). 

3.3.4.8 Contract End Items 

(The contractors 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. 

r 

3-104.33 
RUSSELL A. BERG 

Brig Gen, USAF 

Deputy Director for MOL 

• 

JOHN L. MARTIN, JR. 

Brig Gen, USAF 

Director for Special Projects, OSAF 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 AEGRE- SPECIAL HANDLING 

29 April 1966 

To: R. L. Johnson 

E. A. Miller 

J. M. Sewell 

Subject: Forwarding of Integrated MOL System Specification 

(SS-MOL-1, Integrated) 

1. Two (2) copies each of the "Preliminary Performance/ 

Design Requirements for the Manned Orbiting Laboratory System 

(including Mission Payload) General Specification for", are forwarded 

herewith. Also attached are two (2) copies of SCN-3 (Security control 

number SSS-233-1) to be incorporated in SS-MOL-1 Integrated (Security 

control number SSS-233). 

2. This integrated system specification supplements SS-MOL-1 

by the use of green pages to provide the mission peculiar requirements 

which require DORIAN security procedures for their statement. The 

green pages are included after the white pages containing similar subject 

material (e.g. mission requirements peculiar to Gemini, follow section 

3.3.3, Gemini B System Segment white pages). The section numbers 

of the green pages consecutively follow the section numbers of the white 

pages. 

3. SS-MOL-1 Integrated is effective this date, and shall be 

used for Phase II program planning and estimating purposes. 

-- T-- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -SEMEtSS-MOL-1 Integrated 

SSS-233 

fi) 

Copy' of 

Pages 

PRELIMINARY PER 

DESIGN REQUIREMENTS 

FOR THE 

MANNED ORBITING LABORATORY SYSTEM 

(MOL) 

(INCLUDING MISSION PAYLOAD) 

GENERAL SPECIFICATION FOR 

29 April 1966 
WO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

Ea FINAL 

PAGE 1 OF 52 

DATE 20 Jan 66 

NO. 1 SUPERSEDING 

1. ECP NO. 2. CONTRACT END ITEM NO. 3. SPEC. NO. 

NA MOL System SS-MOL-1 

4. CONTRACT 5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

Program 632A CCN 1 —1 / 2 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 1.2 PURPOSE4) 

To the list of additional objectives ADD: 

(d) Development of MOL hardware and software that will provide for 

the capability of both manual and automatic space flight. 

.This document contains information affecting the national defense of the United States within the meaning of the Espionage tows. 

•Tttle 18. U.S.C.. Section 793 t rile person is prohibited by low. 
---CONMENTA----- • -71 1 - 1 / 2 

eoning of the Espionage lows. 

Person is prohibited by law 

FORM — this document contains in 

SSD AUG 62 20B 1 ale 18. U.S.C., Section 7 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

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 

usefulness 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 ('1/44) 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ---SECREI-_ SPECIAL HANDLING 

1.3 Mission 

The primary mission of the MOL system shall be to conduct 

high resolution photographic intelligence gathering against specific targets 

of interest. 

SP H. 

1-3 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET SPECIAL HANDLING 

3.0.4 Mission Requirements 

3.0.4.1 Photographic Resolution 

It is required that a resolution of be 

obtainable with the MOL system. Unless otherwise noted in this specification a statement of system ground resolution shall be under the following 

conditions: Film having a resolution of Type 3404, and a speed of 6, on 

axis, nadir position, focus and smear included, 2:1 contrast ratio at 

the vehicle, 890-foot lamberts apparent scene luminance, and 80 n. mi. 

altitude. The MOL system shall be capable of the above resolutions 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 cloud-free 

targets per 30-day mission shall be considered the requirement for the 

MOL system, for a cloud-cover of 60 percent (i.e. , 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 MOL 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. 

r 

3-4. 1 
N40 APPROVED FOR 

RELEASE 1 JULY 2015 HANDLING 

PRELIMINARY SPECIFICATION CHANGE NOTICE 

El FINAL NO. 1 

PAGE 4 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-1 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.0.2 PERFORMANCE\tik-3 SAR) 

a) Change "Titan III Initial Launch Capability" to read "MOL Launch 

Facility" 

b) Change second paragraph to read as follows: 

Orbiting vehicle operations involving attitude control, translational 

control and separation of vehicle elements shall be capable of being 

conducted either with crew or automatically. Gemini-B retrofire and 

re-entry shall be performed under pilot control. All system designs 

shall reflect both modes of operation. 

SPECIAL ACCESSREQUIRED 

SENSITIVE ARE4 

PROGRAM NO. 432A IDENTITYA C.7 

SPECIAL HANDLING 

••-n-nt defense of the United States Within the meaning of the Espionage tows. 

f die B. U.5 C Section 703 and 79f • which in any manner to on unoothor•red person is prohibited by law. 

• 

• 

.This document conrcons information offs,. 
SPECIAL HAaiNG, 

SPECIFICATION C ANG-E—Nto- 6 

NO. 1 SUPERSEDING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 PRELIMINARY 

FINAL 

GROUP-3 

Downgraded at 12-year intervals; 

not automatically 'declassified. 

••••••■•••••••.- 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 63ZA . 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-1 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.0.1 GENERAL ''5.s3 SAR) 

Change to read as follows: 

The Manned Orbiting Laboratory (MOL) Program centers around 

an Orbiting Vehicle in which two men will carry out military and 

scientific programs for durations of 30 days. The Orbiting Vehicle 

(OV) consists of a Laboratory Vehicle, a Mission Payload and a 

modified Gemini spacecraft (Gemini B). The OV shall be launched 

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

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

achieVingAoribt, the crew will transfer to the Laboratory Vehicle to 

r 

perform the on-orbit tasks as programmed. 

• 

• 

The on-orbit tasks for the MOL system shall include operation of 

the Laboratory Vehicle and the Mission Payload Segments in both 

manned and automatic modes. During operation in the manned automatic 

(dual) mode, the crew shall monitor orbiting vehicle experiments. 

Provisions shall be made for operation c.-f'the vehicle and the experiment 

by remote control from Mission Control. Provisions shall be made for 

conversion from the (dual) mode configuration of the Orbiting Vehicle 

I. for complete automatic operation within a 4-month pre-launch period,

bvi utilizing appropriately packaged hard'.-.'are and software elements. itOrbital operations shall be planned to enable evaluation of the relative . 

performance .and effectiveness of the two modes of operation. 

After completion of on-orbit experiments, the crew will return 

to the Gemini B, separate the Laboratory Vehicle from Gemini B, 

de-orbit and re-enter, and be recovered. Provisions shall be made 

for disposal of the Laboratory and Mission modules upon completion 

Of the mission. 

The MOL system is specified in terms of system segments , - as 

defined in paragraph 3.1 .2.2. 

SPECIAL HANDLI.NR L 

.This document contains info/motion allecting the notionol defense of the United Stot:sviida.iVe'rneoning of the fspiOntoje (Owl. 

• 

le. U.S C ; Section 793 and 794, the fmnsmosion 01 which ra any manner ro an unauthotited person is ptohibited by low..., 
I. COP NO. 

NI A 

2. CONTRACT END ITEM NO. 

'VOL System 

4. CONTRACT 

Prorram 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

6. EFFECTIVITY 

1V1OL Program 

- 7. TEXT CHANCE 

--- 

. . . 

SPEC. N. 

SS 1 

I FILE OPPOSITE SPEC. PAGE NO. 

3 .1 

• • • 

• 

• • 

•,• 

• 

• 

.• 

• 

,• 

• • 

.• 

• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SSS-233-1 

172] PRF..." IMINARY 

FINAL. 

SPEC0ATiON ChAi 

NO. 3 

2AG 5 oF 25 

S CN- 1 

Paragraph 3.0.1 GENERAL 45,c.3 SAR) 

First paragraph, next to last line, word "orbit" spelled "oribt". 

Second paragraph, after the word "elements" in the 9th line, insert 

the following sentence: 

at..Then configured for automatic operation, the Gemini 9 will be 

replaced with a nose cone." 

r%L. • '•• tiql: •‘ L. 

PROCRAM 
. SPECIFICATiH 

NO. 3 

PAO7-' 

DATE 

SUP7-.RS7D:',G 

25 

PREL.."/'NARY 1c)cb 

LIT FINAL 

'24 11—, 

NRO-APPROVED FOR 

RELEASE 1 JULY 2015 'L az 

SSS-233-1 

ECP NO. 2. 

. ITEM . 

CONTRACT END NO. 3. SPEC. NO. 

• IVA MOL System SS-MOL-1 

4. CONTRACT 5. T;ONTRACT US: L AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

Program 2A CO I 3-1 

G. EFFECTIVITY 

MOL Program 

TEXT CHANGE 

SCIV-1 

Paragraph. 30.1 General''S.43 sem) At the end of the second 

paragraoh„ add the sentence: "Fbr the automatic mode, the NOL system 

shall be designed and qualified for a mission duration that will be 

30 days, initially, ilbwever„ the design shall be such that at a later 

date) brocellants for a 4o day Mission duration can be accommodated.. 
4 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 --3EtRET ECIAL HANDLING 

• 

( 6 3. 0 REQUIREMENTS 

a/ 

3. 0. 1 GENERAL%S%3 SAR) 

The Manned Orbiting Laboratory (MOL) Program centers around an 

Orbiting Vehicle in which two men will carry out military and scientific 

programs for durations of 30 days. The Orbiting Vehicle (OV) consists of a Laboratory Vehicle, a Mission Payload, and a modified 

Gemini spacecraft (Gemini B). The OV shall be launched by a MOL 

Titan III from Vandenberg Air Force Base (VAFB). 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 

on-orbit tasks as programmed. At the end of the mission, the crew 

will return to the Gemini B, separate the Laboratory Vehicle from 

Gemini B, de-orbit and re-enter, and be recovered. 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. 

3. 0. 2 PERFORMANCE3 SAR) 

cioaN tete 

The MOL flights shall be conducted from a Titan III Initial Launch 

Capability (ILC) at VAFB. Upon achieving orbit, the flight crew 

(located in the Gemini B during launch and injection into orbit) will 

prepare 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. 

Orbiting Vehicle operations involving attitude control, translational 

control, separation of vehicle elements, retrofire, and re-entry shall 

'SEGREI SPEC1L Lu Pt.! L. 11 t 

Al• 

.This document contours information of letting .the notional defense of the United Stoles within the meaning of the Estaonoge tows. 

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NO. 1 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-2 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.0.2 PERFORMANCE SAR) 

Change Paragraph 4 with following: 

Communication 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. For operation in the automatic mode, control 

will be exercised by the AVE Computer and Mission Control 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. 

SPECIAL ACCESS REQUIRED 

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PROGRAM NO.C.rzA IDENTITYA,B 

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

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JVLUIAL HAtiaitiLi 

•NPO.APPROVEP EOR 

, .RELEASE 1 JULY 2015 

❑ Pncumuwre..- 

ViL.-.2.7 b 1r1 1.4 

" SPECIFICATION CHANGE NOTICE 

• 

'fPACE ( or _62_..6 .— 

DATE 15 March 6 h. 

I. CCP to 

! 4. CONTRACT • 

Program 632 A 

EFFCC-FIVITY 

MOL Program 

• 

NO. 2 SUPF.RSCDING 

2. CONTRACT iiND ITEM NO. 

MOL System 

3. SPE.C. No, 

SS-MOL-1 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PACE NO. 

3-2 • 

t 

7. TEXT CHANGE 

Paragraph 3,0,2 Perrormance 3 ?kR) 

,i-Ghange.last, sentenceof.thefifth paragraph to read: . Upon 

of. the' flight crew to the_ Gemini B, checkout:. 

_ . • 

• • and activation of.the subsystems associated with 

-• •life support,'sbparation, control, and reentry. 

. • completed by the crew, as augmented by 

the Ground Network.., 

• 

t 

t 

V 

N. 

tt 

f. 

i 

SPECIAL -ACCESS REQUIRED 
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ELEASE 1 JULY 2015 lleRET— SPECIAL HANDLING 

be conducted with pilot control as the primary operational mode. All 

system designs and tradeoffs shall reflect this primary mode of 

operation. 

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. 

Communication with the on-orbit flight crew and mission control functions will be controlled 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 onboard central general-purpose digital computer. Over-all control of 

the various tasks will remain a flight crew function. Certain analyses 

shall be made during orbital flights, both on-board and on the ground; 

the remainder will be accomplished after recovery. 

Upon completion of the mission, the flight crew shall perform final 

checks of the condition of the Gemini 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 Gemini 

B for separation 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 laffel. 

7e€44-f-i-etlAby the ground network. 

'LING 

This document contains information affecting the notional defense of the United States within the meoning of the Espionage taws. 

Title 18. U.S C.. Section 793 and 794, the transmission of which in any mann., to on unauthorized person is prahttnted by law 
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PRELIMINARY SPECIFICATION CHANGE NOTICE gi FINAL NO. 1 

PAGE 6 or _5626_ 

DATE 20 Jan 

SUPERSEDING 

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NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-3/3-4 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.0.2 PERFORMANCE SAR) 

Delete last sentence of Paragraph 6 and replace with following: 

Provision shall be made for Laboratory and Mission Payload 

Segments to continue in orbit in the automatic mode after Gemini B 

separation for re-entry. Data will be transmitted to Mission Control 

by telemetry during the automatic mode operation. Disposal of the 

laboratory and mission payload segments will be accomplished from 

Mission Control. 

SPECIAL ACCESS REQUIRED 

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SPECIAL I g )'"1 

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

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• 

• 
NRO APPROVED FOR. 

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A 

'b• wttm• 

• 

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 deploy a parachute 

system for descent to a water recovery site where ship/aircraft 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. Disposal of the Laboratory and Mission Payloads will be accomplished upon separation from the Gemini B. 

I 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. 

3. 0. 3 

Deleted 

GROWTH CONSIDERATIONS 

' This document contours "'formation affecting the notional defense of the United States with, the meaning of the stnonnqe 

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NO. 2 

PAGE 2 or 62 

DATE 15 March 66 

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3. SPEC. NO. 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

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4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

'Paragraph 3.1.1.1.1 Pre-launch Phas>*Q4,,) 

Change to read: This phase covers the period from arrival of 

systems at the MOL Launch Site (MLS) to the start of 

countdown on the launch pad. Assembly of the 

Laboratory to the Launch Vehicle and the Gemini B 

to the Laboratory will take place at the launch 

pad for checkout and final countdown of the Flight 

Vehicle. The segments of the Launch Vehicle will 

be brought to the launch pad for assembly and 

checkout prior to being mated to the Laboratory. 

Paragraph 3.1.1.1.1.1 Launch Window'(, SAR) 

Change to read: 2). Flight Vehicle constraints.'. 

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I. EC P NO. • 

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SPEC:;iFiCATiON 

No. 3 

2. CONTNACT ENO aTEvi \O. 3, 6-C. NO. 

. MOL Syste:a SS-MOL-1 

5. CONTRACTUAL AUTHORITY 

CCN • 

I FILE OPPOSITE SPEC. PAGE NO. 4. CONTRACT 

Proreraya 632A 

6. EFFECTIVITY 

EOL• P-ogr 1 

7. TEXT CHANGE 

• Paragraph 3.1.1.1.1.1 Launch Window - Yf \ 3 SA) 

ChanLo: 

:—..m. 1) Experiment requirements and priorities to read: 

1) Mission recuirements and priorities 

Paragraph 3.1.1.1.1.2 Solar Angle Sç3 SAR) 

• 

Change to read: 

"The solar angle ) shall be between -60 deg and +60, and may vary 

from one limit to the other during-a 30-day flight. The angle beta. 

is defined as the angle between the earth-sun line and its projection 

on the orbital plane." 

tjJJL 

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RELEASE 1 JULY 2015 SPECIAL HANDLING • 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. 

Pre-launch Phase l'Sc.4) 

This phase covers the period from arrival of systems at the MOL 

Launch Site (MLS) 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. 

3. 1. 1. 1. 1. 1 Launch Window3 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 adverse meteorological 

conditions. Placement of the over-all launch window within a 24 hour 

period shall be determined by: 

IAA, 41, 

.c 2) 

Experiment requirements and priorities 

Vehicle constraints. 

a, 0 

Pf -e)The solar angle ((3) shall be between -60 deg and +60 deg. 

45 1,10 

1' 

3. 1. 1. 1. 1. 2 Solar Angle 1N SAR) 

4 

.This document contains information affecting the notional defense of the United Sinus withinthe meaning of IWOC1,;;0;;;cie lows, 

'Title 18. U.S C.. Section 793 and 794. the transmission of which in any manner to an unauthorised person is ritolstbtled by low 
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r 

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PAGE 7 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-6 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3 .1 .1 .1 .2.1 

Second line from the bottom change "that" to "than" 

UNCLASSIFIED 

711 T:7.1 

J voi .k1 V LA !kiLli 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 1, 1. 1. 2 

liciESPECIAL HANDLING 

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 N\-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 that the 60-min 

hold at T-10 min of paragraph 3. 1. 1. 1.2..2below. 

3. 1. 1. 1. 2. 2 Hold Time \-4) 

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

1) Experiment 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 Ns-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 '11-eRELSP. ECIAL iii-MUNG 

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No. 2 

PAGE _2_ OF 62 

DATE 15 March 66 

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4ZEIEASE 1 JUI,Y 2015 

I. ECP NO. 

NA 

4. CONTRACT 

Program 632. A 

6. EFFECTIVITY • 

MOL Program 

2. CONTRACT END ITEM NO. 

• MOL System 

S. CONTRACTUAL AUTHORITY 

3. SPEC. NO. 

SS -MOL -1 

FILE OPPOSITE SPEC. PAGE NO. 

3-7 

7. TEXT CHANGE 

Paragraph 3.1.1,1.3.2 Trajectory. Safety Nc4) 

Change to read: The ascent trajectory shall be such that, 

in the event of mission abort at any time, the 

Gemini B will not exceed safe conditions for 

recovery of the flight crew. 

Paragraph 3.1.1.1.3.3 Orbital Inclination NO SAR) 

Change first sentence to read: Operation in all orbital 

inclinations between 65 degrees and 125 degrees shall 

be a design objective for the OV. 

LI 

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S 

3. 1. 1. 1. Z. 5 Back-up Launch Capability rt5.4) 

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 Phase 111/44) 

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

initial sustainable orbit and confirmation thereof. 

3. 1. 1. 1. 3. 1 AzimuthiS SAR) 

The system shallbe capable, as aminimum, 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 that, 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 Inclination4S,3 SAR) 

Operation in all orbital inclinations between 65 deg 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. 
MLA g9L HANDLING. 

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NA MOL System SS -MOL -1 

4. CONTRACT 5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

Program 632 A 3-8 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Add: Paragraph 3.1.1.1.3.7 Orbiting Vehicle Separation (U) 

The Orbiting Vehicle shall be capable of separation 

from the LaunCh Vehicle only by flight crew initiation 

from the Gemini B. 
• - 

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Progrua 639A 

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YOL Prograa 

.^. !T 

NO. 3 

I 2. CONTRACT END 

MOL Sy:tem 

5. CONTRACTUAL AUTHORianf 

CON 3-3 

SSS-233-1 

PAGE 25 

SE-MOL-1 

PILE OPPOSITE Sit2C. PAGE NO. 

SSS-2,33-1- 

1. LC P NO. 2. CONTRACT END 1' ;,;0. ,;. 

P:i:o;7,:f'am 632A 

L. 

CONTRACT 

I

5 CONTRACTUAL UTI--XViiTY .A. FL OP?OSZTE PAGE NO. 

CON 

7. TEXT CHANGE 

Paragraph 3.1.1. 1. 3. 4 Insertion Conditions 1'5,Q SAR) 

Chang,e the last sentence to read: 

"Tyically, this orbit shall be a nominal 80 - 130 n :Li elliptical 

orbit with perigee at 55°N latitude." 

MOL System 

NO. 3 

37- 25 
r: 

F 

NRO APPROVED FOR 

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3. 1. 1. 1. 3. 4 Insertion Conclitionscas-3 SAR) 

Insertion shall be performed by the Launch Vehicle into an initial 

orbit with a minimum perigee of 70 n mi. Typically, this orbit shall 

/ go 

be a nominal 80- n mi elliptical orbit with perigee 4retwe-en 

30 ° -50° N latitude-. 11'," 55-°41 hrA,A).ile, 47`.50/ *3, .2.5- 00-1- 6) 

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 Communicationl) 

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 Safety Ns4) 

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 greater than 0. 0 3 

SC?A/W../ 7)-Ze/4} 

3. 1. 1. 1. 4 Early Orbit Phase \-4) 

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 Adjust4) 

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 AV from.the Laboratory Vehicle Attitude Control Translation System (ACTS). 

3. 1. 1. 1. 4. 2 Orbital AltitudeINs3 SAR) 

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

elliptical, within the limits defined in Figure 3-1. The extreme 

3-8 

lergEOPECIAL 11ANDLING • t 

This dot° mem o nfoonlotoon affecting the maroon°, ',lin of the United Stoles within the mthanong of the EsPther,9e tows, 

tole 18, U S C- Seciton 793 and 794, the tiOnym■ SSIOn of whiCh ,n any rnonnef 10 on ,,nourh000yed person II poohtboled by low 
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NA 

2. CONTRACT END ITEM NO. 

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SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-9 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.1.1.1.5 ON-ORBIT PHASE 

Change to Read as follows: 

Paragraph 3.1.1.5 ON-ORBIT PHASE Z5s3 SAR) 

For manned flights, this phase covers the period from insertion 

until separation of the Gemini B from the Laboratory prior to the 

initiation of re-entry. For unmanned flights, this phase covers the 

period from insertion until mission completion including Laboratory 

Vehicle disposal and all data retrieval. 

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I 

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3-9 

PACE OF 62 

DATE 15 March 66 

7. TEXT CHANGE 

Paragraph 3.1.1.1.5 On-Orbit Phase (U) 

Change to read: For Manned flights, this phase covers the 

period from completion of initial crew transfer 

until initiation of final crew transfer. 

SPEC 

UNCLASSIFIED 
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 

'"1T-Sr C- ` 

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• boundaries of 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 Transfer IkSc4) 

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. i‘j./I 

ks, SC' s to .)/ /0 4' 

40;\14'ir1)-)° 3. 1. 1, 1. 5 rj")On-Orbit Phase (U),,C, .5" - 

,y)1 S I 

This phase covers the period from insertion until separation of the 

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

3. 1. 1, 1. 5. 1 Duration Nc4) 

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

3. 1. 1. 1, 5. 2 Nominal Orbiting Vehicle Orientation'4) 

The OV shall be nominally oriented such that the longitudinal axis lies 

in 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 ground track. 

3. 1. 1. 1, 5. 3 Orbit Maintenance S3 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. 
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FILE OPPOSITE SPEC. PAGE NO. 

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7. TEXT CHANGE 

Paragraph 3.1.1.1.5 .6 MISSION OPERATIONS \-3 SAR) 

ADD paragraph after table as follows: 

The equipment shall be designed for remote operation from 

Mission Control with provisions for monitoring both by Mission 

//,3 Control and by the flight crew, 

1,44a.kitaa*.a.tir..--ei44a-Fat-i-e4w.r mission vehicle operations may be programmed 

tqc., for duty cycles in excess of those 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. 

SPECIAL ACCESS REQUIRED 

SENSITIVE AREA 

PROGRAM NO. 452 A IDENTITY 10 

.SPECIAL 

.This docvr,enl con10 ,4 tnfOrmation affecting the notional defense of the United Stoles the meaning of the Espionage tows, 

Title IS. U.S C , Section 793 and 794, the I,ansmission of which in any manner n) on unournorized person is prohibited by low. 
NRO APPROVED FOR 

RELEASE A JULY 2015 MCLASSIFIED TE.CIAL HANDLINU i; 

• 

PRELIMINARY SPECIFICATION CHANGE NOTICE 

FINAL NO. 2 

PAGE. 6 OF 62 

DATE 15 Marrh 66— 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL -1 

4 . CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-10 

6. EFFECTIVITY 

I'LL Program 

7. TEXT CHANGE 

Paragraph 3.1.1.1.6 Re-entry Phase (U) 

Change to read: Re-entry Operations Phase (U) The Re-entry 

• ' Operations Phase is defined as the period commencing 

with separation of Gemini B from the Laboratory and 

ending with landing. This phase includes loiter 

time, retro-f ire, re-entry, parachute deployment, 

and touchdown. Loiter is defined as an emergency 

mode during which the Gemini B is occupied by 

the crew and operates on-orbit as an autonomous 

spacecraft. 

Paragraph 3.1.1.1.6.2 Communications (U) 

Change first sentence to read: During re-entry operations, 

recovery aids (including a beacon) shall be 

provided in the re-entry module to facilitate tracking 

and touchdown prediction. 

3 
1 

5. CONTRACTUAL AUTI,_01TY FILE. OPPOSITE SPEC. PAGE NO. 

Program 632A 1 • CON 3-10 

Nt,f 

SSS-233-1 

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r-1 SP!:-C:F:CAT:ON 

NO. 3 

NA 

2. c:ON'isfiACT END 

l• MOL System 

EFFECTIVITY 

MOL Program 

7. TEXT CHANCE 

Parajraph 3.1.L.1.).6 Mission Operations 

In Table change fourth item to read: 

Crow (Eat/Sleep/Arousal/ 

Conoitioning/Personal/ 

Equipment) 

20.0 

Change TOTAL to read: 

TOTAL Initial Allocation . 40..25 

Change the SCN-1 input to read: 

"The equipment shall be designed for remote ooeration from Mission 

Control with provisions for monitoring both by Mission Control and 

by the flight crew. Mission vehicle operations may be programmed 

for duty cycles in excess of those given in the above table to 

provide additional data. If this is done, crew activities may be 

appropriately scheduled to permit operation (*c..onitoring) in 

accordance with that se-tea:lie." 
NRO APPROVED FOR 

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-tERELSPECIAL HANDLING 

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 safety, 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 Operations1/43 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. 

Maximum Average 

Hr /Day 

16. 0 

4. 0 

0. 25 

=tr.a 0. 

Mission Payload 

Laboratory Vehicle 

Gemini B (Monitoring) 

Crew (Eat/Sleep/Arousal/ 

Conditioning/Personal/ 

Equipment) 

TOTAL Initial Allocation 

(75-z.v 

,R0.7 52;74‘ -9

7tzirgti •90.0?,3— 

3.1.1.1. 5. 7 Maneuvering*%(cs4) 

The OV shall be capable of executing controlled maneuvers with three 

degrees of angular freedom and a fore-and-aft longitudinal translation 

degree of freedom. 

,9_,..6103. 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 

SPECIL ft.iNG 

f p,r, 7; 1. 

11 e. 

3-10 

This document contains information of letting the notional defense of the United States within the meaning of the Espionage tows. 

title 18, U.S C , Section 793 and 794. the transmission of which in any manner to an unauthorized person is prohibited by law 
SS -MO L - 1 

NIRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

2 FINAL • 

SPECIAL HANDLING. 

C 1SSIFIED 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE OF 52 

DATE 20 Jan 66 

SUPERSEDING ex_ 

3. SPEC. NO. 

4. CONTRACT 5. CONTRACTUAL AUTHORITY 

Program 632A CCN 3-11 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

FILE OPPOSITE SPEC. PAGE NO. 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.1.1.1.7 RETRIEVAL PHASE (U) 

Change as follows: 

Replace words "re-entry module" throughout paragraph with words 

"Gemini B." 

Paragraph 3.1 .1 .1 .7.1 RECOVERY SUPPORT (U) 

Change as follows: 

Replace words "re-entry module" with words "Gemini B." 

• 

S UNCLASSIFIED ,1V1 r-1 

QpFP! L;P, Nril 

a ILA r. ovs—. Lij1 La 
NRO APPROVED FOR 

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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. 

,216 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) 

4$ 

Retrieval operations start with theme, ouchdown prediction and end when the crew, data, and4-e--e+kt-r7.4.memeltarie are recovered 

and returned to predetermined locations for tl]iplzi.nitiation of post-flight 

" 0, 

analyses. Retriey,a1 includes location of the .:i--e—.P...atr—y--44vamivrie, physical 

recovery of the , 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

, 

 uipped.with 

proper gear to facilitate recovery of the flight crew, -r=e---e-rftv-f=rripavi ' ttle, 

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. 

3-11 
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DATE 15 Xgrnh 66 

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IFICATION CHANGE NOTICE 

NO. 2 

L ECP NO. 

NA 

4. _CONTRACT 

Program 632 A 

6. EFFECTIVITY 

- - 

MOL Program2. CONTRACT END ITEM NO. 

MOL System 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-12 

3. SPEC. NO. 

SS-MOL-1 

7. TEXT CHANGE 

71r,:r 164 Lull-1v_ 

Paragraph 3.1.1.1.9.2 Pre-Launch Integration, Checkout, and Launch 

Change first sentence to read: Receiving, inspection, and 

installation of various equipment items into the 

various segments of the MOL system will be accomplished 

at the launch site servicing area. Final assembly 

and checkout of the complete MOL flight vehicle 

will be completed at the launch pad. 

r 

;„. 

4. • 

• 
NRO APPROVED FOR 

,4 RELEASE 1 JULY 2015 

3. 1. 1. 1.9 

3. 1. 1. 1. 9. 1 

rt,pt 

Operating Loczttio PECIA HANDLING L. 

Acceptance Tests -4) 

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 tlu Laboratory Vehicle contractor as 

GFE shall be installed at the Laboratory contractor's facility for integration tests. (See Fig. 3-4. ) 

_ 3. 1. 1, 1.9, 2 Pre-Launch Integration, Checkout, and Launch l'Sc4) 

ArA,21, 

3C-"adt.r 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 (\A) 

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 

• c 

*4 3-12 

SSD AFUOGRE2 

• 

This document contains information 74(04 bon 1-1.jnitretr Stntit's 1.4;rtki'f, 114- erretiniFig a e Espionoge tows. 

'tsir 

20B Tttle 18, U.S.C., Section 793 and 71ir ,:,, ::iti.oserisicsgs 88,which in any manner to on unauthorized person is prohibited by law 
NO APPROVED FOR 

RELEASE 1 JULY 2015 

----sfeRg_ISPECIAL HANDUNG, 

PRELIMINARY 

Ea FINAL 

11 52 PAGE _ OF 

DATE 20 Jan 66 

SUPERSEDING 

SPECIFICATION CHANGE NOTICE 

NO. 1 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. T 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-13 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.1 .1 .9.3.2 TRACKING AND COMMUNICATION SITES l'S.c3 SAR) 

a) Add in parenthesis after item (2), Early Orbit, "(manned flight only)." 

b) Add in parenthesis after second line of item (3), "(manned 

flight only)." 

Paragraph 3 .1 .1 .1 .9 .4 RECOVERY AREAS 

Change paragraph as follows: 

Paragraph 3.1.1.1.9.4 RECOVERY AREAS IS:.3 SAR) 

a) Insert words "For Manned flights" at start of paragraph. 

b) Add sentence to end of paragraph as follows, Data capsule recovery 

operations will utilize existing AFSCF facilities and locations." 

SPECIAL ACCESS REQUIRED 

, SENSITIVE AREA 

PROGRAM NO. 4324 IDENTITY A 

•This document contains information affecting the notional defense of the United States within the meaning of the Espionage lows, 

hole 19. U.S C.. Section 793 and 794. the ttonstnission of which in any monnot to on 'unoUthoitzed deismn is prohibited by law. 

• 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 C 

p. 

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F 1NAL 

HANDLING. 

E NOTICE 

PAGE 

DATE 15 March 66 

8 OF 62 

SUPERSEDING 

P,V1 

ft 

r'F 

I A 

NO. 2 

HA 

1 

I. ECP NO. 

NA . 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A '

. 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-13 

6. EFFECTIVITY 

VOL Program 

7. TEXT CHANGE 

Paragraph 3.1.1.2.1 Supply Support (U) 

Change to read: Spare parts support for the Laboratory 

Vehicle, Gemini B, Mission Payloads, and associated 

AGE shall be provided in accordance with SSD Exhibit 

62-13A dated 14 Jan 64. 

F 

Sr UNCV7IFIED 

SPECIAL HANDLING 
NRO APPROVED FOR 

, RELEASE 1 JULY 2015 

• PECIAL HANDLING 

arly Orbit 

SCF stations 

Selected NASA stations 

Selected ETR stations 

Selected WTR stations 

(3) On-Orbit 

SCF stations 

Selected NASA and ETR stations 

,pki 3. 1. 1. 1. 9. 4 Recovery Areas'6...4) 

106 

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 

3. 1. 1, 2. 1 

Logistics 

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 minimum 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 

LNG. 3-13 

FORM This document contoinilt"ormation of fecting the national defense of the United Slates within the meaning of the Espionoge Lows, 

SSD AUG 62 20B Title 18, U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by "law 
ECii41 NG 

cr 

SECRET ofiA'=- 

CONFIDENTIAL 

This document contains information offechng the notional defense of the United States within the meaning o! the Fspi.:.nnan ! iwt 

Title 113, U.S.0 Section 793 and 794, the transmission of which in one manner to on unauthoured person is prohibited by Ina 

3-14 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

responsible contractors. Ma m enance considerations in support of 

the Laboratory Vehicle, Gemini ll, 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 he made available for program 

utilization. 

3. 1. 1. 3 

Deleted 

3. 1, 1. 3. 1 

Personnel and [raining 

Operational Personnel 

There are no Operational Personnel for MOL in the general military 

sense except as included in the support. functions. Support personnel 

associated 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 

be supplied and trained by contractors concerned with the various system segments. 
. 3 

114/N- 30111/17V 3290dV 

_soffPECIA1. 

Dos document contain, "If orrn000n affecting the notronol defense of the United Sures within the meaning of the F spronnye FOwl, 

hue 18. U.S.C. Section 793 and 794, the transmission of which in any manner to on onourhcoled person Is or ohthrted by law 

0 

UW 

> 

0 

X — a. LU 

(7) 

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,sEggiLSPECIAL HANDLING 
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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 

Manned - Automatic 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 crew 

processed and transmitted over a wideband 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 crew in the Gemini B. 

Automatic Configuration 

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

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. 

Manned - Automatic Configuration 

The command and control capability shall use a flight crew of 

two in a manner consistent with the requirement to reserve the flight 

RELW.. 

3-16.1 
NRO APPROVED FOR 

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

The system shall be capable of operation by a single crewman with 

minimum degradation to system performance. 

3.1.1.4.4 Mission Orbital Envelope 

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. 

Apparent scene luminance required for highest quality photography 

defined for this specification is 890 ft. lamberts. 

Orbital parameters for the MOL 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 system shall have the capability of responding to a new 

target list, based on unchanged orbital parameters, as late as hours 

prior to launch. 

3.3.1.4.6 Target Acquisition 

The target acquisition system (exclusive of the crewman) 

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 + 30o 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 a crewman. (Manned-automatic version) 

3.1.1.4.7 Smear Limits 

In addition to the resolution specification, 3.0.4.1 and 

3.3.4.5.3.1, it is required that the amount of smear appearing on the 

format be limited to a maximum acceptable value. 

Manned-Automatic Configuration 

It is assumed that the crew contribution to rate control 

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

3-16.2 

SPEC 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

,d SPECIAL HANDLING 

crew to perform properly in this function within reasonable time 

constraints, the smear contribution provided by the system exclusive 

of crew 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 format: 

a. With final rate control provided by the crewman 

or provided by the navigation and control subsystem through use of the 

devices required for the automatic configuration (i. e., star tracker, 

low drag accelerometer, image motion detector) the value shall be 

b. Without crew participation or use of the devices 

required for the automatic configuration the value shall be 

The uncompensated image smear due to vibration shall 

be no greater than 

Automatic Configuration 

The total smear contribution to dynamic resolution loss 

in terms of angular rate shall not exceed 

The uncompensated image smear due to vibration shall be no greater than 

3. 1. 1. 4. 8 Data Reconstruction 

For reconstruction of ground detail and object location, 

it is required that pointing 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 implementing 

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. 

SE SPECIAL F4 Li1.11G 

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3.1.1.4.10 Flight Crew Requirements (Manned-Automatic Configuration) 

The major crew contributions required for command and 

control consist of: 

a. Selection of Targets 

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

the crew will be capable of selecting 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 crewmen, the other crewman will ensure 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 crewman will then ensure that the tracking error is 

nulled in position and rate while observing the target through the main optics. 

c. 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 minimized by the 

crewman. 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 targets, based on 

the crew-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. Capability for mono also will exist. 

d. Photographic Results 

The crew 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 crew will select that portion. 

f, Verbal reporting of visual observations or photographic 

interpretation of selected high priority target information. 

3-16.4 
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RELEASE 1 JULY 2015 SPEC 'iANDLING 

3. 1. 1.4. 11 Security of Operations 

Provisions shall be made for interfacing technical personnel 

(e. g., Photographic Section Contractor 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. 

SPErfitP r„. 

G. 

3-16.5 
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System Definition 

System Engineering Documentation 

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 Associates 

(contractors or participating government agencies). This contractor/ 

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

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, I 

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 

in 

OA 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 "IECRELSPECIAL HANDLING, 

Imission, (2) the participating Associate responsible for preparing the 

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

Ieach 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 connection (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 

I

(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 changes 

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 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 IHREL SPECIAL HANDLING 

requirements for the assigned functions derived from the Top Level 

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

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 

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" I 

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 

SPECIAL HANDLI 
•

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44 

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4. SPECIAL HANDLING 

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3-21 

"Otr l ars."1 

4 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 L HANDLING 

• 

FIRST DESIGNATOR 

MISSION CODE 

SECOND DESIGNATOR 

ASSOCIATE CODE 

THIRD ursinNAT011 

ARE:1 CODE 

K MOL 10. Laboratory Vehicle Contractor AA Cunt rail r 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 SPO) BB 1s.10L Launch Site (MLS) 

14.2 AC Elect ronics I3BA ILC 

14.3 Martin Company BBT Latin, h Pad in ILC 

14.5 Aerojet-General BBW Receiving Inspection and 

14.6 UTC Maintenani e 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 1‘,st Center 

Mendenhall CA TranstIort 

16. Launch Operations Agency CB Factory to Factory 

(65- - ATW) CC Factory to Government 

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 Re- Ent ry 

Descent 

(-) Designation Pending LA 

EB 

Recovery 

Planned Recovery Area 

EC Contingency Recovery 

Arca 

ED Emergency Recovery. 

Area (MLS) 

EE Emergency Recovery 

Area (Other) 

FA 

XX Pinrality of Areas 

Designation Pending 

I Figure 3-3. MOL System Flow Diagram Code 
I: ;- ■ 

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11 e, ,CI 

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fr 

fl 

83 

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- 

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, 

1 I 

SPECIAL HANDLING. 

tie 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING • integration of these requirements to ensure over-all system assembly, I 

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 ',lunch" 

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. 

3-23 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SEC SPECIAL litINDLING 

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. 2. 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 

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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RELEASE 1 JULY 2015 SPECIAL BAN DUNG 

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. 

3. 1. 2. 1. 4. 8 Block 2, "Perform Retrieval Operations" 

These functions start with earth touchdown and include normal 

retrieval from planned recovery 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. 
4 

O APPROVED FOR 

LEASE 1 JULY 2015 

SPECIAL NG 

SPECIAL LING 

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 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• SPECIAL HANDLING 

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 

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. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 euid. liANDL1116 

•••••••, 

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. 

Orbiting Vehicle System Segment 

This constitutes all segments and parts 

of segments which are retained as a 

unit in orbit. 

LOCATION IN 

THIS DOCUMENT 

3.3. 1 

Laboratory Vehicle System Segment 3. 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 

Test 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. 

3. 1. 2. 4 Deleted 

3. 1.2. 2. 1 through 3. 1. 2.2.11 
ENTIADLING 

SUPERSEDING 

SPECIFICATION CHANGE NOTICE 

No.i 

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0 PRELIMINARY 

El FINAL 

PAGE I OF 52 

DATE 20 Jan 66 

1. ECP NO. 2. CONTRACT END ITEM NO. 3. SPEC. ---------Ir--- NO.

NA MOL System SS-MOL-I 

4. CONTRACT 5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

Program 632A CCN 3-29 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3 .1 .3.1 .1 GENERAL \-4) 

Change third paragraph to read as follows: 

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 automatic mode 

by remote control. Adequate accessibility shall be provided for 

maintainable items and provisions shall be made for storage of 

spare parts and tools. 

of) 

SPECIAL hirt"7:jNG, 

--C-OHFIDENTIAL-_ 

:This document contains information of feeling the national defense of the United States within the meaning of the Espionage Lows. 

T.Ite 18. U.S C., Section 793 and 794. the transmission of which in any manner to on unauthorized person is prohibited by law. 
CIAL HAZLIE 

4 

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RELEASE 1 JULY 2015 

3. 1. 3 System Effectiveness 

3. 1. 3. 1 Effectiveness Measures 

3. 1. 3. 1. 1 General ?k\-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 

effectiveness. 

The presence of the flight crew will permit maintenance on orbit to 

sustain the mission capability. Accordingly, appropriate design measures shall be taken to provide checkout, replacement, and maintenance capabilities consistent with maximum cost effectiveness and extended mission requirements. 

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

(1) Completion of the total of the orbital manhours activity for mission performance including such checkout, alignment, calibration, 

repair, preparation, execution, processing, 

examination, communications, and similar 

tasks which are an integral part of, or are in 

direct support of, the mission 

(2) Return to designated ground stations of the 

specified types, quantities, and qualities of 

data including that delivered by the astronauts 

in person 

• 

3-29 

FORM This document conjoins information affecting the notional defense of the United Stores within the meaning of The Espionage Lows. 

SSD AUG 62 ,a) Title I8. U.S.C., Section 793 and 791. the tronsmisston of which in any manner to on unout noticed person is prohibited by low 
1 Al

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DATE 20 Jan 66 

SUPERSEDING 

1,?a. 

IFICATION CHANGE NOTICE 

NO. 1 

1. ECP NO. 2. CONTRACT END ITEM NO. 

NA MOL System 

4. CONTRACT 5. CONTRACTUAL AUTHORITY 

Program 632A CCN 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

3. SPEC. NO. 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-30 

Paragraph 3.1.3.1.2.2 LABORATORY VEHICLE SYSTEM SEGMENT ?4) 

Change paragraph to read as follows: 

The combined effectiveness of the Laboratory Vehicle including 

the mission module structure for the total mission shall not be less 

than 0.97 in the manned-automatic mode, and 0.90 in the automatic 

mode. 

PECIAL HANDLING 

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

.Title I8, U.S.C., Section 793 and 794. the transmission of which in any manner to on unauthorized person is prohibited by low. 
t 

• 

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PRELIMINARY 

[2 FINAL 

PAGE 9 OF 62 

DATE 15 March 66 

SUPERSEDING 

ECIAL E;:i1DLING 

SPECIFICATION CHANGE NOTICE 

NO. 2 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

_Prn ri--P.mil12 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-30 

6. EFFLCTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.1.3.1.2.2 Laboratory Vehicle System SegmentIV.cld 

Change paragraph to read as follows: 

The combined effectiveness of the Laboratory Vehicle including 

the mission module structure for the total mission shall not 

be less than 0.97 in the manned-automatic mode, and 0.80 in the 

automatic mode.' 

comrillENIIRL 

cprzrr.T PECIAL 1NG 

r., • • " 

I 

t 

; 
3-30 

FORM This document contains mformotion SSD AUG 62 20B Tole 18, U.S C , Section 797 and 7411,16113 1/4211.1191 

L.A 3,1 

I defense of the

.) 

United State, ithin ttle meanie, sc..onage lows. 

any manner to nn unauihottted person .s pebbled by low 

Sp.( A t Tom. A 

RELEASE 1 JULY 2015 

NRO APPROVED FOR 

__suRET HANDLING 

( 3) rovision of environmental conditions, life 

support, performance capabilities, and ground 

support for the duration of the missions as 

required to sustain the system and to perform 

the missions. 

3. 1. 3. 1. 2 Effectiveness Apportionment ((4) 

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 he 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 

retrieval and, for the crew, recovery. 

3.1.3.1.2.1 Orbiting Vehicle System Segment N4) 

The allocation of effectiveness assigned to the Orbiting Vehicle Segment shall be for the time period from launch through 30 days of orbi- 

-IV- • tal operation to separation of the Gemini B. Since the Orbiting Ve- 

...? 

values will be assigned under the other segments. 

~aNi 5C'Aibt 3.1.3.1.2.2 Laboratory Vehicle System Segment tS-4) 

The combined effectiveness of the Laboratory Vehicle including the 

mission module structure for the total mission shall be not less 

than 0.96. 

3.1.3.1.2.3 Gemini B System Segment (\-4) 

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. 

hide segment combines portions of a number of other segments, 
Ii

ioart.; 

fb, 

CATION CHANGE NOTICE 

14 OF 52 

DATE 20 Jan 66 

It 

1 p N 

E 

MRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

Ea FINAL NO. 1 SUPERSEDING 

3. SPEC. NO. 

SS-MOL-1 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

4. CONTRACT 

Program 632A 

6. EFFECTIVITY 

MOL Program 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-31 

7. TEXT CHANGE 

Paragraph 3.1.3.1.2.7 LAUNCH OPERATIONS, FLIGHT OPERATIONS, 

RECOVERY, AND TEST SUPPORT SYSTEM 

SEGMENTS Ns4) 

Change paragraph to read as follows: 

The composite effectiveness of these segments shall be at least 

0.98 for manned-automatic (dual) mode and at least .80 for automatic 

mode. 

'YA r4",. IWZ2 Ad. r : 1,7) 1

sprcf 

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

'Title 18, U.S.C., Section 791 and 794. the transmission of which in any manner to on unauthorized person is prohibited by low. 
NRO APPROVED FOR , 

RELEASE 1 JULY 2015 

SSS-2 3"j--- 1 

No. 3 

HOP NO. 2. CCNTHACT END ITEV. NO. , 3. SP..-2C. NO 

1OL Syst.-..."-a 

4 . C cr 5. CONTFiACTUAL AUTH3Hi-.: : FILE GPPGSITE. S?HC. PAGE NO. 

. E.-FFE.C'T.'IViTY 

MOL 

7. TEXT CHANGE 

Pati3 .1. 3 .2 .1.1 G23und rree 3cluil-mS- t ) 

,L to ;:eadl. as follow/.; 

P.rosrala fo2 Launch - soii COrafOr'' 

-t7.0t o 1=f;--470 arLd. 

f;entance.' 0::: :::oco:aft maz'a-;o1'.i.to e.L3 

of 1.77,-L77_2,;-1;-70 shall apply in 

the ioczot 02 all 07 .:-',23E alleas secf.fically ezzera-,oted. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --steRET_SPECIAL HANDLING 

• 

3, 1. 3. 1. 2, 4 Mission Payload System Segment N-3 SAR) 

The effectiveness of the Mission Payload Segment for the total mission 

shall be not less than 0.95. 

3. 1. 3. 1. 2, 5 Crew Equipment System Segment\-4) 

The effectiveness of the Crew Equipment, including backup modes, 

shall be not less than 0.999. 

3.1.3.1.2.6 Titan III System SegmenttS-4) 

The effectiveness of Titan III from final countdown 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 SegmentsrtS.0) 

The composite effectiveness of these segments shall be at least 0.98. 

3. 1.3.1.2.8 Flight Crew System Segment t5.,..,4) 

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 implemented to run 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\-4) 

(so; .‘ The maintainability program for Launch Vehicle AGE shall conform to 

b) — $141-70 An4 //N. -s -t - 4 7/ 

0-r the requirements of MILei 4. rho-, 

, 1'03 sil_.,./70 Pc "ei: -4171 

(5€4', The requirements of MIL-44-24rrshall apply in the design and de- 

. fit me -7 

CO' velopment of all OV AGE, unless specifically exempted. Maintenance 

ogrr. I 

a—, A 4111 t L3,3' tt,a3 

1hts document contotns information affecting the national defense of the Uni ted Slates within the mecintng of the Esatonage laws, 

•Title 18, U S C.. Section 793 and 794. the ttoopoission of which to any manner to on unauthorized person is prohibited by low 

1 

st • 
PRELIMINARY SPECIFICATION CHANGE NOTICE 

El FINAL NO. 1 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

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PAGE 15 Jan 66 DATE 

SUPERSEDING 

3. SPEC. NO. 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-32 

ECIAL HANDLING 

ICLASSIFIED 

Paragraph 3.1.3.2.1.2 ON ORBIT MAINTENANCE REQUIREMENTS (U) 

Delete and replace with following: 

See Paragraph 3.1.3.1.1 for requirements 

• UNCLASSIFIED 

ECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

..•-••■••■■ . 

40.va.4 

at the launch site sh.illbe're-stricted to major module /component removal and replacement. Module and component repair shall, in 

general, be accomplished at the point of manufacture. The items to 

be repaired at the launch site shall be restricted to that equipment 

which can be repaired and revalidated at the launch facility 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 onorbit 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 have 

features which will facilitate fault isolation and detection. 

/ fr„-- 3.1.3.2.1.2 On-Orbit Maintenance Requirements( -4) 

5CPI The scope of Laboratory Vehicle and Payload on-orbit scheduled and 

6 1° unscheduled maintenance and repair shall be established as a result 

of design optimization studies and tradeoffs. Quantitative maintainability requirements shall be established consistent with allowable 

element downtimes. Adequate accessibility shall be provided for the 

maintainable items, and provisicn shall be made for storage of spare 

parts, 

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 Program are specified in 

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

a. 

0_4 

3-3Z 

•4; FORM This document contains information oil 

SSD AUG 62 20B litle 16, U.S.0 Section 793 and 79e. 

pionage lows. 

h in any manner to an unauthotized person is prohibited by law 

•••••-.11. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ECIAL HANDLING • 

(1) Prelaunch - (Applicable to all segments) 

(2) Launch/Ascent - (Applicable to Airborne Vehicle 

and ground environment) 

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

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

3. 1. 3. 5 Transportability and Handlin 

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) 

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 

ThicieSPECIAL HANDLING 333 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIA, 

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 

Safety 

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. 

SPECIAL HANDLING 

3. 1. 3. 7 

3. 1. 3. 7. 1 
SPECIAL HANDLING 

3-35/36 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 PECf!' u ING 

,11 System design for safety shall be coordinated with maintainability design to optimize system maintainability characteristics, safety characteristics, 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 precedence. 

3. 1. 3. 7. 3 Crew Safety (U) 

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 maximum 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) 

Concentrations of toxic compounds shall be 

within acceptable limits both for short term 

and for continuous exposure. 

Techniques and equipments shall be selected 

to assure that safe exposure levels are not 

exceeded. 

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) 
• WO APPROVED FOR 

RELEASE 1 JULY 2015 

--sfeREIZECIAL 

3. SPEC. NO. 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

la :61 

PAGE 16OF 52 

DATE 20 Jan 66 

SUPERSEDING 

O PRELIMINARY SPECIFICATION CHANGE NOTICE 

g FINAL NO. 1 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

4. CONTRACT 

Program 632A 

S. CONTRACTUAL AUTHORITY 

CCN 3-45 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

AUTOMATIC MODE 

Laboratory Vehicle System Segment 

Nose Fairing 

Mission Payload Segment 

(TO BE 

DETERMINED) ; 

Paragraph 3.3.1.1.1.1 WEIGHT BREAKDOWN3 SAR) 

Change to read as follows: 

MANNED-AUTOMATIC (DUAL) MODE 

Laboratory Vehicle System Segment 13, 555 

Gemini B Segment 5,610 

Mission Payload Segment 6, 200 

Crew Equipment Segment 700 

Flight Crew Segment 360 

TOTAL 26,425 lb. 

TOTAL (Shall not exceed 26,000 #) 

Paragraph 3.3.1.1.2.1 ORBITING VEHICLE N1/4-4) 

Change second sentence to read as follows: 

Power demand over the entire 30 days is a nominal 2.0 kw with nominal 

peaks of 3.6 kw. 

SPECIAL ACCESS REQUIRED 

SENSITIVE AREA 

PROGRAM NO. C12A IDENTITY es 

SPECW_ • t. 

F ts. !Rim 

5 P. 

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

•Title 18. U.S.C.. Section 793 and 794. the ifonsrnission of which in any manner to on unauthorized person is prohibited by low. 
CiAL FIANULA 

P AGE _AI OF 62 

SPECIFICATION CHANGE NOTICE DATE 15 mArch 66 

1 

I. 

NO. 2 SUPERSEDING 

1. ECP NO. 2. CONTRACT END ITEM NO. 3 SPEC. NO. 

NA • MOL System • SS -MOL -1 

4. CONTRACT S. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

• 

Program 612 A 3-45 

6. EFFECTIVITY 

__Mori Program 

7. TEXT CHANGE 

Paragraph 3 

Change 

.3.1.1.1.1 Weight Breakdown tSc13 SAR) 

to read: Within the Orbiting Vehicle System Segment, 

the maximum design allocation of weights shall be 

as follows: 

Laboratory Vehicle System Segment 13,555 

Gemini B System Segment 5,660 

Mission Payload Segment 6,200 

Crew Equipment Segment (In Gemini B) 140 

(In Laboratory) 510 

Flight Crew Segment 36o 

TOTAL 26,425 lb 

Weight allocations and breakdown shall be in 

accordance with the appropriate requirements of 

MIL-M-38310. 

Paragraph 3.3.1.1.2.1 Orbiting Vehicle Ns4) 

Change first sentence to read: The Laboratory Vehicle 

central power system shall provide the total 

power requirements for the Laboratory Vehicle 

and Mission Payload during launch, ascent and 

on-orbit phases. The Laboratory Vehicle central 

power system shall provide power to the Gemini B 

during the early orbit and on-orbit phases prior 

to Gemini B separation. 

SPECIAL ACCESS REQUIRED 

SENSITIVE AREA 

PROGRAM ...... . . 

ECIAL }-iiVi'DLING-• 

- NRO APPROVED FOR 

• RELEASE ;I ,JULY 2015 

O PRELIMINARY 

FINAL . 

dI" 
PAC, 

DATE 4-) rjl 

SUP"'STD'CC, 

PEG. NO. 

SS - MOL -1 • 

3. 

FILE OPPOSITE SPEC. PACE NO. 

3-45 ' 

NRO APPROVED 

RELEASE 1 JULY 

I. 

FOR 

2015 

O PRELPviINARY 

Li..! FINAL .

ECP NO. 

N/A 

SP7CFICATION 

. NO. 3 

2. CONTRACT END ITEM NO. 

MOL System 

4. CONTRACT 

Program 632k 

5. CONTRACTUAL AUTHORITY 

CCN 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANCE 

Paragraph 3. 3. 1. 1: 1. 1 Weight Breakdown 3 SAR) 

Change weights to read: 

MANNED-AUTOMATIC (DUAL) MODE 

Laboratory Vehicle System Segment 13,555 

Gemini B Segment 5, 660 

Mission Payload Segment 8,433 

Crew Equipment Segment (In Gemini B) 140 

(In Laboratory) .. 510 

Flight Crew Equipment 360 

28,658 

AUTOMATIC MODE 

Laboratory Vehicle System Segment (To be 

Mission Payload Segment Determined) 

Weight allocations and breakdown shall be in accordance with the 

appropriate requirements of MIL-M-38310. 

rs 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

3.3 PERFORMANCE ALLOCATIONS 

4 3.3.1 Orbiting Vehicle System Segment (U) 

4 The Orbiting Vehicle shall be composed of the following system segments: the Gemini B, the Laboratory Vehicle which includes the 

mission module structural shell, the Mission Payload, and the Flight 

Crew and Flight Crew Equipment. 

3.3. 1. 1 

3.3.1.1.1 

0 °.'Iv / allocation of weights shall be as follows: 

4, 6. 4' Laboratory Vehicle System Segment 13,555 

/S Gemini B Segment tp!cbe 6, t" 

). v.-4t-°4?-6' 

.) 

/DO 0,1Within the Orbiting Vehicle System Segment, the maximum design 

1,s/ 

3.3.1.1. 1. 1 

kt/ft 3 0 

,.--.7 Mission Payload Segment 4p4e0 5,1133 

hyle 

SC')0.")%1MeCrew Equipment Segment lin 6:0:11,1,)1) 4= 

. 9.C1411+ L Flight Crew Segment 360 

Wit` - a, 1/4 c TOTAL 2:1:rpt= lb 

Weight allocations and breakdown shall be in accordance with the 

requirements of MIL-M-38310. 

3.3.1.1. 1.2 Center of Gravity (U) 

The center of gravity shall be established and controlled such that 

requirements for on-orbit attitude control and Titan III launch phase 

control are not compromised. 

3.3.1.1.2 Electrical Power 

3.3.1.1.2.1 Orbiting Vehicle '1<,...-4) 

..-711/4-The Laboratory Vehicle central power system shall provide the total 

15II 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 1. 8 kw with nominal peaks of 3. 6 kw. 

......SteRE.L.SP_Lr7Cit!L L 

3-45 

•Thfs document contains information of fecting the national defense of the United Stoles within the meaning of the Escaonnge Laws. 

Title 18. U.S C Section 793 and 794, the transmission of which in any manner to on anoutho,,ed oe•son is prohibited by low 

Allocated Performance and Design Requirements 

Mass Parameters 

Weight Breakdown 3 SAR) 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

Ea FINAL 

klibLING 

PAGE 17 OF 52 

ECIFICATION CHANGE NOTICE sot JAPTERS2EDO Jan ING 66 

NO. 1 

1. ECP NO. 

NA 

4. CONTRACT 

Program 632A 

6. EFFECTIVITY 

MOL Program 

2. CONTRACT END ITEM NO. 

MOL System 

5. CONTRACTUAL AUTHORITY 

CCN 

3. SPEC. NO. 

SS -MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-46 

7. TEXT CHANGE 

Paragraph 3.3.1.12.3 LABORATORY \-4) 

change to read as follows: 

The 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 . 

Paragraph 3.3.1.12.4 MISSION PAYLOADN4) 

change to read as follows: 

A nominal 300 watts will be available for the combined mission 

payload segment. 

SPECIAL HANDLING 

CONFIDENTIAL 

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

'Title 18, U.S.C., Section 793 and 794, the transmission of which in any manner to an unauthorized avian is prohibited by law. 
ECLASSIF1 HANDLING' 

NRO APPROVED FOR 

R5LEASE0 JULY 2015 

C] PRELIMINARY 

FINAL. 

URCLASS'ElElsEREISPECIAL HANDLING 

PAGE _Ii_ or 62 

DATE 15 marrIl 

SUPERSEDING 

SPECIFICATION CHANGE NOTICE 

NO. 2 

1. ECP NO. 2. CONTRACT END ITEM NO. 

MOT. ±em 

4. CONTRACT 5. CONTRACTUAL AUTHORITY 

• Prel(78.17L__632__A • 

6. EFFECTIVITY 

MOL Program 

3. SPEC. NO. 

SS -MOL -1 

FILE OPPOSITE SPEC. PAGE NO. 

3-46 

7. TEXT CHANGE 

Paragraph 3.3.1.1.2.2. GeMini B. (U) 

Change to read: Electrical power allocation to the Gemini B 

shall be a nominal 150 watts. 
ECP Na 

NA 

4. CONTRACT 

Program 632A 

2. CONTRACT ENDITEM NO. SPEC. NO. 

147, Svster, I RS-M.:ill-1 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

CCN 3-46 

.. • • 

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SSS-233-1 

• r• .,.. • • 

0 PRE:1- IMINA1-.Y 

PECFCATION 

772 

- FINAL NO. 3. 

6. EFFECTIVITY 

YOL Program 

7. TEXT CHANGE 

Paragraph 3.3.1.1.2.2 Gemini B (U) 

Change to read: 

nElectrical power allocation to the Gemini B shall be a nominal 100 

watts for normal on-orbit storage. All Other Gemini B power system 

requirements shall be provided by the local Gemini B power supply. 

Paragrabh 3.3.1.1.2.3 LIIoraY Ok".4) 

Change to read: 

The Laboratory shall be allocated a nominal 1.1 kw for Its functions 

during all phases of the mission after transfer to internal power with 

a max power of 1600 watts during payload activity. 

Paragraph 3.3.1.1.2.4 2.1 191sitt122.y_ -1; load N4) 

. Change to read: 

A nominal 500 watts will be available for the combined mission payload 

segment, including its computer requirements. Its max power allocation 

shall be 1800 watts. 

f7 r 

L :2)- 

• 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

1AL HAND 

Peak power requirements which exceed the power supply capability 

412 shall be individually accommodated. 

3. 3. 1. 1. 2. 2 Gemini B (U) 

1/ /00 

Electrical power allocation to the Gemini B shall be a zominal*sit watts 

for normal on-orbit storage. Nominal power levels of 480 watts for 

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

Po

, 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 (11/44) 

The Laboratory shall be allocated a nominal power of 1.17 kw for its 

functions during all phases of the mission after transfer to internal 

4,3 

/4) Ajo 

4 

epower. 

04 3. 

6 9,4;111 

3. 1. 1. 2. 4, Mission Payload(\-4) 

id

031A nominal 480 watts will be available for the combined Mission Pay- 

- load Segment. 

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. i. 5), 

plus a leak rate of 1.5 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 

S.h :A72 ThiS document contains information affecting the notional defense of the United Stores within the meaning of the Espionage Laws, 20o Tole 18. U.S.C., Section 707 and 794. the transmission of which In any manner to an unouthoneed person is prohibited by low 

i

z, 

gfzttif 

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

EGIAL HANDLIIV 
E17 -AA;',TUNG 

SPECIFICATION CHANGE NOTICE 

NO. 2 

NROAPPROVEDFOR 

RELEASE1JULY2015 

PRELIMINARY 

1:2) FINAL 

PAGE 12 of 62 

DATE 15 March 66 

SUPERSEDING 

: • 

C1AL 1-; 1' 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL.System 

3. SPEC. NO. 

SS -MOL -1 

t 

[ 4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-47 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.1.2.1.3 Data Transmission System (U) 

Change to read: 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 as required. 
CIAL HANDLING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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

The following requirements are common to all flight configurations. 

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. 

Attitude Control Translation System (ACTS) 

Operational Modes (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 

either inertial orientation or in a local vertical orientation shall be 

provided. Generation of disturbance torques by venting of stored 

material and by starting and stopping of rotating machinery shall be 

minimized. 

3. 3. 1, 2, 2. 3 Maneuverability (U) 

Maneuvers shall be accomplished with the Laboratory ACTS. 

P"U c 

; 010 

3. 3. 1. 2. 2 

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

rCIAL HANDLING 

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

SSD AUG 62 20B Title 18, U.S C., Section 797 and 794. the transmission of which in any manner to on unouthotited person it ptohibireci by law 

3-47 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

PRELIMINARY 

1:1 FINAL 

PAGE 13 OF 62 

DATE 15 Marrh 66 

SUPERSEDING 

WLERIA■ :DLIIIL, 

-6 IFICATION CHANGE NOTICE 

NO. 2 

ECIAL 

UHCLASSEFED 

I. 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-48 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.1.2.5.2 Separation (U) 

Change to read:. The capability shall be provided for separation 

between the Gemini B and Laboratory, and between the 

Laboratory Vehicle and Titan III. 

1,4 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

HANDLING 

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 X-4) 

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. 

3. 3. 1. 2. 5 

3. 3. 1. 2. 5. 1 

Structural Design Requirements 

General (U) 

3. 3. 1. 2. 3 

SSD AFAR:z 20B 

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, including 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). 

This document contains information tense of the UmSic es wi N e7RFdnTnf 'the Espionage tows, 

Title IS. U.S.0 Section 793 and 7 nsrnission 01 whit in any manner to an unauthorized person Is prohibited by low 

/3 

tk, 
• 

I;IRO APPROVED FOR 

RELEASE 1 JULY 2015 

PAGE 18 OF 52 

DATE 20 Jan 66 PRELIMINARY 

FINAL SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-49 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3 .3 .1 .2 .7 .4 VIBRATION (Moved to Paragraph 3.3.1 .2.5.5) 

Add new paragraph 3.3.1.2.5.5 as follows: 

3.3.1 2 .5 .5 VIBRATION (U) 

During on-orbit Mission Payload segment operations, vibrations induced 

on the laboratory vehicle by the normal operation of any OV subsystem 

shall remain within the following limits: (to be furnished) 

UNCLASSIFTD 

IHRESPECIAL HANDLING, 
CIAL 

SPECIFICATION CHANGE—NOTICE 

No. 2 

I

'7'; MI 

114 ...Ad' Li I 1/21.4 

P AGE _IL. OF '62 

DATE 15 Marnh 66 

SUPERSEDING 

NROAPPROVEDFOR 

RELEASE 1. JULY 2015 

PRELIMINARY 

FINAL 

I. ECP NO. 

NA 

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MOL .System .

3. SPEC. NO. 

SS-MOL-1 _ 

4. CONTRACT 

Program 632 A 

S. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-49 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.1.2.6.1 Normal Mode (U) 

Change to read: 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. 

The normal mode of crew transfer from Gemini B 

to Laboratory and Laboratory to Gemini B will 

be via the enclosed internal crew transfer tunnel. 

The crew members will wear the unpressurized MOL 

basic pressure suit during transfer. 

The crew members will transfer singly. The first 

crew member to transfer will perform the required 

activation (Laboratory or Gemini) before transfer 

of the second crew member. The second crew member 

will perform the required deactivation before 

completing the transfer. 

Paragraph 3.3.1.2.6.3 Number of Transfers IN% 

Change last sentence to read: It shall be within the system 

capability to provide up to 12 hours crew stay time 

in the Gemini B during the on-orbit phase without 

degradation of mission duration. 
SPECIAL HANDLINCI 

3-49 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

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

Flutter or other related dynamic instability shall be prevented on the 

Orbiting Vehicle system eitt.4 

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

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

40--- The Gemini B crew transfer hatches will remain open and the LaboraSo tory 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. 
NDLIM 

o ense of the United States within the meaning of the Espionage laws, 

e ransmission of which in any manner to On unauthooled.P1/tOn is prohibited by law 

3-50 

This document contains infoomoto 

1,11e 18. U.S.C, Swoon 793 and 

LC

' 

N 

N 

cri

01 I 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 i SPECIAL HANDLING 

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 Nc4) 

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)S.-4) 

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. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLINGI 

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EEI FINAL NO. 1 

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DATE 20 Jan 66 

SUPERSEDING 

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NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-51 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Delete Paragraph 3.3.1.2.7.4 and replace with following: 

3.3.1 2 .7.4 AUTOMATIC EQUIPMENT OPERATION X-3 SAR) 

Provisions shall be made in the orbiting vehicle to accomplish on-orbit 

operation in the automatic mode for up to 30 days . The automatic mode 

requires capability of replacing crew control of the vehicle with automated 

operation, including fault isolation and corrective action. All automated 

subsystems shall provide for manual override or inhibit by the crew. 

Provisions shall be made for crew and ground control to evaluate the 

operation of the orbiting vehicle in the automatic mode. 

Paragraph 3.3.1.2.8 AEROSPACE GROUND EQUIPMENT (AGE) *(Sc3 SAR) 

Add sentence to end of first paragraph as follows: 

The OV AGE shall be designed to support manual, automatic and mannedautomatic (dual) modes of operation. 

SPECIAL ACCESS REQUIRED 

SENSITIVE AREA, 

PROGRAM NO. C Y2 A IDENTITY 4 ta 

:This document contoins information affecting the national defense of the United States within the meaning of the Espionage Lows, 

•Tille 18, U.S.0 Section 703 and mt, thetransmissi

on of which in any monner to on unauthorized person is prohibited by low. 
NRO APPROVED FOR 

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DATE 15 March 66 

SUPERSEDING 

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FItATION CHANGE NOTICE 

NO. 2 

SPECIAL HA ,IDLING 

COMFIDEETIIAL 

2 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. — 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-51 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.1.2.8 Aerospace Ground Equipment (AGE) (c) 

Change first sentence to read: The OV AGE shall include all 

the Gemini B, Laboratory Vehicle, and Mission 

Payload AGE necessary to transport, handle, mate, 

integrate, verify interfaces, calibrate, checkout, 

isolate faults, monitor, record, service, and 

control the OV. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 L6 

ij;1 ° Lti 

3. 3. 1. 2. 7. 4 

1 

1:014_, 

During on-orbit Mission Payload segment operations, vibrations 

induced on the laboratory vehicle by the normal operation of any OV 

subsystem shall remain within the following limits: (to be furnished) 

1 6'3. 3. 1. 2. 8 Aerospace Ground Equipment CAGE) \-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. This 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 for compatibility with the Titan III AGE, 

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 Simulators) (U) t.0 

Mission simulators shall be provided to accomplish training in 

N.) 

accordance with paragraph 3. 3. 12. 2. 1. 2. 4. 

SUET SPECIAL HANDLING. 

CONFIDENTIAL 3-51 

SSD A PljOGRi2 208 

This document contains inlormotion affecting the notional defense of t he United States within the meaning of the Espionage Lows, 

Title 18, U.S.C., Section 793 and 791, the transmission of which in any manner to an unauthorized Person is prohibited by law 
AL HANDLING PAGE 16 or 62 

ATION CHANGE NOTICE DATE 15 Marrh 

NO. 2 SUPERSEDING 

SPECIAL HA IDLING, 

UHCLASSFIED 

NRO APPROVED FOR 

RELEASE.1 JULY 2015 

PRELIMINARY 

[21 FINAL 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

.MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-52 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.1.3 Fucntional Interfaces (U) 

. Change to read: (Functional interface documents shall be listed 

here when defined and approved in accordance with 

IFS-MOL-100001.) 

t 
SPECIAL HANDLING 

A Aril Lail; NRO APPROVED FOR 

RELEASE 1 JULY 2015 

(14_/- ?

.\11" 3. 3. 1.3 Functional Interfaces (U) 

(Functional interfaces shall be listed here when defined by the cognizant 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. ) 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL "'DPING 

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 cannot be shut down for at least 20 minutes. 

3.3.1.5.2 Malfunction and Post-Gemini Separation Operations (MannedAutomatic Flights only) 

To permit obtaining maximum useful performance data on 

the Mission Payload under flight conditions, the Orbiting Vehicle shall be 

designed so that operation of the Mission Payload hardware shall be possible: 

a. If the flight crew 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 Mission Payload hardware be 

operable. For example, the above shall not require that unmanned 

operational capability be provided for hardware for which only manual 

operation by the flight crew is feasible. Return of useful photographic data 

shall not be a requirement under conditions a. and b. above. 

3.3.1.5.3 Mission Payload Ground Handling 

The mission payload 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. 

6 .77 15-x,U'J 7SPECIAL j arILA r tjhu 

3-52.1 
ANDLING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 2 aoratory Vehicle System Segment Z11/44) 

The Laboratory Vehicle shall consist of two modules: (1) a Standard 

Mission Module (unpressurized, ten feet indiameterand 35 ft long, and 

located aft of the Laboratory Module), and (2) a Laboratory Module 

which shall consist of a pressurized and unpressurized section. The 

pressurized section will consist of two compartments to enclose and 

support the operation of environmental control, life support, attitude 

control, power generation, communications, vehicle status monitoring, 

and mission equipments. 

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

3. 3. 2. 1. 1 Volume 

1. 3. 2.. 1. 1. 1 Pressurized 4) 

The Laboratory Module shall provide a pressurized volume of approximately 1000 eu ft, divided between two compartments. The baseline 

design 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 

A he based upon the optimal de. 

ratory Myduie. 

I It for man's ,,ffeciiveness in the Labo3. 3. Z. 1. 1.2. Unpre ssur 

The Laboratory Module shall provide a usable unpressurized volume 

for service items storage of approximately 500 cu ft. 

3. 3. 2. 1. 2 Internal Arrangement (\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 maintenance tasks by the flight crew. Maintainability objectives shall be adhered to in defining internal arrangement and equipment packaging. 

fa 

HANDLING 3-" 

FORM This document contains infotmotio of the United States within the meaning of the Eso.ormge lows. 

SSD AUG 62 20B Title 18, U S C.. Section 793 and 794. the tronuntssoon okenuftsteh. in any .nulsones. to-on -unouthot Ned-petsen .-rs.eluoMbiled by Inn 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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. 

3. 3. 2. 1. 2, 1 Aft Pressurized Compartment (\-4) 

The equipment in the aft pressurized compartment (launch orientation) 

shall be arranged circumferentially onthe vehicle inner wallto accommodate a "head-up" crew position in prelaunch 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 N4) 

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, stowage and operations, 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 Time (\4) 

The Laboratory Vehicle shall provide for a nominal on-orbit stay time for 

a two-man flight crew of at least 30 days, plus a 10 percent reserve. 

'PEC1AL HANDLINP-A4 

• j 

3-54 

1 I-011 this document contains intormai:on affecting the notional defense of the United States within the meaning of the Espionage laws, 

.'lkUG62 20B title 18. U.S C , Section 793 and 794, the itonsonssion of which in any manner to on unauthortzed person is prohthited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

FINAL 

!ma 

PAGr 0OF 52 

DATE 20 Jan 66 

SUPERSEDING 

SPECIFICATION CHANGE NOTiCE 

NO. 1 

1. ECP NO. 

NA 

4. CONTRACT 

Program 632A 

6. EFFECTIVITY 

2. CONTRACT END ITEM NO. 

MOL System 

5. CONTRACTUAL AUTHORITY 

CCN 

3. SPEC. NO. 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-55 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.5 and 3.3.2.2.5.1 

delete and replace with following: 

3.3.2.2.5 COMMUNICATIONS AND DATA PROCESSING REQUIREMENTS 

3.3 .2 .2.5 .1 COMMUNICATIONS 

3.3.2 .2 .5.1 .1 GENERAL NO) 

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. 

laa 

- 

.Thi, document contains information affecting the notional defense of the United Strifes within the meaning of the Espionage 

tows, 

Tolle 18, U.S C.. Section 793 and 794, the transmission of which on any manner 10 an unouthofized person is prohibited by low 
M1)1 1111r, 

10 * ~d F14 

3. 3. 2. 1. 4 Launch Recycle Operatiotig - (Deleted) 

3. 3. 2. 1. 4 Effectiveness (U) 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

rnF 

3. 3. 2. 2. 5. 1 

Laboratory unications and Data Handling shall be compatible 

all make 

_SPECIAL HANDLINa 

Data Handli 

Effectiveness requirements for the Laboratory Vehicle system segment 

are specified in paragraph 3. 1, 3. 1. 2. 2. 

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

3. 3. 2. 2. 1 On-Orbit Maintenance ( -4) 

Critical Laboratory elements shall be designed and arranged to facilitate on-orbit maintenance and repair operations. 

3. 3. 2. 2. 2 On-Orbit Technical Data "r6....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 and maintenance functions, shall be provided in a convenient and easily accessible form and location. 

3. 3. 2. 2. 3 Data Recovery Capsule (4) 

The Laboratory shall be capable of incorporating the necessary equipment for recoverable data capsules aboard any designated flight. The 

capability shall permit: access for placing data into the capsules in 

an environmentally controlled atmosphere; means fOr adjusting and 

measuring any required ballast; means for deploying the capsule without adverse effects on the OV; and means for controlling the attitude 

and time of release. 

3. 3. 2. 2. 4 Outgas sing and Venting (U) 

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. 

FORM.. This document contains information affecting the notional delense 01 the United Slates with7r;74 .;;;eoning of the Esp.feeage laws. SSD AUG 62 20B Title 18. U.S C.. Section 793 and 794, the transmission of which in any manner to on unouthonted person is Proh.bded by low 
SPECIAL NAHT:.:011 

PRELIMINARY SPECIFICATION CHANGE NOTICE g FINAL NO. 1 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

3. SPEC. NO. 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-56 

PAGE 21 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

NIRO APPROVED FOR 

RELEASE 1 JULY 2015 

Paragraph 3 .3 .2 2 .5 2 , 3, and 4 

delete and replace with following: 

Paragraph 3.3.2.2.5.1.2 INTEGRATED TRACKING, TELEMETRY, 

COMMAND, AND VOICE (TTCV) TRANSPONDER S-4) 

The Laboratory shall contain a transponder consisting of a receiver 

and transmitter 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 on-board 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. 

Paragraph 3 .3.2 .2 .5 .1 2 .1 TRACKING (\-4) 

The SGLS-compatible phase coherent transponder shall provide, when 

used with an SCF SGLS ground station, on-orbit vehicle metric tracking 

data having lo-accuracies as follows: 

Range • 50 ft 

Range Rate 0.2 ft/sec 

Angles, Az &El 2 milliradian. 

Paragraph 3.3.2.2.5.1.2.2 PCM TELEMETRY TRANSMISSION Nv4) 

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. 

MAL ;,•:',;:DLINCt 

--CONFIDENAL--- 

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

irtle Io, U.S C., Section 793 and 794. the f of which on any manner to on unauthortzed person is prohibited by low. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

4 

SPECirik. ill/ 

urot‘Ini !AI 

primary use of the USAF Space Ground Link Subsystem (SGLS). The 

Laboratory Communications and Data Handling equipment shall be 

extendable directly, or by modular add-on, to at least the maximum performance limits of the SCF ground configuration specified he rein. 

3.3.2.2.5.2 Integrated Tracking, Telemetry, Command, 

and Voice (TTCV) Transponder 1.€„.4) 

The Laboratory shall contain a transponder consisting of a receiver 

and transmitter 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 on-board stored program controller or manually. The transmitter shall be capable of being energized by the command link, by use 

of the controller, or by manual switching. 

t 

a2C when used with an SCF SGLS ground station, on-orbit vehicle metric 

3.3.2.2.5.3 Tracking 

14T he SGLS-compatible phase coherent transponder shall provide, 

N‘-4) 

tracking data having lax accuracies as follows: 

Range 

Range Rate 

Angles, Az & El 

50 ft 

0. 2 ft/ sec 

2 milliradian 

3.3.2.2.5.4 PCM Telemetry \--4) 

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 

3-56 

This document contains in, ocrnation e 

1) HANDLING 

ense of the. United Since, within the menmng al the Esp,aange laws. 

18. U S C . Section 793 and 794, e transmission of which any mann,.0 no "na"'hngeed "'"" " p"'h'h.ted by iow 

9 
_ LA/I/IL • 1 1/1111JLIIIU 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PAGE 22 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. : 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-57 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3 .3 .2 .2 .5 .5 and 6 

delete and replace with following: 

Paragraph 3.32.2.5.1.2.3 ANALOG TELEMETRYNO) 

The SGLS compatible transmitter shall include, as a pre-flight option, 

a 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. 

Paragraph 3 .3.2 .2 .5 .1 .2 .4 VOICE It1/44) 

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. 

Paragraph 3.3.2.2.5.1.3 375 COMMAND RECEIVER N-4) 

An SCF compatible 375 me command receiver shall be provided as a 

back-up to SGLS 1 kilobit/second commanding. 

Paragraph 3.3.2.2.5.1.4 BACK-UP TELEMETRY TRANSMITTER (U) 

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. 

Paragraph 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. 

• Kit Er SPECIAL Si 's4 L. I NC 

CONFIDENTIAL 

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

Title IS. U.S C., Section 793 and 794. the II0M5111111iptl of which in any manner to on unauthorized person is prohibited by low. 

• 

PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

• 
sILLAkitil. f,ih It L11 t 

3-57 HANDLING 

They document cantons infotrnott ol defense of the United Strifes within the meaning ni the Espionage Laws. 

Lite 18. U S C Section 793 and 794. the iton,m,,seon of which in ony manner to on onfiv person is wnhshoted by 

I 

;1 NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 128 kilobit/sec or lower. The PCM telemeyer shall accept 8 kbit/sec 

mission data on a single input line. A second line from the mission 

module shall he provided for mission module telemetry at a data rate 

of 1 kbit/sec. Telemetry time line analyses shall provide for transmission availability of mission module data on each SCF station pass. 

Laboratory status and housekeeping data at a multiplexed serial rate, 

of 5 - 10 kilobits/sec shall be real time transmitted or recorded, continuously or intermittently, at crew option. Crew and other test data 

shall be intermittently multiplex ed and recorded at rates up to 

128 kilobits/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 capability for vehicle status measurements for a given mission 

shall be greater than 1000. Sampling rates shall extend from 

1 sample per 10 seconds to at least 512 samples per second. High 

level (0 - 5 volts) and low level (0 - 20 millivolts) remote multiplexers shall be used where appropriate from wiring, noise, and 

sampling considerations. 

Secondary PCM telemetry capability shall be provided for critical 

Laboratory Vehicle and mission data. The link shall be compatible 

with an existing SCF receiving subsystem. Data rate for this secondary telemetry shall be approximately 1 kilobit/sec. 

ge6 

The SGLS compatible transmitter shall include, as a pre-fl.t option, 

a subcarrier which can accommodate IRIG FM/FM, M/FM, or 

zG other analog data having a double-sided moth ion bandwidth of 

500 kc/sec or less. 

3. 3. 2. 2. 5. 6 Si nal Coionin• E ment -4) 

Conditioning of Si:s shall be provided for all Laboratory Vehicle 

subsyste as required for interface with PCM telemetry, vehicle 

ti 
HANDLIN 

- AGE 23OF 52 

SUPERSEDING 

ION CHANGE NOTICE DATE 20 Jan 66 

NO. 1. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

El PRELIMINARY 

FINAL 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-58 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraphs 3 .3 .2 .2.5 .7, 8 and 9 

delete and replace with following: 

Paragraph 3.3.2.2.5.1.6 UHF VOICE TRANSCEIVER 1/44) 

A Gemini-type simplex UHF voice Transceiver shall provide back-up 

to the SGLS voice link and shall provide contact capability with nonSGLS ground sites . 

Paragraph 3.3.2.2.5.1.7 VOICE CONTROL AND INTERCOMMUNICATIONS (U) 

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 subsystem shall be broadcast via the intercom. 

Paragraph 3.3.2.2.5.1.8 VOCODERX-4) 

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 compatible with the SCF vocoder type KY-585 and shall comply 

with Federal Spec. 222. 

Paragraph 3.3 .2.2 .5 .1 .9 COMMUNICATION SECURITY X-4) 

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. 

Paragraph 3.32.2 .5 .1 .10 ANTENNAS AND RF (\-4) 

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. 

SPECIALMa 

This document Contains inicgmolion aYeiting The national defense of the United Stares within the meaning of the Espionage Lows, 

Title 113, U.S C., Section 793 and 794, the transmission of which in ony manner to on unauthorized person is prohibited by low. 
s2LGUItiL 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

shall be made for in-flight change of signal conditioner and remote 

multiplexer channels, adjustment of levels and calibration. 

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. Z. Z. 5. 8 Recorders (t\4) 

Magnetic tape recorders shall be provided as follows: 

CONFIDENTIAL 

(a) Voice - Intermittent analog voice re ording 

with total capability in excess of f u r hours. 

Playback shall be at a rate cons stent with 

transmission using the TTCV ransponder, 

500 kc, analog telemetry ch nnel. The 

recorder shall provide for oth manual and 

voice recording control, shall record signals 

for time correlation, d shall contain fast 

data search and retr val features. 

(b) Telemetry Recor• r(s) - Continuous or intermittent recordi g of vehicle status data for a 

total single-c.-nnel recording period of three 

hours minim m; records crew and other test 

data; prov ,es back-up storage capability to 

the miss '•n module recorder; stores keyboard 

encode operational messages; and provides 

inter storage for messages received via 

the omrnand link. The nominal playback rate 

fo stored telemetry is 128 kilobit/sec. Peror-mance 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. 

t 

All recorders hall allow in-flight tape change; magnetic heads and 

other critica components shall be capable of being removed, serviced, and e-installed or replaced. 

3. 3. 2. 2. 9 Command \-4) 

Command data to the mission module, vehicle decoder, vehicle stored 

com and controller, and teleprinter shall be transmitted in the SCF 

ate. 

Tho. document contains infoimation of 

• 7,1e to. U S C.. Section 793 and 794 any manner ,0 •oh.1,,eri 
SPECIAL HANDLING 

PAGE 24OF 52 

DATE 20 Jan 66 

SUPERSEDING 

NIRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

E FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

I. ECP NO. 2. CONTRACT END ITEM NO. 3. SPEC. NO. 

NA MOL System SS -MOL-1 

4. CONTRACT 

Program 632A 

6. EFFECTIVITY 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-59 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.5.10, 11, and 12 

Delete and replace with following: 

Paragraph 3 .3 .2 .2 .5 .2 DATA MANAGEMENT 

Paragraph 3 .3 .2 .2 .5 .2 .1 COMMAND l'ISs-4) 

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 be provided by the 

vehicle computer . A decoder shall provide real-time command back-up to 

the computer . 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 . 

Paragraph 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 

telemetering 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 ever-or-under voltage, turn ON or OFF, 

or other transient power cdnditions 

Paragraph 3.3.22 .5.2 .1.2 COMMAND CONTROLLER \ -4) 

The controller provides switching functions for various vehicle equipments. 

Solid state type switching of both latching and non-latching types shall be 

employed as required. The controller circuitry shall incorporate manual 

reset and override 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. 

Paragraph 3 .3.2.2 .5 2 .1 .3 TELEPRINTER (U) 

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/ rrvodule compute i 

or tape recorder. .

i 

1:- . +a , • 4 

.s1.\,[c; i r, 

-This document contains infoimotion al fecting the nononol defense of the United Stoles within the meaning of the Espionage Laws, 

Title I8. U.S C.. Section 793 and 794, the I rons,,suon of which in any manner to on unauthorized person is ptohibded by low. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SECRET .OrtlikiL 

CONFID[NTIAL 

omma ys eni 

An SCF compatible 375 Mc command receiver shell be provided as 

back-up to SGLS 1 kbit/see commanding. 

3. 3. 2. 2. 5. 11 Command Decoder4) 

An SGLS-compatible command decoder shall be provided t .t is capable 

of accepting and handling comet n rid words from the tran- onder in the 

SCF trinary format at a bit rate of 1000 per sec. Th decoder shall 

perform command validity cheeks and logic/decodi operations, provide clear command function bits and magnitude is via an output 

register, and generate command outputs to dri e external relays or 

pulse circuits. The decoder shall have a mi mum of 32 separate 

command outputs, seven of which are spec'al commands requiring an 

externally generated signal for comman execution in order to allow 

command format change for continuou data reception or for use with 

additional decoders. Indications of eommand message validity checks, 

the decoded function bits, and rec ipt of an execute signal shall be 

provided as an output for telem- ry relay to the ground. Power to the 

command decoder shall be co rolled by internal logic, by a 

programer/controller, or anually. No false command execution 

outputs shall result from •ver-or-under voltage, turn ON or OFF, or 

other voltage transient onditions. 

-A and A-to-D Converters (Deleted) 

vehicle Stored Command Controller 4) 

3. 3. 2. 2. 5.12 

3. 3. 2. 2. 5. 12 

The The vehicle sto ed command controller shall provide sequencing of the 

majority of v isle equipments and events. The controller stores and 

provides ac uation for up to 64 events resulting in independent double 

pole -dou e throw type switching of 24 selectable functions or channels 

timed i 1-sec increments for duration of 0-12 hr. Verification of 

recei of vehicle-stored commands shall be provided via the real-time 

Lab• ratory Vehicle status telemetry. Means shall be provided for 

ual inhibit/override functions. A means for read-out of stored 

d 

3-59 

This document cumnins onloonotlon 

Tole 18. U S C . Section 777 and 7 

e Stotts wit P ESIAOPIOye tows. 

which in any monne• Po on unolot.00red otosnn is po,tuboed by lo.... 
CIAL HANDLING. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE 25 52 

DATE 20 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MO L-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-60 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraphs 3 .3 .2 .2.5 .13, 14, 15, and 16 

Delete and replace with following: 

Paragraph 3.3.2.2.5.2.2 DATA ACQUISITION 

Paragraph 3.3.2.2.5.2.2.1 PCM TELEMETRY 'kc.4) 

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 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 on 

a single input line . 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 serial 

bit stream having a data rate of 5-10 kb/second which shall be real-time 

transmitted 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 la kb/sec for variable duration g. 

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 volts) and 

low-level (0-20 millivolts) remote multiplexers shall be used where appropriate 

from wiring, noise, and sampling considerations. 

Paragraph 3 .3 .2 .2 .5 .2.2.2 ANALOG TELEMETRY (U) 

IRIG subcarrier oscillators, frequency multiplexers, etc. , shall be provided as 

required to accommodate wideband instrumentation sensors such as vibration 

tbrAr_tWIDLING es 

pickups required for Or ital Vehicle 

C - I 8 

I Os' 

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

Tole IS. U.S C Section 793 and 794. the nonsmussion of which in any manner to on unauthorized person is prohibited by low. 
NROAPPROVED.FOR 

RELEASE J ' JULY 2015 

• 0 PRELIMINARY 

FINAL 

TATION CHANGE NOTICE 

NO. 2 

PAGE _12 OF 62 

DATE 15 Marrh F.)(1 

SUPERSEDING 

HANDLING 

1.4 

kj 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-J. 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-60 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.5.2.2.1 PCM Telemetry 

sixth sentence to read: Orbiting Vehicle status 

and housekeeping data at a multiplexed serial rate 

of 5-10 kilobits/sec shall be real time transmitted 

or recorded, continuously or intermittently, at 

crew option. 

Add as the third paragraph: The Laboratory PCM telemetry 

shall accept serial 5.12 kilobits/sec from the 

Gemini B during the on-orbit phase of the mission. 

Telemetry time line analyses shall provide for 

transmission availability of Mission Module and 

Gemini B data on each SCF station pass. 

Change 

4 

. • I 

.% 

it! ILA . hill.. • 

• 

• 

z1 

7 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

__SEE-Rit-4atritiL rittiluuma 

CONFIMITIAL - 

Teleprinter (U) 

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, or the telemetry tape recorder. 

3.3.2.2.5.14 Voice (U) 

The TTCV transponder shall provide the primary Laborato -ground 

voice link capability. In addition, a Gemini-type simplex HF voice

) transceiver shall provide voice contact with non-SGLS round sites. 

) Each set of voice receiving and transmitting equipm= t is controlled 

ao. by the voice master control panels, two or three r mote control panels, 

and individual crew controls. It shall be possib e for both crewmen to 

have simultaneous voice communications with ground. The aural 

alarm(s) of the monitor and alarm subsyste are broadcast via the 

intercom. 

3. 3. 2. 2. 5. 15 Vocoder X- 4) 

A vocoder shall provide voice transmission and reception via the TTCV 

transponder at the digital data r. e of 2400 bits/sec, The vocoder 

shall be compatible with the S vocoder type KY-585 and shall comply 

with Fed. Spec. 222. 

3.3.2.2.5.16 Vehicle/ onitor and Alarm 1.6.,,,-4) 

The vehicle monitor a d alarm subsystem shall be capable of continuously monirotin or sampling approximately 150 critical vehicle 

subsystem param ters concerned with crew safety and with functions 

whose failure wjDuld jeopardize the mission. Points monitored shall 

be predicated/on a maximum space-ground contact gap of 6 hr. 

/

Offnominal pe.tformance which can persist for more than 6 hr shall be 

diagnosefd on the ground. Sampling rates range from approximately 

1 sample/sec and 1 sample/10 sec, as required. Both aural and 

visual signalling shall be provided for out-of-tolerance conditions. 

Appr . t toleran 

3-60 

Nis document contoinsinforrnotion oil 

Idle 1 U S C. Section 793 and 794, 1 

enie o e nded totes wit. GIso.onage Lows. 

ch to ony manner to on unauthorized person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

_sEeRETVECIAL HANDLING 

CONFIDENTIAL 

PAGE 27 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-61 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3 .3 .2.2 .5 .2 .3 TIMING -4) 

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. Initialization or up-date of the timing logic shall be 

accomplished via command (primary) or manually. -Displays shall include 

Greenwich Mean Time (GMT), vehicle elapsed tim (VET), vehicle ground 

time difference (AT), mission module synchroniz ion indication, two event 

elapsed time (EET) channels, and a mechanical cock. 

Scni 

a g 

--SERET-SPECIAL 

CONFIDENTIAL 

.11,s document contains information olleCting the notional defense of the United Stoles within the meaning of the Espionage Lows. 

T,tle I S C , Section 793 and 794, the tronsmission of which in oily rno,,,, no 00 unouthoilzed Pelson is Piablb.fcd by fol., 

• PRELIMINARY SPECIFICATION CHANGE NOTICE 

0 FINAL NO. 1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

erma-SFECIAL HANDLING, 

--C-041fiefftatt-- 

• PRELIMINARY 

J FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE 26 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-61 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.5.17, 18, 19, 20, and 21 

Delete and replace with following: 

Paragraph 3.3.2.2.5.2.2.3 FORMAT SELECTION EQUIPMENT g *(Ss4) 

The PCM main multiplexer design shall provide in-flight selection of any one of 

several pre-flight prepared digital telemetry formats and data rates . 

Paragraph 3 .3 .2 .2 .5 .2 .2 .4 RECORDERS Ns-4) 

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, 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 Recordert.s4,-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; provides 

interim storage for messages received via the command link. 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, bidirectional 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. 

ti 0• 

ING 

COMOTIAL 

Thi, document contains information affecting the notional defense of the United Stoles within the meaning of the Espionage Lows. 

1,11e 18, U S C.. Section 793 and 794. the teontreission of which in any mom,. to on unauthottled person is prohibited by law. 
HANDLING 3-61 

me of the United Slates within the meaning of the Espionage Lows. 

of which .n any manner to on unouthonted person 15 wohibited by low 

This document contains Informal, 

Title 113. U S C Section 793 and 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

ii

e 

SPECIAL HANDLIkG NFIDENTIALor rapid crew action is required when certain (approx. 50) of the to 

points are out of tolerance. Manual override and reset features 

be incorporated. Design shall provide for modular expansion. 

3.3.2.2.5.17 Timing 

F. 

The timing subsystem shall provide time signal generat n for data 

handling equipment, synchronization and control, ti • correlation of 

data, two channel event timing, time words for ve eicle stored command controller, and time displays. Clock syne ronization shall be 

manually selectable from either an external internal signal source. 

The internal clock shall have a time refer ce stability of 10

-7 

per 

30 days or better. Initialization or up- to of the timing logic shall 

be accomplished via command (primary) or manually. Displays shall 

include Greenwich Mean Time (GMT), vehicle elapsed time (VET), 

vehicle ground time difference (a), mission module synchronization 

indication, two selected vehic command controller event elapsed 

time (EET), stopwatch, and a mechanical clock. 

3.3.2. Z. 5.18 Video/(Deleted) 

3.3.2.2.5.19 Mission Information System (Deleted) 

3.3.2.2.5.20 • bital Naviaation (Deleted) 

3.3.2.2.5.20 Wideband Data Transmitter 15.4) 

A wideband d transmitter shall be provided capable of transmitting 

digital data a rates as high as 20 megabit/sec. The transmitter shall 

be of the tr veling wave tube type and shall operate in the 2200-2300 

Mc RF ba d. Modulation, specific frequencies, frequency stability, 

and othe technical characteristics shall be compatible with the SCF 

S -ban wideband data link. 

3.3. • . 2.5.21 Antenna and RF 

Th= antenna and RF subsystem shall consist of the TTCV transponder,_ 

wideband data (S-band), UHF voice and command, and secondary PCM I 

d their as o 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ECIAL HANDLING 

PAGE 30 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -62 

6. EFFECTIVITY 

MOL Program 

7. TEXT CI-IANGE 

Add following Paragraphs: 

Paragraph 3.3.2.2.5.3.3 DISPLAYS AND CONTROLS (U) 

Provision shall be made for selection and operation of normal control 

and backup 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. 

Paragraph 3.3.2.2.5.3.4 MONITOR/ALARM \-4) 

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. 

bLiNG 

.Tb.s document contains infortootion affecting the notional defense of theUnited 5tores within the meaning 01 the Espionage tows. 

Title to. U.S C Section 793 and 79e. the transmission of which on any manner to on unauthorized person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

sERET SPECIAL HANDLING. 

PRELIMINARY 

Es FINAL 

UNCLASSIFIED 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE 19_ OF 52 

DATE 20 Jan AA 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-62 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

ADD the following paragraphs: 

Paragraph 3.3.2.2.5.2.4.4 DISPLAY AND CONTROL (U) 

The display and control unit provided with each computer subsystem 

shall provide all necessary capability for entering or requesting data 

from the computer, and shall provide all necessary capability for flight 

crew control of the computer subsystem. 1 

$1.30 

Paragraph 3.3.2.2.5.2.4.5 EXTERNAL STORAGE (U) 

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. 

6 

31'G' 

Paragraph 3.3.2.2.5.2.4.1 SOFTWARE (U) 

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 fac- litating 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. 

in.ica or 

rParagraph 3.3.2.2.5.3 INSTRUMENTATION AND DISPLAY (U) 

Paragraph 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. 

Paragraph 3.3.2.2.5.3.2 SIGNAL CONDITIONING (U) 

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. 

i sYvi 

Li Li a ij _ • _ 
PAGE 28 OF 52 

ECIAL HANDLING 

UNCLASSIFIED 

SPECIFICATION CHANGE NOTICE 

O. 1 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 PRELIMINARY 

® FINAL 

DATE 20 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -62 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraphs 3.3.2.2.5.22 and 23 

delete and replace with following: 

Paragraph 3.3.2.2.5.2.4 DATA COMPUTATION 

Paragraph 3.3.2.2.5.2.4.1 COMPUTER HARDWARE (U) 

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 subsystems. It shall also provide the capability 

for performing command functions required to be initiated manually by 

the flight crew through the computer control unit, 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 Payload and Laboratory 

operation while utilizing only one of the computers and its associated 

peripheral units. 

Paragraph 3.3.2.2.5.2.4.2 COMPUTER SUBSYSTEM CONTROL UNIT (U) 

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. 

Paragraph 3.3.2.2.5.2.4.3 DATA ADAPTER UNITS (U) 

The data adapter units shall provide all necessary signal conditioning, 

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 payload. Redundancy shall be 

provided for the two types of data adapter units, and each unit shall be 

capable of interfacing with either computer. 

UNCLASSIFIED 

err, r. t Y flfI 
• 1 

cakri.)11EitilcDLING NROAPP.ROVEDFOR 

RELEASE 1 JULY 2015 

• 0 PRELIMINARY 

FINAL 

Stu-it 

SPECIFICATION CHANGE NOTICE 

NO. 2 

PAGE 18 oF 62 

DATE li March 66 

SUPERSEDING 

I 

I 

I. ECP NO. 

NA 

2. 

• 

CONTRACT END ITEM NO. 

MOT, aystem 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-62 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3 .3.2.2.5.3.2 Signal Conditioning EquipmentNc4) 

Change first sentence to read: Conditioning of signals 

shall be provided for all Orbiting Vehicle subsystems as required for interface with PCM telemetry, 

vehicle displays, and the vehicle monitor and 

alarm subsystem. 

4 

•1ECREPPECIAL ECDLING, 

• COV.FIDENTiA[ 

r•-, a • ° 

c • 

t • 
FINAL NO. 3 

1. EC? NO. 2. CONTRACT END ITEM NO.. 

NA MOT, System 

4. CONTRACT 

Proc.ram 632A 

5. CONTRACTUAL AUTHORITY 

cc.: 

6 EFFECTIVITY 

SUPERSEDING 

I 3. SPEC. NO. 

I SS-VOL-I 

PILE OPPOSITE SPEC-PAGE NO. 

SSS-2.33-1 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

o PRELIMINARY 

L:'‘) L. v. • ;,; .4 .; 

12 .OF 2.-7, 

SPECIFICATM CHANGE: 01.1C...;a DATE 2 Arr"11 10^4. 

--...22/1.42.:CagnaM 

7. TEXT CHANGE 

SCN #1 

Paragraph 3.3.2.2.5.2.3 Timing 

Change last sentence to read as follows: 

"Displays shall include Greenwich Mean Time (GMT), vehicle elapsed time 

(VET), vehicle and ground time difference (LAT), mission module synchronization indication, two event elapsed time (EET) channels, and a 

mecnanical clock." , 

Paragraph 3.3.2.2.5.2.4.4 Display and Control (U) 

Delete the seccd sentence: 

The computer display panel shall consist of all indicators and lights 

necessary for non-textual communications between the computer and the 

flight crew." 

Paragraph 3.3.2.2.5.2.4.5 Software (U) 

Change paragraph number to read: 

Paragraph 3.3.2.2.5.2.4.6 
JAL HANDLING 

CONFIDENTIAt 

4 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

t 

selection and AGE use. The TTCV and UHF antenna system shal 

provide, at crew option, spherical or directive radiation co rage. 

The wideband data antenna shall provide earth coveraen the 

spacecraft is orbiting in its nominal attitude. e TTCV transponder 

I antenna system shall be capable of use du g launch. 

143.3.2.2. 5.22 Laborator Vehi e Controls and Dis a (U) 

Provision shall be made for lection and operation of normal control 

and back-up modes as ap• 'cable for all vehicle subsystems. Displays 

shall include vehicle system status and mode displays, those 

displays directly associated with subsystem control and operation, 

and certain cri cal parameter displays. 

3. 3. 2. 2. 5. 3 Laboratory Vehicle Computation (U) 

Comp tion capability including associated software shall be provided 

to eet the needs of data conversion, monitoring, control, and other 

f 

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

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

The Environmental Control and Life Support (EC/LS) subsystem shall 

consist of the following functional areas: 

(a) Atmosphere Control 

(b) Thermal Control 

(c) Food Management 

(d) Water Management 

(e) Waste Management 

(f) Personal Hygiene 

The specific requirements for each of the above functional areas are 

given below, together with the over-all requirements for the complete 

subsystem. --sEgR OPECIAL HANDLING' 

3-62 

This document contains information affecting the notional defense of the United Slates 'AIM,. the meaning at the Espionage Lows, 

Title 18. U S.0 , Section 793 and 794, the transmission of which in any manner to an unauthorized person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

rn FINAL 

I 

TION CHANGE NOTICE 

2 

PAGE 19 OF 62 

DATE 15 MnrCh AA 

NO. SUPERSEDING 

UNCLASSIRED 

PECIAL HANDLING 

1. ECP NO. 

Nk 

2. CONTRACT END ITEM NO. 

MOT, rgi- pn 

3. SPEC. NO. 

SS-MOL-1 

1. CONTRACT 

. _ 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-63 

6. EFFECTIVITY 

M2L Program • 

7. TEXT CHANGE 

Paragraph 3.3.2.2.6.2.1 General (U) 

Change last sentence to read: Means shall be provided to support 

extra-vehicular activities, as defined in paragraph 3.3.5.1.4 

and 3.3.1.2.7.3 and pressurization of the Gemini B as defined 

in paragraph 3.3.3.2.4.1 and 3.3.1.2.6.3. 
C AL HANDLING 

• 

so' 

'4 

3-63 

C Of ,he Un ee lifity .4 ti 8 h e Espoonoge 1.434N, 

which in any manner to On unnuthoitted Orson if P.Oh•h.f,.d by la* 

Thts document contains inforrnotion 

litle 18, U S C . Section 793 and 794 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 2. 2. 6. 2 Atmo trol 

/r .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. Z Atmosphere Pressure and Composition \-4) 

The atmosphere control provisions shall afford the inherent capability 

to 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. r • 
1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3r-A4 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

MAME) 

Paragraph 3.3.2.2.6.2.4 Shirtsleeve Environment Ns4) 

Change to read:. Shirtsleeve Environment (U) 

HANDLING 

• SPECIFICATION CHANGE NOTICE 

NO. 2 

NRO APPROVED FOR 

RELEASE ,1 JULY 2015 

0 PRELIMINARY 

FINAL 

get h 

ra 

PAGE 20 OF 62 

DATE 15 March 66 

S UPERSEDING 
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CONFIDENTIAL 

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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. 

,2C 3. 3. 2. 2. 6. 2. 4 Temperature Control (Deleted) 

if.p4. • 

3. 3. 2. 2. 6. 2. 4 Shirtsleeve Environment N4) 

An environment shall be provided that will result in physiological 

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 atmospheric composition, and elimination 

of natural convection. An optimum balance of atmospheric temperature, ventilation velocity, water vapor, partial-pressure, and mean 

radiant temperature shall be established and maintained. Provisions 

for the control of shirtsleeve environment, based on nominal metabolicloadings (in the region of 400 to 800 BTU/hr) shall not require 

the utilization of active thermal cooling garments. 

3. 3. 2. 2. 6. 2. 5 Atmosphere Storage Requirements X-4) 

Atmosphere storage shall be based on the following tiquireinntg: 

(1) Oxygen to provide for crew metabolic requirements 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 pressu • 11 td section 

SEECIAL HANDL! 

3-64 

Mit document Contains information affecting the notional defense of the United Stores within the meaning of the Espionage tows, 

• tole IS. U.S.0 • Section 703 and 704, the transmission of which in any monner to on unauthorized person is prohibited by low 
SSS-233-1 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

FINAL. 

SPECF-1CAT:ON OF,Aiv,C,E 

NC. 3 

........ . • - __ : . • - • 2. CONTRACT END ITEM NO. ! 3. ;,-.-EC. NO. 

i 

MOL System 

5. CONTRACTUAL AUTHORITY 1 FILE OPPOSITE SPEC. PAGE NO. 

coN # 

i 

1 3-65 

NA 

4. CONTRACT 

Program 632. 

6. EFFECTIVITY 

mcd. Frocm. 

7. TEXT CHANGE 

Paragraph 3.3.2.2_6.2.7 Carbon Dioxide Control(V) 

Change second sentence to read: 

"...within- 5 (n-3) mm Hg. 

Change third sentence to read: 

%..15 mm Hg for 12 hr. 

• 
• F y 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

; 1 he 

akr 

(including carbon dioxide desorption losses), 

One complete repressurization of the pressurized 

section, and a number of repressurizations as 

required of the pressurized compartment used 

for extravehicular egress. 

(4) Oxygen as required to provide for the support 

of extravehicular operations. 

The above requirements do not include allowances that may be f 

necessary for storage purge and leakage. 

3.3.3.2.6.2.6 Oxygen and Diluent Storage l‘S-4) 

The EC/LS oxygen requirements shall be integrated 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 11S-4) 

A regenerable adsorbent system shall be.used for carbon dioxide 

control. The environmental control system shall maintain nominal 

SY#3) 

carbon dioxide levels within 45E7 mm Hg. The emergency carbon 

dioxide level shall not exceed 15 mm Hg for hr. 

3.3.2.2.6.2.8 Odor and Contaminant Control \-4) 

Equipment shall be provided for the control of odor and trace gases. 

Atmospheric debris traps shall be provided. 

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. 

3-65 

This document (onion,' onforrnotron affecting the notional defense of the United Stoles within the rneonrng of the f soronage tows. 

Title IS, U S C . Section 703 and 794 the transmission of which to any monner to on unouthotored person is prohrbrted by Inv. 
' • • • 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

!•-•, r, rt, 

• : 

Lc-3 PRELIMINARY S 

0 FINAL 

FI C.4; N 

NO. 3 

?AG-L .14 op 25 

DATE 2 ri. 1966. 

SSIDNC 

1 . ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPLC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

CON # 3 -66 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE • 

Paragraph 3.3.2,2.6.2.1.0 Renressarization 

Change the last sentence to read: 

"- ...transfer tunnel to the 5.0 psi level specified... 

7 7 

• \:•!. 
CO L HANDLING 

This document contains information affecting the notional defense of the United Slates within the meaning of the f soionage 

Title 18, U S C . Section 793 and 794, the trons,,,ron of which in any manner to an unovit,,,,d person is n•,h,h.ted by 

I 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

1. 

tl 

Positive control s a be exercised to identify contaminants, their 

sources, and to minimize their introduction into the Laboratory 

atmosphere. 

3. 3. 2. 2. 6. 2. 9 Pressure Maintenance \-4) 

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 (\ -4) 

Repressurization time for either pressurized compartment to a level 

that provides 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. 

e, se..) 

'7°71°4-64 

eye

,1-77 

0. 

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. 1. 2. 1 and 3. 3. 2. 2. 11. 
SPECIF ATION CHANGE NOTICE 

NO. 2 

2. CONTRACT END ITEM NO. 

PACE 21 OF 62 

DATE 15 Mirrh (41 

SUPERSEDING 

3. SPEC. NO. 

NRO APPROVED FOR 

,RELEASE.1 JULY 2015 

PRELIMINARY 

FINAL 

I. ECP NO. 

NA 

4. CONTRACT 

Program 632 A 

5. EFFECTIVITY 

ROL Program 

MOL System 

5. CONTRACTUAL AUTHORITY 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-67 

-SPEC#11 

/Wee 

UNCLASSIFIED 

7. TEXT CHANGE 

Paragraph 3.3.2.2.6.4 Food Management Nc4) 

Change to read: Food Management (U) 

if 

!r 
r.1 

-4 

NRO APPROVED FOR 

--ablitirSPECIAL HANDLINU 

RELEASE 1 JULY 2015 

-1111tFtERIAt-- 

3. 3. 2. 2. 6. 3. 2 Space Radiator 14) 

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 shall 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 

shall 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 presurized 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 

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 

h. 

a. 

g. 

r. 

iF 

t. 

4- 

fr 

3-67 

Ms document contains onfoirnotiok_otiricj Pliimre491 defen t the United States a.iFm tte meaning of the I trii,nocje tn.*, 

T.t le 18, U S C , Section 793 and 794, the 1.trttmtss.on of which in any manner to an wnourhorf red pe■ son is prbhihired by i to 
PAGE 22or 62 

DATE 15 Mnrrh bh 

iPHRANDLING 

SPECIFIC TION CHANGE NOTICE 

NO. 2 SUPERSEDING 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-68 

Paragraph 3.3.2.2.6.5 Water Management 4) 

Change to read: Water Management (U) 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

FINAL 

I. CCP NO. 

NA 

4. CONTRACT 

Program 632 A 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 
NRO APPROVED FOR 

4 RELEASE 1 JULY 2015 

exceed 0-100° F) and s a e such as to protect the food supply from 

ECIAL HANDLING 

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. 

Water Management (o) 

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 (U) 

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 HANDUNG 

Ms document contains informati al defense of the United Stores within the meaning of the Espionage Laws 

Inle 18. U.S C Section 793 and 794. the Ironsmna. •1 which in any manner to on unauthorized person is at ohihited by 
I 

N.R0 APPROVED FOR 

RELEASE.1 JULY 2015 

PRELIMINARY 

[Z] FINAL 

PAGE 23 OF 62 

DATE 15 March 66 

SUPERSEDING 

HANDLING 

ECIFICATION CHANGE NOTICE 

NO. 2 

L ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Proffram632 A ' 

5. CONTRACTUAL AUTHORITY . FILE OPPOSITE SPEC. PAGE NO. 

3-69 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.6.8.2 Launch and Ascent Operations (U) 

Change to read: The atmosphere of the pressurized section, including 

the transfer tunnel, shall be relieved during ascent to maintain 

a pressure differential compatible with the specified orbital 

requirement. 
4 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRE-T-- SPECIAL HANDLING 

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 an devices used by the crew for skin 

cleansing, oral hygiene, shaving, and hair and nail cutting, as required. 

Proper provisions shall he 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 (U) 

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 

SPECIAL HANDLIANiC1 
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RELEASE 1 JULY 2015 --S-ERET- SPECIAL HANDLING 

sr 

3.3.2.2.7 Attitude Control and Translation System (ACTS) 

3.3.2.2.7.1 General \-4) 

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 -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 preplanned or reprogrammed for 

degraded on-orbit operation. 

3.3.2.2.7.2.1 Operating Modes(-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 single axis 

maneuver s. 

`1EC-REL SPECIAL HIASIDLING 

This document contains information alfechng the nalronni defense of the United Stoles within the mennmg of the Fsp.onage la.s. 

title 18, U S C., Section 793 and 794, the transmission of which in ony manner io an unnoh."Tr-T1 person is prohibited by law 

• 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ff.ggELSPECIAL HANDLING 

PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

31 52 PAGE --..... OF 

DATE 20 Jan—g-6-------emSUPERSEDING 

I. ECP NO. 

NA 

 2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL -1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -71 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.7.2.1 \.3 SAR) 

Add items (i) and (j) as follows: 

(i) Vertical Acquisition Mode - shall provide automatic 

acquisition of the local vertical. 

Automatic AV Termination Mode - shall provide automatic 

initiation and termination of velocity changes in the 

x direction. 

SPECIAL ACCESS REQUIRED 

4 SENSITIVE AR 

PROGRAM NO. G IDENTITTAT. 

IteREOETAL HAP 

.This document COMO."s information affecting the national &Ism. 01 the United Stoles within the meaning of the Espionage Laws, 

Title IE, U.S C., Section 793 and 794, the tionscriission of which in any manner to on vnouthortzed person is pcohibtted by low 

(j ) 
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I RELEASE 1 JULY 2015 

4 • 

14 

L HANDLING 

(d) Rate Stabilization Mode - shall provide for 

automatic d,,rnping of vehicle rates and for 

rate maneuvers controlled manually or by 

command from other subsystems. Manual 

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. 

AV Mode - shall provide acceleration in the 

x direction. 

(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 

maneuver s. 

(f ) 

tk„. 56711/44-/, „20 

Csd 

3.3.2.2.7.2.2 Rate Control OperationN3 SAR) 

Provisions shall be incorporated into the system for automatically 

maintaining 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 Deadband Ny 3 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 X-4) 

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. 

q.0 

--stefiff___S2ECIAL 

.This document contours Information effecting the national defense of the United States within Ite meaning of the Fsaiannrje 

Title 18, U S C Section 793 and 794, the imnsrnission of which in any manner to an unauthorized person is prohibited by 10. 
4 NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3 

•

4. 

3.3.2.2.7.2.5 Operating Life 1C44-4) 

The ACTS shall be capable of continuous operation in any of the operating modes at any time during the mission. Propellant and thrust 

chamber requirements shall be based upon the operational mission 

profile. 

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 following accuracies are specified as the maximum (3-a.) 

deviations for the given parameter. 

(1) Vehicle Attitude Reference - In the Local 

Vertical/Orbit Plane mode, the angular deviation of the pitch or roll reference signals from 

the local vertical shall not exceed ±0. 3 deg 

and the angular deviation of the yaw reference 

signal from the orbit plane shall not exceed 

±0.35 deg. 

In the Local Vertical/Relative Velocity Vector 

mode the angular deviations of the pitch or 

roll reference signals from the local vertical 

shall not exceed ±0. 3 deg and the angular 

deviations of the yaw reference signal from 

the relative velocity vector shall not exceed 

±0.45 deg. 

In the Inertial Attitude Hold mode the body 

axis rate signal deviations shall not exceed 

three deg per hour. 

071,— (1,1,1 11 • 

3-72 

r n Nk.:41 &J., b 

This document contain, ,afa,rnar,an affecting the national defense of the United Stoles within the meaning of the Espionage laws. 

Tole 18. U S C.. Section 797 and 794, the ttonsmission of which in any moon,' to on unowthoaied person is prohibited by low 

Stefig— SPECIAL HANDLING 
IRIANDLING,m: 21t March 

NO. SUPERSEDING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• • 

PRELIMINARY 

E] FINAL 

1. ECP NO. 2. CONTRACT END ITEM NO. 3. SPEC. NO. 

NA MOL System SS-MOL-1 

4. CONTRACT 5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-73 Program 632 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.7.6 Gemini B Interfaces N4) 

Change to read: It shall be possible to control the ACTS from 

. the Gemini B. 

tg 

•1 

SPECIAL ik;iisi;LING 
• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 SIIIRETSPECIAL HANDLING 

A 

21 

(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. 

(3) 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 control operation, control logic 

shall be provided to prevent the body axis 

rates exceeding ±0.005 deg/sec for long periods of time. 

3.3.2.2.7.5 Performance Requirements SAR) 

Translational Acceleration - The unidirectional 

translational acceleration shall be greater than 

0.40 ft/ sect in the positive x direction. 

3.3.2.2.7.6 Gemini B Interfaces N_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. 

-IfeRE.01ECIAL 3-73 

•This document contains intormotion olfectingthe national defense of the United States within the meaning of the Espionage tows. 

'Title 18, U.S C.. Section 793 and 794, the ,ronsrmssion of which tn any manner to on unouthn,:ed person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HAN OLEEL. The Gemini B referen en) ,irld displays shall oeucLi.L4Lor 

CUNfID 11,,t/IAL ANDLING 

Thos docsonent contoons nosier/nation a ffecting the Irti no sr 0 the note Stotes on the rneontng 01 the woronno.je Lows. 

Tole 18, U.S C Sech on 793 cod 794, thor-sgansnlii h■ rh on any manner to an 0nouth000,ed peeton ponhoh,ed by law 

3-74 

:I§ 

visual reference but OrN1-1-not be-trrtegrated with the ACTS electronics 

located in the Laboratory Vehi( le. 

3. 3. 2. 2. 7. 7 Control Electronics Subsystem 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 pro% isle translational velocity changes 

while in orbit. 

3. 3. 2. 2. 7. 7. 1 Reference Element \-4) 

This element shall contain the horizon sensors, gyros, and accelerometers necessary to provide vehicle linear acceleration, attitude, and 

angular rate sensing. It shall also include any other equipment necessary 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 

IDeleted, 

3. 3. 2. 2. 7. 8 Propulsion SubsystemNc4) 

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 Life \-4) 

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 
k. 

A 

c. 

e - 

rNRO APPROVED FOR 

RELEASE 1 JULY 2015 SEC-RE-I-SPECIAL HANDLING 

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 Gaging (-4) 

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 No) 

The propellants shall be hypergolic bipropellants which are spacestorable and shall be selected with consideration of thermal environment, minimization of ignition over-pressure transients, and the 

thrust chamber assembly selection. 

The longitudinal translational velocity increment (AV) shall be 475 

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. 

Dual sets of tanks for fuel and oxidizer shall be provided. Crossfeed provisions shall be incorporated. 

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 Source (U) 

The generation of primary electrical power for the CPS shall be 

SPEW HARM 

3-7•5 

FORM This document contains information of feeling the nationol defense of the United Stotes within the meaning of the Esponage Lows. 

SSD AUG 62 20B Title 18, U.S C., Section 793 and 794, the tronsmission of which in any monner to on unauthorized person $s proh.boed by law 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

rt L HANDLING 

accomplished with H2 ue cell modules arranged in parallel, with 

automatic and manually actuated interconnections. 

3-76 

FORM This document contains information a 142si 

=,,SSD AUG 62 208 Title 18, U.S.C., Section 793 and 794,4/ye...Lao 

NDLING 

efense of the fired States within the meaning of the Espionage Laws. 

h in ony manner to on unouihoi, zed person is prohibited by 10 

3.3.2.2.8.1.2 Nominal Power \-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 (-4) 

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 

1 ••""", 

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 (c4) 

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 (4) 

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 (\-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 1.8 kw of power required to be delivered by the 

power plant for the CPS loads. 
UNCL SWEIAL HANDLING 

NRO APRROVED FOR 

RELEASE 1 JULY 2015 

0 PRELIMINARY 

Ej FINAL 

SPECIAL HANDLING 

UNCLASSIFIED 

SPECIFICATION CHANGE NOTICE 

NO. 1 

pAGE 32 Gp 52 

DATE r0 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -77 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.8.2.10 POWER SOURCE FAILURE (U) 

Delete third sentence beginning with "Start up of cold 

redundant 
SSS-233-i 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

17 PRELIMINARY 

LL INA' NO. 3 INC 

cp No. 2. CONT:iACT END ITEM N. 

W/A Mal, System 

CONTI-tAC.7: . ; 5. CONT:-iACTUAL AUT:-10:;:ITY '-ILE OPPOSITE U. PACE * 

Prog.r.,.im 632A 

6.'ECTIVITY 

YOL PrograM 

7. TEXT CHANCE 

Parag--aph 3.3,22.8.2.6 Voltage \-4) 

Change to read: 

"During the mission ohases„ and for all coZoinations• of loading Tithi 

the mission power profile, including emerencies, the Dower sources 

shall maintain 25-31 volts at the bus and 24-31 Volts at the NPSSAVSS 

power interface." 

SP7-CC.A.MON 

PAOLL15_:OF_15— 

25 r."12,.71c)0.0 

e-'7" •. L 4' 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 3. 3. 2. 2. 8. 2. 5 Emergency Power v.4) 

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 )1S-1) 

During the mission phases. and f or all combinations of loading within 

the mission power profile, including emergencies, the power sources 

shall maintain 25-31 volts at the bus. 

3. 3. 2, 2. 8. 2. 7 Specific Reactant Consumption IV) 

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 

fuel cell. 

as potable 

transport system shall remove the product water from the 

The water shall be delivered to the life support interface 

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 cir - 

culating 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 

HANDLING, 3-77 

FORM rh.% document eontoins teforrnoli I defense of the United Scotts within ,he rneomng of the f.sninnore SSD AUG 62 20B f ■ tle 18, U C.. Secn0n 793 and 794, the tronstnission of which in on manner to no person .% PI,,b.I'•'Yt•I by inn 
NI10 APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

El FINAL 

icikt4 

UNCLASSIFIED 

SPECIFICATION CHANGE NOTICE 

NO. 1 

33 52 PAGE OF 

DATE 20 Jan 66 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -78 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.32.2.8.3 POWER CONTROL AND MONITORING (U) 

Delete first paragraph and replace with following: 

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. 

UNCLASSIFIED 

I'm SPECIAL HANDLIE LU 
PECIN. 1„ I , 

3-78 

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. 

j C4'" ==1:±nictilttziensi: Individual control of each module shall allow selec (se) 6 rj" tive grouping of any combination of fuel cell modules. 

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 on-orbit 

storage. 

3. 3. 2. 2. 8. 3 Power Control and Monitoring (U) 

11 

Visual indications of electrical system events, 

conditions, outputs, and malfunctions shall be provided. 

mill111.071wsur. •■••• 

3. 3. 2. 2. 8. 2. 11 In-Space Start (U) 

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 (\-4) 

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 \-4) 

The cryogenic storage system shall have adequate capacity plus a 10 

percent reserve to supply the EC/LS oxygen requirement and all of the 

CONFIDENIK bruilAL HANDLING, 

FORM This document contains information allgE,lI 1 l ense of the United Stores within the meaning of the Espionorie Lows. • 

SSD AUG 62 21:/.2 18. U S C.. Section 793 and 794. t s ich y manner to on unauthorized person Is piohibiterf by law 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE _

34 OF 52 

DATE 20 Jan 66 • SUPERSEDING 

kiECAL 

UNIN 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -79 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.8.6 MISSION PHASE REQUIREMENTS (U) 

Change second paragraph to read as follows: 

A capability shall be provided to monitor the CPS during 

all phases of a mission. 

• 

ti 

CAL 
1 

 NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

❑ PRELIMINARY 

ED FINAL 

1. ECP NO. 2. CONTRACT END ITEM NO. 3. SPEC.. NO. 

NA MOL System SS-MOL-1 

4. CONTRACT 5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

Program 632 A 3-79 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.8.6 Mission Phase Requirements (U) 

Change last two sentences to read: Performance parameters of the 

other Laboratory Vehicle subsystems also shall be exercised, 

and the CPS shall sustain their launch mode power requirements 

upon transfer to internal power. 

A telemetry capability shall be provided to monitor the CPS 

during the launch and ascent phase. 

25 or 6? 

HI HANDLING, PAGE 

TION CHANGE NOTICE 

NO. 2 

DATE 15 Mr4rph (-S 

SUPERSEDING 
NRO APPROVED FOR Elk HANDLING 

RELEASE 1 JULY 2015 

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 th'e 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. 

t. 

A capability shall be provided to monitor the CPS during 4-144-4-a-ttneh 

6t: /it. ie 

-.1444E1=ivere-e-Flt—itha-s-e. 

3.3.2.2.8.7 

3.3.2.2.8.7.1 Equipment Operating Voltage \-4) 

Laboratory equipment shall give specified performance 

with 22-31 volts at the equipment power terminals. 

3.3.2.2.8.7.2 Under and Over-Voltage (\-4) 

Laboratory equipment shall withstand, without damage, 

when operated 

continuous 

Laboratory Vehicle Equipment Power Requirements 

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. 

3-79 

FORM This document contains information at fe 

SSD AUG 62 20B Title 18, U.S C , Section 793 and 794, th 

IAL HANDLING „,e of the Unite. Stotts within the meaning of the Espionage Laws. 

in any manner to on .noulko•.zed person is prohlboeci by lc* 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

-/I-C-RILS-PECIAL HANDLING 

3.3.2.2.8.7.3 Transients /N1/44) 

I 

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 

Vehicle, 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 --Itefff---SPECIAL HANDLING 

This dottoment (oit'vnns infoinsotion affecting the notional defense of the United Stntes within tie meaning of the Espionnge tows. 

18 U S C Sc"icin 79) and 794, the tionsmnssion of which in ony monner ,0 On la,Ou!),■ • ■ ,.1 De‘Sflal pioh.1,,ted by la w 

• 

4 

f. 
PEC1AL HANDLING, 

CONFIDENTIAL 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

4 

* Proof pressure is defined as that pressure which is applied to a 

pressure vessel as a test at room temperature. (U) 

L HANDLING 3-81 

Ilut document confu,s ,nfofrnolion 

f ole 18, U S C ftechon 797 and 794, 

nse of the United States within the 'reactant) of the Espionage tows. 

of which in tiny manner to on undufht,freo pe•snn .5 prohth ,fed by to. 

• 

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. 

3.3.2. Z. 9.4 Factors of Safety (U) 

Limit Proof Ultimate Burst 

Flight Loads 

b. 

Manned Payloads 1.00 

Non-Flight Loads 

-- 1.40 

(Other than Pressure) 

Dangerous to Personnel 1.00 1.50 

c. 

Remote to Personnel 1. 00 

Pressure Loads 

1.25 

Main Propellant Tanks 1.00 * 1.40 1.40 

Rocket Motor Cases 1.00 4' 1.25 1.40 

Pneumatic Vessels 1.00 1.67 2.22 2.22 

(Including Accumulators and 

Pressurization_ Bottles) 

Manned Cabins 1. 00 1.33 2. 00 2.00 

Hydraulic Vessels 1. 00 2. 00 4.00 4.00 

(Including Accumulators and 

Pressurization Bottles) 

Hydraulic Vessels 1.00 1.50 2.00 2.00 

(Normally Under Oil Pressure Only) 

Hydraulic and Pneumatic 1.00 

(Lines, Fittings and Hoses) 

2.00 4.00 4.00 

r. 

Main Propellant 1.00 1. 50 1.88 1.88 

(Supply and Vent Components) 

Cryogenic Tanks 1.00 1.67 2.22 2.22 
3-82 

FOAM Ihts document contains information offean 

' S:s1) AUG 62 2GB T,qr I8. U.S C Sect,on 793 and 794. 441- 

1,4 P i9 1 N 

ense Se E 

r 

kkikalolvdhilk 1491nK%,q411W 99e 1.00,, 

.ch m any manner to on unoutho,zed person Is wohtb.ted by low 

HANDL& 

3. 3. 2. 2. 9. 5 Strength and Stiffness N\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 Nc4) 

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 \-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. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

--sEifig_SPECIAL HANDL1K 

PRELIMINARY 

El FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE 35 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL -1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -83 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.11 MISSION PROVISIONS 3 SAR) 

Add the following to last sentence 

"for operation in the manned-automatic and automatic modes." 

Oek 

SPECIAL ACCESS REQUIRED 

SENSITIVE AREA 

PROGRAM NO. ‘3204 IDENTITY 45 

SPECIAL HANDLING 

This document contoint information affecting the notionol detente of the United Stoles within the meaning of the Espionage tows. 

1. Ile 18, U.S C , Section 793 and Mt, thejr 0,.....tyion of which in any monner to on unauthorized person it prohibited by low. 
ti 

FORM This document contains intannation o 

SSD AUG 62 20B Title 18. U S.C., Section 793 and 79 t 

L HANDLING 3-83 

ense of the United Slates within the meaning of the Esp.onoge Lows. 

whit in any manner so an unauthorized person is prohibited by ic 

1 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 ,tAtr UAL HANDLING 

3. 3. 2. 2. 10. 1 d Equipment (U) 

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. Z. 10. 3 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 requiredt11-12"-at"'2).-e-4- %ie 12e4 1 4Z "2111(/ 

t

ate e e 

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. 
--1111t11-1±E4141- 

NRO APPROVED FOR 

RELEASEel JULY 2015 

• 

PRELIMINARY 

FINAL 

1. ECP NO. 

SPECIFICATION CHANGE NOTICE 

NO. 2 

2. CONTRACT END ITEM NO. 

s. 

: V 

PAGE 26 or 62 

DATE 15 March 66 

SUPERSEDING 

3. SPEC. NO. 

_C1AL HANDLING 

NA 

A. CONTRACT 

Program 632 A 

6. EFFECTIVITY 

MOL Program 

' MOL System 

5. CONTRACTUAL AUTHORITY 

SS -MOL -1 

FILE OPPOSITE SPEC. PACE NO. 

3-84 

7. TEXT CHANGE 

Paragraph 3.3.2.2.13.1 Desing \-4.) 

Change second sentence to read: Portions of this AGE will 

be utilized for Laboratory Vehicle/Mission Payload integration at the OV Integrating Contractor 

facility and Flight Vehicle integrations at the 

launch site. 

Change sixth sentence to read: Laboratory peculiar AGE may 

be integrated into a complete Flight Vehicle 

checkout system as dictated by detailed design. 

requirements. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.3.2.2.11.1.2 S 

SPECIAL HANDLING 

visions (U) 

.• 

FORM this docoment contains mformation 

SSD AUG 62 20B lttle 18, U.S C., Section 793 and 7 w 

.onaqe Laws. 

,in any manner to on unouthor.zed person is prohibired by tno 

3-84 

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 

Flight 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 

`

-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 
SPECIAL HANDLING 

IONFIDENTIAL 

SPECIFICATION CHANGE NOTICE 

NO. 2 

NRO APPROVED FOR 

RELEASE ;I JULY 2015 

• 

PRELIMINARY 

113 FINAL 

PAGE 27 OF 62 

DATE 1.5 March 66 

SUPERSEDING 

I. ECP'NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-85/6 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.2.2.13.2 Performance \-4) 

Change last sentence to read: Portions of the Laboratory AGE 

shall support the Laboratory Vehicle System Segment end-to-end 

systems test when integrated into the Flight Vehicle checkout 

.system. 

Paragraph 3.3.2.3 Functional Interfaces (U) 

Change to read: (Functional interface documents shall be listed 

here when defined and approved in accordance with 

IFS-MOL-100001.) 

SPECIAL HANDLING 
NRO APPROVED FOR • 

RELEASE 1 JULY 2015 

• 

for ease of maintainability, interchangeability, and shall have features 

L HANDLING 

3-85/6 

p GiAL,„,eik4i, Esp.oncie 1.0.1. 

07 ny manner to Ea on unaulho,ted 0e,son is pf.:,h.bord by Ic: ... 

FORM This document contains mien-nao 

SSD AUG 62 20B In 18. U.S C.. Seown 773 and 

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 X-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 

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 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 GEI specification number, nomenclature, 

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

items being provided under these system segments.) 

a 

rl 

,,,Pr • 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL AN 

Mission Peculiar Requirements, Laboratory Module 

Space Allocation Requirements 

The Laboratory Module shall accommodate certain mission 

payload equipment. This equipment includes: Cameras, film handling, 

supply and take-up cassettes, two reconnaissance consoles, a data processing and readout console, acquisition and tracking system equipment, data 

return capsules, data re-entry vehicles and associated support equipment, 

electrical power and distribution system, wideband transmitter and antenna, 

and terrain camera. 

3. 3. 2. 5. 2 Manuevering Capability Requirements 

"Later" 

3. 3. 2. 5. 3 Alignments 

DRV - The launch tube for the DRV shall maintain the DRV 

axes of symmetry with 1/2° of the Laboratory Vehicle yaw axis. 

DRV installation equipment (AGE), support and ejection 

equipment (AVE) shall have provision for making and checking the alignment. 

Mission Module - Provision shall be made so that alignment 

of the MM reference axes to the Laboratory Module reference axes can be 

measured in the factory to within one minute of arc. 

SPECIAL .atUiL aVi.„1 

3. 3. 2. 5 

3. 3. 2. 5. 1 

3-86. 1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

Other - other alignments required for the installation of 

MPSS equipment in the LM and interconnection with MPSS equipment 

in the MM will be defined in the Interface Specification. 

3.3.2.5.4 Electric Power 

The Laboratory Vehicle shall furnish electrical power to 

the Mission Payload as provided in 3. 3. 2.2.8. 

3.3.2.5.5 Mission Module Structure 

The Mission Module structure shall support the Mission 

Payload and protect it from deleterious shock and vibration during 

powered flights. It shall also, during orbital flight, maintain vibration 

at a level which will not degrade mission performance below specification 

requirements. 

SPECIAL HANDLING 

3-86.2. 
r. CONFIDENTIAL 4%I SPECIAL HANDLING: 

ATION CHANGE NOTICE DATE 

PAGE 

NO. 2 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

PRELIMINARY 

C3 FINAL 

28 of 62 

15 March 66 

SUPERSEDING 

I. ECP NO. 

NA 

C CONTRACT 

Program 632 A 

2. CONTRACT END ITEM NO. 

MOT, 

5. CONTRACTUAL AUTHORITY 

3. SPEC. NO. 

SS -MOL - 

FILE OPPOSITE SPEC. PAGE NO. 

3-87 

Y 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 

Change 

3.3 Gemini B System Segment (U) 

second sentence to read: 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 loiter, re-entry, and water landing as an autonomous 

spacecraft 

Paragraph 3.3.3.1.1 Weights (U) 

Change to read: The maximum design allocation weight 

for the Gemini B System Segment at launch shall 

be 5,660 pounds including the CFE Crew Equipment 

but not including experimental gear. 

Paragraph 3.3.3.1.4 Flight Crew Stay Time )1 4) 

Change to read: The maximum total time the flight crew will 

be required to stay in the Gemini B is 62 hours. 

Maximum flight crew occupancy time in the Gemini B 

for the launch, (starting with ground environment 

disconnect) ascent, and early orbit phases shall be 

six hours. Of the total time, at least 14 hours 

shall be available for loiter as defined in 

Paragraph 3.1.1.1.6. 

SPECIAL iikDLING 

«..%•! "..km 111T, 

t. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 . i low 1 Jr it* 

u) 0;. .... t EC AL ijit,NDLING 

3. 3. 3 Gemini B System Segment 

The Gemini B system segment shall consist of a re-entry module 

(REM), an adapter. and the supporting ground system. The CLmini 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 be 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. 

3.3.3.1 Allocated Performance and Design Requirements 

3.3.3.1.1 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 para-

.graphs 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 Time (k4) 

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 available for loiter as defined in paragraph 3.1.1.6. 

3.3.3. 1. 5 Leak Rate (14) 

The Gemini 13 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 

'SSD AUG 

this document contains informorion off t s t w.HANDLINafonoge tows. 

20B Tole 18. 11 S C Section 793 and 794. id, in manner to on unouthorized person is O'nn.b.fed 

'._;0101,11-kpFEC 
NRO APPROVER FOR 

• RELEASE 1 JULY 2015 

• • PRELIMINARY 

FINAL 

46,i. ifitet.utAL 

-1-EWRI44111-14-- . 

SPECIFICATION CHANGE NOTICE 

NO. 2 

PAGE 29 or 62 

DATE 15 March 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-88 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.3.2.1.1 Re-entry Module (c4) 

Add to end of first sentence: and 3.1.1.1.4.2. 

4 

4 ■ 

SIECRETr-_SPECIAL HANDLING 
• 

NIRO APPROVED FOR 

RELEASE 1 JULY 2015 

SSS-233-1 

:M1NARY 

,1■.j 7 :NA L 

PAGE 16 '0,;- 25 

DATE 

O. SUPEP1SE.D1 NG 

1. EC? NO. 

t • 

2. CONT.:ACT ENDT.1:1. 

?DL Svsten 

3. SPEC. NO. 

SS-1-1,0L-1 

CONTACT 

6 

5. CONTRACTUAL AUTi7:0:-.ITY 

CON 

ELE OPPOSITE SPEC. PACE NO. 

3-88 

6. EFFECTIVITY 

iCL :or: 

7. TEXT Cc-.ANGE 

Paragraph 3.3.3.2.1.1.2 Data Packa7e (Ni24) 

Cnanse to read: 

Parcraph 3.3.3.2.1.1.2 Data Return Capsules 

The GemiLiB R2M shall have the cacability for return of data from 

orbit. The data will be returned in four (4) Data Return Capsules 

(:20) each weighing 70 pounds. Ilhe nominal total weight and volume 

of the Data Return Capsules shall be 280 pounds and 4.0 cu. ft., 

ressoectively." 

L.; 

• '

.!r

; • IA 4 
LUAL HANDLING 

CONIDENTIAL 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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/clay. 

Gemini re-entry module capable of re-entry from polar orbits 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 tt 

through the Gemini B main pressure bulkhead and heat shield to an 

internal tunnel consistent with the requirements of paragraph 3.3.3.2.11. 

3.3. 3. 2. 1.1.2 Data PackageNI) 

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 170 lb and 3 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 

ANDLIK 

3.3.3.2 Peculiar Performance and Design Requirements 

3.3.3.2.1 Gemini B Requirements 

1 Re-entry Module4) 

,„,2• The Gemini B re-entry module shall consist of a modified NASA 

3-88 

;.• 

F. 

FORM The, document conioins information affectf' defense of the United States w$1hIn the meaning of 'he E$1..,:no"ite 

SSD AUG 62 20B Imo 18, U.SC . Sect.an 793 and transmission which any manner to on unouthol.zed ve■ son is p•.31111-,ted by !no. 

m 
,erptr 

Ira 0,,P01.ei PPott 

LALVAIDLIII 

ICATION CHANGE NOTICE 

NO. 2 

CIAL HANDLING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

ED FINAL 

PAGE 30 OF 62 

DATE 15 March 66 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

-. 

Program 632 A 

S. CONTRACTUAL AUTHORITY' FILE OPPOSITE SPEC. PAGE NO. 

3-89 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.3.2.1.2 Adapter (U) 

Change third sentence to read: The Gemini B shall have the 

capability of separating from the Laboratory at both the 

Laboratory/Gemini B adapter separation plane and the 

adapter retrograde separation plane. 

Paragraph 3.3.3.2.2.1 General (U) 

Change to read: The Gemini B shall have a guidance and control 

system which provides the functions of back-up inertial 

guidance during the ascent phase after Stage 0, re-entry 

guidance, and attitude control during the period in which 

the Gemini B is separated from the Laboratory. 

4 
3-89 

nol defeSpECIALtes HAMDLIKGBo.-.no9e lnwi, 

ic o r on r p h,b,r•d by low 

FORM This document conto.ns Informori 

SSD AUG 62 20B U S C . Secr,on 703 and 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PECIAL FIANDUG 

but required to support the Gemini B. The Gemini 13 shall have the 

capability of separating from the Laboratory both the Laboratory/ 

Gemini B adapter separation plane and the adapter retrograde separation plane. The Gemini B shall also have the capability of separating 

the re-entry module from the retrograde adapter section. 

3.3.3.2.1 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 tran7portation. pre-laun,h. launch, ascent, on-orbit, retrograde, 

re-entry. landing, retrieval, and abort modes. 

3.3.3.2.1.4 AerodynamicS4 ) 

The re-entry module shall be trimmed by center-of-gravity position to 

provide 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 fircscl), 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 ....+9o0 where, for a zero value of p, the lift vector is directed away from the earth in the vertical plane. 

3, 3, 3, 2: Guibnce anr.1 Contrcl. Rf,c1plirernent,5 

3.3.3.2.2.1 General (U) 

The Gemini B shall have 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. 
L ECP NO. 

NA 

2: CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 • 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY ' FILE OPPOSITE SPEC. PAGE NO. 

3-90 

6. EFFECTIVITY 

MOL Program 

• 

SPECIAL HANDLING 

NRO APPROVED FOR 

RELEASc JULY 2015 

PRELIMINARY 

p FINAL 

im"I q7109:1 

• 

V, r.7. eT'

e'sitji " ; e't• 

pPGE 31 Or 62 

CHANGE NOTICE DATE 15 March 66 

NO. 2 SUPERSEDING 

t•• 

7. TEXT CHANGE 

Paragraph 3 .3.3.2.2.2 Back-up Launch Guidance (U) 

Change first sentence to read: 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 IIIM flight control system. 

Paragraph 3.3.3.2.2.3 Re-entry Guidance and Control (U.) 

Delete last sentence: The system shall have the capability 

to guide to non-nominal points. 

Paragraph 3.3.3,2.3 Instrumentation Requirements (U) 

Change second sentence to read: While the flight crew is in 

the Gemini B, 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, in addition, Gemini B status will be 

telemetered to the ground from the Gemini B. 
riLciAL 

Back unc Guidance (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 

?)/ 3.3. 3.2. 3 Instrumentation Requirements (U) 

SOL 

se"' 

i 3-90 

FORM This document contains onfo,notoon of 

SSD AUG 62 20B Title le, U.S C., Section 793 and 794 

HANDLING, 

noted Stoles within the meon.ng of the Espoonoge Lows. 

annex to on unoutho,i,ed person is prohopoted by low 

..... • • • • 

NRO APPROVED FOR 

RELEASE 1 JULY 2045 

Se It, 3. 3. 3. 2. 2. 2 

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 13 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. 
r 

I WO APPROVED FOR 

RELEASE 1 JULY 2015 

o PRELIMINARY 

E FINAL 

•.r.1 

HANDLING PAGE 32 OF 62 

ANGE NOTICE DATE 15 Wirrh (1() 

NO. 2 SUPERSEDING 

,• 

- i‘ 

c_CIAL HANDLING 

I t 

r 

1. ECP NO. 

NA 

2. CONTRACT END rrem NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A. : 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-91 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.3.2.3 Instrumentation Requirements (1.) 

Delete fourth, fifth, and sixth sentences and add the following: 

While the flight crew is in the Laboratory, capability shall 

-40 be provided for monitoring of Gemini B status by the ground . 

via the Laboratory TTCV. The Gemini B critical parameters 

shall be monitored by the crew using the Laboratory Monitor 

and Alarm System. Critical monitor signals will be provided 

to the Monitor and Alarm System in analog 0-5 V range form. 

Ground status monitoring shall be accomplished by transmission of the Gemini digital telemetry format to the 

Laboratory TTCV. Suitable interface modifications shall be 

provided for integrating and for establishing compatibility 

of SGLS in the Gemini and in the Laboratory with the Gemini. 

PCM digital telemetry. 

Paragraph 3.3.3.2.4.1 General 

Change last sentence to read: Breathing atmosphere and drinking 

water shall be provided for the crew stay time in Gemini B 

compatible with the requirements of Paragraph 3.3.3.1.4. 

ci 
I • L,c,' P-9 control of the Laboratory ACTS. Capability shall be provided for 

3.- EC1AL 

monitoring of Gemini B status by the ground and flight crew while the 

5611/' 

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 

fd 

The 11 shall provide the environmental control and life supsai1- ■i4 port (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 MOL 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 

temperature shall not exceed 150°F. 

3. 3. 3. 2. 4. 3 Suit Environmental Control 

4 NRO APPROVED FOR 

RELEASE 1 JULY 2015 

v, 

Gemini 

Metabolic oxygen, pressurization, and ventilation shall be.provided to 

support the MOL pressure suit assembly. The capability shall be 

SPECIAL HANDLING 

3-91 
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NO. 

lig NADIA& AGE 

DATE 

it• 

t. 

33 or 62 IfJ. 

15 March 66 

SUPERSEDING 

direction of travel 

the Laboratory end 

the out of normal 

maintain proper 

UECLASSL5: 

rEC1AL hANDUNG. 

NROAPPkOVEDFOR 

RELEASE 1*JULY2015 

O PRELIMINARY 

[Z] FINAL 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

1 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

- 

3-92 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Add paragraph 3.3.3.2.4.6 Orientation CO 

Normal Gemini B attitude orientation to the 

shall be for the small end to be forward or 

forward. At altitudes between 70-100 n mil 

attitude shall be controlled in a manner to 

temperature. . 

■...r.■••• 

A 
3-92 SVE:611:11. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

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 

during transfer to the Gemini B. Capability shall be provided to 

permit extravehicular transfer between the Gemini B and the Laboratory as a A 

4 

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. 

3& 

F 
1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A , 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-93 

6. EFFECTIVITY 

NRO APPROVED FOR 

'RELEASE 1 JULY 2015 

PRELIMINARY 

E3 FINAL 

TI

ilithi L. m 34 .OF 62 

CS DATE Pi March 66 

NO. 2 SUPERSEDING 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.3.2.6.1 

Change first sentence to read: The Gemini B shall have the 

capability for providing power for launch, ascent, ascent 

abort, 14 hour. Loiter, Re-entry operation and 36 hours 

post landing. 

1 • 

i 

A 

ECLASSTIED 

lECRET_SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 -q,CRET SfE.GIAL • 3.3.3. 2. 5, 3 On-Orbit Post-Separation Control 

Propulsive capability shall be provided for coot rot of the attitude and 

4 attitude rates of the Gemini B for on-orbit 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 h 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 

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 

A 

` ;2- 3. 3. 3. 2. 6. 1 General 

SCW The Gemini B shall have the capability for providing power for ascent 

abort, on-orbit post separation, re-entry and retrieval. The Laboratory Vehicle shall supply Gemini B power as given in 

ft 
NRO.APPROVED FOR 

RELEASE 1 JULY 2015 

• 

• 

PRELIMINARY 

FINAL 

HANDLINft 

SPECIFICATION CHANGE NOTICE 

NO. 2 

PAGE 35 OF 62 

DATE 15 March 66 

SUPERSEDING 

I. ECP NO. 

NA 

2. 

5. 

CONTRACT END ITEM NO. 

MOL System 

CONTRACTUAL AUTHORITY 

3. SPEC. NO. 

5S-MOT,-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-94 

4. CONTRACT 

Program 632 A 

6. EFFECTIVITY 

MOL Frogram 

7. TEXT CHANGE 

Paragraph 3.3.3.2.6.2 Electrical Power Supply (U) 

Change second sentence to read: There shall be adequate power 

reserve capacity in all power sources. 

Change last two sentences to read: Re-entry module power sources 

must be active during the launch and ascent phase for abort 

purposes. Independent power sources with adequate power 

reserve capacity shall be provided for redundant pyrotechnic 

circuits and other transient producing type loads. 

SPEr,!$!: PAMP!I'vc 

, — - 

LIECLASSIFIED 
3. 3. 3. 2. 7. 2 Event Timer 

A capability for providing short-term timing of function shall be 

provided. 

SPECIAL HANDLM 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

paragraph 3. 3. I. 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 

I 

I 

A capability for distributing the electrical power from the power supply to the using system shall be provided. The spacecraft structure 

shall not be used as an electrical current path. The system negative 

shall be grounded at one point only in the spacecraft. A compatible 

grounding network between Gemini B, Laboratory, and Titan III 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 be provided to furnish accurate accounting of elapsed time, time-to-go, and time correlation. A reset 

capability shall be included. 
I 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

0 PRELIMINARY 

[Z] FINAL 

RAL HANDLING 

PAGE 3() or (0 

SPECIFICATION CHANGE NOTICE DATE 15 March ‘6 

NO. 2 SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-95 

' 6. EFFECTIVITY 

MOL Program 

' 7. TEXT CHANGE 

Paragraph 3.3.3.2.8.2 Safety (U) 

Change first and second sentence to read: Actuation of pyrotechnic 

devices shall not endanger the crew or degrade the performance 

of systems that must function after the pyrotechnic devices 

are utilized. Installation of pyrotechnic devices shall be 

so designed that the hazard to launch ground crews is minimized 

during assembly and checkout of the Gemini B. 

Ii 

EINCLASSMED 

SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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. L Safety (U) 

Actuation of pyrotechnic devic es 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 B. All possible precautions 

shall be taken to preclude inadvertent initiation of pyrotechnic devices. 

Electromagnetic 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 13 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. 

37 3. 3. 3. 2. 9. 2 Descent and Impact 'ci.,4) 

The rate of descent of the re-entry module shall be 32 t 2 fps at sea 

level for a weight of 4860 lb. 

FORM Ihrt document contoins information. defense of the United States within the meaning of the Espionage tows. SSD AUG 62 20B 1,1e 18, ti C Section 793 and . r e transmission of int ch in any manner to on unauthorized pe•son .i'siktan.thited by 

• 
DATE 15 Marnh (.36 

NA 

4 nnNTRACT 

Program 632 

6. EFFECTIVITY 

MOL Program 

NRO APPROVED FOR 

liELEAS 1 JULY 2015 

PRELIMINARY 

E] FINAL. 

S. CONTRACTUAL AUTHORITY 

. MOL System 

I L HANDL' 11(LAGE 37 OF 62 

ATION CHANGE NOTICE 

NO. 2 SUPERSEDING 

1. ECP NO. 2. CONTRACT END ITEM NO. 3. SPEC. NO. 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-96 

. 7. TEXT CHANGE 

Paragraph 3.3.3.2.9.2 Descent and Impact IN15.4.0 

Change first sentence to read: The water and sea state impact 

loads on the re-entry module shall not exceed the deceleration'. 

levels in the following directions with respect to the crew. 

Paragraph 3.3.3.2.10.1 Location (U) 

.Change paragraph to read: The means for location of the re-entry 

module and crew members after landing. shall be provided. • 

This location capability shall include visual devices for 

both day and night operation as well as HF and VHF voice 

and VHF recovery beacon capability. RF type location aids 

in there-entry module shall be operable for a post-landing 

period of 36 hours. 

Paragraph 3.3.3.2.10.2 Flight Crew Safety (U) 

Change third sentence to read: The Gemini B shall be capable 

of floating in water for a continuous period of not less 

than 36 hr after touchdown in water. 

3 

f. 

F. 
LCIAL HANDLIC 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

The water and sea s a e impact loads on the re-entry module shall not 

exceed the deceleration levels in the following directions: 

Forward 30 g 

4 

Aft 30 g 

Up 11 g 

Down 15 g 

Left 11 g 

Right 11 g 

3.3, 3.2. 9.3 Flotation (U) 

Following water impact, the Gemini B shall float in a crew hatch-up 

position. Provisions for additional flotation gear to be manually secured to the Gemini B by recovery force personnel shall be provided. 

3, 3. 3. 2. 10 Post- Landing and Survival Requirements 

.37 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 

Title 18, U C . Section 793 

ttonal deSsPaEhCantesHARDe Esc,tnna9e 

SSD AUGFRr2 208 which in any manner to on unouihorized person ts 0:0h.htted by to.. 

This document contains informa 
NRO APPROVED FOR SPECIAL HANDLING 

RELEASE 1 JULY 2015 

S 

3. 3. 3. 2. 11 

3. 3. 3. 2. 11. t 

Flight Crew Transfer Requirement 

Normal Mode (IT) 

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 he large enough to preclude trapping of the 

crewman if emergency inflation of the suit occurs during transfer. 

Positive stowage of the translc,r hatches shall be provided to prevent 

damage during transfer and on-orbit storage. 

3. 3. 3. 2. 11. Z Back-up and Emergency Modes (U) 

The regular egress hatches used for backup extravehicular transfer 

shall remain closed after transfer of the last crewman. Provisions 

shall he made for opening and closing the hatches from inside and outside Gemini 13 while in a pressurized suit. Provisions shall he provided for handholds, etc. on the exterior of the Gemini B. 

3. 3. 3. 2. 12 Flight Crew Equipment and 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 Displays and Controls (*6,;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 

ANDLING 3-97 

Th.* .'acumen, conloo ns mlormoti tense of the Un..ed Slates within ,hr menn.ng of ,he Esc 

Title IS. U S C Sechon 793 and on of wh,ch .n cny manner to on vnou'ho,,red 9e•son .1 7,. Ov 

r. 

a. 
4 NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 • 

El PRELIMINARY 

El FINAL 

.NECIAL.HANDLING 

/pc-Fn. • 

, 

SPECIFICATION CHANGE NOTICE 

NO. 2 

PAGE 38 or 62 

DATE 15 March 66 

SUPERSEDING 

CIAL HANDLING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-98 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.3.2.13.2 Voice Communications (U) 

Change first sentence to read: In addition to SGLS, two UHF 

and one HF two-way voice communication system shall be 

provided. 

Add a third sentence: HF voice will be utilized.for post landing fE 

retrieval operations only. 

• 
3. 3. 3. 2. 12. 3 Flight Cre\\ Seating(1.1) 

Provisions shall be included for seating of the two-man flight crew in 

the proper position and with adequate restraint to minimize the effect 

of launch and re-entry acceleration forces. These seat provisions 

shall include the capability of successfully ejecting the crew members 

from the re-entry module for certain 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. 

3S 3. 3. 3. 2. 13. 2 Voice Communications (U) 

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. 

[IANDLING. 

This document tontoms information be defense of the United States ...ohm the meaning of the Esp.anacie toas 

Tole 18. U S C . Sechan 793 and 794. the honsmosuon or n any manner to an anauthahced Person PS p,oh•boTed 

3-98 

SECRET SPECIAL HANDLING 

CONFIDENTIAL 

NRO APPROVED FOR. 

191 RELEASE 1 JULY 2015 

.4 

flight cre\k 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. I. I. I. 5. 5 and 3. 3.2. Control provisions for safety of flight 

functions shall be operable by the crew in either vented.or pressurized suits 
AGE 39 or 62 

TION CHANGE NOTICE DATE U5 March 66 

NO. 2 SUPERSEDING 

MAL HANDLINGp 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 PRELIMINARY 

FINAL. 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A_ 

S. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-99 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.3.2.13.3 Telemetry (U) 

Change second and third sentence to read: This telemetry 

capability shall be continuously available when 

in sight of a ground station during ascent, early 

orbit, and re-entry operation phases. During the 

on-orbit phase, the telemetry capability shall 

be available on call through the Laboratory SGLS. 

I Paragraph 3.3.3.2.13.6 Intercommunication (U) 

Delete first sentence: The capability for intercommunication 

between the crew shall be provided during all mission 

phases. 

Change second sentence to read: Intercommunication shall be 

provided during 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 Vehicle. 

UNCLASSIFIED 

11 V2.7ar1* ,

SPECIAL HANDLING 16,11 

r. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 —sEGRET_ SPECIAL HANDLING 

I 

• 

• c>. 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. 13. 4 Tracking and Recovery 

SGLS and additional aids for flight phase radar tracking and for postlanding recovery location shall he 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 inter- 

'1 national 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 13 and the other crew member is in the crew 

transfer mode, and when one crew member is in the Laboratory 

—...4marar , SPECIAL hAiiailiG 3-99 
• 

NRO APPROVED FOR 

RELEASE 4 JULY 2015 

C3 PRELIMINARY 

FINAL 

PAGE _la_ OF 62 

DATE 15 March 66 

SUPERSEDING 

ANDUNG 

CATION CHANGE NOTICE 

NO. 2 

1. ECP NO. , 

NA 

4. CONTRACT 

Program 632 A_ 

6. EFFECTIVITY • 

2. CONTRACT END ITEM NO. 

MOL System 

S. CONTRACTUAL AUTHORITY 

3. SPEC. NO. 

SS-MOL-3. 

FILE OPPOSITE SPEC. PAGE NO. 

3..106 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.3.2.15.1.1 Design 

Change first, second and third sentences to read: The Gemini B 

segment peculiar AGE shall consist of OGE and MGE designed 

to support all Gemini B Segment operations. 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, consistent with 

the functional requirements. 

4 
-L 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

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 Grew 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. 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 

4 

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. 

A0,1-(41414

0. • 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, check out, 

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 

3-100 SPECU HANDLING 

ri 
I. ECP NO. 

NA 

4. CONTRACT 

Program 632 A 

2. CONTRACT END ITEM NO. 

MOL System 

S. CONTRACTUAL AUTHORITY 

3. SPEC. NO. 

SS -MOL -1 

FILE OPPOSITE SPEC. PAGE NO. 

3-101 

trXeLLSZIED 

FECAL HANDLING 

NROAPPROVEDFOR 

RELEASE 1 JULY 2015 p r■ r4 V-71;‘" 

o PRELIMINARY 

FINAL 

CA " HANDLING 

NO 2 

PAGE 41 oF 62 

DATE 15 March 66 

SUPERSEDING 

6. EFFECTIVITY 

MOL Program 

. 7. TEXT CHANGE 

Paragraph 3.3.3.2.15.1.2 Performance 

Change third sentence to read: This AGE shall form a part of the 

Flight Vehicle AGE. and will also support the integration of 

the Gemini B with the other elements of the OV and the 

Titan III. 

t: 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

AGE shall form . a part o tie V 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 L1) 

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 

system 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 N\-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. Z. 16.3 Safety During Mission Abort INgs- 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. 

ThIs document conpuns Inform() 

1.tle 1 8. U S C . Sechon 793 0 

SANDLING 

3-101 

etnan the LInoect Slates v. menn.nq al the f sp•nnn p• L 

ch in any manner to on unOulho,jed 0e•son ma cpr.t.,t 

CON 
NROAPPROVEDFOR 

RELEASE ,JULY 2015 

o PRELIMINARY 

E FINAL 

s.5r7in 

't• SPtijAtiiii,NDLING 

IFICATION CHANGE NOTICE 

NO. 2 

PAGE OF 62 

DATE 15 March 66 

SUPERSEDING 

L ECPNO. 

NA 

2. CONTRACT END ITEM NO. 

... 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program.632- A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-102 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.3.3 Functional Interfaces (U) 

Change to read: (Functional interface documents shall be listed 

here when defined and approved in accordance with IFS-MOL-100001) 

ri• 
11IP116[AL HANDLING 

se of the United Slates wah,n rho meaning of me Tspionoqe t )0.1 

which in any manner to on s.nooth.rriztra person .s PrPhilOitert by 

3-102 

This document cantatas Information &le 

Tale 18. U S C Section 793 and 794, 

NRO APPROVED FOR 

---SEGRUPECIAL HANDLiNG t. 

RELEASE 1 JULY 2015 CONFIDENTIAL 

Stage During Which Maximum Probability of Crew Fatality 

Abort Occurs If An Abort is Required 

Stage 0 Operation 0.100 

Any Other Launch Vehicle 0.020 

Stage Operation 

Orbital Operations 0. 001 

(Functional interfaces shall be listed here when defined by the cognizant Interface Control Working Group - ICWG) 

3.3.3.4 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. 

The probability that the Gemini 13 shall cause a mission abort shall 

not exceed 0.0001 for the entire mission. 

42-3.3.3.3 Functional Interfaces (U) 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.3.3.5 Mission Peculiar Requirements, Gemini B Module 

3.3.3.5.1 Gemini Film Data Return (Data Return Capsules) 

Up to 240 pounds of film data shall be returned by the 

Gemini. The film shall be housed in protective data packages designated 

Data Return Capsules (DRC's) to minimize the possibility of film quality 

deterioration due to (a) physical damage in handling, (b) contamination, 

e.g. dirt, moisture, and (c) light leaks. 

The data packages will total four (4) composed of: 

a. Three (3) DRC's containing 60 pounds each of 

primary record. 

b. One (1) DRC (secondary package) containing 60 pounds 

of secondary record, cues, and terrain camera film. 

The total weight and total volume to be made available in 

the Gemini B REM for the data shall be a nominal 280 pounds and 4.0 

cu. ft. respectively. 

SPEC II 14, , 

e 

3-102.1 
7-71 43 or 62 

15 March 66 

NRO APPROVED FOR 

RELEASE1 'JULY 2015 

a • 

PRELIMINARY 

[X] FINAL 

PAGE 

DATE 

SUPERSEDING 

CONN-Jr:MAL 

PocligruligigLING 

No. 2 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-105 

6. EFFECTIVITY 

MOL Progra m 

7. TEXT CHANGE 

Paragraph 3.3.5.1.2 Weight Ns4) 

Add second paragraph as follows: 

For Gemini B design purposes, the maximum weight of the flight 

crew shall be 360 lbs. Maximum crew equipment weight shall be 

140 lbs. which shall include two integrated pressure garments, 

two emergency oxygen units, bio-medical system and recorder, 

contents of two survival kits, and cabin drinking water. 
HANDLING 

3. 3. 5 

NRO APPROVED FOR 

4 RELEASE 1 JULY 2015 

S 

ild • 

rew quiprnent System Segment (U) 

This system segment defines the crew equipment requirements for 

performance of the MOL mission. 

This section covers equipment for both intravchicular and extravehicular tasks, performed both with and without a pressure suit (both 

pressurized and unpressurized). 

3. 3. 5. 1 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 1V.,c4) 

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. 

FORM This document contains tnformoaon 

SSD AUG 62 20B Ttrte • U.S C , Seca on 79 and 

1 

E! v■ !irl 3-105' 

defense of the United States mottan the meorang of the EsprQnage tows. 

which in ony manner to on vnou,hor,zed fs'sOn 's 
; • r" 4 5i 

HANDLING PAGE 1J. OF 62 

ATION CHANGE NOTICE DATE 15 Mn roll 6(6 

NO. 2 SUPERSEDING 

NRO APPROVED FOR 

RELEASE .1 ,JULY 2015 

• 

PRELIMINARY 

FINAL 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A ' 

S. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-106 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.5.1.4.1 Pressure Suit Assembly (U) 

Change entire paragraph to read: The pressure suit assembly 

(PSA) includes the basic garment, with integral thermal 

and micrometeoroid protective provisions, helmet, 

gloves, communications and provisions for the 

bioinstrumentation harness and signal conditioners. 

Recovery, life raft, survival and rescue equipment 

are in the ejection seat backboard assembly, 

readily available to the crew. Personal flotation 

will be an integral part of the parachute harness. 

Paragraph 3.3.5.1.4.2 Auxiliaty Extravehicular Equipment Ok4) 

Change the first sentence to read: The major equipment items 

to be used in conducting the extravehicular operations 

in addition to the PSA, are an umbilical type 

Environmental Control System, communications 

umbilical, and devices for traversing the OV surface 

such as handholds and tether belt. 

.1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

:4 PECIAL HANDLING 

3. 5. 1. 4 Extrave icu ar Equipment 

ad,tb..2_, 3. 3. 5. 1. 4. 1 Pressure Suit Assembly (U) 

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. 

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, 

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 radiation 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. 2 Auxiliary Extravehicular Equipment X-.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. 

(.4 

nr; 

3-106 

sso 101%4 Th.4 document contains ,'formation defen fed ligfes woihm the rneontng of the Esptonnge tows 

HANDLING 

- 62 20B 1.1. 16. U.S C Sechon 793 and 794. he i,nnsmis sion of which in any manner to on unaufhorIzed pe,son p■ ohM■ fed by to,. 
ail* ECIAL HANDLING 

PAGE 45 or 62 

DATE 15 March 66 

SUPERSEDING 

SPECIFICATION CHANGE NOTICE 

NO. 2 

NRO APPROVED FOR 

R€LEASF, 1 JULY 2015 

0 PRELIMINARY 

FINAL 

I 

Program 632 A 

-6: EFFECTIVITY 

MOL Program 

• 7. TEXT CHANGE 

Paragraph 3. 

• Change 

3 -10 7 

1. ECP NO. 

NA 

2. CONTRACT END rrem NO. 

MOL System 

3. SPEC. NO. 

SS -MOL -1 

4.. CONTRACT . 5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3.5.1.5 Intravehicular Operations (U) 

first sentence to read: Basic operations in the 

Gemini B will consist of operations during 

ground ckeckout, launch, ascent, insertion, Laboratory activation, re-entry operations,and shall 

be conducted in an unpressurized suit during nonemergency operations. 

-MAL HANDLING I 
t. 

I NRO APPROVED FOR 

RELEASE 1 JULY 2015 

a 3.3.5.1. 5 

saag-SPECIAL HANDLING 

Intravehicular Operations (In 

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. 1 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). Tht, intravenicular 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. 

,sEcRET SPECIAL HANDLING 3-107 

SSD A FUOGR642 20 B 
SSD A FUG R642 20B ran 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 ACV-SPECIAL HANDLING 

3.3.5.2 Peculiar Performance and Design Requirements 

3.3.5.2.. 1 Orbital Operations Aids 

3.3.5.2. 1.1 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. L. 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 programed 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. Z. 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 of 3000 kilocalories (kcal) per man per 24 

hour cycle will he 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 SPECiAL HAi\iuUNG 

Cr; 

1 

re; 

rn. 

N* 

LI1* 

M 
tr.) 

1.11 

N 

J1 

N 

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z RELEASE 1 JULY 2015 --sEeRET-SPECIAL HANDLING 

• 

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 nutrient type and calories. 

3.3.5.2.2.3 Water Requirements (U) 

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. 

Flight Crew Test and Monitoring 

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 include acquisition of essential 

pre-flight and post-flight baseline data and extensive ground-based 

of 45 cc/hr except during C NC rcise 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. Z. 2. Food Composition 

The 3000 kcal diet shall consist of a minimum of 70 g of protein, 

(carbohydrate and fat to he defined) and fortified with vitamins and 

minerals and having a calcium content less than 500 mg. 

3.3.5.2.4 

3.3.5.2.4.1 

SEW SPECIAL HANDLING 3-109 
HANDLING PAGE 4 6 OF - 

62 

ATION CHANGE NOTICE DATE 15 March 66 

NO,. 2 SUPERSEDING 

c ti

MICLASSMF.13 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

FINAL 

1. ECP NO. • 

NA 

2. CONTRACT END rrem NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

A. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-110 

6. FFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3 .3.5.2.4.2 Biomedical Monitoring (U) 

Delete both paragraphs which read: 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 flight6. 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. 

Add new paragraphs as follows: 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 measurements shall include continuous 

heart rate plus EKG, blood pressure, and oral 

temperature; all on demand or as scheduled. 

Monitoring during launch, ascent, and re-entry 

phases will utilize Gemini B telemetry. Two leads 

of EKG, one of blood pressure, and one of oral 

temperd:ure from each crew member will be transmitted 

in real time. One biomedical tape recorder with 

time correlation on one channel will record two 

leads of EKG and one of blood pressure from each 

crew member. This will be used for post mission 

analysis. The capability of recording EKG in 

the Lab Vehicle during manned Gemini B operations 

for telemetry dump will be provided. 
NRO APPROVED FOR 

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SPECIAL HANDLING 

47/‘ 

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) 

ui 

rei 

ce; biomedical monitoring equipment to be used for flight safet onitoring in the Laboratory during all flights. These mea es shall include 

continuous heart rate plus EKG, blood pre : are, temperature, and 

• 

c. 

respiration rate on schedule and o emand. 

The baseline scheme...1<ff monitoring during launch and re-entry will 

consist oft ---basic NASA Gemini monitoring scheme. This includes 

2 lea,c1of EKG, blood pressure, respiration profile, and oral 

'11 I 3. 3. 5. 2. 4. 3 Crew Performance Tests (U) 

in 

0"; The flight crew shall be tested on a set of standardized tasks intere; grated 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. 
NRO APPROVED FOR 

RELEASE 2 JULY 2015 

0 PRELIMINARY 

33 FINAL 

Change to read: (Functional interface documents shall be 

listed here when defined and approved in accordance. 

with IFS-MOL-100001.) 

fi 

4 

• UOCLASSIFIED 

PECIAL HANDLING 

PAGE 47 or 62 

ION CHANGE NOTICE' DATE 15 March 66 

NO. 2 SUPERSEDING 

I. ECP NO. 

. NA 

2. CONTRACT END ITEM NO. 

MOL System . 

3. SPEC. NO. 

SS-MOL-1 

4, r7r1NTR ACT 

.Program 632 A 

.5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. . 

3411/112 

6. EFFECTIVITY 

MOL Program 

. • 7. TEXT CHANGE 

Paragraph 3 .3.5.3 Functional Interfaces .(U) 

F.: 
ANDLNG3,,,,2 

NRO APPROVED FOR .-

RELEASE 1 JULY 2015 

• SfiEGAAL hANDLING 

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. 

A 

3. 3. 5. 2. 5 AGE 

3. 3. 5. 2. 5. 1 Crew Support Ili) 

Facilities shall be available rit 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.. 

3. 3. 5. 2. 5. 2 Pressure Suit (U) 

rt 

4 

1 

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. 

1.4j/ 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. 3. 4 Contract grid 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.) 

r 
SPECIFICATION CHANGE NOTICE 

NO. 3 

2. CONTRACT END ITEM NO. 

MOL System 

SSS 3 -1 

PACE: 18 25 

DA,-25 Apr 66 

3. SPEC. NO. 

SS-MOL-1 

• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

i`;i1.:1.1MINAKY 

(Z) 

1. LOP NO. 

N/A 

4. CONTRACT 

Program 632k 

E. EFFECTIVITY 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-113 

TEXT CHANGE 

3.3.6.1.1 Minimum Payload Performance. (Isick) 

Change "32,000 lb Orbiting Vehicle" in first sentence 

to read "33,000 lb Orbiting Vehicle". 

!.; 
I NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

3. 3. 6 Titan III System Segment (U) 

The Titan III 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 Nc3 SAR) 

, 3 

st: (5,b) 

, 000 

The Launch Vehicle shall be capable of launching a 32,-0-90 lb Orbiting 

Vehicle into an 80 deg 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 

yaw steering to meet range safety requirements should be subtracted 

from the above value. Estimates of such decrements associated with 

orbit inclinations other than 800and/or yaw steering requirements 

are tabulated below. 

Orbit Inclination Payload Decrement 

*80° 430 

*82° 500 

*84° 620 

*86° 800 

88° 1020 

90 ° 1250 

95° 1790 

97° 1980 

100° 2230 

*Yaw steering predicated on estimated range restrictions. 

qPrri HANDLINGii3 

Thts document roroo,n, mlormonon nflect.ng the notional defense of the United Slates within ihe meaning .1, the 

10fle 18, U S C Section 793 and 794, the tfonsfoifsion of which on any manner to an onoofho•.zed pefsoo is of oh,i,feel he 
n 

PROGRAM Nu.L. 2 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Li PRELIMINARY 

FINAL 

CE 

SSS-233-1 

pAcy=.19 oF 25 

SPEC:FICAT:ON 

■.1..) -:2 

C:-.:ANCE" .':07 

NO. 3 

1, ECP NO. 

N/A 

SP-C. 6. 

SS- MO L-1 

2. CONTRACT END ITEM NO. 

MOL System 

! 3 . 

4. CONTRACT S. CONTRACTUAL AUTHORITY 1 - r OPPOSITE SPEC. PAGE NO. 

Program 632A CCN I 3-114 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.6.1:2 Insertion Accuracy N. 3.SAR) 

Delete the word "nominal" from the first line. 

Paragraph 3.3.6.1.3 Launch-on-Time 

Change to read as follows: 

The Titan III System Segment (AGE, Launch Vehicle, and Facility) 

shall have a 0.90 probability of meeting a one hour launch window on 

any ono of three successive days specified two weeks in advance of the -

scheduled launch date, at which time the status of the Titan III 

System Segment shall be: 

(a) Subsystem checks complete. 

(b) Titan III System Segment ready to start initial Combined 

System Test (CST). 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 'SEER{ SPECIAL HANDLING 

3. 3. 6. 1. 2 Insertion Accuracy SAR) -Ft I,f91e.. 

(SC g "-Dde 

The required insertion accuracy from the iterrrrirree4- 80/130 n orbit• 

shall be as follows: 

3o-Insertion Accuracy 

Primary Guidance Secondary Guidance 

Inertial Velocity (tangential 12 fps 

velocity) 

Inertial Flight Path Angle O. 05 deg 

Altitude 1 n mi 

Out-of-Plane Velocity 10 fps 

Out-of-Plane Position 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 Nc4) 

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 \-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 'SECALSPEGiAL iikANDLING 

This dor,nent ronanns ,otorma non a 'letting the no ncnol defense of the United States within the eneqn,ng of the Espioncvje laws. 

title 113. U S C Section 793 and 794. the transmission of which in any mann., to on ,,nnythc,ized person is prohibited by law 

4 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 --Hag-SPECIAL HANDLING 

• 3. 3.6. 1. 6 System Monitoring During Ascent(U) 

A capability to monitor critical events and system status during 

ascent shall he provided to the Gemini B and mission control. 

3. 3. 6. 1. 7 Orbiting Vehicle Separation (U) 

The OV shall 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. 

3. 3. 6. 1. 8 Trajectory Constraints (U) 

The dispersed 3 sigma ascent trajectory shall not exceed MOL 

system constraints. 

3. 3. 6. 1. 9 Induced Oscillations (U) 

A 

The Launch Vehicle longitudinal oscillations will not induce sustained 

oscillations in the OV /Booster Interface in excess of 0. 25g peak-topeak in the frequency range of 5 to 30 cps. 

3. 3. 6. 1. 10 Yaw Steering X-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'(5..-3) 

The Launch Vehicle shall accept a programed positive insertion 

flight path angle (y) up to 0.4 deg with a granularity of no more than 

0.05 deg. 

Peculiar Performance and Design Requirements 

Malfunction Detection System (U) 

A Malfunction Detection System (MDS) shall be provided to sense 

impending catastrophic or degrading failures. MDS paths and signals 

I ki..■4141,L.. h Li iitai 15 

IniS document contains information affecting the notional defense of the Uni t ed States within the meaning of the Espionage lows. 

Title IS. U S C , Section 79] and 704, the Pansmissron of which in any manner to on unoWhor.ted person is prohibited by low 

3. 3. 6. 2 

3. 3. 6. 2. 1 
WO APPROVED FOR 

RFLEASE,1 JULY 2015 liANDUNG 

o PRELIMINARY 

[I] FINAL 

CATION CHANGE NOTICE 

NO. 2 

I 

PACE. 48 OF 62 

DATE 15 March 66 

SUPERSEDING 

1. ECP NO. 2. CONTRACT END ITEM NO. 3. SPEC. NO. 

NA MOL System SS-MOL-1 

4. CONTRACT 5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

Program 632 A 3-11. 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.6.2.2.1 Redundant Guidance System (U) 

Change to read: The Gemini B IGS shall backup guidance for 

the Titan IIIM system IGS for Stage I and Stage 

II flight. Automatic and manual switchover 

capability shall be provided. Manual switchback 

capability will alSo be provided. 

4 

1 

c777 c! Dr:r 1 

■+, „ U-H,iida' 

11, ,q!liv;P., 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 '1E11E4-SPECIAL HANDLING 

shall be redundant. Escape shall be manually initiated; however, provisions 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. 

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. 

Verification of an orbit 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 

.1TRET__,SPEC U-1 liANDLING 

(c) 

• 

7t. 

This iforuni.int (onioins inf o,,,01,0, of fe,ting the notional defense of the United States within the rneon.ng of the E soinnn)e 

Title 18. U S C Section 793 and 794. the tronsmnssion of whfch in any monner to on unov ,ho ,reri or son prohibited by 19 . 
UNCLASSIFFT 

ON MILIVICIWAN DtifeE Ma 

r-. 

NO. 2 SUPERSEDING 

NRO APRROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

FINAL 

1. ECP NO. 

VA 

4.. CONTRACT 

Program 632 A 

6. EFFECTIVITY 

MOL Program 

7. T XT CHANGE 

2. CONTRACT END ITEM NO. 

MOL System 

5. CONTRACTUAL AUTHORITY 

3. SPEC. NO. 

SR-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-117 118 

Paragraph 3.3.6.2.4 Performance Constraints (U) 

Change first sentence to read: The Launch Vehicle, for a 

nominal trajectory, shall be constrained to the following: 

Add subparagraph (d) as follows: 

(d) Dynamic pressure at Mach 1.2 shall not exceed 

830 psf. 

Paragraph 3.3.6.3 Fucntional Interfaces (U) 

Change to read: (Functional interface documents shall be 

listed here when defined and approved in accordance 

with IFS-M0L-100001.) . 

4 

yy 

4 

SPE(J1:AL 7-0 

firr-L 01.3 tA 

wirr Ps 717o J- kc 
7 I 

I 

• ' • SSS-233-1 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Paragraph 3.3.6.3 Functional Interfaces (U) 

Change to read: 

here when 

(Functional interface 

defined and approved in 

documents shall be listed • 

accordance with IFS-MOL-100011.) 

SPECIFICATiON23 FINAL NO. 3 

Lioct 

suPERsED:::3 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL -1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CON # 

FILE OPPOSITE SPEC. PACE NO. 

3-117/118 

6. EFFECTIVITY 

MOT Prn!rrm m 

7. TEXT CHARGE 
• 

4 

I 

• tEggiSPECIAL HANINJG 

(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 Launch 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/ft 2 

3. 3. 6. 3 Functional Interfaces (U) 

____-7(Functional interfaces shall be listed here when defined by the cogni- 

_3 zant Interface Control Working Group-ICWG) 

(0,e/ 

Cr 3. 3. 6. 4 Contract End Items (U) 

411 (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. ) 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

r 

SPECJAL HANDLING 

3-117/118 

ihrs document contains information affecting the notional defense of the United Stoles within the meaning of the Espionage taws. 

Tole 18. U.S C Secti on 793 and 794. the transmission of which in any manner to an unoothar ■ red person is prohibited by low 
SSS -233-1 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

EC. 2 

2. No. 

4. CONTRACT 5 • CONTRACTUAL AUT.:OR:TY FILE OPPOS:TE SPEC. ;DACE NO. 

?-,70:7,:a 63;A 

3.EFFECTIV:TY 

7. TEXT C':iANC,LI 

2'--.1—,:•-2)-'aPla 3. I L 1 no.;,:tc•:d 

LNA3 to rea6. 0V53 
.4 

111.11.711 3-119 

4 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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. 1 Allocated Performance and Design Requirements 

Required facilities for MOL System operations include the Initial 

Launch Capability (ILC), an Orbiting Vehicle A so,-*rbly Building 

e/58 

/frit'619 t49-V-A-334, an Engineering and Operation Facility, an Operational Readi- 

,04 ) )` nes s Unit, the Contractor Support Facility (CSF), Hazardous Handling 

SPECIAL HANDLING 

si 

Building, Pyrotechnic Storage Building, Miscellaneous Administration 

• Building, and an Operational Training and Evaluation Facility, all to 

be located at VAFB. 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 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

o PRELIMINARY 

El FINAL 

!'!' P 5/4; Un 

61E iiiaDLING' DATE 15 March 66 

50 or 62 

AT E 

SUPERSEDING 

1. ECP NO. 2. CONTRACT END ITEM NO. 

N/A MOL System 

4. CONTRACT S. CONTRACTUAL AUTHORITY 

Program 632A 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

3. SPEC. NO. 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-120 

Paragraph 3.3.7.2.2 Industrial Area (U) 

Change the first sentence to read: Use of VAFB industrial 

area facilities by the Gemini B and the Laboratory 

prior to entering the ILC shall be minimized. 

Paragraph 3.3.7.2.3.1 Receiving Inspection and Storage Facilities (U) 

Change the first sentence to read: Environmentally controlled 

areas shall be provided for the receipt and inspection 

of the Gemini B. Provisions shall be made for the 

installation of retro rockets and certain pyrotechnic 

devices in the Gemini B segment. 

4 
NRO APPROVED FOR SSS -233-1 

RELEASE 1 JULY 2015 

7-• F :NA L .:3. . 

. _ . 

2. 

S 

O. 

4. OT-ACT ■ S. CONT:SACTU:-.L SC. Ptl.GE 

G. ::'FEC,TIViTY 

7.1 

7. 

?L.. 3. 7,,; 3 0,-, ..; ' ( 

IC: je (Li) 
SPECIAL rANDLING 3-120 

■■••••■•• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 ' h l SPECIAL HANDLING • 

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 

fq The ILC Launch Control Center (LCC) and connecting cable ways and 

ti ducting between the AGE vans and the Launch Control Center shall 

I

accommodate the MOL System AGE installation. Communication lines 

c.`-;connecting the launch complex and the Launch Control Center shall 

Isatisfy MOL system requirements. 

.5'6) 3. 3. 7. 2. 2 Industrial Area 

Use of VAFB industrial area facilities by the Orbiting Vehicle prior to 

ri entering the ILC shall be minimized. New facilities or modifications 

re; to existing facilities shall be provided as follows: 

3.3.7.2.2.1 Engineering and Operation Facility 

Engineering and Operation, and Contractor Support Facilities shall be 

provided for the individual segment contractors and Air Force and 

Aerospace personnel. (5(.11/3 ) 

Sviy0/2.71- 

3. 3, 7. 2. 3 Orbiting Vehicle-Are-st-rrri:3-17 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 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

PRELIMINARY 

FINAL 

SPEGIAIE WALING 

NO. 2 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

3-121 

PAGE 51 or 62 

DATE l 5 Mqrrh (V-1 

SUPERSEDING 

1. ECP NO. 

Program 632 & 

6. EFFECTIVITY 

MOL Program . . 

7. TEXT CHANGE 

2. CONTRACT END ITEM NO. 

MOT. Ssrctem 

5. CONTRACTUAL AUTHORITY 

3. SPEC. NO. 

NA 

4. CONTRACT 

Paragraph 3.3.7.2.3.2 Orbiting Vehicle Subsystem Maintenance Area (U) 

Change title to: Laboratory Vehicle and Gemini B Subsystem 

Maintenance Areas (U) 

Change paragraph to read: Subsystem maintenance areas shall 

be provided for possible modifications and/or maintenance 

found necessary on subsystems that are removed from ,the 

Gemini B or the Laboratory Vehicle. Areas in the contractor support facilities shall be used for this function, 

where possible. 

Paragraph 3.3.7.2.4 Pyrotechnic Receiving, Test and Storage Facilities (U) 

Change the paragraph to read: A pyrotechnic receiving, test, 

and storage test facility shall be provided at a remote 

location for receiving and testing of explosive devices. 

Provisions shall be made for installation of explosive devices 

in the Flight Vehicle at the launch pad. 
• 

Lk) 

N 

t.4 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

of the OV system, w lc wi 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) 

A pyrotechnic receiving,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 Control N,c4) 

Facilities shall be provided at the Satellite Test Center (STC) at 

trol 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. 

itANOLING 3-121 

FORM This document contains Aormation 1) in .

tes 

defense of the United States within the meaning of the Espionage taws, 

SSD AUG 62 20B Title IS. U.S.C., Section 793 and 19 '•=4, nsm;ssion of which in ony manner to on unauthorized Person is Wohiboed by law 

Wm. 

Sunnyvale, California for housing all powered flight and Mission Con- 1 

, 
M.(1 

(5 n E r4U.1 figar 

UNCLASSin9 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

FINAL 

1. ECP NO. 

NA 

4., CONTRACT 

Program 632 A 

PAGE 52 or 62 

DATE 1 5 Mn rrh 66 

NO. 2 s. SUPERSEDING 

2. CONTRACT END ITEM NO. 3. SPEC. NO. 

MOL System SS -MOL -1 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-122 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.7.3 Functional Interfaces (U) 

Change to read: (Functional interface documents shall be 

listed here when defined and approved in accordance 

with IFS-MOL-100001.) 

r 

' URFA A 

EJTA;Lli L HANDLING 

CATION CHANGE NOTICE 

• 
Bioastronautic Operational Support Unit (Deleted) 

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.) 

" n 14 1.}.41441 lOritaa tow'. 

D Ec! ALy N 

any manner to an unouthor.ted person is protulpted by low 

3-122 

This document contains onformation 

Tale 18. U.S C.. Section 793 and 794, the tranitilss4inr; 

'94941,4180 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

L HANDLING 

3. 3. 7, 2. 7 Operational Training and Evaluation Facility (\-4) 

Facilities shall be provided 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 perI

sonnel continuously on duty. This facility shall be located relatively 

close to operational training and evaluation facility. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET SPECIAL HANDLING 

3.3.7.5 Mission Payload Peculiar Facility Requirements 

Adequate provisions shall be made in the checkout, maintenance and launch areas for DORIAN enrionmental 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 3-122.1 
NII30 APPROVED FOR 

RELEASE 1' JULY 2015 

0 PRELIMINARY 

E] FINAL. 

iULING 

PACE 53 or 62 

DATE 15 March 66 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END rrem NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-123 

6. EFFECTIVITY 

MOL Progran 

7. TEXT CHANGE 

Paragraph 3.3.8 Launch Operations System Segment (U) 

Change the last sentence in the second paragraph to read: 

A further requirement is the design, installation, checkout, 

and validation of the AGE/OGE, to be capable of performing 

prelaunch and launch verification tests on both the integrated 

OV and the Flight Vehicle. 

F 
SECgliFIEPPILTGIIA.

L HANDLING 

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 prelaunch 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 to include experiments payload. It 

includes certain training and bioastronautic preparation and readiness 

of the flight crew at the launch site. Additionally, launch site ground 

v. 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 (\-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 

NRO APPROVED FOR 

RELEASE 1 JULY 205'3 

9 

• /1'4 . 3 . 8 

This docvmeni contain, informalion 

Title 18. U.S C • Section 793 and 791,p.... t$441 

" 

3-123 

tam . 

oeren of the Untied Siotes within the meaning of the Espionage tows. 

which in any mann, to an annul honted person Is prohibited by low 
PAGE _14.- OF 62 

DATE 15 Ma Ty. h AA 

SUPERSEDING 

SPECIFICATION CHANGE NOTICE 

NO. 2 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

0 PRELIMINARY 

ID FINAL 

ssinE 

6ri.tArt

p i. 1-IA101.111G 

Ali 

. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL Svqtem 

3. SPEC. NO. 

SS—MOL4. CONTRACT. . 

Program 632 A 

S. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

3-124 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3 .3.8.3 Functional Interfaces (U) 

Change to read: (Functional interface documents shall be 

listed here when defined and approved in accordance 

with IFS-MOL-100001.) 
NRO APPROVED FOR SSS-233-1 

RELEASE 1 JULY 2015 

P.:MINAF-.Y 

7,7 

• 

2 cr_)N".:1-.ACT 1: 

C...ONMAC.T CON'2:AA(.::".'LJA.L., A ! 

CC // 

CI. 122 FFT.0 TIV :TY 

7. TEXT CHANGZ 

P....1.rL.izr2.pi-, Gro C: (u) 

Mz.ximum c.11owable ground wi-a spoeds for tr,,nsport, lauhcn 

mating and other operations shall bo specifiea herein when oste.isned 

from contractor studios. 
EVIL HANDLING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

any 

(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 by Mission 

Control at STC. From the start of countdown until the ground instrumentation systems used during ascent become primary, the LCC 

shall function 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) 

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 

3 3. ". 

3. 3 . 8. 3 Functional Interfaces (U) 

6 

4111 

RA 0-0-k- ft' 

effectiveness (paragraph 3. 1. 3). 

(Functional interfaces shall be listed here when defined by the cogni--\,fi" 

zant 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 system segments. ) 

3-124 

This document contains information affecting 

Tole 113, U S.0 Section 793 and 794. the t 

" r P 

" LiPt. 4 Lc"' I-111U men - 

United Stoles within the meaning of the Espionage Laws, 

f n any manner to on unauthorized person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLING 

3.3.8.5 Mission Payload Peculiar Launch Operations Support 

Mission payload launch operations support is required for 

the planning and manning effort associated with the installation, checkout 

and use of the AGE, MPSS simulator and MPSS AVE. 

The MPSS arrives at VA.NB integrated with the LV. Following 

inspection, it will be prepared for integration with the Titan III. 

Interface inspection will be performed prior to lifting the LV for vertical 

mating with the . 

Compatibility between the T-III and LV will be demonstrated 

before mating of the Gemini B is accomplished. 

Before any hatches are opened for internal inspection, 

maintenance, or other operations, the environmental enclosure must be 

arranged to provide the required level of cleanliness of temperature and 

humidity control. 

Ordnance and pyrotechnic devices will be armed and circuitry 

verified during the R-Count. 

3.3.8.5.1 Contractor Support 

MPSS Contractor Support will be required to develop plans, 

requirements, and procedures and to operate the MPSS equipment at VAFB 

during the pre-launch and launch phases. 

Particular emphasis will be placed on procedure and data 

management to assure that timely, effective, and pertinent information is 

provided. 

Payload contractors will provide training facilities and 

train their personnel for the functions that they will perform during the 

processing of the MPSS. They will provide trained personnel to support all 

other functions associated with the launch of the LV. Development of 

trouble shooting procedures and corrective actions will be undertaken early 

in the program so that they will be available for use during ascent and 

on-orbit operations. 

SPECIAL HANDLING 

3-124.1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 NIG 

3.3.9.5 Mission Payload Peculiar Operations and Support Requirements 

3.3.9.5.1 Ground Support System Requirements 

The major ground support system requirements for command 

and control of the MOL 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 last set of tracking data shall not be greater 

(2 ) than 0.3 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 and command generation within one-half hour 

of receipt of a changed target list and/or new target weather information. 

c. Transmission of orbit parameters commands 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). Process telemetry reports of photographic activity in real time or near real time for target selection and 

subsequent use in preparation of payload reports. As an objective, all 

parameters of interest to the user shall be listed and delivered prior to 

delivery of the processed film. 

e. Analysis of MOL 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 

MOL System components within one-half hour of transmission of telemetry 

data to an SCF tracking station. A capability for preliminary status analysis 

of major MOL subsystems while the transmission is taking place shall also exist. 

3-140.1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SECRET SPECIAL HANDLING 

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. 

g. Verification of commands and data to assure compatibility with the vehicle and the intended operations. 

SPECIAL HANDLING 3-140.2 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

S'EtRELSPECIAL HANDLING 

PRELIMINARY 

a FINAL 

PAGE 36or 52 

SPECIFICATION CHANGE NOTICE 

NO. 1 

DATE 20 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -125 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9 FLIGHT OPERATIONS AND SUPPORT SYSTEM SEGMENT 

Change as follows: 

Paragraph 3.3.9 FLIGHT OPERATIONS AND SUPPORT SYSTEM 

SEGMENT N3 SAR) 

Delete words in fifth line "through flight and data retrieval" 

and replace with following: 

"to mission completion including laboratory disposal, all data 

retrieval and crew recovery when applicable." 

Paragraph 3.3.9.1 MISSION CONTROL OPERATIONS 

Change paragraph as follows: 

Paragraph 3.3.9.1 MISSION CONTROL OPERATIONS \-3 SAR) 

Change third sentence to read as follows: 

"The SCF will provide the on-orbit network, Mission Control, 

and data capsule recovery support." 

b) Add at start of fourth sentence: 

"For manned flights" 

c) Add after "recovery forces" in last sentence the following: 

"for the Gemini B and flight crew." 

SPECIAL ACCESS REQUIRED 

SENSITIVE AREA 

PROGRAM NO. 43=A IDENTITY4 

This document contains infonnotion affecting the notional defense of the United Slates within the meaning of the Espionage lows. 

Tide 113, U.S.C.. Section 793 and 791, the transmission of which in any manner to on unotahorized person is prohibited by low. 
IDLING 

Fli stem Se • ment \4) 

NRO APPROVED FOR 

RELEASE 1 JULY 29 "1 

/Y1--) 

IG 

C . 3. 9 

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 

through flight crew recovery and data retrieval. 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. 3. 9. 1 Mission Control Operations \4) 

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 provides the on-orbit network and Mission Control. Certain supplemental support will be 

provided by NASA (Goddard) and the National 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 networks, with additional services obtained through established 

DOD channels. Recovery forces will be 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 

FORM this document contains information 

SSD AUG 62 20B Title 18, U.S C., Section 793 and 7 

3-125 7 •••• FN. 

defense of e nited States within the meaning of the Espionage in ws, 

in any manner to on unauthorized person is prohibited by low 
SPECIAL HANDLING 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE 37OF 52 

DATE 20 Jan 66 

SUPERSEDING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

® FINAL 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -126 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.1.3 VEHICLE/CREW CONTROL 

Change as follows: 

Paragraph 3.3.9.1.3 VEHICLE/CREW CONTROL Nv3 SAR) 

a) Change first sentence after words "lift-off until" to read 

as follows: 

"mission completion, including data recovery and crew/recovery 

when applicable." 

SPECIAL ACCESS REQUIR ED 

SENSITYVE AREA 

PROGRAM NO. 4314 IDENTITY,' in 

B D Nr1 U 

.This document contains information affecting the national defense of the United States within the meaning of the Espionage lows, 

Trrle 18, U.S.C.. Section 793 and 794. the tionumssion of which in any manner to an unauthorized person is prohibited by law. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CIAL HANDLING 

handling services, shall uring 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 

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 Mission Control shall be revalidated through the instrumentation networks and the required display/control functions activated at 

the STC. 

1 

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 (k-4) 

Launch area and worldwide instrumentation data handling and communications 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 (1\-4) 

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 

4. 

3-126 

0 QM 

G 62 ZUB tole 18, U.S.C, Section 793 and 794, the Ira i 

This document contoins tnformation affecting tii10., ot 

c n any manner to on unauthorized pe,son is prohibited by low 

; n it) ; 

Idled won in the meaning of the Espionage Laws, 
SPECIFICATION CHANGE NOTICE 

NO. 1 

iteilOECIAL HANDLING 

PAGE 38 or 52 

DATE 20 Jan 66 • SUPERSEDING 

NIRO APRROVED FOR 

RELEASE 1 JULY 2015 

0 PRELIMINARY 

121 FINAL 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -127 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.1.7.1 TRACKING 

Change as follows: 

Paragraph 3.3.9.1.7.1 TRACKING?3 SAR) 

a) Change first sentence after "mission control functions" to 

read as follows: 

"including discrete commanding, and slow malfunction 

detection and crew safety when applicable." 

b) Delete word "both" in second sentence on fourth line. 

Paragraph 3.3.9.1.7.3 COMMAND N4) 

Charige a follows: 

a) Delete words "and the guidance system" at end of first sentence. 

b) Delete third sentence. 

SPECIAL ACCESS REQUIRED 

AREA 

PROGRAM NO. Z52 er 

SENSITIVE 

IDENTITY 4 Pt 

1L w? ___GRET:SPECLAL h,-,AL,tg,y03 

:This document contoins information affecting the notional defense of the Unite

d Stores within the meaning of the Espionage lows, 

Title 18, U.S.C.. Section 703 and 794. the ttonsenitsion of which in ony manner to on u

nauthorized person is prohibited by low. 
recovery support. 

HANDLING 

During the countdown, recovery forces shall be 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

brought to an appropriate state of readiness. 

3. 3. 9. 1. 6 Instrumentation and Communications Network -4) 

During launch preparations local launch area instrumentation systems 

shall be brought on-line. Final data acquisition parameters shall be 

transmitted to the worldwide 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 N-4) 

The ground tracking systems shall derive position information to 

assist in the Mission Control functions, including discrete commanding, slow malfunction detection, and crew safety. 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. Tracking of the Gemini B spacecraft and 

impact prediction are required after an abort during powered flight. 

3. 3. 9. i . 7. 2 Telemetry (\-4) 

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 (\-4) 

Commands to the Gemini B shall up-date displays and the guidance 

system. The Gemini B command format and rate will be equivalent 

to NASA Gemini. A command capability from the insertion ship is not 

required. The WTR command system shall provide the necessary 

range safety commands for the Launch Vehicle. 

t 

3-127 

This document contains tricot fense of the United States within the meaning of the Espionage Lows. 

SSD AUGFOR642 20B Tole I 8, U.S.C, Sect,on 793 and 794. the transmission of which in any manner to on unauthorized person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

liANULINU 

CONFIDENTIAL 

PAGE 39OF 52 

DATE 20 Jan 66 

SUPERSEDING 

PRELIMINARY 

EY] FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL -1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-128 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

a) Change Paragraph 3.3.9.1.7.5 title as follows: 

Paragraph 3.3.9.1.7.5 DATA FLOW, COMPUTATION, AND 

DISPLAY (MANNED) l'S-4) 

Add Paragraph 3.3.9.1.7.6 as follows: 

Paragraph 3.3.9.1.7.6 DATA FLOW, COMPUTATION, AND 

DISPLAY (AUTOMATIC MODE) (1\-4) 

For automatic mode flight, 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 system utilized for manual 

flight, and outputs shall be displayed in real time at the mission 

control center. 

CONFIDEN:4/". 

:This document contains information . n4 14; tip defe e oi194-1.1iti.tea • giotes wohin the meaning of the Espionage tows. 

Tdle 18, 

QP.Frip l„ Al HANDLING 

liTA 

U.5 C.. Section 793 and 794, the'itonsmiss.on of which in ony manner to on unouthonzed person is prohibited by law 

5S;:\ 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 9. 1. 7. 4 Voi e •m unications 

IAL HANDLING 

( k4) 

67e,0-74// 

3. 3. 9. 1. 7. 5 16-Data Flow, C putation, and Display (\-4) 

Metric tracking data and selected Launch Vehicle and Gemini B telemetry data shall be used for trajectory, IIP, flight crew 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 b determined. 

z5.3j./.7 C. - Se4/74 / da 

Voice communications between Mission Control and flight crew shall 

be continuous. 

3. 3. 9. 1. 8 

3. 3. 9. 1. 8. 1 

Early Orbit Phase 

Tracking (\-4) 

At least three valid metric tracking passes shall be obtained to establish the orbit for control purposes. 

3. 3. 9. 1. 8. 2 Telemetry ( 4) 

For this flight phase, telemetry data shall be obtained from both the 

Laboratory and Gemini B. Data from both sources shall be simultaneously selectable for retransmission to Mission Control. 

nLf 

---"/ 3-128 

FORM This document contains inforrnotio 

'vU G 62 20B Title 18, U.S C., Section 797 and 7 

1 defense of he e aw,, TIEDLINGionage lows, 

n any manner to an unouthor ■ zed person is proh■ bited by law 
El PRELIMINARY 

El FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

40 52 PAGE OF 

riTh DATE 7 0 n (.4.) 

SUPERSEDING 

fVEAAPSPERAZIAL HANDLING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-129 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.1.8.3 COMMAND ( c3 SAR) 

Change last two sentences to read as follows: 

"A secure command capability shall be provided for the Laboratory 

and mission payload segments." 

SPECIAL ACCESS REQUIRED 

SEMITIVE AREA 

PROGRAM NO. (.324 IDENTITY/. 

a. 

SPECIAL HAS bLIN6 — 

.This document contains informotion affecting the national defense of the United Stoles within the meaning of the Espionage lows. 

•Title IS. U.S.C.. Section 793 and 794. the transmission of which in any manner to an unauthorized person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

5 1.2 

) 

Stelitt 

SPECIAL HANDLING • Ao, 3.3. 9. 1. 8. 3 Command (\-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 only. Vehicle and Mission Payload Segments. 

3, 3. 9.1. 8. 4 Voice Communications (\-4) 

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. 

3. 3. 9. 1. 8. 5 Data Flow, Computation, and Display \.4) 

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. 

On-Orbit Phase N-4) 

Tracking (\4) 

Tracking shall be only that necessary to provide sufficient ephemeris 

accuracy for control purposes. Supplemental tracking shall be called 

up to provide additional accuracy as requiredby the mission. 

riA'LLiNG 

3-129 

This document conto,ns,ntomsoner, a ffectingthe nobonot defense of the United Slotes within the meontno of the Estnonnste 

Title IS. U S C , Se:hon 793 end 794 . the tronsinmion of which in ony wanner to an unpohortred person is prohibitedby Ins 

3. 3. 9. 1. 9 

3. 3. 9. 1. 9. 1 

k. 
AIR° APPROVED FOR 

RELEASE 1 JULY 2015 

SPECIAL HANDLING 

PAGE 41 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

PRELIMINARY 

12 FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -130 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.1.9.5 DATA FLOW, COMPUTATION, AND DISPLAY 

Add after second sentence of second paragraph the following: 

"or near real time as appropriate." 

SPECIAL HA DL1NC 

This document contoins information affecting the notional defense of the United States within the mooning of the Espionage taws, 

Title le. 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 

SSS -233 -1 

. 

2R 

. 

SE -1 

1. E.CP NO. 

INT / 

2. CONTiiACT END 

1.:0L Systcm 

4. CONTRACT 

632A 

5. CONTRACTUAL AUTI-1.0'..;:TY 

CON I 

F;LE `OPPOSITE SPEC. PACE NO. 

3-130 

G. EFFECTIVITY 

7. TEXT CrtANCE 

l'araraph 3.3.9.1.9.5 D..,7,a nov, Cc..outat:.= 7 kT) 

Delete-the la.et sent .nce of the first parc:;r_.)h, ":La;,ion ::..ata in the 

20 mb/nee. rare shall be rzesented to mis.Y.Lon esqmeat ia video form 

or down converted as appropriate." 

t. ; 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 9. 1. 9. 2 Telemetry (\-4) SPECIAL HANDLING 

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 shall be 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 Commandzsc3 SAR) 

Commands for the Laboratory shall be the same as those for the early 

orbit phase with additional allowance for growth in mission information 

system requirements. Secure commands shall be provided. 

3. 3. 9. 1. 9. 4 Voice Communications N4) 

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. 

,$)d t 26 

3. 3. 9. 1. 9. 5 Data low, Computation, and Display N\-4) 

The data handling system shall have the capability during a mission to 

adapt 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. 

3 , 0•2 a cyLA 6d) .6404-: 

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. 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 functions. 

jA 'J 1 

Tht% cnoro,n, ,nformoboo oflecbng the notional detente of the United States wohon the meorong of the Espionage Lows. 

Tette le. U.S C Section 793 end 794. the Imetsaossion of which in any manner to an unoothoozed person it prohrbtled by low 

Jc 

3-130 
4 ISPECIAL HANDLING NRO APPROVED FOR 

R4LEASE11, JULY 2015 

PAGE 55 OF 62 

DATE 15 Mnrnh 6C) 

SUPERSEDING 

SPECIFICATION CHANGE NOTICE 

NO. 2 

PRELIMINARY 

13 FINAL 

I. ECP O. 3. SPEC. NO. 2. CONTRACT END ITEM NO. 

NA 

4. CONTRACT 

SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 

MOL System 

S. CONTRACTUAL AUTHORITY 

Program 632 Al 3-131 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.1.10 Re-entry Phase (U) 

Change title to: 19-entry Operations 

Paragraph 3.3.9.1.10.5 Data Flow, Computation, and Display \-4) 

Delete second sentence: As a result of the limited loiter 

time and back-up capability of the Gemini B, 

the mission control function shall provide extensive 

support for the flight crew. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3-) SPECIAL HANDLING 

3. 3. 9. 1. 10 Re-entry Phase 

3. 3. 9. 1.10.1 TrackingN-4) 

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 Telemetry -4) 

Telemetry capability will support the Gemini B. Support shall be the 

maximum achievable with the primary network stations with voice 

coverage from additional stations. 

3. 3.9.1. 10. 3 CommandX- 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 shall not be provided. Ground command control will provide 

retrofire times and sequence for both planned recovery and contingency 

areas. 

3.3.9.1.10.4 Voice Communications (\ 4) 

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 (\-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 provide 

extensive support for the flight crew. Close flight crew/Mission 

Control interaction shall be effected for the initiation of the re-entry 

sequence. 

SPECIAL HANDLING 

. 1EttRE-T-'■ 3-131 

Ihn docoroontontain, information affecting the noti

onal defense of the United Slates within the meaning of the Espionage tows, 

hide 18, U S 

c 

 sec tion 793 and 794, the tiansmission of which in any manner in an vnnuihrtizfid aeiSOn is piohibired by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL VIANDLING SECRET 

PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE 42 or 52 

DATE 20 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

S. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -132 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.2.1 SATELLITE TEST CENTER(\-3 SAR) 

Add after first sentence the following: 

"as applicable for manned or unmanned flights." 

SPECIAL ACCESS PEQUME1YSENSIIIVE AREA 

PROGRAM NO. 432 A IDENTITY oi 4 a - itn 

'11614EL- SONt /\\\V: 

.This document contains ,nfo,motion affecting the notional defense of the United Stoles within the meaning of the Espionage Lows, 

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

RELEASE 1 JULY 2015 

3. 3. 9. 2 Flight Operations Support N\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 cas3 SAR) 

The STC shall provide the following capabilities: 

(a) Control and display consoles for powered flight, 

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 

SPECI4L HANDLING 

4'A G 

r r r, ; tr-r, r 

nr 

• 

3-132 

Thot document conroins information of (erring thenotional defense of the United States within the meaning of the Espionage Laws. 

Title 18. U S C . Section 793 and 794, the tfon,rnifsion of which in any manner to an unoufhoriced person is prohibited by low 

(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 

(j) Real time computer complex for trajectory 

and orbit related computation 

(k) Communications switching, terminal, technical 

monitoring, and control facility 
PAGE 43 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL -1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-133 

6. EFFECTIVITY 

MOL Program 

ARO APPROVED FOR 

RELEASE 1 JULY 2015. 

SijELiAl. HANDLING 

• PRELIMINARY 

O FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

9. TEXT CHANGE 

Paragraph 3.3.9.2.2 OPERATIONAL COMPUTER PROGRAM SUPPORT 

Change as follows: 

Paragraph 3.3.92.2 OPERATIONAL COMPUTER PROGRAM 

SUPPORT 1%.,3 SAR) 

Add to first paragraph the following: 

"as applicable for manned or unmanned flights." 

SPECIAL ACCESS REQUIRED 

SENSITIVE AREA 

PROGRAM NO. 632 A IDENTITY A tS 

rt 

s?f-ct;If'l "

PAL) 

.This document coniams information affecting the notional defense of the United Slates within the meaning of the Espionage lows. 

• title 18, U.S C.. Section 793 and 794, the transmission of which in any manner to an unauthorized person is prohibited 

by low. 
(a) Tracking data editing and conversion 

(b) Trajectory calculations 

(c) Impact prediction (including abort AV and 

delay options) 

(d) Coordinate conversion of telemetered booster 

and Gemini guidance data 

(e) Orbit injection (including ACTS thruster and 

retro-rocket options) 

(f) Command synthesis 

(g) Orbit determination and related computations 

(h) Injection burn-time and vehicle altitude 

(i) Retrofire and recovery 

(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 

(q) Flight operations planning and scheduling 

HANDL1N93 

hts document confo,n, p■ mofion offeet,og the not ■ onol defense of she Unded Stoles w ohm the meant n9 of the EsO.onrfge tows. 

1.11e 18. U S C Section 793 and 794, the if onsrms,on of which so any moon, in no ■.;novibof .terl Ve.snn n 1,18h,b..erf by low 

• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

--sieREL SPECIAL HANDLING 

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. Z Operational Computer Program Support ( 1/4-4) 

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: 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 '1"frefig-- SPECIAL HANDLING 

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 

(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 (\-4) 

The Ground System Simulation Support shall provide the capability to 

simulate all mission phases and operations and shall provide a means 

for training flight crews, 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 communications lines to remote areas and control centers prior to a 

mission, and (5) finally developing and validating Mission Control and 

payload control procedures. 

S D E r A g t-"ArDLNG 

3-134 'IE-GREL 

this &Kamen, contains information affecting the national defense of the United Stoles within the meaning of the Espionage Laws. 

Title le, u s c.. Section 793 and 794, the transmission of which in any manner to an unouthorited person is prohibited by law 
NRO APPROVED FOR 

RELEASE _1 JULY 21 SPECIAL HANDLING 

PRELIMINARY 

B FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL -1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-135 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.2.4 NETWORK SUPPORT 

Change to read as follows: 

Paragraph 3.3.9.2.4 NETWORK SUPPORT X-3 SAR) 

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; (5) Thule, 

Greenland; 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 and on an emergency call-up 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 Antigua and Ascension; and the WTR 

installation at Wake. Present studies also consider the possibility of requesting C-band radar tracking support from some of the sites listed to 

support 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 manned or unmanned flights, skin track data from SPADATS shall 

be made available. 

SPECIAL ACCESS REQUIRED 

MISITIVE AREA 

PROGRAM NO. 432.A IDENTITYA 4 SPECIAL 14*11) 

-S-EGREL 

•Thrs document contains information affecting the nofionoi defense of the United Stores witlun the meaning of the Espionage laws. 

Trate IS. U.S C.. Section 791 and 794, the transmission of which in any manner to on unauthorized person as prohibited by law. 
NRO APPROVED FOR 

RELEASE 1 

' t 1AL HANDLING/ • 

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. 

(2) 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. 

(3) The generation of suitable simulation tapes for 

use by actual network stations. 

3.3.9.2.4 Network Support \- 4) 

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; 

(5) Thule, Greenland; 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, 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. Supplemental coverage to that of the SCF will be required during early orbits and on an 

1 \ 4,1 

6i)LU AL irtivd■J 

3-135 

This document eontotns infotrnoiton affecting the notional defense of the United Stoles ...thin the meaning of the Espionage tows. 

lilt 18. U S C Section 793 and 79d. the transmission of which in any manner to on unoulho,iteri pei%on piohibiled by low 
NRO APPROVED FOR 

:1 RELEASE 1 JULY 2015 

emergency call-up 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 

C-band radar tracking support from some of the sites listed to support 

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. Skin track data from SPADATS will be made available. 

3. 3. 9. 2. 4. 1 Instrumentation X-3 SAR) 

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 fine grain 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 (TTCV) 

capabilities of the S-band Space-Ground Link Subsystem (SGLS). 

The capability to simultaneously receive all SGLS telemetry and voice 

information from both the Gemini B and Laboratory shall be included 

at certain primary MOL network stations which 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 shall 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 for transmission to Mission 

Control in real time. 

SPECIAL HANDLING "SfeRET,_ 

This document contains rnformatton affecting the nohonol defense of the United Stoles with.n the rneamnd of the Esp.onnar InWS, 

Title 18. U S C . Section 793 and 794. the tronsm.ss.nn of which In any manner to nn unoutho•rrerf person is wohthrled by low 

—S-EDRE-T-- SPECIAL HANDLING 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

.--sEeRg_ Site iikL HAN DU Pi 6 

• PRELIMINARY 

2 FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE OF 52 

DATE 20 Jan 66 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -137 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.2.4.1 INSTRUMENTATION 1\-3 SAR) 

Change fourth and fifth paragraphs to read as follows: 

Primary network stations shall provide support to the orbiting 

vehicle backup command and telemetry systems. 

For the Manned Flights, support of the vehicle wide...1:mnd data link 

,Fin the S-band (2200 - 2300 Mc RF band shall be provided at four 

,A .0 

‘Y locations - Vandenberg AFB, New Hampshire, Alaska and a Pacific 0,e, Q.. Island site. During routine on-orbit operations, time sharing of 

status and payload data dumps and the selection and compression in 

real time of limited amount of received data for transmission to 

Mission Control shall be normal modes of operation. 

SPECIAL ACCESS REQUIRED 

SENSITIVE AREA 

PROGRAM NO. 4„;2A IDENTITY/1 

•This document contains information affecting the notional defense of the United States within the meaning of the Espionage tows, 

Trite 18, U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by low. 
SSS-233-1 

NRO APPRdVED FOR 

RELEASE 1 JULY 2015 

PLIMINAI‘tY SPEC`,FiCAT:ON 

::). 3 

PACE 25 CF 25__ 

LC' 

N/A 

2. CC.'4NiACT 1.:ND 3. 

YOL Systcla • 

S. CON-IiACTUAL. AUTO. TY 

cc 

FILL: i.'AGE NO. . CONTK ACT 

Pro7ra 632A 

G. EFFECTIVITY 

1.10L Procfram 

7. Tc:X7 CHANGE: 

SM-1 

Pararaph 3.3.9.2.4.1 intrl-Lentatios 3,=,a) 

Change the first sentence of the fifth parazranh to read: 

"For the Manned Flights, support of the vehicle 1;ricband data 

link shall be provided at Vandenerg„ 1:ew 111-.1-,pshire, and 

Tracking Stations and a fourth location to be deterlined later." 

•••• : 

k.44+ 
NRO APPROVED FOR 

' RELEASE 1 JULY 2015 

SPECIAL HANDLING 'Stefif-T— 

Primary network stations will provide support to the vehicle 375 mcs 

4 backup command system and 1 kb/sec secondary PCM link. 

4 

Support of the 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 routine onorbit operations, time sharing of status and payload data dumps and 

the selection and compression in real time of a limited amount of 

received 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. 

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 re-entry. 

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. In addition, sufficient data capsule reentry data must be provided to the 6594th Recovery Control 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 NASA networks. Sufficient channel 

capacity and reliability shall be provided to support flight crew-toMission Control voice, network stations control voice, telemetry data 

,i7hi4 document contains information affecting the nohonol defense of the United Stoles within the meaning of the Espronage lows, 

tulle 18. U S C Section 797 and 794. the Ircinswitssion of which in ony manner to an unc,thott ze 3 person is prohibited by low 

s. 
seECIAL HANDLING 

PRELIMINARY SPECIFICATION CHANGE NOTICE 

FINAL NO. 1 

PAGE 46 OF 52 

DATE 20 Jan 66 

SUPERSEDING 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3 -138 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.2.4.2 COMMUNICATIONS IS,s3 SAR) 

a) Add the following to the first sentence of paragraph two after the 

words "ground-to-space communications system:" 

"for both voice and data" 

b) Add the work "direct" to the last sentence of the second paragraph 

after the words "Secure ground communications for" 

Paragraph 3.3.9.2.4.3 DATA TRANSMISSIONN3 SAR) 

Change paragraph to read as follows: 

For Manned Flights, to achieve real time control, 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 the 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. 

SPECIAL ACCESS REQUIRED 

SEPM171YE AREA 

PROGRAM NO. 432 A IDENTITY A 

SPECIAL. 1-1.1NADUj; IteRg, 

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

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

RELEASE 1 JULY 2015 SPECIAL HANDLING 

transmission, command control, and tracking data transmission. All 

launch network stations, including the injection ship and the SCF onorbit stations, shall be netted with the STC utilizing hardline or 

equivalent circuits. Communications satellites may be used where 

appropriate. 

The use of encrypted space-to-ground, ground-to-space communications systems is required; encrypted circuits from and to the STC for 

all SCF network stations shall be provided. Full duplex voice circuits 

from the network stations to the STC shall be employed for OV-toground voice relay. The capability for remote site keying of the 

ground-to-space transmitters from the STC shall be implemented at 

all SCF stations to allow 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 relay of classified 

voice information to the STC. 

3. 3. 9. Z. 4. 3 

(\4) Data Transmission 

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. 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. 

3-138 

SPECUAL HANDLIITAY3 

•Tbis document contains information affecting the nofionol defense of the United States within the meaning of the Espionage lows, 

t,tle ts, U S C., Section 793 and 794, the transmission of which in any manner to an unauthorized person is prohibited by !ow 
Paragraph 3.3.9.3 Functional Interfaces (U) 

Change to read: (Functional interface documents shall be listed 

here when defined and approved in accordance with • 

IFS-MOL-100001.) 

.COL Program 

7. TEXT CHANGE 

4 

UOCLASSIFED 

NRO APPRDVED FOR 

RELEASE 1' JULY 2015 

thICLASSEFIED SPECIAL HANDLING 

• PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 2 

PAGE 56 of 62 

DATE 15 March M 

sur.;,:: EDING 

3. SPEC. NO. I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

IDOL System SS-MOL-1 

FILE OPPOSITE SPEC. PAGE NO. 4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY 

3 

t.

t 

6. EFFECTIVITY 
HANDLING - effiRBENTIAL-- 

3. 3. 9. 2. 4.4 Meteorological Support ( v4) 

Meteorological Support shall provide weather data obtained from 

various reporting and forecast sources 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 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). 

NRO APPROVED FOR 

RELEASPETAL 

- -2 

ncirrq fl 17 

1 

CONFIDENTIAL 3-139/140 

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

SSD AFUOGR642 20 B little 18, U.S.C., Section 793 and 794, the transmission of which in any manner to an unauthorized person is prohil,ted by low 
1. ECP NO. 

NA 

4. CONTRACT 

Program 632A 

6. EFFECTIVITY 

MOL Program 

2. CONTRACT END ITEM NO. 

MOL System 

5. CONTRACTUAL AUTHORITY 

CCN 

3. SPEC. NO. 

SS -MOL -1 

FILE OPPOSITE SPEC. PAGE NO. 

3-141 

NRO APPROVED FOR 

RELEASE 1 JULY 20IV f t 1 II A, fis 

CUli-d. 

PRELIMINARY 

El FINAL 

CONTIDEITIAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE IL _ OF 52 

DATE 20 Jan 

SUPERSEDING 

66 

7. TEXT CHANGE 

Paragraph 3.3.10 RECOVERY SYSTEM SEGMENT \.4) 

Change paragraph to read as follows: 

Paragraph 3.3.10 RECOVERY SYSTEM SEGMENT (MANNED) IVI4) 

SPECK." 

a 

CONFIDENTIAL 

document contours information affecting the notional defense of the United States within the meaning of the Espionage Lows, 

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

SPECIAL HANDLING RE 015 

241,24_ Le-0 

3.3.10 Recovery System Segmen -4) 

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 Nc4) is 

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 Force11/44) 

The recovery force shall be comprised of sea, land, and air units, 

associated crews, and specialist teams as necessary to meet the. 

performance requirements of recovery. Such resources shall be 

provided from existing government sources wherever possible and 

practicable. 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 

SitUIAL ilANOLING 

--eatinaW 3-141 

FO RM This document contains information affecting the notional defense of the United5101es within the meon.ng of the Es0.0nage Lows. 

SSD AUG 62 20B Title 18, U.S.C.. Section 793 and 794, the transmission of which in any monne• to on unauthoazed pecan is pPohihifed h, 
NRO APPROVED 

RELEASE 1 JULY CONFIDENTIAL SPECIAL HANDLING 

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. 

3. 3. 10. 3 Access and Retrieval \-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 Nc4) 

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. 

SPE HAND ING 

3-142 

This document contains information affecting 'the notional defense of the United Stores ...Whin the meeting of the Etroonoge lawn. 

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

RELEASE 1 JULY 2015 SPECIAL HANDLING 

3.3.10.5 Mission Payload Peculiar Recovery Requirements 

3.3.10.5.1 General 

Photographic record will be returned by means of Data 

Re-entry Vehicles and in the manned version via Gemini 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 DRV 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 

"I -142.1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

I --CARIENT-14-- SPECIAL HANDLING 

3. 3. 11 Test Support System Segment ( 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. 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. Test 

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 Pre-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(s) 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 kcc-4) 

In addition to providing for smooth phase-over of support services 

from pre-launch to launch, the employment of the resources in the 

; SPLI ILING Ira U ---CONFRERAL___ 3-143 

SSD FORM ,,,, 

This document contains Information of lecing the notional defense of the United States within the meaning of the Espionage Lows, 

AUG 62 LuB Ltle 18. U.S C , Seciion 793 and 794. the 1,onsrnission of which in any monnet to on unauthorized person is r,ohobited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

iz FINAL 

—Strefig--- SPECIAL 

PAGE 48 OF 52 

SPECIFICATION CHANGE NOTICE DATE 20 Jan 66 

NO. 1 SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-144 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.11.2 LAUNCH AND ASCENT SUPPORT l'k3 SAR) 

a) Add to the last sentence of the first paragraph the following: 

"For all flights" 

b) Add the following to the first sentence of the second paragraph: 

"For the manned flights, a" 

c) Delete the fourth sentence of the second paragraph. 

d) Delete "capsule" in the last sentence of the second paragraph and 

replace with "Gemini B" 

e) Insert the word "also" in the last sentence of the second paragraph 

after the words "impact prediction is". 

f) Add the third paragraph as follows: 

For the unmanned flights, a range instrumentation ship with a 

minimum capability of recording all telemetry links and performing 

impact prediction in the event of mission abort shall be provided. 

This ship shall have reliable voice communications with 

Mission Control. 

SPECIAL ACCESS REQUIRED 

SENSITIVE AREA 

3ROGRAN NO. C5414 'DORI-11'A 4 is 

.This document contains information affecting the national defense of the United States within the meaning of the Espionage Lows. 

Title IS. U.S C., Section 793 and MI. the transmission of which in any manner to on unauthorised person is prohibited by law. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

EC) FINAL 

PECIAL HANDLING 

PAGE 57 or 62 

DATE 15 March 66 

SUPERSEDING 

SPECIFICATION CHANGE NOTICE 

NO. 2 

I. ECP NO. 

N/A 

2. CONTRACT END rrem NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

5-144 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.11.2 Launch and Ascent Support Ns!;.) 

Change last sentence of second paragraph to read: 

Tracking of the reentry module and impact prediction 

is required after an abort during powered flight. 

SPECIAL 1.01Dt 

ti 

4 
FO Rh! 

U G 62 

NIISMT") 

RELEWJ HANDLING 

° t/ik, 

launch site area shall also include all the ground instrumentation 

necessary for the initial powered flight phase. Ascent support downrange shall include one range instrumentation ship to achieve downrange coverage through insertion, plus approximately 30 seconds. 

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 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 high-speed data communications with Mission Control via 

communications satellites. Tracking after insertion is required long 

enough to permit data smoothing and to provide an ephemeris of 

sufficient accuracy for initial control. Tracking of the capsule and 

impact prediction is required after an abort during powered flight. 

3. 3. 11.3 On-Orbit and Recovery Support \-4) 

Test Support for these phases includes the supplemental world-wide 

remote sites necessary to satisfy MOL Orbiting Vehicle requirements. 

Selected Eastern Test Range (ETR) and Western Test Range (WTR) 

and NASA stations shall provide support on a prearranged call-up 

basis for two-way UHF voice to minimize gaps in coverage. In 

addition, C-Band radar tracking from selected ETR, WTR, and NASA 

stations shall be provided, also on a prearranged call-up basis for 

emergency or back-up support of either the Orbiting Vehicle or 

Gemini B using the C-Band transponder located in the Gemini B. 

Metric C-Band tracking data fron-i 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. 

SPECIAL HANDLING 

3-144 

This document coninins information affecting the notional defense of the United States within the meaning of The Espionage Lows. 

2013 Title 18, 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 'LlitinftPECIAL 

HANDLING 

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. 

V 

t. 

SPECIAL HANDLING 

3-145/146 

FORM This document contains information affecting the notional defense of the United Stoles within the Intoning of the Espionage Laws, 

SSD AUG 62 20 B Title 18. U.S.C., Section 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by law 
1 NRO APPROV L EQR. 

nom , RELEASE 1 JU 

I 

• 3. 3. 12 

3. 3. 12. 1 

3. 3. 12. 1. 1 

i 

i 

I 

1 

ii 

4 

Flight Crew System Segment 

Allocated Performance and Design Requirements 

Flight Crew Complement and Performance 

Allocation Ns-4) 

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. 

3. 

3. 

3. 

3. 

12. 

12. 

12. 

2 

2. 

2. 

1 

1. 1 

Peculiar Performance and Design Requirements 

Flight Crew Selection and Training LA/ 

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 

HANDLING 

This document contains information affecting the notional defense of the Untied States within the meaning of the Espionage tows. 

Title IS, U.S.C.. Section 793 and 794, the transmission of which in any manner to an unauthorized person is piohihtled by to. 
(.] 

tr; 

ai 

Ki 3. 3.5.8.3 3. 3. 5. 8.4 

C 

fel 3. 3. 

NRO APPROVED FOR 

RE1CVE,5HANDLING -C-NFEtTitt4EaE - f_, 

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

This document Contains infOrmOtiOn affecting the nolionol defense of the United Stoles within the meaning of the Espionage tows. 

Title IS. U S C. Section 793 and 794, the tionsmission of which in any manner to on unauthorized poison is prohibited by low 
PAGE 58 OF (0 

DATE 15 11.2r,ch 66 

SUPERSEDING 

3. SPEC. NO. 1. ECP NO. 

NA 

C CONTRACT: _ 

Program 632 A 

Ui 

rrir,11/1c;t7',7,747D 

SPECIFICATION CH NOTICE 

NO. 2 

2. CONTRACT END ITEM NO. 

• mnr. System 

S. CONTRACTUAL AUTHORITY 

SS=MOL -1 

FILE OPPOSITE SPEC. PAGE NO. 

3-149/150 

NR4APM0VEDFOR 

RELEASE 1.JULY2015 

• 

El PRELIMINARY 

FINAL , 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

.Paragraph 3. 

Change 

3.12.3 Functional Interfaces (U) 

to read: (Functional interface doduments shall be 

listed. here when defined and approved in accordance 

with IFS-MOL-100001.) 
SPE.CiPti VONOLIRG 

3-149/150 

NRO APPROVED FOR. 

RELEASE 1 JuLleotidiAL 

ji~L1NG 

3. 3. 12. 2. 2 Training and Pro iency Data (Deleted) 

3. 3. 12. 2. 3 Man-Equipment Design Validation (Deleted) 

3. 3. 12. 3 Functional Interfaces (U) 

1\1 

(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. ) 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.3.12.5 Mission Payload Peculiar Flight Crew Support Requirements 

(Manned-Automatic Mode Only) 

3.3.12.5.1 General Training Requirements 

Training required for the crew members shall include indoctrination to the mission payload equipment and its function through the 

engineering specialty assignments associated with engineering and operational design; to final integrated mission simulation. The major crew 

functions for Mission Payload Training shall include: 

a. Mission Payload Activation, Checkout and Alignment 

b. Prepass Preparation and Flight Planning 

c. Acquisition, Tracking and Photography 

d. Data Analysis, Processing and Delivery 

e. Instrumentation Data Monitoring and Control 

f. Mission Payload Maintenance and Contengency Operations 

g. Mission and Flight Planning Support 

h. Nominal Mission Payload Securing 

i. Abort Operations 

3.3.12.5.2 Simulator Requirements 

The Mission Payload Procedures Trainers will be provided at 

VAFB and the LVSS contractors facility for crew training. These trainers 

will be portions of the Mission Simulators. Mission Payload Procedures 

Trainers will be used for pre-flight training for the primary and backup 

crews. These trainers will provide thorough indoctrination with actual 

MPSS hardware for the flight vehicle, of interest, and for training to 

operational readiness criteria in all MPSS operations. In addition, the 

Mission Simulator will be used during the pre-launch rehearsals and to 

support the SCF checkout and training for MOL. 

• SPECIA!. P. J... N G 3-150.1 
NR E LROE E -11,tillING I 

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) 

4. 1 GROUND TEST REQUIREMENTS 

4. 1. 1 Development Tests 

4. 1. 1. 1 General Requirements 

Design development tests shall be performed to determine design feasibility, 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 tests 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 

4. 1. 1. 3. 1 

Deleted. 

4.1.1.3. 2 

Orbiting Vehicle Requirements 

Space Simulation Test 

Compatibility Test 

Tests shall be conducted on the Orbiting Vehicle System Segments to 

demonstrate physical, functional, and EMI compatibility. 

SPECIAL HANDLING 4_1 
gptugatANDLING 

4. 1. 1. 3. 3 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. 3.4 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. 4 Laboratory Vehicle Requirements 

4. 1. 1. 4. 1 Structural Tests (U) 

Static tests shall be performed to design ultimate loads as specified 

by the appropriate segment structural criteria. Consideration shall 

be given to the thermal environment. 

Shock and vibration tests shall be performed in accordance with the 

environmental criteria, using a boilerplate Gemini, mass-simulated 

mission payload within the mission module, and mass induced simulated Titan III inputs. 

4. 1. 1. 4. 2 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 available, 

mass simulated components will be used. 

4. 1, 1. 4. 3 Subsystem Tests (U) 

Separate subsystem development tests shall be made to verify design 

adequacy. Such tests shall include demonstration of on-orbit and 

critical ground maintenance tasks. 

4. 1. 1. 4. 4 Meteoroid and Particle Radiation Test (U) 

The ability of the Laboratory Vehicle to withstand meteoroid impact 

and particle radiation shall be demonstrated by subjecting appropriate 

PP"rLING rn • t...0 it id CONFIDENTIAL 

this document contains Information affecting the national defense of the United States within the meaning of the hoionage lows. 

hue 18, 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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SIJEC IAL 4-3 

NRO APPROVED FOR 

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• Laboratory structural sections to simulated meteoroid and particle 

radiation environment. 

4. 1. 1. 4. 5 Atmospheric Contaminant Test 

A materials atmospheric contaminant test shall be conducted on the 

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

identify contaminants and 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. 6 Space Simulation Test (U) 

The laboratory module development article shall be tested in a thermal 

and 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 development article shall be tested in a thermal 

and vacuum space simulator to determine the thermal characteristics 

of the vehicle. 

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) F. 

Static force, moment and pressure wind tunnel tests shall be performed on the Gemini B configurations where NASA Gemini data do not 

FORM This document contai

ns information affecting she notional defense of the United Stores within the meaning of the Espionage lOws, SSD AUG 62 20B Title 18, U.S C., Sethon 793 and 794, the transmission of which any manner to on unouthol,,ed pe•son is woh,boed by lo* 
s tegloR ;

"L1N R r S 22 15 h i' 1-5 ✓ a

exist. These tests include those cases where the external configuration or flight parameters are significantly changed or where present 

test data are 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 

following a 33-day space standby environment. 

4. l 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 requirements 

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 simulated. 

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. 

SPECIAL HANDLING 

4-4 

FORM This document contains information affecting the notional defense of the United Stoles within the meaning of the Espionage laws. 

:"

„

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

t. 
NRO APPROVED FOR 

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-MET- • PRELIMINARY 

2 FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 1 

PAGE 429_ OF 52 

DATE 0 Jan 66 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

`3. SPEC. NO. 

SS -MOL -1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

4-5 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 4.1.1.9 OPERATIONS COMPATIBILITY REQUIREMENTS N-3 SAR) 

Add following words to sentence: 

in both manned-automatic and automatic modes. 

SPECIAL ACCESS REQUIRED rr 3 AR S PP , f PROGIIAM NO. 432A 

SENSIT/YE 

 IDENTITY if f AP 

Irq !pg.! 

document containsinformation affecting the notion.' defense of the United Stoles within the meaning of the Espionage Laws, 

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

RELEASE 1 JULY 2015 SPECIAL HANDLINti 

PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 2 

PAGE 59 or 62 

DATE 15 March 66 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOT, System - 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

S. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

4-5 

6. EFFECTIVITY 

MOL tProgram 

7. TEXT CHANGE 

Paragraph 4.1.1.10 Aerospace Ground Equipment Requirements (U) 

Change the paragraph to read: Design development testing for. 

Gemini B and Laboratory Vehicle AGE shall be conducted 

to verify the design, to determine equipment 

compatibility, to evaluate performance, and 

to develop procedures. 

Paragraph 4.1.1.11 Orbiting Vehicle Mission Simulator Requirements (U) 

Change to read: Manned Orbiting Laboratory Mission Simulator 

Requirements Development of the MOL mission 

simulator segments shall be conducted to verify the 

design, to determine equipment compatibility, to 

evaluate performance, and to develop procedures. 

Tests shall also be conducted to demonstrate proper 

operation and compatibility of the MOL mission 

simulator segments interface with the SCF and Test 

Support System Segment.. 

4 

V 

!RED S?tC\RV VAV‘ 
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RELEASE 1 JULY 2015 SPECIAL HANDLING 

4 

•'4 

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 shall be 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 be conducted to demonstrate proper operation and compatibility of the Orbiting Vehicle System, the Launch 

Operations, Flight Operations, Recovery, and Test Support System 

Segments. S0%)/ GLru a -

4. 1. 1. 10 Aerospace Ground Equipment Requirements (0) 

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 

Design development of the Orbiting Vehicle mission simulator shall be 

conducted to verify the design, to determine equipment compatibility, 

SPECIAL HANDLING 
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OF 

DATE 20 Jan 6 

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2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS -MOL -1 

4, CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

4-6 

6. EFFECTIVITY 

MOL Program 

- 74 TEXT CHANGE 

Paragraph 4.1;1.11 ' ORBITING VEHICLE MISSION SIMULATOR 

REQUIREMENTS l'S%-3 SAR) 

• 

SPECIFICATION CHANGE NOTICE 

NO. 1 

Add following words to last sentence: 

both'tninned-automatic and automatic modes. 

itri44.t.0 

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PROGRAM NO. 432 4 IDENTITY 4 • & SPECIAL HANDLING 

This document contains information affecting the national defense of the United Stoles within the meaning of the Espionage taws, 

• IOW 1I, U.S.C,, Section 713 oosI 7T1, it.o tiuntwission of whith in any ;runny to on unouthorited Vetsedt is prohibited by 
),11R0 APPROVED FOR 

ELEA§E 1 JUaLY 2015 

CD PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

No.2 

60 62 PAGE OF 

DATE 15 Marrh (d) 

SUPERSEDING 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. ■ 

SS-MOL-1 

4. CONTRACT 

..,- . 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

4-6 

6. EFFECTIVITY 

AOL Program 

7. TEXT CHANGE 

Paragraph 4.1.2.3.1 Mission Life Requirements \4) 

Change the paragraph to read: Orbiting Vehicle elements 

and their subsystems shall be qualified for 

on-orbit life of 33 days including a 3 day contingency. 
NR 

RE 

 APP,B9y,p FOR 

ejlAti5 HANDLING 

C9L t 

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. Ate. 06-14- /7// — 0 a, ,, L.) e‘. 

4. 1. 2 Qualification Tests 

4. 1. 2. 1 General Requirements (U) 

Qualification tests shall be performed to verify design adequacy and to 

demonstrate equipment performance and reliability. The test conditions shall be determined by the design requirements and consist of 

time and stress level factors on the anticipated environments. Full 

qualification tests, including all applicable environments, shall be 

performed at the component or subsystem level. Limited qualification tests, such as thermal-vacuum and EMI, shall be performed on 

the development test article at the system segment level. Appropriate 

qualification tests must be completed prior to the applicable flight. 

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 at this level of assembly, 

except for EMI. The qualification of the various system segments will 

constitute the qualification of the over-all system, except for EMI. 

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(.-61'. 2. 3. 1 Mission Life Requirements \-4) 

IOrbiting Vehicle elements and their subsystems shall be qualified for 

on-orbit life of 33 days. 

SPECIAL HANDLING 0 

4 - 6 

re-RM This document contoins information affecting the nation& defense of the United Stoles within the meaning of the Espionage laws. 

AUG 62 20B Title 18. U.S C., Section 793 and 794, the transmission of which in any manner to on unouthorited Person i s prohibited by low 
Ej PRELIMINARY 

r=1 FINAL 

PAGE 61 OF 62 

DATE 15 March 66 

SUPERSEDING 

SPECIFICATION CHANGE NOTICE 

NO. 2 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632 A 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

4-7 

6. EFFECTIVITY 

• MOL Program 

7. TEXT CHANGE 

Paragraph 4.1.2.4.1 General V) 

Add the following at the end of the last sentence in the last 

paragraph: electronic simulator. 

1.:O ti 

a 1.3 1 1 

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RELEASE 1 J L HANDLING 

• 4. 1. 2.4 Laboratory Vehicle Requirements 

i 4. 1. 2, 4. 1 General (\-4) 

;)----'The Laboratory Vehicle System Segment shall be qualified both at the 

system segment level and at the component/subsystem level. These 

requirements shall be detailed in the Environmental Criteria for the 

MOL System (SSD Exhibit 65-7) and the Electromagnetic Compatibility 

Requirements Specification (SSD Exhibit 64-4). 

In general, the components and/or subsystems will be tested to all 

applicable environments while the Laboratory Vehicle will be subjected to thermal-vacuum and EMI tests. 

The qualification tests of the Laboratory Development Test Article 

shall be performed on the Laboratory with flight crew equipment and 

mission equipment installed in the Laboratory Vehicle System Segment. The tests shall establish the capability of maintaining the required environment, electrical power, leakage rate, communication, 

and data handling for the mission and shall establish the capability of 

Electro/Mechanical Control functions originated for the Laboratory 

Vehicle to be properly transmitted to and executed in the mission 

module and Gemini B. 

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, shutdown and/or standby for an extended period of time and re-start and operation for re-entry. 

f. .•SPECIAL HANKING 4-7 

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

SSD AUG 62 20B' tale' 18, Section 793 and 79d, the transmission of which on any manner to on unouthonzed person is otohoboted by low 
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RELEASE 1 JULY 2015 

4.1.2.6 Mission Payload Requirements \-3 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 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 operations from launch, on-orbit including extravehicular 

activities, re-entry, and recovery. 

Training equipment and simulators shall be qualified to requirements 

consistent with their application and interfaces with other equipment as 

specified in the contract end items specifications. 

4.1.2.9 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. 

4-8 SECRET SPECIAL HANDLING 

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Title 18, U.S.C., Section 793 and 794, the transmission of which in any manner to an unauthorized person is prohibited by low. 
SPECIAL HANDLING • 

4. 1. 2. 10 Aerospace Ground Equipment Requirements (U) 

The MOL System AGE shall be qualified by acceptance test specified 

in paragraph 4.1.4 Acceptance and Flight Readiness Tests of this 

specification. 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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. Extended 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. The test conditions shall be comparable to enduse environments and severe enough to detect and eliminate earlylife failures 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 

4-9 

This &comerst contains information affecting the notional defense of the United Stoles within the meaning of the Espionage Lows, 

Title 18 U.S.0 Section , • 793 and 794, the transmission of which in any manner to on unauthorized person is prohibited by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECV " P i DL if 

acceptance test shall be performed at the system segment level where 

applicable. Acceptance Tests will be sufficient to assure Flight Readiness Test integration. 

4. 1. 4. 2 Flight Readiness Test Requirements (U) 

EMI, 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 interference, and functional operational tests 

performed after integration of these segments to form the complete 

Orbiting Vehicle. 

4. 1. 4. 4 Laboratory Vehicle Requirements (U) 

The Laboratory Vehicle System Segment shall be acceptance tested at 

the system segment level. All components and/or subsystems shall 

have a vibration and a thermal-vacuum test performed in accordance 

with the Environmental Criteria Specification. In addition, the Laboratory Vehicle System Segment and affected Mission Payload equipment 

shall be acceptance tested to thermal-vacuum conditions. 

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 N.3 SAR) 

The Mission Payload Segment shall be acceptance tested at the segment level. All components and/or subsystems shall have a vibration 

4-10 

This document contains information affecting the notional defense of the United Stales within the meaning of the Espionage lows. 

Title le, U.S.C., Section 793 and 794, the transmission of which in any manner to an unauthorised person is prohibited by low. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ltelig_ SPECIAL tiANDLII% • 

• 

and thermal-vacuum test performed in accordance with the Environmental Criteria for the MOL System. 

4, 1. 4. 7 Titan III Requirements (U) 

The Titan HIM System 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 con 

ditions while the system flight equipment will be tested to thermalvacuum conditions only. 

Training equipment and simulators shall be acceptance tested to requirements of the contract end item specification and by complete 

functional operation. Compatibility with other subsystems and segments shall be demonstrated in all planned sequences and modes of 

operation. (U) 

4. 1. 4. 9 Launch Operations, Flight Operations, Recovery, 

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 development 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 functional testing 

to verify specified performance has been conducted. (U) 

4. 1. 4. 10 Aerospace Ground Equipment (AGE) Requirements 

Ns4) 

Orbiting vehicle segment AGE 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 

'SfefiET—, 4-ii 

This document contains information affecting the notional defense of the United States within the meaning of the EsPionooe 

Trite 18, U.S C., Section 793 and 794, the transmission of which in ony manner to an unouthoilted person is prohibited by low 
NRO APPROVED FOR 

RELEASE .1 JULY 2 

4-12 

Thts document contains information of fecting the notional defense of the United State, within the meaning of the Espionage Lows, 

20 B 1." I6, U.S.C.. Section 793 and 794, the transmission of which in any manner to on trnouthorited person is wob.b.ted by low 

I ORM 

G 62 

S E tof 11- II" it" DU ING 

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 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 items to perform their 

intended function. Complete mechanical and electromagnetic interference compatibility shall be demonstrated. Compatibility with other 

,subsystems and segments shall be demonstrated in all planned sequences and modes of simulation. 

4. 2 MOL SYSTEM FLIGHT TEST REQUIREMENTS 

4. 2. 1 Test Program Description \-4) 

The complete MOL System Flight Test and Evaluation consists of formal testing and evaluation including the integration of all system segments into a complete system in the final operational configuration and 

environment. All MOL System Flights shall be launched from VAFB 

with suitable instrumentation employed to determine the system functional performance, operability, and compatibility of the system.segments. 

Titan-III Development Flight Test (MOL Flight No. 1) 

11S-4) 

This flight shall be unmanned and orbital. The Titan-III Launch Vehicle shall have modificatio incorporated to accommodate the seven 

I 4. 2. 2 

'\ (t 
IR7 EA:ESMAI.. HANDLING ID ----stmL 

SPECIFICATION CHANGE NOTICE 

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St-PEAS 1NR 

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PROGRAM NO. 4324 IDENTITY 4 f s 

I. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 fi 

4. CONTRACT 

• Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. ■ 

4-13 , • 1 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Change Title of Paragraph 4.2.4 as follows: 

Paragraph 4.2.4 MOL FLIGHT TESTS (MOL FLIGHT NO. 3 and 4)3 SAR) 

b) Change first sentence of 4.2.4 as follows: 4. 

The third and fourth MOL Flights shall be manned with orbital 

characteristics corresponding to the mission. 

SPECK tIANDLNG 

.This document contains information affecting the nananol defense of the United Stores ...Whin the meaning of the Espionage.lows, 

•I`itte 18. U.S.C.. Section 793 and 791. the ir,:intm,ssion of which in ony manner to an 9noothoraed person .5 piohthited 
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• EeRE— 

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, 

eluded 'for temperature, acoustic, Vibraticin, Fire Sstire, and buffet'. 

measurements. The primary objectives of this flight are to derhfonz. 

strate the structural integrity of the Titan III with the MOL-type payload, collect data on the launch and TitarIL III, demonstrate lcohapati-p ,c; f,- 

bility,of„the MOIrtype, configuration with ILC concept, at VAFB, and 

exercise selected segments of the MOL System. 

((1 

4. 2. 3 MOL Development Flight Test (MOL Flight No. 2) (U) 

This second MOL flight shall 'be unmanned. This .flight shall be .sub 

orbital. • The Gemini B shall employ operable subsystems, but the 

Laboratory Vehicle shall be only structurally complete. The Gemini 

B shall be separated from the Laboratory 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' OL Fliuit Tests (MOL Flight No. 3 and Subsequent) 

3 SAR) 

The third MOL Flight shall be manned with orbital characteristics 

corresponding to the mission. The Laboratory Vehicle.sh.a.11inepr.7, 

por ate all subsystems for system evaluation,and a Gemini B with_thalWoperable subsystems will be used. The mission duration requirement 

shall be 30 days. The gemini B shall be separated for retro, re-entry, 

ffliET-SUCIAL dAINDLthia-13 

. This document contains information affecting the notional defense of the United Slates within the meoning of the Espionage tows, 

Title 'IS, U.S.C., 'Section 793 and 79/, the transmission of which in any manner to on unauthorized person is prohibited by law 

• 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPEC,, I,DL HANOLING t 

PRELIMINARY 

El FINAL 

PAGE 52 52 

SPECIFICATION CHANGE NOTICE DATE 20 Jan 66 

NO. 1 SUPERSEDING 

1. ECP NO. 

NA 

2. CONTRACT END ITEM NO. 

MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

4-14 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Change Paragraph 4.2.4 as follows: \-3 SAR) 

a) Replace last sentence of first paragraph with following: 

A preliminary check of the automatic mode will be achieved. 

Change last Paragraph to read as follows: 

The fourth flight shall include the Mission Payload System Segment 

required for demonstration of mission objectives. 

Add paragraph 4.2.5 as follows: 

Paragraph 4.2.5 MOL FLIGHT TZST (MOL FLIGHTS 5 and 

SUBSEQUENT) 3 SAR) 

The fifth and subsequent flights shall be operated for a 30-day 

orbital flight for operational demonstration of the MOL system. 

SPECIAL. ACCESS REQUIRED 

SENSITIVE AR 

PROGRAM NO. z $2A IDENTIWA 

Ef 

1E-ORET, 

:This document contains information affecting the notiomol defense of the United States within the 

tif, Section 14., 

of the Espionage. tows. 

• I% nrohibited hr bw 
..,";•.1. A 

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RELEASE 1 JULY 2015 ---stee--7SPECIAL HANDLING 

and recovery.in a primary recoverrarea:.; iThrs.effort shall demo 

1 ,! 

strateAti6: orbta.l capabilities of the Gemini B and Laboratory Vehicle 

systems andldemonstrate the Launch Operations,F14ht Operations, 

Recovery and Test Support System Segments As a-manned mission,- • - 

1 rf 

the flight will also 'allow a preliminary check of the biomedicaltand. . 

human performance capability of the flight crew on orbit, crew ira ; 

fer to the_Laboratoxy, the operation of Laboratory Vehicle subSYS-Te4 

and controlled disposal of the Laboratory Vehicle. Verification of 

Gemini B subsystems will be accorriplislied'for laundh; On-orbit roiS.- 

sion operations, re-entrY,' and recovery.'. This flight is-a, back-up,,for '7. f 

Flight No. Z. 

The fourth and subsequent flights shall'be manned and oper_atedlfor.a. , i? !,f 

30-day orbital- flight for operational,idemonstratiton of, theNOL: 

These flights shall include the Mission.Payload System Segment 

quired for demonstration of mission objectives. 

4-14 SECRET 

This document contains information affecting the notional defense of the United Stoles within the meaning of the Espionage lows. 

Title L U.S Section 793 and 791, the transmission of which in any manner to on unovlhofized person is piohibited by love. 
4-15 

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SPEC! 973 

4.3 Mission Payload Peculiar Flight Certification Testing 

The requirements defined in 4.1.1.1 through 4.1.1.4, 

4.1.1.6, 4.1.1.9, 4.1.1.10, 4.1.1.11, 4.1.2.1 through 4.1.2.4, 4.1.2.6, 

4.1.2.9, 4.1.2.10, 4.1.2.11, 4.1.3, 4.1.4.1 through 4.1.4.4, 4.1.4.6, 

4.1.4.9, 4.1.4.10, 4.1.4.11, and 4.2 apply here in terms of the MPSS. 

4.3.1 Qualification Testing 

The MPSS will undergo a qualification test in-plant prior 

to undergoing a simulated flight profile test. The tests will consist of 

the following: 

a. Functional performance (ambient) 

b. Acoustic noise tests will be performed on components 

and major structural sub-assemblies. 

c. Proof level vibration on components and structural 

elements and on the Mission Module with a COA interface substitute. 

dr Thermal vacuum (33 days) with equipment operating to 

a flight duty cycle. The tracking mirror gimbals and drive motors will 

be operated during this test. 

e. Post-thermal vacuum performance check 

Qualification functional performance testing (ambient) of 

the Navigation and Control Subsystem will be performed to determine electrical and mechanical performance and compatibility with the on-board computer. 

Additional testing during LVSS/MPSS integration will be 

performed to check mechanical and electrical compatibility, ENT, and crew 

operations of the mission equipment. These will be mated LM/MPS functional 

performance tests in ambient. 

The Qualification Test will be considered completed and 

successful when performance, as determined by evaluating the data, is 

shown to meet requirements as stated in this document and in Part I of the 

Contract End Item (CEI) Specifications. 
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4.3.2 Acceptance Testing 

4- • 

Vibration tests will be at flight levels for components 

and structural sub-assemblies such as the consoles and tracking mirror 

gimbals. 

The MPSS will be vibration' tested at low levels to determine 

nodal patterns and amplific'ation/attenuation factors at major equipment 

mounting points. A COA interface substitute will be utilized for this 

test. 

Thermal vacuum tests will be conducted as described in 

4.3.1 above. 

The Acceptance Test will be considered completed and 

successful when performance, as determined by evaluating the data, is 

shown to meet the requirements as stated in this document and in Part I of the 

MPSS CEI Specification. 

SP1 

4-16 
.14 

5-1/ 2 

0 

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S 

swig SPECIAL HANOLU 

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-standaid 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. 
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ULAS 

PAGE 62 Or 62 ri PRELIMINARY' 

DATE 15 M 0 h AA 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 2 SUPERSEDING 

1. ECP NO. 2. CONTRACT END ITEM NO. 3. SPEC. NO. 

NA MOL System SS -MOL -1 

4. CONTRACT 

Program632 A ' 

6. EFFECTIVITY 

MOL Program 

5. CONTRACTUAL AUTHORITY FILE OPPOSITE SPEC. PAGE NO. 

Glossar y 

7. TEXT CHANGE 

Change "AEE" to "AAE" 

Delete "OVAB" 

SPECIAL HANDL1N95, 

r i\ssriFti"0 • • 

""'"••••• •••••q+. •••#t. • 
klAhDLING GLOSSARY 

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SPED 

M9-6- 

Aerospace Ancillary ILC Initial Launch Capability 

Equipment TRIG Inter-Range InstrumentaACTS Attitude Control and tion Group 

Translation System ITL Integrate-TransferA-to-D Analog to Digital Launch (Facility) 

(Conversion) 

AGE Aerospace Ground LCC Launch Control Center 

Equipment 

AVE Aerospace Vehicle MDS Malfunction Detection 

Equipment System 

MGE Maintenance Ground 

BECO Booster Engine Cutoff Equipment 

BOSU Bioastronautics Opera- MLS MOL Launch Site 

tional Support Unit MM Mission Module 

CEI Contract End Item NRD National Range Division 

CIP Central Information 

Processor OGE Operational Ground 

CPS Central Power System Equipment 

CSF Contractor Support 

Facility 

OSAF Office of the Secretary 

of the Air Force 

OV Orbiting Vehicle 

DF Direction-Finding nOVAB Orbiting Vehicle 

Equipment Assembly Building 

EC/LS Environmental Control/ PBS Program Breakdown 

Life Support Structure 

ECS Environmental Control 

System RCS Re-Entry Control System 

EED Electro-Explosive Device REM Re-Entry Module 

EET Event Elapsed Time 

EKG Electrocardiogram SCD Specification Control 

EMI Electromagnetic Drawings 

Interference SCF Satellite Control Facility 

EVA Extravehicular Activity SGLS Space-Ground Link 

Subsystem 

FAA Federal Aviation Agency SRM Solid Rocket Motor 

STC Satellite Test Center 

GSE Ground Support Equipment 

T-Count Terminal Count 

ICD 

ICWG 

Interface Control Drawing 

Interface Control Working 

TTC Tracking, Telemetry, 

and Command 

IDEP 

Group 

Inter-Service Data 

TTCV Tracking, Telemetry, 

Command, and Voice 

Exchange Program 

IFS Interface Specification VET Vehicle. Elapsed Time 

IOS Inertial Guidance System VOX Voice 

IIP Instantaneous Impact Point 

SPECIAL HANDLING 

11.'4 docyrnen, contotisi 7niotmotion affecting the notional defense of the United States within the mooning of the Espionage laws. 

title 18. U 5 C Section 793 and 794, the tronsznission of which in any snonner to on unauthorized person is prohibited by :Ow