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sss_2(5 

Copy # n of 8 

Pages 2 

27 June 1966 

(Total page count, 

includ. attachments 

is 91 pages) 

Subject: Changes to SS-IVrOL-1 Integrated, 29 April 1966 

The attached material is the result of a review of the system specification, 

taking into consideration, contractor comments and baseline changes. 

The change material consists of: 

Attachment No. 1 

Suggested Changes to SS-MOL-1 Integrated 

These changes were under consideration for SCN-3; however, time 

did not permit their inclusion. They were previously submitted to 

Capt. Bass, and are included in the SS-MOL-1 changes being circulated by SAFSL-5 (see SSMC-22, dated 26 May 1966). 

Attachment No. 2 

Applicable Documents 

The 10 pages of applicable documents in SS-MOL-1 have been carefully reviewed by R. Papich, J. Dawson, J. Morgan, and A. Gillogly. 

The only ones considered suitable for call-out are those listed in 

Attachment No. 2. Many of the remaining MIL Specs are worthy of 

consideration for inclusion in CEI and/or subsystem specifications. 

Attachment No. 3 

Suggested White Page Changes 

These suggested changes to the white pages are those prepared 

since submission of Attachment No. 1. They have resulted from 

an effort to call out requirements on white pages whenever security 

considerations permit.the bulk of the material is contained in 3.3.4. 

f t " " SPEC • J,; i" , - - 
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Attachment No. 4 

Suggested Green Page Changes 

These suggested changes to the pages complement many of the 

white page changes (e. g. , material deleted from the green pages 

was in most cases moved to the white). Also, requirements 

against the OV or LV were removed from 3. 3.4, and placed in the 

3. 3.1 or 3. 3. 2 (e. g. , DRV launcher requirements against the LV 

were moved to 3. 3. 2. 2. 3 - see page 3-55 of Attachment No. 3). 

Finally, 3. 3.4 was completely rewritten because of the expanded 

white 3. 3.4, and the reorganization of the material into subsystems. 

Cern!. 

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SUGGESTED CHANGES TO SS-MOL-1 INTEGRATED 

Page Paragraph 

3-1 3. O. 1 General 

Add to the first paragraph: 

"The disposal of the Laboratory and Mission 

Payloads shall be accomplished by the ACTS. 

The translation thrusters will be fired by 

ground or stored program command after 

Gemini B separation in order to obtain 

impact into a designated broad ocean area." 

3- 31 3. 1. 3.1. 2. 4 Mission Payload System Segment 

Change to read: 

"The effectiveness of the Mission Payload 

Segment for the total mission shall be not 

less than 0.95 in the manned-automatic 

mode, and 0. 80 in the automatic mode. 

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

Change to read: 

"The Laboratory Vehicle System Segment 

The Laboratory Vehicle System Segment 

shall consist of a Laboratory Module (less 

the mission payload control equipment), plus 

the structural shell of the Mission Module, 

which shall house the mission payloads. The 

Mission Module shall be unpressurized, ten 

feet in diameter, and 36 feet, 2 inches long, 

and located aft of the Laboratory Module. 

The mission module structure shall contain 

a separation plane at station 355. The 

Laboratory Module shall consist of a 

pressurized section and an unpressurized 

section. The pressurized section will 

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RELEASE 

1r 4D OF SUGGESTED CHANGES 

SPEC 

Page Paragraph 

3-53 3. 3. 2 (Cont'd) consist of one compartment to enclose and 

support the operation of environmental 

control, life support, attitude control, 

power generation, communications, vehicle 

status monitoring, and mission equipments." 

3-55 3. 3. 2. 2. 3 Data Recovery Capsule 

Change to read: 

"Data Re-entry Vehicle (DRV) 

The Laboratory shall be capable of 

incorporating and launching one Data 

Re-entry Vehicle with provisions for a 

second DRV. The capability shall permit: 

access for placing data into the DRV in an 

environmentally controlled atmosphere; 

means for deploying the DRV without 

adverse effects on the OV; and means for 

controlling the attitude and time of release." 

3-55 3. 3. 2. 2. 4.1 Allowable Pressure Differentials 

Change to read: 

"Vent paths shall be sized consistent with 

the design pressure differentials. The allowable pressure differentials on the aft 

Laboratory Bulkhead are 6. 0 to -0.5 psi 

(Plaboratory - Pmission module). The 

allowable pressure differentials on the 

Mission Module aft bulkhead are +2.0 to -0.5 

psi ( mission module - fwd booster compartment). No flow shall occur from the 

booster to the Mission Module." 

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Page Paragraph 

3-59 3. 3. 2.2. 2.1 

(SCN-1) 

5. 

3-61 3. 3. 2. 2. 5. 2. 2. 3 

(SCN-l) 

3-61 3. 3. 2. 2. 5. 2. 2.4 

(b) (SCN-1) 

3-62 3. 3.2. 2. 5. 2.4.4 

(SCN-1) 

3-62 3. 3. 2. 2. 5. 2. 4. 2 

Command (C-4) 

Add the following sentence: 

"The capability for flight computer loading 

at 10 kbps shall be provided." 

Format Selection Equipment (C-4) 

Delete the words: "any one of several." 

Add the sentence: "To simplify flight 

operations, the number of formats shall 

be minimized." 

Recorders (C-4) 

Delete the second sentence: 

"The nominal playback rate for stored 

telemetry is 128 kilobit/sec.." 

Display and Control (U) 

Delete the second sentence: 

"The computer display panel shall consist 

of all indicators and lights necessary for 

non-textual communications between the 

computer and the flight crew." 

Computer Subsystem Control Unit 

Add at the end of the paragraph: 

"The MPSS computer shall be primary and 

the Laboratory computer shall be employed 

as back-up." 

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Page Paragraph 

SPE LtAL 'LING 

3-63 3.3.2.2.6.2.1 General 

Add the following: 

"Equipment located in the Laboratory must 

be capable of operation for periods of up 

to two hours in duration with the Laboratory 

unpressurized." 

3-79 3.3.2.2.8.7.2 Under and Over-Voltage 

Change to read: 

"Laboratory equipment shall withstand, 

without damage, continuous voltages from 

20-33 volts at its power terminals." 

3-110 3.3.5.2.4.3 Crew Performance Tests 

Delete entire paragraph. 

4-6 4.1.2.3 Orbiting Vehicle Requirements 

Change to read: 

"An electromagnetic compatibility (EMC) 

qualification test will be performed at 

VAFB on the Flight Vehicle in conditions 

simulating the lift-off R. F. environment. 

The quality assurance provisions of SSD 

Exhibit 64-4 shall apply to this test. The 

mobile service tower shall be removed for 

this test. In addition, electromagnetic 

interference (EMI) measurements shall 

be taken at the Gemini B to Laboratory 

Vehicle interface and at the Laboratory 

Vehicle to Launch Vehicle interface after 

electrical mating of the Flight Vehicle system. 

Additional monitoring of critical circuits in 

any segment may be performed as required 

by the factory EMI test results." 

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RELEASE 117 ASaA915 5 OF SUGGESTED CHANGES 

Page Paragraph 

3-51 3. 3.1. Z. 8 Aerospace Ground Equipment AGE 

Add the following paragraphs: 

"The electronic AGE for the LVSS and MPSS 

shall be designed and implemented to permit, 

but not be limited to: 

a) Simultaneous and independent subsystem 

tests. 

b) LVSS and MPSS combined system tests." 

"The LVSS and MPSS AGE shall include, but 

not be limited to, test control consoles, 

digital computer subsystems, and vehicle 

interface equipments. The LVSS and the 

MPSS AGE computers shall be identical and 

shall permit the execution of test computer 

programs prepared in the MOL Test Engineer 

Oriented Language (MOLTOL), and compiled 

by the appropriate computer prior to their 

(test computer program's) operational use. 

Test computer programs utilized at the 

integration and launch areas shall be functionally identical to those utilized at the factory 

areas." 

"The LVSS and MPSS AGE computer subsystems shall incorporate provisions for 

direct real-time communications, for both 

commands and data interchange between 

identical computer subsystems." 

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4. CONTRACT 

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5. CONTRACTUAL AUTHORITY 

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7. TEXT CHANGE 

Paragraph 2.0 Applicable Documents 

Delete entire section (pages 2-1 thru 2-10), and replace with the 

following two pages. 

3 

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2.0 APPLICABLE DOCUMENTS (U) 

Military specifications, standards, exhibits, manuals, regulations, 

publications, -bulletins, pamphlets, and other documents are herein 

specified as appropriate to obtain first tier compliance for the MOL 

System. 

MIL-D-70327 

(Para. 3.2.1. 7. 4) 

MIL-E-5400H 

(Para. 3. 2.1. 5.1) 

MIL-HDBK-300 

(Para. 3. 2. 1. 3) 

MIL-M-38310 

(Para. 3.3. 1.1.1.1) 

MIL-Q-9858A 

(Para. 3.2.1. 7.1) 

MIL-S-8512B 

(Para. 3.1.3.5.1) 

MIL-STD-143A 

(Para. 3. 2. 1.1) 

MIL-STD-785 

(Para. 3. 1. 3.1. 1) 

SSD 61-47B 

(Para. 3.3.9.2.2) 

SSD 64 -4 

(Para. 3. 2. 1. 8) 

SSD 64 -5 

(Para. 3. 2. 2.1) 

Drawings, Engineering and 

Associated Lists 

Electronic Equipment, Aircraft 

General Specification for 

Technical Information File of 

AGE for Air Weapon System 

Mass Properties Control 

Requirements for Missile and 

Space Vehicles 

Quality Control System Requirements 

Support Equipment, Aeronautical, 

Special General Specification for 

the Design of 

Specifications and Standards, Order 

of Precedence for the Selection of 

Requirements for Reliability 

Program (for Systems and 

Equipments) 

Computer Program Subsystem 

Development Milestones 

Electromagnetic Compatibility 

Requirements for Manned Space 

craft, General Specification for 

General Specification for Wiring 

Harness in Manned Spacecraft 
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FED-STD-209 

FED-STD-222 

(Para. 3. 3. 2. 2.5.15) 

AFSCM 375-1 

SSBD 65-22 

NAVSHIPS 250-649-1 

(Para. 3.3. 2. 2. 6. 2. 8) 

AFWTRM 127-1 

(Para. 3. 3. 2. 2. 8. 7. 7) 

SSMD- 77 

(Para. 3. 1. 1. 1. 10) 

SAFSL -100004 

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

SAFSL -100002 

(Para. 3. 1. 3. 3, 3. 1. 3. 4 & 

3.2.2. 8) 

Clean Room and Work Station 

Requirements, Controlled 

Environment 

Radiation Standards for Communications and other Information 

Processing Equipment 

Configuration Management 

During (All) Phase 

Titan HIM System Performance/ 

Design Requirements, General 

Specification, 12 November 1965 

U. S. Navy Submarine Atmosphere 

Habitability Data Book, Rev 1, 

Navy Bureau of Ships 

WTR Range Safety Manual 

Government Plan for Program 

Management for the MOL 

Structural Criteria for the Manned 

Orbiting Laboratory (MOL) 

Laboratory Vehicle System 

Environmental Criteria for the 

MOL System 

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CCN 

FILE OPPOSITE SPEC. PAGE NO. 

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7. TEXT CHANGE 

SCN #1 

Paragraph 3. 0.1 General (S-3 SAR) 

Change the fourth sentence of the second paragraph to read: 

"Provisions shall be made for conversion of the Orbiting 

Vehicle at the Laboratory Vehicle contractor's plant, from 

the Manned-Automatic configuration to the Automatic configuration, within a 4-month pre-launch period utilizing appropriately 

packaged hardware and software elements. 

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7. TEXT CHANGE 

Paragraph 3.1.1.1. 3. 4 Insertion Conditions (S-3 SAR) 

Change the last paragraph to read: 

It shall be possible to alter insertion parameters within the 

range of system capabilities as late as three days prior to a 

scheduled launch, provided the changes do not exceed the redeployment capability of the down-range elements. 

Fn • ,.!-:. 11;fI 

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7. TEXT CHANGE 

Paragraph 3. 1. 1. 1. 4. 3 Flight Crew Transfer (C-4) 

Change to read: 

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

Vehicle shall normally be accomplished within a pressurized tunnel. 

Capability of extra-vehicular crew transfer through the Laboratory 

Vehicle DRV launch tube will be provided as a backup mode. 
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7. TEXT CHANGE 

Paragraph 3.1.1.1. 5. 8 Command and Control (Manned-Automatic Configuration) 

(C-4) 

Add the following paragraph: 

The OV command and control capability shall use a flight crew of 

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

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. 

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CCN 

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6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 1. 3.1.1 General (C-4) 

Add the following to the third paragraph (as modified by SCN #1): 

Those portions of the AVE designed for on-orbit maintenance 

shall have features which will facilitate on-orbit fault detection, 

isolation, and repai r; and shall, to the maximum possible extent, 

utilize common methods of equipment removal and replacement 

and common tools and checkout equipment. In accomplishing the 

on-orbit maintenance function, the utilization of the crew capabilities, the AVE design features, and the associated ground 

equipment and personnel, including the ground-vehicle communications and command links, shall be optimized. 

Provisions shall be made, where feasible, for back-up 

manned modes of operation of equipments to compensate for 

malfunctions. Degraded performance shall be accepted for 

these back-up modes when necessary. 

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5. CONTRACTUAL AUTHORITY 

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7. TEXT CHANGE 

Paragraph 3.1. 3. 2.1.1 Ground Maintenance Requirements (C-4) 

The last sub-paragraph should be modified as follows: 

The MOL System and its associated AGE shall be designed 

for ease of maintenance and shall have features which will 

facilitate fault isolation and detection in both the AGE and the 

flight equipment. The MOL System and associated AGE shall 

be designed for ease in removal and replacement of the major 

modules and/or components. 

1,U 

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4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-34 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.1. 3. 7. 2 Ground Safety 

Change the first paragraph to read as follows: 

The design shall be such that hazards to personnel and equipment 

during the pre-launch, checkout, and launch operations are minimized. 

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5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-45 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.1.1.1.3 Weight and Balance (C-4) 

Add the following paragraph: 

Weight and balance equipment shall not be required at the MOL 

launch site. Final weight and balance adjustment for the Gemini B 

shall be performed at the contractor's facility prior to shipment to 

the MOL launch site. Final weight and balance adjustment for the 

Laboratory Vehicle shall be performed during the Mission Module/ 

Laboratory Module integration and checkout at the Laboratory Vehicle 

contractor's facility prior to shipment to the MOL launch site. 

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5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-46 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 3.1.1.5 Explosive Devices, Squib Simulator, etc. 

Add the following paragraph: 

AFWTRM 127-1 shall be followed in the design, installation, and 

checkout of ordnance items. Generally, explosive devices shall be 

designed to permit installation as late as possible during the prelaunch phase. 
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Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

3-55 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 3. 2.1. 5 Mission Module Structure (C-4) 

Add the following paragraph: 

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. The Mission Module structure shall contain a separation 

plane at Station 355. 

Paragraph 3. 3. 2. 2. 3 Data Recovery Capsule (C-4) 

Change paragraph title as follows: 

Paragraph 3. 3. 2. 2. 3 Data Re-entry Vehicle (DRV) (C-4) 

Change to read: 

For the manned-automatic mode the Laboratory Module shall 

provide for two Data Re-entry Vehicles (DRY), DRV structural supports, 

launcher tube assembly, release mechanism, auxiliary electrical and 

mechanical equipment required to evaluate DRV status, and to control 

DRV release and separation. 

The Laboratory Module shall provide the required space and 

environmental control for the DRV's. Storage and support for a 

single DRV shall be provided inside the Laboratory Module and if 

required, a second DRV shall be contained within the DRV launch tube. 

The DRV launch tube shall be adequate to contain and support the DRV 

in the launch, ascent, orbit, and deboost environments. The launch 

tube centerline shall be oriented 90 degrees to the Orbiting Vehicle 

roll axis. In the event a DRV does not eject from the DRV launcher, 

the capability to retrieve the DRV data and to reseal the DRV launch 

tube shall exist. 

SPECIAL 

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7. TEXT CHANGE 

Paragraph 3.3.2.2.3.1 DRV Environmental Control (C-4) 

Add the following paragraph: 

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 DRV launcher tube. 

Paragraph 3.3.2.2.3.2 Launch Tube Alignment (S-3 SAR) 

Add the following paragraph: 

The launch tube for the DRV shall maintain the DRV axes of 

symmetry within 1/2o of the Laboratory Vehicle yaw axis. Support 

and ejection equipment shall have provision for making and checking 

the alignment. 

Paragraph 3.3.2.2.3.3 Pre-launch Testing (C-4) 

Add the following paragraph: 

At the launch pad, the DRV's, shall be capable of all necessary 

pre-launch tests as part of an overall system test. 
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6. EFFECTIVITY 

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7. TEXT CHANGE 

Paragraph 3. 3. 2. 2. 8. 7. 2 Under and Over-Voltage (C-4) 

Revise as follows: 

Laboratory equipment shall withstand, without damage, continuous 

voltages from 20-33 volts at its power terminals and power interruptions 

up to one second, and shall give specified performance upon return to 

the equipment operating voltage. 

773 

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7. TEXT CHANGE 

Paragraph 3. 3. 2. 2.13. 2 Performance (C-4) 

Change paragraph to read as follows: 

The Laboratory Vehicle System Segment peculiar AGE shall 

include all of 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. 

In addition, the transportation and ground handling AGE shall be 

capable of maintaining the Laboratory Vehicle and Mission Payload 

requirements for temperature, humidity, dust control, and alignment. 

The Laboratory Vehicle System Segment peculiar 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 module or replaceable component 

level. Detailed fault isolation and failure analysis within modules or 

components will be conducted at contractor or sub-contractor plants. 

Portions of the Laboratory Vehicle 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. 2.13. 3 Alignments 

Add the following paragraph: 

DRV installation AGE shall have provision for making and checking 

the alignment of the DRV axes of symmetry (3. 3. 2. 2. 3). 

Provisions shall be made so that the alignment of the Mission Module 

reference axes to the Laboratory Module reference axes can be measured 

to within one minute of arc. (This is not to imply that the alignment 

shall be within one minute of arc). 

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FILE OPPOSITE SPEC. PAGE NO. 

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7. TEXT CHANGE 

Paragraph 3.3.4 Mission Payload System Segment 

Delete entire page and replace with the following 10 pages. 

tin 7T1-1-?, 77,P ecr:_rt7, .) 7

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3. 3. 4 Mission Payload System Segment 

The Mission Payload System Segment shall be composed of 

the Mission Payload equipment contained in the unpressurized Mission Module 

and the Mission Payload control equipment contained in the Laboratory Module. 

Detailed specifications of the Mission Payload will be provided under separate 

cover. 

3. 3. 4.1 Allocated Performance and Design Requirements 

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 

paragraph 3. 3. 1. 1. 1. 

3. 3. 4. 1. 3 Electrical Power 

The electrical power allocation for this segment is specified 

in paragraph 3. 3.1.1. 2. The allocation per referenced paragraph shall be 

supplied to the Mission Payload System Segment by the Laboratory Vehicle 

System Segment. 

3. 3. 4.1. 4 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. 

3. 3. 4. 2 Peculiar Performance and Design Requirements 

3. 3. 4. 2.1 Structure and Thermal Control Subsystem 

3-15 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIA.L 

3. 3. 4. 2.1.1 Mission Module Structure Design 

The Mission Section contractor shall determine the design 

requirements for the Mission Module structural shell based upon critical 

ground and orbital mission requirements. (The Laboratory Vehicle contractor 

will perform the final design of the Mission Module shell, based on these 

MPSS requirements and predicted launch flight loads). 

3. 3. 4. 2.1. 2 Support Structures 

Supporting structures shall be provided for mounting MPSS 

equipment in the Laboratory Module and in the Mission Module. Protection 

shall be provided for the equipment to withstand handling, transportation, 

launch, and orbit loads. The following major load excitation sources shall 

be considered in the design of MPSS Support Structures: 

Transportation: Shock and Vibration 

On-Pad: Winds and Overpressure 

Launch: Acoustic, Transient Shocks, Sustained 

Acceleration and Vibration 

On-Orbit: Data Re-entry Vehicle Launch, ACTS 

Maneuvers, and Gemini B Separation 

The load levels for the above are specified in SAFSL-100002, Environmental 

Criteria for the MOL System. 

Provision shall be made for installation, inspections, and 

replacement of equipment as required. Factors of safety shall be applied 

such that the structural elements will have sufficient strength to withstand 

(simultaneously) limit loads, applied temperature, and other accompanying 

environmental phenomena without excessive elastic or plastic deformation. 

The factor of safety to be employed is 1.40. 

PEC`AL 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 L 

...•■■•• 

3. 3. 4. 2.1. 3 Thermal Control 

MPSS temperatures for equipment shall be maintained 

within their specified limits of both level and gradient by a combination of 

selected coatings, insulation, and zoned heater control, active thermal 

control shall be employed only where passive control proves inadequate. 

Ground conditioning during all phases of ground 

test (factory system test and pad operations) shall employ internal ducting, 

supplemented electric heating as required to maintain required thermal 

control of the AVE. 

3. 3. 4. 2. 2 Navigation and Control Requirements 

(Includes Communications, Command & Instrumentation) 

The Navigation and Control Subsystem (NCS) shall 

provide for the Mission Payload System Segment communications, command, 

control and instrumentation requirements. It shall utilize the Laboratory 

Vehicle computer and SGLS for data processing and air to ground communication. 

3. 3. 4. 2. 2.1 Navigation Requirements 

The Navigation and Control Subsystem shall determine 

the position of the Orbiting Vehicle by computer interpolation of ephemeris 

data from the Satellite Control Facility (SCF). The SCF data shall be 

up-dated at intervals not to exceed 

prediction accuracies from the SCF 

Error (10") 

four revolutions. Expected orbit 

are as follows: 

Revolutions after End of Orbit 

Determination Span 

(n. mi. ) 0 2 4 

in-track 0.15 0. 25 0. 50 

c ross-track 0.04 0. 06 O. 12 

radial 0.04 0.06 0.12 

S 

3 -/7 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

The subsystem shall provide for the on-board measurement and processing 

of longitudinal accelerations to improve orbit prediction accuracies. A 

star acquisition and tracking system (SATS) shall be integrated into the 

MPSS. Based on the above navigation accuracies, the SATS shall establish 

the attitude of its mounting axes with respect to the local vertical and the 

orbit plane with 2 cr errors no greater than 1.5 arc min. Prior to star 

acquisition, navigation data from the SCF and ACTS data (Orientation 

and rate) shall be utilized by the computer, and through the command loop, 

point the axis of the star trackers to the line of sight to the star with an 

error no greater than 2°. The reliability of the SATS for the 30 day 

mission shall be 0. 95. 

3. 3. 4. 2. 2. 2 Command 

The functions performed by this element shall be 

achieved in the Mission Data Adapter Unit (MDAU). This unit shall 

provide the interface between the on-board computer and other MPSS 

equipment. 

Future commands shall be stored in the computer 

identified by a time label. The time label shall be continuously compared 

against incoming system clock time. The least significant character of 

the time label shall be 0. 001 second. The MDAU shall decode discrete 

commands from the computer. Each decoder shall be separately 

addres sable. 

The command element shall be capable of receiving 

real time commands from the crew or from the ground via the SGLS 

and the computer, and processing them to the affected subsystem. 

3. 3. 4. 2. 2. 3 Instrumentation and Telemetry 

Instrumentation power supplies, analog to digital 

converters, and multiplexers shall be provided in the MPSS to prepare 

telemetry for the main multiplexer in the LVSS. The instrumentation 

points shall be assigned so that no single failure will prevent ground 

receipt of critical instrumentation required for control of the MPSS. 

3-/f 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

The interface between the MPSS and LVSS shall consist of a minimum 

number of wires required for the serial transmission of orbital telemetry 

information. A capability for the convenient addition of instrumentation 

shall be provided. 

3. 3. 4. 2. 3 Electric Power and Signal Distribution Subsystem 

MPSS equipment shall be designed to give specified 

performance when operated with 22 to 31 vdc at the equipment power 

terminals. 

MPSS equipment shall withstand, without damage, 

continuous voltages from 20 to 22, and 31 to 33 vdc at their power terminals 

without damage. 

MPSS equipment shall be capable of withstanding power 

interruptions up to one second and shall give specified performance within 

30 seconds after return of the equipment to operating voltage of 22 to 31 vdc 

at their terminals, providing the timing signal is restored/retained 

correctly. 

a. The functions to be performed by the MPSS 

EPSD subsystem are as follows: 

(1) Condition, distribute, monitor, measure 

and switch electrical power. 

(2) Distribute electrical signals. 

(3) Protect the power source from equipment 

malfunctions. 

(4) Provide secondary power sources to 

protect against power interrupts and 

excursions of primary bus voltage outside 

of specified regulation. 

(5) Incorporate EMC into the MPSS. 

b. The performance requirements are as follows: 

(1) Selectively connect the user subsystems 

load to either the Mission Payload Power 

Interface (MPPI) or the AGE source of 

electric power. 

P EL-L„ 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPE 

(2) Remove the subsystem loads from the MPPI 

under full load conditions. 

(3) Condition the power obtained from either 

source to provide functions of inversion, 

conversion and regulation. 

(4) Distribute power to the loads so that the 

voltage at the equipment terminals is not 

less than 22 vdc. 

(5) Program the automatic switching of power 

for loads that are supplied in an established 

sequence. 

3. 3. 4. 2. 4 Consoles and Displays Subsystem 

The MPSS Consoles and Displays (C&D) subsystem 

shall be designed: 

a. To allow payload operation by a single operator, 

and two operators. 

b. To conform with the basic console appearance 

design established by the Laboratory Vehicle 

contractor. 

c. Such that sub-modules of the consoles can be 

installed and removed through a 32 in. clear 

circular hatch in the side of the Laboratory 

Vehicle. 

d. To accommodate those elements of the Mission 

Section subsystems which are mounted in or on 

the consoles. 

e. To allow for crew operation of the mission equipments and supporting peripheral equipment. 

f. To allow for the display of critical diagnostic 

data from the peripheral equipment for monitor 

and alarm purposes. 

g. To allow for the display of mission data for 

evaluation by the crew. 

t 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Data Re-entry Vehicle Subsystem 

General Requirements 

Manned-Automatic Configuration 

The Data Re-entry Vehicle subsystem (DRYS) shall 

include one Data Re-entry Vehicle (DRV), release mechanism, and 

auxiliary electrical and mechanical equipment required to evaluate DRV 

status, and to control DRV release and separation. Provisions shall be 

made to incorporate a second DRV. 

3. 3. 4. 2. 5. 2 Retro-Rocket Ignitor-Installation 

If required, because of shipping regulations, the DRV's 

shall be designed to allow installation of the ignitors in the rocket motors 

at the Launch Complex without dis-assembling the DRV, and without 

invalidating any previous testing. However, electro-explosive devices, 

i. e. , initiators, shall be shipped separately and installed at VAFB at the 

latest practicable time compatible with safety and operational requirements. 

3. 3. 4. 2. 5. 3 DRV Environmental Control 

The environmental control shall maintain the internal 

20° DRV temperature within 700 + 30 F. This will be accomplished, using 

- 

both passive and active thermal control as required. 

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 3 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 DRV launcher tube. 

3. 3. 4. 2. 5. 4 Pre-Launch Testing 

At the launch pad, the DRV subsystem shall be capable 

of all necessary pre-launch tests as part of an overall system test while 

fully assembled and mated with the Laboratory Module. 

3. 3. 4. 2. 5 

3. 3. 4. 2. 5.1 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL v a t 

3. 3. 4. 2. 5.5 Data Re-entry Vehicle (DRV) 

The DRV shall be the Mark V. 

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, and be capable 

of being deboosted from any position on the orbits defined in paragraph 

3.1.1.1. 4. 2. 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 its payload during launch, orbit, and re-entry operations; and 

will supply status data via telemetry. Its capabilities shall include: 

preparation for de-orbit and separation from the DRVS support structure, 

re-entry and recovery. 

(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. 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. 

(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 for a minimum of 10 hours. 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. 

SPEC! ° 

- 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 , 

(5) The DRV shall 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 DRV subsystem. The DRV shall be ejected so as to 

place it in the correct attitude, and then spin stabilized prior to ignition of 

the retro-rocket. 

c. Deboost and Re-entry Dispersions 

At DRV separation, with the OV under the control of 

the primary stabilization system, the impact point of the DRV shall be 

within a rectangle + 75 nm in-track and + 8 nm cross-track (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 

acceptable dispersion rectangle will be increased by a factor of 2. in each 

dimension. 

d. DRV Electrical Subsystem 

Power required in the DRV shall be supplied by the 

EPSD subsystem of the Mission Payload System Segment until the battery 

has been activated. The DRV will require no more than two electrical 

signals to prepare it for deboost. 

The electrical design of the DRV subsystem, 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 bettery voltages 

and temperature, heat shield temperature and loop continuity. DRV 

sequencing and discretes will be monitored by beacon modulation after 

DRV separation. 

-;t. 3 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPEr 

3. 3.4. 3 Functional Interfaces 

(Functional interface documents shall be listed here, 

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

3. 3. 4. 4 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). 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

PRELIMINARY 

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SPECIAL hhhibliNG 

lei )1.1.a tai 

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3. SPEC. NO. 

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4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

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6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.5.2.4.3 Crew Performance Tests 

Delete entire paragraph 

SPECIAL HANDLING 

3-25 
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MOL System 

3. SPEC. NO. 

SS-MOL-1 

4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

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6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.1.7.3 Command (C-4) 

Change first sentence to read as follows: 

"Commands to the Gemini B shall up-date displays and the 

computer." 

--SERET-s' r • 

- ;4- 
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RELEASE 1 JULY 2015 

PRELIMINARY 

El FINAL 

SPECIFICATION CHANGE NOTICE 

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N/A 

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. 

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6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 3. 9.1. 9. 5 Data Flow, Computation, and Display (C-4) 

Add the following at the end of the section (as modified by SCN #3): 

The capability to up-date the orbit determination and ephemeris 

prediction every orbit revolution shall exist in the software. 

The capability to transmit up-dated orbit parameters to the 

vehicle within one orbit revolution of receipt of the tracking data 

for the orbit up-date shall exist, provided a SCF tracking station is 

available. 

Is 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

1°:n SpEn 

t..1% 

UL(:jjuLL,-_, 

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1;;J FINAL 

SPECIFICATION CHANGE NOTICE 

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3. SPEC. NO. 

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4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

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6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 4.1. 2.1 General Requirements 

Change fourth sentence from: 

"Limited qualification tests such as thermal-vacuum and EMI, 

shall be performed on the development test article at the system 

segment level." 

-to read: 

"Qualification tests shall be performed on qualification test articles 

at the system segment level." 
NRO APPROVED FOR 

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PRELIMINARY 

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Prorrram A3?, A 

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FILE OPPOSITE SPEC. PAGE NO. 

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6. EFFt.-4maTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 0. 4. 2 Target Access 

Add the following to the paragraph: 

It shall be an operational requirement to photograph as many 

targets as possible consistent with high quality stereo photography. 
NRO APPROVED FOR 

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5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

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6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.1.1.4.3 Command and Control 

Delete entire paragraph entitled "Manned - Automatic Configuration". 

4 

• 
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5. CONTRACTUAL AUTHORITY 

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FILE OPPOSITE SPEC. PAGE NO. 

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MOL Program 

7. TEXT CHANGE 

Paragraph 3.1.1.4.4 Mission Orbital Envelope 

Revise first sentence to read: 

The altitude range for photography shall be 

70 to 230 n. mi. 

Paragraph 3.3.1.4.6 Target Acquisition 

Paragraph misnumbered. Should be 3.1.1.4.6. 

Change the first sentence to read 

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° exclusive of target location error throughout the range 

of + 300 in track and + 40° cross track. 

6. 
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6. EFFECTIVITY 

MOT Pro am 

7. TEXT CHANG 

Paragraph 3. 1. 1. 4. 11 Security of Operations 

Insert the following addition prior to the existing paragraph. 

Provisions shall be made for the protection of materials 

revealing the Dorian aspects of the MOL system during launch, 

through recovery and subsequent disposal of the Laboratory 

Module and Mission Payload. Particular emphasis shall be 

placed on safeguarding target location information. 

a 
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7. TEXT CHANGE 

Paragraph 3.3. 1. 5.2 Malfunction Operations (Manned-Automatic Flights) 

Revise entire section to read 

To permit obtaining maximum useful performance data on 

the Mission Payload under flight conditions, the Orbiting Vehicle 

shall be designed so that operations of the Mission Payload hardware 

shall be possible if the flight crew cannot enter the Laboratory Vehicle 

for safety or other reasons. It is not intended that major design 

pertubations 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. 

Paragraph 3.3.1.5.3 Mission Payload Ground Handling 

Delete this section and replace with the following 

Paragraph 3.3.1.5.3 Support Module (Automatic Mode) 

For automatic mode operations, the Gemini B 

shall 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. Provisions shall be made 

to carry and launch six Data Re-entry Vehicles (DRV's). 

The design of the Support Module shall be such 

that additional propellants for 40 day missions can be accommodated, 

(see 3.0.1). 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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4. CONTRACT 

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5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

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6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 3. 2. 5. 1 Space Allocation Requirements 

Delete from the 6th line wideband transmitter and antenna 

Paragraphs 3. 3. 2. 5. 2 through Paragraph 3. 3. 2. 5. 5 

Delete existing paragraphs. 

Add the following paragraphs: 

Paragraph 3. 3. 2. 5. 2 Environmental Requirements 

The Laboratory Vehicle shall provide an environment 

such that the camera platens can be maintained at a temperature F. 

+20

30° 

0 

Film temperatures shall be maintained at a temperature of 70° F. The 

- 

relative humidity within the Laboratory Vehicle shall be such that condensate 

will not form on the film. 

Paragraph 3. 3. 2. 5. 3 Accessibility Requirements 

The Laboratory Module interior shall be arranged for 

crew access to perform the following mission oriented tasks: 

a. Film installation in the DRV's or film removal from 

the DRV's. 

b. Exchange of film cassettes. 

c. Operating and servicing of the film processor. 

d. Transfer of the DRV from the storage location to the 

launch tube. 

e. Spare parts installation or other required maintenance 

and servicing. 
ii.„1;1- 

z." a 

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3. SPEC. NO. 

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4. CONTRACT 

Program 632A 

5. CONTRACTUAL AUTHORITY 

CCN 

FILE OPPOSITE SPEC. PAGE NO. 

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6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

3.3.2.5.4 ACTS Requirements 

a. Maneuvering Capability 

The ACTS shall have the capability of orienting the 

Orbiting Vehicle to any pitch attitude. During pitch maneuvers, the pitch 

attitude determination accuracy shall be allowed to degrade, over that 

specified in 3.3.2.2.7.4.1, to a maximum (probability . 95) of 2% of the 

commanded angle change. The system shall be capabile of settling 

within 30 seccnds from the end of a maneuver down to within the accuracies 

specified in 3.3.2.2.7.4 prior to commencement of photographic operation. 

b. Photography on and off Signal 

During a photographic sequence, the MPSS shall provide 

a signal which may be used to inhibit the ACTS. Following the last photographs 

of a given target (or cluster of targets), an end-of-photography signal will be 

provided which may be used to enable the ACTS until the start of photography 

on the next target. During this between target period, not more than three 

seconds shall be required for the attitude control system to settle to within 

attitude and attitude rate specifications. 

c. Attitude and Rate Control during Photography 

At no time during photography (with probability 0.95 or 

better), shall the angular deviation of the coordinate axes at Station 500, 

relative to the Local Vertical/Relative Velocity Vector, exceed the following: 

Pitch + 2.0 degrees 

Roll + 2.0 degrees 

Yaw + 1.0 degrees 

Similarly, the three combined axes attitude rate shall 

not exceed 0.015 degrees per second (with a probability of 0.95). 
NRO APPROVED FOR 

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FILE OPPOSITE SPEC. PAGE NO. 

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6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

3.3.2.5.5 Mission Module Structure 

The forward section of the Mission Module structure shall 

contain an aperture, approximately 12 feet long by 130 degrees, through 

which the target will be viewed. During transport and launch, this opening 

shall be covered by an ejectable door. 

Separation devices for items such as the ejectable door, when 

activated, shall not cause damage to the payload and peripheral equipment, 

mis-align equipment outside adjustment capability, or cause contamination 

of sensitive equipment to occur. 

3.3.2.5.6 Decryption Requirements 

Data of an encrypted nature received from the MCC (via 

tracking stations) shall be circulated through government furnished decryption 

equipment by the Laboratory Vehicle Command Subsystem prior to its 

dissemination to either Laboratory or Mission Payload Segments. 
NRO APPROVED FOR 

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6. £.1- r EETIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 3. 4 Mission Payload System Segment 

Delete entire section 3. 3.4 (Pages 3-104. 1 through 3-104. 3 3 ) 

and replace with the following pages. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 cPPP,r'l 

3.3.4.5 Mission Payload System Segment 

(Note the green pages under Section 3.3.4 supplement the 

white pages). 

The forward portion of the Mission Module Structure shall 

house the tracking mirror and be termed the TM Bay. The aft portion of 

the Mission Module Structure shall support the Camera Optical Assembly 

and be termed the COA Bay. 

The Mission Payload System Segment AVE shall be composed of two sections as follows: 

a. Mission Section 

This section shall consist of the following AVE subsystems: 

(1) Structures and Thermal Control (TM Bay) 

(2) Navigation and Control (NCS) (Includes 

Communication, Command and Instrumentation) 

(3) Electric Power and Signal Distribution 

(4) Consoles and Displays (Manned-Automatic only) 

(5) Data Re-entry Vehicles 

(6) Terrain Camera 

(7) Acquisition 

(8) Automatic Support 

b. Photographic Section 

This section shall consist of the following AVE subsystems: 

(1) Structure and Thermal Control (COA Bay) 

(2) Camera 

(3) Primary Optics (Camera Optical Assembly and 

Tracking Mirror) 

77-7-',K71:3 
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(4) Visual Optics (Manned-Automatic only) 

(5) Film Handling 

(6) Electrical and Instrumentation 

(7) Film Processor (Manned-Automatic only) 

(8) Image Motion Detector 

(9) Automatic Support 

3.3.4.5.1 Allocated Performance and Design Requirements 

The effectiveness allocation of the Mission Payload System 

Segment for the total mission shall be apportioned as follows: 

Manned-Automatic Automatic 

Mission Section 

Photographic Section 

Combined Effectiveness . 95 . 80 

3.3.4.5.1.2 Weight 

Within the Mission Payload System Segment, the maximum 

design allocations of weights shall be as follows: 

Manned-Automatic Automatic 

Mission Section 2800 

Photographic Section 5633 

8433 lb. 8320 

3.3.4.5.1.3 Electric Power 

Mission Section 

Photographic Section 

500 watts 
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3. 3. 4. 5.1. 4 On Orbit Alignment 

It shall be a requirement that precision alignment of the 

main optics and camera be capable of being performed automatically in orbit. 

A capability shall be provided in the Manned-Automatic mode for disabling 

the automatic feature and for either the crew to perform precision alignments 

of the main optics and camera, or for the alignments to be made by ground 

command. 

3. 3. 4. 5.1. 5 Design Considerations 

Mission Payload System Segment design criteria shall be 

such as to minimize launch base test requirements and to maximum payload security. 

3. 3. 4. 5.1. 6 Flight Termination System 

There are no functional flight termination system requirements for the Mission Payload. Launch abort and eauipment recovery will 

include security provisions for Mission Payload Syst em Segment equipments 

(e. g. , target cues). 

3. 3. 4. 5.1. 7 Torque Disturbances 

The torque disturbances due to outgassing, magnetic 

materials, and other sources of external OV torque associated with mission 

equipment shall not exceed 0.25 ft. lbs. or a total of 5 x 104

ft. lbs. sec. 

for the 30-day mission. The torque disturbances due to internal Mission 

Payload moving parts shall not cause changes in OV angular momentum which 

exceeds the following during the period beginning one minute before and ending 

immediately after an active photographic pass: 

Yaw angular momentum + 25 ft. lb. sec. 

+ 25 ft. lb. sec. 

+ 25 ft. lb. sec. 

Pitch 

Roll 
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The maximum moment imposed on the OV by torquers within the Mission 

Module shall be: 

Roll TBD ft. # 

Pitch TBD ft. # 

Yaw TBD ft. # 

3. 3. 4. 5. 2 Peculiar Performance and Design Requirements 

(Mission Section) 

The Mission Section AVE subsystem design requirements 

presented in this section supplement those contained in 3.3.4. 2 of the white 

pages. The Photographic Section AVE subsystem design requirements are 

presented in 3. 3. 4. 5. 3. 

3. 3. 4. 5. 2. 1 Structure and Thermal Control Subsystem 

3. 3. 4. 5. 2. 1. 1 Mission Module Structure Design (TM Bay) 

The TM Bay shall house the tracking mirror and its 

supporting gimbal, the thermal door assembly with its associated bellows 

and environmental doors, ejectable door, star tracker door, mission section 

electronic equipment, heaters, AGE cooling ducts, test connectors, and 

access doors. 
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3. 3. 4. 5. 2. 1. 2 Support Structures 

Supporting structures shall be provided for housing 

and/or mounting the Mission Section equipment in the TM Bay and the 

following MPSS equipment in the Laboratory Module: 

a. Mission Section Consoles and Displays 

b. ATS mounts (2) 

c Visual Optics mounts 

d. Terrain Camera mounts 

3.3.4.5.2.1.3 Thermal Control (TM Bay) 

The Mission Section Thermal Control Subsystem shall 

maintain the temperature of the Tracking Mirror and other equipment installed in the TM Bay within specified limits. In fulfillment of this requirement, use shall be made of coatings, insulation, heaters and environmental 

doors. 

3.3.4.5. 2.1.3.1 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. 5. 2. 1. 3. Powered Flight 

The thermal control subsystem shall be activated prior 

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

3.3.4.5.2.1.3.3 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. 
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3. 3. 4. 5. 2. 2 

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

Navigation and Control Subsystem (NCS) 

General 

The Navigation and Control Subsystem shall provide for 

control of the camera, acquisition scopes, tracking mirror, and thermal 

doors using stored commands and computations provided by the computer. 

Requirements for communication, command, and instrumentation are included herein. 

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. 

3.3.4.5.2.2,2 Target Acquisition and Selection (Manned-Automatic) 

The NCS shall provide closed loop control of the Acquisition and Tracking Scopes (ATS). The control interface shall be similar to 

that provided for the primary tracking mirror. Manual controller inputs 

shall be accepted from the crew to slew the ATS in the manned search mode 

for target centering or for minimization of tracking rate errors. It shall 

be possible for the crew by activation of a switch, when a target is centered 

and its apparent motion minimized, to up-date the position and rate information utilized by the NCS. Each crewman shall have a capability to control 

either of the acquisition scopes by an appropriate target transfer operational 

sequence. The design shall be such that it is impossible for both crewmen 

to simultaneously control the same acquisition telescope. 

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. 
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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. 5. 2. 2. 3 Main Optics Tracking 

The NCS shall provide closed loop control of the tracking 

mirror. The tracking mirror shall be capable of pointing the line-of-sight 

+ 40° in roll (left and right of the X-Z plane), 30° forward in pitch and 40° 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, utilizing the same hand controller used to train 

the ATS during target acquisition. 

The accuracy and resolution of the digital interface 

with the motors and instruments shall be designed for compatibility with 

the mirror servo-mechanisms. 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. 5. 2. 2. 5. 

3.3.4.5.2.2.4 Minimum Time Between Targets 

The time in seconds between adjacent targets achievable 

by the system shall be no greater than + 3 or 

A17- 

6 + 3 seconds, 

which ever is larger, where and All are the stereo and obliquity angle 

changes, respectively, in degrees commanded between targets. 

3.3.4. 5. 2. 2, 5 Sequential Control 

The NCS shall provide for the sequential control of the 

Mission Payload System Segment. This function shall include the execution 
NRO APPROVED FOR 

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of real time commands within one second of their receipt, and the execution 

of stored commands within 200 msec. of the time indicated by their associated 

time label. Stored commands shall be employed for housekeeping tasks not 

directly related to photography. 

During a single forward to rearward motion of the 

tracking mirror, the NCS shall sequence the events required to photograph 

a single target, or a cluster of targets. 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. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 4. 5. 2. 2. 6 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. 5. 2. 2. 7 Camera Control 

The Navigation and Control System (NCS) shall provide open 

loop adjustments and commands, and off-axis Image Motion Compensation. 

(IMC) control. The open loop adjustments shall include exposure slit width, 

focus setting for slant range, and settings for cross-format image motion 

compensation. Commands shall include camera choice (primary or secondary) 

and a start exposure signal. Calculations required for off-axis IMC shall 

be performed by the NCS. 

In the Manned-Automatic Configuration, camera override 

controls shall allow inhibiting of programmed exposures, manual camera 

selection, and initiation of exposures during non-programmed periods. 

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) angeles. Normally, three different exposure settings shall be 

used for each target. The nominal sequence rate shall be 1 frame per second. 

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 to the 

camera for use by the data lamps. This information shall include a convenient 

rev and frame identifier; system time, accurate to one millisecond, which 

can be sampled by the camera for recording time of exposure; exposure 

setting; across-the-format IMC settings; 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 (2 sigma). 
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`tpiLdlt.1

rt 

Manned-Automatic Version 

The NCS shall provide control signals to select the film 

to be positioned for each exposure. 

3. 3. 4. 5. 2. 2. 8 Image Motion Compensation (IMC) 

By further processing the orbit ephemeris information 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. The NCS shall provide information to the Image Motion Detector 

(3. 3. 4. 5. 3. 5. 8) equating to a V/H error no greater than one percent. The 

Image Motion Detector shall return error signals proportioned to the in-track 

image motion and the cross component resulting from yaw error. These 

error signals shall be fed, as correction signals to the main optics tracking 

mirror control loop, to reduce the image motion. 

Manned-Automatic Configuration 

Manual hand controller inputs shall be accepted from the 

crew to correct image rates. These corrections shall apply to the orbit 

reference, and affect following targets. The use of either the image motion 

detector inputs or primary optics viewing and hand control inputs for 

tracking mirror control shall be a crew option. 

Provisions shall be made for manual hand controller inputs 

when computer aiding is partially or completely deleted because of malfunction. 

3. 3. 4. 5. 2. 2. 9 Alignment Monitor Set 

The NCS shall include an alignment monitor set which shall 

monitor relative alignments between the main optics, star tracker, and 

tracking mirror. Pointing errors due to vehicle thermal distortions and 

motions of the optical barrel in its mount shall be minimized by the computation and provision of correction signals to the ATS and tracking mirror 

control loops. 
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3. 3. 4. 5. 2. 2. 10 Communications and Instrumentation 

Two data services shall be provided for MPSS telemetry 

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. 

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. 

Although the up-link command rate is 1 kbps, NCS equipment shall be designed to accept data at a 10 kbps rate. 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. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 4. 5. 2. 2. 11 Data Readout Assembly (Manned-Automatic) 

A readout assembly shall be provided for the transmission 

of photographic information to the ground at a rate of 20 mbps and compatible 

with the SCF S-band data link. The primary requirements for this system 

are quality, reliability, and security. The data readout subsystem shall 

interface with the Laboratory Module communication subsystem for transmission. 

3. 3. 4. 5. Z. 2. 11.1 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. 5. Z. 2. 11. 2 Quantity 

The readout subsystem shall read out the maximum area 

of photographic material consistent with the other requirements in Section 

3. 3.4. 5. 3. 7. The subsystem shall scan and transmit 5 square inches in 

4 minutes. 

3. 3. 4. 5. 2. 2. 11. 3 Operational Employment 

Operation of the readout subsystem shall require a minimum 

of the crews 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. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 4. 3. 2. 2. 12 Reliability 

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. 

3.3.4.5.2.3 Electric Power and Signal Distribution Subsystem 

The Mission Section EPSD subsystem will receive power 

from the Laboratory Vehicle and distribute it to the Photographic Section and 

to the various Mission Section subsystems. 

3.3.4. D. 2.4 Console and Displays Subsystem 

The Mission Section Consoles and Displays shall be designed 

to enhance the crew contribution in obtaining the greatest number of high quality 

photographs on a timely basis. Appropriate controls and displays shall be 

provided to permit the crew to utilize these equipment design features incorporated 

for degraded operational modes. 

The Mission Section Consoles and Displays subsystem equipment shall be located in Consoles 8, 1, 2 & 3. Consoles 2 and 8 provide the 

controls and displays to accomplish the acquisiti on, tracking and photography 

of targets. Console 1 contains the camera, the camera focusing and alignment 

controls, the film cassette, and the film status displays. Console 3 contains the 

film processing and readout equipment. 

Various other controls and displays shall be appropriately 

grouped in Consoles 1, 8, 2 and 3 for accomplishing and/or displaying various 

other functions, including the following : 

(a) Power switching for various mission equipments (star 

tractor, V/H sensor, voice recorder, terrain camera, etc.) 

(b) DRV Control panel 

(c) Thermal door position and main mirror position display 

(d) Digital and/or analog displays of target prority, time to 

next photo exposures 

(e) Master warning and master caution lights for mission 

equipment status information. 
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RELEASE 1 JULY 2015 

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3.3.4.3.2.3 Data Re-entry Vehicle Subsystem 

(The requirements given below supplement those contained 

in 3. 3. 4.2. 3 of the white pages. ) 

3.3.4.5.2. 5.1 General Requirements 

Automatic Configuration 

In the Automatic Configuration, six DRV's shall be carried 

in the Support Module. The requirements to convert from the Manned-Automatic 

to the Automatic Configuration are given under the Automatic Support Subsystem. 

The DRV used in the automatic mode shall be the same type used for the MannedAutomatic mode. Each shall have the capability of returning 58 lbs. of primary 

record and 4 lbs of terrain film. 
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RELEASE 1 JULY 2015 

3. 3. 4. 5. 2. 5. 2 DRV Environmental Control 

The relative humidity shall be controlled so that no 

condensate will form on the film. 

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. 

3. 3. 4. 5. 2. 6 Terrain Camera Subsystem 

The 70 mm terrain camera shall be provided to the 

Mission Section Contractor as GFE. The camera shall be mounted internally 

on the underside of the Laboratory Module forward of the acquisition scopes. 

An optical window and camera attachments shall be incorporated into the 

Laboratory Module shell. Protection shall be provided as necessary to 

preclude degradation of the optical properties of the window during powered 

flight. The camera shall contain sufficient film for two exposures of every 

target photographed by the main camera. Exposed terrain carmera film shall 

be returned to earth, via the Gemini B in the Manned-Automatic mode and 

via the last (6th) DRV in the Automatic mode. 

3. 3. 4. 5. 2. 7 Acquisition Subsystem (Manned-Automatic) 

The Acquisition subsystem shall perform the following 

functions: 

a. Provide means to observe the ground and to recognize 

and track up to two targets simultaneously. 

b. Provide cueing materials to assist crew in target 

location. 

c. Provide displays at each reconnaissance console and 

means to transfer displays and control between consoles. 

All Acquisition subsystem components (except buried cables) 

shall be designed for removal during conversion from Manned Automatic to 

Automatic mode. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 4. 5. 2. 7.1 Acquisition and Tracking Scopes (ATS) 

Two acquisition and tracking scopes are required. The 

optical axes of the scopes shall be capable of being trained from + 70o to -40o 

in-track, and + 45° cross-track. The NCS shall provide closed loop control 

of these devices. Manual hand controller inputs shall be accepted from the 

crew and corrected position and tracking rate data shall be fed to the computer 

to aid in target acquisition by the main optics. 

The scope image shall provide for a minimum magnification 

of 5 power, with a 4° field of view, with means for adjusting the optical 

magnification up to at least 25 power (0. 8° field of view). The entire scene 

obtained by the optical elements of the acquisition telescope shall be displayed. Each crew member shall have a single control which permits 

changing the magnification of the acquisition telescope being directed by the 

hand controller. The magnification controller, with an appropriate mode 

change, shall also be utilized to control the magnification of the primary 

visual optics (see paragraph 3. 3.4. 5.4). It shall be a design objective to 

also provide lx for a wide field of view. 

The slew rate capability of the ATS shall be at least 

20 degrees per second in both pitch and roll. 

3. 3. 4. 5. 2. 7. 2 Resolution 

The resolution of the Acquisition subsystem, when set 

for minimum magnification shall be such as to be able to detect, at an 

altitude of 80 nautical miles, line patterns of 50 foot wide black and white 

lines having a contrast ratio of 2 to 1. 

3. 3. 4. 5. 2. 7. 3 Target Cue Display 

A means of displaying target cues shall be provided on 

each reconnaissance console. The capability shall exist to display the target 

cue with proper scale corresponding to the optical power of the tracking device 

(ATS or main optics eye-piece) being used. 

3. 3. 4. 5. 2. 8 Automatic Support Subsystem 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 4. 5. 2. 8.1 Functional Requirements 

The Automatic Support subsystem shall provide for the 

conversion of the Mission Section hardware for Automatic mode operations. 

It shall perform the following functions: 

a. Provide a means for automatic de-orbiting and 

retrieving all exposed film from the OV. 

b. Provide a means for automatically inserting main and 

terrain camera film into the DRV's. 

c. Provide for system electrical continuity and loading 

when Manned-Automatic equipments removed. 

The Support Module Structure and fairing shall be supplied 

by the Support Module Contractor. The film tunnel, film cutters, and 

sealers shall be provided by the Photographic Section Contractor. 

3. 3. 4. 5. 2. 8. 2 Hardware Changes 

The Automatic Support subsystem shall include: 

a. The conversion requirements to remove the acquisition 

and tracking scopes, MPSS consoles and displays, DRV's, and other MannedAutomatic mode equipment from the Laboratory Module, together with the 

plugs, seals, and adapters required when this equipment is removed. 

b. Six 33 inch DRV's to be installed in the Support Module. 

c. An automatic programmer, electrical power and thermal 

control provisions for the Support Module. 

d. DRV attachment and ejection provisions. 

e. Support Module instrumentation. 

Note: The Support Module is not part of the Mission Section. 

3.3.4.5.2.8.3 DRV's (Automatic Mode) 

The DRV's used in the Automatic mode will be the modified 

Mark V's specified for the Manned-Automatic mode, except that the last one 

of the six ejected shall include provisions for take-up and returning up to 

4 lbs. of 70 mm terrain camera film in addition to the normal load of 9. 5 inch 

main camera film. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3.3.4.5.3 Peculiar Performance and Design Requirements 

(Photographic Section) 

The Photographic Section shall contain optical, mechanical, 

thermal, electrical, and structural components necessary to perform high 

quality, stereo, photographic reconnaissance. 

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 Module. The Ross corrector 

assembly shall be above and approximately parallel to the optical axis of 

the primary mirror. 

A frame camera utilizing 9-1/2 inch wide film shall be 

located at the end of the Ross corrector barrel on the Laboratory Module 

pressurized side of the bulkhead. 

The total film supply for the primary and secondary 

cameras shall be sufficient to obtain 15,000 frames of photography for a 

30-day mission. The 15,000 photographs may be apportioned by command 

between one and ten photographs per target. The capability shall exist 

to carry up to 20,000 frames (approximately 300 lbs. ) of primary film 

for Automatic mode flights up to 40 days in duration. 

The primary output shall be a latent image recorded on a 

black and white film having the resolving power of Type 3404, but an exposure 

index of 6. The on-axis static, nadir lens-film resolution as a function of 

apparent contrast shall be as indicated in Figure 3-6 when the film has received optimum exposure for a ground scene luminance of 890 feet-lamberts 

and is forced processed in D-19 developer. 

3.3.4.5.3.1 Structure and Thermal Control Subsystem 

This subsystem shall consist of the following: 

a. The COA Structure which shall tie together the 

primary mirror, the folding mirrors, Ross corrector assembly, and the 

main camera. 
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NRO APPROVED FOR 

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RELEASE 1 JULY 2015 

b. The mounts to tie the COA Structure to the Mission 

Module COA Bay, the launch locks for the main optics. 

c. The thermal control of the COA. 

3. 3. 4. 5. 3. 1. 1 COA Structure 

The COA Structure shall provide the necessary support, 

orientation and protection to components of the COA (less Tracking Mirror) 

during handling, transportation, launch and orbit. It shall accurately 

position the primary mirror, folding mirrors and Ross corrector barrel 

relative to the Mission Module attachment points. 

3. 3. 4. 5. 3.1. 2 Mechanical Mounting (COA to Mission Module) 

a. General 

Suitable mechanical mountings for the COA 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. 

b. 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 mounting constraints. 

c. Powered Flight 

The Photographic Section shall be mounted in such 

a way that launch forces cannot endanger the Photographic Section or its 

subsequent performance. 

d. Orbit 

The mechanical mountings during flight must be such 

that no performance degradation results. 

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. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

S 

3. 3. 4. 5. 3.1. 3 COA Bay Thermal Control 

a. General 

The Photographic Section thermal control subsystem 

shall provide proper temperature control for the COA Bay 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. 

b. 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. 

c. 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. 

d. 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. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 (,6= 0, 21 June) and nominal albedo (. 38). 

3.3.4.5.3.2 Camera Subsystem 

3.3.4.5.3.2.1 Primary 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. 

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 9-1/2 inch film. 

Focus adjustments shall be made by ground command. 

Suitable sensor indications shall be passed via telemetry so that the required 

commands may be determined. A capability for the crew to make adjustments 

shall be provided. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPEC NG 

3. 3. 4. 5. 3. 2. 2 Secondary Camera (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. (replacing 

the secondary platen with the primary platen also shall not take longer than 

1 second). The secondary platen shall use the same film format and data 

imprinting as the primary platen. 

3. 3. 4. 5. 3. 2. 3 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. 8o diameter circle about the center of the format 

will be greater than that given by Figure 3-7. Across-the-format IMC shall 

be used only for the primary record. 

3. 3. 4. 5. 3. 2. 4 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 
c94 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPECIAL HANDLINO 

c 

00 (on axis) performance without 

X-Format ii 100% 

SEMI-FIELD ANGLF (DEGREES) 

(DEGREES) 

FIGURE 3-7. ACROSS-THE-FORMAT 

IMC REQUIREMENT 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

41. e 

Vehicle Attitude 

Tracking Mirror Position 

Exposure Slit Number 

Exposure Slit Orientation 

Vehicle Identification Number 

b. Special Markings 

(1) Fiducial Marks 

(2) Interframe Marks 

(3) Special Frame Marking (Auxiliary platen only). 

3. 3.4. 5. 3. 3 Primary Optics Subsystem 

3. 3. 4. 5. 3. 3. 1 Primary Mirror Assembly 

The primary mirror assembly shall be the complete 

assembly of the primary mirror, primary mirror mount, launch locks, 

alignment servos, and end cap. The primary mirror shall have a 70 inch 

diameter clear aperture. Its mount shall provide a minimum strain 

mounting system for the primary mirror when in a gravity-free environment. 

The alignment servos shall provide the capability of aligning the optical 

axis of the primary mirror to the optical axis of the Ross corrector assembly 

and provide a secondary means of focus adjustment. 

3. 3. 4. 5. 3. 3. 2 Diagonal Mirror Assembly 

The diagonal mirror assembly shall be mounted in the 

Newtonian folding position and be supported by a structural spider within 

the COA barrel. The diagonal mirror shall be a piano mirror mounted in 

a minimum strain mounting system. 

7.". 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 4. 5. 3. 3. 3 Tracking Mirror Assembly 

The Tracking Mirror assembly shall comprise the optical 

tracking mirror, its mountings, and launch locks. The tracking mirror 

shall be the main line-of-sight pointing element of the optical system. It 

shall be a 70-inch diameter, circular plano mirror mounted in a minimum 

strain mounting system. The tracking mirror shall be mounted in the 

tracking mirror gimbaled drive provided by the Mission Section contractor. 

3. 3. 4. 5. 3. 3. 4 Ross Corrector Assembly 

The Ross Corrector assembly shall include four refracting 

lens elements housed within a structural tube, the Ross diagonal mirror, 

the pellicle mirror and portions of the visual optics assembly. The 

assembly structure shall provide mountings for the Ross diagonal mirror 

and the camera. It shall be attached to the Laboratory Module bulkhead 

by means of the LM bellows pressure seal. Ross diagonal mirror servos 

shall provide two degrees of freedom to adjust the alignment of the optical 

axis of the Ross correctors assembly with the optical center of the primary 

mirror. 

3. 3. 4. 5. 3. 3. 5 Alignment Optics Assembly 

An alignment optics assembly shall be provided for automatic on-orbit alignment of the primary optics. The alignment device 

shall be pre-aligned to the Ross corrector optical elements, sense the 

apparent positional errors of the primary mirror and activate the 

alignment servos to restore optical alignment. Apparent tilt and longitudinal 

shifts of the primary mirror shall be corrected by motion of the primary 

mirror. Centering corrective motions shall employ two rotational degrees 

of freedom of the Ross diagonal mirror. 

3. 3. 4. 5. 3. 4 Visual Optics (Manned-Automatic) 

An optical system shall allow either crewman to look at 

the central portion of the camera field of view through the primary optics 

for the purposes of reducing rate error and/or making visual observations 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

of the target. Simultaneous operation of the eye-pieces is not required. 

A suitable reticle shall be provided for tracking. The reticle shall be 

programmed to stay in focus for any ground target within the photographic 

range. Consideration shall be given to a reticle with servo controlled 

transverse motions in case reticle quickening is found to be desirable. 

The part of the visual optical system which is attached to 

the Laboratory Module must be adjustable to compensate for any relative 

motion between the Laboratory Module and the Mission Module. 

The magnification of the system shall be variable within 

limits which shall be chosen by simulation of the tracking task, but the 

maximum magnification need not exceed-The minimum magnification 

shall be compatible with acquisition scope magnification for ease of crew 

adaptation when transferring attention from a target on the acquisition scope 

display to the same target in the visual optics. The apparent field of view 

shall be 40°. A derotation prism shall be provided which can be driven 

by the computer to maintain an erect image for all tracking angles. 

a. Minimum Acceptable Performance of Primary 

Visual Optical Subsystem 

Magnification continuously variable 

Apparent Field 40° full field 

Light Transmission 35% for visual relay only 

Revolving Power 

Central 10° 30 lines/degree 

Rest of field 15 lines/degree 

Eye Relief (min.) 40 mm 

b. Minimum Acceptable Performance of Secondary 

Visual Optics Subsystem 

Magnification 

Apparent Field 40° Full Field 

Light Transmission 30% 

Central 10° 25 lines/degree 

Rest of Field 15 lines/degree 

Eye Relief (min.) 40 mm 

4 

S 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

3. 3. 4. 5. 3. 5 Film Handling Subsystem 

3. 3. 4. 5. 3. 5. 1 Film Requirement 

The nominal film width shall be 9-1/2 inches. The primary 

reconnaissance film shall be black and white film having the resolution of 

Type 3403, but a speed of 6. Secondary reconnaissance films shall be 

provided. The secondary records shall also have a 9-1/2 inch nominal 

film width. For the Manned-Automatic mode, the vehicle shall carry a 

nominal film load of 13, 000 ft. , including both primary and secondary 

records. For the Automatic mode, the nominal film load shall be 17, 400 ft. 

of primary record only. Consideration shall be given to protecting the film 

from excessive radiation damage. 

3. 3. 4. 5. 3. 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. 

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. 3. 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 camera. 

3. 3. 4. 5. 3. 5. 4 Data Return Capsules (Manned-Automatic only) 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 ‘i d 

3. 3. 4. 5. 3. 5. 4.1 General 

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

as take-up 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 (for 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 DRC's shall have flotation capability. 

3. 3. 4. 5. 3. 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 maintained at a temperature of 70 _ 300F. However, the sealed film canisters 

are permitted to approach a maximum temperature of 120°F for a period 

not exceeding one hour. 

3. 3. 4. 5. 3. 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 take-up cassette/film alignment and adjustment 

during photographic operations. 

3. 3. 4. 5. 3. 5. 4. 4 DRC Film Weight Breakdown 

The DRC film weight breakdown shall be as follows: 

Data DRC's Weight (pounds) 

Primary Record 3 180 

Secondary Record/Cues 1 60 

Total 240 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Data 

Processed 

Color 

Infra -Red 

High Speed 

Cues 

Terrain 

Canisters 

2 

1 

1 

1 

1 

1 

Weight (pounds) 

20 

10 

10 

10 

6 

4 

3.3.4.5.3.6 Electrical Power and Instrumentation Subsystem 

3. 3. 4. 5. 3. 6.1 Electrical Power 

Electrical power for the Photographic Section shall be 

supplied by the Laboratory Vehicle via the Mission Section EPSD subsystem. 

3.3.4. 5. 3..6. 2 Instrumentation 

Suitable Photographic Section environmental and performance 

monitoring sensors shall be provided to enable real time and post flight 

diagnostic analysis. Photographic Section telemetry signals shall be 

passed to the MCC by the Laboratory Vehicle SGLS via the Mission Section 

C. &C. I. subsystem. 

3.3.4.5.3.7 Film Processor Subsystem (Manned-Automatic Configuration) 

3. 3. 4. 5. 3. 7.1 General 

An on-board processor shall be provided 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. The operation of the 

processor shall be automatic once the film to be processed is loaded and 

the controls set. 

3. 3. 4. 5.3. 7. 2 Acquisition 

There shall be supply cassettes of secondary record 

available for on-board processing. One of these cassettes shall be mounted 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

on the secondary camera prior to these 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. 4.5.3.7. 3 Processor 

The on-board film processor shall be capable of processing 

50 photographs with no more than 5 minutes per photograph total processing 

time. Batch sizes of less than 50 frames shall be processible but at slightly 

longer processing time per photograph. The processor shall not degrade 

resolution by more than 15 percent of the resolution obtainable with otpimum 

ground processing. All chemical contaminants shall be identified and controlled in such a manner that they will not in any way endanger the health, 

safety, or comfort of the flight crew. The processor shall be capable of 

operation in nominal Laboratory Module lighting conditions (10 ft-candles) 

and shall produce a photograph, dried to an RH comparable to the Laboratory 

Module RH level, and suitable for viewing and readout. 

3. 3. 4. 5. 3. 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 resolution limit. The microscope shall be capable of 

scanning an entire image. 

3. 3. 4. 5. 3. 8 Image Motion Detector Subsystem 

An Image Motion Detector (VIII Sensor) shall be provided 

as part of the Photographic Section. This Image Motion Detector shall be 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

snrr r.0 

5 

integrated into the Navigation and Control Subsystem (NCS) of the Mission 

Section. Using information from the NCS, equating to a V/R error no 

greater than one percent, the image motion shall be determined with 

sufficient accuracy to enable the image rate at the center of the format 

to be reduced to a value not to exceed 4 x 10-5 radians/ second (20— ). 

3. 3.4. 5. 3. 9 Automatic Support Subsystem 

The Automatic Support subsystem shall comprise those 

elements required to convert the Photographic Section from manned-automatic 

to automatic mode operations. It shall include the following: 

a. Automatic film handling and transport assembly. 

b. Film chute leading from the camera to the DRV's in 

the Support Module. 

c. DRV/film chute separation mechanism. 

3. 3. 4. 5. 3. 9. 1 Film Chute Design Requirements 

The film chute shall be designed to transport the film 

from the camera to each of the six DRV's in the Support Module. The chute 

shall be designed for up to 40 days of orbital operation without leakage while 

pressurized to 5 psia. Prior to ejecting a DRV, it shall be disconnected 

from the film chute and the chute sealed with negligible loss of pressurization 

gas. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 paragraph 3. 3.1. 2. 8, 

and those for the Laboratory Vehicle in paragraph 3. 3. 2.2.13. Requirements 

for MPSS alignment, special purpose and handling equipment are given below. 

3. 3. 4. 6.1 Alignment Equipment 

a. Mission 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. 

3. 3. 4. 6. 2 Special Purpose Equipment 

a. Mission 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. 

In addition, special power supplies stimulating the 

Laboratory Module CPS shall be provided for testing the MPSS. Fixtures 

for vibration testing also, shall be provided. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Special test equipment for thermal-vacuum testing 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 Section 

AGE shall be provided for handling and transporting the 

MM and other MPSS equipments within payload contractors' plants, and 

between contractors' plants. It is a design requirement that this AGE protect 

the MPSS AVE and control the AVE environments to levels within those the 

AVE is expected to experience while on the pad, at launch, during powered 

flight, and on-orbit. Specifically, the following guidelines apply: 

Shock and Vibration - isolation to levels within 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. 

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. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

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 temperature 

inside the Mission Module as follows: 

Temperature - 70°F + 5° normal requirement 

- 70°F + 1° starting 48 hours before launch 

The AGE shall provide incoming air to the Mission 

Module as follows: 

Cleanliness - Federal Standard 209 class 10,000, 

plus elimination of oils and volatiles 

in the atmosphere. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Q r01 Lk.' 

FkithAtf 

E PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 

PAGE OF 

DATE 

SUPERSEDING 

1. ECP NO. 

NPA 

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. 

3-122. 1 

6. EFFECTIVITY 

MOT. Program 

7. TEXT CHANG 

Paragraph 3. 3. 7. 5 Mission Payload Peculiar Facility Requirements 

Revise to read 

Adequate provisions shall be made in the checkout, maintenance, 

and launch areas for DORIAN environmental and special security requirements. The provisions of FED-STD-222 are applicable to the Mission 

Payload control room of the Launch Control Center. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 *s. 

fl PRELIMINARY 

g FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 

PAGE OF 

DATE 

SUPERSEDING 

1. ECP NO. 

N/A 

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. 

3-124.1 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 3. 8. 5 Mission Payload Peculiar Launch Operations Support 

2nd Paragraph. Revise 1st sentence to read 

The Mission Payload AVE, with the possible exception 

of the DRV's, arrives at VAFB integrated with the Laboratory 

Vehicle. 

4th Paragraph. End of sentence to read "required level 

of cleanliness of temperature, humidity control and security." 

Replace last paragraph with...... 

All explosive ordnance installation operations will be 

performed at the latest practicable time at the launch site as 

compatible with safety and operational requirements. Final 

arming of explosive ordnance systems shall be accomplished 

during the "T-Count" in accordance with these safety and 

operational requirements. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

E PRELIMINARY 

51 FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 

PAGE OF 

DATE 

SUPERSEDING 

1. ECP NO. 

N/A 

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. 

3-140.1 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3.3.9.5.1 Ground Support System Requirements 

2nd line. Delete "MOL System" and replace with "Mission Payload". 

Paragraph a. Delete last sentence. "The capability to update 

exist in the software." 

Paragraph e. 1st line. Delete "MOL System" and replace with 

"Mission Payload". Delete last sentence. "A capability for 

preliminary is taking place shall also exist." 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

its 

E PRELIMINARY 

FINAL 

SPECIFICATION CHANGE NOTICE 

NO. 

PAGE --_ OF 

DATE 

SUPERSEDING 

1. ECP NO. 

N/A 

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. 

3-150.1 

6. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 3. 3. 12. 5. 1 General Training Requirements 

Revise to read 

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 simulation, and operational design. The final 

integrated Mission Simulation (Mission Simulator) will include 

major crew functions for Mission Payload training such as: 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SPE' 

PRELIMINARY SPECIFICATION CHANGE NOTICE 

FINAL NO. 

PAGE OF 

DATE 

SUPERSEDING 

1. ECP NO. 

N/A 

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. 

4-15 

fi. EFFECTIVITY 

MOL Program 

7. TEXT CHANGE 

Paragraph 4. 3 Mission Payload Peculiar Flight Certification Testing 

Delete entire section 4.3 (pages 4-15 and 4-16), and replace with 

the following 3 pages. 

a. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Fm~u : 

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 MPSS Test Flow 

The Mission and Photographic Sections of the MPSS AVE, 

shall each undergo qualification and acceptance testing at the respective 

contractor's plant. Following completion of Mission Section testing, the 

equipment to be installed in the Laboratory Module shall be shipped to the 

Laboratory Vehicle integrating contractor's plant. The TM Bay shall be 

shipped to the Photographic Section contractor's plant for mating with the 

COA Bay. Following completion of thermal optical tests at the Photographic 

Section contractor's plant, the integrated Mission Module shall be shipped 

to the LV integrating contractor's plant. The MPSS integrating contractor 

shall then conduct acceptance testing on the MPSS prior to the start of 

combined Laboratory Module/Mission. Payload tests. 

4. 3. 2 Qualification Testing 

The MPSS equipment shall be qualified at the component, 

section (mission or photographic), complete Mission Module and complete 

Laboratory Vehicle levels of assembly. All equipment components shall 

undergo a qualification test program as individual components. The adequacy 

of the primary load-carrying structure of the Mission Module shall be 

verified in conjunction with the Laboratory Module structure. Acoustic or 

vibration, pyrotechnic-event shock, and thermal-vacuum (33 day) qualification tests shall be conducted on both the TM Bay and COA Bay separately 

as a requirement for qualification of equipment located in those bays. 

Dynamic performance characteristics of the Mission Module shall be verified 

at the Mission Module level of assembly. 

The Mission and Photographic Sections of the MPSS shall 

each undergo EMI/EMC testing at the respective contractor's plant. EMI/EMC 

testing of a complete MPSS shall be conducted in conjunction with the LM at 

the LV integrating contractor's plant. 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 SPLuihk„. 

4. 3. 3 Acceptance Testing 

All equipment components shall be required to operate 

without failure, malfunction, or out of tolerance performance degradation 

during or after exposure (as applicable) to both vibration and thermal-vacuum 

(5 days) acceptance tests. Acoustic or vibration, thermal-vacuum and 

EMI/EMC shall be conducted on both the TM Bay and COA Bay separately 

as a condition of acceptance. 

Dynamic performance characteristics of each Mission 

Module shall be verified at the Mission Module level of assembly. Preliminary information on the dynamic characteristics shall be obtained at 

the TM Bay and COA level of assembly. Final orbital dynamic characteristics 

of each vehicle will be verified by analysis, utilizing test data (resonant 

frequencies, structural damping, and model patterns) obtained during the 

LV vibration model survey. 

4. 3. 4 Development Testing 

4. 3.4.1 Thermal 

Thermo-vacuum tests shall be conducted on the TM Bay 

and COA Bay separately for development of the thermal control system. 

Insulation effectiveness, equipment operating temperatures, along with 

thermal control system location and operation shall be determined or verified. 

4. 3. 4. 2 Dynamic (Mode Surveys) 

Resonant frequencies, mode shapes and structural damping 

shall be determined by test of a dynamically simulated orbiting vehicle. 

Preliminary information on the dynamic characteristics shall be obtained 

at the TM Bay and COA level of assembly. 

4. 3. 4. 3 Acoustic and Pyrotechnic Shock 

Acoustic and pyrotechnic-event shock tests shall be conducted on a dynamically simulated TM Bay and COA Bay (separately or as 

a MM) to determine equipment vibration and shock levels throughout the MM. 

_ 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 kj

(IDEn, 

TA 1-2 ;1 

4. 3. 4. 4 Operational Performance 

The Mission Section and Photographic Section contractors 

shall conduct a development program to determine design feasibility, 

design adequacy, equipment performance, functional parameters, packaging 

and fabrication techniques, and performance testing techniques.