NRO APPROVED FOR 

RELEASE 1 JULY 2015 

• 

9 May 1968 

SUBJECT: Transmittal - SS-MOL-1B 

Allocations Document 

TO: R. Johnson 

E. Miller 

R. Pepping 

J. Sewell 

1. Attached are copies of the SS-MOL-1B Allocations Document, This 

document is an internal SPO technical management control document which 

is provided for your information as an aid in program coordination. 

2. In paragraph 3 of my letter dated 6 May 1968, you were informed that 

you would receive SCN-2. The technical content of the changes to the SPDR 

were not felt to be sufficiently important to include as a Specification Change 

Notice and the attached errata sheet will bring your copy of SS-MOL-1B up 

to date. The errata sheet is not intended to change the technical content of 

the SPDR but only to clean up inconsistencies and make clarifying editorial 

changes. 

Copy to: 

L. S. Norman 

C. L. Gandy 

I. B. Hanson 

C. C. Ledford 

L. D. Paige 

F. H. Dietrich 

B. F. Knolle 

B. Moss 

R. S. Gaylord 

W. D. Pittman 

G. D. McGhee 

W. C. Williams 

J. F. Chalmers-e' 

L. A. Skantz 

D ro 11 cia l,ki 

L-5641 

Copy 6'of le copies 

N rt Page / of 1 page. 

rrs. 

' 1• 

: • 
NRO APPROVED F R 

RELEASE 1 JULY 2015 

SS -MOL - 1B 

ALLOCATIONS DOCUMENT 

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SECTION 

TABLE OF CONTENTS 

TITLE PAGE 

1.0 

2.0 

2.1 

2.2 

INTRODUCTION 

ALLOCATIONS 

OV Weight 

CPS Power 

4 

5 

5 

8 

irtr 

2.3 Mission Effectiveness 10 

2.4 PLOT 12 

2.5 Safety Numerics 14 Ka= 

2.6 Voice Link 16 

2.7 Communication RF Link 19 

2.8 Telemetry 21 

2. 9 Monitor /Alarm 25 

2.10 Computer Memory 27 

2.11 External Data Storage 29 

2.12 FV Transmission Frequencies 31 

2.13 OV Grounding Isolation 33 

2.14 Thermal Loads 35 

2.15 Atmosphere Leak Rates 37 Page 2 of 83 

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• 

SECTION 

TABLE OF CONTENTS (Continued) 

TIT LE PAGE 

2.16 

2.17 

2.18 

Contamination 

Guidance Insertion 

Unobstructed LOS 

39 

41 

43 

fax; 

Inn 

2.19 Main Optics Light 46 

2.20 Main Optics Pointing Accuracy r 49 

2.21 Main Optics Smear (On-Axis) 53 

2.22 Film Plane Vibration (Main Optics) 59 

2.23 ATS Pointing Accuracy 62 

'Z-477 

2.24 ATS Rate Accuracy and Jitter 66 

2.25 Vibration (ATS Operation) 70 

2.26 Star Tracker Command Accuracy 72 

2.27 Translational Momentum Disturbances 74 

2.28 Torque Disturbances 79 

L-5611 Appendix I ACTS Attitude and Rate Accuracy 82 

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• 

1.0 INTRODUCTION 

This document contains contractor allocations against specific numerical 

requirements of SS-MOL-1B. These contractor allocations are to be 

'incorporated in the applicable CEI/IFS or SOW. 

For each numerical requirement, the SS-MOL- la/paragraph and the 

allocation against this requirement are presented. Entries in the 

"CEI Reference" column of the allocation pages refer to those items 

which are or should be incorporated in the applicable CEI/IFS or SOW. 

This document is noncontractual and is provided for referenc_e only. 

sn7-1 -

cG 

Li— 

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2.0 ALLOCATIONS 

2.1 OV WEIGHT 

Performance Requirements 

The Titan IIIM shall be capable of inserting a MOL payload of 30,850 

pounds into an orbit having an apogee altitude of 187 na. miles, a perigee 

altitude of 80 na. miles, with perigee placement at 45 degrees north tr= -

. latitude, and an inclination of 90 degrees. This performance requirement is applicable to both the manned-automatic and'automatic configurations. 

Ii 

E=7:2 

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-B3.3.1.3 

EW 

'M -A3.3. lb -Loy 

AMPS3.3. lc 

lb 

a 

,..7="2-34EW 

Annex. 1, 

1, 5, I, E 

PSA3.3.1.1 

E0S3.3.1.1 

CWG3.3.1.1 

NEW 

NEW 

Basic Pressure Garment -

HS (2) 

Emergency 02System (2) 

Constant Wear Garment -

Spares • 

Miscellaneous Components 

69.78 

13.70 

22.0 

19.3 (Est. ) 

PSA-GFE 1.5 

NRO APPROVED FOR 

RELEASE 1 JULY 015 

CEI 

REFERENCE 

SS -MOL-1B 

REFERENCE 

• 

OV Weight 

The OV contractual weight allocations (April, 1, 1968) for the manned 

automatic configuration are as follows: 

SPEC. WEIGHT 

ITEM LT'S 

GBSS AVE 

GB GFE 

Gemini B 

LVSS AVE 

LM -DAC 12,253 

MM Primary Structure 2,105 

LM GFE 90 

5,600 

59 

5,659 

3.3.6. 2, 

MMSS AVE 

MM -GFE 

PSS AVE 

PSASS 

LV -DAC 14,448 

2,935 

122 

LV -GE 2,557 

5,714 

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REFERENCE 

NEW 

NEW 

OV Weight (Continued) 

ITEM 

Food SS 

Flight Crew 

SS -MOL -1B 

REFERENCE 

SPEC WEIGHT 

LBS 

102 

360 

OV Total 28,966 

Reserved Weight 

1 Mark V DRV 475 

Wideband Scan 485 

Total Reserved 960 

OV weight allocations for the automatic configuration are not 

available at this time. 

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2.2 CPS POWER 

3.1.1.6.17 Orbiting Vehicle Electrical Power 

The Laboratory Vehicle central power system shall be a nominal 28-vdc 

power system, shall provide the total power requirements for the 

Laboratory Vehicle and Mission Payload, and shall provide part or all of 

the power to the Gemini B from early orbit to the late orbit phase. For the 

manned-automatic configuration, the average power demand over the 

nominal mission duration shall not be greater than 1.825 kilowatts (net) 

with peaks not greater than 4.5 kilowatts (net). 

For the automatic' configuration, the average power demand over the 

extended mission duration shall not exceed the capability of the equipment 

developed for the manned-automatic configuration except for added 

expendables. 

Power utilization for peak and average power for each Orbiting Vehicle 

segment shall be as specified in SAFSL Exhibit 30001. All OV equipment 

requiring power outside the characteristics of the LM Central Power 

System (CPS) shall provide individual power conditioning equipment. 

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3.1.1. 6.17 

NRO APPROVED OR 

RELEASE 1 JULY2015 

• SS-MOL-1B 

REFERENCE 

CEI 

REFERENCE 

DAC -NEW 

GE-NEW 

MAC -NEW 

EK-CCN #11 Average Total 

Power Oxygen Hydrogen Reactant 

Watts lbs lbs lbs 

Allocated Power 

Consumption 1825 1036.4 133.6 1170.0 

Unallocated 

Contingency 182 103.6 13.4 117.0 

TOTAL 2007 1140 147 1287 

The contingency is reserved to cover: 

CPS Power 

Power allocations for the manned-automatic configuration are given in 

SAFSL Exhibit 30001. The 30-day average power allocation are based upon 

maintenance of the following reactant allocation and contingency position. 

a. uncertainties in fuel cell characteristics 

b. load uncertainties 

c. timeline effects (reactant consumption is a non-linear function of 

instantaneous power drain). 

Additional average power capacity may be provided to the limit of tankage 

capacity at the rate of 0.88 lbs of reactant per kilowatt hour. 

Power allocations for the automatic configuration and for Flight No. 2 

are not available at this time. L-5611 

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a 

2.3 MISSION EFFECTIVENESS 

3.1.3.1 Effectiveness 

The MOL Program shall provide a capability for stereo photographic 

reconnaissance, to include both manned and unmanned operations, with a 

probability of 30-day mission effectiveness of 0.85 for the manned system 

and 0. 63 for the unmanned system. Mission Effectiveness is defined in 

SAFSL 30002. The allocation of Mission Effectiveness to each contractor's 

AVE and to Flight Operations and Recovery Support shall be as specified in 

SAFSL Exhibit 30002. 

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NRO APPROVERFOR 

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SS -MOL-1B CEI 

REFERENCE 

REFERENCE 

Mission Effectiveness 3.1.3.1 

Mission Effectiveness allocations are given in SAFSL Exhibit 30002, in 

Section 2. 1. 

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DAC -NEW 

MAC-NEW 

T -III -NEW 

GE-NEW 

EK -NEW 
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2.4

a 

PLOT 

3. 1. 3. 3. 1. 3 Probability of Launch On Time (PLOT) 

PLOT is the probability that the equipment (AVE, AGE, Facilities) will 

perform its intended function within countdown operations. The time 

interval over which the probability applies starts with the initiation of MOL 

system countdown (inclusive) and terminates at the end of launch phase. 

It is measured in two ways: 

a. PLOT--Success on the First Window--The probability of completing 

launch within a 1-hour window specified two weeks in advance. 

b. PLOT- -Succes s on Any One of Three Consecutive Windows--The 

probability of completing launch within a 1-hour window on any one 

of three successive days specified two weeks in advance of the first 

1-hour window. 

For tho maom:(1-automatic configuration, the requirement under a. above 

is 0. (,9 and the requirement under h. above is 0.90. For the automatic 

configuration, the requirement. under a. above is 0. 69 and the requirement 

under b. above is 0.89. These numerics do not include delays resulting 

• from adverse meteorological conditions or local rail traffic control. 

Numerical allocations and the methods and techniques for developing the 

PLOT shall be as specified in SAFSL Exhibit 30002. 

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T -III Annex 

3

I -7-11 

• DAC -NEW 

Automatic 

=ig NEW 

, 

;1== 

3.1. 3. 3.1. 3 # 

NRO APPROVED FOR 

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• 

SS -MOL-1B 

REFERENCE CEI 

REFERENCE 

MannedAutomatic 

MAC -NEW 

MM-NEW 

PSS-NEW 

PSA-NEW 

PLOT 

Plot Allocations are given in SAFSL Exhibit• 30002, Section 2.2. 

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2.5 SAFETY NUMERICS 

Safety 

The. MOL System Safety Program shall preserve mission- essential 

characteristics 1)1 the system while assuring that hazards to pe rsonnel, 

equipment and property are eliminated or reduced to an acceptable level_ 

This shall be accomplished by implementing a safety engineering program 

as defined in SAFSL Exhibit 30002 and the requirements specified herein. 

3.1.3.7.1 Flight Crew Safety, 

The probability of a flight crew fatality during any portion.of the MOL 

mission as a result of equipment or system segment failures shall be no 

*greater than the values specified below. These values include the abort 

capability provided by the Gemini B where applicable. The requirements IJ 

G,77 are applicable for the period of time from crew entry into the Gemini B 

TI?) during launch countdown through crew recovery following reentry. 

LJ 

t_--1 

ff-11-0-) 

Launch Phase 0.00070 

Ascent Phase 0.00250 

On-Orbit (includes Early Mission 

and Late Orbit) Phase 0.00100 

Reentry Phase 0.00075 

Retrieval Phase 0.00005 

L-5611 

Total Mission 0.00500 

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SS-MOL-1B 

REFERENCE 

CEI 

REFERENCE 

Safety Numerics 

Safety numerics allocations are given in SAFSL Exhibit 30002, Section 2.3 

• 

DAC -NEW 

MAC -NEW 

GE-NEW 

EK-NEW 

T -III -NEW 

3.1. 3. 7 

3.1. 3. 7. 1 

• 

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v.* 

2.6 VOICE LINK 

3,1.1.6.5.1 Voice Communication 

Communication between the Mission Control Center (MCC) and crew will be 

continuous during station contact. Voice quality of the overall TTCV and 

Gemini B VHF voice links shall meet a word intelligibility score of 80 percent 

or better as determined by ASA 3.2-1960 (or equivalent) for all voice modes 

with the PSA helmet removed. 

Intercommunications shall be provided during those times when both crew 

members are in, the Gemini B or LV, when one crew member is in the Gemini B 

and the other crew member is in the crew transfer mode and when one crew 

member is in the LV while connected to the transfer umbilical. 

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LM -A 

3.1.1.1.2t. 7 

DAC -NEW 

ORD 

ORD 

3.1.1.6.5.1 e. 

3.1.1. 6. 5. 1 '

NRO APPROVED FcR 

RELEASE 1 JULY 2'015 

CEI 

REFERENCE 

SS -MOL -1B 

REFERENCE 

2. Same as Test 1 - with Type 

4B data lines and Collins 

TE216 or equivalent modem. 

3. Same as Test 1 except use 

microphone input. 

4. GVC S 

5. Ground SGLS with GVCS 

6. Ground SGLS-GVCS-MCC 

Design Goal - 80 

Design Goal - 80 

25 88 85 

25 10-5 85 85 

20 Design Goal - 85 

Voice Intelligibility (TTCV) 

Voice quality of the overall ground vehicle voice link shall meet a word 

intelligibility score of 80% or better for all voice words. Voice 

intelligibility shall be measured in accordance with ASA Standard S. 3. 2-1960 

using the phonetically balanced word lists. Voice intelligibility test 

requirements for elements of the voice system are listed below. 

Link 0,, /0 

Input , Bit Error Intelligibility 

Elements S/N(dB) ' Rate(BER) Uplink Downlink 

1. AVE (VCC-KG-XMTR) 25 10-5 85 

to MGE(RCVR-KG-VSDVocode r) 

MGE(Vocoder-VSD-KG- 20 10 4 85 

XMTR) to AVE 

(RCVR-KG-VCC) 

(Use master voice test tape 

as the input. 

3.1.1.6.5,1 

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CEI SS-MOL-1B 

REFERENCE REFERENCE 

Voice Intelligibility (Gemini B) 

Voice intelligibility test requirements for elements of the Gemini B VHF 

voice system are not available at this time. 

3.1.1. 6.5. 1 • 1:7

07 

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2.7 COMMUNICATION RF LINK 

3.3.2.2.7.2 Communications 

LV communications shall be compatible with and shall make primary use of the 

USAF Space-Ground Link Subsystem (SGLS). 

The LV shall contain a transponder consisting of a receiver and transmitter 

which combines TTCV functions over a single uplink and two-carrier downlink. 

The LV communication system shall provide a secure vehicle-to-ground fullduplex voice link with 1/2 duplex backup capability and analog clear voice. It 

shall provide two independently-operated voice recorders. Processing of the 

voice shall provide a quality with minimum degradation considering, encryption, 

decryption, SGLS link, and the requirements of the SCF secure voice link. 

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CEI 

REFERENCE 

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■21 

SS -MOL -1B 

REFERENCE 

Communications RF Link 

Communication link requirements are specified in the Air-to-Ground 

Interface for MOL, Appendix D to the Orbital Requirement 

Document (ORD). 

3.3.2.2.7.2 

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2.8 TELEMETRY 

3.1. 1. 6. 11 Telemetry 

L-12.1 

Telemetry shall be provided for the transmission of data to SCF remote 

(-'D stations. Data multiplexing shall be provided by the Mission Module, 

it ' Laboratory Vehicle, and Gemini B system segments. 

The Laboratory Vehicle telemetry subsystem shall combine PCM multiplexed 

data from the MMSS and PSS with the LVSS data into a serial bit stream for 

f±3 real-time or delayed transmission. Laboratory Vehicle continuous channel 

FM data and Gemini 13 PCM data shall be transmitted in real time only. 

Fourteen Interrange Instrumentation Group (TRIG) FM telemetry subcarriers 

shall be provided during ascent for high frequency vibration or acoustic 

measurements, six to be utilized for LVSS, four for MMSS, and four for PSS. 

The combined MMSS and PSS video output will be mixed with the LVSS FM 

telemeter control unit. 

1 

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i7•••' 

-A, 

'ION 39, AI 

LM-A CCN 39, AI 

GE CCN 39, A2 

NRO APPROVED FOR 

RELEASE 1 JULY 2'015 

SS -MOL -1B 

REFERENCE 

CEI 

REFERENCE 

OV PCM Telemetry 

Capability: The PCM telemetry system servicing the LVSS, the 

MMSS, and the PSS for Flights 3 and up has the 

following formats and characteristics: 

FORMAT TITLE 

BIT RATE 

(kbps) 

FRAME RATE 

(Frames/Sec) 

WORDS/ 

FRAME 

1) Real Time, 

Periodic, & 

65.536 64 128 

Mission 

2) Undefined 65.536 64 128 

3) Contingency 4.096 4 128 

Mode 

4) EKG 4.096 4 128 

Gemini B PCM telemetry is carried on a separate link. 

Allocation of Capability: The allocation of words /frame for each 

format for both the manned automatic 

and automatic configuration is as 

follows: 

WORDS / 

Format 1 FRAME 

LVSS 67 

MMSS 61 

PSS 

Total 128 

Format 2 - Undefined 

Format 3 

LVSS 128 

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CEI 

REFERENCE SS-MOL-1B 

REFERENCE 

OV PCM Telemetry (continued) 

lb 

WORDS/ 

FRAME 

Format 4 

' LVSS 128 

GBQ Allocations: 

The PCM telemetry channel for Flight No. 2 has a 760 kbps 

capacity. Allocations for this vehicle are not available at this time. 

* Format 4 is not used for the automatic configuration. 

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V 

M-A, 3.1.1. 2. 3.1 

3.1.1. 2.1. 6 

SEW 

C"--=1 

,D 

L 

NRO APPROVED FOIR 

RELEASE 1 JULY 2015 

CEI SS-MOL-1B REFERENCE REFERENCE 

OV FM/FM Telemetry 

Capability: The FM/ FM telemetry system servicing the LVSS, the 

MMSS, and the PSS has a 14 channel capacity. Twelve 

of these channels have 500 H

z 

bandwidth and two have 

2, 000 H

z 

bandwidth. 

Allocation of Capability: The FM/FM telemetry channels are allocated 

for the manned automatic configuration as 

follows: 

500 H

z 2, 000 Hz 

CHANNELS CHANNELS 

LVSS 

MMSS 

PSS 

Total 12 2 

Assignment of FM channels by measurement numbers is not 

available at this time. 

Allocation of FM/FM channels for the automatic configuration is 

not available at this time. 

5 1 

3 1 

4 

3. 1. 1. 6. 11 

1b 

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2.9 MONITOR/ALARM 

3.3.2.2.9 Monitor/Alarm 

The Laboratory Vehicle monitor and alarm system shall be capable of alerting 

the crew to critical out-of-tolerance Orbiting Vehicle conditions. Monitored 

functions shall be classified in two levels of alarm urgency: warning and caution. 

Each of these levels shall actuate a distinct set of visual and aural alarms for 

crew alerting. The crew display shall be centralized. Criteria for monitoring 

and classifying signals shall be: 

a. Warning Function—Functions which, if out-of-tolerance, present an 

immediate threat to crew life. 

b. Caution Function—Functions which if out-of-tolerance, indicate 

degradation of Orbiting Vehicle performarc e to a degree which, if no 

action is taken through crew or ground command procedures, can 

result. in degraded systems performance or reliability. 

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LM -A 

3. 1. 1. 1. 4b 

LM -A 

3.1.1.1. 4b 

lid NEW 

r NEW 

i!tt1.4b j

NEW 

NRO APPROVED FC)R 

RELEASE 1 JULY 2015 

CEI 

REFERENCE 

1 

SS-MOL-1B 

REFERENCE 

Monitor /Alarm 

Capability: The LVSS Monitor and Alarm System has a 206 channel 

capacity to service the OV. 

Allocation of Capability: The Monitor and Alarm System channels 

are allocated for both the manned automatic 

and automatic configuration as follows : 

WARNING (FULLY 

REDUNDANT CHANNELS) 

GBSS 

LVSS 

MMSS 

PSS 

Total Warning 20 

CHANNELS 

0 

8 

12 

3.3.2.2.9 • 

CAUTION 

GBSS 

LVSS 

MMSS 

PSS 

• 10 

88 

88 

Total Caution 186 

Total Allocated 206 

Total Unallocated 

Channels 206 L-5611 

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2.10 COMPUTER MEMORY 

3. 3. 2. 2. 8. 4. 1 Computer 

A centralized capability shall be provided for performing required on-board 

computations and data handling functions and command functions initiated through 

the command link or by the crew. Control of the computer shall he provided 

through the command link via real-time or stored program commands or upon 

receipt of a signal from the computer subsystem controller. 

Capability shall be provided for the crew to enter or request data from the 

computer, to include but not be limited to operational and failure status displays. 

Flight crew control of the computer subsystem will be provided as backup. 

Two identical computers, together with required peripheral units, each capable 

of executing all functions essential to Mission Payload and INSS operations, shall 

be included. Both computers shall have the capability of interfacing with the 

MMSS and LVSS. 

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• 0 

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LM-A 3.1.7 

NEW 

NEW 

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CEI SS-MOL-1B 

REFERENCE REFERENCE 

• 

Computer Memory 

Capability: The computer core memory capability is 16,384 words. 

This memory capacity must satisfy all MMSS, PSS, 

LVSS requirements for resident word storage. 

Allocation of Capability: The core memory allocation is as follows: 

Manned-Automatic Automatic 

Configuration Configuration 

(Words) (Words) 

GE 

Resident 

Shared* 

9, 300 

(1,264) NOT 

DAC 

Resident 5,000 AVAILABLE 

Shared* (1,264) 

Contingency 820 

TOTAL 16, 384 

Free storage and non-resident program block, time shared. 
NRO APPROVED FCIR 

RELEASE 1 JULY 2f015 

2.11 EXTERNAL DATA STORAGE 

3. 3. 2. 2. 8. 4. 4 External Storage 

External storage shall be provided to allow read-only storage of all computer 

programs required during the mission. The storage unit shall be addressable 

by either computer for access to stored programs and target data. 

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SS -MOL-13 

REFERENCE 

External Storage 

Capability: The AMU (Auxiliary Memory Unit) has a storage capacity 3.3.2.2. 8. 4. 4 

.of 204,300 words. (6 million bits. ) 

Allocation of capability: The AMU storage allocation is as follows: 

GE 

Manned Automatic 

Configuration 

(Words) 

Automatic 

Configuration 

(Words) 

Data 68,000 NOT 

Copy of resident programs 9,300 AVAILABLE 

Non-resident programs 1,250 • 

Record gaps 50,250 

DAC 

Copy of resident programs 5,000 

Self-test and non-resident 

programs 830 

Maintenance and diagnostic 

programs 8,000 

Record gaps 3,696 

TOTAL USED 146,326 

Contingency 57,974 

TOTAL 204,300 

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CEI 

REFERENCE 

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2.12 FV TRANSMISSION FREQUENCIES 

3. 2. 2. 1 Electrical and EMC 

All electrical components, subsystems, systems, wiring, and segment 

interfaces of the Orbiting Vehicle AVE and AGE shall meet the requirements 

of SAFSL Exhibits 20005, 30005, and 30006. All electrical components, 

subsystems, systems, wiring, and segment interfaces of the T-IIIM shall 

meet the requirements of SSD-CR-65-334 and SAFSL Exhibit 20005. 

All electrical components, subsystems, systems and wiring of the launch 

.facilities shall. meet the requirements of IFS-TIII-34000. Interfaces of 

the launch facility with AVE and AGE shall meet the requirements of 

SAFSL Exhibit 20005. The launch facility shall be compatible with the 

EMC, grounding and electrical bonding requirements of SAYSL Exhibit 30005. 

Electrical wiring design and manufacturing technique shall be specified and 

controlled so that potential ignition due to damage wire insulations shall be 

minimized. This shall include: 

a) Utilizing the criteria specified in MIL-W-8160D. 

b) Protection of bundles from abrasion from adjacent hardware 

and ground and flight crew action. 

Load protection to restrict the current level and duration 

in shorted wires. 

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Pad and Launch 

Frequencies 

OL 

7-70 

PRD, p. 190 

1-Orbit Frequencies 

(,-.)_. xhibit 67-101, 3.4.2 

NRO APPROVED F9R 

RELEASE 1 'JULY 2015 

CEI 

REFERENCE 

SS-MOL-1B 

REFERENCE 

Flight Vehicle Transmission Frequencies 

The allocated Flight Vehicle transmission frequencies are as follows: 

Frequency (M Hz) USE 

15.016 - .

• 

001126 Gemini B Post Reentry 

Communication 

Gemini B Recovery Beacon 

Gemini B Voice Transmission 

Gemini B Telemetry 

Gemini B Radar 

LM - Telemetry 

LM - Telemetry 

LM - Development Telemetry 

T-IIIM Telemetry 

T-IIIM Telemetry 

T-IIIM Telemetry 

T-IIIM Radar 

T-IIIM Radar 

T-IIIM Radar 

T-IIIM Command 

T-IIIM Radar 

T-IIIM Radar 

T-IIIM Radar 

Gemini B Radar (FPS-16 & TPQ-10) 

Gemini B Command Transmitter 

LM - TTCV 

Gemini B Survival Beacon 

3. 2. 2. 1 

r

L 

0-1 

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243.0 - . 0243 

296.8 ± .

• 

018 

*259. 700 

5765. 0 - 

• 

4. 0 

2212.5 - 2.0 

2217.5 - 2.0 

***S- Band 

2201.5 - . 5 

2252. 5 - . •5 

2287.5 - .

• 

5 

9310 - 

• 

20 

8425- 1 

***9550 - 20 

416.0 J.-0.

• 

11 

8425 - 

• 

1 

9220 - . •5 

94601-. 5 

5690.0 

*400-420 

1775.731 - 2.0 

243.0 + 0.0243 

* Development Flights Only 

** Three Channels for Development TM to be Assigned 

*** Alternate Channel 
NRO APPROVED FqR 

RELEASE 1 JULY 2015 

2.13 OV GROUNDING ISOLATION 

3.1.1.2.2 Grounding Resistance 

With all OV structure grounding points electrically disconnected, the combined 

resistance of the negative power returns to the laboratory central power 

system (CPS) shall have a dc resistance to the vehicle structure of greater 

- than 3,000 Ohms. OV design shall be compatible with this level of isolation. 

L-5611 

Page 33 of 83 

Copy 19 of 30 
NRO APPROVED FAIR 

RELEASE 1 JULY 2015 

SS -M01,- 1B 

REFERENCE 

CEI 

REFERENCE 

OV Grounding Isolation 

With structural grounding points electrically disconnected, each segment 

shall have a DC resistance to the vehicle structure exceeding the 

following values: 

Manned-Automatic Automatic 

Configuration Configuration 

103 ohms 103 ohms 

Gemini B 40 

LVSS 4 4 

MMSS 40 40 

PSS 40' 40 

OV System Equivalent 

Impedance 3 3 

L-5611 

NEW 

NEW 

• NEW 

NEW 

3.1.1.2. 2 

Page 34 of 83 

Copy /f of 30 
NRO APPROVED F9R 

RELEASE 1 JULY 2015 

2.14 THERMAL LOADS 

3. 1. 1. 1. 5. 2 On Orbit 

All equipments located in the LM shall be integrated with the LM thermal 

control system. All power dissipating equipments in the LM requiring active ' 

cooling shall utilize the LM liquid cooling loop for heat dissipation. Passively c-3 

controlled equipments shall be mutually compatible with the convective and 

rJ 

radiative environments that surround the equipment. 

Interface thermal effects shall be minimized by using a common design 

criteria for the LV segments as specified in SAFSL Exhibit 10003. 

L'-5611 

Page 35 of 83 

Copy of 30 
NRO APPROVED FQR 

RELEASE 1 JULY 2015 

CEI SS-MOL-12, 

REFERENCE REFERENCE 

Thermal Loads 

Allocations for thermal loads are not available at this time. 

.0 0 

3.1.1.1. 5. 2 

DAC -NEW 

GE-NEW 

EK -NEW 

L-5611 

Page 36 of 83 

Copy /f of 30 
NRO APPROVED F9R 

RELEASE 1 JULY 2'015 

2.15 ATMOSPHERE LEAK RATES 

3 • 1. 6. 4. 1 Leak Rate 

The overall atmospheric leak rate for the OV in the manned-automatic 

configuration shall be no greater than 1.55 lbs/day equivalent oxygen with 

the Gemini B at 0. 1 psi and the LV at 5.0 psi. 

The automatic configuration system leak rates shall include the leakage 

contribution from the LM, film handling system, and DRV's, including the 

effects of the cutter-sealer units. These leak rates shall be compatible with 

the extended life duration. 

L-5611 

Page 37 of 83 

Copy /9 of 30 
NRO APPROVED F9R 

RELEASE 1 JULY 2015 

CEI t SS-MOL-1B 

REFERENCE I REFERENCE 

Atmosphere Leak Rates 3.1.1.6.4.1 

For the manned automatic configuration, atmospheric leak rates shall be 

less than the following values: 

02 

Gemini B Tunnel 

#/day #/day 

H

e 

Tunnel 

#/day 

Lab Tunnel 

#/day #/day 

Lab Tunnel 

#/day #/day 

H

e

@ 5 psia 

Ross 

Barrel 

#/day 

DAC 

H 02 e 

2GB, 3.1.1.2. 

2.1.1.1 

3

LM-A, 3.1.1. 

1. Id 

A-Dual Gas 

1. On-Orbit NA ---- 

2. Early Orbit 1.52 • 

(A) 

B -Single Gas 

1. On-Orbit 

2. Early Orbit 1.52 

.97 

(A) 

;0187 

.97 

.053 

(A) NA, 

1.55 0027 

1. 193 NA 

MAC EK 

.0001 

.00018 

Atmospheric leak rates for the automatic configuration are not 

presently available. 

NOTE 

(A) Leakage rate in dual gas mode shall be equivalent to oxygen 

leakage rates shown. 

L-5611 

Page 38 of 83 

.Copy /../ of 30 

5

0V Spec 

7S106002, 

3.1.4.1.1.4 

8

NEW 
NRO APPROVED F9IR 

RELEASE 1 JULY 2015 

2. 16 CONTAMINATION 

• 

3. 1. 1. 1. 7 Contamination 

-------- 

The r V shall he designed such that contamination shall not:cause electrooptical untlint.; devices to operate out of specification during the entire 

30-day mission nor the degradation in optical systems performance be 

greater than the following: 

Camera optical system (resolution) 1 percent. 

Acquisition and tracking system (resolution) 5 percent, 

View port windows(transmissibility) 10 percent 

The effects of effluents upon sensitive elements, such as optics and 

de sign including 

thermal coatings, shall be minimized by/selection and control of material, 

outlet location, direction of flow, sequencing, and equipment filtering or 

sealing where appropriate. Effluent sources to be considered include: OV 

wastes; DRV rockets; LV ACTS and propulsion jets; ascent fairings and MM 

door separation devices; and SRM.ignition, staging, or separation rockets 

of the T-IIIM. 

Contamination of MM optics resulting from internal sources 'shall be minimized 

by material selection design and controlled manufacturing and test procedures. 

Potential sources include bearing lubricants, blanket, or coating deterioration 

and trapped foreign material released or redistributed during ascent. 

Contamination of the LM internal optical elements, windows, precision 

mechanisms and film shall be minimized by material selection, equipment 

sealing or filtering, compartment and flow distribution, design and controlled 

manufacturing, and test procedures. Potential sources include lubriceInts, 

trapped foreign material, food particles, liquid spillages, lint, skin flakes, 

and the like. 

LI 561 1 

Page 39 of 83 

Copy/ of 30 
NRO APPROVED FR 

RELEASE 1 JULY 2015 

SS-MOL-1B 

REFERENCE 

Contamination 

Quantitative contamination allocations are not available at this time. 3.1.1.1. 7 

MAC -NEW 

DAC -NEW 

GE-NEW 

T -III-NEW 

CEI 

REFERENCE 

L-5611 

I Page 40 of 83 

Copy 0-of 30 
vt, 

NRO APPROVED F9R 

RELEASE 1 JULY /015 

2.17 GUIDANCE INSERTION 

3.1.1.4.3 Insertion Accuracy 

The uncertainty in achieving the nominal insertion conditions, within the limits 

of 3.1.1.4.1 shall not exceed the values (0.997p) specified below: 

Inertial velocity (tangential in-plane) ± 25 fps 

Inertial flight path angle ± 0.10 degree 

Altitude ± 2.0 n. mi. 

Out-of-plane velocity ± 250 fps 

Out-of-plane position ± 10 n. mi. 

Guidance Requirements 

The guidance system shall be capable of meeting the requirements of 

3.1.1.4.1 and 3.1.1.4.2. The guidance system shall have the capability of 

.switc.hover to a backup guidance system located in the. Gemini B vehicle 

for Stage I and Stage II flight. Automatic and manual switchover to the 

secondary guidance system and manual switchback to the primary 

guidance system shall be provided. L-5611 

Page 41 of 83 

Copy /Pof 30 
L-5611 

Page 42 of 83 

Copy/9 of 30 

NRO APPROVED FTR 

RELEASE 1 JULY 1015 

CEI 

REFERENCE 

7.-•-f71 • 

'2; -;:)T IIIM SP/DR 

,77-21 

GB CEI 

+ ECP 010R 

H=j) 

Inertial Velocity (In-Plane) (fps) 

Inertial Flight Path Angle (deg) 

Altitude (n. mi. ) 

Out-of-Plane Velocity (fps) 

Out-of-Plane Position (n. mi. ) 

12 22* 

0.05 0.08 

1.0 1.5 

12 123 

0.5 4.7 

Guidance Insertion Accuracy 

Allocations for guidance insertion accuracy (0,997p) are as follows: 

BIGS(1) GIGS(2) 

SS-MOL-1B 

REFERENCE 

3.1.1.4.3 

3. 3. 6. 2. 3 

• 

Contingent on Stage II tailoff not exceeding 6.2 fps- 

** Does not include switchover decision requirements 

Guidance Malfunction Monitoring 

Allocations for the third data source for guidance switchover decisions 

are given below. These allocations assume initialization of the 

autonomous phase of flight to occur at 280 sec. after liftoff. The 

values specified for the TIIIM auxiliary reference system (ARS) are 

equipment errors only. All values are specified as (0.997p). 

TIIIM Auxiliary Reference System (Insertion) GERTS (At 280 Sec) 

AV

x 

= 20 fps Radial Velocity 28 fps 

AV

z 

45 fps Tangential Velocity 7.1 fps 

Pitch Normal Velocity 6. 0 fps 

Attitude = 0.54 deg. 

NEW 
NRO APPROVED F0i3 

RELEASE 1 JULY 2015 

2.18 UNOBSTRUCTED LOS 

3. 0. 1.1.2 Target Access 

The MOL Systemshallprovide the capability for photographic access, at 

obliquity angles up to 37 degrees relative to the orbit plane, to arbitrarily 

located targets any-where on the sunlit surface of the earth between 80° S 

and 80° N latitude at least three times during a 30-day mission. Stereo 

capability relative to the orbit plane shall be a minimum of 14° forward to 

25 0rearward. 

L-5611 

Page 43 of 83 

Copy kf of 30 
GE-NEW 

TBD-NEW 

EK -NEW 

GE-NEW 

NEW -Replaces 

GE, 3.1.1.2. 

5. 2. 6. 1 

MV.RXERM 

NRO APPROVED Hp 

RELEASE 1 JULY 2'015 

SS -MOL -1B 

P_EFERENCE 

CEI 

REFERENCE 

3. 0. 1. 1.2 

GE has analysis responsibility for this requirement. The contributors 

to loss of LOS angular range are as follows: 

Unobstructed LOS 

3.1.1. 6. 10. 1 

Orbital to LV/RVV coordinate system 

Yaw + 3.5 deg 

DAC -AVE 

OV reference coordinate system attitude excursions 

from LV/RVV (maximum error): 

Roll + 5.8 deg 

Pitch + 2.64 deg 

Yaw + 3.0 deg 

Mission module thermal hotdogging (0.95p): 

+ 0.5 deg effective COA deflection per axis 

EK-AVE 

Optical axis alignment - 0.1 deg per axis (0. 95p) 

GE-AVE 

Optical axis alignment - 0.1 deg (0.95p) per axis 

Unobstructed LOS angular range relative to the Orbiting Vehicle 

reference coordinate system (minimum excluding hotdogging): 

Manned -Automatic 

Manned-Automatic and Automatic 

Configuration, Configuration, 

Manual Mode Automatic Mode 

L-5611 

Page 44 of 83 

Copy 4of 30 

Stereo, deg + 19.4 to -29.5 + 22.0 to - 29.5 

Obliquity, deg + 41. 7 + 42. 0 
NRO APPROVED FOR 

RELEASE 1 JULY)2015 

SS-MOL-1B 

REFERENCE REFERENCE 

Unobstructed LOS (Continued) 

The above contributors result in the following minimum capability. 

Alr 

Manned-Automatic 

Manned-Automatic and Automatic 

Configuration, Configuration, 

Manual Mode Automatic Mode 

Stereo, deg +14 to -25 +17 to -25 

Obliquity, deg + 37 + 37. 5 

L-5611 

Page 45 of 83 

Copy of 30 
NRO APPROVED PPR 

RELEASE 1 JULY 2(015 

2.19 MAIN OPTICS LIGHT 

3..3.13. 2, 2 Optical Assembly and Tracking Mirror Assembly 

The OA of the payload shall consist of a 70-inch aperture, 

length, Ross telephoto lens having a 0.54-degree semifield angle. The optical 

axis shall be approximately parallel to the roll axis of the tracking mirror 

gimbal. A 70-inch diameter, circular, flat tracking mirror shall be located 

in front of the main optics for target tracking. 

The static nadir resolution 0.4 degree off-axis shall be at least 90% of the 

static on-axis values. 

Approximately 5% of the image forming light shall be diverted from the OA 

for use in the visual optics and the image velocity sensing system. All, 

approximately one half, or none of the light diverted from the OA shall be 

provided to the visual optics with the residual energy to the IVS. In the 

automatic configuration, the visual optics shall be replaced by a second IVS 

system. 

Appropriate mechanical mounts shall be'provided to connect the OA to the 

MM. 

L-5611 

Page 46 of 83 

Copy 1 of 30 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SS -MOL 13 

REFERENCE 

CEI 

REFERENCE 

EK SOW 

Appendix I 

IIIG 

GE-NEW 

Secondary Light 

The total energy diverted from the main optics system for use in the visual 

optics and/or the IVS system is 5 percent of the light incident on the main 

pellicle. The split between the visual optics and the IVS for the various 

options is as follows: 

IVS VO 

MiTror 0 

Pellicle 40% 40% 

Open 0 100% 

41. 

3.3.13.2.2 

L-5611 

Page 47 of 83 

Copy [7of30 
GE- 

.2K6 

IFS- 

-0101. 

NEW 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CEI 

REFERENCE 

SS-MOL-1B 

REFERENCE 

Stray Light 

The total non-image forming light incident on the film plane is controlled 

to be less than 1% of the incident image forming light. This percentage 

is allocated as follows: 

EK -AVE 0.7% 

GE-AVE 0.3% 

TOTAL 1.0% 

The area-average diffuse reflectance of the surface visible, looking 

forward at the MMFS along the optical axis excluding the tracking 

mirror assembly shall be 0. 3% integrated spectrally from 0.3 to 

1.0 microns. 

L-5611 

Page 48 of 83 

Copy49 of 30 
NRO APPROVED FOR) 

RELEASE 1 JULY 2015 

2.20 MAIN OPTICS POINTING ACCURACY 

7-2) 

[T1-9 3.3.3.2.1.4 Target Pointing Accuracy 

The system, exclusive of the crewmen, shall be capable of automatically 

acquiring the target to within. 0.1 degrees (0. 95p) including all OV errors, 

assuming perfect ground-furnished ephemeris data and perfect target-location 

data. Further, the system shall be capable of correcting the actual main 

=7) optics pointing error within 0.1 degrees under control of a crewman. 

L-5611 

Page 49 of 83 

Copy of 30 
GE, 

3.1.1.1. 6. 3 

EK Annex I 

EK Annex I 

NEW 

NRO APPROVED FQR 

RELEASE 1 JULY 7015 

SS-MOL-1B 

REFERENr 

CEI 

REFERENCE 

Main Optics Pointing (Manned-Automatic or Automatic Configurations, 3.3. 3.2.1. 4 

Automatic Mode) 

GE has responsibility for the 0.1 deg (0.95p) pointing requirement. 

The budget against this requirement is as follows: 

LOS Error (0.95p) 

Arc Min 

EK -AVE 

TM to mounting ring alignment 

(30 sec (0.95p)) 

Optics alignment assembly 

(20;ec (0.95p)) 

FAMS light source placement 

(10g-FC (0.95p)) 

RSS EK -AVE 1. 3 

GE-AVE 

TM alignment 3. 0 

Gimbal angle measurements 1. 1 

Software 1. 0 

TM control system 1. 0 

Attitude measurement 

Star tracker and alignment (1 /Sin (0. 95p)) 

to hub 

Roll axis alignment (6 frill (0.95p)) * to 

LM /MM mating plane 

RSS GE-AVE 

1.8 

0. 1 

3.9 

L-5611 

Page 50 of 83 

Copy/ of 30 

Roll axis alignment contribution is based upon use of 40 sec between 

star tracker updates and (0. 95p) vehicle rates as given in Appendix I. 

1.0 

0.67 

0.33 
' 

=-11 NEW 

(See Appendixl) 

L'a 

NRO APPROVED F9R 

RELEASE 1 JULY 2015 

SS -MOL-1B 

REFERENCE CEI 

REFERENCE 

Main Optics Pointing; (Continued) 

LOS Error (0.95p) 

Arc Min DAC-AVE 

3.3 

5.3 

5.1 

Structure (3rciri (0.95p) star tracker to LM/MM 

mating plane) 

Equivalent rate gyro error 1.4 

RSS DAC-AVE 

TARGET LOCATION RSS TOTAL 

3.0 

In-track (500 ft) 3. 5 

Cross-track (500 ft) 3. 5 

. Altitude (100 ft) 0. 4 

RSS TARGET LOCATION 

EPHEMERIS 

In-track (1200 ft) 8.5 

Cross-track (210 ft) 1.5 

Altitude (145 ft) 0.5 

RSS EPHEMERIS 8.7 

RSS TOTAL TO TARGET 11.4 

Rate gyro error is based upon 40 sec between star tracker updates, 

(0.95p) low frequency rate errors, and (0.95p) rate dependent errors 

as given in Appendix I. 

L-5611 

Page 51 of 83 

Copy J$of 30 
HJ 

F2) 

NRO APPROVED FQR 

RELEASE 1 JULY 2015 

CEI SS -MOL-1B 

REFERENCE REFERENCE 

GE-NEW 

EK-NEW 

CREW -NEW 

Main Optics Pointing (Manned-Automatic Configuration, Manual Mode) 3.3.3.2.1.4 

wo 

GE has analysis responsibility for this requirement. Allocations for 

this mode are not available at this time. 

L-5611 

Page 52 of 83 

Copy iirof 30 
NRO APPROVED FpR 

RELEASE 1 JULY 2015 

, 2. 21 MAIN OPTICS SMEAR (ON-AXIS) • 

3. 1. 1. 6. 22 Smear Limits and Tracking Mirror Target Acquisition Time 

The total OV smear contribution to dynamic resolution loss in terms of angular 

rate shall not be greater than the values given in the table below at the center 

of the format. 

The slew and settle time for the tracking mirror shall not be greater than A•60- 

+N seconds, where A0 = slew maneuver, in degrees of the gimbal motion 

required at the instant the slew command is issued. 

Slew and settle time is defined as the time to accomplish the slew maneuver 

and attain the specified pointing accuracy and to allow all elements of the OV 

to settle to the LOS rate accuracy given in the table below. 

LOS Rate Accuracy (0.95p) 

(Microradian/Sec) 

.N 

Seconds 

3 

4 

5 

Automatic or Manned-Automatic 

Configuration without LOS IMC 

Automatic or Manned-Automatic 

Configuration, Automatic Mode 

Manned-Automatic Configuration, 

Manual Mode 

*These are the RSS values of the vibration, IVS or crew, and NCS, with 

cross format IMC and visual optics magnification inhibited. 

L-5611 

main optics LOS rate shall be within 100 ,urad/sec (0. 95p) of the desired target 

With the main optics slaved to the ATS and with crew rate-nulling of the ATS, the 

tracking rate after on-orbit boresighting. Page 53 of 83 

Copy / fof 
NRO APPROVED FPR 

RELEASE 1 JULY 2015 

2.21 MAIN OPTICS SMEAR (Continued) 

3. 3. 3. 1. 2 Total NCS Contribution to Smear 

The MMSS shall provide the capability to limit image smear rate due to the IVS 

to a vector sum ofillimicro-radians per second (0. 95p). In addition, he NCS 

contribution to image smear rate (except the IVS contribution above) during 

photography shall be limited to a vector sum oillimicro-radians per second, 

(0. 95p). 

L-5611 

Page 54 of 83 

Copy jof 30 
GE, 

3. 1. 1. 1. 6. 3 

GE, 

3.1.1.2.6.3.5 

Drive noise 

only, GE, 

3.1.1. 2. 6. 3. 4 

GE, 

3.1.1.1. 6. 3 

(See page 51) 

(See Appendix 

I and below) 

Main Optics Smear (Manned-Automatic and Automatic Configurations, 

Automatic Mode Without IMC) 

GE has responsibility for /sec (0.95p) requirement. The 3.1.1.6.22 

o 

NRO APPROVED F9R 

RELEASE 1 JULY 2015 

vt, 

SS -IvIOL - 1B 

REF.17J;. ENG E 

CEI 

REFERENCE 

(See page 6 1 ) 

budget against this requirement is as follows : 

LOS Rate Error 

(O. 95p) p. Rad/Sec 

GE-AVE 

TM gimbal angle measurements (30 sec each axis) 

Software 

Servo performance 

Tracking mirror drive noise 

Attitude measurement (See 

page 50) 

DAC-AVE RSS GE-AVE 

Structure (See page 51) 

Vehicle rate measurements 

(0.95p vehicle rates as given in 

Appendix I, 0. 0005 deg/sec 

measurement error each axis, 

and 6.0 min misalignment 

about each axis)* 

RSS DAC-AVE 

VIBRATION (See page 6 I ) 

EPHEMERIS (145 ft altitude error) 

RSS TOTAL 

3. 3. 3.1. 2 

3. 1. 1. 6. 22. 1 

L-5611 

DAC -NEW 

DAC-NEW 

Misalignment (0. 95p) about each axis 

gyro input axis to LM/MM mating plane 

mating accuracy Page 55 of 83 

RSS TOTAL Copy / fof 30 
NRO APPROVED OR 

RELEASE 1 JULY 2015 

CEI 

REFERENCE 

SS -MOL-1B 

REFERENCE 

Main Optics Smear (Manned-Automatic and Automatic Configuration, 

Automatic Mode with IVS) 

GE has analysis responsibility for thellaradisec (0.95p) requirement. 3. 1. 1. 6. 22 

The allocations against the requirement are as follows: 

LOS Rate Error 

(0.95p) ,uRacl/Sec 

.ive noise only, 

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

3. 1. 1. 1. 6. 3 

'1`?e page 61) 

-NEW 

GE-AVE 

Tracking mirror drive noise 

VIBRATION (See page 61) 

IVS PERFORMANCE 

RSS TOTAL 

3. 3. 3.1. 2 

3.1.1. 6. 22. 1 

3. 3. 3.1.2 

L-5611 

Page 56 of 83 

Copy Jjof 30 
RSS TOTAL 

N 

N 

Trackingmirrordrivenoise 

VIBRATION (Seepage 61) 

N 

en en N

.0 .0 

•-■ .0.... 

Cl) 

o 

..-. 

.1) 

•--I ,-I 

• 

• 

. 

en cr) 

- - a) 

o., 

ca 

a) 

V.) 

0 

III 

Z 

1.1 s. 

)i

1 - 1.1 

0

C rr

:1r

cL,7v-, i 

1 r , 

z 

N 

N ce, 

N 

tx4 

N 

;Li TT\ 1.,F1 F11 

ftJ 

(T) 
N 

In 

Z 

UW 

(- 17;)!

-Firi)fl 

RSS TOTAL (Main Optics toTarget) 

P4 

U) 

U) 

U 

14 

* Computed for 6 cps servobandwidth 

0 

Slavingerror 

co 

> 

14 E-1 

cn.4. 

---- 

El----' VIBRATION(Seepage 61) 

11.1.1 

(1.) 

/-4 

0 U) 

cd •CI 

g 

rd

U) CY, 

0 • 

Thebudgetagainstthisrequirementisasfollows: 

GE hasresponsibilityforthe (0. 95p)ratetracking 

MainOptics Sme ar(Manned-AutomaticConfigur ation,Slaved Mode) 
NRO APPROVED RpR 

RELEASE 1 JULY 2015 

2.22 FILM PLANE VIBRATION (MAIN OPTICS) 

3.1.1.6.22.1 Vibration Smear 

During photography, the uncompensated image smear resulting from random 

vibrations and impulse distrubances shall not be greater than a vector sum 

of microradians/second (0. 95p) on axis when across-the-format IMC 

and visual optics magnification changes are inhibited. ' 

L-5611 

Page 59 of 83 

Copy a of 30 
• 

NRO APPROVED FR 

RELEASE 1 JULY 2015 

2.22 FILM PLANE VIBRATION (Continued) 

3.3. 3. 1. 1 Vibration Smear Limits 

The vibration contribution of the MMSS AVE to image smear rate during 

photography shall be limited to a vector sum of 

(0.95p) on axis. 

r"-17-11 3.3.13.1.1 Vibration Smear Limits 

The vibration contribution of the photographic payload system segment equip- 

:)1JD ment to image smear rate during photography shall be lirnitedto a vector sum 

of (0. 95p) on axis when across the format IMO 

and visual optics magnification changes are inhibited. 

3.3.2. 1. 1 Vibration Smear Limits 

equipment 

I The vibration contribution of the LVSS/to image smear rate during photography 

!"311).) shall be limited to a vector sum of (0.95p) on axis, 

3. 3. 1.1. 1 Vibration Smear Limits . 

The vibration contribution of the Gemini B system segment equipment to 

• image smear rate during photography shall be liMited to a;vector sum of 

:0.95p) on axis. 

L-5611 

Page 60 of 83 

Copy ../.1 of 30 
3. 3. 2. 1. 1 

3.3.1. k. 1 

• 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SS -IVIOL-1B 

REFERENCE 

CEI 

REFERENCE 

Film Plane Vibration (Main Optics) 

GE has analysis responsibility for this requiremert . Image smear due 

to vibration is allocated as follows : 

LOS Rate Error 

(O. 95p) p. Rad/Sec 

GE-AVE 

EK -AVE 

DAC-AVE 

MAC-AVE 

CONTINGENCY 

RSS TOTAL 

NEW 

EK Annex I, 

P.1-65M 

NEW 

NEW 

L-5611 

Page 61 of 83 

Copy J9of 30 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

2.23 ATS POINTING ACCURACY 

3.1.1.6.27.2 ATS Pointing Accuracy 

The system, exclusive of the crewmen, shall be capable of automatically 

pointing the ATS to within 8 arc-minutes (0. 95p) of the target including all 

OV errors, but assuming perfect ground-furnished ephemeris data and 

perfect target-location data. Further, the system shall be capable of 

correcting the actual ATS pointing error within 2 arc-minutes (0. 95p) 

under control of a crewman. 

After initial boresight alignment, when the main optics is commanded to 

track the ATS, the ATS LOS and main optics LOS shall remain aligned to 

within 0.1 degree (0. 95p). 

L-5611 

Page 62 of 83 

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GE-ECP 17R5 

3.1.1.1. 6. 3b 

(Assumes 1/2 

min for DAC 

structural 

changes) 

(See page 51) 

(See page 51 ) 

NEW 

NEW 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

) 

REFERENCE 

(See page 64) 

SS-MOL-1B 

REFERENCE 

3.1.1.6.27.2 

3.1.1.6.27.2 

L-5611 

Page 63 of 83 

Copy ifof 30 

ATS Pointing Accuracy (Manned-Automatic Configuration, Automatic Mode) 

GE has responsibility for the 0.95p) pointing requirement. The budget against this requirement is as follows: 

LOS Error (0.95p) 

Arc Min 

GE-AVE 

Alignment (ATS optical axis to 

ATS-TM ref) 

Gimbal angle measurements 

Software 

TM control system 

Attitude measurement (See page 50 ) 

DAC -AVE RSS GE-AVE 

Structure (See page 51) 

Equivalent rate gyro error (See 

page 5 ) 

Structural changes 

ATS optics to mating plane (1.0 Min 

(0.95p) total) 

ATS-TM to ATS optids(1.4rri AP, 

0. 4 ni-37-.n hotdogging, and 1. 1niTil '

radiator expansion) 

RSS DAC -AVE 

SLAVING ACCURACY 

RSS TOTAL 

TARGET LOCATION (See page 51) 

EPHEMERIS (See,page 51) 

RSS TOTAL TO TARGET 
RSS DAC -AVE 

RSS TOTAL (Main Optics to 

ATS) 

ATS TRACKING ERROR (Crew) 

RSS TOTAL (Main Optics 

to Target: 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 

CEI 

REFERENCE SS-MOL-1B 

REFERENCE 

ATS Pointing (Manned-Automatic Configuration, Slaved Mode) 

GE has responsibility for the (0.95p) slaving requirement. 

The budget against this requirement is as follows: 

LOS Error (0.95p) 

Arc Min 

BORESIGHTING ERROR (Crew) 

GE-AVE 

Alignment change 

Software 

ATS 

TM control system 

Gimbal angle 

measurements 

Main optics 

TM control system 

Gimbal angle 

measurements 

RSS GE-AVE 

DAC -AVE 

Structural changes (See page 6 3 

ATS optics to TM ref. 

ATS-TM to ATS optics 

3.1.1.6.27.7. 

3. 1. 1. 6.27. 2 

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3.1.1.1. 6. 3 

(Excludes crew 

contribution) 

GE-NEW 

, (See page 63 ) 

(See page 63) 

(See page 65) 
v. • 

NRO APPROVED FC/R 

RELEASE 1 JULY 2015 

CEI SS-MOL-1B 

REFERENCE REFERENCE 

GE-NEW 

DAC - NEW 

CREW - NEW 

ATS Pointing Accuracy (Manned-Automatic Configuration, Manual Mode) 3.1.1.6027.Z 

GE has analysis responsibility for this requirement. 

Allocations for this mode are not available at this time. 

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2. 24 ATS RATE ACCURACY AND JITTER 

3.1.1.6.27.3 ATS Rate Accuracy and Jitter 

At the end of ATS slew and during ATS track, the LOS rate error without 

crew participation due to all OV sources shall not exceed 

(0. 95p). Capability shall be provided to reduce the LOS rate error below 

with manual control. 

During ATS tracking cycles, the image jitter at the ATS eyepiece shall not 

exceed 0.25 arc sec (1/2 amplitude) above 6 cps (0.95p). 

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GE-ECP 17R5 

3.1. 1.1. 6. 3b 

(See page 55) 

(See page 55) 

NEW 

(See page 7 1 ) 

3.1.1.6.27.3" ca7 

NRO APPROVED FqR 

RELEASE 1 JULY 2b15 

CEI 

REFERENCE 

SS-MOL-1B 

REFERENCE 

ATS Rate A c curacy (Manned-Automatic Configuration, Automatic Mode) 

GE has responsibility for the 0.95p) LOS rate 

accuracy requirement. The budget against this requirement is as follows: 

LOS Rate Error (0.95p) 

v. Rad/Sec 

GE-AVE 

Rate offset 

Servo performance 

ATS servo noise 

Gimbal angle measurements 

(30Cee each axis) 

Software 

Attitude measurement (See page 55) 

RSS GE-AVE 

DAC -AVE 

Vehicle rate measurements (See page 55) 

Structure (See page 55 ) 

Rate gyro noise (ACTS firing, slewing, etc) TBD 

RSS DAC-AVE TBD 

VIBRATION (See page 71) T 'Pt T1 

EPHEMERIS (145 ft altitude error) 

RSS TOTAL TBD 

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NRO APPROVED FPR 

RELEASE 1 JULY 2015 

SS -MOL -1B 

REFERENCE 

CEI 

REFERENCE 

ATS Rate Error (Manned-Automatic Configuration, Manual Mode) 

GE has analysis responsibility for this requirement. 

Allocations for the manual rate accuracy are not available at this time. 

CREW - NEW 

VIBRATION 

' (See page 71) 

• •• GE-NEW 

3 

3,1.1.6,27.3 

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0.236 

TED 

 O. 102 

TED 

1 

1 

! 1 1 

I 

TED 

0. 174 

1 

!! 

I 

I .-g 

truil 

[1 

NRO APPROVED FPR 

RELEASE 1 JULY 2015 

SS -MC:, - 73 

REFERENCE 

CEI 

REFERENCE 

ATS Jitter 

GE has responsibility for' the ATS jitter requirement. The I 3.1. 1.6.27.1 

budget against this requirement is .as follows: 

Error 

Contribution 

(0,95p) Arc Sec. I

I 

GE-AVE 

Bearing noise 

Electronic noise 0. 070 

Gyro noise 

Input noise • 0.098 

RSS GE-AVE 

DAC -AVE 

Rate gyro noise (ACTS 

firing, slewing, etc.) • 

VIBRATION (See page 71) • 

RSS TOTAL 

GE-ECP 17R5 

3.1.1.1. 6. 3 . b 

NEW 

See page 71) 

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NRO APPROVED FOR 

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2.25 VIBRATION (ATS OPERATION) 

No specific SS-MOL-1B requirement, but included in the 

jitter requirement of paragraph 3.1.1. 6.27. 3. 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

SS -MOL- lB 

REFERENCE 

CEI 

REFERENCE 

Vibration (ATS Operation) 

GE has analysis responsibility for this requirement. Allocations for 

vibration at the ATS eyepiece are not available at this time. 

DAC -NEW 

EK -NEW 

GE-NEW 

MAC -NEW 

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NRO APPROVED FOR 

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• 

2.,26 STAR TRACKER COMMAND ACCURACY 

3.3.3,2, 1. 6 Vehicle Attitude Determination 

The MMSS shall provide two star trackers which shall supply data to be 

utilized by airborne .computer software in conjunction with the ACTS reference 

data to accurately determine vehicle attitude. The specific stars to be 

tracked shall be determined by ground data processing prior to target 

acquisitions on photographic passes. 

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(See Appendix I) 

5=LT1 

(See page 51) 

(See Page 55) 

Allocation of Requirement: 

DAC -AVE 

Attitude control (RSS of all 

axes, See Appendix I) 

Error Contribution 

(O. 997p) , Deg 

0.80 

Structure (See page 51) 

0.08 

Mating accuracy (See 

Page 55 ) 0.05 

RSS DAC-AVE . 0.81 

GE-AVE 

Software Negligible 

Mechanical alignments and 

pointing accuracy (6 min 

(0. 95p)) 0. 15 

RSS GE-AVE 0.15 L-5611 

RSS TOTAL 0.82 Page 73 of 83 

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NRO APPROVED FtR 

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VP 

CEI 

REFERENCE 

SS -MCI., -113 

v

11,15-:Nr E 

GE, 3.1.1.1.6.2 

(2 cr rather 

than O. 997p) 

Star Tracker Command Accuracy 

Requirement: The star tracker must be initially aligned to within + 2 degree4 

of the selected star for acquisition. GE has responsibility 

for this requirement. 

3. 3. 3. 2.1. 6 
4 

NRO APPROVED FOR 

RELEASE 1 JULY/ 2015 

.0. 

2,27 TRANSLATIONAL MOMENTUM DISTURBANCES 

3. L. 1. 6. 15 Translational Momentum Disturbances 

The effects of overboard venting, overboard leakage, and altitude control 

shall not be greater than: 

IMPULSE (LB-SEC/REV) 

Mission Phase Posigrade Retrograde 

Normal to the Velocity Vector 

Out-of-Plane In-Plane 

Early Orbit 125 

Orbit 

First Orbit 100 15 400 400 

After First 15 

Orbit 

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NRO APPROVED FOR 

RELEASE 1 JUI„,015 

SS -1\401_,- 1B 

REFERENCE 

CEI 

REFERENCE 

Translational Momentum Disturbances 

The posigrade (forward) translational impUlse is allocated as follows : 3.1.1. 6.15 

Contribution, lb-sec/rev 

DAC -AVE 

Overboard venting 

and leakage 

Attitude control 

misalignments/ 

Early 

Orbit 

Operations 

Orbit Operations 

First Orbit 

After 

First Orbit 

3.4 3.4 3.4 

impingement 10.0 10.0 10. 0 

RSS DAC-AVE 11 11 11 

MAC -AVE 

Overboard venting 

and leakage * 122 60 2 

RSS TOTAL 123 61 11 

m 

U 

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Assuming that the Gemini B guidance system is shut down. 

NEW 

NEW 

NEW 
CEI SS 0 L 

3.1. 1. C. 15 

NRO APPROVEDOR 

RELEASE 1 JULY 2015 

sE IZENC:It R NCE 

Translational Momentum Disturbances (Continue:1) 

The retrograde (aft) translational impulse during the Early Orbit and 

Orbit operational phases is allocated as follows ; 

. Contribution 

Lb-Sec /Rev 

MAC -AVE 

Overboard venting and leakage 

• DAC -AVE 

Overboard venting and leakage 

Attitude control misalignments / 

impingement 

RSS DAC-AVE 11 

RSS TOTAL 11 

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NEW 

NEW 

NEW 

4 

A 

) 

2 

3. 4 

10.0 
NRO APPROVED OR 

RELEASE 1 JULYI2015 

VA 

SS-MOL-1B 

REFERENCE 

CEI 

REFERENCE 

Translational Momentum Disturbances (Continued) 

The out-of-plane lateral impulse is allocated as follows: 3.1.1. 6.15 

Contribution, lb-sec/rev 

Early 

Orbit 

Operations First Orbit 

Orbit Operations 

After 

First Orbit 

DAC -AVE 

Overboard venting 

and leakage 3 10.4 

Attitude control, 

misalignments , and 

impingement 150 150 150.0 

RSS DAC-AVE 150 150 150.5 

MAC -AVE 

Overboard venting 

and leakage * 22 10 1 

RSS TOTAL 152 150 15 1 

NEW 

NEW 

NEW 

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Assuming that the Gemini B guidance system is shut down. 
NRO APPROVED fOR 

RELEASE 1 JULY/2015 

SS -MOL - 173 

REFERENCE 

CEI 

• REFERENCE 

Translational Momentum Disturbances (Continued) 

The in-plane lateral impulse is allocated as follows: 3.1.1. 6.15 

Contribution, lb-sec/rev 

Early 

Orbit 

Operations First Orbit 

Orbit Operations 

Afte r 

First Orbit 

3 , 3 32 

150 150 150 

150 150 153 

155 70 2 

216 166 153 

X 

NEW 

NEW 

NEW 

DAC -AVE 

Overboard venting 

and leakage (down) 

Attitude control, 

misalignments, and 

impingement 

RSS DAC-AVE 

MAC-AVE 

Overboard venting 

and leakage (up) *. 

RSS TOTAL 

Assuming that the Gemini B guidance system is shut down. 

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NRO APPROVED FOR 

RELEASE 1 JULY/2015 

2.28 TORQUE DISTURBANCES 

3. I I .6. I Torque Disturbances 

The disturbance torque induced due to magnetic field interactions, purging, 

overboard venting, and overboard leakage shall not be greater than 

4.5, 1.0, and 0.1 ft-lb about the pitch, yaw, and roll axis, respectively. 

The maximum allowable angular momentum of the OV induced by overboard 

purging, venting, and leakage for a 30-clay mission excluding failure 

conditions shall be limited by the following formula: 

3 1 I I H I +12 H

R 

1 9. 2 x 104ft-lb-sec 

Where 

H p= pitch angular momentum 

Hy== yaw angular momentum 

H

R = roll angular momentum 

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' 

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RELEASE 1 JULY 2015 

NEW 

HJ • 

Guy NEW 

Cr,T'D 

NEW 

NEW 

CEI SS-MOL-117; 

REFERENCE REF ER ENC 

Disturbance Torque 

Magnetic Disturbance: 

The maximum magnetic moment about any axis is allocated as follows : 

3.1.1. 6.16 

MomentEquivalent Torque 

Amp Turn Eta Ft-Lb 

DAC -AVE 14 x 103 0.057 

MAC -AVE 7 x 103 0.029 

EK -AVE 17 x 103 0. 072 

GE-AVE 6,x 103 0.027 

RSS TOTAL 24 x 103 0, 10 

Overboard Venting and Leakage: 

The maximum moment due to overboard venting and leakage is 

allocated as follows: 

Contribution, Ft-Lb 

Roll Pitch Yaw 

NEW 

NEW 

MAC -AVE 0.036 4.20 O. 616 

DAC -AVE O. 020 O. 18 0, 176 

TOTAL 0.056 4. 38 0.792 

Total Disturbance Torque (Ft-Lb) Roll Pitch Yaw 

' 

Magnetic 

Overboard venting and 

0, 010 0, 10 0. 050 

leakage 0. 056 4, 38 0. 792 

TOTAL 0, 066 4, 48 0. 842 

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3.1.1. 6.16 • 0 

trir 

C 

NRO APPROVED F9DIR 

RELEASE 1 JULY 2015 

• CEI 

REFERENCE 

SS -MOL -1B 

REFERENCE 

Disturbance Angular Momentum 

DAC has analysis responsibility for this requirement. The 30-day mission 

disturbance momenta during the Early Orbit and Orbit operational phases 

due to overbaord venting and leakage is allocated as follows: 

Contribution 

Ft-Lb-Sec 

Roll Pitch Yaw 

MAC -AVE 400 47000 6900 

DAC-AVE 1475 8100 6110 

TOTAL 

MAC -AVE 47000 + 6900 + 12(400) = 5.9 x 104Ft-Lb-Sec 

DAC-AVE 8100 + 6110 + 12(1475) = 3.2 x 104Ft-Lb-Sec 

TOTAL= 9.1 x 104 Ft-Lb-Sec 

NEW 

NEW 

NEW 

: NEW 

L-5611 

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U7S" 707003, ICN096 

t-_-_IFS-707003,1CN096 

■_-=1 

CF-J) 

h 

NRO APPROVED FQR 

RELEASE 1 JULY 2015 

1. 

SS-MOL-1B 

REFERENCE 

CE1 

REFERENCE 

Appendix F, - ACTS Attitude and Rate Accuracy 

• 

Attitude Accuracy 

In the LV/RVV mode, the ACTS shall provide the following OV reference 

coordinate system attitude information to the GE-AVE computer, providing 

the changes in angular momentum due to operation of MPSS-AVE are as 

specified in IFS-707003, ICN 030. The attitude reference accuracy 

(0. 997p) relative to the orbital coordinate system, in deg, is: 

Pitch 0.37 

Yaw 0.60 

Roll 0.37 

Rate Accuracy 

In the LV/RVV mode, the ACTS shall provide the following OV reference 

coordinate system rate information to theGE-AVE computer. The total 

body rate accuracy (0.997p) relative to an inertial reference, in deg/sec, is: 

High (> 1 rad Low rad Freq. (sl—) 

sec 

Rate 

Freq. Dependent 

sec ) 

Pitch 0.0003 0.0003 0.00096 

Yaw 0.0003 , 0.0003 0.00096 

Roll 0.00168 0.00052 0.00077 

The quantization shall be less than 0.0005 deg/sec. 

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REFARENCE 

IFS-707003, 

ICN 030 

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NRO APPROVED FOA 

' RELEASE 1 JULY 2015 

SS-MO-1B 

REFERIENCE 

OV Rate Excursions 

The maximum vehicle rates at the end of a 60 sec inhibit period, exclusive 

of MPSS-AVE disturbances are: 

Pitch + 0.0244 deg/sec 

Yaw + 0.0244 deg/sec 

Roll + 0.0231 deg/sec