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PRIMARY EXPERIMENTS DATA 

FOR THE 

MANNED ORBITING LABORATORY SYSTEM 

(MOL) 

PROGRAM 

MARCH 1965 SPECIAL ACCESS 

REQUIRED 

preyeal-Pv (0 .3`1 Itreq Air 

HEADQUARTERS 

SPACE SYSTEMS DIVISION 

AIR FORCE SYSTEMS COMMAND 

UNITED STATES AIR FORCE 

Group 1 

Excluded from automat/6 

downgrading and 

declaelifination 

"1111111111111111111 

SSMM-67 

This document contours tefotreolton al fecheg the notional defense of the United States within the meaning .of the Espionage lows, 

Tune 18. U 5 C . Section 793 and 794, the I■ ons,hission of which in ony mann, to on Linoutha•ized person .5 prohibited by low 
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IL 

ABSTRACT 

The 13 Primary Experiments and the On-Orbit Experiments Information 

System for the MOL mission constitute an experiments package that 

exercises all critical manned functions relating to key military missions. 

The discussions of each experiment which follow as individual sections 

to this Data Book are complete within the scope of present development. 

The format which has been utilized makes possible a tabular consideration 

of the experiments. With the exception (On-Orbit Experiments Information System), the six areas considered for each experiment are: 

Objective 

Description 

Experiment Equipment Design Characteristics 

and Requirements 

Alignment and Calibration 

Test and Evaluation Procedures 

Manning Data 

A brief description of each of the 13 experiments and of the On-Orbit 

Experiments Information System follows: 

P-1 Acquisition and Tracking of Ground Targets 

Measures man's ability to acquire and track pre-assigned 

ground targets under varying conditions. 

P-2 

P -3 Direct Viewing for Ground Targets 

Measures man's ability to detect surface targets of opportunity and to make cursory intelligence assessments. 

P -4 Electromagnetic Signal Detection 

Measures man's ability to make semi-analytical decisions and 

adjustments based on information from electromagnetic emitters. 

SEeRET-- 

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CONTENTS 

Page 

1. INTRODUCTION 

1.1 Purpose 

2. EXPERIMENTS PROGRAM DEFINITION 2-1 

2.1 Primary and Secondary Experiments 2-1 

3. EXPERIMENT P-1 - ACQUISITION AND TRACKING 

OF GROUND TARGETS 3-1 

3.1 Objective 3-1 

3.2 Description 3-1 

3.3 Experiment Equipment Design Characteristics 

and Requirements 3-6 

3.4 Alignment and Calibration 

3.5 Test and Evaluation Procedures 

3.6 Manning Data (Crew Members) 

4. 

4-1 

4.1 Objective 4-1 

4.2 Description 4-1 

4.3 Experiment Equipment Design Characteristics 

and Requirements 4-2 

4.4 Alignment and Calibration 4-2 

4.5 Test and Evaluation Procedures 4-2 

4.6 Manning Data (Crew Members) 4-4 

5. EXPERIMENT P-3 - DIRECT VIEWING FOR 

GROUND TARGETS 5-1 

5.1 Objective 5-1 

5.2 Description 5-1 

5.3 Experiment Equipment Design Characteristics 

and Requirements 5-1 

-viiSECRET 

1-1 

1-1 

3-17 

3-20 

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CONTENTS (continued) 

Page 

9. EXPERIMENT P-7 - . . . 9-1 

9.1 Objective 9-1 

9.2 Description 9-1 

9.3 Experiment Equipment Design Characteristics 

and Requirements 9-8 

9.4 Alignment and Calibration 9-14 

9. 5 Test and Evaluation Procedure 9-14 

9.6 Manning Data (Crew Members) 9-17 

10. EXPERIMENT P-8 - AUTONOMOUS NAVIGATION 

AND GEODESY 10-1 

10.1 Objectives 10-1 

10.2 Description 10-1 

10.3 Experiment Equipment Design Characteristics 

and Requirements 10-7 

10:4 Alignment and Calibration 10-13 

10.5 Test and Evaluation Procedures 10-17 

10.6 Manning Data (Crew Members) 10-33 

10.7 Checkpoint Selection (Precision Orbit Determination) 10-43 

11. EXPERIMENT P-9 11-1 

12. EXPERIMENT P-10 - MULTIBAND SPECTRAL 

OBSERVATIONS 12-1 

12.1 Mode I - Background Measurements 12-2 

12.1.1 Objective 12-2 

12.1.2 Description 12r2 

12.1.3 Experiment Equipment Design 

Characteristics and Requirements . 12-5 

12.1.4 Alignment and Calibration 12-11 

12.1.5 Test and Evaluation Procedures 12-14 

12.1.6 Manning Data (Crew Members) 12-21 
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CONTENTS (continued) 

13. EXPERIMENT P-11 - GENERAL HUMAN 

Page 

PERFORMANCE IN SPACE 13-1 

13.1 Objective 13-1 

13.2 Description 13-1 

13.3 Experiment Equipment Design Characteristics 

and Requirements 13-2 

13.4 Alignment and Calibration 13-5 

13.5 Test and Evaluation Procedures 13-5 

13.6 Manning Data (Crew Members). 13-9 

14. EXPERIMENT P-12 - BIOMEDICAL AND 

PHYSIOLOGICAL EVALUATION 14-1 

14.1 Objective 14-1 

14.2 Description 14-1 

14.3 Experiment Equipment Design Characteristics 

and Requirements 14-12 

14.4 'Radiation Measurements 14-30 

15. EXPERIMENT P-13 - OCEAN SURVEILLANCE 15-1 

15.1 Objective 15-1 

15.2 Description 15-1 

15.3 Experiment Equipment Design Characteristics 

and Requirements 15-10 

15.4 Alignment and Calibration 15-31 

15.5 Test and Evaluation Procedures . . 15-31 

15. 6 Manning Data (Crew Members) 15-36 

16. ON-ORBIT EXPERIMENTS INFORMATION SYSTEM . 16-1 

16.1 Objective 16-1 

16.2 Description 16-3 

16.3 MOL Experiments Information System and 

Experiments Interactions 16-15 

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FIGURES (continued) 

Figure Page 

5-1 Target-of-Opportunity Procedure 5-3 

6-1 Experiment P-4 Equipment Block Diagram 6-4 

6-2 Experiment P-4 Operational Sequence Diagram 

for Coded-Pulse Alarm 6-5 

6-3 Experiment P-4 Acquisition Antenna Elements 6-17 

6-4 Experiment P-4 Proposed Tracking Antenna 6-19 

6-5 Experiment P-4 Equipment Arrangement 6-21 

6-6 Experiment P-4 Equipment Arrangement 6-36 

6-7 Comparative Traffic Rates (Extrapolated) 6-46 

6-8 Time-Line Analysis for Sub-Experiment 4 6-62 

8-1 Typical Equipment Arrangement, AMU Back-Pack . . 8-6 

8-2 Typical AMU Manual Controller 8-7 

9-1 Intermediate Range Target Inspection 9-6 

9-2 Representative RMU Installation 9-10 

9-3 RMU Arrangement 9-11 

9-4 Experiment P-7 Power Profile 9-12 

10-1 Autonomous Navigation Subsystem Equipment Tree . . 10-3 

10-2 Autonomous Navigation Modes 10-4 

10-3 Star Tracker 10-8 

10-4 Preliminary MOL Autonomous Navigation 

Display and Control 10-9 

10-5 Autonomous Navigation Mode I: Star Tracker/PTS • • 10-34 

10-6 Autonomous Navigation Mode II: Star Trackers/ 

Horizon Scanner 10-35 

10-7 Autonomous Navigation Mode III: PTS/Horizon 

Scanner 10-36 

10-8 Autonomous Navigation Mode IV - Manual: Horizon 

Scanner, PTS, Air Almanac, Wrist Watch 10-37 

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FIGURES (continued) 

Figure Page 

16-1 MOL Experiments Information System 16-2 

16-2 MOL Experiments General-Purpose Central 

Computer 16-5 
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TABLES 

Table 

Equipment Weight and Volume, 

Page 

3-1 

Experiments P-1, P-2, P-3, and P-8 3-3 

3-2 Summary of Tracking Servo Requirements 3-10 

3-3 IVSS Target Characteristics 3-24 

3-4 Experiment P-1 Evaluation Techniques and Criteria . . 3-28 

3-5 Console Data Recording Requirements 3-32 

3-6 Sensor Data Requirements 3-41 

3-7 DCS - Computer Interface Data Requirements 3-43 

3-8 Unique Calibration Equipment Data Requirements 3-44 

3-9 Normal Data Recording 3-45 

3-10 Photographic Tag Data 3-46 

3-11 Photographic Interpretation Data 3-47 

3-12 Alignment and Calibration Data 3-48 

6-1 Recorder Requirements, 6-30 

6-2 Experiment P-4 Equipment Weight and Volume 6-32 

6-3 Orbital Experiments 6-45 

6-4 Selected U.S. Emitters with Characteristics 

of Special Interest 6-48 

6-5 Evaluation Criteria 6-53 

6-6 Performance Measure - Sub-Experiment 1, 

Detect and Analyze Exotic Emitter 6-54 

6-7 Experiment Analysis Data Requirements 6-56 

6-8 Preliminary Emitter-Word Data Content 6-58 

7-1 Sub-Experiment Requirements 7-6 

7-2 Mission and Vehicle 7-9 

8-1 Experiment P-6 Equipment Weight and Volume 8-5 

9- 1 Standard RMU Maneuver 9-7 

9-2 P-7 Weight and Volume Requirements 9-9 

-xvi- 
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TABLES (continued) 

Table Page 

16-4 Computer-Experiment Interactions P-1 16-17 

16-5 Computer-Experiment Interactions P-2 and P-3 16-21 

16-6 Computer-Experiment Interactions P-4 16-22 

16-7 Computer-Experiment Interactions P-5 16-24 

16-8 Computer-Experiment Interactions P-6 .... .. . . . 16-25 

16-9 Computer-Experiment Interactions P-7 16-26 

16-10 Computer-Experiment Interactions P-8 16-27 

16-11 Computer-Experiment Interactions P-10 16-29 

16-12 Computer-Experiment Interactions P-11 and P-12 . . . 16-31 

16-13 Computer-Experiment Interactions P-13 16-32 
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1. INTRODUCTION 

1. 1 PURPOSE 

The purpose of the Primary Experiments Data Book is to insure that 

all organizations concerned with the MOL Program have access to a 

common technical baseline description of the primary experiments 

identified by completed pre-phase I studies. 

1 -1 

This document contains information effecting the notional defense of the United States within the meaning of the Espionage lows, Title 

IS, U 5.0 , Section 793 and 794, the transmission or revelation of which In ony manner to an unauthot.yed person ts prohibited by law. 
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MDC, 

KA/4c tivfvfii tAvit( 1,41 /9.41,41,---x 

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2. EXPERIMENTS PROGRAM DEFINITION 

2. 1 PRIMARY AND SECONDARY EXPERIMENTS 

The experiments have been divided into two categories: (1) Primary 

Experiments which have the objective of measuring man's utility in 

space, and (2) Secondary Experiments which have the objective of 

advancing technology or providing scientific data of unusual importance. 

This document provides technical characteristics and discussions of 

the Primary Experiments as identified at the completion of pre-phase I 

studies. 

2-1 

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18, U S C , Section 793 and 79A, the transmission or revelation of which in any manner to on uncruthorieed person is prohibited by low. 
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3. EXPERIMENT P-1 - ACQUISITION AND TRACKING OF 

GROUND TARGETS 

3. 1 OBJECTIVE 

Future military land observation missions will require the capability to 

obtain very high resolution photographs for technical intelligence. The 

high resolution photographs can be obtained if a sufficiently large optical 

system is provided and if precise image motion compensation (IMC) can 

be accomplished. 

The objective of this experiment is to evaluate man's performance in 

acquiring preassigned targets and tracking them to an accuracy compatible 

with the requirements for precise IMC determination under various 

conditions of target type and lighting. The crew member will be 

provided with reference photos of the target area to aid in acquisition, 

thus permitting evaluation of his proficiency in accomplishing acquisition 

(under various conditions of target-type and lighting) as a function of the 

resolution of the reference photographs. The results of the evaluations 

will provide a quantitative basis for design of future manned orbital 

reconnaissance systems. 

3.2 DESCRIPTION 

3. 2. 1 Experiment Equipment 

The equipment complement for Experiment P- 1 will consist of: 

Pointing and Tracking Scope (PTS), including scanners 

Frame Camera (2) 

Film Processor 

PTS Electronic Interface Unit 

Briefing Material and Film File 

Briefing Presentation Unit 

Film Viewer 

Film Comparator 

3 -1 

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Table 3-1. Equipment Weight and Volume, 

Experiments P-1, P-2, P.3, and P-8 

Item Weight (lb) Volume (cu ft) 

PTS, 8 inch Aperture 262 31. 0 

Cameras (2) 70 mm 12 0. 5 

Electronic Interface Unit 25 0. 5 

Briefing Material 10 0. 5 

Briefing Presentation Unit 16 1. 0 

Film and BiMat - 5000 Frames 25 1. 0 

Film Viewer 15 0. 5 

Film Comparator 15 1. 0 

Displays and Console 75 3. 0 

Mounting and Cold Plates 55 1. 0 

Wiring and Circuitry 35 2. 0 

Spares and Calibration 50 3. 0 

Film Processer 10 0, 5 

Star Trackers (3) 70 2. 5 

Star Tracker Electronics 57 1. 0 

Accelerometer 3 ON OP.. 

Fairings (10 percent of 160 lb) 16 

Contingency 75 

Total 826 49. 0 

3 -3 

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

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t 300 

14B 

200 

.e 

100 

Standby 

Film Projector ON Film Projector, Console "OFF" 

12 15 18 21 24 27 30 33 36 39 42 45 

Time In Minutes "0 

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Acquisition, Tracking 

Zoom, Derototion 

Servos "ON" (Moo 

Slew) Briefing Off NOTE: During Film Advance, 

Momentary Surge of 

100-200 Watts Will 

Occur 

1000 

Search For 

1st Target 

Briefing "ON" 

Search For 2nd Target 

Track 2nd Target 

Track 1st Target 

900 

800 - 

700 

t 

600 

se 500 - 

400 

300 - 

Stortrocker, Console "ON" 

Shut Down Servos, Record Comments 

All Off 

Except Standby 

200 - 

100 

Briefing "ON" 

1 I 7 7 1 

-' 1 2 

5 

6 7 8 9 10 II 12 13 14 15 

Time In Minutes -et 

Figure 3-2. Experiment P-1 Power Profile 

Typical Sighting on Targets of Opportunity, Two Targets 

Figure 3-3. Experiment P-1 Power Profile 

Typical Photo-Data Measurement and Analysis Period 

3-5 

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65.5. 

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3-7 

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Dual field telescope 

system 

Acquisition and 

tracking scanners 

The wide-field optical system will 

be capable of simultaneously 

focusing images at the operator's 

eyepiece, the observer's eyepiece, 

and the wide-field camera. Both 

eyepieces will have a 45 deg 

apparent field angle; magnification 

will vary from 1.5 x to 9 x. The 

objective focal length will be 

1.5 inches, the objective diameter 

0.75 inch. 

The narrow-field optical system 

will be capable of simultaneously 

focusing images at the operator's 

eyepiece and the narrow-field 

camera. The operator's eyepiece 

will have a 45 deg apparent field 

angle; magnification will vary from 

18 x to 108 x. The objective focal 

length will be 36 inches, the objective diameter 8 inches. The 

operator's and observer's eyepieces will have a 6:1 zoom system. 

The operator will be able to select 

either the wide or the narrow field. 

A manually controlled focusing 

system will be provided for the 

narrow field. 

The acquisition and tracking 

scanners will each contain two 

servo-positioned reflecting elements 

that will direct the LOS of the wideand narrow-field optical systems 

from nadir to 80 deg above nadir 

in all directions. The two scanning 

systems will be slaved to the 

acquisition system. Table 3-2 

presents a summary of tracking 

servo requirements. 

3-9 

This document document ronto,ns information affecting the notional defense of the United Stoles within the meaning of the Espionage Laws, Title 

113, U S C Seit.on 793 and 79e, the transmisslon or revelation of which in an, mann, to an unauthorized person is prohibited by low. 
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Frame Camera 

Film processor 

PTS electronic interface unit 

Briefing material and film 

file 

Briefing presentation unit 

Film viewer 

Two 70 mm frame cameras will 

provide photographs for evaluating 

results of the experiments, one 

each for the narrow- and the widefield optical systems. Each 

camera will have a data-recording 

block. Up to 100 ft of film will be 

provided and exposure rates up to 

4 frames/sec will be adjustable 

from the operator's console. 

Special high-definition serial film 

will be used; exposure time can be 

varied from 1 sec max to 0, 001 sec 

min. 

The film processor will develop 

the exposed film by a web monobath technique. 

The PTS electronic interface unit 

will contain all the PTS system 

electronics and will provide for the 

interconnection of the PTS system 

to the Experiment Information 

System (EIS) and the displays and 

controls console. 

This unit will store briefing 

material, exposed and unexposed 

film, and processing material. 

This unit will be capable of 

presenting a briefed target in the 

same perspective as the actual 

target will be viewed. The unit 

will have magnification capability. 

This unit will contain a film holder 

and an arrangement to project the 

film onto a translucent screen. 

Means will be provided for 

magnification for measurement 

of relative distances between 

points on the film. 

3-11 

-SECRETlhis document contains information affecting the notional defense of the United Stoles within the meaning of the Espionage Lows, Title 

19 U 5 C . Sect on 793 and 794. the transmission or revelation of which cn on, monne, to on unauthorized person is prohibited by low 
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0.1.,u1C,00.. I 

=I 

Figure 3-6. IVSS Control Panel 

This doc

T N0 

3-13 

document contoins information affecting the notional defense of the United States within the meaning of ument the Espionage laws, Title 

IS, U S.0 Section 793 and 794, the transmission or revelation of which in any manner to on unauthorized person is prohibited by low. 
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Vehicle Stability 

Vibration Limits 

Launch Vibration and 

Shock Limits 

Hazards Peculiar to Equipment 

Temperature Limits 

0.05 deg/sec angular acceleration, 

0.01 deg/sec angular velocity, 

0.5 deg angular position, all three 

axes. 

The MOL vehicle attitude control 

system will first null vehicle 

rates, then be shut down after 

acquisition. Rate gyros will 

supply body axis rates to the 

computer with a threshold 

performance of 0. 001 deg/sec. 

A star tracker will be required for 

consecutive tracking of several 

targets (optional mode) to provide 

long-term celestial reference for 

PTS pointing from target to target. 

Alignment errors between PTS 

servos and the star trackers 

should be minimal. 

To be specified during laboratory 

Phase I study. 

The equipment will withstand the 

Titan MC launch environment. 

None 

The equipment will be designed to 

withstand a minimum skin temperature of -150 F. Temperatures 

inside the MOL are not expected 

to exceed 60 to 130°F. Because of 

the wide variation between internal 

and external temperatures, each 

optical unit should be packaged 

either completely inside or 

completely outside the vehicle 

skin. 

3-15 

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Other Units 

The PTS may be mounted 45 deg up 

from the lower centerline of the 

vehicle to allow the operator to 

manually aid the star trackers 

during acquisition and lock-on, and 

to facilitate on-orbit checks of 

star tracker alignment with the 

PTS. 

All other P-1 hardware will be 

mounted adjacent to the PTS 

inside the laboratory. Figures 3-4 

and 3-5 show the relative locations 

of most of these units. 

3. 4 ALIGNMENT AND CALIBRATION 

On-orbit alignment and calibration procedural flow charts are presented 

in Figures 3-8 and 3-9. 

3. 4. 1 Alignment and Calibration Equipment 

Alignment and focusing of the PTS and cameras will be required. The 

items required to perform this task will include: 

(a) A ground-glass viewing plate for camera check. 

(b) A PTS camera preset-microscope attachment 

for examination of the sharpness of the star 

diffraction pattern for proper focusing. 

3. 4. 2 On-Orbit Alignment and Calibration Procedures 

PTS Camera Focus and 

Misalignment 

Alignment and focus Spatial alignment will be achieved 

by sighting on a stationary target 

(a star) and centering the PTS 

crosshairs on the target. Micrometer screws on the camera will 

be used to bring the target image 

into similar alignment. 

Focus adjustment will be performed 

by removing the film deck and 

attaching a prefocused microscope 

in the camera image plane. The 

focus will be varied by micrometer 

screws to bring the diffraction 

pattern of the target image into 

maximum sharpness. 

3-17 

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cn E-1 it 4-1 O 0 c),) .,-4 0 0 Cn 0 U O 4.4 

Fig

ure 3-9. 

3-19 

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Experiment Parameters 

to be Varied 

Environmental parameters 

Target or reference 

point characteristics 

System parameters 

These parameters are assessed by 

utilizing an adequate number of 

samples and by scheduling subexperiment testing at appropriate 

times during the mission. Specific 

environmental parameters of 

interest are: 

Weather: Clear, 10 to 60 percent, 

clouds, 60 to 90 percent clouds, 

90 to 100 percent clouds. 

Lighting: Incident angle of sun or 

moonlight 

Time of Day: Day, night, dawn, 

dusk 

Atmospheric Characteristics 

(nominal): Temperature, pressure, 

humidity 

Atmospheric Characteristics 

(special): Aerosol content, etc. 

Target parameters and reference 

points of at least five general 

categories will be used. Each 

category will consist of targets 

or reference points of considerable 

variability within target class. 

Target types are: 

Test Patterns 

Cultural Targets (nonmilitary) 

Military Complex (large) 

Military Complex (small) 

Geographic (significant or unique) 

System parameters will be varied 

in a systematic manner to insure 

that human contribution can be 

assessed at several meaningful 

levels of man-machine interaction, from minimal or no-aiding 

to more complex types of aiding. 

3 -21 

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United States (preferably an arid 

region), and in the eastern 

United States or Puerto Rico. 

Military Complexes - 55 military 

complexes (see Table 3-3), 

ranging from airfields to army 

installations, have been assessed 

with regard to availability, time 

of exposure to optical sighting, 

etc. These analyses have 

permitted estimates to be made 

of elapsed orbits to completion 

of Experiment P-1. 

Cultural Targets - Significant 

cultural features such as intersections of long straight lines 

(interstate highways), cities, and 

bridges will be used as known 

reference points, particularly 

in areas where military complexes 

are scarce or nonextent. 

Target locations 

Test Procedure 

Targets will be located within the ZI, 

Hawaii, Puerto Rico, and Australia. 

Exact locations are to be 

determined. Table 3-3 is a list 

of possible Experiment P- 1 targets. 

In a typical test procedure, the crew 

member or the general purpose 

computer will select an appropriate 

preassigned target, display the 

target area map, and enter the 

target coordinates into the display. 

Preselected test targets both in 

and out of the orbital plane will be 

used. These may include airfields, 

missile sites, and specially 

prepared target areas. The crew 

member will then activate the 

equipment and align the vehicle 

so one body axis is parallel to 

the ground track. The PTS 

scanning element will be rotated 

to the correct azimuth and elevation for acquisition. Scan and 

acquisition will then be accomplished 

3-23 

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I°. U 5 C Seit.0,` 79", and 794. the tionsmission or revelation of which in °Ismarine: to on unauthorized person is prohibited by low. 
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Table 3-3. IVSS Target Characteristics (continued) 

Name Latitude Longitude Possible Targets 

Castle AFB 37°23' 120°32'30" B-52 A/C 

Norfolk 36°54' 76°58' Shipyard 

Blytheville AFB 35°57'30" 89°56'30" 13-52 A/C 

Tinker AFB 35°25' 97°23'30" AF Depot 

Oklahoma City 

Clinton Sherman AFB 35°2' 30" 99°12' B-52 A/C 

Seymour Johnson AFB 35°20'30" 77°58' B-52 A/C 

Amarillo AFB 33°13'30" 101°42' 13-52 A/C 

Little Rock AFB 34°55'30" 920 9' Titan II 

Edwards AFB 34°54' 117°53' AF Test Range 

a- Sighting from Space 

b- Sighting from Ground 

(Tracking Capabilities) 

Vandenberg AFB 34°42' 120°33' Atlas D. E. F. 

Various Facilities for 

Missile & Space 

Vehicle Launches 

Tracking Capabilities 

Altus AFB 34°39' 99°16'30" 13-52 A/C 

Atlas F 

Sheppard AFB 33°59' 98°30'30" 13-52 A/C 

March AFB 33°53' 117°16" B-52 A/C 

15th AF 11q. 

Columbus AFB 33°37'38" 88°26' B-52 A/C 

Walker AFB 33°18' 104°31' 13-52 A/C 

Atlas F 

Holloman AFB 32°52' 106°6' WSMR 

a- Sight [rem Space 

b- Tracking Capabilities 

Carswell AFB 32°46'30" 97°26' 13-58 A/C 

13-52 A/C 

Dallas, Ft. Worth 

Warner Robbins AFB 32°38' 82°35' 13-52 A/C 

Depot, Electronics 

Yuma Test Range 32°38' 114°35' Test Range 

a- Sight from Space 

3-25 

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Evaluation Procedure 

with a low magnification and large 

FOV. The target will be centered 

and automatic tracking engaged. 

The magnification will then be 

increased and the crew member 

will manually correct tracking 

errors through the nadir point. 

During the run, periodic frame 

photographs with a superimposed 

crosshair will be taken by the 

coupled camera. 

The information flow will proceed 

in the following manner. Knowledge of the MOL ephemeris, from 

ground tracking or autonomous 

navigation, and of the target's 

geographic coordinates, will 

allow precomputation of the motion 

of the LOS to the target. This in 

turn will allow the computation of: 

(1) the orientation of the PTS 

scanning plane, (2) the orientation 

of the target locus relative to the 

MOL, and (3) the initial pointing 

angles of the PTS and its associated 

angular rate profile. 

The operator, upon acquisition of 

the target with the viewfinder slaved 

to the digital computer, will generate 

error signals to the PTS pitch and 

roll gimbal servos. These error 

signals will be used to stabilize the 

image presentation and to update 

the MOL orbital parameters using 

linear perturbation theory. 

The evaluation criteria established 

for Experiment P- 1 range from 

measurement of photo data on 

records returned to earth to 

analysis of system state variables 

telemetered to ground. The 

evaluation procedures and criteria 

are shown in Table 3-4. 

3-27 

--SECRET- 

'Mk document contains information affecting the notional defense of the United Stotes within the meaning of the Espionage Laws, Title 

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3-29 

-SECRET 

This document contains information olfezting the notional defense of the Un■ ted States within the meaning of the Esp.onoge Lows, Title 

S C . Section 793 and 794 the tronsm,

s.on or revelation of whirh in any manner to on unauthorized person is prohibited by low. 
NRO APPROVED FOR 

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the correct value. The 

difference between this 

value and that computed onboard with imperfect 

tracking will be the IMC 

error. 

Data To Be Recorded 

On-Board Data Processing 

During an experiment, data will 

be sampled from the following: 

Console 

Sensor 

Computer Interface 

Unique Calibration Equipment 

Some sample data from the console 

which will be employed for realtime experiment control will not 

be recorded. This will also be 

true of some computer interface 

data. Tables 3-5 through 3-8 

list the data to be sampled and 

recorded. Where no sampling 

or recording is necessary, it is 

so noted. The approximate 

storage rates are shown in 

Tables 3-9 through 3-12. 

The experiment information 

system (EIS) will allow the crew 

to control and monitor the IVSS 

experiments. The EIS must 

receive, convert, store, and 

distribute data concerning targets, 

vehicle state parameters, operational subsystems, and experiments. 

It must interpret the data where 

appropriate, and transfer the data 

to the communications subsystem 

for transmittal to the ground. 

The EIS will route IVSS data to 

various MOL equipment. This 

task will comprise four major 

subtasks: collecting, converting, formatting, and storing all 

IVSS data which must be subsequently analyzed. 

3 -31 

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RELEASE 1 JULY 2015 -SECRETTable 3-9. Normal Data Recording 

Parameter 

Data Rate 

(bits/sec) 

PTS Gimbal Angles 

Vehicle Attitude 

Star Present 

PTS Servo Loop Error Signal 

76 

72 

2 

760 

Roll and Oblique Perspective of Briefing Slide 12 

GMT 27 

Horizon Sensor 22 

Horizon Sensor Inhibit 1 

Vehicle Rates 36 

Mode Select (Mode Panel) 5 

Function Select (Mode Panel) 4 

Target Select (Mode Panel) 16 

Track Mode (Mode Panel) 5 

Scan Select (Mode Panel) 2 

Display Mode (Briefing) 1 

Slide Orientation (Briefing) 2 

Frame Number (Briefing) 12 

Red Filter (Briefing) 2 

PTS Magnification 6 

Spectral Filters 6 

Reticle Hue 4 

Attenuation 4 

Polarizer "In-Out" 1 

Polarizer Adjust 5 

Quality Filter 2 

Malfunction Indication 20 

Time to Target 16 

Target Latitude 20 

Target Longitude 21 

Attitude Control System Mode 3 

Hand Control 380 

Subtotal 1545 

Identification 5 

Total 1550 

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Table 3-11. Photographic Interpretation Data 

Data Rate 

Parameter (bits/frame) 

X Position of Crosshair 17 

Y Position of Crosshair 17 

X Position of Target 17 

Y Position of Target 17 

Subtotal 68 

Identification 2 

Frame Number 10 

Total 80 

3-47 

SECRETTh., document contams information affecting the national detente of the United States within the meaning of the Espionage Laws, Title 

c r -- 70: 70A 'h. fron‘rn,sson or revelation of wh, h in any manner to on unauthorized person is prohibited by tow . 
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The functional requirements of the MOL 

computer which must be included are: 

Vehicle alignment for acquisition 

and tracking. 

Generation of initial PTS pointing 

angles. The relative vehicle state 

vector will be transformed into vehicle coordinates whereby position and 

velocity vector projections on the 

vehicle axes will be used to provide 

gimbal angle and gimbal angle rate 

commands for PTS control. 

Estimation of relative trajectory 

parameters for accurate image 

motion sensing and focus adjustment. 

PTS control and image velocity 

sensing. 

Communication Data Requirements 

to Ground 

The telemetry/communications/ground 

support interfacing required by the 

experiment results from the data continuously recorded during the experiments, photo tag data, photo interpretation data, and alignment and calibration data. 

3 -49 

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Thi, document contain, information affecting the national defense of the United States within the meaning of the Espionage Laws, Lute 

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Fig

ure 3- 12.Task Flow forBriefingFunction- Station I 

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Fig

ure 3- 14.Task Flow forCameraCo

ntrol Function- StationI 

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• 
Fig

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Flow forTrackingFunction-StationI 

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Figure 3- 18. Task Flow,VoiceComme

ntaryDu

ringExp

e

rime

nt 

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Figure 3- 21.Task Flow forPhoto-DataFunction- Station II 

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