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2 7 OCT 1989 

3 

CANDIDATE. EXPERIMENTS 

FOR 

MANNED ORBITING LABORATORY 

VOL I CEVIEri tri 3 k Dee- %11P14 

DaS1ROY 

1 APRIL 19 hUMANNED ORBITING LABORATORY 

EXPERIMENTS WORKING GROUP 

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deplores., Lows, Title 11 U.S.C., Sweden 7f3 and 714. 

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manner to in unauthorised person Is prohibited by law. 

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2 7 OCT 1989 

CONFIDENTIAL 

NOFORN 

CANDIDATE EXPERIMENTS 

FOR 

MANNED ORBITING LABORATORY 

VOL I 

EVEri T1.13-2.WasSL 

1 April 1964 

Manned Orbiting Laboratory 

Experiments Working Group 

SPECIAL HANDLING REQUIRED 

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• 

CONFIDENTIAL 

NOFOnN 2 7 OCT 1989 

FOREWORD 

The selection of specific experiments is a critical item in 

achieving the Manned Orbiting Laboratory (MOL) objectives. The 

objective of the MOL experiments program is to establish a qualitative and quantitative measure of man's usefulness in apace for 

performing military tasks. 

This report, presented in two volumes, contains those experiments submitted to the MOL Experiments Working Group which 

survived preliminary screening, as well as those written by the 

Group during the evaluation procedure. The experiments in the 

report were written by personnel of the Air Force, the Navy, and 

the Aerospace Corporation. In addition, Army requirements were 

considered during the evaluation and selection process. The 

experiments are in three groups: Primary; Secondary; and 

Contributory, Deferred, and Marginal. The 12 Primary and the 

18 Secondary experiments are in Volume I. The remaining experiments, numbered 31 to 176, are in Volume II (Part 1 and Part 2). 

The Primary experiments are the best of those considered 

which directly assess the role of man qualitatively and quantitatively in performing military space tasks. They have been 

tentatively selected for inclusion in the MOL Program. The Secondary experiments are the best of those considered for advancing 

technology applicable to future military space missions or those 

which will gather scientific data of national importance. The 

Secondary experiments will be performed as crew and vehicle 

capabilities permit after the requirements of the primary experiments have been satisfied. The three types of experiments in the 

third class are: (1) Contributory - used or considered in writing or 

revising the Primary, Secondary, or Deferred experiments; (2) 

Deferred - considered fairly good, but not as appropriate to MOL as 

the selected experiments; and (3) Marginal - those which marginally 

passed the preliminary screening but which, upon further analysis, 

were not considered appropriate for MOL. 

The classifications of all the experiments must be considered 

tentative. It is expected that with further study, additions, deletions, 

and modifications will be made to the list of selected experiments. 

In addition to possible changes in the list, the experiments themselves 

must be analyzed further to define equipment, test procedures, simulation techniques, and evaluation procedures before they, as a group, 

can serve as an adequate input to the MOL design. 

NOFORN SSTA- 1- 9 

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ACKNOWLEDGEMENT 

This report is the result of the efforts of many members of the DOD, 

the Aerospace Corporation, ICS (ITT) Corporation, and The Mitre 

Corporation, who participated either as panel members on the MOL 

Experiments Working Group, as consultants to the Panels, or as 

sponsors of experiments. 

41% 

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MEMBERS OF 

EXPERIMENTS WORKING GROUP 

Mr. R. Adams 

Mr. D. Armstrong 

Mr. C. Bates 

Mr. E. Baum 

Co. W.D. Brady 

Capt F. Brunstetter 

Col T.S. Byington 

Dr. S. Cain 

Dr. D. Chiles 

Dr. J. Christensen 

Lt Col Croner 

Lt Col D. Downs 

Cmdr R.K • Engle 

Maj. D.L. Evans 

Maj. T. Fiden 

Lt Col V .E. Fieker 

Dr. R. Friedman 

Mr. G. Frost 

Mr. R. Glasser 

Capt Graveline 

Dr. W. Grether 

Lt Col Harrington 

Lt Col M. Harris 

Dr. B. Hartman 

Capt W.W. Hoover 

Lt Col R. Johnson 

Dr. D. Kasten 

Col A.I. Karstens 

Cmdr R. Lawson 

Mr. D.C. Lind 

Dr. E. Liske 

Maj. H. Logsdon 

Capt T. Lynch 

Dr. E. Mayfield 

Capt J. McPhaui 

Mr. C. McNulty 

Lt Col J. Ord 

Capt G. Parker 

Lt Col R.R. Regnier 

Capt J. Simons 

Capt P. Stevens 

Mr. S. Tennant 

Maj. T. Wahab 

Dr. M. Warrick 

Maj. J.T. Wallace 

Maj. E. Westlake, Jr. 

Lt Col S. White 

Capt R. Zeigen 

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■ 

4 

CONTENTS 

VOL I 

PAGE 

Introduction xix 

Experiment Selection Procedure xix 

Criteria for Selection of Experiments xx 

Index for Volume II xxi 

NO. EXPERIMENT TITLE 

P-1 Acquisition and Tracking of Ground Targets 1 

P- 2 9 

P-3 Direct Viewing for Ground and Sea Targets 15 

P-4 Electromagnetic Signal Detection 23 

P-5 In-Space Maintenance 31 

P-6 Extravehicular Activity 53 

P-7 Remote Maneuvering Unit Operation 69 

P-8 Autonomous Navigation 87 

P-9 Negation and Damage Assessment 101 

P-10 Multi-band Spectral Observations 109 

p-11 General Performance in Military Space 121 

P-12 Biomedical and Physiological Evaluation 133 

S-1 VLF Communication Propagation Experiment 269 

/T 

S-2 Secure Communications Using Narrow Beams 283 

S-3 Laser Propagation Experiment 299 

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CONTENTS 

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5-4 High Frequency Ionospheric Ducting Communication 315 

S-5 Encapsulation and Recovery of Space Objects 333 

S-6 Expandable Structures Techniques 347 

S-7 Antenna Deployment, Alignment, and Pointing 355 

S-8 Space Rendezvous Radar 357 

S-9 Manually Controlled TV and Orbital Inspection Photography 

of Extravehicular Objects 371 

S-10 Mapping and Geodetic Survey for Identified Points 387 

S-11 Determination of Mass 405 

S-12 Hydrogen Reduction Atmospheric Regeneration 

System 429 

S-13 Vapor Compression Distillation Water Purification 

System 443 

S-14 Passive Propellant Settling Systems 455 

S-15 Coherent E-M Propagation and Antenna Loading 469 

S-16 . Solar X-Ray Warning System 471 

S-17 Materials Degradation and Malfunction Analysis 475 

S-18 Astronomical Photography 477 

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CONTENTS 

VOL II 

PART 1 

PAGE 

Introduction xix 

Experiment Selection Procedure xix 

Criteria for Selection of Experiments 20C 

Index for Volum9 II xxi 

NO. EXPERIMENT TITLE 

1 

13 

17 

31 

32 

33 

Optical Camouflage 

Vehicle Camouflage 

Camouflage 

.1 34 Decoy Deployment 21 

35 Expandable MOL Decoy 25 

36 Chaff 35 

37 Conductive Coatings 51 

38 Projectile Firing RMU for Neutralization of 

Enemy Satellite 71 

39 Recovery of Satellites via an Expandable 

Foam Rigidized Structure 75 

40 Spherical Grid Type Passive Satellite 79 

41 Tethered Objects 85 

42 Heat Transfer 101 

43 Intervehicular Transfer of Resupply Liquid 113 

44 Recovery of Rocket Engine Thrust Chambers 127 

45 Extendible Boom 141 

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CONTENTS (Cont'd) 

NO. PAGE 

46 Thermal Radiation Property Changes of 

Coatings and Surfaces 145 

47 Effects of Space Environment on Normal 

Spectral Reflectivity of Coatings and 

Surfaces 151 

48 optical Property Changes of Lenses, 

Windows, Filters, and Mirrors 157 

49 Cold Welding 163 

50 Man's Capability in Orbiting Command 

Post Functions 167 

51 MOL Combat Information Center 169 

52 In-Flight Proficiency Maintenance for 

Critical One-Time Procedures 173 

53 On-Board Data Interpretation for Activity 

• 185 

54 Human Performance in the Acquisition of 

Military Targets from a Space Platform 189 

55 Human Performance in the Operation of 

Space Reconnaissance Systems 199 

56 

203 

57 Laser Communication 219 

58 Secure Communication, Radar, RFI, and 

Radiometry in the Millimeter Wavelength 

Region 223 

59 Anti-jam and Crypto Equipment 235 

60 Visible Light Communication 239 

61 Beacon System 243 

62 VLF Electromagnetic Communication 245 

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CONTENTS 

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63 Radio Propagation and Radio Background Mapping 251 

64 VLF/LF Amplitude and Doppler Measurements 257 

65 Determination of Electron Density Profiles 

Above the F2 Peak 259 

66 Whistler Ducts 261 

67 Moon Communication - Ground - Moon - MOL 263 

68 Low Drift Gyro and Low-Level 

Accelerometer 265 

69 Momentum Exchange Attitude Control 269 

70 Control Moment Gyro and Inertial 

Wheel 271 

71 Attitude Control of Passive Satellite 273 

72 Manual Space Navigation System 275 

73 Integrated Infrared and Ultraviolet 

Experiment 291 

74 Ultraviolet Background and Horizon 

Measurements 305 

75 Ultraviolet Satellite Measurements 309 

76 Ultraviolet Missile Measurements 311 

77 Near Infrared Spectral Measurements 

of Space Vehicles Scanning of Sea Surface 313 

78 Infrared Scanning of Sea Surface 331 

79 Target and Background Radiometer 333 

80 Space Studies Using a Far Ultraviolet 

Image Orthicon 345 

ol• 

81 Airglow Horizon Photography 351 

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82 Airglow Spectroscopy 355 

83 Infrared Sensor and Display for 48 Inch 

Optical Telescope 359 

z 84 Infrared Mapping 361 

85 Stellar Irradiance Mapping in the 

Ultraviolet and Infrared Spectral Region 363 

86 Infrared Reconnaissance 367 

87 Aurora and Airglow UV Spectral 

Observations 369 

88 Horizon Scanner Components and Systems 373 

89 Infrared Earth Radiation 379 

90 Infrared Sea Scanner 381 

91 Earth and Outer Space Target 

Measurements 387 

92 Radiation Characteristics of the Earth's 

Horizon 301 

93 Infrared Horizon Measurements 395 

94 Space Radiation Measurements of 

Significance to Man 401 

95 Charged Particle Flux Monitor 425 

96 Nuclear Emulsion Exposure and Partial 

Photographic Processing 429 

97 Cosmic Ray Observations 437 

ri 

98 Electron Density and Effective Temperature 453 

4 

99 Observations in Outer Space of the H2 

Line at 85p. 457 .1 

100 Gas Composition of the Upper Atmosphere 469 

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CONTENTS 

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Orbital Plasma Characteristics -Scatter 

PAGE 

101 

Method 483 

102 Direct Observation and Photography of 

the Solar White Light Corona 489 

103 Meteoroid and Radiation Sampler 497 

104 Recovery of Meteoric Material 501 

105 Micrometeoroid Chemical Composition 505 

106 Nuclear Radiation Personnel Monitor 521 

107 Heavy Particle Dosimeter 539 

108 Electrostatic Surface Effects on 

Spacecraft Materials and Equipment 545 

109 Manned Electronic Spectrum 

Surveillance 551 

110 Ferret Sensor 553 

111 Ferret 565 

112 Extravehicular Operational Support 579 

PART 2 

113 Astronaut Maneuvering Unit (AMU) 607 

114 Thermal Evaluation of the Extravehicular Suit 619 

115 3-D Man Attitude Control System 611 

116 Remote Maneuvering Unit (RMU) 625 

4 117 Remote Manipulator 649 

118 Space Assembly Techniques 651 

119 Space Station Assembly 655 

120 Orbital Maintenance 657 

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' CONTENTS (Cont'd) ‘ 

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121 Space Rescue and Recovery 675 • 

122 Solar Thermionic Power Module 677 

123 Solar Cells 689 

124 High Resolution Optical Photography 701 

125 Medium Resolution Photographic 

Camera - 707 

126 Oceanographic Observations and 

Interpretations 711 

127 Photo Interpretation 713 

128 Photographical Study of the Earth 721 

129 Photographic Ocean Surveillance 725 

130 Global Television Surveillance 729 

131 Night Surveillance 733 

132 Optical Surveillance Sensor 735 

133 Visibility of Ocean Targets 737 

134 Visual Acuity 739 

135 Visual Perception of Targets 743 

136 Visual Observations of Ocean Based 

Targets 751 

137 Multi-Sensor Observation of Ocean 

Based Targets 755 

138 High Resolution Radar 759 

139 Radar for Ocean Surveillance 761 

140 Ocean Surveillance Radar Parametric Tests 765 

141 Millimeter Satellite Surveillance Radar 777 

• 

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142 Satellite Detector and Tracker 779 

143 Laser Surveillance System 781 

144 Laser Ranging 783 

145 An Infra-Laser Sensor for Surveillance 785 

146 Cooperative Shipping Surveillance 789 

147 Identification of Exhaust Trails 791 

148 Dual Function Long Range IR Manual Acquisition 

Automatic Tracking and Thermal Imaging 

Inspection at Stand-off Ranges 793 

149 Thermal Radiation Pattern Analysis and 

Remote Temperature Measurement of 1 

Extravehicular Objects 809 

150 Nuclear Material Detection 841 

151 Measurement of Effects of High Altitude i 

Nuclear Explosion 855 

4 

152 Identification of Meso-scale Weather Systems 859 

153 Weather Observation and Prediction 863 

154 Orbital Command Post 865 

155 Crew Locomotion Under Zero Gravity 1051 

156 Dynamic Response of Human Operator 

Under Long Term Zero Gravity 1059 

157 Effects of Weightlessness on Sensitivity 

to Angular Acceleration 1071 

158 Expandable Structure Grappling Rescue 

or Retrieving Device 1085 

159 Expandable Space Maitenance Cocoon 1097 

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CONTENTS 

NO. 

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Changing the Orbital Trajectory of 

Enemy Satellites by Expandable 

PAGE 

160 

Structure Techniques 1107 

161 Expandable Structures 1111 

162 Expandable Work Area 1115 

163 Extendible Tubular Boom 1129 

164 Materials and Mechanisms 1139 

165 Radiative Surface Deterioration 1145 

166 Structural Materials in Total Space 

Environment 1147 

167 Vibrating Reed Analysis of Structural 

Materials 1163 

168 Electron Beam Welding 1181 

169 Rendezvous and Docking Simulated 

Experiments 1185 

170 Mechanical Rendezvous Subsystems 

Cable Connection 1187 

171 Gaseous and Particulate Diffusion 1197 

172 Spacecraft Radiators 1199 

173 Liquid Transfer Between Two Space 

Vehicles 1201 

174 Cryogenic Fluid Transfer and Storage 1205 

175 Active Cycle Cooling System 1207 

176 Exhaust Plume Photography 1209 

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1. INTRODUCTION 

The primary purpose of reproducing this collection of MOL experiments 

is to insure the availability of the experiment data to technical personnel for 

further detailed analysis. The experiments included in this report are generally identical to the ones submitted to the MOL Experiments Working Group. 

Very little editing and retyping was accomplished, since improvement in 

technical content would be negligible. 

2. EXPERIMENT SELECTION PROCEDURE 

The selection of the experiments in this report has been the result 

of across-the-board DOD participation. Requirements submitted by the 

Army, Navy, and Air Force, in support of their respective missions have 

been analyzed by a composite Experiments Working Group. The Experiments 

Working Group was formed under the direction and guidance of the Air 

Force Space Systems Division to accomplish the task of determining the 

preliminary experiments package. This group was organized into four 

functional panels: observation, mission analysis, bioastronautics, and 

general scientific. 

The functional panels gathered proposed experiments from various 

contributors from within the DOD and industry. These experiments were 

analyzed to determine feasibility, applicability to the MOL program objectives, and compatibility with the selection criteria. Of the 405 input 

experiments, 164 were recommended by the panels for further consideration. In order to define a meaningful set of experiments which would provide 

an assessment of man's ability in military space tasks, it was necessary to 

analyze each military space mission and determine how man could be used 

to enhance the mission capability. 

t The experiments recommended by the panels were categorized into 

technical areas and reviewed by committees comprised of technical experts 

in the particular specialities as follows: optics, IR/UV, radar, communications, ELINT, maintenance/assembly/and deployment, physical sciences, 

extra vehicular, bioastronautics, and applied mechanics. These committees 

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analyzed the experiments to determine common objectives and common 

equipment which might satisfy more than one experiment objective. As 

the result of elimination and combination, the technical committees identified 59 experiments. These 59 experiments were then further examined 

by an integration board to determine compatibility with the preliminary vehicle 

concepts. A resulting package of 50 experiments was reviewed by SSD/ 

Aerospace from which 30 experiments were selected and classified as Primary 

and Secondary experiments. 

3. CRITERIA FOR SELECTION OF EXPERIMENTS 

The following criteria was used to evaluate the experiments presented 

in this report. 

a. The MOL is a space laboratory, not an operational vehicle. 

b. The experiments should be focused upon the role of man rather 

than specific equipment. 

c. The proposed experithents should consider the entire spectrum 

of possible military applications. 

d. Photography of reconnaissance quality will not be used to record 

or verify experiments. • 

e. Maximum use should be made of ground simulations, aircraft 

tests, and existing space programs for testing. 

f. Experiments selected for MOL should be those that cannot be 

achieved in any other way, or which constitute a proof test of 

experiments primarily conducted in ground simulations or 

aircraft tests. 

The cost of the experimental program should be minimum, making 

use of existing equipment, and provide a comprehensive and meaningful test effort. 

h. Where new or modified test equipment are required, the equipments must be technically feasible of attainment with minimum 

technical risk and readily available within the MOL program 

schedule. 

i. Experiments which contribute to the development of military 

technologies and scientific experiments which are of 'national 

importance may be considered as secondary experiments, 

particularly if they provide an assessment of man's utility. 

g. 

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INDEX FOR VOLUME II 

Following is a subject index for the experiments in Volume II, numbers 

31 through 176. In the index, the experiments are referred to by number 

only. The Table of Contents, which appears in both volumes, may be consulted for experiment titles. It may be noted that experiment number is 

on the top of each page of each experiment. 

Airglow. 81, 82, 87 

Assembly and Construction. 49, 118, 119, 168 

Astronomy. 99, 102 

Astronaut Maneuvering Unit. 113, 115 

See also: Extravehicular Operations. 

Attitude Control Systems. 68-71, 115 

Camouflage. 31-33 

a See also: Survivability Improvement. 

Coatings (for satellite offense). 37A 

Command Post. 50, 51, 154 

Communication. 57-67 

Cooling System. 175 

Decoys. 34, 35 

See also: Survivability Improvement 

Dispersion of Material. 32, 36A, 171 

Drag, Atmospheric. 36B 

Expandable and Extentible Structures. 34, 35, 39, 45, 158-163 

• Extravehicular Operations. 112-115, 118, 119, 159, 173 

Ferret. 51, 109-111 

Fluid Dynamics. 42, 43, 171 

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Fluid Transfer. 43, 173, 174 

Heat Transfer. 42 

Horizon. 73, 74, 81, 92, 93 

Human Performance. 50, 52-56, 72, 124, 127, 132, 137, 155-157 

See also: Command Post, Reconnaissance, Vision, and Weather 

Observation 

Infrared. 73, 77-79, 83-86, 88-93, 145, 148, 149 

Inspection, Satellite 

See: Satellite Inspection 

Laser. 57, 143-145 

LF/VLF. 62, 64, 66 

Liquids 

See: Fluids 

Maintenance. 120 

See also: Space Operations 

Mapping. 73, 84, 86, 90, 128 

Materials and Mechanisms 

See: Structures, Mechanisms, and Materials 

Meteoroids. 103-105 

Millimeter Waves. 58, 59 

Missile Detection and Tracking. 73, 76, 77, 79, 145, 147 

Navigation. 68-72 

Nuclear Explosion. 151 

Ocean Observation. 78, 90, 136, 143 

See also: Reconnaissance 

Offense, Satellite. 37, 38, 160 

Optical Background (IR and UV). 73, 74, 77, 79, 80, 85 

Optics, Exposure of, 48 

A 

• 

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Orbiting Command Post 

See: Command Post 

Plumes. 176 

Power Supplies. 122, 123 

Radar. 58, 138-141 

Radiation. 94-97, 103, 106, 107 

Radiators. 172, 175 

Radio Propagation and Radio Background. 58, 62-65 

Recovery and Rescue. 61, 107, 121, 158 

Reconnaissance, Optical. 54, 55, 83, 86, 90, 124-137, 146 

Reconnaissance, Radar. 137-140 

Remote Maneuvering Unit. 37B, 38, 116, 117 

Rendezvous and Docking. 169 

Rocket Engines. 44, 176 

Satellite Detection and Tracking. 51, 56, 73, 75, 80, 141-145, 148 

Satellite Inspection. 58, 148-150 

Satellite Recovery. 39 

Solar Power Systems. 122, 123 

Space Environment. 65, 98-101, 103, 108 

See also: Meteoroids 

Space Operations. 37B, 112-121, 158-160, 173 

Structures, Mechanisms, and Materials. 40, 46-49, 108, 164-168. 

See also: Expandable and Extendible Structures. 

Surveillance. 

• See: Missile Detection and Tracking, Ocean Observation, Reconnaissance, 

and Satellite Detection and Tracking. 

Survivability Improvement. 31-38 

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Tethered Objects. 43 

Thermal Background and Mapping. 89, 90 

Ultraviolet. 73-76, 79, 80, 85, 87, 91 

Vision. 54, 56, 134-136 

Weather Observation. 90, 143, 152, 153 

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-SECRET° Experiment No. P-1 

ACQUISITION AND TRACKING OF GROUND TARGETS 

I. TEST OBJECTIVE 

The objectives of the experiment are to evaluate man's performance 

in acquiring pre-assigned targets and precisely tracking them to an accuracy compatible with the requirements for precise IMC determination 

under various conditions of target type and lighting. Additionally, since 

the pre-assigned target acquisition function would most probably be accomplished by providing the astronaut with some reference photo (of 

modest resolution) of the target area, this experiment will evaluate the 

astronaut's proficiency in accomplishing the acquisition as a function of 

the quality (resolution) of the reference photo, again under various conditions of target type and lighting. 

II. DESCRIPTION OF EXPERIMENT 

A. Experimental Equipment 

The equipments required for this experiment include a direct 

viewing pointing and tracking telescope, a tracking servo system, a 

general purpose computer, and a coupled camera. The functions and 

general characteristics of each of these equipments are described in the 

following subsections. 

1. Direct Viewing Pointing and Tracking Telescope 

A pointing and tracking telescope, similar in nature to 

an optical bombsight, is required. Additionally, since wider fields-ofview at less magnification are desirable during the acquisition phase, and 

narrow fields-of-view with higher magnification are desirable during the 

tracking phase, the optical configuration should be capable of being zoomed 

over a range from approximately 6 x to 100 x. An optical element to provide 

scanning in both azimuth and elevation is required, as are a set of manually 

controlled crosshairs. 

4 2. Tracking Servo System 

The function of this system is to provide for adjustments 

in the slewing rate of the scanning element during the tracking mode to in- 

,. sure that the target does not leave the field-of-view of the pointing and 

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Exp No. P-1 

tracking telescope because of differences in the nominal slewing rate 

(based on predicted LOS angular rate) and the actually required slowing 

rates. Two possible techniques for achieving these adjustments can be 

considered: a direct servo feedback to the scanning element based on 

motions with respect to the center of the field-of-view, of the manually 

controlled crosshairs which are moved by the astronaut to keep them on 

the target, or continuous recomputation of the line-of-sight angular rates 

by the general purpose computer with, signal being provided to the scanning element drive to make adjustments in the slowing rate. 

3. General Purpose Computer 

This computer may be utilized in conjunction with the 

tracking servo system, as discussed above, and is utilized in the computation of the expected line-of-sight angular rate at the instant a high 

resolution photo would have been taken. In accomplishing the latter, 

inputs are provided from the tracking system, based on motions of the 

scanning element and manually controlled crosshairs, and from the 

vehicle guidance and navigation system with respect to angular motions 

of the vehicle. 

4. Coupled Camera 

The purposes of this item are to verify that the astronaut has acquired the proper target and to permit evaluation of the man's 

performance in accomplishing the tracking function. During the tracking 

run, periodic photos will be taken, with the manually controlled crosshairs 

superimposed on the image, to determine the operator's proficiency in 

keeping the crosshairs on the target. Analysis of these photos will enable determination of the accuracy to which the required IMC would have 

been determined. On-board film processing equipment may permit 

analysis of the test results and thereby limit communication/data retrieval requirements. 

B. Test Procedures 

Pre-selected targets, which could include military airfields, 

operational missile sites, missile flight test development centers (e. g. , 

AMR), naval bases, and specially prepared target sites, would be acquired and tracked by the astronaut. To evaluate his proficiency in 

target acquisition, the reference photos of the various targets would be 

intentionally varied in quality. Repeated tests would be made to evaluate 

the astronaut's proficiency under varying conditions of lighting, and the 

target areas would be so selected as to provide various background and 

color conditions. 

The orbital altitude of the spacecraft for these tests is not 

especially critical and could be anywhere within the range fromoapproximately 100 to 175 n. mi. Orbit inclinations of approximately 40 may be 

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required to insure that a sufficient number of target sites are available 

within the Z. I. Therc are no presently identifiable requirements for 

sun synchronous orbits, in fact, non-synchronous orbits may be desirable 

to permit repeated acquisition and tracking of the same target under various lighting (times of day) conditions. 

A typical experiment scenario might be as follows: 

(a) The astronaut aligns the vehicle in yaw by pointing the 

PTS at the ground underneath him. A grid is superimposed in the field-of-view and a zero azimuth angle 

is set on the scanning element. The grid line will be 

parallel to the vehicle longitudinal axis, and yaw alignment errors will be indicated by target points 

drifting across the grid lines instead of parallel to them. 

(b) Based on knowledge of orbit ephemeris astronaut would 

at appropriate time scan the land area within which he 

expects to find the target using his direct viewing pointing 

and tracking scope at low magnification. 

(c) The astronaut attempts to match some segment of that 

land area with the reference photo of the target area. 

(d) Upon doing so, the astronaut centers the particular 

target in the field-of-view of the telescope, increases 

the magnification of the telescope, and initiates the 

tracking mode (the astronaut may have to wait for accomplishment of a roll maneuver between the time he 

positions the target in the center of the field-of-view 

and the time the tracking run is initiated). 

(e) During the tracking run, the astronaut attempts to keep 

the crosshairs of the pointing and tracking telescope 

positioned on the target. 

C. Evaluation Procedures 

The preferred approach is the utilization of the coupled camera 

to take periodic frame photographs during the tracking run, as discussed 

earlier. 

III. IMPORTANCE OF TEST (RATIONALE) 

Future reconnaissance missions may require the capability to obtain very high resolution photographs, for example, for technical intelligence purposes. Very high resolution photographs can, in theory, be 

obtained if a sufficiently large optical system is provided, and if precise 

image motion compensation can be accomplished. A potentially promising 

technique for the precise IMC determination involves the utilisation by an 

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astronaut of a direct viewing pointing and tracking telescope. With this, 

the astronaut would acquire the target of interest (probably pre-assigned), 

and then precisely track it for a period of approximately half a minute 

prior to the taking of the very high resolution photo. The tracking information (i.e. , the changing line-of-sight angles with respect to the spacecraft 

axes) would be provided to an IMC computer which, with additional angular 

references and vehicle angular rate data provided by the spacecraft navigation and guidance subsystem, would then precisely compute the expected 

line-of-sight angular rate at the time the photo is to be taken. The computer 

would then provide signals to the film drive servo of a very high resolution 

optical system to accomplish the IMC. Through such techniques it is 

expected that IMC can be accomplished to an accuracy significantly better 

than 0.2%, perhaps as good as 0. 01%, though it is obvious from the above 

scenario that the precision attainable is quite dependent on the performance 

of the human operators. 

IV. VEHICLE REQUIREMENTS DATA 

A. Power 

Power requirements are imposed by the tracking servo system, 

the general purpose computer, the coupled camera, and the film processing 

equipment. Power levels are not expected to be high, most likely on the 

order of 200 watts. 

B. Stabilization 

In an operational mission, the primary requirement for stabilization arises from the necessity of having the target pass through the fieldof-view for the reconnaissance sensor. For this MOL experiment, however, 

stabilization requirements are not critical, and angular positioning of the 

spacecraft to several degrees with residual angular rates of 0.1 degree/sec. 

would be quite sufficient. 

C. Weight (Preliminary Estimates) 

Pointing and tracking telescope (including 400 # 

trac king servo and coupled camera) 

General purpose computer 

Film processing equipment 

D. Volume (Preliminary Estimates) 

Pointing and tracking telescope - clear volume approximately 

18" diameter by 6 feet in length 

50 # 

75 # 

Total 525 I 

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General purpose computer - 1. 5 cu. ft. 

Film processing equipment - 1. 0 cu. ft. 

E. Aperture Requirements 

A viewing aperture of approximately 12 inches in diameter will 

be required. This should be a direct opening to the space environment. 

F. Clear Field-of-View 

With the optical axis of the telescope in the vertical direction, 

a clear field-of-view downward, t 60 in elevation from the local vertical, 

and forward, t 90 in azimuth with respect to the orbital velocity vector, 

is required. 

G. Miscellaneous 

If on-board processing and analysis of the coupled camera 

photos is anticipated, then a suitable working table with proper lighting 

will be required. Additionally, typical photo interpretation equipment. 

(e. g. , microscopes with mensuration, etc.) must be provided. 

V. SIMULATION PROGRAM 

A. Pre-Phase I 

Prior to the initiation of Phase I, it is recommended that a 

study relative to the detailed definition of the experimental IMC subsystem 

be conducted (see Section VI-A). However, realization of the objectives of 

such a study and the associated design effort, are dependent on the knowledge of certain human performance factors. Therefore', a separate concurrently running study is also recommended during which certain elemental 

simulations will be performed. Among these are those which will provide 

data on: 

(a) Proper magnification, fields-of-view, and scan rates for 

target detection/acquisition 

(b) Preferred manual techniques for target re-acquisition 

after discontinuation of automatic scan mode 

(c) Preferred magnifications for precise tracking 

(d) Desirable design approaches and techniques for precise 

tracking. 

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B. Phase I and Subsequent 

During the developmental phase of the MOL program the 

various portions of the experiment would be simulated to insure a high 

probability of success for the MOL experimental mission, to verify the 

experimental concept, and to evolve design refinements for the experimental equipment. Initial simulations of the acquisition portion of the 

experiment might be accomplished in ground-based facilities, though 

later simulations should be performed using aircraft to obtain more 

realistic conditions of target characteristics, background, color, and 

lighting. Simulations of the tracking function can, however, best be 

accomplished in ground facilities as aircraft cannot provide a suitable 

stabilization environment. 

VI. EXPERIMENT DEFINITION 

A. Pre-Phase I Studies 

While the concept of manned tracking for precise IMC determination has been explored in sufficient depth to establish general validity, 

it is particularly important to conduct a study relative to the detailed definition of the experimental IMC subsystem, including the direct viewing 

pointing and tracking telescope, the tracking servo, the coupled camera, 

and the general purpose computer. This study will include consideration 

of: 

(a) Pointing and tracking scope optical configuration 

(b) Coupled camera and film processing equipment design 

(c) Tracking servo system analyses and design 

(d) IMC computational requirements and associated computer specifications 

(e) Vehicle interfaces 

(f) Functions of man with respect to set-up, operation, and 

maintenance of the IMC sub system. 

B. Phase I and Subsequent 

The aforementioned study will have defined the experimental 

IMC subsystem in sufficient depth to permit awarding of Phase I development contracts concurrently with the MOL vehicle developments. Conducting these developments simultaneously will insure proper coordination 

of all interfaces. 

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• VII. FUNDING 

A. Pre-Phase I 

1. IMC Subsystem Study - 1 contractor for 3 months - 

$200,000 total. 

2. Tracking, Scanning, and Data Interpretation Study -

1 contractor for 3 months - $100, 000 total. 

B. Phase I and Subsequent 

Funding for this experiment is expected to be in the 10 to 25 

million dollar range, these figures including the development and fabrication of the experimental equipments. 

VIII. PARTICIPATING AGENCIES 

Sponsor: AFSSD/Aerospace 

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-SEGRET- Experiment No. P-3 

DIRECT VIEWING FOR GROUND AND SEA TARGETS 

I. TEST OBJECTIVES 

The first objective of this experiment is to evaluate the astronaut's 

proficiency in detecting ground targets of opportunity under varying conditions of target type, lighting, and background, and to define preferred 

scanning techniques thus optimizing the percentage of the land area which 

may effectively be examined during a given orbital pass. 

The second objective of the experiment is to determine the detectability of ships and surfaced submarine targets under varying conditions 

of target size, color, contrast, sea state, sun angle and atmospheric 

transmission. 

The third objective of the experiment is to evaluate quantitatively 

man's ability to perform ship classification, and possibly actual identification, from orbit using varying degress of optical magnification. The end 

result of this part of the experiment would be the determination of probability of correct classification versus time duration of observation for various 

classes of ships, light levels, sea states, levels of atmospheric contrast 

transmittance, and levels of resolution. 

It will be a specific objective of the MOL program to extend the 

knowledge gained in the Mercury and Gemini programs relative to manned 

visual observations of surface targets from near-earth satellites. In 

contrast to those programs, the MOL will contain optical equipment 

capable of presenting the astronaut with a magnified view of the ground 

and ocean surface, and thus will permit studies of detection probability 

of targets of smaller size and lower contrast than those visible to the 

naked eye. 

II. DESCRIPTION OF EXPERIMENT 

A. Experimental Equipment 

The equipments required for this experiment include a direct 

viewing pointing and tracking telescope, a coupled camera, and a general 

purpose computer. These equipments are essentially the same as those 

already described in Experiment P-1, except that provision may have to 

be made for automatic scanning operation of the direct viewing system. 

The astronaut will also utilize equipment for direct voice recording when 

scanning with the unaided eye. 

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The telescope will be fitted with filters, both chromatic and 

polarizing, in order to minimize contrast attenuation for the ship and 

submarine experiments. In addition, the telescope will contain a reticle 

designed to provide two orthogonal pairs of "crosshairs" which are brought 

together to provide direct indication of ship length and beam width. This 

measurement together with the observer's impression of general class of 

ship, recorded verbally or digitally, comprise the basic data required on 

the spacecraft. 

B. Test Procedures 

On selected orbital passes, the astronaut would either operate 

the direct viewing system in an automatic or manual scanning mode or scan 

with the unaided eye and attempt to detect certain types of ground targets 

of opportunity (see Section D following). The orbital passes would be so 

selected as to provide various conditions of lighting. Repeated tests with 

the direct viewing system would be made at various magnifications and 

scanning rates to determine the percentage of targets detected. In certain 

cases, the astronaut would carry out those procedures necessary to obtaining a frame photograph of the detected target to obtain a time index of his 

performance, though the photograph so obtained would not be of reconnaissance 

quality. The astronaut would note by means of direct voice recording any 

features of interest observed while scanning with the unaided eye. Orbit 

requirements for the experiment are the same as those discussed in 

Experiment P-1 

Simulation, aircraft flight tests and Gemini experience will 

be required to rigorously define the ship detection experimental test procedures. In general, however, the procedure will involve placing target 

vessels in otherwise deserted ocean areas which lie near or under the MOL 

'orbital path during local daylight hours. The astronaut will be given pointing instructions (or approximate target geo-coordinates, depending on 

computer-servo implementation) and will be required to perform a visual 

search of the prescribed area of the ocean surface during the fly-by. 

Parameters to be measured include detection capability as a function of 

target ship size, contrast (color) speed (wake) line-of-eight angle, sea 

state, atmospheric condition (contrast transmittance) magnification, filtering, etc. Additional tests will include search for targets of opportunity 

in densely populate-II shipping areas, observation of Kepplerian wakes from 

cooperative submarines, and recording of results with the coupled camera 

and/or such other means as are appropriate to both the operational and 

scientific aspects of the detection tests. 

The targets for the ship classification and identification 

experiment should include as many classes of ships as possible, both 

naval and merchant. The naval ships should include surfaced submarines, 

destroyers, landing ships and carriers. The merchant ships should include tankers, dry cargo ships, passenger ships (esp. troopships), and 

trawlers. The naval ships would be deployed in selected ocean areas having 

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low probability of cloud cover. A limited number of merchant vessels 

should be provided for a controlled experiment, augmented by experiments 

on normal ocean traffic using low flying aircraft (or other means) to pro -

vide identification simultaneously with spacecraft overflight. Low 

inclination orbits are acceptable; regions off the southern coasts of 

the U. S. , Mexico and near Hawaii will provide suitable conditions. 

Atmospheric conditions in the test areas would be monitored. 

A scenario could be envisioned as follows: 

(a) Following the detection experiment, the astronaut 

selects a target, slews the scope to put the target 

into the field-of-view at low magnification. 

(b) The scope is zoomed as rapidly as possible (without 

losing the target) to a specified magnification. 

(c) The measuring "crosshairs" are adjusted to just 

touch the extremities of the target, and these 

measurements are recorded automatically. 

(d) The astronaut spends a specified time examining the 

target and records his impression of ship class, of 

the heading of the ship, and any uniquely identifying 

featues he can discern. 

C. Evaluation Procedure 

The particular evaluation procedures to be utilized in connection with the ground target experiment are based upon certain assumptions relative to the scanning methodology to be employed. While 

it would be desirable if complete coverage of the land area being traversed 

could be achieved through rapid, automatic scanning with the direct viewing system, practical considerations of minimum allowable dwell times 

on a particular land area to permit the astronaut to detect targets within 

it may require that only a limited number of selected areas be examined on 

any overflight. For example, areas in and around known cities, military 

installations, or railroads could be examined, while rural areas of those 

geographical in which there is a small probability of detecting anything of 

potential interest would be neglected. Targets of opportunity would 

generally be defined as items or activities which are relatively impermanent 

in nature (e. g. , new aircraft types or airfields, mobile systems, moving 

railroad trains, etc. ). 

Therefore, in conducting the experiment with the direct viewing scope, the astronaut would be instructed to look for the aforementioned 

type targets of opportunity within pre-selected areas. Within any given 

target area, the presence of a number of such targets could be varied 

orbit-to-orbit or day-to-day, to provide a reasonable measure of the 

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astronaut's target detection capabilities. Where targets do exist and 

the astronaut would have been motivated to take a photograph, he would 

voice record what he observes, this data being correlated with knowledge 

of the make-up of the target area at the time of the particular orbital pass. 

In the case of scanning with the unaided eye, somewhat larger 

areas of terrain can be covered; however, because of the poorer resolution, 

the features of interest are necessarily of fairly large dimensions. Important features or activities which could be detected include construction 

of new roads, preparation for new airfields or missile sites, etc. 

In conducting the experiment with the unaided eye the astronaut 

would be instructed to scan a pre-selected area and describe by means of 

direct voice recording, all features of interest observed within the area. 

This data could then be correlated with the known make-up of the area at 

the time of the orbital pass. 

Among the experiment parameters to be varied are the dimensions 

of the land areas to be scanned, the lighting (time of day) conditions, the 

magnifications of the telescope, and the types of targets to be detected. 

The experiment evaluation for ship detection will largely rest 

on the comparison of astronaut sighting reports, including geo-referenced 

location coordinate data available from the computer output, with actual 

target ship presence and location. In the general case, each ship detection 

experiment will be coupled with a ship-identification experiment which will 

verify the detection and ensure against false sighting reports. The principal 

evaluation procedure will involve scaling of MOL-astronaut results in ship 

detection against prior simulation and aircraft testing results for verification and correlation of results. 

Evaluation in the case of the ship classification and detection 

experiment would be performed by direct comparison of the observations, 

measurements, and interpretation thereof, with the (known) ship targets. 

In addition, pictures should be taken with a coupled camera to provide a 

permanent record. 

III. IMPORTANCE OF TEST (RATIONALE) 

The general reconnaissance mapping of large land areas for purposes 

of detecting long-term developments and deployment of known weapon types 

can best be accomplished by panoramic cameras. However, a valuable 

.adjunct in this mission may be the astronaut's ability to detect targets of 

opportunity of potential interest and• perhaps take frame photographs with 

resolutions somewhat better than could be provided by the panoramic 

cameras. To accomplish this, the astronaut could utilize a pointing and 

tracking telescope in an automatic or manual scanning mode. Upon detectiod of a target, the astronaut would over-ride the automatic scan mode, 

re-acquire the target, place and retain it in the center of the field-of-view, 

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increase the magnification of the system, and obtain a frame photograph 

with a coupled camera. In addition, the astronaut would perhaps provide 

important information by scanning larger areas of the terrain with the unaided eye and noting (by voice recording) any features or activities of 

interest. The operational utility of such a capability is, of course, dependent on the types of targets which can be detected under various conditions of lighting and background, and the percentage of the land area 

which can be effectively scanned during a given orbital pass. 

The primary military significance of the planned ship detection 

experiments is the acquisition of data regarding the optical detectability 

of surface ship targets and consequent determination of optimum means 

for achieving an operational capability for this mission from space. As 

a result of several decades of experience and many years of study and 

experimentation, the U. S. Navy has begun to acquire a systematic body 

of.knowledge about the detection of surface ships and surface phenomena 

from aircraft, and many studies have been performed to translate this 

knowledge and experience to space platform observation altitudes. It is 

known, for instance, that the ocean's surface viewed from space has a 

widely variable contrast (luminence) depending on atmospheric conditions, 

sea state, sun angle, elevation angle and viewing spectral wavelength. In 

the optical spectrum, the probability of detection of ship targets in open 

ocean by unaided visual search in real-time from a low-altitude satellite 

(such as MOL) is estimated to be relatively low under average conditions. 

Assuming "clear" skies (no obvious cloud cover), some pointing or 

locating information (such as elint, radar, IR, pronounced wakes in 

calm seas, or intelligence data from ground sources), would appear to 

be required if the probability of visual detection were to approach unity. 

The aforementioned estimates of visual detectability are, however, somewhat subjective and a carefully planned program of experimental investigation could indicate better than the estimated capabilities, particularly if 

only localized areas of the oceans were to be examined. The MOL experiment on ship detection will concentrate on the determination of man's 

abilities as a sensor when aided by optical devices of varying characteristics. The astronaut's functions will include visual observations of both 

open ocean areas and pre-designated "salted" areas for surface ship 

targets using the pointing and tracking telescope installed for other 

experiments. Because of the widely variable magnification and spectral 

response of this instrument, a variety of search and detection techniques 

may be employed, and measurements of detection probability for each may 

be made. 

In addition to the detection and surveillance of surface shipping, the 

MOL experiments will involve search for, and investigation of, such other 

surface phenomena as may be observed from orbital altitudes with the 

available optical equipment. These could include, but are not limited to, 

smoke detection, submarine detection by Keplerian Wave and "clinker" 

effect, sea state detection, oil-slick detection (significant in sea-rescue 

efforts) etc. 

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A vital factor in determining the value of ocean surveillance is 

the degree to which ships can be identified. If the name of the ship or 

some other unique feature can be seen, then it is quite clear that the 

surveillance problem is reduced to one of moving markers on a plotting 

board. At the other extreme, if only position of the ship is known, then 

a very complex system is required; the ships must be scanned and 

located very frequently if ambiguity is to be eliminited, and a largescale computer is required to correlate this massive flow of data with 

other sources which give ship identifications, ports of origin and destination, cargo, etc. One means of approaching a direct, unique identification is through the use of an optical system which provides man with 

sufficient ground resolution to be able to classify the ship within a small 

group of possible candidates. This would still require some data processing, 

but it would be very small compared to the location-only approach. Ground 

resolutions of the order of 5 to 10 feet appear to be appropriate to the 

classification problem. Man's function is to perform real-time pattern 

recognition, yielding, an indication as to which targets should be followed 

up by aircraft or sea-based forces, as well as data for updating large 

scale surveillance systems. 

IV. VEHICLE REQUIREMENTS DATA 

Reference is made to the corresponding discussion under Experiment 

P-1. No significant differences in spacecraft requirements from those discussed therein are presently identifiable with the exception that a viewing 

post for direct scanning of the terrain with the unaided eye will be required. 

V. SIMULATION PROGRAM 

A. Pre-Phase I 

The pre-phase I simulation study described in Experiment P-1 

will also provide data applicable to the design of the direct viewing telescope 

for use in this experiment. 

B. Phase I and Subsequent 

During the development phase of the MOL program scanning 

with the direct viewing system (pointing and tracking telescope) will be 

simulated in aircraft. A proper selection of aircraft altitude and velocity 

will enable exact simulation to be made of the apparent ground motion 

beneath the satellite. The magnification and field-of-view of the aircraft 

simulation equipment can also be selected to reproduce the satellite condition. Flights will also be made over pre-selected areas of the oceans 

in which a variety of ships have been positioned, these flights being made 

under varying conditions of lighting, atmospheric transmission, etc. 

Identification of specific surface ship targets will be included in the simulation procedures. 

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VI. EXPERIMENT DEFINITION 

A. Pre-Phase I Studies 

Reference is made to the corresponding section in experiment 

P-1. 

B. Phase I and Subsequent 

Reference is made to the corresponding section in experiment 

P-1. 

VII. FUNDING 

A. Pre-Phase I 

No additional funding is required over that stipulated for 

experiment P-1. 

B. Phase I and Subsequent 

An incremental cost of from 1 to 10 million dollars, over that 

associated with experiment P-1 is associated with this experiment. This 

increase is for the cost of aircraft operations and ship deployments for 

the simulation program and the development and fabrication of a "scaled" 

telescope system for the aircraft simulations. 

VIII. PARTICIPATING AGENCIES 

Sponsor. AFSSD/Aerospace 

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ELECTROMAGNETIC SIGNALNAL DETECTION 

I. Objective: 

This experiment will validate man's capability for making semianalytical decisions and control adjustments to optimize the orbital collection 

of intercept data from advanced electromagnetic emitters. 

Automatic collection systems operate at high-speed, have high-intercept 

probability, and are excellent for generating location or deployment of emitters 

in dense or dangeroUs environments. Automatic systems have certain inherent 

limitations, including: quantizing, with limited logic and possible loss of intelligence, of intercept parameters to conserve data storage in long missions; need 

for frequent readout or recovery for wide-band analog data; sensitivity loss to 

reduce false alarms; and tendencies to "lock-up" program logic on strong or 

saturating signal conditions. 

Semi-automatic manned systems, although inherently limited by man's 

slow time constants and requiring visual/aural displays, have certain potential 

advantages: optimum adjustment of collection system controls; lower false alarm 

threshold; recognition of anomolous signal characteristics; conservation of wideband recording media; real-time adaptive redirection of mission objectives, plus 

over-ride of logic routines; evaluation of faulty equipment, maintenance, adjustment and calibration. 

The application of these capabilities to increasing advanced emitter 

intercept quality, for maximal content extraction per intercept, is the basis 

of this experiment. 

A natural consequence of this experiment will be the factual base for 

development of new or improved program logic usable in future automatic 

system development. Each sophisticated emission intercept and its dissection, 

analysis and interpretation are individual laboratory-like experiments, using 

flexible instrumentation to encompass many probabilities; manned guidance for 

this electronic capability is initially essential, prior to sufficient understanding 

necessary to logic system development. 

II. Description of the Experiment: 

a. Experimental Equipment: 

The on-board equipment will be representative portions of militarily useful intercept systems designs, with sufficient frequency difference to 

introduce diversity of operating decisions and actions. Since the MOL time 

period considered is a major segment of normal advanced development cycles, 

it is anticipated that extension to space compatible designs from present de-. 

velopment programs is quite feasible. 

Capability will exist, over the selected frequency ranges. for fixed 

and steerable antennas, automatic and semi-automatic receivers, signal-sorting 

and processing equipment for operator alerting to exotic signal conditions, 

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Exp No. P-4 -Emeasurement and display console and record-playback storage equipment. 

Suggested frequency regimes are 400-900 mc/s and a choice of C-band or 

S-band. (Actual coverage should be studied relative to development trends 

in emitter design and use, circa 1970). 

Sensitivity of reception equipment must be that capable of operating to the horizon, at orbital altitudes of approximately 150 n. m. , against 

radiators of 10kw 100kw average power, whose effective minor lobe power 

may be -20 to -30 db relative to the main lobe. Bandwidths must be commensurate to the spectra of frequency agaility systems anticipated in the 1968-

1970 time period. 

Antenna structures must provide general coverage patterns, 

consistent with orbit pattern chosen, for acquisition and high intercept probability in favored directions. Possible inclusion is considered of steerable 

(electronically phased or mechanical) structures to prolong time of intercept 

or improve location fixing. Specific studies (see below) are indicated on this 

problem. 

The complexity and inclusion of the automatic (environment 

scanning) reception and processing equipment will be a function of the breadth 

of the mission objective, in the operational context, required of the console 

operator. Simulation experiments (see below) must provide guidelines for 

this decision. One may hypothesize that more limited objectives and highly 

pre-instructed operators will allow reduction of signal sorting equipment. 

Measurement and display console equipment, and associated recording playback capability, will be somewhat independent of frequencies of 

reception. Included in this equipment should be: frequency activity monitoring display, frequency resolution display (associated with selectable bandwidth choices of the semi-automatic receivers), slow and fast time base modulation envelope displays and such alpha-numeric readouts as are essential 

to operator alerting. Recording capability must include wideband (4-6 me/s) 

analog video tape, multi-track digital and narrow band aural recording for 

control status, low-frequency signal modulation and comment. Frame-by 

frame photo recording may also be desirable for post-real-time, partial 

analysis or ground examination. 

Additional supporting equipment needed in the performance of 

the experiment are ground and sea based emitters as sor■ res of specific 

known signals. Since emphasis of this effort is on sophisticated emitters, 

such targets must include frequency agility, long pulse internal coding, and 

other.: intentioned parameter modulations or complex scan modes. Use of 

vessel-based emitters under U. S. Navy or USAF control (i. e. , missile 

launch cruisers and tracking vessels such as AR/S) can provide fairly sophisticated targets in light density environments. 

Ancillary equipment such as data readout and/or recovery systems 

are not dealt with here, as it is presumed they will be a necessary subsystem 

to the general performance of the overall program. Extended requirements 

imposed by this experiment must be injected as a result of more specific definition of the program and separate study. 

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b. Test Procedure: 

Certain assumptions are necessary to development of procedures 

for the experiment. Orbit inclination must be chosen to give some continuous 

over-flight of ZI territory, or other areas well controlled, accessible and in 

good communication to the MOL Flight Control. The ability to establish known 

signal environments, under control, is dependent on such choice. Inclination 

of greater than 30 is essential. Cooperation of cognizant commands, agencies 

and other responsible organizations must be secured early and well exercised, 

so that a "ground truth" condition is established during orbital flight. 

The extension of simulation program results to orbital test requires 

some calibration of the initial performance capability of the operator as a frame 

of reference to subsequent performance. It will therefore be necessary to utilize targets representative of those employed in aircraft simulation tests, thus 

providing continuity in evaluation. 

The basic matrix of tests includes the cross products of: 

1. light versus dense signal environments. 

2. simple versus highly complex signal parameters. 

3. self versus machine-aided alerting, and 

4. maximum versus minimum precognition or instruction. 

Additional subcategories of investigation should provide tests of signal anomoly 

recognition, "non-intentioned" radiation events, activity level significant changes 

and adjustment and calibration maintenance. These must be "programmed-in" 

under ground control to provide realism and objective data taking. 

On each available orbit (assuming competition from other test programs) including day and night crossings of the test points, the console operator will be offered successively more difficult problems in terms of the 

above mentioned matrix of choices. The development of this test sequence 

is a major item of preliniinary study. 

Specific control actions to be taken by the console manipulator 

include: 

1. Center frequency tuning adjustment to center signal in pass - 

band. 

2. Choose optimum bandwidth of S/N improvement. 

3. Set gain controls for dynamic range control in recording most 

important sections of strong signals or extracting weak ones. 

4. Adjust synchronizing controls of displays to maximize or minimize effects of interleaved clutter signals. 

5. Employ time gating or frequency exclusion gating for removing 

clutter. 

6. Select appropriate detector outputs for display, particularly 

with the reference to clarifying signal coding. 

7. Select appropriate recording medium and length of recording. 

8. After a pass, play back recordings, as desired, for evaluation 

of next pass procedure, or improvement of approach. 

9. Respond to direction for or programmed adjustment and 

calibration. 

10. Monitor and report "events" in.nactivity level", unusual noise 

level, etc. 

11. Alerting of other sensors. 

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Exp No. P-4 --SEGREfc.. Evaluation procedures: 

Evaluation of test results will be in part a function of the data 

reporting system available. A combination of "hot-flash" verbal reporting, 

video signal readout, tape and/or photo recovery, while in flight, will exercise and grade the operator on his accuracy, quality of intercept, and ability 

to compress data. Specific scoring elements should include: 

Recognition and recording of significant signal parameter 

modulations. 

Recognition and recording of emitter radiation patterns. 

Recognition of aperiodic, "non-instructed" activity level events. 

Speed of acquisition and processing time per test intercept. 

Response to "system degradation" or "failure" modes of operation. 

Due consideration must be given to equipment performance factors and propagation effects in comparing ground based reference data to orbital reports. 

Study on calibrating requirements will assist objective evaluation of the manes 

performance. For example, measurement of the!performance degradation 

of the operator with time must be accomplished by resubmitting a standard 

test intercept periodically during the course of orbital flight. 

M. Vehicle Requirements Data. 

Major Equipment - Wt/lbs Vol/cu. ft. Power/watts 

Antennas 75 1. 5 50 

Receivers 100 1. 5 200 

Display Console 200 3 300 

Recorders 125 2 200 

500 ?50 

Vehicle stabilization of I° is required. Apertures may be required for control 

cables and possible mechanisms for erection and/or extension of antenna arrays. 

IV. Simulation Program 

a. Prophase I. 

The geometry of the satellite-in-orbit electromagnetic intercept 

experiment provides, at 125-175 n. m. altitudes, approximately 0-16 minutes 

from horizon point forward pickup to horizon point rearward loss. On the nadir 

track, the maximum time is available; at the edges of the circle of horizon 

coverage the time becomes zero. 

Assuming all other factors equal and favorable, the fundamental 

questions behind this proposed experiment simulation are: 

What tasks can the operator perform in the time available? or, 

What is the minimum time 'necessary for operator intercept 

processing under varying conditions of signal and physical 

environment complexity? 

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--SECRET- Exp No. P-4 

Recent teats of new airborne systems with capability analogous to 

that described above have shown results which border on the feasibility limits. 

However, these results are not a directly usable data point as the intent of the 

test program was equipment shakedown and evaluation. No great emphasis was 

placed on operating speed. Improvement factors possible have been estimated 

at from 2 to 4:1, thus providing fair justification for additional consideration, 

as this would provide 1-2 minutes per intercept processing on selected targets. 

Therefore it is recommended that an immediate simulation program 

be instituted using this aircraft intercept system, 7,71117—Matial.equal, to determine the operator's reaction and processing speeds against typical emitters 

of interest. (A prelininary study for implementing this action is suggested below). 

Use of ZI complexes such as the Eglin Field area, New York-New Jersey area, 

Southern California area and others will provide ample test targets in reasonably known environments. 

It is believed that such simulation using real signal environment, 

while more difficult to control than chamber or mock-up simulators, will provide authentic results capable of translation to the next step of development and 

test. In this method, radio frequency reception controls become "live" as compared to video playback systems in chambers or static test consoles. 

b. Phase I 

During Phase I and subsequent times, it is presuMed that composite 

simulation of a MOL in entirety with all controls will be studied and built. This 

experiment and its equipment should be included, assurniql fruitful results from 

Prephase I simulation and studies. Input signals for this simulation could be derived from tapes of the aircraft tests and comparative results analyzed. 

V. Experiment Definition 

a. Prephase I Studies 

(1) Simulation in aircraft: 

For the aircraft simulation tests, wherein a first calibration 

of the operator's response and control action timing is achieved, an initial 

prephase I study encompassing at least the following items is suggested: 

(a) Determination of approproate aircraft availability. 

(b) Assessment of control and display functions analogous 

to a potential MOL console. 

(c) Determination of suitable flight test areas providing 

proper emitter targets. 

(d) Lay-out of a test matrix embodying the possible crossproducts of the test difficulties in (II, b) above. 

(e) Decision on type of operator selected for testing. 

(f) Plan for test flights and ground coordination. 

(g) Plan for test and evaluation procedures capable of 

being extended to future simulations in other modes. 

(2) Optimum orbit and antenna patterns for MOL intercept 

experiment 

This study should explore the orbital inclination, altitude 

and repetition pattern most suitable to conduct of this experiment. Ground 

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Exp No. P-4 --SECRETrange availability, including sea borne targets, and emitter choices consistent 

with simulation testing are included. Relation to high inclination orbits is a 

topic to be evaluated. Antenna patterns should be explored for highest acquisition probability, spatial clutter filtering, location fixing and gain. 

(3) Study of space borne display systems for rapid recognition 

of signal modulation variations. 

The console for the MOL operator will be limited in size and 

weight. It is of great importance to be able to present. to the operator, displays 

emphasizing departures from simple non-varying signal modulations. Consolidation of display and/or correlative displays should be studied for possible improved presentation systems. 

(4) Study of recording, storage, readout and recovery of 

selected intercept data in MOL experiments. 

This study is directed.to analysis of the quantity of data to 

be taken and its digestion and manipulation in the testing of the operator's activities. Attention is directed to recording and storage time in cessary, bandwidths, status and monitoring recording. This study is inter-related with the 

general problem of on-orbit test reporting and would provide inputs to that effort. 

b. Phase I Studies 

At this time it is considered vital to establish a firm base upon 

-which to plan Phase I effort by conduct of the studies and aircraft simulations 

described above. U results are sufficiently encouraging from these efforts, 

Phase I preliniinary design studies leading to firm specifications would include: 

(1) Advanced simulation studies relating to combined payloads 

in MOL chamber mockups and using normal mission time clocking. 

(2) Study for adaptation or redevelopment of intercept equipment 

designs suitable for inclusion in the MOL. 

(3) Study of specific antenna designs providing general coverage and 

steerability in the chosen experimental frequency ranges. 

(4) Study of orbital experiment test plan and ground range selections. 

VI. Funding 

a. Prephase I Studies 

(1) Aircraft simulation program study $50K 

(2) Optimum orbit and antenna patterns for 

MOL intercept experiment 25K 

(3) Study of space borne display systems for 

rapid recognition of signal modulation variations 50K 

(4) Study of recording, storage, readout and 

recovery of selected intercept data 50K 

(5) Simulation pro ram 

50K

ram direction (not including 

operating costs) 

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b. Phase PhasI Studies 

Estimated rough costs $500K 

VII. PARTICIPATING AGENCIES 

Sponsor: AFSSD/Aerospace 

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Experiment No. P-5 

IN-SPACE MAINTENANCE 

(PART 1) 

INTRODUCTION. 

This experiment is in two parts. Part 1 discusses maintenance 

of electronic equipment required in experiment P-4. Part 2, discusses 

the maintenance, of the MOL vehicle, subsystems, and equipment of other 

experiments. 

I. OBJECTIVE. 

The objective of this test is to verify, to evaluate and to establish 

the capability of an astronaut operator to perform the maintenance function 

of complex military electronic signal detection equipment in a spaceborne 

environment. Although the experiment was directed towards electronic 

signal detection sensors, it is also believed to be applicable to communication radar, IR and guidance sensors. 

EXPERIMENT DESCRIPTION. 

The on orbit experiment will be performed in conjunction with the 

equipments required in Experiment P-4. The additional equipments to support this experiment are the Fault Generating Programmer Unit, appropriate 

tools, maintenance manual, support self-test set and/or an external portable 

test set. Replacement spares, as optimized in kind and quantity by previous 

study, will also be required. 

The proposed procedure is to cause programmed failures through 

the use of the Fault Generating Programmer Unit. The initiation of the 

faults may be done through internal preset timers or by direct control from 

the ground Command and Control Facility. The types of failures would include: 

Failures that cause significant degradation of performance. 

Failures that are catastrophic, causing complete breakdown of 

operation. 

Through the operation of the external and/or internal test sets, the 

astronaut will localize the fault; then the maintenance function proven by the 

ground simulation program may be applied. (It is assumed that the design 

of the sensor is configured upon a fail safe concept.) 

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The maintenance function selected may be one of the following, 

based upon the design of the primary equipment: 

1. The equipment may contain built-in, inherent redundancy 

such that a common failure does not produce a catastrophic 

failure. In actual practice a failure of a component may 

occur without the astronaut operator being aware of the 

failure. Operation of the device would continue to be normal. The ability to locate such failures will be dependent 

upon the degree of complexity of the test sets. 

2. The equipment may contain redundant components which are 

available by the action of automatic fault sensing and automatic switch over. 

3. The equipment may contain redundant components which 

are available by the action of automatic fault sensing and 

manual switch over. 

4. The sensor may contain redundant components which are 

available by the action of the manual fault sensing and manual 

switch over. 

5. The Manual Maintenance Functions are defined as: 

a. Removal and direct replacement of a modular unit. 

Examples are receiver IF amplifier, video channel, 

logic chain. These are usually mounted as a selfcontained unit on a plastic plug-in board or a plugin capsule. 

b. Direct replacement of major component parts. 

Examples: replacement of a cooling blower motor, 

gyroscope, power supply, etc.; the component may 

be part of a base frame or structure member. 

c. Disassembly of a complex component and replacement 

of the defective part and/or parts. Example: replacement of an electron tube, transistor, etc., from an 

assembled unit; removal of the beam unit of a TWT or 

similar replacement may be required. 

d. Repair of the actual defective component, if practical. 

Example: repair of mechanical damage, securing of 

parts to structure, etc. 

e. Adjustment of controls to initial state. Examples: 

adjustment of gain controls to overcome loss of circuit gain, or to correct the effects due to loosening,etc. 

f. Alignment of electrical circuits and mechanical assemblies. 

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Exp No.P-5 

The evaluation of the astronaut operator will be based upon: 

1. The time required to recognize the existence of a 

system malfunction. 

2. The time required to perform the test function of 

localizing the specific area of failure. 

3. The time required and quality of the system characteristics after direct replacement of a defective module, 

part, etc. The evaluation is based on the assumption 

that absolute minimum down time is essential, and 

further, that some loss of system performance is 

tolerable. In other words, some operation is preferable to none. 

4. The time required and quality of the system characteristics after performance of the proper kind of maintenance function(other than in 3). The evaluation, in this 

case, assumes that sufficient time exists before the 

next required operational period. In such circumstances, ground to space instructions may be considered practical. 

5. Where possible, the quality of the repair will be 

evaluated from the study of photographs. 

It is recognized that during the mission of the experiment, nonprogrammed natural failures will occur. In such cases the astronaut is 

expected to perform the maintenance functions required to return the device 

to proper operating condition, and such action will provide additional data 

on the validity of the maintenance concepts. 

The method of confirmation of return to proper operating condition 

may be determined from: 

1. By detailed observations taken by the associate astronaut. 

2. By the print-out or manual recording of the check-out 

data given by the external and/or self-test sets. 

The experiment will be covered photographically with proper time 

references. From the pictures, comparison may be made with similar data 

taken during the ground and/or aircraft simulation program. Additional data 

on the basic time and motion behavior may be determined. 

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III. IMPORTANCE OF THE EXPERIMENT. 

Upon completion of the experiment, it should be possible to determine the specific kinds of maintenance functions the astronaut operator can 

perform. Also and maybe more important it should be possible to determine 

those kinds of maintenance functions that an astronaut operator cannot or 

should not perform. 

In those cases where the maintenance function was found to be 

unsatisfactory, then the implications upon the design to overcome the deficiency must be determined. 

From the results of the experiment it should be possible to further 

optimize a design philosophy such that it is compatible with the capability of 

the average astronaut operator to perform maintenance in the spaceborne 

environment. 

IV. VEHICLE REQUIREMENTS. 

The estimated physical and electrical characteristics of the equipment required for the experiment are listed: 

Fault Generating Programmer 

Weight 

(lb) 

Volume 

(ft) 

Power 

(w) 

Unit 20 2.5 100 

Malfunction Detection Panel 30 5.0 100 

Portable External Test Set 7 0.2 50 

Tool Kit, Maintenance Manual 5 * •• IOW - 

Cameras and Lights 20 1.0 200 

82 8.7 450 

V. PARTICIPATING AGENCIES. 

Sponsor: (PART 1) AFSSD/Aerospace 

(PART 2) RDT (Aero Propulsion Lab) 

Stored in console space. 

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Experiment No. P-5 

INSPACE MAINTENANCE 

PART 2 

I. TEST OBJECTIVE. 

The principal objective of this experiment is to provide a demonstrated 

capability of orbital maintenance. This orbital maintenance capability will 

result in future reduction in weight of space systems by reducing or eliminating the number of redundant systems required to complete a mission. 

Finally, this experiment is a necessity before undertaking longer and 

deeper space missions where the probability of component failure is high 

and mission success will depend on man's ability to effect on the spot repairs . 

II. IMPORTANCE OF THE TEST. 

This maintenance kit will be available for all MOL missions and will 

provide a significant increase in safety to the crew. This proposed space 

maintenance experiment is important to verify maintenance techniques that 

have been established through R & D contractural and inhouse efforts. Previous manned space missions undertaken by NASA have established the requirement for orbital maintenance capability. That is, these flights have 

had a number of failures which required the astronaut to correct the malfunction or to take alternate or redundant approaches . 

These experiments must be conducted on the MOL because this vehicle 

will be the only manned vehicle in orbit for a thirty (30) day mission. These 

space maintenance techniques require the utilization of man in the repair 

cycle. There are no adequate facilities on the earth which could simulate 

zero g and a vacuum simultaneously for prolonged periods of time, which 

would be required for conducting these experiments. 

The use of a KC-135 or C-130 will not provide sufficient time under 

"0"g conditions to properly assess the tools techniques perceivable. Likewise, air bearing simulators cannot simulate the true conditions of "0"g's: 

therefore, MOL is the only known method of carrying out various sustained 

manual operations which can provide a thorough insight into the problems as 

they are actually encountered in sustained space operation. Without question, 

the man/machine relation can be thoroughly demonstrated to asses man's 

ability and utility while functioning in the role of maintenance and repair. 

Little is known as to what effect the total space environment will have on 

man and tools and techniques to be used for apace maintenance. 

This experiment will definitely assess and demonstrate man's ability 

in maintaining his vehicle in the hostile environment of space. All of the 

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proposed experiment relies on the inclusion of man's ability to do maintenance tasks. 

III. DESCRIPTION OF THE EXPERIMENT. 

This experiment will include maintenance tasks to be conducted both 

inside the MOL and inside unpressurized module. These tasks will incorporate the zero reaction power tool, minimum reaction manual tools, space 

qualified adhesive system, instant attachment systems, electrical conducting 

rapid setting plastic cements, insulating (electrical) rapid setting cements, 

and welding techniques (thermite, contact.) and electronic transistorized 

fault detection device. The astronaut will conduct tests on the interior of 

MOL, utilizing the above mentioned techniques. These techniques, in addition to being used experimentally, can be integrated into actual emergency 

repairs to the basic MOL mission. 

The astronaut will enter unpressurized module and perform various 

maintenance tasks such as replacing components, performing structural 

repairs, applying and repairing coatings for control of emissivity/absorptivity, checkout new materials for maintenance (rapid setting plastics, etc.), 

checkout thermite type welding and pressure welding techniques, checkout 

utilization of zero reaction space power tool, verify astronaut attachment 

techniques, and checkout small hand held fault detection device (for electronic devices). 

Problems: The most significant problem anticipated for the performance of these experiments is the development of a truly flexible extravehicular space suit. Many unforeseen problems are expected but primarily 

in learning to use the tools in space when working against a time deadline. 

These problems, however, should not be of such critical nature to affect 

crew safety on vehicle operation. As in the other military missions, the 

receiving and evaluation of data on the ground must be part of the test so 

that decisions can either be made or simulated on earth and transmitted back 

to the satellite as an expedited command. 

It should be recognized that the available payload space and crew time 

available in MOL would dictate the degree of complexity permitted for these 

tests. The actual test could vary from one minute of time to one hour and 

could require little or a lot of expended man and machine energy. 

a. Configuration of Test Items... 

The experiment would be contained in a 5.0 cu. ft. tool box, 

total weight of 100 lbs., preferably located in pressurized area of MOL. 

The location preferred would make available repair kit to astronauts for 

emergency repairs to interior of MOL. Key items in tool box are; zero 

reaction power tool, Welding device, astronauts attachment device, rapid 

setting cements, emissivity coatings, and fault detection device. See 

Attachment I. 

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h. Test Support Equipment Required. 

The experiments will require use of several maintenance task 

panels . These panels would have bolt patterns, simulated micro-meteorite 

holes, damage electrical cables, and a pressure vessel with a blow-out 

plug . 

c. Test Procedure. 

This experiment will demonstrate the extent of man's ability to 

perform representative maintenance tasks inside the vehicle. It will also 

define problems that have not been anticipated during the performance of 

a maintenance mission in an actual space environment. 

Internal Maintenance and Repair - Bench tests will be conducted 

to demonstrate the man/machine relation of selected mechanical and electrical maintenance and repair tasks. The crews will rotate the tasks and 

a still photo, movie, and note record will be made as to the outcome of the 

individual efforts. The work will initially be carried out in a shirt-sleeve 

environment throughout a range of temperatures and pressures gradually 

working up to a full suit operation in the laboratory working in a space vacuum environment. The tasks will be conducted at various times of the 

24-hour period to evaluate the physiological as well as the psychological, 

performance of the crews. After the routine operations of the tool use and 

specific techniques are identified, the crew will vary the tasks to attempt 

to function against time in simulating various emergencies that might occur 

in the MOL. Areas of test would involve: leak detection; gas diffusion; 

simulating meteorological etching and fatiguing of coatings, glass, metals; 

fabrication and assembly by riveting, adhesives, welding, cutting of structural and ahtennae material with constant and differential temperatures. 

Emergency electrical repairs will be simulated, such as cable repairs, 

detection, and replacement of electronic components. Most of the =pressurized tests will be conducted in the unpressurized compartment of the 

MOL. 

External Maintenance and Repair - Within safety limitations, the 

crew members will conduct extravehicular inspections and conduct tests on 

their own vehicle in an area which is not critical to the mission. The process will be much the same, as described above, and will repeat work in 

those areas that are considered of a nature requiring vehicle repairs and 

simple construction tasks while tethered, as well as operating with an Astronaut Maneuvering Unit. 

d. Category of Experiments. 

These experiments fall in category B as defined by the format. 

e. Cost . 

(1) See Attachment 4 

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f. Schedule. 

(1) Hardware and software available for test - Early 1966 or 

late 1965. 

(2) Hardware and software flight readiness date - Early 1967. 

W. PARTICIPATING GOVERNMENT AGENCIES . 

Sponsor: (Part 1) AFFSSD/Aerospace 

(Part 2) RDT-Aero Propulsion Lab. 

Test Equipment Acquisition: Air Force Aero Propulsion Laboratory 

APFT, WPAFB, Ohio 

V. ADDITIONAL REQUIREMENTS. 

a. Special Security. 

Unclassified 

b. Manning Description Summary. 

The maintenance and repair tasks will be rotated between the 

two astronauts. They will require ground and aircraft training in the use of 

the tools with and without equipments for functioning in free-space. 

c. Logistics,. CY 64 CY 65 CY 66 TOTAL 

(1) Manpower (Man Years) B B 

(a) Hardware Dvlpmt 1 1 2 

(b) Installation 1 1 2 

(c) Operation 1 1 

(d) Additional Support 1 1 

TOTAL 6 Man Years 

d. Facilities. 

Sponsor can use existing facilities located at WPAFB without 

any modification being required. Man will be using space qualified equipment. All of the facilities required to conduct the experiments, prior to the 

flight, are available at WPAFB and no new facilities are required. These 

items will be man rated. 

An air bearing table capable of supporting a 500# weight will be 

available at WPAFB and can be used to conduct portions of the experiment. 

Following the air-bearing tests, the "Ong KC-135 should be used with minor 

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modifications to incorporate the test tools, tether and task item, . Lowpressure work in an AMU is desirable. A 24 foot diameter 10" mm Hg 

vacuum chamber is available for vacuum testing. 

e. Simulation and Training, 

(1) Astronaut: The astronaut that will perform these experiments would perform the required maintenance test on a six degree of 

freedom simulator in a pressurized suit prior to the flight. The extent of 

the training would depend on the astronaut's confidence that he could perform these same tests in a space environment. For these tests the astronaut can be trained as a technician. Zero g flight tests will be utilized to 

train astronauts. 

(2) Ground Personnel: Not required 

(3) Equipment: Simulators, G degree freedom platform, zero 

"g" aircraft, and vacuum chamber 

VI. GENERAL. 

a. Communications and Data Handling Requirement 

See Attachment 6 

b . Development Characteristics 

See Attachment 7 

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Exp. No. P-5 Atch. #1 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED - Zero reaction power tool, instant 

attachment device (device to anchor astronaut to a work site), hand tools, 

materials repair kit (consisting of rapid setting plastic and organic cements), 

thermite welding technique, and a•transistorized fault detection device for 

locating electronic malfunctions. For simplicity, all of the above items are 

assumed to be in one kit or tool box. 

2. WEIGHT - 100 lbs . (Materials Wt. 15 lbs, attachment device and 

adhesive pads 20 lbs, zero reaction power tool and support equipment 20 lbs, 

thermite welding technique and support equipment 15 lbs .) 

3. VOLUME - Stored 5.0 cu. ft. In use 5.0 cu. ft. 

4. POWER 

a. Continuous - No continuous power required, periodic recharging 

of hand held power tool battery will be required; however, this can be done 

on a small trickle charge basis. 

5. SPARES - Extra batteries for power tool 

a. Volume - .05 cu. ft. 

b. Quantity - 1 battery 

c. Weight - 2 lbs 

6. TOOLS - Since this experiment has tools as its primary equipment, 

listed under Item 1 of Attachment 1, this section is not applicable. 

7. HEAT OUTPUT - Negligible 

8. STABILITY - This experiment requires no special stabilization and it 

will not impart to basic MOL. 

9. VIBRATION LIMITS - The items or equipment to be utilized in this 

experiment do not have any critical vibration limits. The tool case will be 

lined with a plastic foam to absorb vibration and shock. 

10. SHOCK LIMITS - Not critical, especially with plastic foam tool box 

liner . 

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11. HAZARDS - Power tool will present little or no hazard. The welding 

technique may involve some hazard but nothing that cannot be overcome with 

proper safety procedure. Chemical reactions from rapid setting plastics 

will not be toxic in quantities given off. In fact. rapid setting non-toxic 

plastics would be utilized. 

12. TEMPERATURE LIMITATIONS - *150°F 

13. TYPE AND RANGE OF MEASUREMENT - Since this experiment will 

evaluate various maintenance techniques to be utilized by man, the optimum 

measurement technique would be the astronaut's comments or evaluations 

plus a stop motion picture coverage of the test. Stop motion camera could 

be mounted on astronaut's helmet to record every 10-20 seconds a photograph of what the astronaut views.. 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS - None except an 

extravehicular space suit. Prefer MOL atmosphere not to be pure oxygen. 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS - No 

special orientation required. 

16. EQUIPMENT OPERATING CYCLE - The operating equipment is battery charger for hand power tool. 

17. EQUIPMENT LOCATION REQUIREMENTS - Prefer to be stored in 

actual pressurized cabin, but this is not an absolute necessity. 

18. SPECIAL MOUNTING REQUIREMENTS - The only mounting requirements would be a bracket or tie down to hold tool box. 

19. PRESSURE VESSELS - Small pressure vessel of nitrogen prefered for 

experiment on sealing a punctured pressure vessel. 

20. ELECTRO MAGNETIC INTERFERENCE - Only possible interference 

would be from portable hand held power tools; however, the tool will be 

shielded against transmission of interference signals. 

21. MAINTENANCE REQUIREMENTS 

a. Ground - None 

b. Space - Only periodic recharging of hand held power tool battery. 

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TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape - Record astronauts comments 

b. Film - 16 or 8 mm stop motion camera film 

c. Other - Experiment notebook kept by astronaut and strain gages. 

2. HANDLING 

3. PACKAGING - N/A 

4. CALIBRATION - Strain gages 

5. JIGS AND FIXTURES - Three (3) each maintenance test panels for 

conducting extravehicular repair tasks in unpressurized module of MOL. 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION - None 

anticipated. 

7. SENSORS - Strain gages 

8. TRAINERS/SIMULATORS - Six (6) degree freedom simulator, 24 ft. 

dia. 10-9 mm Hg vacuum chamber, 30 sec. zero g flights, etc. are available 

in-house under auspices of APFT sponsoring organization. 

9. INSTRUMENTATION - Strain'gages 

10. RELATED SUPPORT EQUIPMENT 

a. Targets - None required 

b . Ground Stations - None required 

c. Tracking - None required 

d. Handling Equipment - None 

11. AGE - None required 

12. ENVIRONMENTAL TEST EQUIPMENT - None required 

13. FACILITIES - None required beyond what is now available to APFT. 

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Atch. #3 Exp . No. P -5 

TEST OPERATING CHARACTERISTICS 

ORBITAL PARAMETERS 

a. Altitude - Below Van Allen Belts 

b . Inclination - Any 

c . Epoch - Any 

d. Ellipticity - Any 

2. PLANE CHANGE - None 

3. ALTITUDE CHANGE - None 

4. TIME ON ORBIT - Would like to conduct portions of experiments in 

both daylight and also dark portion of orbit. 

5. TEST DURATION - Eight (8) maintenance tests will be conducted in 

pressurized module of MOL. These tests would last about 30 minutes each. 

Four (4) extravehicular missions to be conducted in unpressurized module 

duration 35 to 40 minutes each. Later astronaut wearing an AMU will 

possibly inspect MOL and try to repair micro-meteorite bumper. 

6. TOTAL NUMBER OF TESTS - Eight (8) pressurized cabin tests. 

Four (4) non-pressurized compartment test and possibly one extravehicular 

test with AMU. 

7. TEST FREQUENCY - As often as necessary to ascertain effectiveness. 

8. INTERVAL BETWEEN TESTS - As necessary to adapt to the environment. 

9. CREW TASK LOADS - Man hours 

a. Internal pressurized tests - 4 to 5 manhours 

b. Non-pressurized compartment test - 3 manhours 

c. Extravehicular test - At discretion of astronaut 

All test times include donning space suit, AMU and servicing of AMU/ 

or tools. 

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10. CREW TASK FREQUENCY - One astronaut will be required to devote 

his full attention and effort to the experiment, with possible exception in 

pressurized compartment test. Other astronaut would periodically observe 

experimenter in non-pressurized and extravehicluar tests. Astronauts 

would rotate after completion of each experiment. 

11. FIELD OF VIEW REQUIREMENTS - Angle of view afforded by space 

helmet would be adequate. Direct observation is prefered. 

12. GROUND CONTROL LIAISON DURATION - Not required 

13. GROUND CONTROL LIAISON FREQUENCY - Not required 

14. EXTERNAL TEST ITEMS: 

a. Launched from Station - None required 

b . Launched from Resupply - None required 

c. Launched from Ground - None required 

15. QUALIFICATION TESTS 

a. Ground - Mandatory vacuum qualification tests, shake, rattle, 

roll test, temperature limitation testing, and reliability qualification testing. 

b. Atmosphere - Mandatory zero g flight testing on KC-135 aircraft. 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT 

a. Pressurized test - (1) Test and use a zero reaction power tool 

for replacing components inside the MOL. (2) Test method for use of hand 

tools in performing a maintenance task inside the MOL. (3) Test and 

evaluate the application of rapid setting adhesive system and other techniques 

for repairing electrical connections (e.g. insulators, conductors) and also 

evaluate application of adhesive system for performing maintenance task 

inside the vehicle. Finally, a pressure vessel of nitrogen will have a leak 

initiated in it. The astronaut will try and effect a repair with his tool kit. 

b. Unpressurized Test Inside Vehicle - (1) Perform a maintenance 

task utilizing the zero reaction power tool and hand tools, including the 

checkout of using a fast setting adhesive attachment system in the performance of the maintenance task. (2) Evaluate the application of rapid setting materials for the performance of maintenance task such as: repairing 

electrical malfunctions, patching hole in a structure. (3) Evaluate thermite 

welding techniques. (4) Sealing a leaking or punctured pressure vessel. 

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Atch. 03 (Cont'd) Exp. No. P-5 

c. Extravehicular test - The astronaut will don the AMU, exit the 

vehicle and maneuver to a preplanned work site. He will conduct an overall 

inspection of the MOL, and attempt to effect repairs on the vehicle, such 

as patching outer shell of micro-meteorite bumper. 

17. HANDLING PROCEDURES - AMU will be utilized where possible. 

a 

SSTA -1 -9 

45 
co 

Exp . No. P -5 Atch . #4 

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mber: 62405336 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Atch. 05 Exp . No: P -5 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required - One astronaut will be required to perform 

the experiments . 

(1) Man's function -- 

(a) As part of test - Man will actually be part of the test. 

He will be required to go outside his pressurized environment and perform 

the described maintenance test and analyze the results. Man will conduct 

and execute specified maintenance task in the pressurized portion of MOL. 

(b) As technician conducting test - The astronaut will be 

required to utilize his technical judgment during experiments. He will be 

required to assess to effectiveness of his tools and repair materials. 

b. Crew skill requirements - The skill of the average astronaut will 

be enough to perform these experiments with knowledge of the specific operational techniques to be used. 

c . Manpower Profile - Astronauts should be familiar with system 

maintenance requirements. The tests will consume about 8 hours out of the 

entire 30 day mission. 

d. Critical Functions - The critical function throughout these experiments is demonstrating the effectiveness of using the maintenance techniques specified to perform a maintenance task in the unpressurized compartment of MOL. 

e . Work Positions - Work positions will be inside the pressurized 

vehicle, inside the unpressurized vehicle, and possible extravehicular at 

astronaut's discretion. He will work both tethered and untethered. 

f. Time Controlled Tasks - Each task will be time-controlled. The 

astronaut will be required to be outside the pressurized portions of the 

vehicle for forty (40) minutes, maximum. He should function under simulated emergency "time" conditions. 

g. Human Performance Measures - Time measurements are required for man in a pressure suit in a hostile environment to perform a 

required maintenance task. 

h. Physiological and Psychological Measures - Both of these factors 

will be considered in this experiment. 

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Exp. No. P-5 Atch. #5 (Cont'd) 

i. Selection Factors - Astronaut should have normal dexterity. 

j. Training Requirements - Training relative to the procedures and 

techniques required in the performance of the maintenance task will be required. Simulator-air-bearing as well as ',Ong aircraft tests are mandatory 

for familiarization with the tools and techniques. 

2. GROUND PERSONNEL - Not required 

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COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE - N/A 

2. FUNCTIONS TO BE MEASURED - N/A 

3. TYPE OF ANALYSIS REQUIRED - Two (2) way voice communication 

and astronauts evaluation of the performed operation. 

4. PICTORIAL DATA REQUIRED - Stop Motion camera to take pictures 

every 20 seconds. 

5. REAL TIME MONITORING REQUIREMENT - N/A 

6. DATA EDITING OR COMPRESSION - Stop motion film and notes by 

astronaut will be returned to earth. 

7. READ-OUT TIME - N/A 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS - Film and notes . 

9. MANUAL AND/OR AUTOMATIC CONTROL - N/A 

10. SIMULTANEITY - N/A 

11. GROUND COMMANDS REQUIRED - N/A 

12. COMMUNICATIONS AND DATA HANDLING - Not mandatory - photos 

and movie record will be returned with the crew. If space permits imaging 

photos from a hand held TV camera would provide the ground with early 

visual observations of the test as a supplement to any terse verbal summary 

of the activities. 

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DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME - Through CY 65 to early part of CY 66. 

2. FINAL DEFINITIVE TEST DESIGN TIME - Through CY 66 to early 

part of CY 67. 

3. NUMBER OF GROUND OR FLIGHT TEST REQUIRED - Tests will be 

required on a six degree of freedom simulator throughout CY 67, on the 

ground. 

4. TYPE OF DEVELOPMENT TEST ITEMS 

a. Vacuum Chamber - Power tool, adhesives, welding. 

b. Shaker - N/A 

c. Thermal - Power tool, adhesives 

d. Acoustic - N/A 

e. Simulators - (Six degrees of freedom) all test items, typical 

MOL flight simulators. 

f. Aircraft - Flying Keplerian Trajectory all test. 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME - Available 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test - 5 repair kits 

b. Atmospheric Test - 3 repair kits 

c. Space Test - 8 complete repair kits to be made available for all 

MOL missions for added crew safety. 

7. DATE AVAILABLE FOR TESTS - Early CY 67 

8. CURRENT DEVELOPMENT STATUS 

a. Proposed only - N/A 

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Atch. 07 (Cont'd) Exp. No. P-5 

b. Project or program is approved and test item is under study, 

breadboard stage, etc. - Program is approved and test items are under 

study and some have reached the breadboard stage. 

c. Funds expended to date - $160K 

OP 

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Experiment No. P-6 

EXTRAVEHICULAR ACTIVITY ACTIVITY 

I. TEST OBJECTIVE 

The objective of the experiment is to determine what functions man 

can effectively perform while outside a spacecraft, and the tool and equipment requirements. The experiment resultr will determine the tools and 

equipment which are necessary and effective for man to perform and operate in an extravehicular environment. 

H. IMPORTANCE OF TEST 

There are many tasks in long term space operation which might 

be more easily accomplished if man can be used in extravehicular operation. 

These operations include assembly, maintenance, rescue, logistics, and 

crew transfer. Feasibility of the concept has already been established in 

tests on the ground and in aircraft. The limitations of these tests to date 

have missing one or several of the following: zero "G", long time, orbital 

mechanics effects, space environment, and attitude reference requirements. 

The Astronaut tasks to be performed inside the spacecraft will require a 

large free volume in which the motion of the astronaut will be free of 

obstructions. 

III. DESCRIPTION OF THE EXPERIMENT 

Each astronaut will perform various tasks such as replacement, 

connecting. and patching; using such tools as zerts and spunfits; while inside 

the spacecraft in a shirtsleeve environment and in a pressure suit with 

various levels of suit pressure, different tie-down techniques, and with 

and without the maneuvering unit attached. The other astronaut will 

observe and take pictures during the experiment. Performing this part of 

the experiment inside the spacecraft is safer and provides better monitoring 

capability without compromising objectives. 

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Exp No. P-6 EONFIDENTIALAt the conclusion of the above tests, one astronaut will enter an 

airlock with the integrated environmental control/maneuvering unit, attach 

a tetherline, and egress to space. The environmental control/maneuvering 

unit consists of a self contained environmental control subsystem for operation with the astronaut suit and a propulsion system for linear and angular 

control and stabilization. Locomotion tasks will be performed on the exterior 

of the spacecraft using various means such as hand holds, foot holds and 

magnets. The astronaut then tests the maneuvering unit first tethered and 

then untethered. The other astronaut monitors and observes the experiment. 

During all phases of the experiment information about the astronaut 

and system performance will be recorded. 

A. Configuration of Test Items 

The extravehicular experiment consists of four different categories: 

(1) Performance of astronaut tasks using various hand tools and tie-down 

methods on simulated spacecraft equipment, that require replacement, connecting, erection or patching familiar to primary experiment No. P-5: (2) Locomotion on spacecraft surface; (3) Locomotion away from spacecraft with the 

aid of a maneuvering propulsion unit; and (4) Measurement of astronaut performance and physiology, and suit integration. 

Category 1: 

A storage box for various tools and tie-down equipment is required. 

The experiment is performed at a panel containing tasks such as nuts, bolts, 

screws, tubes with various types of connections, etc. with enough free space 

in front of the panel to show motion of astronaut during attachment to the surface, 

performance of tasks and detachment. Performance of this part of the experiment inside the spacecraft can be done with more safety and more easily monitor( 

without compromising the experiment. 

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Category 2: CONFIDENTIAL-. 

A test area on the exterior of the spacecraft is required which 

contains various types of locomotion aids for both hands and feet such as 

bars, adhesive pads, and magnets. The area should be long enough to 

allow the astronaut to transverse at least eight feet. Inherent in this part 

of the experiment is the provision of an air lock, tetherline and individual 

environmental control system (part of the combined environmental control/ 

maneuvering unit). 

Category 3: 

A combined environmental control/maneuvering unit will be 

stored in the air lock. The unit is to be attached to the astronauts back 

with the control device attached to the front of the astronaut in a position 

for hand control in a pressurized suit. A tetherline is also required for 

this part of the experiment. 

Category 4: 

Provision will be made for the recording and storage of the 

astronaut performance and physiological information obtained during the 

parts of this experiment. Integration of the environmental control/maneuvering unit, the tetherline, tie-down equipment and physiological measure- 

: ment with the astronaut suit is required. 

B. Test Results 

The purpose of this experiment is to test the equipment and 

procedures which are required by man to perform extravehicular operations. 

The test sequence is such that the experiment is to be performed in a safe 

a manner as possible, with a build up and evaluation of successive steps 

before proceeding further. The astronaut is an integral part of the experiment 

--CONFIDENTIAL- SSTA 4 -9 

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Exp No. P.4 -CONFIDENTREtherefore the astronaut's opinion will be used to a large extent in carrying 

on the experiment. The information obtained in the performance of this 

experiment will provide knowledge of the procedures, tools, environmental 

control and maneuvering requirements for man's extravehicular activity. 

IV. SIMULATION 

Simulation work should be done preceding and concurrently with the 

flight program in order to determine what simulations best represent actual 

conditions, and what can be used for more refined studies of the requirements 

for actual performance of extravehicular activity missions which might be 

required. The procedures, tools and tie-down methods for the experiment 

astronaut tasks will be chosen after an extensive simulation program using 

air bearing platforms is accomplished. The maneuvering unit selected 

after Pre-phase 1 studies will be simulated and tested aboard the zero "G" 

aircraft before it is used in space. Simulation of the back unit donning and 

switchover from the spacecraft environmental control system techniques 

will be accomplished using the space suit configured for the MOL. 

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ATTACHMENT 1 

DESIGN CHARACTERISTICS OF TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED 

2. WEIGHT 275 lbs 

3. VOLUME 

a. Back unit 8 cu ft (3.2 x 2.5 x 1) 

b. Storage Box 1 cu ft 

c. Panel 1 cu ft 

d. Recording 2 cu ft 

4. POWER REQUIRED FROM MOL 

a. Communication 25 watts 

b. Telemetry Receiver 25 watts 

c. Light 50 watts 

d. Recorder 50 watts 

e. Total watts 150 

5. SPARES - To be determined 

6. TOOLS - To be determined (Battery, propellant, environmental control 

system (ECS) service and adjustment). 

7. HEAT OUTPUT - To be determined. 

8. STABILITY - No special MOL requirements - AMU to be determined. 

9. VIBRATION LIMIT - To be determined (T-utc launch). 

10. SHOCK LIMITS - To be determined (T-IIIC launch). 

11. HAZARDS - To be determined 

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Exp No. P-6 EONFIDENHAL12. TEMPERATURE LIMITATIONS - To be determined (pad to space 

environment). 

13. TyRE AND RANGE OF MEASUREMENTS 

a. Subsystem operation and status 

b. Control characteristics 

c. Physiological measurements and photographic coverage 

14. SPECIAL ENVIRONMENT REQUIREMENTS - To be determined 

(In space at MOL altitudes) 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS - 

To be determined 

16. EQUIPMENT OPERATING - To be determined 

17. EQUIPMENT LOCATION REQUIREMENTS 

a. Task panel and tools in MOL laboratory 

b. Maneuvering unit in air lock 

c. Surface locomotion aids in view of pointing and tracking scope 

18. spEorAza MOUNTING REQUIREMENTS 

a. View port between air lock and MOL laboratory. 

b. Mounts for cameras (top CLand side near task panel) 

c. Storage area for environmental/maneuvering unit accessible 

from air lock and to space. 

19. PRESSURE VESSELS Air lock 198 cu ft (4 x 5 xia. MOL) 

20. ELECTRO MAGNETIC INTERFERENCE - To be determined 

21. MAINTENANCE REQUIREMENTS 

a. Ground - To be determined 

b. Space - To be determined (Provide reuse capability). 

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ATTACHMENT 2 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape Recording of physiological measurements 

b. Film Photographic coverage of astronaut during experiment 

2. HANDLING - To be determined 

3. CALIBRATION - None 

4. JIGS AND FIXTURES - To be determined (autopilot and nozzle alignment) 

5. NUMBER OF LEADS FROM OUTSIDE TO DS IDE STATION - None 

6. SENSORS - None 

7. TRAINERS/SIMULATORS - The MOL and AMU provided for astronaut 

training will be required. 

8. INSTRUMENTATION - Display of physiological and system status 

information. 

9. RELATED SUPPORT EQUIPMENT 

a. Handling equipment - To be determined (for AMU) 

10. AGE 

a. Required for checkout of AMU and data subsystems 

11. ENVIRONMENTAL TEST EQUIPMENT 

a. Test equipment as normally used to perform environmental tests 

on space equipment (tests limited to environmental extremes as 

necessary to determine functional effects). 

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ATTACHMENT 3 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired) 

a. Altitude 150 - 250 naut mi. 

b. Inclination - less than 36°, that normally planned for MOL 

c. Epoch - No special requirement 

d. Ellipticity - Near zero 

2. PLANE CHANGE None 

3. ALTITUDE CHANGE - None 

4. TIME ON ORBIT - 30 days 

5. TEST DURATION - 3 hours 

6. TOTAL NUMBER OF TESTS - 3 

7. TEST FREQUENCY 

8. INTERVAL BETWEEN TESTS - 10 day interval 

9. CREW TASK LOADS - man hours: 1 hour tasks, 1/2 hour donning, 

1/2 hour surface locomotion, 1/2 hour maneuvering. 

10. CREW TASK 1.1(41,U.W.I - Each of the its under 9 may be done separately 

with each crew member taking a turn. 

11. FIELD OF VIEW REQUIREMENTS - Extravehicular astronaut should be in view 

of other astronaut either through port or using pointing and tracking 

scope. 

12. GROUND COATROL LIAISON DURATION - None 

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13. GROUND CONTROL LIAISON FREQUE/CY - None 

14. EXTERNAL TEST ITEMS - Tetherline and loccootion aids 

15. QUALIFICATION TEM (other than space) 

a. Ground - Functional and environmental performance of AMU 

b. Atmosphere - AMU in I(C-135 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT 

a. Set-up for astronaut tasks 

b. Perform tasks (one astronaut performing while other is photographing 

and observing. 

c. Enter air lock 

d. Perform donning tests 

e. Connect up environmental/maneuvering unit 

f. Depressurise air lock 

g. Go extravehicular 

h. Performance of surface locomotion tests 

i. Perform maneuvering tests 

j. Return to pressurised volume 

17. HANDLING PROCEDURES - Normal procedures for transporting and stowing 

AMU. Special precautions with AMU propellant may be required. 

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Exp No. P-6 -CONFIDENTIALIMAM= 4 

MANNING DESCRIPTION 

1. ASTRONAUTS: Two astronauts are required to perform the experiments. 

While one is performing the actual experiment the other is photographing and observing. Each astronaut will also take a turn at 

performing experiment. The astronaut experiment roles are: 

a. Perform work tasks. 

b. Don environmental control/maneuvering unit. 

c. Loccmote on exterior surface. 

d. Perform maneuvers free of spacecraft. 

Normal motor and perceptual skill levels are required for the execution of the orbital experiments. The astronaut should be average 

height, weight, and physique and capable of withstanding the high "G" 

launching environments and the weightlessness of space. He should be 

able to carry out his normal functions under temporary environmental 

extremes within human limitations and with the aid of normal life-support 

systems. There are no anticipated critical functions involved in the 

experiments. The astronauts will be required to stand and move about 

when performing the functions of (a) and (b) above and will be able to 

sit when performing (c), and (d) functions described above. Their tasks 

will be predetermined and scheduled according to instructions both onboard and on the ground and during pre-flight training. It is suggested 

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they they possess scientific training in the fields of optics, radar 

and dynamics. During and following MOL launch no human performance 

measures are required, but same measure of physiological and pycholow 

gical factors should be made for the following: 

(1) Errors and erratic behavior 

(2) Fatigue 

(3) Visibility and vision 

(4) Dexterity 

(5) Motion sickness 

Normal selection during astronaut training program:will suffice. 

Specific training with a simulator in lib/eh normal NOL and RHO controls and procedures must be learned are a requisite prior to final 

selection and flight. 

2. GROUND PERSONNEL 

There are no unique requirements for the training of ground personnel. 

Persons normally employed at ground stations during space flights v111 

provide adequate manning for the experiments. The number of men requiredwill be contingent upon the number of ground stations employed.. 

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C-ONFIDENTIAL--- 

Exp No. P -6 

ATTACHMENT 5 

COMMUNICATIONS AM) DATA HANDLING 

1. DATA HANDLING: Off-BOARD 

a. Functions to be measured - sensor and physiological data and 

human performance 

(1) Data rate/frequency response - to be determined 

Volume of Data 

Accuracy required 

(2) Form of data - output of transducer with time correlation 

(3) Onboard processing - human judgement 

(4) Communication requirements (to ground) - analog/digital -

raw/real time for extravehicular activity when over stations 

otherwise nearest dump point. 

b. Requirements for Processing and Analysis To be determined 

c. Permanent Data Records (for ay-down with recovery capsule) 

(1) Photographic 

(2) Magnetic tape recording 

2. COMMUNICATION REQUIREMENTS 

a. Data Transmission to ground - Progress of experiment and physiological 

data by TM. 

b. Two-way communication data feedback from around - Voice only' 

(1) Data processing on ground - Physiological for astronaut condition 

(2) Allowable delays - Routine unless critical conditions noted. 

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--CONFIDEtifht Exp No. P-6 

Ground Transmission (one center to another) - Test Progress 

Accuracies - To be determined 

Data Recording - No special requirement 

Security - Crypto - None 

Atch 5 (Cont'd) SSTA -1 -9 

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ATTACHMENT 6' 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMERT TIME - 32 months from Pre-Phase I go-ahead. to launch. 

2. FINAL MIN= MT DESIGN TIME - 15 months to completion of 

Phase I. 

3. • EWER OF GROUND OR FLIGHT TESTS ReQUIRED - Numerous ground. test, 

several KC-135 Test and. 3 MDL Tests. 

4. TYPE OF DEVELOPMENT MT IMIS 

a. Vacuum Chamber - Tools, adhesives and. AMU to hard vacuum. 

b. Shaker - Enviroramental simulation of T-IIIC & MOL. 

c. Thermal - Environmental simulation of T-rfic & MOL. 

d.. Acoustic - Ernrironmental simulation of T-IIIC & MOL. 

e. Simulators - 5 degree of freedom air bearing for all tasks 

f. Aircraft - KC-135 Zero G test of AM and other tests 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME - Cospatable with AMU development 

6. NUMBER OF TEST ARTICLES REWIRED FOR: 

a. Ground Test - One (qualification) 

b. Atmospheric Test in KC-135 - One 

c. Space Test - Two 

7. DATE AVAILABLE FOR TESTS - Qualification unit August 1966 and flight 

units February 1967. 

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8. CURRENT DEVELOPMENT STATUS 

a. RTD has been testing AMU's in KC-135's for two years and Gemini 

Experiments Program 631A is going into Phase II Hardware 

Procurement. 

b. Funds expended to date - About $1 million Program 631A completion 

estimated to $4. million 

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-C-ONFIDENAL--- Experiment No. P-7 

REMOTE MANEUVERING UNIT 

I. TEST OBJECTIVE 

The objective of this experiment is to determine man's capability to 

control a maneuvering unit remotely. In military operations it would be 

desirable to be able to control a maneuvering unit remotely as an aid to 

inspection, damage assessment, maintenance, logistics and rescue. 

II. IMPORTANCE OF TEST 

A remote maneuvering unit is important for future manned inspection 

missions. Such a controlled maneuvering unit could be used to approach 

and circumnavigate a target while the astronaut remains at a safe distance 

to prevent harm from an active defense or booby trapped target. In addition, 

a remote maneuvering unit could be used to carry sensors for a close inspection. In a logistics operation an unmanned spacecraft could be placed in 

orbit near the MOL and then rendezvoused with the MOL by remote control. 

In a rescue operation the system could be used in a manner similar to that 

of throwing a life bouy to a drowning person and hauling him in with the 

attached rope. 

III. DESCRIPTION OF THE EXPERIMENT 

a. The experiment equipment consists of the maneuvering unit, the 

associated control system necessary to remotely maneuver the unit, the 

required monitoring equipment and appropriate target. The major components 

of the maneuvering unit are: propulsion and attitude control subsystem; 

stabilization and control unit consisting of rate gyros and control logic 

computer; a command and data link which includes a TV transmission unit 

command,• communications, and data telemetry; sensor unit consisting of 

a TV camera. 

---0014FIDENTIAL- SSTA-1 -9 

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Exp No. P-7 CONFIDENTIAL 

The major parts of the MOL control panel are: hand controllers 

(linear and angular), TV monitor, radar range and range rate readings from 

RMU to target. The monitoring equipment consists of equipment to record 

TV, radar, rate gyro output, command data, etc. The radar must be capable 

of monitoring both the target and the RMU. The target will be a passive inflatable structure with preselected surface characteristics and markings. 

b. Vehicle Requirements Data 

1. Power - 500 watts 

2. Stabilization - required 

3. Volume (a) RMU and target approximately 12 cu ft. 

(b) Console and recording equipment approximately 

4 cu ft. 

4. Weight (a) RMU and target 300 lbs. 

(b) Console and reading equipment 50 lbs. 

5. Aperature (view ports) 

6. Miscellaneous (a) Storage and ejection compartment direct 

to space for both target and maneuvering 

unit. 

(b) Console placed so that the RMU can also 

be viewed through port, while being 

controlled by the astronaut. 

c. Teat Procedure 

A target is deployed from the MOL vehicle by ejecting the target vehicle 

at a small Li V (several feet per second) such that it will cross the MOL orbit at 

an approximate distance of 5 naut mi. The MOL vehicle is maneuvered such 

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that the target will remain at a constant distance for the test duration. The 

RMU is ejected so that the MOL is in the field-of-view of the RMU television 

camera. After the RMU reaches a distance of about 50 feet from the MOL, 

the propulsion system is activated and the astronaut assumes control. The 

RMU will be maneuvered around the MOL, at a safe distance, with and 

without direct viewing. All the equipment will be checked out for proper 

functioning (e. g. , TV, radar, and control in all degrees of freedom). After 

checkout,' the RMU is oriented to acquire the target and given a AV necessary 

to place it near the target. At the appropriate time the astronaut will start 

corrective maneuvers such that the RMU arrives in the vicinity of the target 

with a small relative velocity. The other astronaut will monitor the RMU 

and target on the MOL radar. 

Attempts to rendezvous the RMU with the target will be made from 

a distance of 500 feet by using TV alone, radar alone, and combination of 

TV and radar. 

The RMU will be maneuvered around the target in order to view 

it from all aspects and inspect the target surface markings. The relative 

distance between the RMU and target will be controlled as accurately as 

possible. At the conclusion of the test the RMU will be returned to MOL for 

recovery and reuse. 

IV. PARTICIPATING GOVERNMENT AGENCIES 

Sponsor: RTD (Aeropropulsion) 

V. ADDITIONAL REQUIREMENTS 

a. Special Security - to be determined. 

b. Simulation - The basic attitude control system will be checked out 

in a five degree of freedom airbearing simulator and the zero "G" aircraft. 

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Exp No. P-7 -CONFIDENfitklSince the maximum length of control time is 30 seconds in the Zero "G" 

aircraft and the length of the cabin is limited, translation control simulation 

would be limited. Also, firing of some higher performance propellants in 

the aircraft would be undesirable. Procedures for the rendezvous of the RMU 

with the target would be determined by running digital and/or analog simulated 

missions. 

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This dwament cancan information affecting the national defense of the linked Paws within the meaning of the Espionage laws. 

Tine U

usc. Soca' 793 and 794. the 

. S

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--CONFIDENIAL-- 

ATTACHMENT 1 

Exp No. P-7 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED 

2. WEIGHT: 300 lbs 

3. VOLUME: 6.25 cu ft RMU, Control Panel 1.0 cu ft, Target 1.0 cu ft, 

MOL Radar 2.0 cu ft. Others to be determined. 

CRITICAL DIMENSIONS - SHAPES - RMU(2. 5 ft x 2. 5 ft x 1 ft) Others 

to be determined. 

4. POWER REQUIRED FROM MOL: 

Command Transmitter 50 

TV Receiver 50 

Telemetry Receiver 25 

Displays 25 

Recorders 50 

MOL Radar 100 

300 W 

5. SPARES - to be determined 

6. TOOLS - to be determined (Battery Et propellant servicing; system 

adjustment. 

7. HEAT OUTPUT - To be determined 

8. STABILITY 

a. .1 degree @ . 01°/sec for launch of RMU and target 

b. Moving parts - None 

9. VIBRATION LIMITS - To be determined (T-IIIC Launch environment) 

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10. SHOCK SHOCK LIMITS - To be determined (T-IIIC Launch Environment) 

11. HAZARDS (fire, explosion, electrical, toxics, other) - To be determined 

12. TEMPERATURE LIMITATIONS - To be determined (pad limits to 

outer space). 

13. TYPE AND RANGE OF MEASUREMENT (definition of parameters to 

be measured while test is underway). 

a. Attitude and rates in all axis. 

b. Subsystems (power, autopilot, propellant) condition status. 

c. Sensor performance and condition status. 

d. Photos of TV and radar display. 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS - To be determined 

(in space at MOL altitudes). 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS - To be 

determined - (RMU must be able to approach target within 20 ft.) 

16. EQUIPMENT OPERATING CYCLE 

R/C Transmitter T/14 & TV Receiver 

Frequency 434 me/sec 537 

Time Duration 54 min 54 min 

17. EQUIPMENT LOCATION REQUIREMENTS - Controls & displays in MOL 

Laboratory, RMU in air lock, electronic equipment in unpressurized 

volume of MOL. 

18. SPECIAL MOUNTINGS REQUIREMENTS 

Apertures - View port required 

Antennae - 3 required (command transmitter, T/M & TV receiver and 

MOL radar). 

Bracketry - To hold RMU & target prior to launch & recovery 

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19, PRESSURE PRESSURE VESSELS - RMU stowed in air lock. 

20. ELECTRO MAGNETIC INTERFERENCE - To be determined 

21. MAINTENANCE REQUIREMENTS 

Ground - To be determined 

Space - To be determined - (replace batteries & refill propellant). 

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Exp No. P-7 -60NFIDENflitATTACHMENT 2 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape: Magnetic tape recordings will be made of the radar photoelectric and TV information sensed both in the MOL and by the 

ground stations. 

b. Film: Photographic recordings will be made by the MOL crew 

of the RMU maneuvering. 

c. Human: Observations will be recorded both on magnetic tape 

and on paper by MOL and ground stations crews. 

2. HANDLING 

a. The experimental target will be stored in the MOL in suitable 

containers. 

3. CALIBRATION: 

a. Calibration of test equipment or test support equipment will be 

required of those calibrations normal to the tracking radar, and TV. 

4. JIGS AND FIXTURES - To be determined (boresighting TV, radar, autopilot and nozzle alignment). 

5. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION: 

To be determined (RMU and target deployment, antenna coax, etc.) 

6. SENSORS 

a. A tracking radar system yielding angular orientation target signature and range information will be desired in the MOL. A system 

at the ground station will perform similar tasks. 

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b. A TV camera on the RMU will provide about 600 line definition 

at about 25 frames per second. The display on MOL is convenient 

to the control panel. 

7. TRAINERS/SIMULATORS 

a. The MOL and RMU simulators provided for astronaut training 

will be required. 

8. INSTRUMENTATION 

a. Sequential frame or motion picture camera with suitable controls 

for varying the exposure duration, exposure setting, and focal 

length, and the camera position against the celestial background. 

b. A radar tracking device including passive-tracking and active 

tracking features. 

c. Recording equipment and associated amplifiers. 

d. Indicators may display the radar information in the MOL. 

e. Other indicators may be employed to indicate the quality of 

operation of the other sensors. 

f. Such indicators already may be available as standard MOL 

instrumentation. 

9. RELATED•SUPPORT EQUIPMENT 

a. Targets: 10 ft diameter expandable about 40 lbs. 

b. Ground Stations: Ground stations already engaged in tracking the 

MOL will be employed to track and observe the decoys. 

c. Tracking equipment already engaged in MOL tracking at the ground 

stations will be employed. 

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Exp No. P-7 --CONFIDENTIALd. Handling Equipment: Special-purpose handling equipment will 

be required for folding the targets. 

10. AGE 

Most of the following equipment and facilities are anticipated as 

already being a part of the MOL program:. 

a. Equipment for checkout of control system, power, TV & radar. 

b. Tracking SPADATS network for tracking of the test from earth. 

c. Optical tracking facilities including photographic capabilities. 

d. Recording equipment and associated amplifiers. 

11. ENVIRONMENTAL TEST EQUIPMENT 

Test equipment as normally used to perform environmental tests on 

space equipment will be required. Such tests will check limited 

environmental extremes as necessary to determine functional effects 

on target system performance. 

12. FACILITIES 

a. The MOL with its RMU will provide the orbital facilities for 

the target equipment and its related support equipment. 

b. The ground stations will provide the facilities for ground-conducted 

observation of the tests. 

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ATTACHMENT 3 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS 

a. Altitude: 150 - 250 naut mi. 

b. Inclination: Less than 36°, use that normally planned for the MOL. 

c. Epoch: No special epoch is applicable. 

d. Ellipticity: A circular orbit is preferable for early experiments; 

the effects of increasingly more elliptical orbits may be studied 

in succeeding experiments. 

2. PLANE CHANGE: No change 

3. ALTITUDE CHANGE: No change in altitude will be.effected during 

any specific test; tests may be conducted at different altitudes. 

4. TIME ON ORBIT: 30 days 

5. TEST DURATION: To be determined 

6. TOTAL NUMBER OF TESTS: To be determined (dependent on targets 

carried and ability to reservice the RMU). 

7. TEST FREQUENCY: To be determined 

8. INTERVAL BETWEEN TESTS: To be determined 

9. CREW TEST LOADS 

a. Experiment preparation & deployment: 1 man for 1/2 hour. 

b. Experiment Performance: 1 man for operation and 1 man parttime for observation for duration of test. 

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10. CREW TASK FREQUENCY 

Two astronauts will alternate between individual reciprocating periods 

of activity and rest as required. They may be performing interim 

duties between periodic intervals of observation if continuous observation becomes needless. 

11. FIELD-OF-VIEW REQUIREMENTS: To be determined (RMU TV 

camera to have two field-of-view settings). 

12. GROUND CONTROL LIAISON DURATION: As necessary when over 

tracking stations. 

13. GROUND CONTROL LIAISON FREQUENCY 

A specific ground station will observe a test so long as the MOL and 

the target can be tracked. Tracking will be passed from station 

to station. 

14. EXTERNAL TEST ITEMS 

a. Launched from MOL: RMU and targets. 

15. QUALIFICATION TESTS: 

a. Ground: Functional and environmental performance of RMU 

and targets to be determined. 

b. Atmosphere: RMU in KC-135 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT: 

a. Coordinate with ground stations and activate all sensors and 

recording devices. 

b. Eject target. 

c. Release and maneuver RMU. 

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d. Observe, Observe, track, and record data. 

e. Return RMU and recover 

f. Repeat experiment. (May require reservicing.) 

17. HANDLING PROCEDURES: 

Normal procedures for transporting and stowing the targets packages 

will be sufficient. Special precautions with RMU propellant may be 

required. 

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ATTACHMENT 4 

MANNING DESCRIPTION 

1. ASTRONAUTS: Two technicians are required to perform the experiments. Their roles are to: 

a. Deploy target and RMU. 

b. Maneuver MOL and RMU. 

c. Observe the experiment and record results. 

d. Prepare raw data for subsequent transmittal to ground stations. 

Normal motor and perceptual skill levels are required for the execution of the orbital experiments. The astronaut should be average 

height, weight, and physique and capable of withstanding the high "G" 

launching environments and the weightlessness of space. He should be 

able to carry out his normal functions under temporary environmental 

extremes within human limitations and with the aid of normal life-support 

systems. There are no anticipated critical functions involved in the 

experiments. The astronauts will be required to stand and move about 

when performing the functions of (a) and (b) above and will be able to 

sit when performing (c), and (d) functions described above. Their tasks 

will be predetermined and scheduled according to instructions both 

on-board and on the ground and during pre-flight training. It is 

suggested that they possess scientific training in the fields of optics, 

radar and dynamics. During and following MOL launch no human 

performance measures are required, but some measure of physiological 

and psychological factors should be made for the following: 

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(1) Errors and erratic behavior 

(2) Fatigue 

(3) Visibility and vision 

(4) Dexterity 

(5) Motion sickness 

Normal selection during astronaut training program will suffice. 

Specific training with a simulator in which normal MOL and RMU controls 

and procedures must be learned are a requisite prior to final selection 

and flight. 

2. GROUND PERSONNEL 

There are no unique requirements for the training of ground personnel . 

Persons normally employed at ground stations during space flights will 

provide adequate manning for the experiments. The number of men 

required will be contingent upon the number of ground stations employed. 

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ATTACHMENT 5 

CCMMUNICATIONS AND DATA HANDLING 

1. DATA HANDLING: ON-BOARD 

a. Functions to be measured - on-board radar, and RMU TV and radar 

data. Subsystem status information time correlated. 

b. Requirements for Processing and Analysis - To be determined. 

c. Permanent Data Records 

(1) Photographic 

(2) Magnetic Tape 

2. COMMUNICATION REWIREMENTS 

a. Data transmission to ground - None 

b. Two-way communication data feedback from ground - Voice only routine. 

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ATEACHMENT 6 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME - 32 months from Pre-Phase I go-ahead to launch. 

2. FINAL DEFINITIVE TEST DESIGN TIME - 15 months to completion of Phase I 

3. NUMHER OF GRCURD OR FLIGHT TESTS REQUIRED - Numerous ground test, several 

KC-135 Test and 2 NUL Tests. 

1. TYPE OF DEVELOPMENT TEST ITEMS 

a. Vacuum Chamber - Tools, adhesives and AMU to hard vacuum 

b. Shaker - Environmental Simulation of T-IIIC and NOL 

c. Thermal - Environmental Simulation of T-IIIC and MOL 

d. Acoustic - Environmental Simulation of T-IIIC and ))L 

e. Simulators - 5 degree of freedom 

f. Aircraft - 1C-135 sero G Test of RKU. 

5. SUPPORT =mew DEVELOII(ET Tne - Compatible with AMU Developmen$ 

6. HUNGER OF TEST ARTICLYS REQUIRED FOR: 

a. Ground Test - One (qualification) 

b. Atmospheric Test in 1CC-135 - One 

c. Space Teat - Two 

7. DATE AVAILABLE FOR TESTS - Qualification Unit August 1966 and Flight Units 

February 1967. 

8. CURRENT DEVELCTMENT STATUS 

a. RED has been testing RMU's in KC-135's for tvo years and Gemini 

Experiments Program 631A is going into Phase II Hardware procurement. 

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Attachment 6 Page 2 

b. Funds expended to date - About40.4Million, Program 631A completions 

estimated at $4.0 Million. 

c. Ground transmission (one center to another) - Test Progress 

d. Accuracies - To be determined 

e. Data Recording - No special requirement 

t. Security - Crypto - None 

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--GONFIDEPA6 Experiment P-8 

AUTONOMOUS NAVIGATION 

I. TEST OBJECTIVE. 

The objective of the MOL Experiment on Autonomous Navigation is 

to evaluate the ability of man to act as a spacecraft navigator. The evaluation will be conducted by analyzing the performance of members of theMOL 

crew in the operation of data gathering, processing and display equipment 

while pursuing the experiment goal. 

IL IMPORTANCE OF TEST 

A basic requirement to be satisfied in the achievement of operational 

autonomy is the ability to determine and predict orbital position independently of ground based facilities. 

A variety of spacecraft navigation techniques have been proposed 

employing horizon scanners, star trackers, terrestrial sightings and, in 

some cases, man. The introduction of man into the spacecraft navigation 

system tends to reduce the mechanical complexity of the system and renders 

it more flexible through the exercise of human judgement. Terrestrial 

landmarks and stars may be acquired and tracked with a minimum of automated devices. The most efficient combinations of equipment and data 

collection and reduction methods may be selected to meet the demands of 

particular situations. 

The experiment on autonomous navigation proposed for incorporation 

on the MOL vehicle brings together the unique capabilities of man and the 

capabilities inherent in a variety of sophisticated navigation aids for the 

purpose of performing extensive experimentation in the area of manned space 

navigation. The experience gained in the development and/or operation of 

such guidance and navigation systems as present aboard the Gemini and 

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Apollo and the development of the Standardized Space Guidance System 

will be drawn on extensively. In addition, much use will be made of ground 

and aircraft simulation facilities during the development of the experiment 

techniques, procedure and equipment. 

Space-borne testing of the navigation experiments is of great importance. While factors such as man-equipment relationship and duty cycle, 

astronaut response to sensor outputs, effect of training on astronaut performance, and the effect of astronaut, instrumentation and orbit model 

errors on navigation accuracy may be simulated through the use of terrestrially based facilities, a true understanding and appreciation of the above 

factors may be gained only through testing aboard a manned orbital vehicle. 

The MOL is ideally suited for such a task as it is the first orbital 

vehicle designed for the purpose of exploring the man-machine relationship 

and investigating the utility of man as an integral component of military 

space activity. 

III. DESCRIPTION OF THE EXPERIMENT 

To provide maximum experiment flexibility, the MOL experiment on 

Autonomous Navigation is to be configured about a basic set of equipment, 

the major components of which are a pointing and tracking scope (PTS), 

a set of horizon scanners, a precision time reference system, two automatic star trackers; a re-programable digital computer, and various prepared 

navigational data. All of the above equipment, with the exception of the star 

trackers, will be available as components of the MOL or associated experiments. 

A variety of navigation techniques will be developed employing the 

above equipment. 

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The astronaut will utilize information provided by star sightings, 

terrestrial landmarks, horizon scanners and inertial measuring units 

to determine the orbital orientation and position of the MOL. Orbital 

corrections will be predicted and executed on the basis of navigational 

data generated by the on-board systems. The accuracy of the orbit prediction, and corrections, will be established by the on-board comparison 

of predicted and actual orbit state. The experiment evaluation would be 

accomplished by comparing recorded flight data with ground track information. 

The astronaut(s) would serve as spacecraft navigator(s) during the 

course of the experiment. The astronaut(s) would acquire terrestrial 

and/or celestial references as required by the experiment to determine 

the spacecraft orbital position and would select the experiment mode of 

operation and requisite displays. They would provide data to the computation system and monitor its operation, interpret the forthcoming navigational data, and determine and execute the orbital corrections required to 

establish a specific, pre-selected orbit. 

It is required of any orbital navigation system which intends to establish the position of the spacecraft in terms of geocentric coordinates that 

measurements be made of inertial and terrestrial references as functions 

of time. In practice, the inertial coordinate frame is established by the 

spaceCraft inertial platform which is periodically updated by celestial 

sightings; in some instances, celestial sightings, with star trackers, are 

utilized to obtain the inertial reference without recourse to a true inertial 

platform. Terrestrial references are obtained through measurements of 

the earth's horizon or the sighting of landmarks. Data filtering and smoothing techniques are applied to the above measurements, which are often 

redundant, and the resulting information is utilized to obtain the spacecraft 

orbital elements in geocentric coordinates thereby establishing the position 

of the spacecraft relative to the earth. 

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An Experiment in orbital navigation, typical of the above description, may be conducted utilizing the following equipment components and 

man. 

1. Inertial Measuring Unit (IMU) 

Typically, a combination of gimballed gyros and accelerometers. 

2. Star Trackers 

An optical system sensitive to the stars emissions which, when 

positioned, will track a given star by virtue of its spectral characteristics. 

3. Pointing and Tracking Scope (PTS) 

An optical sighting system of variable magnification which is coupled 

to the IMU for measurement of the line-of sight in the inertial coordinate frame. 

4. Time Reference System (TRS) 

An accurate clock. 

5. Spacecraft Displays 

Equipment which will inform the operator of the spacecraft position 

relative to the earth, the spacecraft orientation in inertial space, absolute 

and relative time, etc. , and which will allow the operator to monitor and 

control the operation of the system. 

6. Spacecraft Computational Facilities 

A computer, with sufficient capacity and memory, will filter and 

correlate measurement data, store celestial and terrestrial reference positions as functions of time, store astrodynamic constants and models and 

monitor the peripheral data gathering equipment. Additional equipment related to the computation system (e. g. , Manual Data Insertion Unit) may be 

required. 

7. Adequate Data Recording and/or Telemetry Capacity 

Data on measurements and operation will be obtained from the 

spacecraft and the ground tracking network to allow post-flight analysis of 

the experiment. 

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The experiment will utilize the above equipment to establish an inertial coordinate frame (IMU with star trackers) and obtain earth references by sighting known terrestrial landmarks (PTS). As an example of 

experiment variations which would be performed, the spacecraft horizon 

scanners could be used to establish a terrestrial reference in lieu of the 

PTS. 

The determination of the MOL orbital position would be accomplished 

through the use of the mechanized elements of the navigation system by 

operator. At a suitable point in the MOL mission profile, the astronaut 

would prepare the computer for the experiment by positioning required 

programs and navigational data through the selection of a computer operating 

mode. Requisite equipment, such as the IMU, would be activated. The 

astronaut would select two stars from the catalog available to him, enter 

their codes into the computer and acquire them with the star trackers. Once 

the stars were within the trackers field-of-view, the star trackers, would 

be allowed to track,the stars automatically, The trackers, in conjunction 

with the IMU, would establish the inertial coordinate frame. Similarly, 

a terrestrial landmark appropriate to that phase of the MOL mission would 

be selected and its code entered into the computer. The astronaut would 

sight the landmark with the PTS and register a number of readings into the 

computer. The data provided by the star trackers and PTS would be used 

by the mathematical orbit model to determine the spacecraft's orbital position. This positional information would be displayed to the astronaut in 

terms of equivalent earth latitude and longitude and, perhaps, pictorially 

through the use of a simulated ground trace. The operation described above 

would consist of a course, preliminary orbit determination scheme, based 

on relatively few measurements, to establish the initiation point for a refined orbit determination scheme utilizing greater quantities of measure• 

ment data as they would become available. 

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Exp No. P-8 --6ONFIBEfNtkThe second portion of the experiment would call for increased astronaut participation. The astronaut would introduce specific orbit perturbations into the computer and predict, through computation, the effect on the 

MOL orbit. From displays giving the spacecraft orientation, the astronaut 

would establish the desired spacecraft attitude and execute the orbit perturbations mentioned above through the application of incremental velocity. 

The orbit determination scheme described earlier would then be repeated 

and the resulting orbit compared with that predicted. 

A typical navigation problem would be the over-flight of a pre-selected 

point on the earth. The desired accuracy of the over-flight would be dependent on the mission to be performed over the terrestrial point. If a sensor 

such as the PTS was to be used for viewing purposes, the over-flight accuracy would be dependent on the field-of-view of the PTS. In such an instance 

an over-flight deviation on the order of 10 miles may be tolerable. Once 

the coordinates of the terrestrial point and an acceptable deviation were fed 

into the computer through the Manual Data Insertion Unit', the computer 

would compare the projected ground trace of the established MOL orbit to 

the location of the terrestrial point. Adjustments to the established MOL 

orbit, intterms of orbit inclination and/or period, may be required. If 

such was the case, a number of potential orbit adjustments would be suggested 

by the computer. The astronaut would select the most suitable orbit adjustment, in keeping with time and propulsive energy requirements, and execute 

the correction at the appropriate time. The resulting orbit would be determined with the ,on-board instrumentation and compared with the predicted 

orbit. If required, a portion of the above procedure would be repeated. 

In all instances, the flight data obtained from on-board instruments 

and ground track would be recorded for subsequent post-flight analysis. 

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IV. EXPERIMENT FUNDING 

Based on estimated provided for the 631A Program, the total 

funding required for the MOL Experiment on Autonomous Navigation 

would approach ten million dollars. The following breakdown of costs 

would be typical: 

V. PARTICIPATING AGENCIES 

Sponsor: AFSSD/Aerospa.ce 

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COST 

ITEM (millions) 

1. Experiment development 

fabrication 6. 5 

2. Installation, integration 

and support 2. 5 

3. Simulation & Misc. 1.0 
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Exp No. P-8 CONFIDENTIAL 

ATTACHMENT A 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. Equipment to be Tested (Used in the Test): 

IMU (MOL equipment) 

Stellar Trackers (Experiment Equipment) 

Pointing and Tracking Scope (MOL Equipment) 

Horizon Scanner System (MOL Equipment) 

Time Reference System (MOL Equipment) 

Spacecraft Navigational Display System (Experiment Equipment) 

Spacecraft Computer (re-programable) (MOL Equipment) 

Data Recording and Telemetry System (MOL Equipment) 

2. Weight: 65 lbs (approx.) 

3. Volume: 7 ft3 (approx.) 

4. Power: 

a. Continuous: 200 watts 

b. Stand-by: 50 watts 

c. Average operating: 200 watts 

d.• Peak: 225 watts to 250 watts 

e. Duty cycle: Not known 

5. Spares: 

No estimate available at present 

6. Tools 

No estimate available at present 

7. Heat Output: 200 watts 

8. Stability: (At least 1 degree, .25 deg/sec) 

9. Vibration Limits: Titan III spectrum 

10. Shock Limits: Titan III spectrum 

11. Hazards: Negligible 

12. Temperature Limitations: Undefined at present 

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13. Type and Range of Measurement: Angles; 0° to 90° 

14. Special Environmental Requirements: Those of astronaut for 

experiment equipment. 

15. Orientation and Position Accuracy Requirements: Variable orientation 

for earth/star sightings with a pointing accuracy of approximately 1. 0°. 

16. Equipment Operating Cycle: Continuous operation from min of 1.0 to 

max. of 8.0 hours. 

17. Equipment Location Requirements: Star tracker on "upper" section 

of MOL to view stars. 

18. Special Mounting Requirements: Apertures: None Booms: None 

Windows: Optically flat windows for star tracker and pointing/tracking 

telescope, Bracketry: None, External: Body mounting of horizon 

scanners: 

19. Pressure Vessels: None 

20. " Electromagnetic Interference: None 

21. Maintenance Requirements: None anticipated at present. 

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ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. Recording Media: Tape; possible photograph star backgrounds for 

post-flight analysis. 

2. Handling: None 

3. Packaging: No special requirements. 

4. Calibration: Alignment and calibration of star trackers (PTS, horizon 

scanners and inertial platform) 

5. Jigs and Fixtures: Alignment 

6. Number of Leads from Outside to Inside 

Station: Horizon scanner leads 

7. Sensors: Horizon scanners; pointing/tracking telescope, stellar trackers 

8. Trainers/Simulators: Undefined at present 

9. Instrumentation: Navigation data display; individual instruments not 

defined at present. 

10. Related Support Equipment 

a. Targets: None 

b. Ground stations: Earth landmarks 

c. Tiacking: Existing tracking network 

d. Handling Equipment: None 

11. AGE: Check-out for star trackers, navigation displays (horizon scanners) 

12. Environmental Test Equipment: Existing and low vacuum 

13. Facilities: No estimate available at present 

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ATTACHMENT C 

TEST OPERATING CHARACTERISTICS 

1. Orbital Parameters: 

a. Altitude: 150 to 250 naut mi 

b. Inclination: Less than 36° 

c. Eccentricity: Zero 

2. Plane Change: Not defined at present 

3. Altitude Change: Not defined at present 

4. Time on Orbit: Up to 30 days 

5. Test Duration: Variable, 1 to 10 orbits 

6. Total Number of Tests: Approximately 50 

7. Test Frequency: Not defined at present 

8. Interval between Tests: Up to 1 day 

9. Crew Task Loads: Approximately 200 man-hours 

10. Crew Task Frequency: Not defined at present 

11. Field-of-view Requirements: + 180° 

12. Ground Control Liaison Duration: None 

13. Ground Control Liaison Frequency: None 

14. External Test Items: None 

15. Qualification Tests (Other than space): Not defined at present 

16. Sequence of Events as they Occur During Flight 

a. Coarse alignment 

b. Data gathering 

c. Data processing and smoothing 

d. Readout of autonomous navigator 

e. Interpretation of results. 

17. Handling Procedures: Not critical 

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ATTACHMENT E 

MANNING DESCRIPTION 

1. Astronauts 

a. Number Required; One (maximum of two) 

(1) Man's function 

(a) As part of test: Coarse Alignment; initial set-up; data 

interpretation. 

(b) As technician conducting test: Monitor all functions. 

b. Crew Skill Requirements: Highly knowledeable in navigation 

theory and practice. 

c. Manpower Profile (Per test) 

One man continuously for up to 2 hours. 

d. Critical Functions: Control of spacecraft 

e: Work Positions: Seated at console 

f. Time Controlled Tasks: Thrusting of spacecraft engines 

g. Human Performance Measures: Not critical 

h. Physiological and Psychological Measures: Not critical 

i. Selection Factors: Not critical. 

j. Training Requirements: Navigation theory and practice. 

2. Ground Personnel: Chcck-out of experiment and spacecraft equipment. 

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ATTACHMENT F 

COMMUNICATIONS AND DATA HANDLING 

I. Data Handling: On-Board 

a. Functions to be measured: Angles - optical and horizon scanner 

data. 

(1) Data rate/frequency response) ) 

Volume of data ) - not defined at present 

Accuracy required 

(2) Form of data: Digital and analog 

"(3) On-board processing: Computer 

(4) Communication requirements (to ground): Ground tracking 

information sent to vehicle for comparison purposes. 

b. Requirements for Processing and Analysis 

(1) Data reduction: Comparison of predicted to determined position 

(2) Computation: On-board computer 

(3) Evaluation and Interpretation: Astronaut function 

(4) Pictorial Analysis: None 

(5) Real-time monitoring: Continous during experiment 

(6) Displays: All navigational information 

c. Permanent Data Records (for fly-down in a recovery capsule): None 

2, Communication Requirements 

a. Data transmission to ground: Not defined at present 

b. Two-way communication data feedback from ground: Not defined 

at present. 

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ATTACHMENT G 

DEVELOPMENT CHARACTERISTICS 

All items, with the exception of star tracking and display equipment, 

would be developed as part of the MOL system. 

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Experiment No. P-9 

NEGATION AND DAMAGE ASSESSMENT 

OBJECTIVE 

The objective of this test is to evaluate man's ability in carrying out 

a negation and damage assessment function. 

IMPORTANCE OF EXPERIMENT 

The objectives of satellite inspectiOn are to gain intelligence, identify 

the mission-of unknown satellites, and negate satellites determined to be hostile. 

The object of negation is to incapacitate or physically destroy the satellite as 

required. The satellite inspector could contain its own negation equipment and 

be directed to carry out the negation following an inspection mission. It is 

presently anticipated that negation missiles would use non-nuclear warheads 

and that the missiles could be guided, unguided, or carried in a,guided-unguided 

mix. 

The potential of placing weapons in either near or far earth orbits 

is closely related to the reliability and cost-effectiveness such systems can 

attain in the future. The possibility of an enemy using this type of system 

cannot be fully substantiated at the present time. Investigation of the basic 

techniques involved in storing weapons in space and their precision delivery 

are currently underway. Thus, it is necessary to determine the advisability 

of developing counter systems based on requirements, capabilities and limitations 

of orbital negation systems and the contribution that an astronaut can make 

to such a military system. These tests will also contribute to the considerations for our own possible delivery systems in reducing vulnerability of our 

retaliatory forces. 

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The other important application of negation is to dell defense missions 

when it has been determined that an inspection or surveillance satellite is 

under actual or imminent hostile attack. It could be expected that this 

encounter would not necessarily be from a rendezvous situation, but involve 

greater velocities and crossing angles. Thus, the most appropriate weapon 

might be an automatic tracking missile with a proximity fuse and shrapnel or 

pellets. However, the development of the negation system would follow the 

same lines as above and this experiment would indicate the capacity of an 

astronaut to aim, fire and successfully destroy an attack missile within a 

reasonable extrapolation of the range and closing velocities employed in the 

experiment. 

BACKGROUND 

The 706 Program has been conducting studies of negation devices to be 

launched from a satellite inspector to destroy a target satellite. Studies 

conducted included four contracted efforts prior to Phase 0 with General 

D)nemics/Pomona, Aerojet-General, Raytheon, and Hughes. These studies considered 

the problem f unmanned operations at very short ranges. Additionally, in-house 

Jz.udies are xiderway which are also considering both guided and unguided systems 

:or unmanned and manned/unmanned operations at various ranges. These studies 

nave been supported by information from the Army (Picatinny Arsenal) and R&TD 

Detachment 4 at Eglin APB, and are scheduled to be completed in June 1964.. 

These 706 studies have provided sufficient preliminary information and trends 

• to begin a pre-Phase I in-house experiment definition. 

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Studies have been conducted by the R&TD Detachment 4 and the Avionics 

Laboratory at Wright-Patterson AFB on various aspects of weapon characteristics, 

launch and guidance problems, effectiveness against different targets, and kill 

probability, although these studies have concentrated on other than a spaceto-space mission. 

Analysis of the above studies indicates that a penetration type weapon 

gives greatest assurance of complete destruction of a bomb warhead. A destruct 

charge would probably be preceded by a shaped charge in order to penetrate into 

the weapon interior through any armor which might be used. Pellets and shrapnel 

might be effective against softer targets, and would reduce the accuracy requiremf 

for guided missiles and increase the effective range for unguided missiles. 

For the guided missiles, consideration will be given to beam rider, radio, 

wire,visual, and IR guidance systems, and reaction jet attitude control. Capabil 

to penetrate a specific desired location on the target will be determined. 

While the effective range of unguided missiles is considerably less because 

of accuracy requirements and dispersion, they do allow reduction in the complexiv, 

of the missile and on-board checkout equipment with the higher probability of 

successful operation. 

DESCRIPTION OF EXPERIMENT 

Equipment; A console would be located convenient to the pointing and 

tracking scope that would allow the astronaut to control the experiment while 

observing the target. Switches and controls would be provided that would deploy 

the target which would then have a sequenced expansion. 

The target to be employed for the negation and damage assessment experimenwill be an expandable structure approximately 10 ft in diameter that will be 

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deployed from the MOL at a very low velocity, about 1 ft per sec. Initial tests 

will have previously been made to determine the desired coating and surface 

characteristics. Results of R8dD lab tests indicate the unexpanded target should 

weigh about 110 pounds and occupy about two cu ft when stored. It may be necessary 

to install a low powered C band battery operated radar beacon in order to 

accurately determine the range and range rate for complete evaluation of the tests. 

Also, since some momentum, will be imparted to the target when struck by the 

negation missile a code signal could be added to the beacon in order to denote 

a hit. This would allow knowledge of a hit if the pointing and tracking scope 

is unable to assess the damage and it is not desired to expend the AV of the MOL 

to effect a close rendezvous with the target. 

The experiment control console would also contain the arming switches and 

firing switches for launching the missiles, as well as displays indicating the 

condition of the missile system. An on-board system very similar to that used 

for aircraft launched GAR's would be appropriate. A launching tube containing 

about four guided missiles and six unguided missiles would be extended upon 

command, and upon acquisition and aiming of the launcher by means of the 

pointing and tracking scope the missile would be fired. .It would be considered 

appropriate for the experiment to use the Gemini type interferometer radar for 

cooperative range and rate rather than an ATS system which would be more suitable 

for an operational device. 

The 706 studies have indicated that it is desirable to have all burning 

take place within the launching tube in order that obscuration of the target by 

the rocket combustion flame and products be minimized. 

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The requirements of the experiment may well be satisfied by adaptation 

of existing systems. For example the TOW missile being manufactured by Hughes 

for the Army uses wire guidance with about a mile of wire,with radio backup. 

Unguided missiles may be adapted from the Army's M-72 LAW or WASP, both of 

which are light.veight, ground prodf-tested missiles. Adaptation of other 

guided and'unguided systems is considered feasible. The missile warhead would. 

probably consist of a shaped charge as a penetration device ahead of the destruct 

charge which might depend on shrapnel for more effective destruction of a warhead. 

It would be expected that some timing device would explode the warhead at a safe 

distance similar to that currently employed in anti-aircraft shells. A proximity 

fuse should be considered in order to assess misses, although its use in an 

operational weapon would be more efbctive for self defense missions. 

The checkout equipment would consist of devices to determine the integrity 

and safety of arming and firing circuits, ability of the3auncher to extend, the 

capability of the target deployment system to function, and bore sighting equipment 

to align the launcher with the pointing and tracking scope. In addition, there 

would be equipment to check the guidance system of the guided missiles, and 

facilities to attach fuses for wiring and firing charges for the remote motors 

with safety during the late hour of the missile countdown. It is considered 

that equipment and procedures common to aircraft would be appropriate. 

Procedure: The experiment would begin at the appropriate time which 

would allow for the best target visibility by the astronaut who would deploy 

a target, and after it has proceeded about 2000 ft away for guided missile tests 

or 400 ft for unguided tests, effect an appropriate maneuver of the spacecraft 

—41744214[4— 

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to stabilize the range rate. The point and tracking scope is used as the 

sighting device and the missile launcher is extended, the missiles checked 

out, and aimed and fired at the target. The higher power of the pointing and 

tracking scope would be used to assess the damage to the target and, if 

sufficient AV is available, to rendezvous with the target for a close evaluation. 

Reception of coded radar signals might prove sufficient to establish hits. 

In order that an adequate test be performed, several rounds should be fired 

at two or three targets that would be deployed in various lighting conditions, 

directions and distances from spacecraft. It is possible that this experiment 

may be completed with a remote maneuvering unit which would be used to deploy 

the target and return it to the vicinity of the MOL for assessment of damage, 

if the basic RMU systems are not damaged by a hit. This portion of the test 

of course, be conducted after tests of the ability of the RMU to maneuver. An 

alternative would be to deploy the EMU to survey the target damage which would 

could minimize the AV to be supplied by the MOL in the event that some 

velocity is imparted to the target by the missile impact. A further alternative 

would be to o...ntion the MOL in the vicinity of the target at the time the test 

is to begin. evaluation of the experiment will consider the ability of 

the astronaut. ,1..!.:rately provide initial aiming of the missile which can 

be assessed from the PTS camera record. The accuracy of the missile and the 

amount and type of damage likewise will be determined from astronaut comments 

and PTS camera records and possibly video records from the RMU if employed. 

Previous pointing and tracking tests and visual observation capability tests 

mill ,determine man's ability to use the equipment provided and determine when 

negartfarc sitourcrere taken against' targetnr, wireater-fecrazr-arbitvespar 

tion or self defense. 

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Simulation: Extensive simulation of this experiment is possible and 

required. Most of the accuracy determination and initial aiming of the 

launcher by the pointing and tracking scope will be obtained from this 

experiment's simulation program. Expected performance of various types of 

missiles can be extrapolated from ground teats, although most current missiles 

employ aerodynamic stabilization rather than reaction jet stabilization. This 

aspect will be the most difficult characteristic to simulate and is a 

reason for conducting on-orbit tests. The damage to various targets can 

be assessed by firings at Eglin AFB by R&TD. The human factors evaluation of 

the experiment can be a part of the observation simulation tests by adding the 

sufficient controls and displays required for the missile launches. Also, 

assessment of damage by the pointing and tracking scope can be simulated during 

these tests. 

Studies: It has been considered appropriate to conduct the pre-Phase I 

experiment definition in-house as an extension of the 706 Program negation 

study. This effort will be closely coordinated with R&TD at Eglin AFB. However, 

the Phase I effort will require contractor study in order that preliminary design 

concepts be available for integration into the MOL lab plan design at an early 

date. 

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MULTIBAND SPECTRAL OBSERVATION 

I. TEST OBJECTIVES 

The primary objective of the multiband spectral experimer.t is to evaluate 

man's ability to operate specialized radiometric and related equipment as aids 

in the following military mission and related scientific activities: 

1. Acquisition and tracking of orbiting objects and/or ballistic 

missiles during their boost, midcourse and. re-entry phases. 

2. Detection of high flying aircraft in clear weather or against 

a cloud background. 

3. Determination of temperature profile of ground and sea, and 

of orbiting targets. Detection and identification of camouflage, day and night 

observations. 

4. Collection of data essential to the design of improved horizon 

sensors from which advanced attitude control subsystems may be derived. 

5. Collection of a wide range of background measurements, in 

particular, earth albedo and sky background data which will be used to design 

advanced sensing systems. 

II. IMPORTANCE OF TEST 

The MOL vehicle provides a unique opportunity to assess the ability and 

utility of man to perform tests of military value. The sensor will consist of 

an IR/UV multiband scanning radiometer capable of measuring radiation from 

cooperatively launched missiles, from orbiting objects, high flying aircraft, 

and from the most adverse earth background configurations. In addition, the 

sensor will be capable of obtaining the thermal profile of selected regions of the 

earth's surface as well as orbiting targets. The 'experiments,. which will.beconducted 

under complete control of the astronauts, will provide fundamental data of crucial 

value to the proper design of advanced ienbors for various military space systems 

such as 461, 706, 893, SSGS, infrared reconnaissance, etc. 

The use of the MOL vehicle will permit measurement of extreme value to be 

made of areas of greatest interest while uninteresting areas are disregarded, thus 

avoiding swamping the system with nonessential data. Furthermore, in just a few 

orbits crucial information will be obtained which could require years of measurement at prohibitive cost from unmanned satellites. 

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The MOL multiband spectral observation of targets and backgrounds does 

not constitute a duplication of Gemini experiments 4 and 9 presently under consideration. In the Gemini experiments both the man's role and the sensor performance are limited. While in the Gemini experiments the astronaut's function 

is essentially restricted to turning the equipment on and off and aligning the 

sensor for maximum deflection, in the MOL experiments the astronaut will 

perform additional functions such as select interesting areas for measurement; 

change detectors, filters, scanning mechanism, and associated equipment; 

make preliminary evaluation of the data presented to him on the console. The 

Gemini and MOL sensors are entirely different. The Gemini experiments 4 and 9 

will make radiance measurements with non-scanning radiometers and interferometers in the spectral region from .2 to 12 microns. In the MOL experiments 

the multiband sensor will be used both as spatial and spectral scanning radiometer 

covering the UV band and various IR bands from one to 30 microns. In addition, 

the multiband sensor will have the capability to acquire and continuously track 

the targets of interest. 

III DESCRIPTION OF THE EXPERIMENT 

The multiband sensor will consist of an all reflective optical system which 

may be operated both as a spatial and spectral scanning radiometer each being 

capable of accommodating several detector assemblies to be used for measurements 

in the infrared or in the ultraviolet, as required during the various phases of 

the experiment. 

The optical system will be mounted on what is normally the earthward side 

of the MOL vehicle, and it will be possible to rotate it about two axes so that any 

portion of the portion of the earth observable from the satellite may be brought 

into the field of view. 

Configuration of Test Item 

The multiband spectral sensor may be housed either in the pressurized first module or in the unpressurized second module of the MOL vehicle. If 

housed in the unpressurized second module, it will be remotely operated, as a 

slaved unit, by an astronaut from the pressurized first module of the MOL vehicle. 

In either case, a pointing and tracking scope (PTS) Paragraph 3. 8) will be available 

for use as an optical director. As a design goal, the optics needed for the subject 

sensor will be limited to an all-reflective system with a maximum of 12 inches 

in diameter, and a weight of 65 pounds or less. 

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The remaining portions of the radiometer and auxiliary equipment 

(including cryogenics) will be limited to 250 pounds with a maximum power 

consumption of 300 watts. 

Test Support Equipment Required 

It is anticipated that most of the required support equipment will 

be available from other MOL Experiments. 

1. On Spaceciaft 

a. A Pointing and Tracking Scope (PTS). During the experiment 

the multiband spectral sensor may be remotely connected and slaved to the 

PTS to provide accurate pointing of the sensor. When targets, invisible 

to the human eye, are being sought, the PTS will be used as a goniometer 

if advanced target location data are available to the astronaut. 

b. A 16 MM stop frame camera with which the astronaut photographs the object being tracked. 

c. A display console for the radiometer outputs. 

d. A magnetic tape recorder capable of up to 5 MC read-in and 

1 MC read-out with up to 30 minutes temporary storage. 

e. A star tracker to provide reference angles during the horizon sensing phase of the experiment. 

2. On the Ground 

a. An Aerospace ground equipment (AGE). 

b. A computer to process results of each test as soon as the 

data are received so that the measurements may be interpreted and the 

program for succeeding experiments may be modified so as to converge 

on the desired goal as rapidly as possible 

Test Procedure 

The astronauts will play a crucial role during all phases of the experiment. Their activities shall include the following: 

1. Pointing of optics in the direction of phenomena or target using 

the PTS or other controls. 

2. Selection of area for measurement. 

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3. Changing Changing of detectors, scanning mechanisms and associated 

equipment. 

4. Changing of filters. 

5. Adjustments and calibrations. 

6. Preliminary evaluation, recording of data, and verbal descriptions. 

7. Coordination with the ground. 

During one MOL mission the following phases of the experiment 

will be covered: 

1. Infrared Background Measurements 

During this phase of operation, the multiband spectral sensor 

will be used both as a spatialand a spectral radiometer. 

Two modes of operation are contemplated, (1) a visual search 

with manual scanning mode performed by the astronauts and (2) an automatic scanning mode. It will be an objective of this study to determine 

whether the additional complexity of an automatic scanning mode is justifiable in terms of the quality and amount of data collected. 

a. Manual Scanning . The visual search with manual scanning 

mode will be accomplished as follows: 

(1) One astronaut will search visually for regions of strong 

background return, while the other observes the output of the spatial scanning array on his display console. They will then selectively record and/or 

telemeter the output of their array and their commentaries on what was 

observed visually during the measurement. This will be done for several 

strong return areas. 

(2) The astronauts will scan similar areas with the spectral 

scanning radiometer. 

(3) These data will be analyzed and the astronauts will insert 

an optimum filter (or filters) to use in the scanning array. 

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(4) Using this optimum filter they will study as many 

regions of high return as possible. They will track these regions so 

as to view them from a range of aspect angles and to determine whether 

there are rapid temporal changes. The scanning array will observe a 

large enough area so that the sizes and spatial distributions of the regions 

of strong return can be determined. 

b. Automatic Scanning . The automatic scanning mode will be 

accomplished as follows: 

(1) The astronaut will start the atuomatic mode after setting 

a radiance threshold for each of the spectral bands to be used in the measurement. 

(2) The field-of-view used in the scanning operation will be 

adjusted by the astronaut. 

(3) Whenever the preset thresholds are exceeded the radiometer stops scanning, locks on the area generating the signal, and proceeds 

with spectral scanning using a preprogrammed group of filters for the purpose of determining sizes, spatial and spectral distributions of the regions 

of strong return. 

2. Infrared and Ultraviolet Sensing of Ballistic and Orbital Targets 

During this phase of operation, the multiband spectral sensor 

will be used primarily as a spatial scanning radiometer to perform the 

function of detecting and tracking cooperative ballistic missiles and orbiting 

objects through the longest possible portion of their flight, or orbit, from 

boost to re-entry inclusive. During this mode, one additional important 

function of the sensor will be to obtain spectral signature of the target. 

The astronaut's functions in these tests are to: (1) make measurements 

in regions of interest only, (2) track targets, (3) point the scanner across 

regions of interest, (4) assembly and adjust the many possible equipment 

combinations, and (5) calibrate and maintain the equipment. 

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Once the astronaut is notified of a ballistic launch, he is given 

the relative target coordinates, and selects the proper sensor spectral 

bands required for detection of the ballistic missile in the boost phase. 

The astronaut points the sensor in the direction of the target with the help 

of the slaved PTS, used as a goniometer only, if target is invisible to the 

human eye, andrstarts searching a relatively small space volume which is 

expected to contain the target. In the case of orbiting objects, these may 

be either active or inactive artificial cooperative satellites or targets of 

opportunity including some in orbits higher than the MOL vehicle. In all 

cases, the experiment shall be designed to provide data on man's ability 

to detect the targets described, using the multiband spectral sensor alone 

or in conjunction with other sensors or aids such as radar and the SPADATS 

network. 

Upon detection of a target, the astronaut will commence automatic 

or manual tracking using the PTS or the output of the radiometer itself. He 

will continue tracking as long as possible throughout the midcourse and reentry phases of the missile trajectory. Filters may be changed, in rapid 

succession, during this part of the test procedure. 

The sensor output shall consist of detection signals and identification of the spectral bands providing the signals, as well as angle and 

angle rate. This output shall be recorded for later ground evaluation as 

well as being displayed to the astronaut for his information on the conduct 

of the experiment. 

In the acquisition and tracking mode, the multiband sensor must 

be compatible with MOL operation, and shall have automatic sequencing 

capability through the spectral bands, pre-set before mission onset or 

modified by the astronaut, as required by the experiment. 

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3. Thermal Profile of Ground and Space Targets 

During this mode of operations, the multiband spectral sensor 

will be used as an optical scanning radiometer. Using the proper filterdetector-radiometer combination, the astronaut will point the radiometer 

to the region of the earth to be mapped. An attempt will be made to detect 

thermal structures produced by ocean currents and sea states, harbor 

activities, shipping and wakes, air field activities, meteorological formations, geological formations, underground nuclear tests and man-made 

structures such as missile sites and underground factories. 

Pictorial data of cooperative targets will be furnished and displayed by rear screen projection in an easily accessible manner which 

will facilitate comparison with the actual target. The astronaut will select 

targets based on orbit configuration, and cloud cover consideration. 

Visual sighting and photographic imaging of targets will be made for comparative purposes. 

For daylight targets, the astronaut will concentrate largely on 

camouflage discrimination using various filter combinations and detectors 

in the red, near and intermediate IR. A few daylight measurements in 

the far IR will also be made to assess target thermal emission contrast 

with adjacent surroundings for comparison with orbital night measurements. 

During orbital night, measurements will be made with carefully 

selected filters and resolution elements (detector size) in the 8 - to I4-micron 

region. Orbital targets, approached by MOL in a station-keeping mode, at 

ranges of 2000 feet or less, will also be submitted to a radiance profile analysis. 

The astronaut will be obtaining on-the-job (in space) training for 

this type of observation. 

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--eONNENTIAL4. Horizon Sensing Data 

During this mode of operation, it is desired to measure the 

radiance profile of the earth's horizon as a function of line-of-sight 

angles for various spectral regions in the infrared over a wide variety 

of meteorological conditions and geographical locations. The experiment will provide a better understanding of the radiation characteristics 

of the horizon and the variations to be expected. 

The astronaut will select the desired filter-detector-radiometer assembly. He will scan the horizon spatially and spectrally to 

determine the sharpness of the horizon for the optimum spectral response 

of the radiometer. The position of the horizon will be determined for 

various azimuth angles,latitudes, sun positions and weather conditions. 

5. Detection and Tracking of High Flying Aircraft 

An attempt will be made to detect and track high flying aircraft against the sunlit earth background. 

The sensor operation in this mode is identical to that used in 

the detection and tracking of ballistic missiles and orbiting objects outlined in Paragraph 3.4.2. 

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Category of Experiment 

The multiband spectral observation experiment is considered 

category 1 because it places a rather heavy demand on the astronaut. 

Cost 

The multiband components are expected to be all within the state 

of the art, no new development will be required, and hence the cost can be kept 

relatively low. 

Prior FY 65 FY 66 FY 67 FY 68 FY 69 Total 

1) Pre-Phase I Study $200k $200k 

2) Engineering & 700k 700k 400k 1800k 

Development 

3) Installation 400k 

4) AGE 75k 75k 

5) Training & Simulation 100k 100k 

TOTAL $200k 700k 875k 975k 

400k 800k 

50k 200k 

200k 400k 

650k 3400k 

Schedule 

1. Availability for Test 

Eighteen months after contract is let. 

2. Flight Readiness 

Twenty-four months after contract is let. This includes a 

training program for the astronaut with tests in an aircraft. 

Participating Government Agencies 

Sponsor: AFSSD/Aerospace Participant: OAR 

Additional Requirements 

1. Special Security 

Equipment unclassified. 

Background data confidential. 

Target data secret. 

2. 

3. 

4. Facilities 

Existing and planned ground facilities should be sufficient. 

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a. Astronaut (continued) 

Equipment to be tested and astronaut trained in aircraft. 

A well trained team of scientists and computer engineers must 

be on duty during measurements. Computer programs must be 

tested during the pre-flight training of the astronaut. 

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TEST OPERATING CHARACTERISTICS 

1. Orbital Parameters desired. 

a. Altitude • approximate 200 miles 

b. Inclination - near polar desired but 30' acceptable. 

c. Epoch - not critical 

d. Eccentricity - Approximately circular 

2. Plane Change . none required. 

3. Altitude Change - none required. 

4. - 

5. Test duration - Twenty-five daylight hours minimum for background tests plus 

half hour measurements each on as many cooperative targets as possible. 

6. Total Number of Tests - See S. 

7. Test Frequency - no specific frequency. 

8. Interval between tests - 

Background tests - daylight side only 

Target tests - depend upon target availability 

9. Crew Task Loads • 40 man hours. 

10. Crew. Task Frequency - as in 8. 

11. Field of View Requirements - 

Instantaneous . 2° to 5° cone 

Scan possibility - From nadir to 60' elevation angle, and all azimuths for background tests. Target to be tracked for target studies. Highly desirable that 

vehicle be able to. turn over for target measurements. 

12. Ground Control Liason Duration 

Communication as required for data reception, and for transmittal of ground 

commends, 

13. Ground Control Liason Frequency 

Once per orbit during background tests 

Continuously during target tests 

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14. External Test Items. 

a. Launched from Station - None 

b. Launched from Resupply - None 

c. Launched from Ground - Cooperative targets as available preferably 

from MOL launch facility. 

MANNING DESCRIPTION 

1. Astronauts 

a. Number required - two during test 

(1) Man's function 

(a) As part of test 

Select areas of interest 

Track object being measured 

Record Verbal description 

Record photographs of object 

Operate radiometers and record their output 

(b) As technician 

Change filters, detectors and scanning mechanism 

Install proper radiometer as commanded 

Telemeter recorded data to ground station 

Perform routine calibrations, checks, and adjustments 

b. Crew skill requirements 

Must be excellent technicians 

Scientific training desirable but not essential 

c. Manpower profile - 80 man hours 

d. Critical functions - All items under a. are critical 

j • Training requirements - must go through!preflight training and equipment checkout in aircraft before equipment 

is installed in satellite 

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GENERAL PERFORMANCE IN MILITARY SPACE 

I. Test Objective: 

The objective of this test is to assess the psychological status of the 

operator on a day-to-day basis throughout the mission with respect to his 

readiness to perform tasks that are basic to his contribution to system 

and subsystem effectiveness. 

II. Imoortance of Test: 

The performance measurements to be made will provide information 

that is needed for two purposes. First, the broadly defined biomedical 

status of the operator must be further delimited by precise information 

about the man's alertness, general performance capabilities and performance reserve via a vis the problems presented by the systems 

management functions and the re-entry profile. Second, the operation of 

the vehicle and military subsystems entails two potential sources of 

variance - the equipment and the man. Since we typically will have 

incomplete knowledge about the detailed nature of the forcing functions 

which "drive" these subsystems these general performance measures are 

required to provide an index of the man's performance as a possible 

source of variance in subsystem operation. 

III. Description of Experiment: 

a. Confizuration of Teat Items - The performance tasks will be 

mounted in a panel that will occupy a volume of .3 cu. ft. (3" x 8" x 15"); 

the weight of the panel will be approximately 15 pounds; the power drain 

of the panel of displays will be about 20 watts. 

b. Test Support Equipment Required - This device would be programmed by a suitable on-board computer that could presumably be 

acquired as an existing or modified general purpose mission task computer. 

c. Test Procedure - Each operator would be tested on this device on 

alternate days at the rate of 30 minutes per session, two sessions per day, 

for a total of one man-hour per day. The daily schedule of testing should 

provide for one of the test sessions to occur at a fixed time each day, e. g. , 

at 0800; the second test session will occur alternately at a time approximately 8 or 18 hours after the first test session for that operator on that 

day. 

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The specific tasks to be included will provide measures of the following 

psychological functions: (1) Monitoring of static and dynamic displays, (2) 

Visual discrimination, (3) Short-term memory, (4) Psychomotor performance, 

and (5) Intellectual activities. 

The chart below names the specific tasks and shows the propoeed performance schedule for a given 30-minute session: 

0 5 10 15 20 25 30 

Warning Lights X X X X X X X 

Probability Monitoring X X X X X X X 

Tracking X X 

Mental Arithmetic X X X 

Code Lock X X X 

Target Identification X X 

d. .Category of Experiment - This item falls in both Categories A 

and C. 

e. god - See Atch 4. 

f. Schedule - See Atch 7. 

IV, Participating Government Agencies; 

Sponsor: AMD (6570 AMRL, Wright-Patterson AFB, Ohio) 

Test Equipment Acquisition: 8570 AMRL, Wright-Patterson AFB, Ohio 

V. Additional Reauirements: 

a. Special Security - N/A 

b. ktiall1111Lialarbtion Summary - See Atch 5. 

c. Logistics - To be determined. 

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d. Facilities - Existing AMRL facilities will be sufficient. 

e. Simulation and Training - See Atch 5, Section 1, Item J. 

VI. General: See Atchs 6 and 7. 

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DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED: Performance Battery 

2. WEIGHT: 15 pounds 

3. VOLUME: Stored - .3 cubic feet; In use - .3 cubic feet 

CRITICAL DIMENSIONS - SHAPES: 8" x 15" x 3" 

4. POWER: 

a. Continuous - N/A 

b. Stand-by - N/A 

c. Average Operating - 20 watts 

d. Peak - 20 watts 

e. Duty Cycle - 30 minutes/8 hours 

5. SPARES: 

a. Volume - 12 cubic inches 

b. Quantity - Miscellaneous light bulbs, etc. 

c. Weight - 8 ounces 

8. TOOLS: N/A 

7. HEAT OUTPUT: To be determined 

8. STABILITY: N/A 

9. VIBRATION LIMITS: 2 g' s rms 5-100 cps 

10. SHOCK LIMITS: To be determined 

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11. HAZARDS (fire, explosion, electrical, toxics, other): N/A 

12. TEMPERATURE LIMITATIONS: + 390°Fahrenheit 

13. TYPE AND RANGE OF MEASUREMENT (definition of parameters to 

be measured while test is underway): See Section III. c. 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS: N/A 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: N/A 

Station 

Equipment 

16. EQUIPMENT OPERATING CYCLE: 

Frequency: Once/8 hours 

Time Duration: 30 minutes 

17. EQUIPMENT LOCATION REQUIREMENTS: At station keeping console 

18. SPECIAL MOUNTING REQUIREMENTS: N/A 

19. PRESSURE VESSELS (fluids, gasses, etc. ): N/A 

20. ELECTRO MAGNETIC INTERFERENCE: N/A 

21. MAINTENANCE REQUIREMENTS: None 

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TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA: Magnetic tape 

2. HANDLING (special equipment required to handle items being tested): 

N/A 

3. PACKAGING: N/A 

4. CALIBRATION (alignment, deployment): N/A 

5. JIGS AND FIXTURES: N/A 

8. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION: N/A 

7. SENSORS (Transducer-Output Signals): To be determined 

8. TRAINERS/SIMULATORS: Currently existing at Lockheed-Georgia Co. 

9. INSTRUMENTATION: Requires programming from digital computer 

10. RELATED SUPPORT EQUIPMENT: N/A 

11. AGE: N/A 

12. ENVIRONMENTAL TEST EQUIPMENT: N/A 

13. FACILITIES: N/A 

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TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired): N/A 

2. PLANE CHANGE: N/A 

3. ALTITUDE CHANGE: N/A 

4. TIME ON ORBIT: N/A 

5. TEST DURATION: 30 minutes/8 hours 

6. TOTAL NUMBER OF TESTS: 60 

7. TEST FREQUENCY: 2/day 

8. INTERVAL BETWEEN TESTS: 8 hours 

9. CREW TASK LOADS (manhours): 1 hour/day 

10. CREW TASK FREQUENCY: 2/man/on alternate days 

11. FIELD OF VIEW REQUIREMENTS: N/A 

12. GROUND CONTROL LIAISON DURATION: Transmission time 

13. GROUND CONTROL LIAISON FREQUENCY: 1/8 hours 

14. EXTERNAL TEST ITEMS: N/A 

15. QUALIFICATION TESTS (other than space): N/A 

16. SEQUENCE OF EVENTS AB THEY OCCUR DURING FLIGHT: See 

Section III. c. 

17. HANDLING PROCEDURES: N/A 

Atch 3 SSTA-1.9 

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CD 

k. 

O 

a 

0 0 

C43 

0 0 

0 

Tobedetermined 

co 

0 0 z z Simulators/Trainers 

DataReduction 

Tobedetermined Equipment Rework 

6 

a 

8 E. 

Sourceof Funds - Hitch LineNu

mber - 62405124 

Exp No. P-11 

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1 28 

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MANNING DESCRIPTION 

1. ASTRONAUTS: 

a. Number Required: 2 

Man' s function - As subject in test, self administered 

b. Crew Skill Requirements: Not specific 

c. Manpower Profile: Not specific 

d. Critical Functions: Not specific 

e. Work Positions: 1 

f. Time Controlled Tasks: 30 minutes/8 hours 

g. Human Performance Measures: See Section 111.c. 

h. Physiological and Psychological Measures: See Section III. c. 

1. Selection Factors: Adaptability to 4-hours work/4-hours rest 

schedule. 

j. Training Requirements: Section 1 above and this requirement 

could be satisfied simultaneously in a 10-day period. 

2. GROUND PERSONNEL: 

Number Required: There is a requirement for a psychologist 

experienced in research on the performance effects of environmental 

stress to be available to integrate data on day-to-day basis. 

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COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE: 2 transmissions/day; 24 data points/30 minutes of 

performance. 

2. FUNCTIONS TO BE MEASURES: See Section M. c. 

3. TYPE OF ANALYSIS REQUIRED: Means 

4. PICTORIAL DATA REQUIRED: None 

5. REAL TIME MONITORING REQUIREMENT: N/A 

IL DATA EDITING OR COMPRESSION: N/A 

7. READ-OUT TIME: To be determined 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS: Yes 

9. MANUAL AND/OR AUTOMATIC CONTROL: N/A 

10. SIMULTANEITY: N/A 

11. GROUND COMMANDS REQUIRED: N/A 

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DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME: 16 months 

2. FINAL DEFINITIVE TEST DESIGN TIME: 12 months 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED: N/A 

4. TYPE OF DEVELOPMENT TEST ITEMS: 

a. Vacuum Chamber - N/A 

b. Shaker - 2 g rms, 5-100 cps 

c. Thermal - + 390°Fahrenheit 

d. Acoustic - To be determined 

e. Simulators - Existing simulators will do the job 

f. Aircraft - N/A 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME: N/A 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test - 1 

b. Atmospheric Test - N/A 

c. Space Test - 1 

7. DATE AVAILABLE FOR TESTS: January 1966 

8. CURRENT DEVELOPMENT STATUS: Program is approved and 

purchase request for the design study is to be initiated in July 1964. 

Contract for an in-house laboratory version now being negotiated. 

Funds Expended to Date - $1, 250M 

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Experiment P-12 

EXPERIMENT P-12 

BIOMEDICAL AND PHYSIOLOGICAL EVALUATION 

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The Identification, Analysis and Control 

of the Biological Changes and Adaptive 

Mechanisms within the Body of Man During 

MOL Missions 

TABLE OF CONTENTS 

Page 

SUMMARY 135 

FOREWORD 139 

AREA 1 - CARDIOVASCULAR 

The Study of the Cardiovascular Effects Resulting from 

Missions of MOL Duration 145 

AREA 2 - CNS 

Study of Central Nervous System and Motor Effects Resulting 

from Flights in MOL 156 

AREA 3 - GI - DIET 

Study of the Gastrointestinal Effects Resulting from 

Missions of MOL Duration 175 

AREA 4 - METABOLISM 

Study of Effects on Metabolism Resulting from Flights 

on MOL 194 

AREA 5 - RENAL-FLUIDS BALANCE 

Renal and Electrolyte Effects Resulting from MOL Mission .. 205 

AREA 6 - RESPIRATION 

Evaluation of Pulmonary \Function During MOL Missions • • • 216 

AREA 7 - DETERIORATION AND CONTROL 

Study and Control of System Deterioration and Associated 

With MOL Missions 223 

RADIATION 

Space Radiation Measurements of Significance to Man 237 

MISCELLANEOUS 264 

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SUMMARY 23 March 1964 

BIOMEDICAL AND PHYSIOLOGICAL EVALUATION 

I. OBJECTIVE: 

The biomedical testa pre designed primarily to evaluate those 

effects of weightlessness which can potentially compromise mission 

success. Sufficient data is required to validate supportive measures 

employed, devise improved methods, if necessary, and afford plausible 

estimates of biomedical status for missions longer than 30 days. 

II. DESCRIPTION: 

By taking full advantage of pre-flight and post-flight studies, 

as well as all previous manned orbital flight experience, the only tests 

to be conducted during flight are those which fulfill the necessary and 

sufficiency statements given in the test objectives. Measurements will 

be made of the following functions considering the effects of weightlessness, 

environmental loads and body demands: a) blood volume, pressure, and flow, 

b) the elentro-mechanical behavior of the heart, c) fluid and electrolyte 

levels and oalance, d) gastrointestinal function and nutritional status, 

e metabolism of selected body materials; e.g., calcium and protein, 

5 respiratory mechanics and rate of energy metabolism, g) nervous system 

functions; e.g., muscle strength and coordination, general mental status. 

Important associated environmental parameters will be measured, including 

physical and tissue equivalent. radiation measurements. 

A. Experimental Equipment: Sensors for electrical, mechanical, 

and chemical measurements, signal analyzers and converters, data recording 

and storage systems. (2) Equipment for selective data transmission. 

(3) Voice communication equipment. (4) Real-time TV or motion picture 

recording, if fdasible. 

B. Test Procedures: Typical procedures will include donning a 

vest with sensors and leads, switching on recording systems, and monitoring 

results' to assure adequate recording; recording fluid and food intake; 

measuring and recording urine output and preserving sample for subsequent 

analysis; performing sample chemical (spectrophotometric and electrode 

chemistry) determinations on urine and occasionally on blood. Specific 

sequence of procedure will be determined by ground-based studies and 

simulation in Prephase I, Phase I. These procedures will be carried out 

by giving one member of the crew the requisite training to conduct all 

the tests in a reliable manner. 

C. Evaluation Procedures: Results will be partly interpreted in 

real-time both in flight and through transmission of selected data to 

ground. Quantitative data obtained are directly and unequivocally translated into meaningful evaluation of normality or deterioration in physiologic status of the astronauts. Other data along with pro- and post-flight 

data will be used to evaluate over-all results, devise subsequent test 

plans and guide future flight procedures. 

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III. IMPORTANCE OF TEST: 

The physiological effects of long-term weightlessness can be 

predicted to some extent qualitatively, but cannot be determined quantitatively with an adequate level of confidence through ground-based 

studies. The MOL 30-day flights presume prior 14-day weightless NASA 

flights; while these add some applicable data and an additional level of 

confidence, they do not eliminate the requirements for tests during the 

30-day NOL missions. The measures proposed reflect a reasonable concern 

for both the astronaut's health and the need for his support to ensure 

mission success. 

The mission profiles and manned operational modes envisioned for 

useful military applications (e.g., in enhancing reconnaissance capabilities) require that the'crew be maintained in good physiological status. 

Tests are essential to establish that such status, in fact, exists. The 

severe configuration and operational constraints of providing an artificial 

gravity implies that it is mandatory to secure the type of test data 

indicated. Such data will serve to devise improved preventive measures--

short of aritificial gravity--or for a major decision to employ some 

gravity mode. 

IV. VEHICLE REQUIREMENTS: 

Power 30 watts avg., 300 watts peak 

Volume: 12 cu.ft. 

Weight: 260 lbs. 

Aperature: The omnidirectional proton, electron, and alpha 

spectrometer should be mounted externally or extended 

from the unpressurized compartment during operation. 

In the cosmic ray emulsion experiment, an aperature 

must be available through which emulsions can be 

extended and e::posed for predetermined periods of time. 

V. SIMULATION PROGRAM: 

PREPHASE I: Simulation of all biomedical tests in realistic 

sequence in a MOL environmental mock-up to establish 

test validity, equipment 'modification and location, 

and task-time reopirements. The radiation measurements 

will also be simulated as part of the biomedical experiment. This simulation work will be accomplished in-house 

by A. 

PHASE I: Build prototype mock-up and integrate biomedical testi; 

with other experiments and station.operations. 

.Establish crew function and activity time parameters 

for test plan. 

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VI. LXPERDIENT DEFINITION: 

PREPHASE I: Validation study of proposed biomedical testa; 

parametric studies for feasibility of procedures and 

man-activity. Evaluation of existing instruments and 

feasibility of modifications to ensure flight-rated 

items. These studies will be accomplished in-house 

by AMD. 

PHASE I: Integrate experiment procedures and equipment--parametric 

studies. Initiate equipment developments. Design 

procedures and equipment for flight environment 

compatibility. 

THROUGHOUT: Aggressive ground-based studies are essential to develop 

and confirm weightlessness countermeasures. 

VII. FUNDING REWIRED: 

PREPHASE I: No additional funds required. 

PHASE I: To be determined. 

VIII. PARTICIPATING AGENCIES 

Sponsor: A?il 

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FOREWORD 

The challenge presented to the Biomedical Panel of preparing 

the experimental program required for accomplishment aboard the 

Manned Orbiting Laboratory has led to an exciting and fruitful 

analysis of the problems to be encountered by man on this mission. 

This document reflects the distilled resultant of this analysis. 

Although the document appears lengthy, the biomedical studies 

presented here are considered to be the minimum tests essential 

if we are to answer the questions of man's utility in performing 

in military space vehicles and if we are to be able to provide 

guidance for extending man's exposure to a weightless environment 

beyond the first MOL missions. 

The authors felt it to be important to present backup information which was used to arrive at the proposed test protocol in order 

that it will be clear as to how the in-flight studies evolved to their 

present state. The series of annexes at the end of the document 

attempts to fulfill this goal. 

It is realized that in a document of this complexity it is 

difficult to integrate segments of the study to meaningful information that can be used to measure the impact upon the total program. 

In the miscellaneous section, an attempt to aid the reader in 

meeting this task has been done. 

This document will require future refinement through continuous literature review, extensive ground based studies, and 

further detailed analysis of the feasibility of performing some of 

the proposed tests in a space environment. However, the need 

for the information is valid. If the tests need to be curtailed due 

to technical or operational reasons, the ability to answer the 

fundamental questions concerning man's adaptability to the space 

environment and therefore his utility in performing while there 

will be curtailed. 

This document is the consolidation of the thoughts of an Air 

Force Biomedical Panel and a group of outstanding consultants. 

These people should be recognized for their efforts, both individually and in their Joint efforts which load to the experimental 

package. 

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General Biomedical experimental program integration was 

accomplished by Lt. Colonel Stanley C. White, USAF (MC), 

Headquarters AMD, and by Gerald McDonnell, M.D. , UCLA 

School of Medicine, Los Angeles, California. 

Dr. Bryce Hartman of USAR SAM has acted as the 

technical bridge between the Biomedical and the Human 

Performance panels. In this capacity he has provided 

excellent continuity in our efforts and. save many 

hours for the Biomedical panel 

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Area 

The members of the team include: 

Air Force Team 

& Affiliation 

Consultants 

& Affiliation 

1. Cardiovascular Lt Col John Ord USAF (MC) 

Wilford Hall Hospital 

A. Stuart Bondurant M.D. 

Univ. of Indiana 

College of Medicine 

Indianapolis, Indiana 

B. Earl Wood Ph. D. 

Mayo Brothers Clinic 

Rochester, Minn. 

2. Central Nervous 

System 

3. Gastrointestinal 

Tract & Nutrition 

Ed Liske M.D. 

USAF SAM 

Capt Gerald Parker USAF 

(MC) 

Wilford Hall Hospital 

A. Marvin Schleisenger M.D. 

Cornell University 

New York City, N. Y. 

4. General Metabolism Lt Col Robert Johnson 

USAF (MC) 

USAF SAM 

Capt Theodore N. Lynch 

USAF (MC) 

USAF SAM 

A. Gilbert Gordon M.D. 

Univ of Calif Medical 

Center 

San Francisco, Calif 

B. David Kipnis M.D. 

Barnes Hospital 

St Louis, Mo. 

5. Renal & Fluid 

Balance & 

Electrolytes 

6. Pulmonary 

7. Deconditioning 

& Control 

Capt John McPhaul 

USAF (MC) 

Wilford Hall Hospital 

Capt Paul Stevens 

USAF (MC) 

USAF SAM 

Dr. Stephen Cain 

USAF SAM 

Capt Duane Graveling 

USAF (MC) 

Hq AMD 

A. William B.Schwartz M.D. 

Tufts New England 

Medical Center 

Boston, Mass. 

A. Herman Rahn Ph.D. 

Dept of Physiology 

Univ of Buffalo 

Buffalo, N. Y. 

A. Stuart Bondurant M.D. 

B. Earl Wood Ph.D. M.D. 

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THE IDENTIFICATION, ANALYSIS AND CONTROL OF THE 

BIOLOGICAL CHANGES AND ADAPTIVE MECHANISMS 

WITHIN THE BODY OF MAN DURING THE MOL MISSIONS. 

I. Test Objective: 

A. The experiments, studies and observations accomplished 

throughout the flight program will provide the criteria needed to understand the human adjustments occurring during the exposure of the crew 

to mission durations of the MOL. Further, through integration of the 

data collected during flight with that obtained by the pre-flight and 

post-flight control studies and the data accumulating on man's system 

changes measured during exposures up to 14 days by the NASA Gemini 

and Apollo programs and the future Russian manned flights, the quid,- 

ance for future mission planning will be obtained. Qualification of 

changes, analytis of the significance of the changes and definition 

of the provisions for maintaining a reliable functioning man will be 

obtained. Prediction of the rate of extension of mission duration 

based upon the limits dictated by man will be assessed. Evaluation 

of the medical status of man through trend changes will permit 

analysis of the inclusion of man in more complex assignments during 

missions of similar 30-day mission duration. 

II. Importance of the Test: 

A. This test program will provide essential information in the 

following areas: 

1. The weightless effects upon man remains as one of the 

main open areas in manned space flight. .The only way to assess this 

area is through flight. The MOL mission.from. its onset plans to 

extend the time of exposure of the crew to continuous weightlessness 

by a factor of 2 over that obtained by present NASA programs. There 

are several indications of significant changes expected and predicted 

which could effect the crew's well-being•and ability to perform either 

"in orbit" or during re-entry that will become manifest in the period 

of 4-weeks exposure. 

2. The MOL program is dedicated to the measurement of 

man's utility in the military missions. The bioastronautics mea surement of man's abilities is predicated upon not only mission performance but also upon his readiness to perform or upon the changes 

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which will lead to deterioration or unsatisfactory performance in the 

future. Further, assuming there are changed which will become 

significant enough to depreciate his worth, the data obtained will 

permit the quantifying of the effects and the design of countermeasures to offset these effects. Through this cause, effect, countermeasure approach, the mission requirement for providing flexibility 

for crew utilization will be met. 

3. The accomplishment of this study and the closely 

related human performance studies will provide the documented proof 

of man's utility in space. If the mission goes well, the data obtained 

will give technical depth as to how successful man is. Data obtained 

will give essential information needed to introduce the crew more 

deeply into the following missions. If there are problems found, this 

data, when integrated with the human performance results, will provide understanding as to whether the problems were man's inherent 

failure or whether he was overwhelmed through poor operational 

scheduling or through poor systems design. 

4. The data obtained as part of this study program will be 

available for operational integration during the mission and will be 

useful during the daily flight control assessment. Decisions concerning mission modification can be made using the study program 

data as well as flight safety information. Man, as an important 

system aboard the vehicle will thereby be studied as completely as 

the engineering systems aboard the MOL.. 

B. This test program must be studied in space because it is 

based upon the study of man while he is exposed to the total spectrum 

of space stresses. Even though a great amount of ground simulation 

and aircraft experience will need to be done in preparation for the 

flight data, the final proof can only be obtained through the space 

flight experience. 

III. Description of Experiment: 

A. The experiment is designed to analyze the total man through 

specific testing of the body systems presently predicted to have a high 

probability of changes which could embarrass the man's performance. 

Each body system is discussed and presented as a separate area of 

study below, however, integration of instrumentation and data 

analysis are already planned to provide for total man assessment. 

Further, the data obtained by this experiment will be integrated with 

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the human performance results for the purpose•of answering the prime 

objective of the MOL mission. The following sections discuss the 

studies needed for each body system: 

1. Study of Cardiovascular Effects Resulting from Missions 

of MOL Duration. 

2. Study of Central Nervous System and Motor Effects 

Resulting from Flights in MOL. 

3. Study of the Effects on the Castro-Intestinal Tract 

and Nutrition by the MOL Mission. 

4. Study of the Effects on Metabolism Resulting from 

flights on MOL. 

5. Renal, Fluid, and Electrolyte Effects Resulting from 

MOL Mission. 

6. Evaluation of the Pulmonary Functions During MOL 

Missions. 

7. Study and Control of System Deterioration and 

Associated with MOL Mission. 

Sections IV, V, and VI of the suggested experimental protocol will be 

covered within each of the seven areas for study noted above. Attachments 1 through 8 of the experimental format will be considered.for 

each study area as well. 

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1. Study of the Cardiovascular Effects Resulting from Missions of 

MOL Duration. 

The cardiovascular experiments have been selected to provide 

important information regarding the two paramount problems anticipated 

to be produced by the weightless environrrent and the gravitational 

stresses of launch and re-entry, while at the same time providing the 

essential observations required for mission safety. The tests are 

designed to give data concerning loss of normal cardiovascular 

regulation and changes in blood volume, with quantitation of their 

magnitude and some clarification of the time course of their production. Relatively small time costs are involved and no onboard 

interpretation of data is required. 

a. Configuration of Test Items 

(1) Gemini (for both astronauts). 

(a) ECG,real time, frequency 0.1 to 50 cps, one 

or two bipolar chest leads. 

(b) Blood Pressure,real time, reading 1 per minute. 

Korotkoff sound technique. 

(c) Ear Oximetry,tape recorded, two channels, 

• D.C.-20 CPS. 

(2) MOL 

(a) Heart Rate,instantaneous, fundamental frequency 

20-200/min. System being developed at Bioengineering, SAM, based 

on R-R interval coding would be ideal. H.F. T.M. desired. Personal 

electronic package to obviate interference with astronaut freedom 

should be provided. 

(b) Blood Pressure,one automatic system, Korotokoff 

sound type, 1 reading per minute. Manual system for astronauts to 

record each other's blood pressure with digitally keyed or voice 

transmission. 

(c) Electrocardiogram,there channel orthogonal lead 

system, Frank or Schmidt, frequency 0.1 to 100 cps, quick don 

electrode belts or vests. 

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(d) Ballistocardiogram, three channel, low frequency 

(0.1 to 20 cps). Three orthogonally oriented accelerometers required. 

Coupling to free floating man over a relatively noncompliant body area 

must be developed. 

(e) Body Mass, one channel, low frequency (to be 

-determined), accelerometer determination of period of oscillation 

ofmann-constant spring device. 

(f) Body Volume, determined by. ambient pressure 

measurement (strain gauge of high sensitivity) before and after the 

sudden addition of a known volume of gas to a sealed, calibrated 

free volume section of the MOL. An air lock would be ideal. One 

channel (DC to 10 CPS). 

(g) Total Body Water, determined by analysis of 

equilibrated urine or serum labeled by ingestion of a known amount 

of D20, The analysis would require mass spectrometry. Account 

will have to be taken of contamination of water supply through 

recycling, etc. 

(h) Blood Volume. Determined by intravenous 

injection of known amount of T-1824 blue dye, and determining 

hematocrit and indicator volume diultion on a venous blood sample. 

The procedure requires calibrated needles and syringes, simple 

bench type centrifuge and tubes and photocolorimetric reading at 

approximately 610-620 mm. The photometer output will be D.C. 

and can be meter read and/or taped. 

(i) Cardiac Output and Oximetery. A calibrated red 

and infrared sensing earpiece with two channel output (0-20 CPS) 

will be used for both. Time concentration curves of the T-1824 injected for blood volume yield quantitative cardiac output, arm to ear 

circulation time and qualitative systemic circulation time and blood 

mixing volume. Measurement of occlusive pressure of the earpiece 

balloon (strain gauge, one channel, DC-20 CPS) will provide qualitative head level pulse pressure and systolic pressure. Arterial 

oxygen saturation at head level is accurately determined. 

(j) Venous Pressure. Strain gauge, one channel, 

DC-20 CPS, mean pressure measurement. 

(k) Cntocholamine Excretion. Aliquots of urine processed for analysis on ground following mission completion. 

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(1) Oxygen Consumption and CO3Production. 

Appropriate sensors of 02 and CO2 content of expired air samples after 

drying, and determination of timed volume of ventilation. Mass 

Spectrometric sensing of 02 and CO2would be useful because of the 

speed of analysis. (See pulmonary section). 

(m) Autonomic Stress Maneuvers. 

1. Calibrated exercise response (heart rate, 

blood pressure, ECG, cardiac output, oxygen consumption and CO2 

production, catecholamine excretion). 

2. Valsalva maneuver. Airway pressure should 

be recorded (one channel-strain gauge). (Response observed in 

ECG-heart rate, manual blood pressure). 

b. Test Support Equipment Required 

(1) Spacecraft - no requirement. 

(2) Age - no requirement. 

(3) To be determined. 

c. Test Procedure 

(1) Continuous real time monitoring of ECG and blood 

pressure from the Gemini vehicle must be performed during launch 

and re-entry. This is a mission safety requirement and will also 

provide data concerning cardiovascular tolerance for comparison 

with G profile centrifuge runs prior to the mission. Oximetry should 

be recorded on tape aboard the Gemini during launch and re-entry. 

The re-entry phase is especially important in that the effects of prolonged weightlessness on transverse G tolerance can be assessed 

using a measurement of arterial oxygen saturation which is most 

likely to be seriously deranged. 

(2) Heart rate should be monitored constantly or at least 

during long periods involving recurrent performance of the same 

astronaut functions throughout the missions and sampling all forms 

of activity. This will provide means of amassing a large volume of 

data for machine analysis of directional changes in response of the 

cardiovascular system. HF telemetry would provide continuous real 

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time data with few receiving stations, and would allow simple computer detection of significant rate and rhythm changes indicative 

of danger. In any case this system must-be available for medical 

emergencies in real time. Respiratory rate is a fall-out measurement 

obtainable by this technique. 

(3) Blood Pressure. Either the automatic or manual blood 

readout should be obtained with each recording of ECG-BCG at rest 

and after exercise, and with the Valsalva maneuver the manual system 

will be used. 

This parameter must also be available for real time 

transmission in event of an emergency. 

(4) ECG-Ballistocardiogram. At each measurement as programmed below the three simultaneous EGG leads would be recorded 

for 30 sec. on each astronaut, following which one lead (orthogonal 

projection selected for each individual) of ECG and BCG would be 

simultaneously recorded for 30 sec. The taped data could then be 

dumped to ground on a convenient fly-over later in the same day. 

This program should be performed. as soon as possible 

and at +6-8 and t 24 hours after entering orbit.. At the t 24 hour test 

a second and third program, each to run for 2 minutes should be 

obtained immediately after programmed exercise and with and following a 30 second Valsalva maneuver. 

At the same Greenwich hour as the t 24 hour test, 

an identical rest, exercise and Valsalva program should be transmitted on approximately the 3rd, 5th, 7th, 10th, 15th, 20th and 

25th days. On the 29th day (assuming re-entry on day 30) the 

same recordings would be repeated, and if blood volume and other 

measurements indicated the need for administration of plasma 

expander or other reparative measures prior to re-entry would again 

be performed on day 30. Consideration should be given to the 

possiblity of resting measurements of ECG during partial G suit 

inflation immediately prior to re-entry. 

Tho ECG must be readily available for emergency 

use, all throe channels, on a roalahtime basis. 

(5) Body Mass, Body Volume), Total Body Water, Blood 

Volume 

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There measurements will be made four times during a 

30-day mission, on approximately the 2nd, 9th, 20th and 29th days of 

weightlessness. Hematocrit will be simultaneously determined. The 

measurement should be made under standard conditions relative to 

ground time, probably fasting and with controlled fluid intake during 

the previous 12 hours. The final determination will indicate the need 

for infusion of a plasma expander or for other protection prior to 

re-entry. 

Three hours for equilibration of the tracer dose of 

D20 for total body water should be allowed prior to blood sampling 

for blood volume. The urine formed during the last hour of this 

equilibration or serum drawn for dye concentration may be used for the 

mass spectrometric analysis. Results of dye and D20 dilution analyses 

and body mass and volume data may be transmitted on later passes by 

voice or digitally keyed. 

(6) Cardiac Output will be simultaneously determined with 

blood volume. The dose of T-1824 should be administered in two 

increments, after warming the arm to increase flow rate, one at rest 

and one immediately after programmed exercise to allow indicator 

dilution recording from the earpiece. 10-15 minutes after the exercise 

injection a venous sample for blood volume is obtained. ECG, blood 

pressure and oxygen consumption - CO2 production should be obtained 

with or immediately after the indicator dilution curves. Taped record 

may be dumped later. Routine oxygen saturation should be obtained 

prior to dye injection. 

(7) Venous pressure should be measured at rest when the 

blood blank for blood volume determination is m,ade. Strain gauge 

calibration and signal may be taped for later telemetry. 

(8) Urinary catecholamine excretion should be performed on 

aliquots of urine formed during launch, at rest and during exercise 

after adaptation to weightlessness on about the sixth and 25th days, 

and during re-entry. The first three samples must be freeze-dryed 

and stored for return and ground analysis. 

(9) Oxygen consumption-CO2 Production will be determined 

with cardiac output above and as programmed under metabolic and 

pulmonary sections. 

(10) General. All of the above MOL parameters will require 

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participation of both astronauts, either as subject or tester, with the 

exception of the heart rate measurements. (See attachment 3 - not 

applicable). 

d. Category of Experiment 

All phases listed are Category A or B. 

e. Cost - To be determined. 

f. Schedule 

(1) Instruments ready for test-by July 1965. 

(2) Instruments and software flight ready by July 1966. 

IV. Participating Agencies 

Sponsor: AMD - Lt Colonel John W. Ord, USAF, MC, Wilford Hall 

USAF Hospital, Lackland AFB, Texas. 

Test Equipment Acquisition: AMD. December 1964. 

V. Additional Requirements 

A. Special security - Some aspects of instrumentation details 

will require Secret classification, and all will be considered limited 

medical access. 

B. Manning Description Summary - Reference attachment 5. 

C. Logistics - To be determined. 

D. Facilities - Existing facilities are adequate for all phases of 

preflight testing and training except for the need for a mock up MOL 

within an altitude chamber for actual mission testing and rehearsal. 

A Gemini flight simulator will also be required. Requirement may 

develop for a central laboratory facility for intricate metabolic 

analyses. 

E. Simulation and Training 

1. Astronaut. The experiments listed require technician 

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level training only, and are not of a difficult or complex nature. The 

results do not require on board interpretation by the astronauts. The 

training will entail instruction, demonstration, supervised practice 

and application in mission simulation. One hour weekly for eight months 

is a gross estimate of time required for training. 

2. Ground Personnel. Physicians will monitor the data 

and provide immediate interpretation. Minimal training will be required 

for carefully selected personnel. Special training in specific analytic 

procedures for ground analysis of metabolic balance samples will need 

to be provided for both physicians and medical technologists. 

3. Equipment. Training equipment should for the most part 

be actual mission equipment. Conventional instruments may be employed 

for theory and early phases of demonstration and practical training. 

VI. General 

A. Communications and Data Handling Requirement. Frequency band 

widths required have been indicated. With the exception noted, all of 

the data may be taped on board and dumped at a single biomedical ground 

facility when convenient. The limited real time requirements for 

monitoring and emergencies have been identified and indicate a need for 

3 or 4 stations capable of receiving one or two channels of biomedical 

data. The desirability of a single HF channel for constant telemetry 

is indicated. Relatively simple digital machine analysis may be 

required. 

B. Development Characteristics. - To be determined. 

C. Reference la, Atch 1; lb(3), Maki_ 2; le, Atch 4 and VI A, 

Atch 6 - To be determined later. 

D. Reference Annex 1, Study of the Cardiovascular Effects 

Resulting from Missions of MOL Duration. 

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Attachments 1 • 4 (To be determined) 

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MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required; Two per mission. 

(1) Man's function 

(a) As part of test - yes. 

(b) As technician conducting test - yes. 

b. Crew skill requirements - limited medical technician. 

c. Manpower Profile - To be determined. 

d. Critical Functions - see basic document and Annex 1. 

e. Work Positions - see basic document and Annex 1. 

f. Time Controlled Tasks - see basic document and Annex 1. 

g. Human Performance Measures - not applicable. 

h. Physiological and Psychological Measures - not applicable. 

1. Selection Factors - see Annex 1. 

J. Training Requirements - One hour weekly for 8 months prior 

to flight. Using flight equipment in and out of simulators. 

2. GROUND PERSONNEL 

a. Number required: To be determined. 

(1) Man's function 

(a) As part of test - in training of astronaut and 

interpreting flight data. 

(b) As technician conducting test in training of 

astronaut. 

Sec 1, Attachment 5 

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b. Crew skill requirements - physician, medical technologist. 

c. Manpower Profile - To be determined. 

d. Critical Functions - Interpreting flight data, ascertaining 

accuracy of inflight and postflight measurements. 

e. Work Positions 

f. Time Controlled Tasks 

g. Human Performance Measures 

h. Physiological and Psychological Measures 

i. Selection Factors - see Annex 1. 

J. Training Requirements - see Annex 1. 

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2. Study of Central Nervous System and Motor Effects Resulting 

from Flights in MOL 

In the final analysis, man's utility in space is dependent on his 

nervous system. It is with his nervous system that he detects changes 

in his environment, whether they be events taking place at a distance 

or near at. hand, such as the movement of a pointer on a dial. With 

this information he can make calculations, comparisons, and evaluations which will ultimately lead to an executive decision, The decision 

to act will require use of his sensorimotor apparatus, such as adjusting a vernier or throwing the proper switch. Measurements of 

nervous system activity are necessary to evaluate the ability of the 

brain to function during prolonged exposure to weightlessness. 

The following tests will be done: 

(1) Electro-oculograms (EOG) 

(2) Egocentric visual localization of the horizon (EVLH) 

(3) Sleep electroencephalograms (EEG) 

(4) Muscle tone measurement 

(5) Muscle strength measurement 

(6) Motor coordination 

(7) Intellectual functions 

When the aforementioned test results are obtained and compared 

to the astronauts prelaunch measurements, the manner in which his 

nervous system was affected by prolonged weightlessness can be judged. 

Problems which might he encountered cannot be predicted with 

certainty, but a reasonable approach would start with the gravity sensing 

organs and lead to the nervous system circuits with which they are 

immediately concerned, viz; ocular control, postural tone, sensorimotor movements, and possible disorders of sleep and respiratory 

regulation. A group of less predictable problems concerns nausea, 

vomiting, disorientation, and vestibulogenic convulsions. 

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a. Configuration of Test Items(see attachment 1) 

(1) Miniaturized DC amplifier weighing less than 50 gms. 

with electrodes and wire leads. Volume of 1 cu. inch. Located on 

bulkhead in MOL. 

(2) EVLH weighing less than 50.gms. Volume 4" x 2" x 1". 

Stored in MOL. No power required. 

(3) Sleep EEG. Weighs approximately 50 gms. Size and 

shape of silver dollar. In addition, a headband. Located in MOL. 

(4) Muscle tone scale. When stowed will occupy 3" x 1" x 1". 

Weighs 50 or less gms. No power requirements. 

(5) Muscle strength. When stowed will occupy 4" x 1" x 3" 

and weigh approximately 50 gms. No power required. 

(6) Motor coordination. No equipment necessary. 

(7) Intellectual functions (per Dr. Bryce 0. Hartman). A 

panel box 18" x 10" x 8". Weighs 4 pounds. Located in MOL. 

b. Test Support Equipment Required 

(1) Spacecraft 

(a) FM tape recorder to store EOG and EEG until transmission to earth. (PCM is equivalent) 

(b) AM voice tape recorder to stare results of EVLH, 

muscle tone, muscle strength, and motor coordination until transmission to earth. 

(c) A bi-valve or harness-and-tether to stabilise astronaut near EEO amplifier when sleeping. This should include rubber 

bands to keep hands from drifting near head when asleep. 

(d) Dispenser with die-cut rings of colostomy tape (3M) 

for attaching electrodes. 

(e) Disposal system for taps rings after each use. 

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(f) Tube of electrolyte paste (Redux) with hollow needle 

tip cap for dispensing. 

(g) Small vacuum cleaner for removing dried paste from 

skin and electrodes. Can be modified vacuum-operated shaver. 

(h) Circular-head shaver (Norelco-type) for shaving 

electrode-scalp sites. Can be same shaver used for beard. 

(2) AGE 

(a) FM or PCM tape recorders to store EOG and EEG data. 

(b) AM voice tape recorders to store readings from muscle 

tone, muscle strength, motor coordination tests, and EVLH. 

(c) Tape recorder to store results of intellectual functions 

test. 

(d) Medical examination room near launch area. 

(e) Grass EEG machine in or near medical examination 

area. 

(f) EEG write-out machine to yield paper tracing at time 

EEG is transmitted to earth. To be used to monitor sleep adequacy 

by EEG during the flight. 

c. Test Procedure 

In the months prior to launch, serial sleep EEG's will be 

obtained on each astronaut so that their EEG sleep profile is familiarized. Excerpts from various stages of sleep may be mounted in 

celluloid and bound so a sleep reference on each astronaut is readily 

available. A complete neurological examination is done the week 

before the flight. Muscle tone, strength, and coordination scores will 

be recorded. 

During the flight, the seven measurements noted in III will be 

carried out, always watching the relationships between the new data 

and the data obtained prior to the flight. 

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After recovery, a complete neurological examination will 

be done. Serial EEG's will be made. An interpretation of the data 

will result. 

Man's role will be both active (applying electrodes, using 

equipment, recording observations) and passive (generating brain 

potentials while asleep). He will be utilized as both subject and as 

observer. His contributions will be measurectby comparing the 

measurements obtained on the flight with those obtained prior to 

the flight. _ 

- Testing sequence. The neurological testing sequence will 

begin 20 minutes before his sleep period. He will apply the two periorbital electrodes and record eye movements when viewing first a 

distant object, then a near object. Next, he will move his eyes 

through a full range in the vertical and horizontal planes and maintain 

end point conjugate positions for 10 seconds each. The electrodes 

are removed. 

Dur.ing the 10 minutes the electrodes are stabilizing, he will 

perform the intellectual functions tests per Dr. Bryce 0. Hartman. 

The astronaut next puts on the EVLH instrument and records 

his subjective horizon. 

The muscle tone instrument is put in place and finger flexor 

tone is measured. The hand grip dynamometer is used next. Then, 

finger-to-nose and heel-to-toe tests are done. Finally, the EEG is 

applied to his scalp by his fellow astronaut and he goes to sleep. 

Upon awakening, the EEG is removed, ending the neurological sequence. 

d. Category of Experiment 

(1) Category a. 

e. Cost. To be determined. 

f. Schedule 

(1) Hardware and software available for test: 

1 Grass EEG machine needed for ground tests in the week 

prior to launch. 

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1 EEG technician needed to operate the EEG machine. 

1 FM tape (7-channel) recorder, Ampex FR1300 

1 Electronic Coupler for tape recorder 

1 3" oscilloscope to check signal reaching the tape 

1 Neurologist 

1 Secretary to handle the large paper workload. 

Paper, ink, electrodes, collodion, and other expendables 

1 DC recording Offner EEG for EOG's and portable work 

(2) Hardware and software flight readiness date. 

Should be ready 3 months prior to the flight. In addition 

to the hardware necessary for the flight, there should be 2 identical 

replacements for each on-board piece of equipment used in the CNS 

studies. 

IV. Participating Government Agencies 

Sponsor: U. S. Navy (Captain Ashton Graybiel), Pensacola, Florida 

Test Equipment Acquisition: The EVLH device 

V. Additional Requirements 

a. Special Security. None 

b. Manning Description Summary. (see attachment 5) 

c. Logistics: CY 64 CY 65 CY 66 TOTAL 

(1) Manpower. To be determined 

(2) Hardware Development. To be determined 

(3) Installation. To be determined 

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(4) Operation. To be determined 

(5) Additional Support. To be determined 

d. Facilities 

Need only a medical examining area and the EEG facilities 

one week prior to launch to perform the preflight neurological evaluation on the astronauts. During the flight itself a facility will be 

needed where the EEG write-out in real-time can be visually Interpreted. 

This can be located near the launch area or at the USAF School of 

Aerospace Medicine, Brooks AFB, Texas. 

e. Simulation and Training 

(1) Astronauts. He would not have to be a scientist, he can 

be trained as a technician. Level of knowledge need not be high. 

Motive is more important; he must want to do the medical tests well. 

A single knowledge of electronics whould be desirable. Training 

could be accomplished by three hours of lectures, three hours of 

demonstration, and three hours of participation by the candidates 

themselves. Finally, the 30-day run in the MOL mock-up under 

every condition of the flight itself (except actual blast-off and prolonged weightlessness) will be mandatory for his training. 

(2) Ground Personnel: 

For the sleep study: EEG technicians should, at the 

minimum, be Air Force-trained and then have an additional 3 months 

OJT training and lectures at SAM. 

Neurologist, trained in the usual manner. 

(3) Equipment: 

The equipment peculiar to the training situation is 

identicle to that used in flight. 

VI. General: 

a. Communications and Data Handling Requirement. (see attachment 6) 

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(1) FM or PCM tape storage is required on board to store 

sleep EEG until spacecraft can transmit it to earth receiver, 

(2) Earth telemetry receiver compatible with the spacecraft 

transmitter. 

(3) FM tapes to store all EEG data for later processing 

(4) EEG write-out, pen and ink, paper speed 30 cu. /sec. 

for real-time visual interpretation. 

(5) FM or PCM tape recorder on board to record DC EOG's 

until transmitted to earth. 

(6) Earth receiver and FM tape recorder to store EOG data. 

(7) Paper, pen, ink write-out system for EOG data for realtime interpretation. 

(8) Voice tape recorder on board to record muscle tone, 

strength, and coordination for later transmission to earth. 

(9) Tape facilities for storing high functions scores for late 

analysis. 

(10) Write-out device to chart trends of higher functions 

scores in real-time. 

(11) Voice transmission link from medical officer to space 

laboratory to counsel astronauts in the event of neruological emergency on board, such as a convulsion. 

b. Development Characteristics. (see attachment 7) 

c. Refer to Annex 2 - Study of Central Nervous System and Motor 

Effects Resulting from Flights in MOL, for more detailed discussion of 

this area. 

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DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED: Miniaturized EEG, miniaturized 

DC EOG, muscle tone scale, muscle strength dynamometer, EVLH, 

and intellectual functions test box. 

2. WEIGHT: Weight of all test equipment, exclusive of intellectual 

test functions box, should be less than 400 gms. 

3. VOLUME: Stored: Less than 20 cu. inches. In Use: Less than 

15 cu. inches. 

CRITICAL DIMENSIONS - SHAPES: EEG the shape of a silver 

dollar with rounded edges so that chances of it catching on anything 

are minimized. A headband will aid stability. 

4. POWER: The EEG and the EOG would draw power of a few milliwatts. Of course, voice recording the readings of the muscle tone, 

muscle strength, and EVLH scales will require power to operate the 

AM voice tape recorder. Intellectual functions box of Dr. Hartman 

will draw power to be determined. EEG would draw a few milliwatts 

of power throughout the 6 to 8 hours of sleep. 

5. SPARES: No spares aboard the aircraft. Two spares of every 

piece of equipment needed for central nervous system study should 

. be available on the ground prior to launch. 

6. TOOLS: No tools required. 

7. HEAT OUTPUT: Negligible. 

8. STABILITY: No factor, except in EEG and EOG where attempts 

will be made to attach the equipment to the scalp surface as mechanically stable as is possible. 

9. VIBRATION LIMITS: EEG will measure the slightest vibration 

causing a change in the impedance between the scalp electrode and 

scalp surface. Vibration should be kept minimal, 

10. SHOCK LIMITS: To be determined. SSTA- 1 -9 

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11. HAZARDS: Hazards are minimal. Electrodes will be fastened to 

the scalp with colostomy tape made by the 3M Corporation rather than 

by collodion or other adhesive with a volatile solvent. Electrode paste 

is of the Redux variety and contains no known toxic products. 

12. TEMPERATURE LIMITATIONS: Both the EEG and EOG will be 

adversely affected by temperatures which will produce visible perspiration on the skin of the astronaut. 

13. TYPE AND RANGE OF MEASUREMENT: Scalp voltage changes 

from 0.5 cps to 100 cps will be measured. EOG will measure a dipole 

of 500 to 800 millivolts at the source, but probably greatly reduced at 

the point of measurement. Muscle tone will be measured in grams. 

muscle strength in grams, and other measurements will be digital. 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS: Temperatures 

between the range of 65° to 75' F. are ideal for the CNS tests. 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: 

Station: The test stations should be located where the astronaut 

will sleep. 

Equipment: Equipment should include a bi-valve or harness to 

stabilize the astronaut when he sleeps so that he will not drift away 

or twist the leads. In addition, rubber thongs should hold his hands 

so that he will not involuntary pull the electrodes while asleep but is 

able to free himself quickly in an emergency. 

16. EQUIPMENT OPERATING CYCLE: 

Frequency: EEG will be used on Astronaut "A" every 48 hours 

and should alternate with Astronaut "B" every 48 hours so that one 

sleep EEG is done every 24-hour cycle. Other neurological tests are 

keyed to the astronaut's sleep in a similar fashion. 

Time Duration; Time duration is listed more clearly in description of the experiment. 

17. EQUIPMENT LOCATION REQUIREMENTS: Again this is required 

near where the astronauts sleep. 

18. SPECIAL MOUNTINGS REQUIREMENTS: The amplifiers will 

be mounted on a bulkhead near the head of the astronaut when he is 

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asleep. The EOG amplifier should be mounted on a bulkhead near 

the porthole so the astronaut may view outside the spacecraft while 

his eye movements are being recorded. It would be nice to have 

this porthole window near where the astronaut sleeps so that CNS 

equipment could be centralized. 

19. PRESSURE VESSELS - fluids, gasses, etc. N/A 

20. ELECTROMAGNETIC INTERFERENCE: This is critical for 

EEG. Electric field alternating at a frequency of 1 to 200 cycles per 

second are bothersome. Sparking commutators, discharge gas tubes, 

magnetos, will all interfere with the EEG if not shielded or too close 

to the astronaut's head. 

21. MAINTENANCE REQUIREMENTS: Electrodes will have to be 

kept clean of particulate matter after each use and the colostomy 

tape discs used for affixing them to the scalp will be disposed of 

after each use. 

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TEST SUPPORT EQUIPMENT 

I . RECORDING.MEDIA • 

a. FM or PCM tape in addition to AM or voice recording tape. 

b. N/A 

c. 

2. HANDLING (special equipment required to handle items being 

tested). Usual handling of magnetic tape. 

3. PACKAGING. The usual required for handling recording tapes. 

4. CALIBRATION - alignment, deployment. This will be done prior 

to launch. 

5. JIGS AND FIXTURES. Not applicable. 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION. Not 

applicable. 

7. SENSORS (TRANSDUCER - OUTPUT SIGNALS). Not applicable. 

8. TRAINERS/SIMULATORS. Not applicable for the inflight study. 

9. INSTRUMENTATION - cockpit and/or laboratory (note effect of 

time sharing instruments with other experiment). Not applicable. 

10. RELATED SUPPORT EQUIPMENT. As better described in the 

experiment. From the ground will be required appropriate telemetry 

receivers and FM tape recorders to permanently store the EEG, EOG, 

and AM tape recorders to store information from E.V.L.H. muscle 

tone, testing, muscle strength testing and motor coordination tests. 

Dr. Hartman will want intellectual functions stored on tape on 

the ground in addition. 

11. AGE - not applicable. 

12. ENVIRONMENTAL TEST EQUIPMENT. Not applicable. 

13. FACILITIES. Not applicable. 

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TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired). Not critical. 

a. Altitude - 

b. Inclination - 

c. Epoch - 

d. Ellipticity - 

2. PLANE CHANGE. Not critical. 

3. ALTITUDE CHANGE: Not critical. 

4. TIME ON ORBIT. Not critical. 

5. TEST DURATION. Entire test can be performed 20 minutes prior 

to the sleep period and then EOG recording throughout sleep, 6-8 

hours. 

6. TOTAL NUMBER OF TESTS. Each astronaut will get a series of 

neurological tests once every 48 hours. 

7. TEST FREQUENCY. Each astronaut will get neurological sequence 

of tests every 48 hours. 

8. INTERVAL BETWEEN TESTS. Each astronaut will get test once 

every 48 hours. 

9. CREW TASK LOADS - man hours. Twenty minutes every 48 hours 

and then entire sleep period of 6-8 hours► 

10. CREW TASK FREQUENCY. Once every 48 hours. 

11. FIELD OF VIEW REQUIREMENTS. Not critical. 

12. GROUND CONTROL LIAISON DURATION. Not critical except 

during a medical emergency. 

13. GROUND CONTROL LIAISON FREQUENCY. Not critical except 

during a medical emergency. 

Sec 1, Attachment 3 

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14. EXTERNAL TEST ITEMS: 

a. Launched from Station - none. 

b. Launched from resupply - none. 

c. Launched from ground - none. 

15. QUALIFICATION TESTS (other than space) 

a. Ground - none. 

b. Atmosphere - none. 

16. SEQUENCE OF EVENT AS THEY OCCUR DURING FLIGHT. This is 

described in the sequence of events in the experimental-package. 

17. HANDLING PROCEDURES. Not applicable. 

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FUNDING SUMMARY 

BUDGET REQUIREMENTS BY FISCAL YEAR 

To be determined. 

Sec 1, Attaclu-nent 4 

Page 1 

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MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required - one is a minimal requirement. 

(1) Man's function 

(a) As part of test - subject. 

(b) As technician conducting test - the same 

astronaut is also the technician. 

b. Crew skill requirements - Very few. skills requirements are 

necessary. Critical is the application of the instruments to the 

scalp, of the skin near the eyes and in applying the muscle tone 

cables. 

c. Manpower Profile - Not applicable. 

d. Critical Functions - Applying the scalp electrodes properly. 

e. Work Positions - In the sleeping position. 

f. Time Controlled Tasks - None. 

g. Human Performance Measures - In a sense everything is a 

human performance measure. 

h. Physiological and Psychological Measures - Should meet the 

psychological and physiological requirements of a pilot candidate of 

the USAF. 

i. Selection Factors - Should meet the qualifications of a pilot 

in the USAF. In addition, he should have a very high motive for 

performing medical tasks on himself. 

j . Training Requirements - This is better described in the 

experiment package. 

2. GROUND PERSONNEL 

a. Number required 

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(1) Man's function 

(a) As part of test not applicable. 

(b) As technician conducting test - Not applicable. 

However, a neurologist should be interpreting the sleep EEG in realtime to detect any serious deviations from normal. In addition, the 

data sent back on muscle tone, muscle strength, EVLH, and motor 

coordination as well as intellectual functions should be charted on 

a graph in real-time so that the general trends of the CNS are 

obtained in real-time. 

b. Crew Skill Requirements - Neurologists familiar with the 

astronaut's EEG sleep patterns is required. 

c. Manpower Profile - not applicable. 

d. Critical Functions - not applicable. 

e. Work Positions - On the ground near EEG write out from 

radio telemetry set. 

f. Time Controlled Tasks - None. 

g. Human Performance Measures - In.a sense, everything 

is human performance. 

h. Physiological and Psychological Measures - Not critical. 

i. Selection Factors - not critical. 

J. Training Requirements - Usual training requirements for 

a neurologist. 

Sec 1, Attachment 5 

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COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE. Data should be transmitted to the earth as often 

as possible so that tape recorder storage facilities on board need not 

be too large. Neurological tests will require data for 20 minutes 

out of every 48 hours for a given astronaut. Interdigitated will be 

date from the other astronaut every 48 hours, thus 20 minutes plus 

a full sleep period will come down every 24 hours from the space 

ship if two astronauts are aboard. 

2. FUNCTIONS TO BE MEASURED. There are seven areas to be 

measured: (1) EEG, (2) EOG, (3) Muscle Tone, (4) Muscle 

Strength, (5) EVLH, (6) Motor Coordination, and (7) Intellectual 

Functions. 

3. TYPE OF ANALYSIS REQUIRED. Real-time visual analyses of the 

data is required during the time the neurological tests are being performed during the 24 hour cycle. 

4. PICTORIAL DATA REQUIRED. An analog record of the EEG 

during sleep. is required. 

5. REAL TIME MONITORING REQUIREMENT. Real-time monitoring 

. requirement for all the neurological tests is desired. 

6. DATA EDITING OR COMPRESSION. Not applicable. 

7. READ OUT TIME. This depends entirely on the capability of the 

equipment available. The EEG write out should have a paper speed 

of 30 centimeters per second. Pen and ink writers are preferred 

over the heat stylus and wax paper. 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS. FM or PCM 

tapes are required for permanent records of EEG .and EOG. AM or 

voice tapes are required for the other data for the neurological tests. 

9. MANUAL AND/OR AUTOMATIC CONTROL. Not applicable. 

10. SIMULTANETTY. Not applicable. 

11. GROUND COMMANDS REQUIRED. None unless a medical 

emergency arises. 

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DEVELOPMENT CHARACTERISTICS 

I. DEVELOPMENT TIME. One year. 

2. FINAL DEFINITNE TEST DESIGN TIME. One year. 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED. Ground 

testing concerning the inlflight package is primarily aimed at 

astronaut training and familiarization with the use of the simple 

pieces of equipment needed in the central nervous system as 

programmed. As stated in the training session this will require 

3 hours of instruction, 3 hours of demonstration. and 3 hours 

of participation. After this preliminary approach a full scale 

flight in the MOL mock-up inside the vacuum chamber is 

necessary for final corrections to be made . No flight test 

would seem necessary at this time. 

4. TYPE OF DEVELOPMENT TEST ITEMS. The miniaturized EEG 

would need to be developed only from a standpoint of small space 

and size and low power requirements. Basic configuration.(i.e., 

that of a differential amplifier) is well known and needs no further 

development. The muscle tone gauge would have to be fabricated 

at the SAM workshop, but being of simple design and consisting 

only of a.spring and cable with graduated scale and pointer, 

should prove no real problem. Stoelting hand grips dynamometer 

exists. 

a. Vacuum Chamber 

b. Shaker 

c. Thermal 

d. Acoustic 

e. Simulators 

f. Aircraft 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME. To be determined. 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test - Not applicable. SSTA-1-9 

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Sec 2, Attachment 7 

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b. Atmospheric Test - Not applicable. 

c. Space Test - This will be the test itself. 

7. DATE AVAILABLE FOR TESTS. End of 1965. 

8. CURRENT DEVELOPMENT STATUS 

a. Proposed only - 

b. Project or program is approved and test item is under 

study, breadboard stage, etc. - 

c. Funds expended to date - 

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3. Study of the Gastrointestinal Effects Resulting from Missions of 

MOL Duration 

This experiment intends to determine the degree of alteration, if 

any, in the human gastrointestinal tract during the stresses of prolonged 

orbital flight. The specific parameters to be observed and investigated 

are nutrition, digestion, absorption and excretion. The experiment is 

deliberately designed to interface with tests being performed in the 

metabolic, renal and cardiovascular areas so that the knowledge compiled by the biomedical panel will give the broadest possible basis for 

assessment of the physiologic responses of man during the MOL mission 

with the least possible expenditure of time during the MOL flight 

(flight safety). By examination of the pre-flight, in-flight and postflight biomedical data, it is anticipated that extrapolation will be 

possible to allow reliable predictions concerning man's status during 

longer flights (growth potential). 

Considerable knowledge concerning function of the gastrointestinal 

tract may be obtained by providing a diet which contains known amounts 

of calories, protein, carbohydrate, fat, vitamins and minerals and 

measuring the level of constituents in the blood and the amount of 

excreted substances in feces and urine. This "in-flight" metabolic 

balance study is considered essential to assess the multiple body 

systems of man for 30 days of weightless existence. This particular 

experiment intends to feed the astronauts a diet containing known 

nutritional constituents and several non-toxic test materials; to collect 

and return all feces in a lyophilized form and all urinary solids in a 

similar form; and to analyze these wastes for the test materials and 

other organic constituents. No in-flight monitoring will be necessary. 

An accurate record of diet must be provided in a daily taped report in 

order to insure that the occupants of the MOL are consuming adequate 

nutrients. The astronauts will serve as their own controls during the 

experiment. Pre-flight and post-flight studies are imperative in order 

to establish an assessment of the overall effect of prolonged space 

flight. 

a. Configuration of the test items 

(1) Diet 

It is anticipated that a 2400 Kcal liquid diet, reconstituded in flight, will be used (Ref. Annex 3), although ground tests 

and Gemini-Apollo flights may prove that a freeze-dehydrated diet is 

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more acceptable. This liquid diet will contain approximately 70 gm 

protein, 300 gm carbohydrate and 100 gm fat. It will be artifically 

flavored with reasonable variety and palatability, will be fortified 

with vitamins and minerals and will contain less than 500 mg of 

calcium in order to reduce the degree of hypercalcemia and hypercalciuria anticipated from calcium mobilization in the weightless 

state. The diet will be consumed 4-5 times daily- and will utilize 

250 ml. of water for reconstitution at each feeding. Assuming a 

water allowance of 2500 ml/man/day,. there will be 1250-1500 ml/ 

man/day remaining for drinking and washing. Space requirements 

in the MOL for such a liquid diet are not well determined but are 

anticipated to be appreciably less than an isocaloric amount of 

freeze-dehydrated food. It is anticipated that space requirements 

for freeze-dehydrated foods on the. Gemini and Apollo vehicles are 

already determined. Since freeze-dehydrated food may be found 

to be satisfactory for Gemini flights and estrapolation allows their 

use on MOL flights, weight and volume specifications should be on 

the basis of freeze-dehydrated foods. (See Atch 1, "Design Characteristics"). 

(2) Ingestible test doses 

One ingestible test dose is considered: d-xylose 

(a pentose). This substance may be pre-packaged in granular form 

in the diet packet, dissolved in water and consumed as part of.the 

diet at a specified time in flight, but since the diet may delay gastric 

emptying, it is advisable to have the test dose taken as a solution 

in a fasting (6 hour post prandial) state. The urine is to be collected, 

lyophilized and returned. No in-flight analysis of this test is 

necessary. 

Two (2) twenty-five (25) gram packets of d-xylose occupying 

42.5 cubic centimeters of space each (total space 85 cubic centimeters) 

if packaged in plastic wrapper anti reconstituted in flight are required. 

The d-xylose may be pre-packaged in a plastic container separated 

from 250 ml. of water by a diaphragm. When the diaphragm Is punctured, 

the water will be mixed with the sugar, producing a palatable solution 

which may be consumed by means of a drinking spout. Such a container would occupy a total space of approximately 350 cubic centimeters 

and weigh approximately 300 grams. Total space and weight requirements for two astronauts would be 700 cubic;centimeters and 600 grams. 

Tablets of d-xylose are not recommended since crumbling of the tablets 

poses a threat of aspiration to the astronaut. Furthermore, since the 

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test is a function of time, and a certain delay due to dissolution of 

the tablet in the stomach will occur, the test results may be 

invalidated. 

(3) Injectable test doses 

No injectable test doses are necessary for this 

particular experiment but an injection of tracer substances requiring 

recovery of urine and feces is considered by the metabolic section. 

(4) Blood 

Collection of 10 ml. of venous blood (total) from each 

astronaut is necessary for analytical study by the metabolic section, 

the renal section and the gastroenterology section on days 2, 7, 14, 

21 and 26. From the serum recovered after coagulation and centrifugation, analysis of calcium, alkaline phosphatase, bilirubin (conjugated 

and unconjugated), 5-nucleotidase, serum transaminases (SGOT and 

SGPT), urea, amylase, lipase, lactic dehydrogenase and protein 

electrophoresis will allow indirect evidence of hepatic and pancreatic 

function, during the weightless period as well as provide information 

concerning hematopoetic activity, bone activity and hepatic parenchymal 

degeneration. No in-flight analyses are necessary for this portion of 

the experiment. The serum is to be lyophilized, packaged, labeled 

as to content, subject, date, and time and must be returned in the 

Gemini vehicle for analysis and comparison with pre-flight and postflight determinations. 

(5) Urine 

No in-flight analysis of urine is necessary for this 

experiment. The lyophilization and return of urine for post-flight 

analysis is extremely important to this experiment however, for 

constituen:s in the urine can give indirect evidence of hepatic and 

pancreatic function. intestinal microfloral activity and intestinal 

absorptive ability. Analyses to be performed on the returned urine 

includes: 5 hydroxy indole acetic acid. indole acetic acid, indicant 

calcium, sulfur, 24 hour uropepsln, amino acids, urobilinogen, bile 

and d-xylose. The total urinary solids to be returned for use by the 

gastroenterology, renal, and metabolic sections will be approximately 

1800 Gm/man/month (total weight 3600 Gms). Total volume of these 

dried urinary solids is approximately 2000 cubic centimeters. 

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(6) Feces 

The total accumulation of feces produced by each 

astronaut during the mission must be lyophilized and returned for 

analysis in order to evaluate the gastrointestinal and metabolic 

function of the individual 'during the mission. No in-flight fecal 

analysis is necessary for this experiment. Approximately 900 Gms 

of dry feces/man/month will be produced (total weight 1800 Gms 

occupying approximately 1000 cubic centimeters of space). Postflight analysis will include the determination of bile pigments, total 

fat and partitioned fat (neutral fat, fatty acids, etc.), and trypsin. 

Bacterial cultures for viable clostridial spores, etc. will also be 

performed. These analysis will give indirect information concerning 

intestinal absorptive capacity, pancreatic function, hepatobiliary 

function, and intestinal microflora activity. 

b. Test Support Equipment Required (See Atch 2) 

(1) Spacecraft 

(a) Diet: Storage space for diet should, for purpose 

planning, be the same as that for Gemini. It is conceived that the 

diet will be labeled in a digital form, identifying total calories and 

constituents. The diet consumed by each man is to be recorded on 

tape and data dumped each 24 hours. Appropriate tape for biomedical 

data is necessary on board. Details for separating biomedical data 

from other data should be developed to facilitate analysis each 24 

hours at the ground based biomedical center. 

(b) Lyophilizer with water recycling equipment: At 

present, there is no apparatus designed for incorporation into the 

MOL vehicle. Development is imperative for the performance of 

this experiment. 

(c) Centrifuge for blood specimens: Development 

is imperative. 

(d) Containers for lyophilized stool and urine: 

These containers should be flexible, leakproof, easily labeled, and 

capable of being placed on board the Gemini vehicle for return. 

Plastic containers appear to be the most satisfactory type at this 

state of the art. 

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(e) Labeling equipment: Small marking pencils 

similar to the commercial "Magic-Marker" appear to be ideal for 

labeling containers, especially plastic ones. 

(2) Ancillary Ground Equipment 

Ancillary ground equipment necessary for this experiment during the flight consists of a receiving station for biomedical 

data. Post-flight analysis of the specimens will require a laboratory 

of the highest reliability. Such a laboratory could be developed from 

in-service sources, combining the talents of the USAF Epidemiological 

Laboratory, SAM and Wilford Hall USAF Hospital. 

c. Test Procedure (See Atch 3, "Test Operating Factors") 

(1) The occupants of the MOL are to consume a diet 

containing approximately 2400 Kcal each 24 hours. Each astronaut 

will carefully record his dietary intake by reciting the digital coded 

label of the packages he consumes onto data tape. If he is unable 

to consume all of his diet, he will measure the residual by placing 

it into a volumetric measuring device, record the amount of unconsumed 

liquid on data tape, and discard the waste. Calculations of calories, 

etc. lost can be made at the biomedical data area. Every encouragement will be given to the occupants to consume all of the diet once 

it is reconstituted. 

(2) All feces produced during the flight will be collected, 

emulsified and lyophilized. It has not been determined whether each 

individual stool should be immediately lyophilized or whether the 

collective stools from each astronaut should be lyophilized each 24 

hours. When the packet containing the stools is lyophilized, it 

should be labeled as to subject, time, date and then stored. At the 

completion of the flight, the packets should be placed on board the 

Gemini vehicle and returned for analysis. Space on board the Gemini 

could be made available by off loading part of the emergency food 

supply from the Gemini to the laboratory portion of the MOL prior to 

detachment and de-orbit. 

(3) During a specified 5 hour period on the 14th flight 

day, and while in a fasting state, one MOL occupant will consume a 

packet containing 25 Gm of d-xylose. All urine collected for the next 

five hours will be lyophilized, appropriately labeled as to subject, 

day, hour and stored. On flight day 15, the second occupant of MOL 

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will perform the test on himself. It is not necessary that the astronaut 

fast after the test but it is advisable that one hour pass from the time 

the d-xylose is taken until food is consumed. The lyophilized urine 

of the second subject will also be returned in the Gemini vehicle. 

(4) On days 2, 7, 14, 21 and 26, ten ml. (10) of venous 

blood will be obtained by venepuncture (vacutainer) from each 

astronaut, centrifuged and the serum lyophilized. The dried serum 

will be labeled as to subject, date, time and stored. The packets 

will be placed aboard the Gemini vehicle prior to re-entry and analyzed 

following the flight. 

d. Category of Experiment 

An experiment which contributes to the MOL primary objective 

but does not have a significant influence on the design characteristics 

of the orbital laboratory (Category B). 

e. Cost 

It is as yet undecided whether diet funding will be from MOL 

funds or experimental funds. See Atch 4, "Funding Summary". 

f. Schedule 

(1) Hardware and software available for test: The date of 

testing for a lyophilizer and centrifuge are undetermined. Commercial 

liquid diets and hospital liquid dieti are available at the present time. 

These items can be tested for acceptability and metabolic effects 

immediately. Freeze-dehydrated foods are within the state of the art, 

have been shelf tested and evaluated in sealed cabin environments 

and found to be acceptable. Packaging of both liquid and freezedehydrated diet is not satisfactorily developed but must be developed 

by FY 66-67. 

(2) Hardware and software readiness date: To be determined but anticipated for FY 67. 

IV. Participating Government Agencies 

Sponsor: Captain Gerald W. Parker, USAF, MC, Gastroenterology 

Service, Department of Medicine, Wilford Hall USAF Hospital, 

Aerospace Medical Division (AFSC), Lackland Air Force Base, Texas. 

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Test Equipment Acquisition: Aerospace Medical Division 

V. Additional Requirements 

A. Special Security 

Development of the lyophilizer and centrifuge may require 

special security. Medical records of astronauts and results of all 

biomedical determinations should have limited access. 

B. Manning Description Summary 

See Atch 5, "Manning Description". 

C. Logistics 

To be determined. 

D. Facilities 

Existing facilities are adequate for performance of all 

pre-flight testing, training and post-flight testing except for the 

need for a mock-up MOL within an altitude chamber for actual 

mission testing and rehearsal. A Gemini flight simulator will also 

be required. Adequate biomedical analytical laboratory facilities 

are available from in-house facilities including the USAF Epidemiological Laboratory, SAM, and Wilford Hall USAF Hospital. A 

laboratory should be specifically set up for testing, quality control 

and modification of existing techniques as applied to the MOL 

mission. One of the specific missions of the USAF Epidemiological 

Laboratory is to perform just such quality control and it appears 

that this facility would be ideal for establishing laboratory procedures , 

maintaining quality control, and supervising and performing all 

analytical determinations. 

E. Simulation and Training 

1. Astronaut: Will perform as a technician. Simulation 

can be achieved by a moderate amount of medical training which 

could be accomplished in conjunction with other biomedical sections. 

2. Ground Personnel: Physicians will monitor data. 

Minimal training will be required. Members of the MOL biomedical 

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panel could monitor the data with the greatest amount of facility 

since they would be familiar with the entire biomedical package 

and its interfaces. Specific physicians should be designated to 

collect all specimens and personally deliver them to the appropriate 

laboratory. 

3. Equipment; Training equipment should be actual mission 

equipment. 

VI. General 

A. Communications and Data Handling 

The data required for this experiment during the in-flight 

portion consists of a daily log of dietary (food and water) intake 

and verbal notification of symptoms concerning the gastrointestinal 

tract if emergency or simi-emergency conditions exist. No real 

time data is required. Information regarding dietary intake may be 

dumped at a biomedical data area and calculated in order to assure 

adequate nutritional intake. (See Atch 6, "Communications and 

Data Handling"). 

B. Development Characteristics (See Atch 7) 

C. Justification of Experiment (See Atch 8 and section E, 

Reference Annex 3) - 

D. Reference Material (See Reference Annex 3) 

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DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED: D-xylose containers, 1 each occupant 

2. WEIGHT: 300 Gms each 

3. VOLUME: Stored 350 cc each in use same 

4. POWER: None 

5. SPARES: 1 each occupant 

6. TOOLS: None 

7. HEAT OUTPUT: None 

8. STABILITY: Indefinite until mixed 

9. VIBRATION LIMITS: Undetermined 

10. SHOCK LIMITS: Undetermined 

11. HAZARDS: None 

12. TEMPERATURE LIMITATIONS: Limits of plastic container 

13. RANGE OF MEASUREMENT: Absorptive ability of small intestine 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS: None 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: None 

16. EQUIPMENT OPERATING CYCLE: N/A 

17. EQUIPMENT LOCATION REQUIREMENTS: Placed in living area MOL 

18. SPECIAL MOUNTINGS REQUIREMENTS: None 

19. PRESSURE VESSELS: Fluids (water) in plastic container 

20. ELECTROMAGNETIC INTERFERENCE: None 

21. MAINTENANCE REQUIREMENTS: None 

Sec 3, Attachment 1 

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TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA: Voice tape for dietary log reporting 

2. HANDLING: Specimens stored in MOL, onloaded to Gemini 

prior to de-orbit 

3. PACKAGING: Plastic bag containers for specimens 

4. CALIBRATION: N/A 

5. JIGS AND FIXTURES: None 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION: None 

7. SENSORS: None 

8. TRAINERS/SIMULATORS: Mock-up MOL with Gemini, metal, 

in altitude chamber. FY 66 

9. INSTRUMENTATION: None 

10. RELATED SUPPORT EQUIPMENT: Lyophilizer for biomedical 

specimens 12" x 12" x 12" FY 66 

11. AGE: Biomedical data gathering station 

12. ENVIRONMENTAL TEST EQUIPMENT: None 

13. FACILITIES: Laboratory facilities for analysis of in-flight 

specimens 

■ 

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TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS: N/A 

2. PLANE CHANGE: N/A 

3. ALTITUDE CHANGE: N/A 

4. TIME IN ORBIT; 30 days 

5. TEST DURATION: 30 days 

6. TOTAL NUMBER OF TESTS: One in flight plus analysis of urine 

and feces collected 

7. TEST FREQUENCY: 

a. D-xylose - day 14 astronaut "A", day 15 astronaut "B" 

b. Urine lyophilization, packaging, labeling and storing daily, 

each astronaut 

c. Fecal lyophilization, packaging, labeling and storing 

approximately every 3 days, each astronaut 

d. Blood - aspiration, centrifugation, lyophilization, packaging, labeling and storing on days 2,7,14,21 and 26 

8. INTERVAL BETWEEN TEST: As in Item 7 

9. CREW TASK LOADS: 

a. D-xylose: 6 minutes each astronaut 

b. Urine: 15 minutes one astronaut 

c. Feces: 15 minutes one astronaut 

d. Blood: 10 minutes each astronaut 

10. CREW TASK FREQUENCY: Undetermined 

11. FIELD OF VIEW: N/A 

12. GROUND CONTROL LIAISON DURATION: Undetermined 

13. GROUND CONTROL LIAISON FREQUENCY: Undetermined 

14. EXTERNAL TEST ITEMS: None 

15. QUALIFICATION TESTS: Undetermined 

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16. SEQUENCE OF EVENTS: See Item 7 

17. HANDLING PROCEDURES: Samples of blood, urine and feces 

to be on loaded to Gemini vehicle, 

stored and returned for laboratory 

analysis 

Sec 3, Atch 3 

SSTA-1-9 Page 2 of 2 Pages 

186 
Exp No. P-12 

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Ca .-• ni 0 0 0 

0 al 4 k 0 

C4 I C 0 al 0 4., CO 0 

Sec 3, Attachment 4 

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MANNING DESCRIPTION 

1 . Astronauts 

a. Number required: 2 

b. Manls function 

(1) As part of test: Astronaut will act as his own control in 

assessing parameters of physiologic function and their ability to 

withstand a prolonged weightless environment. 

(2) As technician conducting test: Astronauts will perform 

at a medical technician level and require talents for venepuncture, 

chemical analysis, waste collection, recording and reporting. 

c. Crew skill requirements: Must be able to accurately record 

dietary intake, collect urine and feces and process the wastes for 

later analysis, perform venepunctures on companion astronaut and 

process blood for later analysis, and must have basic knowledge of 

first aid. 

d. Manpower profile: N/A 

e. Critical functions: None 

f. Time controlled tasks: None 

g. Work positions: Undetermined 

h. Human performance measures: None 

1. Selection factors: Astronauts must have no primary gastrointestinal disordF or functional bowel syndrome. Past appendectomy 

with no complications desirable. Must have no evidence of hiatus 

hernia or free reflux from stomach to esophagus. 

j . Training requirements: 

2. Ground Personnel 

Ground personnel requirements consist of two major groups: 

subjects and biomedical experimenters. During the development 

stages, at least 100 subjects will be necessary in order to test the 

acceptability, digestibility and toxicity of the proposed liquid diet. 

Biomedical personnel will be required to perform these tests and 

gather data for interpretation. During the in-flight tests, only 

members of the biomedical panel will be necessary to analyze data 

and provide instructions. Following the flight, laboratory facilities 

and technicians will be necessary to make chemical determinations 

and biomedical personnel will be necessary to correlate the data 

and arrive at conclusions. 

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COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE: Records of intake of food and water and output will 

be necessary from both astronauts on a 24-hour basis. 

2. FUNCTIONS TO BE MEASURED: Caloric intake, fluid intake, 

urinary output and number of defecations. 

3. TYPE OF ANALYSIS REQUIRED: Ground analysis only to determine 

nutritional status of occupants of MOL. 

4. PICTORIAL DATA REQUIRED: None. 

5. REAL TIME MONITORING REQUIREMENT: None. 

6. DATA EDITING OR COMPRESSION: Biomedical data should be 

separated from operational data, compressed and data dumped 

every 24 hours. 

7. READ OUT-TIME: 5-7 minutes each 24 hours. 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS: Taped records 

sufficient. 

9. MANUAL AND/OR AUTOMATIC CONTROL: N/A 

10. SIMULTANEITY: N/A 

11. GROUND COMMANDS REQUIRED: Verbal communication from 

ground to astronaut required. 

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DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME: 

a. Liquid diet: FY 66 

b. Lyophilizer: FY 66 

2. FINAL DEFINITIVE TEST DESIGN TIME: FY 67 for both items 

3. NUMBER OF GROUND OR FLIGHT TEST REQUIRED: 

a. Liquid diet: 4-6 ground tests 

b. Lyophilizer: 10-12 ground tests 

4. TYPE OF DEVELOPMENT TEST ITEMS: 

a. Liquid diet: Vacuum chamber, shaker, thermal, simulators, 

aircraft. 

b. Lyophilizer: Vacuum chamber, shaker, thermal, simulators. 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME: Same as Item 1. 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground test 

(1) Diet: 100-200 man days 

(2) Lyophilizer: One(1) for MOL mock-up, 3 for development 

testing. 

b. Atmospheric test 

(1) Diet: 30 man days 

(2) Lyophilizer: None 

c. Space test: One (1) for each MOL. 

7. DATE AVAILABLE FOR TESTS: Crude liquid diets available FY 64 

for acceptability tests. 

8. CURRENT DEVELOPMENT STATUS: 

a. Liquid diet in granular form for reconstitution in space 

proposed only. Lyophilizer proposed only. 

b. Project is not approved and is not under study. 

c. No funds have been expended to date. 

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JUSTIFICATION OF EXPERIMENT 

A need exists not only to assess man's work performance while 

he is performing mission oriented duties in an orbiting vehicle, but 

also to gather information concerning as many parameters of physiological function as possible without compromising weight and space 

requirements or the primary mission of the MOL. It is to this end 

that this experiment has been designed. At the present state of 

knowledge, there is no proof that intestinal absorption proceeds 

normally during orbital flight but respected opinions of consultants 

result in the impression that it will (1,2,3,4). Two studies of the 

absorptive ability of the small intestine have been performed during 

U. S. orbital flights. The pilot of MA-6 (Glenn) ingested a 5 gram 

tablet of d-xylose in a non-fasting state and excreted 34.9% of the 

administered dose by the fourth hour (normal test) (5). The pilot of 

MA-7 (Carpenter) excreted only 25.7% of the 5 gram test dose (6) 

but urinary collection was inaccurate and the test cannot be relied 

upon. While Glenn consumed his test dose of d-xylose at 23 

minutes 11 seconds g.e.t., Carpenter took his test at 2 hours 41 

minutes 35 seconds g.e.t. in the hope that any gastrointestinal 

changes would be more marked after a longer time. Disappointed 

at the failure to obtain information during the second flight, the 

biomedical investigators suggested that "if this test is to be used 

on future flights, the accurate timing of xylose ingestion and 

urination must be known. Ideally, urine specimens passed while 

the subject is under the influence of gravity should be separated 

from those specimens voided while he is weightless". (6) A 

critical analysis of information available reveals that the only 

knowledge obtained to date about intestinal absorption is that 

carbohydrate absorption (as reflected by d-xylose) appears to occur 

normally during an orbital flight of 4 hours 55 minutes. 

In an attempt to determine the ability of the intestine to absorb 

carbohydrate after prolonged weightlessness the d-xylose test is 

again recommended. It is a simple, inexpensive, convenient test 

to perform, requiring only the ingestion of 25 grams of d-xylose in 

250 milliliters of water and collection of the urine excreted for the 

next five hours. If 4.5 grams of d-xylose are recovered from the 

urine, absorption can be considered normal. With lyophilization 

of the urine, the xylose will remain indefinitely and the sample can 

be reduced to a few grams in weight so that it may easily be returned. 

No careful volume measurements are necessary since it is the total 

amount of xylose excreted in the specified time which is important•in 

assessing the absorptive function of the small bowel. The use of a 

25 gram test dose rather than 'a 5 gram tablet is recommended because 

it has been shown that there is better reproducibility of results using 

the 25 Gm dose (7). Furthermore, a solution is preferable to a tablet 

Sec 3, Attachment 8 SSTA-1-9 

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for ingestion because there is greater assurance that a complete test 

dose has been administered. 

The ability of the intestine to absorb fat can be assessed without 

imposing undue burden on the subjects. There is presently no knowledge available concerning fat absorption during weightlessness. 

Considering that the protein, fat and carbohydrate content of the 

foodstuffs ingested is known, the pilots of the MOL can serve as 

their own control since pre-flight and post-flight absorption studies 

are also contemplated. Analysis of fecal fat while the astronauts 

are at ground level can be easily and conveniently ascertained by 

fecal fat analysis before the flight and after the flight. With minimal 

technical knowledge, the astronaut can collect his feces during 

flight, lyophilize it and return with it. The total space requirements 

in the return vehicle will amount to approximately 1000 cubic centimeters. The fat content will be unaffected by lyophilization. 

These two tests are proposed because their performance does 

not require a great deal of technical knowledge by the astronaut, 

they are inexpensive, the samples returned will impose no appreciable 

weight or space penalties on the vehicle, can be stored indefinitely 

without loss of constituents. The information obtained will be a 

valuable addition to the total assessment of the physiological 

functions of man under the stresses of space and will bear strongly 

on flight safety and growth potential for future flights. 

The requirement for the experiment which necessitates test 

support equipment is the lyophilizes. There is a need in the metabolic, 

renal, cardiovascular and pulmonary biomedical sections for the 

return of blood, urine and fecal specimens. A centrifuge for blood 

specimens is a requirement of other sections. It appears to be the 

consensus of all biomedical sections that the return of specimens 

should be in a form which imposes the least weight and volume 

penalty on the returning vehicle. The use of lyophilization procedure 

in obtaining specimens for studies of intestinal absorption would 

integrate well with contemplated collection of specimens in other 

sections. Present engineering problems concerned with installation 

of such a device in the MOL are not available at this writing. 

Although present laboratory lyophilizers appear to be bulky and 

heavy, (8) the major components consist of refrigerating compressors 

and vacuum. It appears that the space environment offers cold 

temperature and vacuum - the very elements necessary for lyophilization. 

Sec 3, Atch 8 

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References 

1. Sleisenger, M. H. (Civilian Consultant in Gastroenterology 

to MOL Project): Personal communication 

2. Kipnis, D. M. (Civilian Consultant in Metabolism to MOL 

Project): Personal communication 

3. Gordon, G. (Civilian Consultant in Metabolism to MOL 

Project): Personal communication 

4. Palmer, E. D. (Chief, Gastroenterology Service and Chairman 

Department of Medicine, Brooks Army Hospital): Personal 

communication 

5. Results of the First U. S. Manned Orbital Space Flight, 

NASA, 20 Feb 1962 

6. Results of the Second U. S. Manned Orbital Flight, May 24, 

1962, NASA SP-6 

7. Christiansen, P. A. , Kirsner, J. B. , and Ablaze, j.: D-xylose 

and its use in the diagnosis of malabsorptive states. Am. M. 

Med. 27:433, 1959 

8. Catalog, Scientific Products Division, American Hospital 

Supply Corp. , 1210 Leon Place, Evanston, Ill. Local source: 

2505 Butler Street, Dallas 35, Texas 

Sec 3, Attachment 8 

Page 3 of 3 pages 

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4. Study of Effects on Metabolism Resulting From Flights. on MOL. 

This test is designed to provide inflight determinations of 

serum calcium and glucose and of urinary calcium at approximately 

weekly intervals. Abnormalities in the metabolism of either of these 

substances may constitute a definite threat to astronaut safety and 

mission success. The tests rely heavily upon chemical determinations 

which can be adapted to the MOL requirements. In addition, inflight 

samples of blood, urine and feces will be collected for later ground 

analysis of numerous metabolic and endocrine parameters. Current 

techniques will allow the accumulation of a large amount of metabolic 

data which will characterizre the metabolic changes secondary to 

weightlessness on space flights of 30 days duration. Data from these 

samples collected inflight will be compared with preflight and postflight data to provide a relatively comprehensive view of important 

metabolic changes and thus provide a basis for protective measures 

essential to extension of space flights for periods longer than 30 

days. The inflight studies will be validated by an extensive ground 

research program. 

It is not anticipated that serious problems will be encountered 

in accomplishing the tests. Minimal training of the astronauts will 

be required. Some work on the development of a suitable technique 

for measuring calcium will be needed and it will also be necessary 

to devise a simple apparatus to collect, measure and lyophilize the 

biological specimens to reduce the volume and weight of material 

sufficiently for later return to earth. 

a. Configuration of Test Items: Design Characteristics Test 

Equipment. 

- (1) Equipment to be tested: Inflight testing upon small 

volumes of blood and urine which the two astronauts will furnish. 

Urine calcium and blood calcium and glucose samples will be determined five times during the 30 days inflight period. From the same 

collection five blood specimens will be centrifuged, the plasma 

lyphilized, packaged, stored and later returned. Urine specimens 

will be collected continuously throughout the flight by an automatic 

process which will also proliille lyophilization and packaging. Equipment requirements consist of a collection and lyophilizing device for 

each astronaut and equipment for onboard analysis of blood and 

urine specimens. The former will require a centrifuge for processing. 

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(2) Weight: Weight of the packaged blood and urine 

samples collected inflight from both astronauts is estimated to be 

in the neighborhood of five pounds after lyophilization. Weight of 

collecting, lyophilizing, and testing equipment is to be determined. 

(3) Volume: Volume of the lyophilized blood and urine 

specimens to be returned is estimated to be in the neighborhood of 

approximately one-sixth cubit feet. Volume of collecting and lyophilizing device and of chemical determination equipment is to be 

determined. Shape of lyophilized and packaged samples will be 

flexible since they will be in small individual plastic packages. 

Dimensions and shapes of the lyophilizing device and chemical 

testing equipment is to be determined. 

(4) Power: 

(a) No requirements for continuous power. 

(b) Stand-by power for analytical equipment to be 

operated for approximately one hour during the entire flight. 

(c) To be determined. 

(d) To be determined. 

(e) To be determined. 

(5) Spares: 

(a) N/A. 

(b) N/A. 

(c) N/A. 

(6) Tools: None. 

(7) Heat Output: To be determined. 

(8) Stability: To be determined. 

(a) Moving parts: Limited to the small centrifuge 

necessary for obtaining plasma from blood specimens. 

(9) Vibration Limits: To be determined. 

(10) Shock Limits: To be determined. 

(11) Hazards: None anticipated. 

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(12) Temperature Limitations: To be determined. 

(13) Type and Range of Measurement: Chemical determination of calcium and glucose in blood and of calcium in urine. 

(14) Special Environmental Requirements: Equipment used 

for collecting and measuring urine samples and blood and the recording 

method, requires only the environment of the enclosed MOL vehicle. 

Environmental limitations for the specimens will be those of the 

plastic containers, which must be determined. 

(15) Orientation and Position Accuracy Requirements: N/A. 

(16) Equipment Operating Cycle: Ten times for each 

astronaut for a 30 day flight. Each of these tests is estimated to require approximately 10 minutes. Blood specimens, to be lyophilized 

and returned to earth, will be obtained 9 times on each astronaut 

during flight. This process estimated to require 10 minutes for each 

collection and preparation. Two injections to be given to each 

astronaut will require approximately 7 minutes per astronaut. Collection and lyophilization of urine specimens are estimated to require a 

total of 360 minutes per astronaut. Application of filter paper twice 

by each astronaut for collection of sweat specimen is estimated to 

require ten minutes. 

(17) Equipment Location Requirements: Flexible. Noncritical areas can be utilized. 

(18) Special Mountings Requirements: None. 

(19) Pressure Vessels: N/A. 

(20) Electro Magnetic Interference: N/A. 

(21) Maintenance Requirements: To be determined. 

b. Test Support Equipment Required. 

(1) Recording Media: Tape, electronic or visual writeOut. 

(2) Handling: Urine collecting container of approximately 2500 cc volume for each astronaut for collection of 24 hour urine 

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volumes, attached container of approximately 100 cc volume for 

obtaining an aliquot of each 24 hour urine specimen, and lyophilizing 

equipment are all envisioned as a closed single liquid system. Plastic bags for specimens which conform to lyophilization requirements 

are to be developed. 

(3) Packaging: Special plastic bags suitable for use 

in lyophilization. 

(4) Calibration: Limited to electronic recording device

. if such is used. 

(5) Jigs and Fixtures: Collecting container, centrifuge, 

and testing equipment are all to be stationary and permanently mounted 

in non-:critical areas. 

(6) Number of Leads From Outside to Inside Station: 

None. 

(7) Sensors: Calcium electrode or other sensing device. 

(8) Trainers/Simulators: None for this test. 

49) Instrumentation: Limited to electronic analytical 

equipment, to be used during non-working periods only. 

(10) Related Support Equipment: N/A. 

(11) Age: To be determined. 

(12) Environmental Test Equipment None. 

(13) Facilities: To be determined. 

c. Test Procedure 

The test itself requires the collection of blood and urine 

samples and onboard analysis of calcium and glucose, with each 

astronaut to perform these tests on 5 blood specimens and 5 urine 

specimens during the flight. The man will be required to perform venipuncture and obtain blood specimens, to operate centrifuge for 

separation of plasma from the blood specimen, and to perform the 

chemical determinations for calcium and glucose. The chemical 

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determination in the case of both blood and urine specimens will 

be simple and require no complicated operation, with only simple 

manipulations required for operating an electronic measuring device 

and either a visual read-out or recorder for later transmission of data 

to earth. The collection of urine specimens will be designed to make 

minimum requirements upon the man's time by the use of automatic 

methods. 

Test Operating Characteristics 

(1) Orbital Parameters: N/A. 

(2) Plane Change: N/A. 

(3) Altitude Change: N/A. 

(4) Time on Orbit: N/A. 

(5) Test Duration: Daily operation of urine collecting 

and lyophilizing device will require 10 minutes per astronaut per 

day. Collection of urine and blood for onboard analysis will require 

approximately 20 minutes per astronaut on 5 occasions at approximately 

weekly intervals during flight. Two injections during flight for each 

astronaut on approximately the 12th and the 22nd day require approximately 7 minutes. 

(6) Total Number of Tests: As in 5. 

(7) Test Frequency: As in 5. 

(8) Intervals Between Tests: As in 5. 

(9) Crew Task Loads: Total time requirement for each 

astronaut is estimated to be 9 hours for the entire flight. The specimens collected during these times will be shared with other areas. 

The volumes and times of urine and blood collections listed here are 

essentially those required for all tests in other areas as well -as the 

metabolic area. 

(10) Crew Task Frequence: As in 5. 

(11) Field of View Requirement: N/A. 

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(12) Ground Control Liaison Duration: N/A. 

(13) Ground Control Liaison Frequency: N/A. 

(14) External Test Items: N/A. 

(15) Qualification Tests: 

(a) Ground: Validation of the methods of determination and equipment for such determinations will be required. 

Suitable plastic for collection and lyophilization of specimens must 

be tested. Centrifuge adapted for inflight use must be developed 

and tested. Urine collection, aliquot separation, and lyophilization 

equipment must be developed and tested. 

(b) Atmosphere: None. 

(16) Sequence of Events as they Occur During Flight: 

Collection of urine will be on a continuous basis. The 24 hour 

collection device, and aliquot separation device should require no 

more than the turning of a valve at the time that the aliquot of the 

24-hour urine specimen is obtained. This will be done once daily 

for each astronaut except on 4 days when aliquots from ,2 twelve-hour 

specimens are collected. The aliquots of the 24-houetind 12-hour 

urine specimens will be 100 cc in volume and will be collected in 

plastic bags or containers which can be sealed, exposed to cold 

and vacuum for lyophilizing, stored in an out-of-the-way area, later 

-gathered, stored in non-critical area of Gemini capsule, and returned. 

Blood specimens, to be obtained for lyophilization, will require 

centrifugation, separation of plasma, and lyophilization. On 5 of 

these 9 occasions when blood must be drawn determinations will be 

made inflight. On the same day 5 urine specimens will also require 

onboard determinations. 

(17) Handling Procedures: As described in 16. 

d. Category of Experiment 

(1) Category a: None. 

(2) Category b: These tests contribute to the primary 

MOL objectives. With the possible exception of the urine collection 

and lyophilization system they should have no significant influence 

on design characteristics. 

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(3) Category c: None. 

e. Cost: Ground research studies begun 2 years ago by 

Clinical Sciences Division, School of Aerospace Medicine, will be 

continued with in-house funds. 

f. Schedule 

(1) All hardware and software required for the tests is 

available except for an optimal method and equipment to measure 

calcium levels of urine and serum during flight, a suitable centrifuge 

suit and the equipment necessary to collect, measure, aliquot, 

package and lyophilize biological specimens. 

(2) To be determined. 

IV. Participating Government Agencies 

Sponsor: School of Aerospace Medicine. 

Test Equipment Acquisition: To be determined. 

V. Additional Requirements 

a. Special Security:N/A. 

b. Manning Description Summary: 

(1) Astronauts 

(a) Number required: Two 

1. Man's function 

a. To function as a subject of the test and 

operate equipment to collect and lyophilize biological specimens and 

perform venipunctures, intravenous injections and chemical analysis of 

biological specimens. 

b. All of the performance will be as 

technician. 

(b) Crew skill requirements: Technician level which 

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will require little special training. Minimal training will be required to develop the ability to perform venipuncture and intravenous injections and to operate equipment. 

(c) Manpower Profile: Tests required for the metabolic area can be performed by one man working alone except for 

intravenous injections and venipunctures which will require two 

astronauts working together and which should not require longer 

than 30 minutes during a 30 day mission. 

(d) Critical Functions: Accurate performance of 

chemical determinations. 

(e) Work Positions: Flexible. 

(f) Time Controlled Tasks: Collection of urine over 

12 and 24 hour periods. Performance of venipuncture no less than 

6 hours after a meal. 

(g) Huinan Performance Measures: N/A. 

(h) Physiological and Psychological Measures: N/A. 

(i) Selection Factors: Not critical insofar as these 

tests are concerned. 

(J) Traibing Requirements: As in (b) above. 

(2) Ground Personnel 

(a) Number required: One or twcr:to monitor, correlate 

and analyze returned data. 

(b) Crew Skill Requirements: Board-qualified 

Internist. 

(c) Manpower Profile: N/A. 

(d) Critical Functions: Analysis of significance of 

returned data. 

(e) Work Positions: N/A. 

(f) Time Controlled Tasks: To be determined. 

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(g) Human Performance Measures: N/A. 

(h) Physiological and Psychological Measures: N/A. 

(1) Selection Factors: N/A. 

(J) Training Requirements: Board-qualified Internist. 

c. Logistics: To be determined. 

d. Facilities: Existing facilities are adequate at present 

to continue ground research applicable to MOL. A mock-up of the 

Gemini Flight Simulator would be desirable to assist in the minimal 

training which the astronauts will require to carry out the technibian 

type tasks. 

e. Simulation and Training 

(1) Astronaut: Technician level of required tasks will 

require minimal training of individuals otherwise quilified for mission 

facilities, for training including inflight methods and equipment, will 

be available at the School of Aerospace Medicine. 

(2) Ground Personnel: No additional requirements at 

present. 

(3) Equipment: No additional requirements at present. 

VI. General: 

a. Communications and Data Handling Requirement 

(1) Data Rate: Barring the occurrence of emergency situations requiring diagnosis and treatment, results of tests could be 

transmitted once very 24 hours. 

- (2) Functions to be Measured: Serum calcium, glucose. 

Urine calcium. 

(3) Type of Analysis Required: Chemical. 

(4) Pictorial Data Required: None. 

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(5) Real Time Monitoring Requirement: None. 

(6) Data Editing or Compression: N/A. 

(7) Read-out Time: N/A. 

(8) Requirements for Permanent Data Records: None. 

(9) Manual and/or Automatic Control: N/A. 

(10) Simultaneity: N/A. 

(11) Ground Commands Required: None. 

b. Development Characteristics 

(1) Development Time: To be determined. 

(2) Final Definitive Test Design Time: To be determined. 

(3) Number of Ground or Flight Tests Required: Ground 

tests only would be required except for flight-testing equipment. 

Those involving astronaut training would probably be limited to several 

sequences of collecting and testing procedures, preferably in a 

simulator. Metabolic studies covering approximately seven weeks on 

the two astronauts is desirable. 

(4) Type of Development Test Items: 

(a) Vacuum Chamber: All testing equipment. 

(b) Shaker: All testing equipment. 

(c) Thermal: All equipment. 

(d) Acoustic: All equipment. 

(e) Simulators: As in (3) above. 

(f) Aircraft: No requirements in connection with 

tests or ground research. 

(5) Support Equipment Development Time: To be 

determined. 

(6) Number of Test Articles Required For: 

_ (a) Ground Test: Two each of collecting and lyophilizing device, centrifuge, suitable equipment for determination of 

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calcium and glucose in biological specimens. 

(b) Atmospheric Test: To be determined. 

(c) Space Test: To be determined. 

(7) Date Available for Tests: To be determined. 

(8) Current Development Status: 

(a) Proposed Only: Calcium electrodes. Further 

refinements to increase reliability required. 

(b) None. 

(c) Funds expended to date: None. 

co See Annex 4 Study of Effects on Metabolism Resulting From 

Flights cm MM. 

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S. Renal and Electrolyte Effects Resulting from MOL Mission 

This experiment is designed to reflect and elucidate the processes 

which represent the acute adaptive responses to weightlessness and 

also the steadystate which probably will occur with prolonged weightless flights of 30-120 days. Project Mercury flights provided information that astronaut personnel sustained definite body fluid losses 

which were manifested by weight loss, evidence of dehydration and 

serious cardiovascular instability. To this time, data are not 

available which clearly demonstrate the mechanisms of this fluid loss 

in each. Moreover, none of our orbiting personnel can be judged to 

have achieved a steady state of equilibration in the weightless 

environment. Hence, it is expected that careful studies in future 

flights will enable us to make sound decisions as to the pathcphysiological processes utilized, and enable us to have in hand the necessary 

data to compensate for any serious fluid shifts or losses encountered 

in flight. The analyses and records relate directly to flight safety. 

a. Configuration of That Items 

(1) Photoelectric spectrophotometer: approximately 1 cu foot 

volume, square, 4#, in the MDL 

(2) Sodium electrode: 12 x 24 x 12 inches, oblong, 4#, in 

the MDL vehicle. 

(3) Micro-pill-meter: 12 x 24 x 12 inches, oblong, #4, in the 

MOL. 

(4) Optical refraotometer: 12 x 3 x 3 inches, cylinder, 111, 

in the MOL. 

(5) Centrifuge (torque - countertorque probably necessary), 

1 cu foot volume, 5# weight, cylinder, in the MOL. 

(6) Volumetric cyclinders for measuring urine volume, in the 

MOL. 

(7) Calibrated syringes, stopcocks, containers and sample bags 

(8) Biological sample lyophilizer: no estimate at present, 

located in the MOL. 

(9) Body mass meter: from a calibrated spring gauge, in the 

MOL. 

b. Test Support Equipment 

(1) Spacecraft: needles, syringes, stopcocks, standard 

solutions necessary. 

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(2) AGE: Duplicate equipment must be mounted in simulators 

to familiarize personnel prior to flight. Other equipment (duplicate) 

will have to be thoroughly tested in lab, and flight personnel taught 

the technical details of equipment usage to assure accurate, reproducible results. 

c. Test Procedure: The test is to observe and record the fluid 

shifts occurring in the flight personnel by recording food and fluid 

intake and measurable fluid output. Body mass (as a measure of 

weight) will be recorded daily, urinary solute excretion will be 

measured and the net serum stabilization will be assessed using 

hematocrits and serum sodium determinations. 

(1) Orbiting crew members will make the observations, testing 

each other. They will therefore be the subjects as well as the 

technicians for the experiment. 

(2) Man will be used to the extent that his adaptation is 

under scrutiny and it is he who is making the observations. The 

observations will be judged by the serial changes recorded in the 

physiological systems being tested. 

(3) Testing sequence: certain tests will be performed daily 

in the early.phases of flight, thereafter, testing will be at greater 

intervals, viz, weekly. 

(a) Daily tests: to be done each day by each crew sember 

1. Record of 24 hour intake - fluid and food 

2. Collection of 24 hour urine excretion will be 

aliquoted and approximately 100 cc of each 24 hour volume lyophilized. 

The residue is to be labelled and returned to earth with crew members. 

3. Measurement, in flight, of daily urinary sodium 

excretion (from aliquot of 24 hour volume) and urinary total solids 

from optical refractcmeter (also calibrated for urinary specific 

gravity and total serum solids). 

(b) Daily tests: done each day during the early (first 

week) of flight or until steady state is achieved. 

1. Body mass 

Capillary hematocrit 

!. Total serum solids (can be taken from supernate 

of hematocrit) 

(c) Periodic tests: will be done at intervals during 

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for example on the 2nd, 7th 14th, 21st and 28th days. They can be 

done at other times if clinical situation is thought to warrant it, 

as in medical emergency. 

1. General physical examination: more in the 

nature of inspectgh - look for petechie, edema, assess skin and 

tongue turgar, auscultation of chest (if indicated) and abdomen 

(likewise). 

2. Urinary protein, glucose, pH (dip sticks) 

T. Blood volume: using injection of known amount 

of T1824 dye and sampling in 30 minutes for spectrophotametric 

determination of dye density. 

4. Body water: using D20 as marker, mass 

spectrametry of urine can be used to assess body water in flight. 

5. Serum sodium: can be measured from venous 

sample on cationic exchange electrode (glass) 

6. "Arterialized" capillary pH: on capillary 

micro - pH meter 

7. pCO2: can be appmcmimated from end-alveolar 

sample using a CO2 sensing device, specifically amass spectrometer. 

8. Blood calcium, B.U.N.: for former the 

detection of hyperEacemia is sufficient and exquisite accuracy is 

not necessary, for the latter also a rough quantitative estimation 

is sufficient. A colorimetric determination on spectrophotometer, 

or kit, will suffice. 

9. Plasma sample (15cc) will be lyophilized 

weekly and preserved for return to earth, appropriately labelled. 

The results of all these tests can be determined and calculated 

visually in flight or the electrical impulses from oolorimetric 

reactions read-out on demand. Peal time records are not critical, 

but results should be retrieved the day of testing so that important 

trends are not overlooked. 

(d) If alarming values are reported, or consistent 

trends detected vthich require urgent action, the orbiting crew can 

be commanded from the control station to carryout the critical test 

cn "instantaneous" basis or to test at more frequent intervals. If 

illness should develop in flight, ar if puzzling behavior or perfarmance supervene, the capability to detect major metabolic alterations 

and the equipment necessary is aboard in the form of pH meter, sodium 

electrode, total solid meter, etc. This is a definite "flight safety" 

feature of the test. 

(e) In terse of efficient expenditure of time one crew 

member will be responsible for the analytical work and the other for 

aliquoting samples and recording values. In this way greater 

efficiency and minimal time investment will be achieved. 

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1. Urinary nitrogen 11. Uropepsin 

T. Creatinine IT. Amylase 

T. Uric acid IT. 5-hydroxyindoleacetic 

4: Calcium acid 

3: Phosphorus 14. Oxalate 

r. Sodium In Ascorbic acid 

7. Potassium In Aldosterone 

1.. Chloride IT. Cortisol and interT. Protein mediary products 

1T. Indican 18. Anti-diunectic 

activity 

19. Hydroxyproline 

These analyses will give definite insight into the intermediary 

metabolism of man in prolcmged weightless flight. The analyses will 

be performed in research laboratories under the direction of a central 

laboratory supervisor. 

d. Category of Eicperiment: the entire experiment is category a. 

The equipment required may be specifically categorized: 

(1) Spectimphotorreter: category a. 

(2) Sodium electrode (cationic exchange glass): a 

(3) Micro-pli meter (capillary): a 

(4) Optical refreatcenter: b 

(5) Centrifuge: a 

(6) Volumetric devices: b 

(7) Calibrated syringes, etc: b 

(8) Lyophilizer: a 

(9) Body mass meter: a 

e. Cost 

(1) ESD: $10,000 FY 65 

(2) Installation: $10,000 FY 66 

(3) Ground Support: $10,000 FY 67 

Data retrievalwill'alreadybe programed from the MOL 

f. Schedule 

(1) limndware and software available for test: Dec 1965 

(2) HardWare and software available for flight: June 1966 

(f) Tests that will be performed on aliquots of 

urine returned (stool specimens should also be returned) are the 

following: 

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IV. Participating Government Agencies 

Sponsor: John J. McPhaul, Digt, USAF, MC 

Wilford Hall, USAF Hosp 

AMD, AFSC 

Test Equipment Acquisition: AFSC 

V. Additional Requirements 

a. Special Security: probably for official use only 

b. bee attactment b 

c. N/A 

d. Facilities: no new facilities required, except duplicate 

equipment must be installed in a simulator and complete 

flight simulation carried out using and proving the equipment 

e. Simulation and : for the test contemplated the tasks 

are complex enough flea training is required. The level of 

knowledge necessary is not critical. The crew member who 

is to operate the test equipment must have sufficient practice 

so that readout data supplies accurate info:creation. It is 

sufficient that a pilot or engineer be aboard; it should not 

require a technologist or physician. The training, will 

entail two phases: 

Cl) Introduction to the equipment and the techniques of use 

so that crew members are thoroughly familiar with its 

use. Personnel will also be taught proper,methods of 

venipuncture, specimen handling and recording of 

observations. The crew members must be able to judge 

whether instruments are functioning optimally. 

Technique checkout prior to flight will indicate 

sufficient familiarity. 

(2) "Flight" of short duration in an MIL simulator should be 

performed prior to actual orbital missions in oder to 

thoroughly familiarize personnel with position of 

instruments and importance of precision analytic work. 

This will afford opportunity to detect flaws and correct 

errors of technique under simulated flight conditions. 

(3) Equipment necessary► is a complete setup of analytic 

monitoring and testing equipment as it will be flown 

of MOL. 

VI. General: 

a. Came nicatials and Data Handling Requirement: No real time 

observations are needed except in emergencies. Data can 

be dumped by telemetry from tape in one location daily - 

preferably in a central medical facility, such as S.A.M. 

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b, Development Characteristics: 

(1) Attachments 1 through 4 to be determined. 

(2) See attachments 5 through 7. 

c, See Annex 5 Renal Fluid and Electrolyte Effects Resulting 

frau 1.101. Missions for core detailed information in this 

area. 

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Attachments 1-4 to be determined. 

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• MANNING DESCRIPTION APPENDIX 

A. Astronauts 

1. Number required: 2 

a. Man's functicn 

(1) As subject - both must be subjects 

(2) As technician - only 1 need be actual technician -

it is preferable that 1 man do all the testing 

consistently. 

b. Crew skill requirements - mast do venipunctures, perform 

injections, measure accurately, and carry cut the test protocols 

exactly as pre-planned and practiced prior to flight in lab and 

simulator. Must operate the testing equipment as per instructions. 

c. Manpower profile - will require 1 man 25 minutes daily 

to perform the capillary finger stiCks, hematocrit, total solids 

determination and urine analysis. Will require 25 minutes additional 

to record urinary volumes, fluid volumes, and diet intake, and 

lyophilizaticn of biological samples to return. This is 50 minutes 

total time (of 48 hours available from both astronaughts). After 

initial adaptation period (probably 1 week) only aliquoting and 

urine analyses will be daily work. 

d. Critical functions - careful technique of measuring, 

pursult of protocol and use of equipment. 

e. Work positions - can be performed sitting. 

f. Time controlled - must be done daily at same time of day, 

preferably post-absorptive. 

g. Human performance measures - are biological measures. 

Consistent skill of performance will serve as an added indicator 

of reliability and ability to follow direction. 

h. Physiological and psychological measures - this is the 

test. 

i. Selection factors - no particular skills required beyond 

crew selection of qualified astronauts and proper preflight training 

in lab and in simulator "flight". 

j. Training requirement - will require 2 hours of work overall 

with each piece of equipment to attain fetni1i4ritY and consistency 

Sec 5, Atch 

Page 1 of 2 Pages 

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in its use; can be supervised by qualified laboratory personnel. 

Venipunoture requires little practice. Additional requirement of 

complete mockup simulator "flight" with actual equipment. 

B. Gromvi Personnel 

1. A medical director can Coordinate the medical monitoring 

and supervise the distribution of daily and periodic biomedical 

data for evaluation and interpretation. 

2. Proper data reception, processing, and print-out must be 

assured. 

3. Emergency changes may be dictated by in-flight trends, 

symptoms, or analytic results. 

Sec 5, Attachment 5 

Page 2 of 2 pages 

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Comunicatices and Data Handling 

1. Data rates daily; spread 

2. F:noticn to be measured: test result, can be direct voice 

or code 

3. Type of analysis to iittsized s data recovery only 

4. Pictorial data s none 

5. Real time tali . requirements, me, except in mutt 

medical irtergancy .1....;:','"'.' 

6. Data' editing on ocmpressicat none 

7. Raadcast.tiiret r.;. 3 minutes. . .. 

8. Require: int - ft:permanent data swords: on reosptial only 

9. Manual control or antarctic: no proforma; manual in emergency 

10. SimultanietYs all data to one receiver site 

11. Ground emends required: only' in emergency 

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Development Characteristics of Equipment 

1. Development time: 18 months 

2. Final definitive test design time: 6 months 

3. Number of ground tests required: 2 =plate simulator runs 

prior to flight 4. Type of development test items 

a. Simulator reliability needs denonstratiat prior to flight 

b. Kist be stable enough to withstand severe vibration 

5. N/A 

6. Number of test articles required 

a.- Ground testing: 2 

b. N/A 

c. Should be aboard each of unmanned flights so as to assess 

stability and durability 

7. Date available for tests: June 1966 

8. Current development states: 

a. Proposed only: lyophilizes, sodium electrode for space use, 

body mass gauge, suitable centrifuge, and spectrophotometer 

b. On shelf: optioalrefrectometer 

Sgc 5, Attachment 7 

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6. Evaluation of Pulmonary Function During MOL Missions 

Because respiration'serves &e'en interface between man's external and 

internal environment, it is more.accessible to measurement than any other 

body system.. Furthermore, dysfunction in any other body system will be 

reflected'by changes in respiratory parameters. Broad spectrum monitoring 

of pulmonary function, therefore,. iseminently practical and will provide a 

sensitive early warning.system.of detrimental' change in not only pulmonary 

function but also of any other physiologic system which could affect man's 

operative abilities in a military space mission. If the primary site of 

physiologic.alteration is pulmonary in origin, the change can be qualitated 

and quantitated so that proper corrective measures can be instituted or an 

accurate estimate of duration.limitation can be made. The pulmonary test 

items were'selected with the above goals in mind. 

a. Configuration of test items 

(1) In Gemini capsule 

(a) Impedance pneumograph: uses ECG electrode 

(2) In 1101. 

(a) Face mask: modified CWS gas mask for collection of expired 

gases;' weight, 1 lb.; volume, approximately 144 cubic inches; plastic shape. 

(b) Capillary pneumotachometer: gas flow measuring device from 

which volume of gas can be obtained by electrical integration; weight, 1 lb.; 

volume, 20 cubic inches; shape, bisymmetrical truncated cone. 

(c) Pressure transducer: sensitivity of ±0.3 p.s.i. differential; weight, 1 lb.; volume, 18 cubic inches; shape, cylinder. 

(d) Milner-Frans dry test gas meter: direct reading and automatic sampling of mixed'expiratory gas volumes; weight, 8.5 lbs.; volume, 

0.6 cubic feet;-shape, rectangular block. 

(e) Gas analysing equipment: specifications to be added to 

operational equipment in HOL control system for gaseous environment (see 

below). 

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(f) Associated paraphernalia: assorted sizes of rubber 

balloons for gas collection, large bore stopcocks, rubber tubing, drying 

agent, pinchcocks; total weight, approximately 12 lbs.; volume and shape, 

can be packed in carton occupying 0.7 cubic feet. 

b. Test support equipment required 

(1) Spacecraft 

(a) Gas environment control system: analysers or sensors 

to be sensitive to at least.O.r& (v/v) CO2 and 02; accessible to astronauts 

for sample analysis and calibration; response time of 957. in 0.1 second. 

(b) Tape recorder 

(c) TIM 

(d) Meter read out 

(e) Operational amplifier and integrator 

(2) Am. no special requirement 

c. Test procedures 

The specific parts of the test procedure provide broad spectrum 

monitoring of pulmonary function. All tests will be performed by the subject on himself and will only rarely require aid from a second person. The 

data will be interpreted on the basis of previously acquired control data 

at ground simulation of HOL mission. The tests will provide medical safety 

monitoring as well as an .assessment of man's ability eb function in space 

in relation to his ability to perform the same mission operations at ground 

level. Priority of specific test procedures are shown in "Annex to Area 6 -

Respiration" attachment. 

(1) Timed vital capacity (TVC) and vital capacity (VC). These will 

be measured by the integrated signal of the pneWmotachometer while the 

subject is at rest and fasting every third day in orbit. The tests provide 

a simple means of measuring total incremental lung volume as well as 

indicate (in the case of TVC) the presence of changes in.airway resistance. 

These tests, therefore, assess the lungs' ventilatory function. The 

respiratory maneuvers necessary to the measurement' are themselves of therapeutic value in maintenance of airway patency and re-expansion of shrunken 

alveoli. 

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(2) Alveolar partial pressures of carbon dioxide (PAc02) and oxygen 

(4012). These will be obtained by gas analysis of a Haldane alveolar gas 

sample, which consists of trapping the gas expelled by a forced, rapid 

expiration at the end of a normal expiration. The derived PAc02 and PA02 

will furnish an assessment of the lungs' function in gas exchange between 

the tissues and the external gaseous environment. In addition, repeated 

daily measurements. of PAc02 will provide valitative.indications of acid'- 

base derangement and, by judicious examination of sequential changes, whether 

such derangement is primarily respiratory or metabolic. 

(3) Discrete oxygen utilization. Measurement of individual oxygen 

consumption rates-at specific phases and levels of activity will be carried 

out by the open circuit method utilizing. he Mli1lsr-Franz dry test meter 

and.analysis of. automatically collected mixed expired gas. Direct measure- - 

ment of this parameter requires the pretence of an_inert gas in the environment, but-an accurate estimate can. be obtained.by the same method even in 

.the absence of an .inert gas. •EXcept for special test requirements (such 

.as basal state measurements), this determination can be tarried out without 

interferehca with other. ssigned duties. Information derived by calculation 

from.the test:will. aaso provide'data on carbon dioxide production, respiratory exchange ratio (respiratory quotient when a steady state exists), and 

.minute expiratory volumes. In addition-to its extrapolative value for 

prolonged mission system design features, such.information will also provide 

a measure of man's acclimatization to the weightless'state in terms of 

efficiency of physical movements. 

• 

(4) .Carbon dioxide response curves. By permitting the subject to 

rebreathe into a suitable:volume of- 100%-,02, carbon dioxide concentration 

will increase in a regular manner: By.measuring the end-tidal concentration 

.of CO2, together with the instantaneous ventilatory rate by integration of 

the signal-from-a serially connected pneumptichomiter, a dose-response curve 

for carbon.dioxide is obtained. From such,information garnered periodically, 

the state of CNS respiratory regulation mechanisms can be-ascertained. If 

acclimatization.to carbon dioxide is taking,plaCe, the quantitative progress 

to this end can also be evaluated.. The former area can be best assessed 

by making the test during.sleep. That -would require the services of the 

second astronaut for a maximum period of 10 minutes. 

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(5) Maximal breathing capacity (MBC). Measured by maximal voluntary hyperventilation through the pneumotachomecer for a 15-second period. 

This will also serve as a cardiovascular test sequence. The MBC is a 

reliable, well-standardized, reproducible index of total expiratory potential in healthy stimulated individuals. It affords not only an estimate 

of actual parenchymal function but also provides an estimate of musculoskeletal coordination, psychological motivation, and alertness. It provides 

a relatively more sensitive index of airway resistance than the TVC. The 

deep forced respiration necessitated by this measurement can also be regarded 

as a form of respiratory exercise with beneficial effects. 

(6) Pulmonary compliance. A single experimental point will be 

measured on the combined relaxation pressure volume curve of the lung and 

chest. This will be obtained by relaxing the chest at a known lung volume 

while the open airway is connected to a pressure transducer. The pulmonary 

compliance is calculated from the slope of the line connecting this point 

to the origin. Changes in this parameter may be used as an index of venous 

admixture and will give early indications of alteration in pulmonary blood 

volume distribution and parenchymal tissue damage. 

(7) Breath sounds. A suitable microphone will be used, if available, 

for transmission of chest sounds from preselected points on a real-time or 

T/M basis. If other measures of pulmonary function detect clinically 

significant changes, the astronaut will be instructed to place the microphone in a specified sequence on predetermined locations of the chest. 

This will serve as a further diagnostic aid to the physician on duty at 

the Mission Monitoring Station. 

d. Category of experiment 

All tests performed in the area of respiration fall into Category a. 

The results will contribute directly to the 101. program primary objective 

by providing information on which to base the decision of whether or not 

respiratory function will prove limiting to man's realization of full 

operating potential in a military space mission. Respiratory function 

tests will pay a major role in design characteristics in that they will 

provide the most sensitive detection and direct physiologic reflection of 

possibly debilitating contaminants in the atmosphere. 14DL system validation 

procedures should be incorporated with the bioastronautics ground tests for 

these reasons. 

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e. Cost 

All test items are "on-the shelf" and require no further development nor any special installation. The only exception to this is the 

engineering and development of suitable gas'analysers. Since it is proposed 

only to place a further requirement on those used for environmental control, 

their cost considerations do not appear here. 

f. Schedule 

(1) All items are presently available for test. 

(2) Flight readiness date of test items can be set within 30 days 

after procurement. 

IV. Participating Government Agencies 

Sponsor: SAM; Dr. Stephen M. Cain and Captain Paul M. Stevens 

Test Equipment Acquisition : SAM and SSD 

V. Additional Requirements 

a.- Special security:,Results of this test are identical to medical 

status data.and only limited access should be granted.. 

b. Manning description summary: To be determined. 

c. Logistics: To be determined. 

.d. Facilities: For evaluation of test items and procedures as well 

as preliminary training•of MOL candidates, facilities of USAF SAM can be 

used without modification. A completyMOL simulation run in a low pressure 

chamber with provisions for actual mission simulation will be required for 

final training and control data acquisition. 

e. Simulation and training 

(1) Astronaut 

,AnymotiVated intelligent person can be trained sufficiently 

well to carry out these tests successfully: Graduates of the Space Research 

Pilot's Sthool, for .example, would be suitable. Some indoctrination into 

the physiologic reasons for the tests voularbe impaited to provide enough 

understanding so that the importance of the tests became intuitively selfevident. After thorough familiarisation with the tests under ideal laboratory conditions (approximately 1 to 2 weeks), training would by restricted 

to full dress-rehearsal in Ma simulator. 

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(2) Ground personnel 

Competent, experienced professional personnel will be 

required to make appropriate judgments of the quality of data received 

daily and to make fully qualified recommendations on the basis of such 

data, either in respect to mission safety or possibly with respect to some 

treatment or therapy when indicated. 

- (3) Equipment: (See'Configutation'of test items" above.) 

VI. General 

a. Communications and data-handling equipment: (See Bioinstrumentation Section.) _. 

b. Development characteristics: N/A. 

c. Annex - Section 6 - Respiration: (Attached) 

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ATTACHMENTS TO AREA 6 

1. Design Characteristics Test Equipment: To be determined 

2. Test Support Equipment: To be determined 

3. Test Operating Characteristics: N/A 

4. Funding Summary: To be determined 

5. Manning Description: To be determined 

6. Communications and Data Handling: To be determined 

7. Development Characteristics: To be determined 

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7. Study and Control of System Deterioration and Associated with 

MOL Missions. 

One of the most important and completely unstudied problems of 

manned space flight relates to the cumulative, time-dependent, and 

adaptive changes of prolonged exposure to weightlessness. It is 

probable that extended exposure to zero gravity will result in 

deterioration of certain gravity oriented physiologic systems by disuse. Such deconditioning in an environment of reduced or absent 

gravitational force may seriously impair man's ability to tolerate 

normal or increased gravitational forces after this exposure. The 

problem becomes: How can gravity oriented biologic systems be 

maintained in the absence of gravity? 

• An astronaut support program must be devised which will insure 

maintenance'of physical well-being during and subsequent to deorbit 

and provide information necessary to extend man's operational effectiveness for longer duration missions. 

Although ground based laboratory research has been and will 

continue to be vital in the definition of the magnitude of this potential 

problem area, validation of the experiment al data can be made only 

in the weightlessness of space. 

Manned orbital experiments of one and two-week duration preceding MOL are expected to provide information. vital to this area and 

will permit rational modification of this test protocol as operational 

information becomes available. 

a. Configuration of the Test Items 

(1) Muscle Conditioning Technique 

The Soviets have placed great emphasis upon the 

requirement for effective muscle exercise regimens during prolonged 

exposure to weightlessness. From the onset of their man-in-space 

program they have utilized inflight exercise routines• designed to 

maintain anti-gravity muscular effectiveness. Their early regimen3 

apparently were primarily isometric in nature. In addition to the 

isometric exercises of his predecessors, Cosmonaut Bykovskiy 

utilized an isotonic devicel suggesting that isometric exercises 

alone may not not have been entirely adequate. Continued and 

increased emphasis on this requirement, despite the information 

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available to them from orbital flights of up to five day's duration, 

suggest that perhaps even the isometric-isotonic combination may 

not be completely effective and may require revised concepts. 

Information derived from ground based deconditioning 

studies indicate that with prolonged exposure to relatively hypodynamic conditions, programmed muscular exercises are sequired 

to maintain control level musculoskeletal effectiveness. ' 

It appears mandatory that a specific muscle exercise 

regimen will have to be incorporated into.the MOL for routine use 

and an effective exercise schedule developed. 

An approach which appears to offer some promise and 

which can be easily integrated into the MOL vehicle is the use of the 

bicycle ergometer technique. This device can be engineered to 

exercise both upper and lower extremities simultaneously, thereby 

involving all major muscle groups in a combined isometric-isotonic 

approach. 

It can be designed into the astronaut's "rest and test" 

area as part of a couch or platform which also will serve as the site 

of selected biomedical testing and as the sleeping area or facility. 

Having previously been calibrated during ground studies 

to arrive at optimum astronaut work rates, this technique lends itself 

to precise quantification of total work performed. 

It is probable that with appropriate design of the 

ergometer, useful work can be derived such as operation of a 

generator or battery charger. 

This device should meet the demands br.maintenance 

of musculoskeletal (and, in part, cardiovascular) effectiveness during 

MOL, be adaptable under dynamic operational conditions and have 

a growth potential for longer duration missions. 

,(2) Saace &fit Modification to Permit Deorbit Counterpressure, If Reauired 

Literature available from deconditioning research to 

date, using bed rest and immersion techniques reveals that deficiencies of blood volume and venomotor tone appear to play a prominent 

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role in the altered stress tolerance following such deconditioning. 

Several such studies have amply documented the effectiveness of 

a bladder type G-suit, or a modified lower torso and extremity 

counterpressure suit, to compensate for both blood volume 

deficiencies and altered venomotor tone. Such simple mechanical 

devices restore control equivalent stress tolerance. 

In light of available information it appears to be 

highly desirable to design this capability into our astronaut support 

systems for expected probable use during. deorbit. It can be considered a reliable, simple, mechanical form of insurance. 

A separate quick-don counterpressure garment consisting of what amounts to an optimization of the existing operational 

G-suit may prove to be more feasible than integrating this capability 

into the space suit. It could have its own separate air source, if 

necessary, and can be designed and fabricated to have minimal weight 

and volume. 

(3) Muscle Strength Measurements 

Direct readings of the strength of any particular 

muscle group, especially the anti-gravity musculature, on a routine 

basis will be mandatory for assessing effectiveness of cosmonaut 

support techniques such as muscle exercise and to permit valid 

predictions of astronaut physical potential during deorbit. 

Available evidence indicates that musculoskeletal 

adaptation to weightlessness is time dependent and indicators of 

this will be of continued interest for astronaut support during future 

longer missions. 

An electrical strain gauge dynamometer will be 

developed which will have minimum size weight and power requirements and will provide reliable quantitative readings of strength 

of selected muscle groups. 

(4) Blood Volume Determinations 

Literature available from deconditioning research 

indicates that blood volume, having adjusted to experimental hypodynamic requirements, may be substantially decreased from control 

values and play a prominent role in the reduced stress tolerance 

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resulting from such studies. Additional information suggests that 

such readjustment of blood volume is progressive with time at least 

up to several weeks before plateauing is evident. Although there are 

many factors to consider, a reduction in circulating blood volume has 

been evident in all astronauts to date (including Cosmonaut Titov)4 

in the immediate recovery phase. 

The configuration of this test item is as described in 

the cardiovascular section. It has been considered in this discussion 

because of its important role in cardiovascular capability and general 

physical conditioning. High priority should•be given this test item. 

Blood volume determinations must be made periodically, 

at approximately weekly intervals, using Evan's blue dye or some 

operationally suitable modification of this technique. Inflight real 

time analysis must be done by the crew members and results recorded 

on tape and reported. Plasma expanders must be made available and 

administered prior to deorbit, if significant decrease in circulating 

blood volume is evident. This will insure optimization of astronaut 

physical capability. 

(5) Measurements of Vascular Reactivity 

The vascular system of the astronaut must be assessed 

periodically to evaluate the integrity of circulatory mechanisms having 

countergravity role such as venomotor tone, arteriolar responsiveness, 

and rate control reflexes. Such assessment can provide information 

about adequacy of astronaut support techniques and predict astronaut 

stress tolerance and possible deorbit support requirements. 

Such measurements will include: 

(a) Blood pressure and pulse rate response to 

calibrated exercises as described in cardiovascular section. 

(b) Cardiac output determination before and 

during calibrated exercise as described in cardiovascular section. 

(c) Blood pressure and pulse rate response to a 

calibrated Flack test. 

Equipment for this test procedure will consist of an 

aneroid type pressure sensing device with the dial calibrated to read 

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from zero to the equivalent of 40 mm Hg. This will be positioned in 

such a manner that the astronaut by blowing into a mouthpiece through 

tubing can visually maintain a programmed pressure value for a given 

number of seconds. 

(d) Blood pressure and pulse rate response to 

a calibrated venous occlusion test. 

Equipment for this will consist of quick-don 

extremity or abdominal tourniquets which, when inflated to a predetermined value, will reduce venous return to the heart simulating, 

in part, orthostatis. The aneroid type pressure sensing device used 

in the previous test may have application to this test as a monitor 

of inflation pressure. 

(e) Blood pressure and pulse rate response to 

calibrated negative pressure applied to the lower half of the body. 

This device can be designed into the "rest 

and test" area mentioned in item (1), muscle conditioning techniques. 

Equipment would consist of a rigid shell device which can be integrated 

with the sleeping platform, be designed to isolate the lower half of 

the astronaut's body. Calibrated negative pressure can then be 

applied causing significant body fluid trapping simulating orthostasis 

or even multiple +Gz. The amount of negative pressure required is 

yet to be determined, but should be minimal permitting the hard shell 

device to be very light-weight. 

Such a device may find additional use as a 

sleep facility and also may prove to have some usefulness as a 

cardiovascular maintenance technique but this remains to be defined 

by ground-based studies. 

(f) Some indication of venomotor responsiveness: 

Existing direct techniques are not 

operationally feasible. 

An attempt will be made to develop an 

indirect method of measuring venous tone using a tonometer -- closed 

venous segment technique. Such a device, if it can be developed within thi time allowed, should be light-weight (50 gms), small in size 

and have minimal power requirement. 

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High priority should be given the development 

of this test item in an operational utilizable configuration because of the 

prominent role played by venomotor tone in cardiovascular responsiveness and the probability that the venous side has a significant role in 

cardiovascular deconditioning. 

(6) Periodic Blood and Urine Aliquots 

At this time it appears feasible to go for a 30-day 

mission with no real time analysis of blood and urine data providing 

reliable information has been obtained from preceding manned orbital 

experiments. 

Blood must be drawn periodically and the plasma 

samples frozen and stored. Urine aliquots must also be taken 

periodicilly, frozen and stored. Total urinary outputs must be recorded 

on each test day. 

The technique of sampling and aliquot preparation and 

storage is as described in genitourinary and gastrointestinal sections. 

Frequency of such measurements is not critical for this area and will 

depend upon priorities established by these sections. 

In the later post deorbit analysis of these samples particular attention will be devoted to those determinations which reflect 

adequacy of astronaut inflight conditioning techniques and provide 

more basic information on tolerance of man for longer duration missions. 

Such considerations will include calcium, phosphorus, and nitrogen 

mobilization studies and catecholamine-vascular reactivity interrelationships. 

(7) Additional Astronaut Support Considerations 

Other techniques and devices for as tronaut support 

are being actively considered for possible application and are de 

signed to attempt to compensate for lack of gravity without going 

to artificial gravity. 

One such group of techniques is aimed at maintenance 

of cardiovascular adaptability: 

(a) Intermittent positive pressure breathing. 

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(b) Periodic venous occlusion. 

(c) Automatic conditioning. 

Another device which appears promising is a whole body 

longitudinal vibrator to provide some measure of cardiovascular conditioning as well as musculoskeletal. 

The potential of these various:considerations remains 

to be 'established by ground based deconditioning studies. It may be 

that a deorbit counterpressure device used to compensate for 

anticipated deterioration of countergravity cardiovascular mechanisms 

may be effective and reliable enough to permit extended flight with 

no special cardiovascular maintenance techniques. 

b. Test Support Equipment Required 

(1) Spacecraft 

(a) Negative pressure source capable of periodically 

reducing the pressure in a lower body rigid shell device for time 

durations of from 2-20 minutes. Optimum amount of negative pressure 

remains to be determined but expected to be minimal. 

(b) Positive pressure source capable of periodically 

pressurizing various components of astronaut support equipment to 

pressure tames of 10-60 mm Hg equivalent. 

(c) A device for freeze-dehydrating urine and serum 

aliquots -- described in genitourinary and gastrointestinal sections. 

(d) A technique and device for real time blood volume 

determination -- described in cardiovascular section. 

(e) A device such as a centrifuge or microscope filter 

for separation of particulate constituents from body fluid samples. 

(f) Power requirements are• expected to be minimal 

and could be met by appropriate design of the exercise ergometer 

device to produce useful power. 

(g) A positive pressure source for use during deorbit 

to pressurize astronaut support equipment. This requirement could 

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be met by a small high pressure source carried out on the astronaut 

and possible integrated within his suit. 

c. Test Procedure 

(1) General: The tests involved in this astronaut support 

plan are designed to accomplish two intimately related goals. They 

can logically be classified into one group of tests designed to provide 

control of system deterioration and another group of tests designed 

to permit periodic evaluation of.. system deterioration. The first 

group consists of the muscle exercise device designed to maintain 

musculoskeletal effectiveness and the deorbit counterpressure device 

designed to compensate in part for possible cardiovascular deficiencies resulting from prolonged zero gravity exposure. The second 

group of tests include periodic muscle strength testing, vascular 

reactivity assessment, blood volume determinations, and collection 

of aliquots of serum and urine for later analysis. This group is 

designed to monitor the degree of system deconditioning, indicate 

adequacy of control measures, and permit valid predictions of 

astronaut deorbit stress tolerance and•deorbit support requirements. 

The post flight analysis of serum and urine samples will further 

define adequacy of control measures and will provide additional 

information on tolerance of man for longer duration missions. 

(2) Exercise: The exercise ergometer device will be 

operated on a programmed basis by both astronauts. The precise 

schedule remains to be-established by ground based studies. Information from the Gemini and Apollo one•and two-week missions 

will permit rational modifications of this test procedure. Particularly 

desirable would be an approach wherein only one astrqnaut would 

employ the exercise device, the other remaining as control. It 

remains to be determined if this can be done without compromising 

flight safety. 

The ergometer will have been calibrated for a predetermined work rate so that to perform a programmed amount of 

work the astronaut need only to operate the device for a certain time 

period. Information available from ground based studies indicates 

that optimum work rates may be from 200 to .600 cal/hr with total 

work of from 100 to 200 cal/24 hrs. This approach to maintenance 

of musculoskeletal effectiveness has the flexibility to permit reprogramming of total work requirements at any time inflight in 

accordance with the results of periodic muscle strength testing. 

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It is probable that the exerciser will have to be operated at least once 

per 24 hours and possible twice, although the time periods and total 

time remain to be established. 

(3) Deorbit Counterpressure: The counterpressure device 

will be inflated prior to deorbit as a prophylactic support measure 

based upon results from periodic assessment of cardiovascular responsiveness. It may also be feasible to initiate deorbit without 

counterpressure and pressurize only if necessary, in response to 

blood pressure, pulse rate and subjective evidence of inadequate 

venous return. 

(4) Muscle Strength; For muscle strength measurements, 

the strength of preselected muscle groups will be assessed in a 

standardized manner on approximately a weekly basis using a dynamometer technique. Results will be read and recorded on tape. 

Existing methods for this type of testing are not suitable for 

operational use except for limited muscle groups. The device to be 

developed for MOL will be lightweight and small in size, will have 

minimal power requirement, and will permit rapid and reliable testing. 

(5) Flack: The calibrated Flack test will be administered 

approximately weekly. This test is usually performed by holding 

the equivalent of 40 mm Hg pressure at expiratory apnea for a given 

number of seconds. It is suggested that lower pressures be used 

earlier in the mission until response profiles have been estalished 

and that the standard Flack be preceded by a preliminary "minimal 

Flack" at each test session. During each test blood pressure and 

heart rate will be recorded on tape. 

(6) Venous Occlusion: The calibrated venous occlusion 

test will also be administered at approximately weekly intervals. 

It will consist of the astronaut applying to himself quick-don 

extremity or abdominal tourniquets and inflating them to a pressure 

equivalent of approximately 60 mm Hg for a programmed period of 

time. During this time blood pressure and heart rate will be recorded on tape. 

(7) Negative Pressure; To test the response to negative 

pressure applied to the lower half of the body the astronaut will 

insert himself into the device which has been integrated into the 

"rest and test" area and may be doubling as a sleeping facility. 5 

He will pressurize a waist seal which will permit calibrated 

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negative pressure to be applied to the lower half of his body for a 

programmed period of time. During this time blood pressure and 

heart rate will be recorded on tape. Evidence available from ground 

based studies indicate that this technique may be of much more 

effective cardiovascular stress test than the calibrated Flack and 

venous occlusion and may replace them. 

(8) Venomotor Tone: Technique for venomotor tone remains 

to be determined. 

(9) Others: The testing procedures for the remaining items 

(blood volume, cardiac output, blood pressure and heart rate response 

to calibrated work and serum and urine aliquot collection) is as 

described in cardiovascular, gastrointestinal and genitourinary 

sections. 

(10) Sequence: The suggested testing sequence for those 

tests designed to periodically assess degree of system deconditioning 

is as follows: 

(a) Blood volume determination (serum aliquot). 

(b) Muscle strength testing. 

(c) Calibrated exercise. 

(d) Cardiac output. 

(e) Venomotor tone. 

(f) Flack. 

(g) Venous occlusion. 

(h) Negative pressure. 

d. Category of Experiment 

(1) Category a: The muscle exercise device appears to 

warrant this classification because it is a primary inflight astronaut 

support item and because it may involve elaborate equipment requirements. If adequate astronaut support for zero gravity deconditioning 

for..30klay MOL cannot be provided by such devices, artificial gravity 

appears to be the only remaining solution for support of man in this 

environment. 

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(2) Category b: 

(a) Deorbit counterpressure garment. 

(b) Muscle strength testing. 

(c) Blood volume. 

(d) Tests of cardiovascular responsiveness. 

(e) Urine and serum aliquots. 

e. Cost 

It is expected that the development of the devices, procedures, and equipment required for this area can be met by in-house 

facilities and personnel. 

f. Schedule 

Development of 6n operationally suitable muscle exercise 

device has already been started. Validated design criteria and 

exercise regimens should be available June 1965. 

A method for measuring the strength of selected muscle 

groups should be available by June 1965.. 

The deorbit counterpressure device is essentially 

optimization of an on-the-shelf item, the standard G-suit, and 

should be available as a separate item.by March 1965 and as a 

pressure suit integrated item (if desired) by January 1966. 

Techniques for assessment of cardiovascular responsiveness 

require minor modifications of existing equipment and procedures for 

the most part, and with the exception of venomotor tone measurement 

should be available by June 1965. An indirect simple and reliable 

venomotor tone technique should be available by June 1966. 

IV. Participating Government Agencies: 

Sponsor: Duane E. Graveline, Captain, USAF, MC, Aerospace 

Medical Division, Brooks AFB, Texas. 

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V. Additional Requirements: 

A. Special Security 

At this time there appears to be no justification for a special 

security classification of either the equipment or procedures which 

have been discussed. It is assumed that medical findings, preflight, 

inflight, and postflight, will be afforded the usual treatment of such 

data and be restricted to the medical community. 

B. _ Manning Description Summary 

1. Astronaut 

The following test items for control and evaluation of 

system deterioration will be designed for one man operation with 

this man serving both as subject and technician: 

a. Muscle exercise device. 

b. Deorbit counterpressure. 

c. Muscle strength testing. 

d. Urine aliquot preparation. 

e. Cardiovascular response to calibrated exercise. 

f. Cardiovascular response to calibrated Flack. 

g. Cardiovascular response to calibrated venous 

occlsuion. 

h. Cardiovascular response to calibrated lower 

body negative pressure. 

The following test items will involve both astronauts, 

one as a subject and the other as technician: 

a. Blood volume determination. 

b. Serum aliquot preparation. 

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c. Venomotor tone testing, 

d. Cardiac output determination during calibrated 

exercise. 

The level of technical competence required of the 

astronaut for effective performance of the various test items discussed 

for this area should be easily within his capability with a minimum of 

training. The configuration and procedures of all test items will be 

optimized for operational use. 

2. Ground Personnel 

There are no foreseeable requirements for ground 

personnel to participate directly in the test items described for this 

area. 

C. Logistics 

Described in Annex (Approach to Ground Based R&D). 

D. Facilities 

Described in Annex (Approach to Ground Based R&D). 

E. Simulation and Training 

Described in Annex (Approach to Ground Test Simulation and 

Training). 

VI. General 

A. Reference Specific Attachments 

I. Design Characteristics Test Eauipment 

For each test item in this astronaut support program 

the approximate equipment configuration, weight, volume and power 

requirements have been indicated under 7 a,• b, and o. Addditional 

more definitive information is not available at this writing. Total 

heat output from the muscle exerciser may range 50-200 cal/24 hrs. 

and will come during the once or twice daily programmed exercise 

periods. The exercise ergometer will be mounted in the astronaut 

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"rest and test" area as described in .7 a. The design configuration 

of this area remains to be established but will have special mounting 

requirements. Other items mentioned in the guidelines set down for 

this area are either not applicable or not definable at this time. 

2. Test Support Equipment 

Additional elaboration of support equipment requirements 

beyond that presented in 7 b is not possible at this time. 

3. Test Operating Characteristics 

An estimate of test duration, total number of test, 

test frequency and interval between test has been made in 7 a and c 

where appropriate. Other items referenced in the guidelines do not 

appear to bo applicable at this state of planning. 

4. Funding Summary 

Ground based research and development requirement 

for the test experiments, procedures and equipment discussed in 

this section can be met with existing in-house personnel and 

facilities. 

5. Manning Description 

As described in V b. Further elaboration cannot be made 

validly at this time. 

6. Communication and Data Handling 

For all test items considered in this area of control 

and evaluation of system deterioration the information obtained from 

the various measurement techniques (i.e., muscle strength, blood 

volume, cardiovascular responsiveness) will be either read visually 

and recorded on tape or recorded directly on tape for subsequent 

fast playback during passage over selected stations. 

7. Development Characteristics 

Most of the items pertinent,to this area have been 

discussed in 7 f and in Annex (Approach to Ground Based R&D). 

B. Reference Annex VII, Study and Control of System Deterioration 

and Associated with MOL Mission. 

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SPACE RADIATION MEASUREMENTS OF SIGNIFICANCE TO MAN 

I. Test Objectives: 

The objectives of the radiation environment measurements or studies 

are to 

A. Provide the necessary instrumentation for monitoring the intraand extravehicular ra&ation environment of the MOL, 

B. Update existing space radiation maps, at low orbital altitudes, 

C. Validate or update computer programs and to provide more 

accurate predictions for future flights, and to 

D. Establish inflight biological values which may be used as "biodosimeters" or indices or radiation dose in the event of accidental exposure. 

II. Importance of the Test: 

A. The test program is needed because: 

1. For many years investigators have been active in studying 

the basic mechanisms of action of ionizing radiation as it interacts with 

biological tissue. From these studies, measurements have evolved which 

are relatively dose-dependent (biodosimeters). Although not entirely satisfactory, because of individual and even time-of-day variability, and 

because these same biological values may also be influenced by disease 

processes, they are accepted as valuable tools in diagnosis, prognosis, 

and therapy. 

Now we are faced with the possibility that many of these biological value s 

may change as the astronauts are subjected to conditions of weightlessness, 

altered atmospheric conditions, etc., encountered on a space mission. It 

is therefore necessary to a) establish new inflight values, b) test the 

validity of using "biodosimeters" as indices of radiation exposure, and 

c) provide biological endpoints for estimating radiation dose in case of 

accidental exposure to a solar flare, although it is anticipated that the 

radiation doses encountered in the MOL flights will be below the threshold 

of detection by current biological techniques 

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2. Evaluation of the radiation environment as related to the 

vehicluar configuration (crew compartments) and possible launch configurations including a 30-day launch from either the AMR or PMR, with and 

without unfriendly action (detonation of a high-altitude nuclear device) during 

flight, resulted in the formulation of the following basic physical dosimetry 

requirements: a) determination of dose, dose rate, etc., for extravehicular 

space (dosimetry of free space); b) determination of dose, dose rate, etc., 

in selected crew compartments or positions; and c) selected personnel 

dosimetry in space operations. 

B. This test package must be included in the MOL program to provide 

crew safety and more accurate predictions of radiation environments for 

future space operations. 

III. Description of the Experiment. 

Studies designed for inclusion in the on-board MOL program fall into 

two general categories: 1) Biological and 2) Physical Dosimetry. 

Requirements for biological observations will be minimal and consistent with a policy of establishing base-line data from which radiation damage 

may be assessed in the event of accidental exposure. Ground-bases support 

studies will be continued to study the basic mechanisms of action of ionizing 

radiation and to develop techniques for the detection and quantitation of doses 

below 25 to 50 rads. 

Physical dosimeters will be provided in adequate numbers, types and 

location aboard the MOL to accomplish the objectives outlined in I above. 

Consideration is being given to a dosimetry package of minimal weight, 

volume, and astronaut time required for operation. It is anticipated or 

hoped that dosimetry measurements can continue to be made and telemetered 

to ground stations after completion of the programmed 30-day flights. 

A. Configuration of Test Items: 

1. Biological Observations: To be determined. It is assumed 

that these requirements will be consolidated with those of other test areas and 

that the data will be made available as required. 

2. Physical Dosimetry: 

a. Spectrometric Devices (Unmanned): (See atch 2) 

(1) Two (2) Plastinauts instrumented with tissue 

equivalent ion chambers; one located in the living quarters and one in the 

laboratory compartment. 

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(2) Tissue equivalent ion chambers, and LET (Linear 

nergy Transfer) spectrometers, giving surface, 5 cm., and 10 cm. dose 

and LET spectrum; located in the laboratory and unpressured compartments. 

(3) Externally mounted omni- and unidirectional proton, 

alpha, electron and heavy nuclei spectrometers located in the unpressurized 

compartment. 

(4) Internally mounted omnidirectional proton and neutron 

spectrometer located in the laboratory compartment. 

b. Spectrometric and Monitoring Devices (Manned): (See atch 3) 

(1) Portable tissue equivalent ion chamber (TEIC); high 

level for emergency) visual readout; located in Gemini. 

(2) Portable TEIC: low and high level; visual read-out; 

located in living quarters; to be operated continuously. 

(3) Omni-directional proton, and electron, spectrometer; 

portable; adjustable; located in laboratory compartment. 

(4) Portable TEIC, low level, visual read-out; to be 

operated continuously; located in laboratory compartment. 

(5) Fixed TEIC: high resolution:, in-flight calibration; 

located in laboratory compartment. 

(6) LET spectrometer; located in laboratory compartment. 

(7) Shields for depth-dose measurements. (for use with 

TEIC and LET Spectrometers). 

(8) Fixed TEIC: shielded to provide inside space-suit 

dose rate; located in unpressurized compartment. 

(9) Omni-directional proton, electron and alpha spectrometers for external environment measures; located in unpressurized compartment. 

(10) Cosmic ray emulsions; to be sensitized and extended 

from the MOL. 

c. Passive Dosimeters (Manned Flights): 

(1) Personnel dosimeters: Up to five (5) packs in the 

space suit of each astronaut (film, thermoluminescent dosimeters, etc.) 

Locations to be determined. Doses received by each astronaut should be 

recorded accurately end become a permanent part of his medical record. 

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(2) Dosimeter packages or units: Five units each to 

contain pocket chambers, film, thermoluminescent dosimeters, glass rods, 

foils, etc. One unit to be located in the Gemini vehicle, and two each 

in the living quarters and laboratory compartment respectively. 

B. Test Support Equipment Required: 

1. Biological Observations: To be determined. 

2. Physical Dosimetry: 

a. Spectrometric Devices (Unmanned): Will require approximately 0.6 watt continuously, 5.6 watts intermittently. 

b. Spectrometric and Monitoring Devices (Manned): 

(1) Equipment listed in III. A.2.b. will require 

approximately 0.6 watt continuously and 6 watts intermittently. 

(2) Tape recorder, telemetry, and voice communications 

required. Voice requirements will be minimal except in unanticipated 

emergency conditions (Occurrence of a solar flare or unfriendly action) 

or upon request after passage through the Cape Town anomaly. 

c. Passive Dosimeters: No power requirement. Voice communication for reporting pocket chamber readings following extravehicular 

operations. 

AGE 

1. Biological Observations: N/A 

2. Physical Dosimetry 

a. Spectrometric Devices (Unmanned): Telemetry and power• 

check only. 

b. Spectrometric and Monitoring Devices (Manned): Telemetry 

and power check only. Cosmic ray emulsions must be sensitized, extended 

from the MOL for a pre-determined time and returned. 

c. Passive Dosimeters: N/A 

C. Test Procedure 

1. Biological Observations: To be determined. A tentative list 

of requirements are listed below. 

a. Hematocrit: *L-14 and L-7; bi-weekly during flight; upon 

return and as indicated:thereafter. Use microPipette technique and small 

clinical centrifuge. ' 

* L Day of Launch 

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b. Blood Volume: Determinations on L-7 at weekly intervals 

during flight and upon return. Technique to be determined. 

c. Reticulocyte and platelet counts: Determination on L-7 

and L-1, and at weekly intervals during flight, assuming that insignificant 

radiation levels are encountered. Slides can be prepared and returned 

for evaluation. If high dose levels are measured, then determinations 

will be performed as directed by the ground monitoring station. If methods 

are available or can be developed for WBC determinations, counts should 

be performed at weekly intervals during flight, or as required, since 

this is one of the most sensitive indicators of radiation exposure. 

d. Differential Counts: Preflight determinations will be 

made on L-7 and L-1. Slides can be prepared at weekly intervals during 

flight and returned for staining and evaluation. Post-flight determinations to be made upon return and as indicated thereafter. 

e. Serum Electrolytes: Determinations at L-7 and L-1. 

Serum samples to be collected at weekly intervals and stored for analysis 

upon return. 

f. Additional tests on serum and uripe samples returned to 

ground laboratories are being considered. 

2. Physical Dosimetry: 

a. Spectrometrin Devices (Unmanned): Data readout would be 

accomplished at specified intervals which are to be determined. 

b. Spectrometric and Monitoring Devices (Manned): The majority of data obtained will be taped and transmitted without reference to 

the man. On a few orbits passing through the magnetic anomaly and during 

a solar flare the astronauts would be requested to move the portable spectrordtry and dosimetry package to various preassigned positions within the 

space'craft, and read out variations in cabin intensities. A series of 

dose rate measurements and LET spectral measurements through different 

thicknesses and kinds of shields would be requested as part of the experiment. During extravehicular operation the•astronaut might be asked to 

relay dose rate information from en easily read portable dosimptric 

device. 

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c. Passive Dosimeters: 

No single passive dosimeter, currently available, can 

adequately record the total radiation dose from the many types of particles 

and energy spectra encountered in space. Various types of dosimeters, 

having definite physical characteristics, will have to be calibrated against 

known ground sources--cyclotrons, x-ray units, etc.--and incorporated into 

a package to cover the radiations and energies expected. Any advances in 

the state-of-the art will be included in this package. Ideally, a pocket 

dosimeter capable of distinguishing between doses of protons, electrons, 

and electro-magnetic radiations would be desirable. 

D. Category of Experiments: The tests outlined above fall within 

Category b. 

E. Cost: 

1. Biological Observations: To be determined. 

2. Physical Dosimetry: 

a. Spectrometric Devices (Unmanned): Approximately 830K 

Does not include integration costs, backup packages, or spare parts. 

(See etch 2 - FUnding Summary) 

b. Spectrometric and Monitoring Devices (Manned): Approximately 762K. Does not include integration costs, backup packages or 

spare parts. (See Atch 3 - FUnding Summary) 

c. Passive Dosimeters: To be determined 

F. Schedule: 

1. Biological Observations: To be determined. 

2. Physical Dosimetry: 

a. Spectrometric Devices (Unmanned): Items except neutron 

spectrometer are developed and flight worthy. The neutron spectrometer 

should be ready by July 1965. 

b. Spectrometric and Monitoring Devices (Manned): Same as 

F.2.a. 

c. Passive Dosimeters: As stated previously, many types of 

passive dosimeters are available but none is completely inadequate for 

space flights. A calibrated package containing the best available dosimeters should be ready by JUly 1965. Advances in the state-of-the-art 

will be incorporated as more reliable dosimeters become available. 

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IV. Participating Government. Agencies: 

A. Sponsor: 

1. Biological Observations: AND 

2. Physical Dosimetry: 

a. Spectrometric Devices (Unmanned):. AMD 

b. Spectrometric and Monitoring'Devices (manned): AND 

c. Passive Dosimeters: AND 

B. Test Equipment Acquisition: 

1. Biological Observations: To be determined 

2. Physical Dosimetrx.: 

a. Spectrometric Devices (Unmanned): Air Force Weapons 

Laboratory. 

b. Spectrometric and Monitoring Devices (Manned): Air 

Force W

e

apons Laboratory. 

c. Passive Dosimetry: SAM and AFWL 

V. Additional Requirements 

A. Special Security: None 

B. Manning Description Summari: 

1. Biological Observations: Astronauts to alternate as subject 

and as testor. 

2. Physical Dosimetry: 

a. Spectrometric Devices (Unmanned): N/A 

b. Spectrometric and Monitoring Devices (Manned): One man 

required ten minutea per.oebit for 3 orbits/day at beginning of flight, 

with periodic check at 5 day intervals thereafter (unless more frequent 

checks are required by the ground station in the event of a solar flare) 

(See Atch 3) Specific details to be determined. 

c. Passive Dosimeters: Prior to extravehicular operations 

pocket dosimeters must be set to "zero" and read upon completion of the 

extravehicular mission. This information should then be passed to the 

ground station via radio as soon as possible. During extravehicular 

operations, the astronaut remaining aboard the MOL should monitor the 

'ead-out of the external radiation environment spectrometer for necessary 

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action in case of an emergency situation. The only additional requirement would be to recover five (5) dosimeter packages (two in the living 

quarters and the laboratory compartment, respectively and one in the 

Gemini capsule) near the end of the flight and return to the ground laboratory. 

C. Logistics: 

1. Biological Observations.: 

a. Manpower: 3 . MY required during FY65. 

b. Hardware Development: Off-the-shelf items with minor 

modifications. 

c. Operation: N/A 

d. Additional Support: None 

2. Physical Dosimetry: 

a. Manpower* 

b. Hardware Dev. 

c.. Installation 

d. Operation 

e. Additional support 

TOTAL 

*Manpower figures furnished are AFWL scientists and technicians now directly engaged in space radiation and biophysics studies 

in support of Air Force requirements who could be diverted to this task. 

Will include ground support and associated sattelite programs. 

f. Passive Dosimeters: 

(1) Manpower: Two-man-years FY 65 

(2) Hardware Development: Off-the-shelf items, with 

modifications to incorporate advances in state-of-the art. 

(3) Installation: N/A 

(4) Operation:. N/A 

(5) Additional Support: N/A 

D. Facilities: No additional special facilities required. 

E. Simulation and Training 

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cY 65• 

24 MY 

cr 66 

20.5MY 

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69.5NY 

0 0 0 0 

0 1.0MY 4.5MY 5.5MY 

0 A 0 0 

0 0 0 0 

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1. Biological Observations: 

a. Astronaut: Must be able to perform certain biological 

tests, which are to be determined, at a technician level. Training for 

this task will be incorporated with those of other test areas in the 

Biomedical Experiment. 

b. Ground Personnel: None required. 

c. Training Equipment: Equipment will be the same as planned 

or developed for MOL flights. 

2. Physical Do4imetry: 

a. Spectrometric Devices (Unmanned): N/A 

b. Spectrometric and Monitoring Devices (Manned): 

(1) Astronaut: No special skins or knowledge required 

not expected to be possessed by the typical astronaut. Technician level 

training is adequate. Simulation test run would be desirable. Checkout of instrumentation operation would require about one to two days for 

indoctrination. 

(2) Ground Personnel: One or two highly skilled professilmal persons would be used to relay specific instructions during solar 

flare active periods or during magnetic anomaly experiments. These would 

be provided by the laboratory performing the experiment. 

(3) Training equipment would consist of prototype models 

of scientific instruments and data display panel. 

c. Passive Dosimeters: 

(1) Astronaut: One to two manhours training required for 

reading and repair of dosimeters. 

(2) Ground Personnel: None 

(3) Equipment: Training to be accomplished through the 

use of equipment that will be used on MOL. 

VI. General: 

A. Biological Observations: 

1. Ctomunications and Data Bandling Requirement: Lab note book 

and voice. (Data to be reportied upon completion of required. laboratory 

,:ests). 

2. Development characteristics: N/A 

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B. Physicol Dosimetry 

1. Sect: p....._221LcDevicobUn 'o:i ..___LLj lanned: 

a. Communication and Data Handling Requirements: Telemeterina of data stored on magnetic tape would be required. (See Atch 2) 

b. Development Characteristics: (See Atch 2) 

2. Spectrometric and Monitoring Devices (Manned): 

Communications and Data Handling Requirements: Telemetering 

of data stored on tape, would be required. Some voice communication might 

be required on occasion. (See Atch 3) 

Cosmic ray emulsions should be returned to the ground laboratory for evaluation only. 

3. Passive Dosimeters: 

a. Communications and Data Handling Requirement: Voice contact with ground station following completion of extravehicular operation. 

Return five dosimeter packages to ground at end of mission. 

b. Development Characteristics: N/A 

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Atch 1 - BIOLOGICAL MEASUREMENTS 

Design Characteristics Test Equipment -- To be supplied 

Atch 2 - SPECTROMETRIC DEVICES (UNMANNED) 

Test Support Equipment -- To be supplied 

Atch 3 - SPECTROMETRIC DEVICES (MANNED) 

Test Operating Characteristics -- To be supplied 

Funding Summary -- N/A 

Manning Description -- See V. b. and c. 

Communications and Data Handling -- N/A 

Development Characteristics -- Off the shelf 

Atch 4 - GROUND-BASED EXPERIMENTS 

Atch 5 - BACKGROUND INFORMATION ON THE SPACE RADIATION 

ENVIRONMENT ON THE BIOLOGICAL EFFECTS OF 

IONIZING RADIATION. 

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ATTACHMENT 1 

• 

BIOLOGICAL MEASUREMENTS 

a. Hematocrit: *L-14 and L-7; bi-weekly during flight; upon 

return and as indicated thereafter. Use micropipette technique and small 

clinical centrifuge. 

b. Blood Volume: Determinations on L-7 at weekly intervals 

during flight and upon return. Technique to be determined. 

c. Reticulocyte and platelet counts: Determination on L-7 

and L-1, and at weekly intervals during flight, assuming that insignificant 

radiation levels are encountered. Slides can be prepared and returned for 

evaluation. If high dose levels are measured, then determinations will be 

performed as directed by the ground monitoring station. If methods are 

available or can be developed for WBC determinations, counts should be 

performed at weekly intervals during flight, or as required, since this is 

one of the most sensitive indicators of radiation exposure. 

d. Differential Counts: Preflight determinations will be made 

on L-7 and L-1. Slides can be prepared at weekly intervals during flight 

and returned for staining and evaluation. Post-flight determinations to be 

made upon return and as indicated thereafter. 

e. Serum Electrolytes: Determinations at L-7 and L-1. 

Serum samples to be collected at weekly intervals and stored for analysis 

upon return. 

f. Additional tests on serum and urine samples returned to 

ground laboratories are being considered. 

L ■ Day of Launch 

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SPECTROMETRIC AND DOSE MEASURING DEVICES (UNMANNED FL/ORTS) 

Location Instrument 

Weight 

(lbs) 

Volume 

(ft..)) 

Power 

(watts) 

T.M. 

Points 

Gemini 1. Tissue of equivalent 

ion chamber; low and 

high level 2.5 0.06 0.3 4 

Living 2. TEIC, low and high 

Quarters level 2.5 0,06 0.3 4. 

3. Instrumented Tissue 

Equivalent Manikin 150.00 12.00 - 2.5 80 

Laboratory 4. Omni-directional 

spectrometer;' protons 

10-200 Mev. electrons 

0.5-2 Mev. neutrons 

(thermal and fast) 4.5 0.10 1.5 12 

5. Fixed TEIC, high 

resolution 2.5 0.06 0.4 6 

6. LET Spectrometer 6.0 0.15 1.5 64 

7. Instrumented Tissue 

Equivalent Manikin 150.00 12.0 2.5 80 

unpressurized 8. Fixed TEIC, inside 

Compartment • space suit dose-rate 2.5 0.06 0.4 4 

9. Omni.;directional 

spectrometer. Protons 

50-250 Mev; electrons 

0.5-5 Mew and alphas 6.0 0.20 1.5 15 

10. Unidirectional 

charged particle . 

spectrometer (Philco) 

(protons, electrons, 

alphas, and heavy 

nuclei 15.0. 0.20 8.0 25 

341.5 24.89 18.9 294. 

Equipment should operate 30 minutes per orbit for 3-6 orbits per day 

(1 1/2 3 hours total operating time per day) 

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SPECTRO:ZTRIC AND DOSE VXASUR/NG DEVICES (MANNED) 

Weight Volume Power 

Location Instrument (lbs)• (ft.') (watts) 

T.M. 

Points 

Gemini 1. Portable TEIC*, high 

level for emergency. 

Fisual read-out • 2.5 0.06 0.3 3 

Living 

Quarters 

2. Portable TEIC, low 

and high level. Visual 

read-out 2.5 0.06 0.3 4 

Laboratory 3. Omnidirectional Spectrometer. Protons 

10-200 Mev; electrons 

0.5-2 Mev 4.5 0.10 1.5 12 

4. TEIC, low level, high 

resolution, visual 

read-out. Portable 

option 2.5 0.06 0.3 4 

5. LET Spectrometer 6.0 0.15 1.5 64 

6. Shields for depthdose measurements 

(TEIC and LET) 4.0 'o.lo ---- ---- 

Unpressurized 

Compartment 

7. Fixed TEIC-inside 

space suit dose-rate 2.5 0.06 0.4 4 

8. Omni-directional 

Spectrometer. Protons 

50-250 Nev., electrons 

0.5-5 MAY and alphas 6.0 0.20 1.5 15 

Passive 

Dosimeters 

1. High-level pocket 

chamber in Gemini 

2. Personnel Dosimeters 

(up to 5 packs in 

space suit of each 

astronaut) 

3. Dosimeter packages 

1 in Gemini 

2 in Living quarters 

2 in Laboratory 

5 at 0.2 lb 1.0 0.03 

- 

none none 

ftsmic ray emulsions• 10.0 0.20 

- 

none none 

-- 

* Tissue Equivalent Ion Chamber 

Notes Only instruments Nos. 2 and 4 vill be operated continuously,,requiring 0.6 watt continuously, and 5.0 watts intermittently (1 1/2-3 hrs. 

per day) 

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GROUND-BASED RADIATION EXPERIMENTS IN SUPPORT OF MOL 

The ground or laboratory studies, outlined below, basically reflect 

on-going and/or planned investigations at the Air Force Weapons Laboratory, 

Kirtland, N. M. and the School of Aerospace Medicine, Brooks Air 

Force Base, Texas. It is anticipated that "inputs" or proposals from 

other DOD and NASA laboratories, will be considered along with the ones 

listed in this report and that the ground support studies will be revised 

to obtain a maximum amount of information for support of the MOL. 

A. Experiments Needed (includes those in progress and/or required 

in support of MOL): 

1. Biological 

a. Proton Focal-Eye Studies: 

The eyes of primates (Macaca mulatta) have been exposed 

to doses of radiation between 125 to 2000 rads of 14, 40, 185 and 730 Mev 

protons to determine the approximate threshold dose required to produce 

iridocyclitis, erythema, epilation, keratitis, desquamation, and cataracts. 

Animals are still being observed. Data accrued from this study shouldbe 

of value in determining the critical or maximum permissable radiation dose , 

to the eyes. This work has been partially funded by both the AF and NASA. 

b. Proton Whole-Body Studies: 

Groups of primates (Macaca mulatto.) will be exposed to 

whole-body protons in the energy range between 14 and 730 Mev at cyclotron 

facilities in the United States and Europe. In wi:.'.tion to clinical and hematological observations and determination of the LD 50/30 Dose, depthdose measurements will be made in a tissue equivalent phantom and 

correlated with pathological changes in the various organ systems. These 

data additionally will provide information on a depth-dose vs biological 

effects prediction model and can hopefully be used in the computer program 

for extrapolation of animal data to man. This work is also partially funded 

by the Air Force and NASA. 

Studies are also being conducted by Dr. Cornelius A. 

Tobias, Univ. of California, in cooperation with NASA, utilising a 

mixed proton energy spectrum, in contrast to studies planned by SAM 

in which monoenergetic energies will bo used. In the latter, average 

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cnorgies which might be aseociatod with solar flare activity aro being 

si....ulatod. Data from both studios will bo complimentary. 

c. Chromosomo Abborations: 

Studios aro prosontly underway at the School of Aerospace 

:4sdicine, through an in-house and contraotual effort, to study chromosomal 

changes in the peripheral blood and skin resulting from oxposuro to ionizing radiation.' This work should provide information, not only on the 

mechanisms of action of.:adiation, but hopefully chromosomal abborations 

can be quantitated to provide a tool or "bio-dosimeter" for estimating 

dose in the event that en individual is exposed. Funds for this research 

are provided by the Air Force. 

d. Altitude Chamber Studies: 

Details. concerning research in this area have not been 

determined, however, it is felt that the radio-sensitivity of laboratory 

animals should be tested as a function of time and atmospheric conditions 

expected in the MOL. Data from these studies also would serve to delineate 

any influence that other variables, such as weightlessness, might exert 

on' the sensitivity of crew members to radiation ir. the event of exposure. 

Funding of this research to be• determined. 

e. Prophylaxis and Theraphy: 

Laboratory studies in this area, although not specifically 

planned for the MOL program, could have a direct influence on the health 

and welfare of the crew in case of exposure to unanticipated high levels 

of.radiation. Results, despite the man years of effort and the large 

sums of money expended, are still grossly inadequate. Much has been 

learned, but no tested radioprotectants are available for use in man. 

Investigations are continuing in many laboratories, using various chemical agents and transfused homologous and entelogous bone marrow calls. 

Results of studies will be followed. Any major "':break-through'; in the 

state-of-the-art will be proposed for inclusion in the MOL program for 

emergency use. 

2. Physical Dosimetry: 

a. Spectrometric and Dose Measuring Devices: 

Instruments will bo calibrated with known radiation typos, 

intensities; onergios, etc.; on the around and flown aboard as many cattelites (Programs 631A, 431; 162, and Saturn 10) as possible prior to the 

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MOL. This is an Air Force funded project. 

b. Passive Deets:eters: 

Zany passive dosimetry devices aro now available, however, 

already .acntiened, none are.complotely satisfactory in a space radiation 

.wironment. Ground studies are needed to select, calibrate, and assemble 

t:lo best available dosimetry package fro:* existing devices and to take advantage of any new or more efficient dosimeters which may be developed 

prior to Funding to be determined. 

C. Computer Program: 

Ground support for the ZOL in the computer program will 

be to provide estimated doses, dose rates, etc., of radiation expected in 

the YOL flight profile. Information gained from other programmed flights 

(see 2.a. above) will provide data which will make the space radiation map 

more complete and-further increase the reliability of predictions by the 

computer systems. 

B. Schedule• 

1. Biolonicel Studies: 

a. Proton Focal-nye: 

All animals in this study have been irradiated and are now 

2 to 3 years post-exposure. It is anticipated that observations vill be 

complete& during FY64 and a final report written by early FY65. 

b. Proton Whole-Body: 

The exposure of animals in this study is scheduled to 

start in Narch, 1964. All exposures should be completed Burins FY65 or 

:luring the first half of FY66. 

c. Chromosomal Abberations: 

Studies are now in progress to investigate chromosomal 

abberations in the peripheral blood. Cells are lulling typed and an attempt 

being made to correlate observed changes with radiation dose. An additional 

study of the effects of radiation on the skin and corresponding chromosomal ebborations is to be started in the rqar future. Data from this study 

should bo available during the first quarter of YY66. 

d. Altitude Chamber Studies: 

The experimental design of studies in this area have not 

been determined. Both design and schedule will be determined in the near 

future. 

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o. Pronyloxin rnd Thdrnpy: 

Vo upocific experlmontation is plennvd for the MOL ProZram. Any major "break-through" in this area will be proposed for inclusion in the EDI. Program as cmorgency procedures. 

2; Physical Dosimetry 

a. Spectrometric and Dose Mensurin3 Devices: 

1,11 spectrometric devices will be available.for flight during FY65. 

b. Passive Dosimeters: 

Selection and calibration bf passive dosimeters will bo 

a continuing process to tako advantage of new and more efficient dosimeters 

which sight become available. 

c. Computer Program: 

Already in existence at the Air Force Weapons Laboratory, 

Kirtland APB, N. M. (Boeing) and at the Aerospace Medical Research Labora-

;ory, Wright-Patterson AFB, Ohio (Northrup). 

C. Where and Now to be Accomplished and Contact. 

1. Biological Studies: 

a. Proton Focal Eye: 

(1) School of Aerospace Medicine (SAM), Brooks AFB, Tex. 

(2) In-House 

(3) Lt. Col. Edwin R. Ballinger (SAM) 

b. Proton Whole-Body: 

(1) To be accomplished at the School of Aerospace Medicine 

as a cooperative effort with various cyclotron facilities in the United 

States and Europe. 

(2). In-House and Contract 

(3) It. Col. Edwin R. Ballinger (SAM) 

c. Chromosomal Abberationo: 

(1) School of Aerospace Medicine 

(2)• In-House and Contract 

(3) Dr. John Prince. (SAM) 

d. Altitude Chmber Studies: 

(1) School of Aerospace Medicine. Additional inputs or 

proposals by other laboratories are suggested. 

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(2) SAM In-House and probably other laboratories not yet 

determined. 

(3) Lt. Col. Edwin Ballinger (SAM) 

e. Prophylaxis and Therapy: 

This is a continuing program at the School of Aerospace 

Medicine with both in-house and contractual work being performed. Other DOD 

laboratories, universities, and private firms are also actively engaged in 

this research area. 

The contact in this area is Capt. George Melville, SAM. 

2. Physical Dosimetry: 

a. Spectrometric and Dose Measuring Devices: 

(1) Air Force Weapons Laboratory (AFWL), Kirtland AFB, N.M. 

(2) In-House and contract 

(3) Col. Irving Russell (AFWL) 

b. Passive Dosimeters: 

Responsibility for the selection, calibration, and packaging 

of the most efficient passive dosimetry package available is to be determined. 

c. Computer Programs 

(1) Air Force Weapons Laboratory, Kirtland AFB, N.M. 

Aerospace Medical Research Laboratory, Wright-Patterson AFB, Ohio 

(2) In-House and Contract 

AFWL - Boeing 

AMRL - Northrop 

(5) lol. Irving Russell (AFWL) 

Lt. Col. Evan Goitre (AMRL) 

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ATTACHMENT 5 

BACKGROUND INFORMATION ON THE SPACE RADITION 

ENVIRONMENT ON IffE BIOLOGICAL EF'F'ECTS OP IONIZING 

RADIATION 

Attacbment'5 is, currently being revised and will 

be distributed when completed. 

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BACKGROUND INFORMATION ON THE SPACE RADIATION ENVIRONMENT AND THE BIOLOGICAL EFFECTS OF IONIZING RADIATION 

The purpose of this section of the experimental package is to provide 

additional information to support the radiation research dr test requirements aboard the ZOL. 

I. Space Radiation Environment: 

One of the areas of medical concern in a manned space flight is the 

radiation which might be encountered. A tremendous effort has gone into 

the mapping of this radiation environment through the use of dosimetric 

equipment aboard various space probes and/or satellites. The principal 

sources of radiation can be listed as (1) galactic cosmic radiation, 

(2) geomagnetically trapped corpuscular radiation, (3) solar flares, and 

(4) artifically injected fission products from high altitude nuclear detonations. 

The galactic cosmic radiations mainly originate outside of the solar 

system and consist of atomic nuclei accelerated to very high velocities. 

Atomic nuclei of all elements in the periodic chart up to iron have Jeen 

observed in these radiations (1). 

The presence of trapped radiation particles in the earth's geomagnetic 

field were first discovered in 1958 by Van Allpn (6) bymeans of equipment flown in U.S. Satellites Explorer I and II.. These belts of trapped 

particles, known as the Van Allen Belts, and for descriptive purposes 

consist of two annular-or donut-shaped zones of radiation in the equatorial regions--the inner and outer belts--described by Van Allen as 

follows: "The inner zone of geomagnetically trapped particles occupies 

an annular region encircling the earth and lying approximately between 

altitudes 600 and 7,000 km and between latitudes 40°N and 400S. The 

radiation comprises a sufficient intensity of protons of energies of the 

order of 100 Melt as to make effective shielding technically impractical 

for prolonged missions in this region (i.e., ones of more than a few hours 

duration). Beyond this region the earth is encircled by a second or outer 

radiation zone of mach greater spatial dimensions, the maximum intensity 

of which occurs at a radial distance of about 3.6 earth radii (23,000 km) 

from the center of the earth." The radiation in this belt is primarily 

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cemposed of electrons of enerzies up to a few huadrod kov. 7.-reys (bremsstrahlung) will be produced whin those electrons are stopped in the wall 

o: the space ship, the magnitude of which will depend upon the weight, 

composition and design of the shield (1). The regions within those boundcxies are not regular or even steady. It has been proposed that the 

c.njor discontinuities in the outer radiation belt is the result of the 

Cape Town anomaly in the geomagnetic field. In the general area of Cape 

Towa, Union of South Africa, the earth's magnetic field has a minimum 

value (7). In this region, relatively high intensities of electrons 

arc found is close to the earth's atmosphere, creating a radiation hazard. 

Solar flare radiations are related to sun-spot activity and number. 

Flare activity is a cyclic phenomenon, with the average cycle lasting an 

average of 11.2 years. Maximum activity in the current cycle is expected 

during the period 1968-1969. Typically in these solar events,. the arrival 

of particles (principally protons) at the earth comes from about one to 

five hours after the optical flare is first observed (7). The duration of 

a- solar flare may be on the order of a few hours to several days. At present it is impossible to predict the occurrence of a flare by more than a 

few minutes in advance (5); however, various methods are being investigated 

to give more accurate predictions in future operations. 

Artifically injected fission particles from high altitude nuclear 

detonations is another source of radiation hazard in the space environment. It is estimated that a one megaton explosion at en altitude of 

200 miles would cause an immense perturbation of the geomagnetic field 

to a distance of almost 700 miles from the point of detonation (5). The 

lifetime of the artifically injected particles seems to be on the order 

of months or years. 

BIBLIOGRAPHY 

1. Curtis, H. J.: Limitations on Space Flight Due to Cosmic Radiations. 

Science 151 (3449):312-316, February 1961. 

2. Rosen, A.: Natural and Man Made Radiation in Space. Lectures in Aerospace Medicine. 'USAF SAM and AMD 301-228, 4-8 February 1963., 

3. Van Allen, J.A.: Corpuscular Radiations in Space. Lectures in Aerosp:ao 

Medicine, USAF SAM. Presentation.No. 7, 16-20 January 1961. 

4. Space Radiation Made. TDB No. AMBL-TDB-62-86,August 1962. 

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II. Biological Dose vs. Effects 

No attempt will be made to discusa the broad field of radiation 

biology, however, certain biological effects which could interfere with 

or seriously influence the outcome of the MOL mission will be discussed 

briefly. 

Many factors influence the response of mammals to ionizing radiation, 

e.g., age, weight, sex, species (even individual within a species), type 

and energy of the radiation, dose rate, total dose, radiosensitivity 

of tissues exposed, and the exposure pattern - the latter referring to 

whole-body vs. partial-body exposure and to single exposure, fractionated, 

and/or low-level continuous irradiation. 

Data from human radiation exposure cases, e.g., reactor accidents, 

Hiroshima and Nagasaki, cancer therapy, etc.; have. been studied in detail and documented; however, data are still insufficient to allow more 

than estimates of the dose required to produce certain biological responses. 

Results of animal studies serve as valuable guidelines in dose-effect 

predictions, however, extrapolation to man must be made with caution. 

For purposes of this report only the acute radiation effects, i.e., 

clinical manifestations which might possibly interfere with the successful 

accomplishment of the MOL mission, will be discussed. It should be 

stressed, however, that certain effects may not be observed for months or 

even years. These long-term or latent effects may include but are not 

limited to life-span shortening, genetic effects, increased incidence of 

tumors (including leukemia), sterility, and cataracts. It is evident 

that certain risks are involved; however, with the doses or radiation 

predicted for the MOL flight profile, these risks in all probability are 

less than other risks associated with the mission. 

A maximum of 10 m rad/hr or a total of 7.2 rad for a 30 day mission 

is predicted for the MOL flight profile by the Air Force Weapons Laboratory, Kirtland Air Firce Base, N. M. (4). Doses of radiation in this 

range are below the threshold of detection by current biomedical techniques 

and should produce no clinical signs and/or symptoms which would interfere 

with man's function in space. Except for the occurrence of a relativistic 

solar flare or the detonation of a high-altitude nuclear weapon during 

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flight, no major problems are anticipated. Monitoring of the radiation 

environment by means of physical detectors is a requirement, regardless 

of the predicted dose) to assure safety for the crew. 

In regard to the cosmic galactic radiations, the general consensus 

of opinion is in agreement with 'Anglian (2) who states that "the expected 

infrequency of heavy cosmic ray interactions with vital areas of the body, 

dependence of their biological effect on volume of tissue affected, and 

the redundancy inherent in most body tissues and organs suggest that their 

potential hazard_to manned space exploration is probably well within 

limits of an acceptable calculated risk.". 

Generally speaking, biological effects resulting from exposure to 

ionizing radiation may conveniently be divided into low, middle, and 

high dose responses. Dose estimates and discussions in the following 

paragraphs are based on whole-body x- or gamma radiations. Focal irradiation to the eye of the primate with 14, 39, 185, and 730 Mev protons indicate the RBE (relative biological effectiveness) for cataract formation, 

iridocyclitis, erythema, and epilation ranges between 1 and 2 when compared 

to Co 60. Preliminary whole body exposure of primates to 730 Mev protons 

yields on LD50/30 of 312 rad, suggesting an RBE of approximately 1.6. 

(6). Animal experimentation will be continued in an effort to relate 

particle type and energy, dose rate and dose to observed tissue effects. 

. Between zero and 100 r,.single whole-body exposure, probably no 

clinical symptoms will be observed. A few minor hematological changes 

may be detected by laboratory techniques after exposure to doses of 25 to 

50 r, however, as the radiation dose increases these changes are in 

general proportional to dose up to a point of maximum depression between 

approximately 600 and 800 r. 'Regeneration and recovery is expected in 

practically all persona exposed to doses below about 300 r. The minimum 

sickness dose (lethargy, nausea) of radiation in man has been estimated 

at 100 r to 225 r, when the dose is delivered at high dose rates. At 

low dose rates, the minimum sickness dose may be somewhat larger (1). 

The lower threshold doses, i.e., below approximate1y.150 r, may be influenced to a great extent by the individual's awareness that he has been 

subjected to radiation exposure. On a space mission, nausea and vomiting 

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caa result in serious consequences and is of little importance whether 

produced phyachologically or 'from actual exposure. Glasatone's (1) discussion of tha human response to acute whole-body ionizing radiation has 

been suzutarized (5) (Table I). In groups of persons exposed to approxiautely 100 r acute whole-body radiation, approximately 5 to 10% will show 

the same symptomc after exposure to 150, 200 and 300 r respectively. 

Dosee in the lethal range are not expected, however, for completeness a short discussion is included. The acute Ld. 50/30 dose of x- or 

gamma radiation for non is not known but is variously estimated at from 

300 to 700 r (1). Glasstone's estimate (table 1) is between 400 and 

500 r. Approximately 450 r (delivered as a single dose) is a commonly 

accepted ID 50/30 dose. Beginning at about 300 r an occasional death may 

occur. The percentage of deaths increases as a function of dose, described by a sigmoid-curve, reaching 100% lethality at about 600 to 900 r. 

Deaths in the dose range of about 300 to 600 r are Commonly described 

as being caused by hematological damage and occur after a period of several 

weeks to months--depending upon dose. After exposure to doses of approxiLately 600 to 1500 r, the gastrointestinal form of death is evident. 

Deaths are relatively independent of dose and occur in about 1 to 2 weeks 

after exposure. After exposure to several thousand roentgens, central 

nervous system symptoms predominate and deaths are observed within hours 

to a few days, again depending upon dose. 

III. Tolerance Limits 

The f011owing tolerance limits or criteria, based upon the rad as 

the unit of measurement, have been recommended by the Aerospace Medical 

Division: 

A. Accumulated Whole-body exposure-- 

Total accumulated Whole-body exposure to space radiation during 

a routine,flight career should be limited to 150 rad, independent of dose 

rate and the men= in which the dose is reached. 

B. Single Emergency Exposure--A single whole-body emergency exposure 

Up to 250 rad can be permitted if the priority of the mission warrants it. 

This dose should be considered only in the event of a national emergency. 

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Expected Effects of Acute Whole-Body Radiation Doses 

400 to 500 

Probable Effect 

No obvious effect, except possibly minor blood changes. 

Vomiting and nausea for about I day in 5 to 10 percent 

of exposed personnel. Fatigue, but no serious disability. 

Vomiting and nausea for about 1.day, followed by other 

symptoms of radiation sickness in about 25 percent of 

personnel. No deaths anticipated. 

Vomiting and nausea for about 1 day,* followed by other 

symptoms of radiation sickness in about 50 percent of 

personnel. No deaths anticipated. 

Vomiting and nausea in nearly.all personnel,on first day, 

followed by other symptoms of rataation sickness. ,About 

20 percent deaths within 2 to 6 weeks after exposure; 

survivors convalescent for about 3 months. 

Vomiting and nausea in all personnel on first day, followed 

by other symptoms of radiation sickness. About 50 percent 'deaths within 1 month; survivors convalescent for 

about 6 months. 

Acute Dose 

(roe:Azar-0 

0 to 50 

80 to 120 

130 to 170 

ISO to 220 

270 to 330 

550 to 750 Vomiting and nausea in all personnel within 4 hours from 

exposure, followed by other symptoms of radiation sickness. 'Up to 100 percent deaths; few survivors convalescent for about 6 months. 

1000 Vomiting and nausea in all personnel within 1 to.2 hours. 

Probably no survivors freni radiation sickness. 

5000 Incapacitation almost immediately. AU personnel will be 

fatalities within 1 week. 

TABLE I 

(From Space Radiation Guide Technical Documenting Report No. AMRL-TDR62-86, Aerospace Medical Research Laboratories Wright-Patterson AFB, 

Ohio. pg Aug 1962) 

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Flights aboard. the MOL should be well below this level. Personnel who 

have received levels of•300 rad or more must be considered as not available 

for further crew duties. 

Whole body toleranhe levels have been established on the basis that 

genetic effects could be ignored and that the estimated life expectancy 

will be minimal, since risks associated with these factors are in all 

probability less than other risks associated with the mission. 

C. aes - Tolerance dosage to the eyes is 250 rad. based upon 3 mm 

of shielding over the measuring device (tissue depth of lens). Thts level 

may cause lens changes in 3+ opacities within one to two years. These 

changes in the eyes are considered relatively acceptable because the 

changes will not interfere with the mission and is amenable to medical or 

surgical treatment. 

D. Blood-Forming Organs - Tolerance dosage to the blood forming organs 

varies from 50 tl 150. rad. This level will cause changes in the bone 

marrow that are reversible, with several weeks required for recovery. 

Measurement of this dosage is based upon 8 = shielding over the measuring 

detice. 

The USAF, NASA, and AEC have an extensive program underway to determine tolerance levels of radiation encountered in space. The dosages given 

above are tentative and will be changed to reflect recommendations resulting from this program. 

BIBLIOGRAPHY 

1. Glasstone, S. (Ed). The Effects of Nuclear Weapons, AEC, June 1957. 

2. Langham, W.H.: Implications of Space Radiations in Manned Space 

Flights. Aerospace Medicine 12: 410-417, June 1959. 

3. Langham, W. H.: Some Radiation Problems of Space Conquest. Astronautilt 2: 272-294, 1961. 

4. Russell, I. J. Personal Communication 

5. Space RadiatiOn Guide. Technical Documentary Report No. AMRL-TDR-62-86. 

pg. 146-162. August 1962 

6. Talbot, J.M. and Pickering, J. E.: A Reappraisal of the Radiation 

Hazards to Manned,Space Flight. Presented at the American Institute 

of Aeronautics and Astronautics. Second Manned Space Flight Mooting 

April 23, 1963. 

SSTA-1-9 

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Exp No. P-12 

(MISC, SECT 1) 

TIME ANALYSIS OF ASTRONAUT DUTIES 

IN BIOMEDICAL EXPERIMENT 

FOR 30 DAY MISSION 

SSTA01.9 

264 
Exp No. P- 12 

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TA-1-9 

265 

NRO APPROVED FOR 

RELEASE 1 JULY 2015 
WT. *V0i,. :'cA;c2r 

LT-Z. 

r7-R MEASURED EQUIPMENT Tv, • • • 

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RELEASE 1 JULY 2015 

Ex p No. P-12 

24 March 1964 

IIIWEDICAL AND PHYSIOLOGICAL PARAMENTERS 

SUM:i.ARY Or EQUIPMENT 

(::on::tored and/or recorded 

--, car ) 

7" - se Harness,. Electrodes, Amplifier, 

Transmitters 

Receiving Equipment 

Attachable electrodes, amplifiers 

0.2 

15.0 

0.5 

<3.3 

0.1-,___ 1 

<0.G.:_ 

1 3.3 

z_,_:_ectrocardiogram 0.10 

(3-Lead) 

Blood Pressure Cuff, Microphone, amplifier, inflator 8.0 10.30 4.03 

:c..ar.::cal Events -

:.=t) 

Microphone, accelerometers, 

Pressure transucer, amplifiers 3.8 0.03 0.5 

__..r.o:1 C2 Con.,,ent and 

:2:.1.;:iac 0-c,tnut; (T-1824 Dye) 

Ear 0::to.eter, Power Supply 

Amplifier 7.0 0.05 o.0 

Respiratory Flow, 

02 and CO2 content of inspired 

and e:(pired air . 

Flow Meter, amplifier, integrator, 

gas sensors 

20.0 0.30 15.0 

Electroencephalograms and 

electroculograms 

Electrodes, amplifiers 

(4 channels) 1.3 0.01 0.2 

Body ::ass Catapult, Accelerometer, 

amplifier 9.0 0.07 0.5 

Physical condition and Deconditioning countermeasures Ergometer, Tachometer, Power 

Meter, Dynamometers 40.0 0.1:0 

Goneratc:;-: 

30watt 

nor-min 

_%,1..:iatLon--Electrons, 

protons, neutrons, heavy 

nuclei, alphas 

Uni and Omni-Directional 

Spectrometers, TEICS 45.5 0.93 14.2 

blood and Urine Constituents, 

Volumes, and total body water 

pH meter, Spectrophotometer, 

Centrifuge, Mass Spectrometer, 

and miscellaneous supplies 90.2 0.99 60.0 

Astronaut General Status 

Visual Observation of work anti 

=e7ent in zero g 

Voice Communication Equipment 

TV (During certain station passes) 

(Included in Life 

Support Equipment) 

3:Lochemical Samples 

(for post-flight analysis 

Centrifuge, Lyophilizer, 

Supplies 35.0 0.82 30.0 

:.. Storage Magnetic Tape Recorder 60.0 1.30 co.o 

_ Total 335.5. 5..41200.5 5 

Note: Weights and volumes do not include storage containers or mountings. Power 

represents average values for. operating equipment. 

SSTA- I-9 

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CONFIDENTIAL--- 

SECONDARY EXPERIMENTS 

NR TITLE 

S-1 VLF Communication/Propagation Experiment 

S-2 Secure Communication Using Narrow Beam Widths 

S-3 Laser Propagation 

S-4 High Frequency Ionospheric-Ducting 

S-5 Encapsulation and Recovery of Space Objects 

S-6 Expandable Structures Techniques 

S-7 Antanna Deployment, Alignment and Pointing 

S-8 Space Rendezvous Radar 

S-9 Manually Controlled TV and Orbital Inspection Photography 

S-10 Mapping and Geodetic Survey 

S-11 Determination of Mass. of Orbiting Body 

S -12 Hydrogen Reduction Atmospheric Regeneration System 

S-13 Vapor Compression Distillation Water Purification System 

S-14 Passive Propellant Settling System 

S-15 Coherent EM Propagation and Antenna Loading 

S-16 Solar X-Ray Monitoring 

S-17 Materials Degradation and Malfunction Analysis 

S-18 Astronomical Photography 

-CONFIDENTIAL-- SSTA-r-9 

267/268 

This document contoins information allotting the national defense of the United States within the meaning al the Espionage lova, 

Tole 1S, U.S.0 Section 793 and PK the tranimiltiOn of which in any Milner to on unauthoticitd person is prohibited by low 
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SECRET Experiment No. S-1 

3 March 1964 

VLF COMMUNICATION/PROPAGATION 

I. TEST OBJECTIVE 

The objective of the experiment is to determine if the propagation characteristics of the ionosphere will support VLF communications between MOL 

and globally distributed ground terminals on a continuous basis. 

II. IMPORTANCE OF THE TEST 

The potential operational application of a global VLF communication 

capability using a space-mission vehicle is the extension into space of the 

VLF global network. Such a capability would improve the global coverage of 

the VLF net and ensure alternate routing of traffic following the degradation 

or destruction of ground facilities. Communication VLF traffic normally 

transmitted from large ground antenna systems could be transmitted to a space 

vehicle at UHF or microwave frequencies and retransmitted from space at 

the VLF net frequency to the dependent weapon systems. 

The current information on the propagation of VLF energy transmitted 

between space and the earth is inadequate to determine the full potential of 

this frequency range to provide global coverage. The propagation characteristics cannot be ascertained from simulated methods. The orbit of MOL will 

place it within the ionosphere, and many questions concerning the coupling of 

the VLF energy into the plasma and its subsequent propagation are still to be 

resolved. 

III. DESCRIPTION OF THE EXPERIMENT 

Basically the dxperiment will consist of transmitting VLF energy from 

the MOL during various locations of the MOL with respect to the diurnal variations of the ionosphere, and recording the received signal profile at a number of globally distributed earth based terminals, i.e. ground, ships. An 

adjustable length VLF antenna will be required, and it will be necessary to 

vary its length for maximum coupling to the ionosphere. The antenna.extension need not be a problem since the Alouette Satellite has demonstrated the 

technique. 

(a) Configuration of Test Items tl 1/2 cu. feet 

30 lbs. 

(b) Test Support Equipment Required: Primary power 300-500 watts 

Antenna to be shell mounted. 

Items required for the test will consist of a VLF transmitter, variable-length antenna, test equipment for achieving maximum coupling 

SSTA-1 -9 

269 

Th. document eaniams Inlatonahon oH.chnp In* nahanol Menu of lb* Unitad Stales *ohm Ina ratanong el the Esp.enage la... 

Tale la, U S.0 . Sittlean 793 and 794, the teanynusvon of .h.ch ,n any manna' to an unauthowed person .t proh.b.ted by to.. 
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(radiated power indicator) and recorder to coordinate time and antenna length. 

In addition, a preprogrammed modulation sequence unit will be required or 

incorporated into the TX. 

The ground equipment will be standard VLF signal monitoring and 

recording. This equipment no doubt is in use now. 

(c) Test Procedure: 

The important variable in this experiment is the length of the antenna. 

Since the electrical length of the antenna will vary according to the plasma 

density, it will be necessary to continuously tune the antenna for maximum 

radiated power. The man's role in the test is to vary the length of the antenna 

to ensure optimum coupling at all times. The antenna tuning will be shown by 

maximum indication of the radiated power meter. The man's contribution 

will be measured by his ability to manipulate the antenna-length equipment by 

visual observation of the power meter. His coordination will be recorded on 

board by notebook or voice onto a tape. 

Initially the test sequence will consist of radiating continuously for 

somewhat more than 1 orbit in order to obtain signal profiles corresponding 

to a complete diurnal variation of the ionosphere. Subsequently the test periods could be shortened to correspond to reception.at particular ground terminals for different hours of the day. 

Using the signal strength profiles, in conjunction with time-synchronization, it will be possible to estimate propagation time delay, absorption, 

and estimate propagation ray patterns. From the foregoing it should be possible to determine the feasibility of a space ground VLF link for operational 

traffic. 

(d) Category of Experiment: 

Category (b) - Minor structural accommodation for extending the 

VLF antenna. 

(e) Cost: FY 65 FY 66 FY 67 FY 68 FY 69 TOTAL 

260 K 300 K 10 K 10 K 10 K 590 K 

(f) Schedule: 

1. FY 66 (12 months after issue of contract) 

2. FY 66 

IV. PARTICIPATING GOVERNMENT AGENCIES 

Sponsor - NAVY; Participant: RTD and ESD 

7-41-44 SSTA-1 -9 

270 SECRET 

Thie document contains information allecting the /10b01101 Memo al Ilse Uniled Voles *whin Int meaning or the Etp.onoge 

Tit!, ie. U.S.0 . semen 793 and 794. lb. rronsmnsion of which in any manner to On unauthorised person is push.b.led by to. 
SSTA2

1 -9 

71 

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— cr Exp No. S-1 

V. ADDITIONAL REQUIREMENTS 

(a) Special Security: No 

(b) Manning Description: See attached sheet 

(c) Logistics: Not known 

(d) Facilities: Existing facilities probably exist for ground monitoring 

and recording. Personnel would normally be trained in this operation. 

(e) Simulation and Training: 

1. Astronaut: Minimum technical skill. Familiarity with the purpose and his partcipation in the experiment would require a short prior 

briefing to become acquainted with the response of the antenna controls. Onboard procedures will be provided. 

2. Ground Personnel: Technician level. 

3. Equipment: Nil. . 

VI. GENERAL 

(a) Command and Data Requirements: 

Telemetry data on status of the MOL's VLF transmitter, antenna 

extension and radiated power. Shared with on-board system. 

y.ht;: .nyetmw,.„ ef",..0 the 001,000• Mins. 01 ore Untied Solve' 0./bon the mlerong of IC. 110,0,099 T 

 

ie. U S C . Sim°. 793 cv.d 794. the transm•st,e. of 4.0 try otorwee to Oo uotouthoo.ted perion .t wok bled by 10. 
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VLF EXPERIMENT 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED: VLF Transmitter and Antenna ExtensorTuner. 

2. WEIGHT: 30 lb. 

3. VOLUME: Stored 1.5 cu ft. In use 1.5 cu ft. 

CRITICAL DIMENSIONS - SHAPES - To be supplied to MOL designer 

during development of VLF equipment. 

4. POWER 

a. Continuous: None 

b. Stand-by: None 

c. Average operating: 400 watts 

d. Peak: 400 watts 

e. Duty cycle: Continuous during test periods 

5. SPARES: None required in flight. 

a. Volume 

b. Quantity 

c. Weight 

6. TOOLS: None required in flight. 

a. Volume 

b. Quantity 

c. Weight 

d. Power 

7. HEAT OUTPUT: 200 watts during test periods 

SSTA-1-9 

272 SECRET Atch 1 

this document contains information affecting the notianot dtleme of the United States within one mooning of the Espionage La.,. 

Title 113, U.S.C.. Section 793 and 794, the transmission of which in any manner to on unauthoticed person is prohibited by tow 
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Exp No. S-1 

DESIGN CHARACTERISTICS TEST EQUIPMENT (Cante d) 

8. STABILITY: No rapid rotations during.test periods. 

a. Moving parts: Antenna extensions up to 150 feet from MOL in 

opposite directions. 

9. VIBRATION LIMITS: Less than 0.1g during operation less than 20 g at 

other times. 

10. SHOCK LIMITS: 20 g in any direction when not operating. 

11. HAZARDS (fire, explosion, electrical, toxics, other): None. 

12. TEMPERATURE LIMITATIONS: 0°C to 50°C ambient. 

13. TYPE AND RANGE OF-MEASUREMENT (definition of parameters to be 

measured while test is underway): See Section III C. 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS: Air circulation 25 cu ft. 

min. 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: 

Station: Angle maintained within ±3° of equilibrium position/ angular rate 

not greater than 1° per min. 

Equipment: No accuracy requirement; must be accessible to operator. 

16. EQUIPMENT OPERATING CYCLE 

Frequency: 2 per day 

Time Duration: Continuous during 1 or 2 early orbits. 

17. EQUIPMENT LOCATION REQUIREMENT: Antennas extend in a straight 

line up to 150' from vehicle in two opposite directions. Transmitter 

accessible to operator. 

18. SPECIAL MOUNTINGS REQUIREMENTS 

Apertures: See No 17. 

Booms: None 

Windows: None 

Antennae: See No. 17. 

Bracketry: None. 

Atch 1 - p2 SECRET SSTA-1 -9 

273 

This ektcument Contemns information olleettne the !When& defence Of the United Stales wlihin Inc meaning of the Etwonoge to.,, 

Title It. U. S. C.. Section 793 and 794, the transmission of which in any manner to on unouthotised person is proh■ bited by low 
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Exp No. S-1 

DESIGN CHARACTERISTICS TEST EQUIPMENT (Cont'd) 

19. PRESSURE VESSELS - fluids,, gasses, etc.: None required. 

20. ELECTRO MAGNETIC INTERFERENCE (spurious generation, special 

shielding required, etc.): No special shielding required. 

21. MAINTENANCE REQUIREMENTS 

Ground: Ability to test, replace, repair transmitter and antenna extensor/tuner. Conventional Laboratory test equipment is sufficient. 

Space: None required. 

SSTA-1-9 

274 SECRET Atch 1 - p3 

This document contains inlormahon ollecttha th• nol.onol delitnte al the Umted Swat .01,n Int eneon■ n9 of the Eta,onage La.,. 

Tiffo le, U.S.C.. Section 793 and 794. the itonstmwon 01 which in any manner to an vnouthemzed person ,t p.efob.led by low 
NRO APPROVED FOR 

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Exp No. S-1 

VLF EXPERIMENT 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape: Conventional audio types at monitoring stations. 

b. Film: None Required. 

c. Other: Strip chart recorders for signal strength. 

2. HANDLING (special equipment required to handle items being tested): 

None required. 

3. PACKAGING: Mine required. 

4. CALIBRATION - alignment, deployment: Conventional systems are 

available at monitoring locations. 

5. JIGS AND FIXTURES: None required. 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION: None 

required. 

7. SENSORS (TRANSDUCER - OUTPUT SIGNALS): None required. 

8. TRAINERS/SIMULATORS: None required. 

9. INSTRUMENTATION - cockpit and/or laboratory (note effect of time 

sharing instruments with other experiments). Laboratory only: Power 

on/off controls and pilot light. Indication that antenna is tuned, control 

of modulation cycle. Necessary metering of transmitter. 

10. RELATED SUPPORT EQUIPMENT 

a. Targets: None required. 

b. Ground Stations: Will make use of existing VLF monitoring and receiving stations operated by Air Force, Navy, and Bureau of 

Standards. 

c. Tracking: None required. 

d. Handling Equipment: None required. 

11. AGE: Conventional test equipment is sufficient. 

12. ENVIRONMENTAL TEST EQUIPMENT: None required after acceptance 

tests. 

13. FACILITIES: None required except as noted above. 

Atch 2 SECRET SSTA-1 -9 

275 

This document Contain% information on/Min the notional defense of the United Storm within tne meaning 01 the Espionage low, 

Titre Ifl. U.S.0 . Section 793 and 794, the tronsmillion of which in any manner to on unouthorqed person rs prok•boed by low 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp No. S-1 SECRET 

VLF EXPERIMENT 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired) 

a. Altitude: Any altitude between 100 and 250 miles is satisfactory. 

b. Inclination: 30° or greater is preferred, to increase time over the 

United States. 

c. Epoch: N/A 

d. Ellipticity: N/A 

2. PLANE CHANGE: None required. 

3. ALTITUDE CHANGE: None required. 

4. TIME ON ORBIT: Full orbit (one or two per complete MOL operation). 

5. TEST DURATION: 2 full orbits plus 60 10-minute tests. 

6. TOTAL NUMBER OF TESTS: 62 

7. TEST FREQUENCY: 2 per day 

8. INTERVAL BETWEEN TESTS: 6-24 hours 

9. CREW TASK LOADS - man hours: 13 man hours per MOL Mission. 

10. CREW TASK FREQUENCY: 2 per day 

11. FIELD OF VIEW REQUIREMENTS: Ability to determine antenna extension. 

12. GROUND CONTROL LIAISON DURATION: From 5 min. before test until, 

5 min. after end of test. 

13. GROUND CONTROL LIAISON FREQUENCY: Normal MOL voice 

Communication channels. 

14. EXTERNAL TEST ITEMS: 

a. Launched from Station: None 

b. Launched from resupply: None 

c. Launched from ground: None 

SSTA-1 -9 

276 SECRET Atch 3 

Thit document contains information affecting the national defense of the United States within the meaning of the Espionage Low, 

Title 18. U.S.C., Section 793 and 794. the transmission of which in any manner to on unauthorized person is proh.bded by low 
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SECRET Exp No.S-1 

TEST OPERATING CHARACTERISTICS (Cont'd) 

15. QUALIFICATION TESTS (other than space) 

a. Ground: Normal acceptance tests including simulated space 

ertviornment 

b. Atmosphere: None 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT: See Section III C. 

17. HANDLING PROCEDURES: None required. 

Atch 3 - p2 SECRET SSTA.1 -9 

277 

This document contains infotrnation attesting she notional defense of the United Elates within the meaning of the Espionage saw,. " 

Title IC U.S.C., Section 793 and 791, the transmission of which in any manner to an unoutharized person is prohibited by low 
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This document contains information alfecling the national defense of the United States ...akin In. meaning at the Espionage. 

Title 19. U.S.C., section 793 and 794, the ironpni,,;on of which in any Monne, to an unauthorized parson is prohibited by low 
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RELEASE 1 JULY 2015 

Exp No. S-1 

VLF EXPERIMENT 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number require& One; intermittent duties. 

(1) Man's function 

(a) As a part of test: Determining optimum antenna extension 

in cooperation with ground observers 

(b) As technician conducting test: turning equipment on and off, 

adjusting for optimum operations. 

b. Crew skill requirements: No special skills required. 

c. Manpower Profile: 2 full orbits early in flight plus two 10 minute 

tests per day. 

d. Critical Functions: See 1 (1), (a) above. 

e. Work Positions: In pressurized Module. 

f. Time Controlled Tasks: None. 

g. Human Performance Measures: Skill in cooperating with ground 

observers. 

h. Physiological and Psychological Measures: None. 

i. Selection Factors: None. 

j. Training Requirements: Brief instruction period - three half hour 

sessions. 

2. GROUND PERSONNEL 

a. Number required: 3 to 60 (depending on monitoring statious involved) 

(1) Man's function 

(a) As part of test: monitoring received signals and directing 

astronaut in adjustments. 

(b) As technician condUcting test: recording signal strength 

and quality. 

SS TA -1 -9 

Atch 5 279 

This document contains information affecting the noloonol defense of the Unused Stoles within the meaning of the Espionoge 

Title Ifl, U.S.C., Section 79n and 794, the transmission of which in any mom., to on unouthonced person is prohibited by low 
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Exp No. S-1 -SEGREf-- 

MANNING DESCRIPTION (Cont'd) 

b. Crew skill Requirements: Present crews of monitoring stations are 

satisfactory. 

c. Manpower Profile: Same times as item I-C above. 

d. Critical Functions: Evaluation of signals. 

e. Work Positions: In present monitoring stations. 

f. Time Controlled Tasks: None. 

g. Human Performance Measures: None. 

h. Physiological and Psychological Measures: None. 

i. Selection Factors: None; personnel now on the job for other purposes. 

j. Training Requirements: None. 

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This document contains information affecting the notional Moose of the United Static within the meaning of the Espionoge Low, 

title 18, U.S.C., Section 793 and 794, the transmission of which in any manner to en unauthorized person is prohibited by tow 
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Exp No. S-1 

VLF EXPERIMENT 

COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE: Low. Summaries of data gathered on ground will be sent 

to mission headquarters by teletype. Detailed data may be collected by 

mail. 

2. FUNCTIONS TO BE MEASURED: Strength and quality of the received 

signal. 

3. TYPE OF ANALYSIS REQUIRED: Propagation attenuation and variation 

as a function of: 

a. Path length 

b. Location of MOL 

c. Ionospheric variations 

d. MOL transmitting antenna adjustments 

4. PICTORIAL DATA REQUIRED: None, unless malfunction of MOL antenna 

can be documented by photographs taken by astronaut (recovered with 

Gemini capsule and log of trip). 

5. REAL TIME MONITORING REQUIREMENT: None required. 

6. DATA EDITING OR COMPRESSION: See Item 1 above. 

7. READ-OUT TIME: Not pertinent. Data is gathered on the ground. 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS: None in MOL; 

data is gathered on the ground. Records include magnetic tape recording of audible sounds of received signals and pen tracings of signal 

strength, coordinated against time of reception. 

9. MANUAL AND/OR AUTOMATIC CONTROL: MOL Equipment manually 

controlled. Ground equipment may be manual or automatic according to 

types of devices with which the ground recording stations are presently 

equipped. 

10. SIMULTANEITY: No special requirements other than comman time 

reference accurate to approximately 0.1 second to permit correlating 

test records. 

H. GROUND COMMANDS REQUIRED: None, except for brief periods of cooperative tests when astronaut must have voice contact with ground 

observer while he adjusts antenna tuning for optimum performance. This 

test only two to four ten-minute periods during a complete mission. 

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This document contains information affecting the national defense of the United States within tne mooning of the Espionage 

Title 18, U.S.C., Section 793 and 794. the transmission of which in any morale, to an unauthorized person is prohib.ted by low 
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Exp No. S-1 RE 

VLF EXPERIMENT 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME: 12 months 

2. FINAL DEFINITIVE TEST DESIGN TIME: 18 months 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED: None. 

4. TYPE OF DEVELOPMENT TEST ITEMS: 

a. Vacuum Chamber: Required. 

b. Shaker: Required. 

c. Thermal: Required. 

d. Acoustic:-Not required. 

e. Simulators: Not required. 

f. Aircraft: Not required. 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME: None required. 

6. NUMBER OF TEST ARTICLES REQUIRED FOR 

a. Ground Test: One. 

b. Atmospheric Test: None. 

c. Space Test: Six 

7. DATE AVAILABLE FOR TESTS: 12 months after award of order. 

8. CURRENT DEVELOPMENT STATUS: 

a. Proposed only. See below. 

b. Project or program is approved and test item is under study, breadboard stage, etc.: Similar devices of comparable power and size 

have been manufactured in prototype quantities. Antenna tuner must 

be developed to meet impedance anticipated for this special antenna 

system. 

c. Fun& expended to date: None directly to this program. 

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Title IS, U.S.C., Section 793 and 791, the transmission of which in any manner to an unauthorized person it prohibited by low 
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Experiment No. S-2 

3 Mar. 64. 

SECURE COMMUNICATION USING NARROW BEAM WIDTH 

I. TEST OBJECTIVE: 

It is required to determine the potential utility of narrow beam 

communication links for space-to-space and space-to-aircraft information 

transfer. The potential mission application is in the establishment of command and control links between space vehicles and between Airborne Command Posts and Space Command Posts. 

II. IMPORTANCE OF THE TEST: 

In order to provide a reliable and continuous command capability 

between ground command posts, airborne command posts and space command 

posts, the communications systems must be resistant to jamming and interception by the enemy. Narrow beam radiation responds to both these requirements and is particularly desirable between ABCPs and spacecraft. 

The test is necessary in order to respond to questions relating to 

narrow beam communication link establishment. Because of the relative 

velocity of the terminals (i. e. , space vehicle-to-space vehicle and space 

vehicle-to-aircraft) and the potentially high tracking rates involved, the 

initial antenna pointing angle represents an important system consideration. 

In the initialifeasibility experiment on the MOL, automatic link establishment will not be available and a space crew member will be required to 

point the antenna in the direction of the other terminal, i. e. , another spacecraft, if available, or an aircraft. This experiment will provide a capability 

assessment of the potential contribution which man-in-apace can make in a 

narrow-beam communication system. If this experiment shows a positive 

result, it would reduce the complexity (weight, power, .space) which would 

otherwise be necessary in an automatic link establishment procedure when 

using narrow-beams. 

III. DESCRIPTION OF THE EXPERIMENT: 

The experiment will investigate the potential value of a narrow-beam 

communication link between the MOL and an aircraft flying at an altitude of 

the order of 40,000 feet and along the ground-track of the MOL. The experimental time duration will not be more than 5 minutes per contact. After a 

link has been established, a canned message sequence can be transmitted 

alternately from the MOL and from the aircraft. This will be a man-controlled 

experiment. Received-signal profiles will be recorded on both the MOL and 

aircraft for subsequent analysis. 

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(a) Configuration of Teat Items: 

The experiment would be carried out in the 75KMcs or higher 

frequency spectrum in order to provide a relatively narrow-beam with a 

small antenna and to reduce signal strength at ground level because of atmospheric attenuation. At this frequency, a 6-inch dish provides 8. beamwidth of 22 or 40db gain; a 12-inch dish provides a beamwidth of 1 or 46 db 

gain. From a space vehicle at an altitude of 150 miles, the beamwidth at 

the aircraft altitude will be approximately 5.0 and 2.5 miles respectively. 

Similar terminal equipment will be required in both the aircraft 

and the MOL, i. e. , transmit, receive, record equipment. At 75Kmcs, the 

equipment will occupy about 1 1/2 cubic feet, weigh approximately 25 lbs. 

and require 25 watts during the test. 

(b) Test Support Equipment: 

The test support equipment in the MOL will consit mainly of 

signal-profile recording for permanent record and for transmission to the 

ground at an appropriate time. Provision will be made for a crew-member 

to listen to the received de-modulated signal for man-evaluation of the link 

for voice communications. 

An aircraft will be required to be modified to provide a stabilized 

platform. The aircraft will contain essentially the same equipment as in the 

MOL. 

(c) Test Procedure: 

1. Establish communication between MOL and aircraft by 

conventional means (e. g. , UHF) in order to conduct the experiment. 

2. From a determination of the relative positions of MOL and 

aircraft, align antennas. MOL will transmit on frequency A and aircraft 

will transmit on frequency B to provide a capability to antenna-track on 

signal and remain aligned. 

3. When the link has been established, a canned modulation 

sequence, i. e. , voice, can be transmitted either simultaneously or alternatively between MOL and aircraft. 

4. The received signal would be permanently recorded. 

Man's role in the test will involve initial link establishment 

by pointing the antenna to locate the other terminal and to ensure that lockon is sustained during the test. Continuous voice communication will be 

maintained between MOL and aircraft for the duration of the test. In addition, 

man will be required to initiate any canned sequences. 

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(d) Category of Experiment: 

This experiment will be in category (a). In order to carry out the 

experiment, the antenna will need to be external to MOL to allow the required 

directional flexibility. This will be a significant design consideration in the 

structure of MOL since the antenna will probably be extended. 

(e) Cost: FY 65 FY 66FY 67 FY 68 FY 69 TOTAL 

420 K 520 K 75 K 275 K 200 K 1,490 K 

This experiment needs to be performed in every MOL. 

(f) Schedule: 

1. Hardware and software available for test: Not now available. 

2. Hardware and software flight readiness date - 1966. 

N. Participating Government Agencies: 

Sponsor: SSPD/Aerospace 

Participant: CRL-ESD 

V. Additional Requirements: 

(a) Special Security: No 

(b) Manning Description Summary: See attached 

(c) Logistics: Not known 

(d) Facilities: 

This test will require the modification of an aircraft to support a stabilized 

platform for the equipment, to accomodate a small randome on the top of 

fuselage, and to permit pointing of the antenna by a crew member. 

(e) Simulation and Training: 

1. Astronaut: The astronaut must be familiar with the sequence 

of the experiment and the response of the pointing angle system. Technician 

training only required. Details for operating experiment will be provided. 

Training would consist of operating the equipment on a simulated basis during 

training. It would not represent a long training period. 

2. Aircraft personnel: Same as above 

3. Equipment: No special equipment required for training 

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VI. General: 

(a) Communication Data Handling Requirement: 

Voice UHF contact will be maintained between the aircraft and 

MOL throughout the test. Simple telemetry of the MOL test equipment will 

be transmitted to the ground. Signal profile data obtained in the MOL will 

be transmitted to a ground terminal when opportune to do so. 

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NARROW BEAM COMMUNICATION EXPERIMENT 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED: Transmitter-Receiver and associated 

tracking antenna. 

2. WEIGHT: 20 lbs. 

3. VOLUME: Stored 1.5 cubic feet. In use 1.5 cubic feet. 

CRITICAL DIMENSIONS - SHAPES - Steerable Antenna 1-foot diameter. 

Dimensions of equipment to be supplied to MOL designer during development of millimetric wave equipment. 

4. POWER: 

a. Continuous: None required 

b. Stand-by: None required 

c. Average operating: 25 watts 

d. Peak: 25 watts 

e. Duty Cycle: Continuous during test periods (6 minutes) 

5. SPARES: None required in flight. 

a. Volume: N/A 

b. Quantity: N/A 

c. Weight: N/A 

6. TOOLS: None required in flight 

a. Volume: N/A 

b. Quantity: N/A 

c. Weight: N/A 

d. Power: N/A 

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DESIGN CHARACTERISTICS TEST EQUIPMENT (Cont'd) 

7. HEAT OUTPUT: 24 watts 

8. STABILITY: See Item 15 below. 

a. Moving Parts: Antenna. and mount to track co-operating airborne 

terminal. 

9. VIBRATION LIMITS: Can accept available environment by vibration 

mounting antenna assembly. 

10. SHOCK LIMITS: 20 g in any direction, non-operating 

11. HAZARDS (fire, explosion, electrical, toxics, other): None 

12. TEMPERATURE LIMITATIONS: Transmitter: 10° - 40° C, air cooled 

Antenna: Space Environment 

13. TYPE AND RANGE OF MEASUREMENT (definition of parameters to be 

measured while test is underway). Measurements of strength and quality 

of received signal, and antenna pointing angle. 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS: See item 12 above. 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: 

STATION: Angle maintained within +3° of planned orientation to permit 

antenna to view the earth. Angular rate not greater than 1° per minute. 

Equipment: Transmitter and receiver must be accessible to the operator. 

16. EQUIPMENT OPERATING CYCLE: 

Frequency: May be scheduled as convenient; total of ten tests per MOL 

mission. 

Time Duration: Ten minutes. 

17. EQUIPMENT LOCATION REQUIREMENTS: Antenna must be able to 

view substantially all visible areas of earth surface. Transmitter and 

receiver accessible to operator. 

18. SPECIAL MOUNTINGS REQUIREMENTS 

Apertures: See below 

Booms: None required 

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DESIGN CHARACTERISTICS TEST EQUIPMENT (Cont'd) 

Windows: Operator must see antenna when necessary 

Antenna: See Item 17 above 

Bracketry: Antenna support 

19. PRESSURE VESSELS - fluidi, gasses, etc.: None required 

20. ELECTRO MAGNETIC INTERFERENCE (spurious generation, special 

shielding req. , etc): No special shielding required. 

21. MAINTENANCE REQUIREMENTS: 

Ground: Ability to test, replace, or repair transmitter, receiver, and 

antenna. Conventional laboratory test equipment is sufficient. 

Space: None required. 

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NARROW BEAM COMMUNICATION EXPERIMENT 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape: For recording signal profile 

b. Film 

c. Other 

2. HANDLING (special equipment required to handle items being tested): 

None required. 

3. PACKAGING: None required 

4. CALIBRATION - alignment, deployment: conventional test equipment 

may be used at ground installations. 

5. JIGS AND FIXTURES: None required 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION: None required 

7. SENSORS (TRANSDUCER -OUTPUT SIGNALS) - None required 

8. TRAINERS/SIMULATORS: None required. 

9. INSTRUMENTATION - cockpit and/or laboratory (note effect of time 

sharing instruments with other experiments): No instrumentation in 

cockpit. In the laboratory 

1. Indication of transmitter power 

2. Indication of received signal 

3. Modulation sequence activated 

10. RELATED SUPPORT EQUIPMENT 

a. Targets: None required 

b. Ground Stations: Airborne terminal 

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TEST SUPPORT EQUIPMENT (Cont'd) 

c. Tracking: Totally steerable tracking capability 

d. Handling Equipment: None required 

11. AGE: Conventional laboratory test equipment is satisfactory. 

12. ENVIRONMENTAL TEST EQUIPMENT: None required after equipment 

acceptance tests. 

13. FACILITIES: None required except as noted above. 

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NARROW BEAM COMMUNICATION EXPERIMENT 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (DESIRED) 

a. Altitude: Not critical - 100 to 250 miles is satisfactory 

b. Inclination: •Not critical 

c. Epoch: Not critical 

d. Ellipticity: Not critical 

2. PLANE CHANGE: Not required 

3. ALTITUDE CHANGE: Not required 

4. TIME ON ORBIT: Not critical 

5. TEST DURATION: 10 minutes per test 

6. TOTAL NUMBER OF TESTS: 10 per MOL mission 

7. TEST FREQUENCY: One per day preferred until 10 have been completed 

8. INTERVAL BETWEEN TESTS: Approximately 1 day - not critical 

9. CREW TASK LOADS - man hours: Approximately 4 hours per MOL 

mission 

10. CREW TASK FREQUENCY: Approximately once per day 

11. FIELD OF VIEW REQUIREMENTS: Antenna must be able to see substantially all the visible areas of the earth's surface. 

12. GROUND CONTROL LIAISON DURATION: Continuous from 5 minutes 

before test until test completion. 

13. GROUND CONTROL LIAISON FREQUENCY: Once per day 

14. EXTERNAL TEST ITEMS: 

a. Launched from Station: None required 

b. Launched from resupply: None required 

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TEST OPERATING CHARACTERISTICS (Cont'd) 

c. Launched from ground: None required 

15. QUALIFICATION TESTS (other than space) 

a. Ground: Acceptance of equipment in environment specified. 

b. Atmosphere: Not required 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT 

1. Establish radio contact between MOL and aircraft 

2. Power on transmitters 

3. Attempt to align antennas 

4. After align switch to auto-'track on signal' 

5. Record received signal 

6. Initiate modulation sequence 

7. Transmit record to ground on first opportunity. 

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Data Reduction N 

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0 

Exp. No. S-2 

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NARROW BEAM COMMUNICATION EXPERIMENT 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required: One 

(1) Man's Function 

(a) As part of test: To point antenna to establish link. 

(b) As technician conducting test: To activate sequence of 

experiment recording received signal and transmitting canned 

modulation. Transmit to ground. 

b. Crew Skill requirements: No special skills required 

c. Manpower Profile: Not more than 10 minutes per test 

d. Critical Functions: Antenna Pointing 

e. Work Positions: Seated 

f. Time Controlled Tasks: Not applicable 

g. Human Performance Measures: Ability to continuously monitor 

incoming signal. 

h. Physiological and Psychological Measures: N/A 

i. Selection Factors: N/A 

j. Training requirements: Familiarity with control response 

2. GROUND PERSONNEL: 

a. Number required: Two; 1 engineer, 1 technician 

(1) Man's function: Same as (a) above 

(a) As Part of test: It It 

(b) As technician conducting test: Same as (a) above 

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MANNING DESCRIPTION (Cont'd) 

b. Crew Skill Requirements: Same as Astronaut 

c. Manpower Profile 

d. Critical Functions 

e. Work Positions 

f. Time Controlled Tasks 

g. Human Performance Measures 

h. Physiological and Psychological Measures: Same as Astronaut 

i. Selection Factorl 11 

j. Training Requirements 11 

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Exp. No. S -2 

NARROW BEAM COMMUNICATION EXPERIMENT 

COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE: 4 kc 

2. FUNCTIONS TO BE MEASURED: ANTENNA POINTING ANGLE, 

received wave form, AGC voltage 

3. TYPE OF ANALYSIS REQUIRED: Astronauts assessment of voice 

intelligibility 

4. PICTORIAL .DATA REQUIRED: No 

5. REAL TIME MONITORING REQUIREMENT: No 

6. DATA EDITING OR COMPRESSION: No 

7. READ-OUT TIME: No 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS: Not required 

after transmission to ground 

9. MANUAL AND/OR AUTOMATIC CONTROL: Manual control 

10. SIMULTANEITY: No 

11. GROUND COMMANDS REQUIRED: Radio contact between MOL and 

aircraft to start experiment. 

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NARROW BEAM COMMUNICATION EXPERIMENT 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME: 12 Months 

2. FINAL DEFINITIVE TEST DESIGN TIME: 6 Months after development 

time 

3. NUMBER. OF GROUND OR FLIGHT TESTS REQUIRED: 2 

4. TYPE OF DEVELOPMENT TEST ITEMS: Space Acceptance Test 

Standards 

SUPPORT EQUIPMENT DEVELOPMENT TIME: Will be developed with 

equipment 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test: 1 for aircraft installation 

b. Atmospheric Test: None 

c. Space Test: 6 for MOL series 

7. DATE AVAILABLE FOR TESTS: Early 1966 

8.. CURRENT DEVELOPMENT STATUS 

a. Proposed only: Proposed only 

b. Project or program is approved and test item is under study, breadboard stage, etc. 

c. Funds expended to date. 

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Experiment No. S-3 

3 March 64 

LASER PROPAGATION 

I. TEST OBJECTIVE: 

It is required to determine the potential value for ground-to-space and 

space-to-ground of communication links using laser beams. The inherently 

wide bandwidths which can be supported by a laser carrier would be applicable to space missions involving transfer of wide band data, e.g. , photographic. The use of a concentrated beam of a fraction of a degree with antiintercept and anti-jam advantages would provide a reliable and secure 

information-transfer link between an orbiting command post and a ground 

command center. 

II. IMPORTANCE OF THE TEST: 

The test is necessary in order to be able to assess the propagation 

characteristics of the medium by recording the signal profiles, as the MOL 

passes from maximum slant range from the ground transmitter (minimum 

elevation angle) to minimum range (in the case of a zenith pass this corresponds to the orbital height of MOL). These include climatic conditions, 

cloud cover, turbulences, beam scintillation, and interfering signals, e.g. , 

cloud reflections. Because of the randomness of the propagation medium it 

would not be possible to simulate its characteristics and thus obtain the required data for analysis. An astronaut will be required to adjust for maximum signal the lens system of the laser detector on board the MOL and 

continuously monitor its orientation during a test pass of not more than 

5 minutes. 

III. DESCRIPTION OF THE EXPERIMENT: 

In this experiment the major complexity will be retained on the ground. 

The ground facility will consist primarily of a laser radar and the MOL will 

be equipped with a laser receiver only. A portion of the MOL surface will 

contain suitable reflectors for the laser radar in order to ensure track-onsignal. Initially the pointing angle for the pencil beam radar will be provided by slaving to a conventional radar. The receiver equipment on-board 

MOL will simply detect and record the signal froth the LASER radar. 

Pointing of the LASER receiver lens system for maximum signal will be a 

critical part of the test since the angle of arrival of the signal will be an 

important parameter which will be recorded. The astronaut will point the 

lens system for maximum signal during a contact. 

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a. Configuration of Test Items: The fundamental items for this test 

are a LASER detector with direction flexibility and a recording device of four 

channels to record time, angle of arrival, signal profile and a voice channel. 

The space, weight, characteristics are 1 cu ft. , 20 lbs and 25 watts. The 

equipment will be located on the wall of MOL. 

b. Test Support Equipment Required: 

(1) Space craft: (as above) 

(2) AGE: A ground based LASER radar (refer S-66 satellite 

program) and a recorder for returned-signaI profile, azimuth, elevation, 

range, and time. 

(3) A ground based tracking radar for back-up initial orientation 

of LASER beam. 

c. Test Procedure: Voice contact between the ground terminal and 

MOL will be established prior to initiation of test. The ground LASER radar 

will illuminate MOL and the LASER receiver will be oriented by an astronaut 

to receive the maximum signal. As soon as tracking is confirmed the recorder on-board will be turned on and recording will continue for the duration of 

the pass. 

(1) The astronauts role will be maintaining the LASER receiver 

pointed to receive maximum signal from the ground radar and his ability to 

do so will be a subjective opinion of the astronaut and so conveyed during 

voice contact with the ground terminal. A test will not exceed 5 minutes and 

could be repeated on any orbit which would allow not less than a 3 minute 

contact. 

d. Category of Experiment: This experiment falls in category (b) 

since only a minor structural accommodation will be required to support 

the test.- Provision must be made for unobstructed orientation of the receiver consistent with the attitude of MOL during the test, i.e. , a lookthrough capability. 

e. Cost: FY 65 FY 66 FY 67 FY 68 TOTAL 

150 K 225 K 150 K 50 K 575 K 

f. Schedule: Not determined. 

IV. PARTICIPATING GOVERNMENT AGENCIES: 

Sponsor: RTD 

Participant: ESD-CRL 

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V. ADDITIONAL REQUIREMENTS: 

a. Special Security - No. 

b. Manning Description - See attachment. 

c. Logistics: Not determined. 

d. Facilities: A ground LASER radar has been developed for the S-66 

satellite, however, it is expected that modifications and design improvements 

will be achievable for the MOL program. It would be desirable to have more 

than one such terminal and mountain locations would probably be necessary 

to reduce atmospheric attenuation. • 

e. Simulation and Training: 

(1) Astronaut: Technician level will be adequate. Familiarity 

with the sequence of the test and the response of the receiver-pointing controls will be necessary. This would not require special simulation equipment. Procedures will be provided. 

(2) Ground Personnel: Engineering level'will be necessary and 

good knowledge of the operation of a LASER radar will be essential. 

VI. GENERAL: 

a. Communication and Data Handling Requirement: The data required 

to be sent from MOL to the ground would be equivalent to a low information 

rate 4 channel tape and would be sent when convenient. 

b. Development Characteristics: See attached. 

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DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED: LASER Beam tracking and receiving 

equipment. 

2. WEIGHT: 20 lbs (max) 

3. VOLUME: Stored 1 cu. ft. In Use same. 

CRITICAL DIMENSIONS - SHAPES Ability to orient optical receiver 

(lens) through a 180° viewing angle. 

4. POWER 

a. Continuous - 25 watts 

b. Stand-by - none 

c. Average operating - 25 watts 

d. Peak - 25 watts 

e. Duty cycle - continuous during experiment 

5. SPARES 

a. Volume 

b. Quantity none required 

c. Weight 

6. TOOLS 

a. Volume 

b. Quantity 

none required 

c. Weight 

d. Power 

7. HEAT OUTPUT - 90 BTU/hr 

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8. STABILITY 

a. Moving parts - Lens system must be capable of movement through 

a 180 angle (j90° from vertical) 

9. VIBRATION LIMITS - MIL SPEC as applied to other equipment in the 

MOL will be satisfactory. 

10. SHOCK LIMITS - 20g 

11. HAZARDS (fire, explosion, electrical, toxic, other) - none 

12. TEMPERATURE LIMITATIONS - 80° C ambient 

13. TYPE AND RANGE OF MEASUREMENT (definition of parameters to be 

measured while test is underway). Signal strength, fading rates, tracking angle error. 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS - none 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: 

Station - angle should be maintained within 39° of planned position and 

drift rate should not exceed 1° per minute. 

Equipment: No position accuracy established. Will be furnished later; 

must be accessible to operator. 

16. EQUIPMENT OPERATING CYCLE 

Frequency - 1 per day 

Time duration - 15 minutes 

17. EQUIPMENT LOCATION REQUIREMENTS - not critical except for lens 

system which must be earth oriented. 

18. SPECIAL MOUNTINGS REQUIREMENTS 

Apertures - sufficient to achieve desired positioning (See below) 

Booms - Boom is necessary for operation of lens system over a 180° 

angle 

Windows - none required 

Antennae - lens mount as above 

Bracketry - Brackets for extension and orientation of lens system 

Atch 1 (cont'd) SSTA-1 -9 

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NRO APPROVED FOR 

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Exp No. S-3 

19. PRESSURE VESSELS - Fluids, gasses, etc. none required 

20. ELECTRO MAGNETIC INTERFERENCE (spurious generation, special 

shielding req. etc) none 

21. MAINTENANCE REQUIREMENTS 

Ground - standard radar tracking maintenance 

Space - none. 

SSTA-1-9 

304 

Atch 1 (cont'd) ■ 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp No. S- 3 

LASER PROPRAGATION EXPERIMENT_ 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape: 4 channels 4 kc bandwidth 

b. Film: None 

c. Other: None 

2. HANDLING (Special equipment required to handle items being tested). 

None 

3. PACKING: Standard 

4. CALIBRATION - alignment deployment: none required 

5. JIGS AND FIXTURES: none required 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION: not 

applicable 

7. SENSORS (TRANSDUCER - OUTPUT SIGNALS): not applicable 

8. TRAINERS/SIMULATORS: LASER Transmitter 

9. INSTRUMENTATION - cockpit and/or laboratory (note effect of time 

sharing instruments with other experiments). Indicator light; Tape 

recorder for recording data may be time shared. 

10. RELATED SUPPORT EQUIPMENT 

a. Targets - none 

b. Ground stations: 1 ground station 

c. Tracking: LASER radar ground station with standard tracking radar 

as back-up. 

d. Handling Equipment: none required 

SSTA-1-9 

305 Atch 2 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp No. S-3 

11. AGE: Standard laboratory test equipment will be sufficient. 

12. ENVIRONMENTAL TEST EQUIPMENT: Vacuum chamber and temperature test chamber. 

13. FACILITIES: None required except as noted above. 

SSTA-1 -9 Atch 2 (cont'd) 

306 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp No. S-3 

LASER PROPAGATION EXPERIMENT 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired) 

a. Altitude: Not critical 

b. Inclination: Not critical 

c. Epoch: Not critical 

d. Ellipticity: Not critical 

2. PLANE CHANGE: Not critical 

3. ALTITUDE CHANGE: Not critical 

4. TIME ON ORBIT: Within view of ZI 

5. TEST DURATION: 10 minutes 

6. TOTAL NUMBER OF TEST: 10 

7. TEST FREQUENCY: 1 per day for 10 days 

8. INTERVAL BETWEEN TESTS: 24 hours 

9. CREW TASK LOADS - man hours: 100 mins/per 30 day MOL flight 

10. CREW TASK FREQUENCY: 1 per day 

11. FIELD OF VIEW REQUIREMENTS: 180° 

12. GROUND CONTROL LIAISON DURATION: 5-minutes 

13. GROUND CONTROL LIAISON FREQUENCY: 1 per day for 10 days 

14. EXTERNAL TEST ITEMS: 

a. Launched from Station 

b. Launched from resupply not applicable 

c. Launched from ground 

Atch 3 SSTA-1 -9 

307 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp No. S-3 

15. QUALIFICATION TESTS (other than space) 

a. Ground: Normal bench tests 

b. Atmosphere: Check operation from aircraft 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT: 

1. Power on 

2. Recorder check 

3. Voice contact with ground 

4. Manual acquisition 

5. Switch to automatic track 

6. Close voice channel to ground 

7. Power off 

17. HANDLING PROCEDURES: None 

SS TA-1-9 Atch 3 (cont'd) 

308 
BUDGET REQUIREMENTS BY FISCAL YEAR 

0 

0.1 fs4 

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Atch 4 SS TA-1 -9 

309 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp No. S-3 

LASER PROPAGATION EXPERIMENT 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required: one 

(1) ManIs function 

(a) As part of test: none 

(b) As technician conducting test: to operate equipment and 

orient antenna in manual mode 

b. Crew skill requirements: none 

c. Manpower profile: Not applicable 

d. Critical functions: adjustment of lens in manual acquisition mode 

e. Work Positions: Normal 

f. Time Controlled Tasks: None 

g. Human Performance Measures: Not applicable 

h. Physiological and Psychological Measures: Not applicable 

i. Selection Factors: No special 

j. Training Requirements: Training in operation of LASER equipment. 

2. GROUND PERSONNEL 

a. Number required: 3 

(1) Man's Function 

(a) As part of test: none 

(b) As technician conducting test: To operate equipment. 

b. Crew Skill Requirements: Radar operation skills. 

SSTA-1-9 At ch 5 

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NRO APPROVED FOR 

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Exp No. S-3 

c. Manpower Profile: 1 Engineer, 2 technicians 

d. Critical Functions: Operation of tracking equipment 

e. Work Positions: Normal 

f. Time Controlled Tasks: None 

g. Human Performance Measures: Not.applicable 

h. Physiological and Psychological Measures: Not applicable 

i. Selection Factors: No special 

j. Training Requirements: Training in LASER equipment operation. 

SSTA-1-9 

311 

Atch 5 (cont'd) 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp No. S-3 

LASER PROPAGATION EXPERIMENT 

COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE: Voice bandwidth - 4 kc. 

2. FUNCTIONS TO BE MEASURED: Tracking error signal, signal strength, 

signal/noise ratio, acqusition time, time. 

3. TYPE OF ANALYSIS REQUIRED: Correlation of tracking error, fades, 

and signal/noise ratios. 

4. PICTORIAL DATA REQUIRED: None 

5. REAL TIME MONITORING REQUIREMENT: 4 channel tape recorder 

voice bandwidth 

6. DATA EDITING OR COMPRESSION: None 

7. READ-OUT TIME: 5 minutes/pass 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS: Tape storage 

and punched card stores 

9. MANUAL AND/OR AUTOMATIC CONTROL: Automatic level control. 

Start- stop manual. 

10. SIMULTANEITY: All channels to be recorded simultaneously. Staggered 

recroding heads are permitted. 

11. GROUND COMMANDS REQUIRED: Voice contact with astronaut for 

first 2 1/2 minutes and last 2 1/2 minutes. 

SSTA-1 -9 Atch 6 

312 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp No. S-3 

LASER PROPAGATION EXPERIMENT 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME: 12 Months 

2. FINAL DEFINITIVE TEST DESIGN TIME: 2 Months 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED: Bench tests for 

30 days 

4. TYPE OF DEVELOPMENT TEST ITEMS 

a. Vacuum chamber 

b. Shaker 

c. Thermal 

d. Acoustic 

e. Simulators 

f. Aircraft 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME: 12 Months 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test: 2 

b. Atmospheric Test: 2 

c. Space Test: 2 

7. DATE AVAILABLE FOR TEST: 15 months after award of contract 

8. CURRENT DEVELOPMENT STATUS 

a. Proposed Only 

b. Project or Program is approved and test item is under study, 

breadboard stage, etc. 

c. Funds expended to date. 

SSTA-1 -9 

313/314 Atch 7 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Experiment No. S-4 

HIGH FREQUENCY IONOSPHERIC-DUCTING COMMUNICATION 

I. TEST OBJECTIVE 

The purpose of this test is to determine the propagation of high frequency waves between points on the ground and the orbiting laboratory as it 

moves within and above the ionosphere. In particular, it is desired to 

determine to what degree it is possible to communicate with the orbiting 

laboratory by means of high frequency radio waves while the laboratory is 

beyond line-of-sight range of the ground communication point. Communication to and from high flying aircraft should also be examined. From this 

data it will be possible to decide how many ground stations are necessary 

to insure maintaining continuous contact with an orbiting space vehicle, 

and to predict the operating frequencies and power requirements for such 

communication. While such communication channels are likely to be limited 

in bandwidth, and may not serve the purpose of linking a command post to 

the ground for high rate data transmission, they still can form an extremely 

effective backup system for the essential elements of command and control. 

II. IMPORTANCE OF THE TEST 

To achieve the operational results indicated above, we must be able 

to forecast propagation conditions with accuracy and design an effective 

communication system. Although, a substantial amount of data has been 

obtained on the electron density in the ionosphere, and although some experiments with high frequency communication between an orbiting object and 

ground were made during Project Mercury flights, we still have insufficient 

information to indicate what may be expected of such a system or to measure 

the confidence factor with which it may be applied in military missions. 

SSTA-l-9 

315 
NRO APPROVED FOR 

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Exp. No. S-4 

Such tests must be made in space because the propagation conditions cannot 

be accurately simulated in any other location. Tests of limited duration 

might be made from missiles, but the thorough examination of the propagation 

phenomena that are necessary require more time than can be easily allotted 

to missile investigations. 

Conducting this experiment in the manner indicated below will directly 

help to assess man's ability and utility in spaCe by determining his effectiveness in operating relatively conventional communication equipment to perform 

communication .experiments and to record the results. 

III. DESCRIPTION OF THE EXPERIMENT 

The experiment may conveniently be planned in two major phases: (1) 

receiving in the orbiting laboratory and (2) two-way communication between 

the laboratory and a ground station. Extensions of these experiments to include aircraft stations in contact with the orbiting laboratory are possible, 

and will be encouraged. 

a. Configuration of Test Items 

The test equipment required in the spacecraft includes: receiver 

covering the H. F. frequency range, a high frequent),transmitter, capable of keyed 

AM and singlesidedband voice modulation. the necessary antennas and antenna 

tuning equipment for effective operation over these ranges, a graphic recorder for 

receiver signal strength capable of being keyed with an accurate time reference, 

a twin track voice recorder capable of recording for the entire duration of the 

experimental period, and the necessary power supplies. Note that special 

power supplies mi ght -be shared with those used for the normal vehicle 

communications in the interest of weight conservation. 

SSTA-1 -9 

316 
NRO APPROVED FOR 

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Exp. No. S-4 

b. Test Support Equipment Required 

The supporting equipment required outside the space vehicle consists 

of normally installed radio transmitters which exist in large numbers of 

around the globe and which will provide a variety of useful signals for 

observing in receiving tests at the spacecraft. Furthermore, selected 

ground stations must be able to transmit on appropriate frequencies for communication with the spacecraft when the spacecraft undertakes to transmit. 

All the necessary equipment for ground support already exists, with the possible exception of specialized recording equipment which may be necessary 

to preserve certain of the test results. 

c. Test Procedure 

At selected times during the mission, as it may be fitted in between 

other experiments, one of the spacecraft personnel will operate the receiving 

position in the spacecraft. After deploying the antennas as necessary, he 

will tune carefully over the frequency range assigned for the experiment, 

noting the call letters and other identification of signals observed. As 

he makes these observations the signal strength recording equipment will 

be activated and will provide a log of the signals received against time 

references obtained from the vehicle timing system. At the same time the 

twin channel voice recorder will be operative. One channel will record the output 

of the receiver to which the operator is listening; the other channel will 

be connected to a microphone used by the receiver operator, and will record 

his comments on what he hears and observes, and on what troubles he may have 

in performing the experiment. Tone impulses or other identification signals 

from the vehicle timing reference system will be imprinted on the channel 

on which the operators voice is recorded to enable correlating his observations and the received signals with the signal strength record. 

SSTA-1 -9 

317 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp. No. S-4 

A program and schedule for the observations will be provided to 

the operator enabling him to make specific observations with regard to 

ground locations that are favorably situated, unfa vorably situated, or 

in a marginal location. From analysis of this data, it is expected that 

we will ba able to predict the attenuation between the spacecraft and ground 

locations beyond line-of-sight. 

From time to time during the operation, it will be desirable for 

the operator to attempt to establish two-way contact with selected ground 

stations. This will be accomplished by single sideband voice, or if this 

proves impractical, by keying a tone in appropriate code. 

To facilitate this two-way communication, it shall be possible 

for the transmitter to be synchronized with the receiver in the fashion 

normally known as "transceiving operation". This is an operation wherein 

the heterodyning oscillators are used in transmitting and receiving so that 

the transmission is necessarily on exactly the frequency to which the receiver is tuned. This insures maximum precision of tuning for reception 

on the ground, except for the corrections that may be necessary for doppler 

frequency. 

It is desirable that the receiver be capable of continuous tuning 

throughout the range, rather than synthesized in descrete steps, to permit 

the following and tracking incoming frequency of ground stations despite 

the changes in apparent frequency due to doppler effect. 

Summaries of significant observation may be transmitted to ground 

as part of the ships normal report through the appropriate data links, the 

recording comprising the entire set of observations made during the test 

will be returned with the capsule to the ground if necessary. 

SSTA-1-9 

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NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp. No. S-4 

Development of compact recorders capable of functioning without 

attention for long periods of time will be necessary to instrument this 

activity. 

The human operator plays a vital role in this experiment for many 

reasons. The skill of a human operator in extracting intelligence from a 

mix ture of signal and noise has been noted in numerous experiments. The 

ability of the operator to scan, acquire, and track signals especially when 

these signals may be intermittent or fading, exceeds what can be successfully provided by automatic devices. To be useful for command and control 

purposes, it is vital that we know exactly what can be accomplished by 

a skilled operator in manipulating communication devices of a conventional 

type. The number and variety of experiments that can be carried out during 

a limited time by a human operator exceed what can be planned for an 

automated sequence. It would be difficult to devise command signals of 

sufficient complexity to permit a similar observation to be made on command 

from an unmanned satellite. 

d. Category of Experiment 

This experiment may be classified in category (a) because the ability 

to transmit and receive beyond line-of-sight contributes directly to the 

safe aspects of the orbiting laboratory program. Ability to remain continuously in contact with the vehicle for extended periods of time from a 

single ground point will enhance the ability of ground observers to determine the condition and status of the vehicle operators. The effect on 

crew moraleof having dependable long range communication from the vehicle 

is expected to be advantageous. 

SSTA-1 -9 

319 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp. No. S-4 

e. Cost 

FY 65 FY 66 FY 67 FY 68 FY 69 TOTAL 

$25,000 $129,000 $44,000 $16,000 $4,000 $218,000 

f. Schedule 

It is anticipated that suitable equipment can be prepared in time 

for inclusion within the manned orbiting laboratory without adversely effecting the schedule for these experiments. 

IV. Participate in Government Agencies 

Sponsor: RDT 

Participant: ESD-RADC 

V. Additional Requirements 

a. Special Security 

None. 

b. Manning Description Summary 

See attachment 5. 

c. Logistics 

Not -yet determined. 

d. Facilitie 

Ground station facilities with necessary equipment already exist. 

The stations must be able to transmit on frequencies compatible for communication with the spacecraft during periods of two-way transmission. 

The spacecraft facilities consist of presently available receivers 

and transmitters which will require only modifications for installation in 

spacec raft. 

SSTA-1-9 

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Exp. No. S-4 

e. Simulation and Training 

(1) Astronaut; technician level will be adequate, familiarity with 

the sequence of tests and ability to adjust and tune receiver and transmitter 

should be adequate. There will be no requirement for special simulation 

equipment. 

(2) Ground Personnel; technician level will be adequate during 

operation of global distributed VHF stations. 

VI. General 

a. Communications and Data Handling Requirement 

The two-way voice transmissions from the MOL spacecraft to the 

ground would be equivalent to a low information rate and could be recorded 

on a four-channel tape recorder. 

b. Development Characteristics 

See attachment 7. 

SSTA-1-9 

321 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp. No. S-4 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED: VHF Communications Equipment 

2. WEIGHT: 50 lbs. 

3. VOLUME: Stored 4 cu. ft. In use Same 

CRITICAL DIMENSIONS - SHAPES: None - deployable antenna required 

with tuning to be made by astronaut. 

4. POWER 

a. Continuous - 100 watts 

b. Stand-by - 10 watts 

c. Average operating - 100 watts 

d. Peak - 100 watts 

e. Duty cycle - continuous during test 

5. SPARES 

a. Volume - none 

b. Quantity - none 

c. Weight - none 

6. TOOLS 

a. Volume - none 

b. Quantity - none 

c. Weight - none 

d. Power - none 

7. HEAT OUTPUT - 200 BTU average 

8. STABILITY 

a. Moving parts -not critical 

SSTA-1-9 

Atch 1 

322 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp. No. S-4 

DESIGN CHARACTERISTICS TEST EQUIPMENT (Cont'd) 

9. VIBRATION LIMITS - MIL SPEC as applied to other equipment in the 

MOL will be adequate. 

10. SHOCK LIMITS - 20g 

11. HAZARDS (fire, explosion, electrical, toxics, other) None 

12. TEMPERATURE LIMITATIONS - 80° C ambient 

13. TYPE AND RANGE OF MEASUREMENT (definition of parameters to be 

measured while test is underway). Tuning across frequency range, 

noting of station call letters, identification of signals, observation of 

signal strength, and logging of signals received. 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS - None 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: 

Station: Not critical 

Equipment: No position accuracy established, must be accessible to 

astronaut. 

16. EQUIPMENT OPERATING CYCLE 

Frequency - continuous during first six orbits by recording of stations 

received, other sequence of tests shall occur three times each day. 

Time Duration - 15 minutes per test 

17. EQUIPMENT LOCATION REQUIREMENTS 

Not critical except for deployment of the antennas 

18. SPECIAL MOUNTINGS REQUIREMENTS 

Apertures - not critical 

Booms - none required 

Windows - none required 

Antenna - Must be extendable from at least two sides of vehicle 

Bracketry - brackets must be provided for mounting of receiver and 

transmitter and for extension of the antennas. 

Atch 1 (Cont'd) SSTA-1 -9 

323 
NRO APPROVED FOR 

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Exp. No. S-4 

DESIGN CHARACTERISTICS TEST EQUIPMENT (Cont'd) 

19. PRESSURE VESSELS - fluids, gasses, etc. - none required 

20. ELECTRO MAGNETIC INTERFERENCE (spurious generation, special 

shielding required etc.) None 

21. MAINTENANCE REQUIREMENTS 

Ground - technician level adequate 

Spacecraft - none will be required 

SSTA-1.-9 Atch 1 (cont'd) 

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NRO APPROVED FOR 

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Exp. No. S-4 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape - 2 channel with 4-kc bandwidth per channel; compact recorder 

capable of functioning for long periods will be required. 

b. Film - none 

c. Other - none 

2. HANDLING (special equipment required to handle items being tested). 

None 

3. PACKAGING - standard 

4. CALIBRATION - alignment, deployment: none 

5. JIGS AND FIXTURES: N/A 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION: N/A 

7. SENSORS (TRANSDUCER - OUTPUT SIGNALS): Record output of 

receiver and connection to microphone used by astronaut. 

8. TRAINERS/SIMULATORS: N/A 

9. INSTRUMENTATION - cockpit and/or laboratory (note effect of time 

sharing instrument with other experiments). Indicator lights, astronaut 

observations, and tape recordings. 

10. RELATED SUPPORT EQUIPMENT 

a. Targets - none 

b. Ground Stations - ground stations for two-way communication 

between astronaut and ground - also aircraft-to-MOL tests. 

c. Tracking - N/A 

d. Handling Equipment - standard equipment sufficient 

11. AGE - standard test equipment sufficient 

12. ENVIRONMENTAL TEST EQUIPMENT: Vacuum chamber and temperature test chamber. 

13. FACILITIES: None required except as noted above. 

Atch 2 SSTA-1 -9 

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NRO APPROVED FOR 

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Exp. No. S-4 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired) 

a. Altitude - not critical 

b. Inclination - not critical 

c. Epoch - not critical 

d. Ellipticity - not critical 

2. PLANE CHANGE - not critical 

3. ALTITUDE CHANGE - not critical 

4. TIME ON ORBIT - continuous during first six orbits for monitoring 

of receive signals; for voice communications within view of CONUS 

5. TEST DURATION - continuous monitoring during first 6 orbits of 

receive signals 15 minutes required for voice communications test 

6. TOTAL NUMBER OF TESTS - 30 tests 

7. TEST FREQUENCY - 3 voice test per day for 10 days; continuous 

monitoring during first 6 orbits of receive signals 

8. INTERVAL BETWEEN TESTS - not critical 

9. CREW TASK LOADS - man hours: 1000 minutes per 30 day MOL orbit 

10. CREW TASK FREQUENCY - 3 per day 

11. FIELD OF VIEW REQUIREMENTS - not critical 

12. GROUND CONTROL LIAISON DURATION - 3 times a day; 15 minute 

duration 

13. GROUND CONTROL LIAISON FREQUENCY - same as above 

14. EXTERNAL TEST ITEMS: 

a. Launched from Station - N/A 

b. Launched from resupply - N/A 

c. Launched from ground - N/A 

SSTA-1 -9 Atch 3 

326 
NRO APPROVED FOR 

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Exp. No. S-4 

TEST OPERATING CHARACTERISTICS (Cont'd) 

15. QUALIFICATION TESTS (other than apace) 

a. Ground - normal bench tests 

b. Atmosphere - can be tested in chambers 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT 

1. Power on 

2. Deploy antennas 

3. Recorder on 

4. Tune over frequency range of receiver 

5. Identify call letters and signals 

6. Observation of receive signal strength 

7. Log of signals received against time 

8. Switch-over to two-way communications 

9. Establish two-way contact with selected ground stations 

10. Describe observations during test to ground 

11. Power off 

17. HANDLING PROCEDURES - N/A 

Atch 3 SSTA-1-9 

327 
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328 

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Simulators/Trainers Data Reduction 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp. No. S-4 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required: two occasionally 

(1) Man's function: 

(a) as part of test: none 

(b) As technician conducting test: to operate continuous tuning 

receiver, adjust antenna, and provide voice communications 

to ground during tests 

b. Crew skill requirements: none 

c. Manpower Profile: N/A 

d. Critical Functions: adjustment of antenna and monitoring and logging 

of communications stations received 

e. Work Positions: normal 

f. Time Controlled Tasks: none 

g. Human Performance Measures: N/A 

h. Physiological and Psychological Measures: N/A 

i. Selection Factors: trained to technicians level to operate communications equipment 

j. Training Requirements: Trained to technicians level to operate 

communications equipment 

2. GROUND PERSONNEL 

a. Number required: three 

(1) Man's function 

(a) As part of test: none 

(b) As technician conducting test: to operate HF equipment 

during two-way voice communications with astronaut 

b. Crew Skill Requirements: technicians level 

c. Manpower Profile: 1 engineer, 2 technicians 

Atch 5 SSTA-1 -9 

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Exp. No. S-4 

MANNING DESCRIPTION (Cont'd) 

d. Critical Functions: none 

e. Work Positions: normal 

f. Time Controlled Tasks: N/A 

g. Human Performance Measures: N/A 

h. Physiological and Pyschological Measures: N/A 

i. Selection Factors: not critical 

3. Training Requirements: operation and maintenance of HF communications equipment 

SSTA-1 -9 

330 

Atch 5 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp. No. S-4 

COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE: voice bandwidth - two 4-kc channels 

2. FUNCTIONS TO BE MEASURED: tuning across frequency range, noting 

of station call letters, identification of signals, observation of signal 

strength, logging of signals received, and two-way voice communications 

from spacecraft to ground 

3. TYPE OF ANALYSIS REQUIRED: judgement of astronaut as to signals 

received, signal strength, location of stations, and voice reporting 

to ground 

4. PICTORIAL DATA REQUIRED: none 

5. REAL TIME MONITORING REQUIREMENT: two-channel tape recorder, 

4-kc bandwidth per channel 

6. DATA EDITING OR COMPRESSION: none 

7. READ OUT TIME: N/A 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS: two-channel 

tape recorder 

9. MANUAL AND/OR AUTOMATIC CONTROL: on HF transceiver, remote 

frequency control, and antenna tuning and steering control are automatic; 

stop/start of communication equipment, recorder and tuning across HF 

frequency band to be manual 

10. SIMULTANEITY: two-voice channels to be recorded simultaneous 

11. GROUND COMMANDS REQUIRED: voice communication with astronaut 

on scheduled test that will be determined at a later date 

Atch 6 SSTA-1 -9 

331 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

Exp. No. S-4 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME: no development time required; 12 months lead 

time for procurement 

2. FINAL DEFINITIVE TEST DESIGN TIME: 6 months 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED: ground tests 

using chambers for 30 days; no flight tests required 

4. TYPE OF DEVELOPMENT TEST ITEMS 

a. Vacuum Chamber: yes 

b. Shaker: yes 

c. Thermal: yes 

d. Acoustic: yes 

e. Simulators: no 

f. Aircraft: no 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME: no development time 

required, existing equipment available 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test: 2 

b. Atmospheric Test: none 

c. Space Test: 5 

7. DATE AVAILABLE FOR TESTS: 12 months after award of contract 

8. CURRENT DEVELOPMENT STATUS 

a. Proposed only: yes 

b. Project or program is approved and test item is under study, 

breadboard stage, etc. - existing equipment in HF band presently 

available 

c. Funds expended to date: none 

SSTA -I -9 Atch 

332 
NRO APPROVED FOR 

RELEASE 1 JULY 2015 

GONFH)ENTIAL Experiment No. S-5 

ENCAPSULATION AND RECOVERY OF SPACE OBJECTS 

I. TEST OBJECTIVES 

The objectives of this test are three-fold; determine man's ability to 

apply polyurethane or other plastic ablators to an object (such as an enemy 

satellite), determine the effects of the space environment on the free flowing, 

foaming, and setting characteristics of these ablators, and finally, to determine the feasibility of deorbiting and recovering this object from space. The 

successful execution of this experiment will provide the USAF with the capability of recovering either previously launched U.S. satellites, or more important, 

recovery for ground inspection of enemy or foreign satellites. 

II. IMPORTANCE OF THE TEST 

The inspection and ultimate recovery of foreign enemy satellites is one 

of the potential military missions for USAF. Also inspection and recovery of 

previously launched U.S. satellites would provide invaluable data on materials 

degradation, and causes of failures of satellites. 

The only way available to test man's ability to utilize encapsulated foam 

recovery satellites is to conduct a small scale experiment in apace. Since • 

man is in the experiment, a piggyback shot experiment is not feasible. Hence, 

this experiment should be conducted on the MOL. Zero g aircraft tests will 

not provide sufficient test durations; also they do not provide a vacuum 

environment. 

This will definitely assess man's ability and utility in the area of 

recovering enemy satellites. 

III. DESCRIPTION OF THE EXPERIMENT 

A small scale satellite, containing recovery aids, will be stowed in the 

unpressurized area of MOL. An astronaut will enter this area and apply the 

polyurethane foam to the test article. The foam will expend by a factor of 

20 and form a rigidized ablative coating over the satellite's surface. (The 

space available in MOL witl determine the size of the target. The techniques 

and methods of applying the foam are to be determined by further study.) 

Following application of the foam, the astronaut will conduct an 

inspection of the teat article and will determine the effects 

SSTA-1-9 

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Exp. No. S-5 -CONFIDENTIAL-- 

Recovery of Satellites via the Utilization 

of man and encapsulated Foam Coatings 

-2- 

of zero "g" and hard vacuum on the free flowing characteristics of polyurethane foam. This portion of the experiment will determine man's ability and 

utility in applying polyurethane foam coatings to satellites or data capsules 

for eventual recovery. The next phase of this experiment is contingent on 

the previously outlined phase being completed successfully. This second phase 

will deal with the deorbiting and re-entry of the foam:encased satellite. 

Several techniques are available for this phase of the experiment. Retro 

recovery pack or piggy back re-entry on Gemini. The selection as to which 

approach to foliar will be made during the early stages of R&D. Man's 

ability to recover unfriendly or previously launched U.S. satellites will be 

the final determination of this experiment. 

a. Configuration of Test Items 

The key items of this experiment are mock up small enemy satellites, 

capsulated foam reactants, and possibly retro recovery pack. Total experiment weight 45-50 lb. and 3 cu ft. package' volume. This experiment will be 

stored in unpressurized module of MOL. See Attachment 1. 

b. Test Support Equipment Required 

(1) Spacecraft - None 

.(2) AGE - None 

c. Test Procedure 

The test satellite will be staved in unpressurized module of MOL. 

Astronaut will photograph and inspect satellite, astronaut will encase 

satellite in a ball or casing of polyurethane foam, astronaut will attach 

retro recovery package, and finally command deorbitat-directiCa.of ground 

control of satellite. Alternate possible deorbit re-entry piggyback on 

Gemini. 

Man's rolevill be a key portion of this mission, he is directly 

involved in all atests. Man will apply foam to satellite, observe its 

reaction in total space environment, and finally command deorbit. The 

success or failure of this experiment vill be very dependent on man. 

d. Category of Experiment 

This experiment to determine the one aspect of military capability 

of man in space, but requires no modification to MOL vehicle. Category B. 

SS TA-1-9 

334 

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-CONFIDENTIAL-. Exp . No. S-5 

Recovery of Satellites via the 

Utilization of Man and Encapsulated 

Foam Coatings 

-3- 

e. Cost 

Total - $1,800K. See Attachment 4. If Gemini piggy back recovery 

is utilized, reduce funds by $600K-700K. 

f. Schedule 

(1) Hardware and software avilable for qualification tests, late 

1965. 

(2) Hardware and software available for flight readiness, 1966. 

IV. PARTICIPATING GOVERNMENT AGENCIES 

Sponsor: AF Aero Propulsion Laboratory, RTD, (APPT), and SSD. 

Test Equipment Acquisition: Same and SSD 

V. ADDITIONAL REQUIREMENTS 

a. Special Security 

Mission objective and success of mission classified SECRET, because 

of military implications. 

b. Manning Description Summary 

See Attachment 5. One astronaut required for 70 minutes for test. 

No special skills required. 

c. Logistics - N/A 

d. Facilities 

Existing facilities such as vacuum chamber, zero "g" flights, shakerattle-roll, etc. are in existence and are-available to AFFT, sponsor. 

e. Simulaticn and Training 

(1) Astronaut: Astronaut would be required to learn techniques 

for applying and triggering encapsulated foam reactants. Astronaut would be 

required to learn how to apply retro recovery package to satellite. This 

training you'd last approximately four (4) vcrking days. 

(2) Ground Personnel: A Discover recovery team would be utilized 

for recovery of satellite. No additional training would be required. 

Alternate Gemini piggy back reentry would require no additional recovery 

forces. 

(3) Equipment: All necessary facilities, etc. are available to 

sponsor. 

SS TA - 1 -9 

-CONFIDENTIAL- .335 

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Exp. No. 5-5 -CONFIDENTIAL-. 

Recovery of Satellites via the 

Utilization of Man and Encapsulated 

Foam Coatings 

-4- 

VI. GENERAL 

a. Communication and Data Handling Requirement - See Attachment 6. 

b. Development Characteristics - See Attachment 

55 TA-1-9 

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Exp. No. S-5 -CONFtDENTIAL--- 

ATTACHMENT 1 (cont'd) 

Recovery of Satellites via the Utilization of Man and Encapsulated Fdam Coatings 

- 6 - 

15. ORIENTATION AND POSITION ACCURACY REQUIREMNTS: 

a. Station - N/A 

b. Equipment - Mist be stable, not tumbling during deorbiting sequences. 

16. EQUIPMENT OPERATING CYCLE 

The test items vili be operated once during the experiment. Total time 

duration of it 45-60 minutes... . Maximum, possibly less. 

17. EQUIPMENT LOCATION REQUIREMENTS - Dbpressurized compartment for all 

experiment items. 

IS. SPECIAL MOUNTINGS REQUIREMENTS - Brecketry for launching enemy target 

'satellite, and stowage bracketry or tie 

down fittings. 

19. PRESSURE VESSELS - Small nitrogen pressure bottle for pressurizing foam 

reactants. This say be an unnecessary item if micro 

encapsulated foam reactants are utilized. 

20. ELECTRO MAGNETIC INTERFERENCE - NIA 

21. MAINTENANCE REQUIREMENTS - N/A 

• SSTA-1 -9 

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-CONFIDENT-1MAttachment 2 

Exp. No. S-5 

Recovery of Satellites via the 

Utilization of Man and Encapsulated 

Foam Coatings 

- 6a - 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Possibly tape record astronaut's comments on experiment 

b. Film - 16-35mm still photo coverage 

2. HANDLING - N/A 

3. PACKAGING - 

4. CALIBRATION -N/A 

5. JIGS AND FIXTURE - N/A 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE VEHICLE - None 

7. SENSORS - None 

8. TRAINERS/SIMULA'T'ORS - N/A 

9. INSTRUMENTATION - N/A 

10. RELATED SUPPORT EQUIPMENT 

a. Target - 20 lb., satellite 1.2 cu. ft. volume 

b. Ground Stations - Tracking stations 

c. Tracking - should be available for tracing reentry path of 

satellite 

d. Handling equipment - N/A 

11. AGE - N/A 

12. ENVIRONMENTAL TEST EQUIPMENT - N/A 

13. FACILITIES - Vacuum chamber for testing foam reactants over satellite, 

shock, vibration, thermal limit, and reentry simulator required; however, 

all of these facilities are available or are directly under auspices of 

APPT sponsor. 

SST A.-1-9 

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Exp. No. S-5 CONMENTIALAttachment 3 Recovery of Satellite via the Utilization 

of Man and Encapsulated Foam Coatings 

• 7 

TEST OPERATING CHARAL1MISTICS 

1. ORBITAL PARAMETERS - Any orbit selected for MOL will be satisfactory for 

this experiment. 

2. PLANE CHANGE - None. 

3. ALTITUDE CHANGE.- None. 

4. TIME ON ORBIT - Prefer to conduct retrieval of object on daylight 

portion of orbit. 

5. TEST DURATION - 70 minutes. 

6. TOTAL NUMBER OF TESTS - One (1). 

7. TEST FREWENcY - N/A. 

8. INTERVAL BETWEEN TESTS - N/A. 

9. CREW TASK LOADS - One astronaut required. 1.2 manhours. 

10. CREW TASK FREQUENCY - N/A. 

11. FIELD OF VIEW REQUIREMENTS - Field of view afforded by space helmet 

is adequate. 

12. GROUND CONTROL LIAISON DURATION- 30-40 minutes. 

13. GROUND CONTROL LIAISON FREQUENCY - 10 minutes intervals. 

14. ECTERNAL TEST ITEMS - 

a. Launched from Station - 20 lb enemy target satellite 

15. QUALIFICATION TESTS: 

a. Ground - Coating and Foaming of satellite in vacuum chamber, 

shake-rattle-roll, thermal limits, re-entry simulation. 

b. Atmosphere - Aircraft dropping. of satellite with recovery package. 

16. MUMS OF EVENTS Amer OCCUR DURING maw: 

T = 0 Astronaut dons space suit. 

T 8 Astronaut enters unpressurized module of MOL. 

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340 -CONFIDENTIALthu 4fteaseil wrote leleverelee elleillne tee eelleeel deers* eller UMW blesi wife* the leeenleg el the flee.*11* t.... TM, 

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-CONFIDENTIAL- Exp. No. S- 5 

Recovery of Satellite via the Utilization 

Attachment 3 (cont'd) of Man and Encapsulated Foam Coatings 

. 8 - 

T • 9 Astronaut inspects satellite in MOL unpressurized compartment. 

T is 10 Astronaut photographs and inspects satellite. 

T • 16 Astronaut places encapsulated dry reactants over satellite 

and initiates foam reaction. 

.T a 22 Astronaut attaches recovery retro package to satellite. 

T a 25 Astronaut places foam coated satellite outside vehicle. 

Alternate piggyback Gemini re-entry may be utilized. 

T • ? At proper time in orbit determine via ground contact satellite 

is deorbited. 

17. HANDLING PROCEDURES - The astronaut would place encapsulated foam 

reactants coating over entire satellite. Nothing 

else critical involved. 

SSTA-1-9 

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-9- 

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Exp. No. S-5 

Attachment 4 

FUNDING SUMMARY 

BUDGET REQUIREMENTS BY FISCAL YEAR 

PRIOR FY 65 FY66 FY67 FY68 FY69 TOTAL 

Engineering, Developmental 0 300K 300K 400K 400K 225K 1725K 

Environmental Testing 

Integration & Installation 0 0 0 0 75K 75K 

AGE 0 0 0 0 0 0 0 

Simulators/Triiners 0 0 0 0 0 0 0 

Data Reduction 0 0 0 0 0 0 0 

Equipment Rework 0 0 0 0 0 0 0 

Other 0 0 • 0 0 0 0 0 

TOTAL 0 300K 300K 400K 475K 225K 1800K 

Hitch Number 62405336 

* If Gemini piggy back reentry is utilized reduce overall funding by $600K 

to $700K 

SSTA-1-9 

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-CONFIDENTIAL- Exp. No. S-5 

Attachment 5 -loMANNING DF2CRIPTION 

1. ASTRONAUTS 

a. Number Required - One (1) 

(1) Man's function - Man will photograph satellite, apply foam 

reactants to satellite, and finally deorbit satellite. 

b. Crew skill requirements - Normal skills possessed by astronauts 

is adequate. Astronaut will be shown how to apply foam reactants and 

retro recovery pack. 

c. Manpower Profile - Require no more 1.2 manhours per MOL mission. 

d. Critical Functions: - Placing foam reactants over satellite, 

proper deorbiting sequence for landing satellite in desired recovery area. 

e. Work Positions - During inspection - application of foam - de-orbit 

cycle, inside unpressurized module of MOL. 

f. Time Control Task - Only deorbit sequence 

g. Human Performance Measures - Ability of man to place encapsulated 

foam covering and retro recovery pack over a satellite. 

h. Physiological and Psychological Measares N/A 

i. Selection Factors - Normal factors required for astronauts. 

j. Training Requirements - Astronaut to be trained how to cover 

satellite with foam reactants, and how to fire retro recovery pack. 

2. GROUND PERSONNEL - Typical Discover team would be required for recovery 

of reentering satellite unless alternate piggy back reentry undertaken. 

SSTA-1-9 

-CONFIDENTIAL-- 

343 

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Exp. No. S-5 -CONFIDENTIALAttachment 6 

COMMUNICATIONS AND DATA 

HANDLING 

1. DATA RATE - N/A 

2. FUNCTIONS TO BE MEASURED - N/A 

3. MEM' ANALYSIS REQUIRED - N/A 

4. PICTORIAL DATA REWIRED - Still photographs required 16mm or 35mm. 

5. REAL TDB MONITORING RBQUIREi4EMrS - N/A 

6. DATA EDITING OR COMPRESSION - N/A 

7. READ-01M TIME - N/A 

8. REQUIREMENTS FOR PERMANEMB DATA RECORDS - N/A 

9. wawa AND/or AUDOMATIC COMM - N/A 

10. SIMUMANETTY - N/A 

11. GROUND COMMANDS REQUIRED - Ground control vculd give commands for 

specific de-orbit time. 

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Exp. No. S- 5 

Attachment 7 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME - 1.5 years to qualification testing. .5 .8 year 

for testing. 

2. FINAL DEFINITIVE TEST DESIGN TIME - .8 - 1 year. 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED six (6). 

4. TYPE OF DEVELOPMENT TEST ITEMS: 

a. Vacuum Chamber - 4 ea. 

b. Shaker - 2 ea. 

d. Acoustic - 0 

e. Simulators 0 

f. Aircraft Zero "g" - 2 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME 

6. NUMBER TEST ARTICLES REQUIRED FOR: 

a. Ground Test - 4 ea. 

b. Atmospheric - 2 ea. 

c. Space Test - 3 ea. 

7. DATA AVAILABLE FOR TESTS: 

a. Ground and Atmospheric That Mid 1965 

b. Space Test on MOL - 1966 

8. CURRENT DEVEIDFMENT STATUS: 

a. Proposed only - N/A 

b. Project is approved 

c. Funds expended to date - $800K 

SSTA-1 -9 

CONFIDENTIAL-- 345/346 

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Experiment No. S-6 

EXPANDABLE STRUCTURES TECHNIQUES 

I. Test Objective 

This experiment will provide the USAF with the capability of boosting into 

orbit minimum package-size structures which can be expanded into useful larger 

MOL's and space structures. The results of this experiment will have a direct 

bearing on whether or not any portion of a relatively large future space system, 

which of necessity must be partially formed and erected in space, can be so 

designed. 

II. Importance of the Test 

This kind of experiment is needed to determine which of several types of 

expandable structures show potential for space application. The most important 

reason to conduct these tests in space by man is to observe the expanding 

process, resulting stability and deformation characteristics in a zero "g" 

environment. Further, it is desirable to utilize man's observations on the 

long term effects of exposing these structures to the space environment. The 

following future space systems data can be obtained from these tests. 

a. Complete Space Stations and Components 

Numerous expandable space station configurations have been proposed. 

Some of the design problem areas which lend themselves to solution 

through model tests using a manned space station are: 

(1) Deployment characteristics of inflated configurations including stability. 

Effects of complete space environment of rigidization processes. 

Methods of deploying rigid module systems (telescoping systems). 

Gas retention of gas stabilized structures. 

Long term effects of structural exposure to space environment. 

Man will be needed to make these periodic observations. 

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Exp No. S-6 

b. Solar Collectors and Antenna Applications 

An experiment designed to determine the applicability of a particular 

expandable concept to solar collector and antenna construction would consist 

of deploying a dynamically scaled structural replica of a solar collector in 

the space environment and conducting tests in which signal pattern and intensity 

are recorded along with measurements of local reflective surface deformation. 

The principal objective of the experiment is the measurement of deformation 

tolerance control to structure size. Man would play an invaluable role in 

determining surface imperfections of the rigidized solar collectors, which 

is of paramount importance. 

Scaling of collector-antenna results to full scale is straightforward. The principal problem area in this experiment is the extrapolation of 

structural data to full scale. MI, will afford the earliest possible platform 

from which these experiments can effectively be conducted. 

III. Description of the Experiment 

Four small expandable structure cylinders would be deployed early in a 

MIL mission. One cylinder would be constructed of airmat, one of expandable 

self-rigidizing honeycomb, one of a foamed-in-place structure and, finally, 

a telescoping structure. Each one of these types of expandable structures has 

the most potential in the areas of minimum package volume and strength fro 

weight, except the telescoping structure. Each cylinder will be pressurized 

to the cabin pressure of the MDL. An astronaut will periodically inspect the 

exterior of the structures, and will possibly cut a small segment of each 

structure out to be returned to earth for laboratory analysis. No major 

problems are anticipated in this experiment. 

Two small expandable solar collectors will also be expanded and rigidized 

in this experiment to determine the ability to form useful solar energy conversion devices in space. These solar collectors will also provide sufficient 

test data to determine the feasibility of utilizing these types of structures 

for antennae systems. One solar collector will be an expandable honeycomb 

type, while the other collector will be either a metal unfurlable or a 

SSTA-1 -9 

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Exp No. S-6 

foamed-in-place type. Such types of structures are now ready, or are nearly 

ready for space testing. It is proposed to make each item of the experiment 

a module in order that the over-all weight and package volume can he trimmed 

to meet MOL flight requirements. The priority of structures to be tested 

would be one expandable honeycomb cylinder and one expandable honeycomb or 

foam rigidized solar collector. 

a. Configuration of Test Items 

The four unexpanded cylinders will have a package volume of 4 to 5 

cu. ft. total, while the four expanded cylinders will have an expanded volume 

of 400 cu. ft. However, minimum of one honeycomb expandable cylinder and one 

expandable solar collector experiment can be conducted with a maximum weight 

of 35 pounds and 1.7 cu. ft. package volume. The total experiment weight will 

be 80 to 100 pounds. The experiment can be stowed in the unpressurized module 

of WL. Experiment requires no power except for instrumentation. 

b. Test Support Equipment Required 

(1) Spacecraft - None 

(2) AGE - None 

c. :Pest Procedure 

Man will be utilized to monitor periodically instrumentation, photograph structures during deployment and rigidization and, finally, to inspect 

exterior of structures exposed to space environment. He may also be utilized 

to remove a small piece of each structure, and bring it back to earth for 

laboratory analysis. 

SSTA-1 -9 

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Testing Sequence 

T a 0 Airmat cylinder is deployed. 

T • 10 Foamed-in-place structure deployed. 

T - 20 Foamed-in-place structure fully cured. 

T • 21 Expandable honeycomb structure deployed. 

T = 30 Telescoping structures deployed. 

T = 80 Honeycomb structure fully rigidized. 

T = 90 All three structures pressurized to cabin pressure. 

Instrumentation 

1. Temperature profile across structure every hour. 

2. Strain gage data recorded hourly. 

3. Leak rate recorded hourly. 

4. Number of leads required from inside to outside = 30. 

(This number of leads may possibly be reduced.) 

d. Category of Experiment 

Category "c", although man will be utilized considerably in the 

experiment. 

e. Cost 

Prior FY 65 FY 66 FY 67 FY 68 FY 69 TOTAL 

Engineering 

Development 

Installation 

Ground Support 

Total 

0 

0 

0 

0 

200 K 

0 

• 0 

200 K 

300 K 

0 

0 

300 K 

300 K 

30 K 

0 

330 K 

300 K 

70 K 

0 

370 K 

300 K 

0 

0 

300 K 

1,400 K 

100 K 

0 

1,500 K• 

Hitch Number: 62405334 

"Cost can be reduced if only minimum previously 

mentioned experiment is utilized. 

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f. Schedule 

(1) Hardware and software available for qualification testing, 1965. 

(2) Hardware and software flight readiness date 1966 (mid to late). 

IV. Participating Government Agencies 

Sponsor: AF Aero Propulsion Laboratory, RTD 

APFT 

Test Equipment Acquisition: APFT, WPAFB, Ohio 

V. Additional Requirements 

a. Special Security - Unclassified 

b. Manning Description Summary 

One astronaut will be required to initiate deployment of all structures, periodically monitor instrumentation, and to inspect exterior of 

structures with AMU. The astronaut will require no special skills or qualifications. His normal work position will be inside of MOL. Total man hours 

involved over a thirty day mission is 3 hours. Frequency of AMU inspection 

missions - 10 day intervals - 12 minutes each. 

c. Logistics - N/A 

d. Facilities 

The following qualification tests are considered essential to the 

over-all success of this experiment; vacuum deployment, thermal limit, 

structural testing, shake-rattle-roll, and centrifuge tests. The sponsor, 

APFT, has under it auspices all facilities necessary to conduct above tests. 

This experiment does not require man rating. 

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Exp No. S-6 

e. Simulation and Training 

(1) Astronaut: Astronaut will require no additional training, 

except for a one or two day briefing on sequence of experiment. 

(2) Ground Personnel: None required. 

(3) Equipment: None 

VI. General 

a. Communication and Data Handling Requirements 

Thermocouple monitors, strain gage monitors, and pressure leak rate 

required for instrumentation. Would prefer to time-share all instrumentation. 

Require data taking once/hour. Require 16mm movie or stop motion pictures of 

deployment and rigidization sequence. 

b. Development Characteristics 

(1) Development time 1.2 years 

(2) Final Definition Test Design Time - 8 years 

(3) Number of Ground or Flight Tests - 36 

(4) Type of Development Test Items 

a) Vacuum chamber; 3 each type = total 9 

b) Shaker - 3 total 

c) Thermal - 3 total 

d) Acoustic - 0 

e) Simulators - 0 

f) Aircraft - 3 (Zero "g" deployment) 

f) Static Testing - 3 each 

(5

) Support Equipment Development Time - None 

(6) Number of Test Articles Required for: 

a) Ground test - 18 

b) Atmospheric - 0 

c) Space tests - 3 units for M3L readiness 

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(7) Data Available for Test - 1965 

(8) Current Development Status: 

a) Project approved 

b) Funds expended to date - $900K 

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Experiment No. S-7 

ANTENNA DEPLOYMENT, ALIGNMENT AND POINTING 

I. OBJECTIVE: To deploy, align and point as necessary an antenna typical 

of those that may be employed in spaceborne high resolution radar equipments. 

DESCRIPTION: The astronaut will deploy (unfold or unfurl) an antenna 

of approximately 25 ft. in length. Studies have indicated that this is a minimum length antenna for even experimental spaceborne radar equipments. 

After deployment, the astronaut will check the alignment of the antenna and 

adjust as necessary to maintain a phase relationship of 1/8 - 1/10 wave of the 

antenna is designed for operation at X band the alignment must be maintained 

to with in .5-1 cm along the entire 25 ft. length. The alignment must be maintained inspite of the severe temperature variations that will be encountered 

as the MOL moves in and out of the earth's shadow. After alignment and at 

an appropriate time the astronaut will position the vehicle so that the antenna 

will point at a calibrated ground target range. Coherent R/F energy will be 

transmitted and the reflected energy recorded and stored aboard the MOL 

vehicle. If suitable equipments exist, data processing and signal analysis 

may be done aboard the MOL and the astronaut may adjust equipments as 

necessary to optimize or measure performance of various system components. 

III. IMPORTANCE OF TEST: 

The application of high resolution radar techniques in space reconnaissance is a tremendously complicated problem in which there are many 

scientific phenomenological and engineering unknowns. One of the chief problem areas is the antenna with many specific problem areas such as: construction, deployment, alighment, the transmission of r-f energy to the 

antenna segments, etc. It is extremely doubtful if these problem areas can 

be overcome in space without a man performing a vital role. 

IV. VEHICLE REQUIREMENTS: 

Power: 

Volume: 

Weight: 

Stabilization: 

Aperture: 

1 kw (short periods only) 

20 cu ft in spacecraft 

1000 lbs (includes extra batteries) 

05 °/Sec 

Small viewing ports for astronaut to observe antenna 

and to assess antenna adjustments 

V. SIMULATION PROGRAM: 

Pre-Phase I - None 

Phase II - Astronaut Familiarity and Practice only 

SECRET 88T 1355 -9 

I 355 

Th., desemens C00101,

11 infototohon offeshno the nohonof defense of Ilse Untted Stotts *alio% the meaning 01 the esponoee loot. 

Tate le. U S C . Section 793 and 791. the 1,00101.11.00 Of 0,11411 01 009 mann*, to on vnevlbo"ted mien •1 ptoh.b.ted by low 
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VI. EXPERIMENT DEFINITION: 

Pre-Phase I - Contractor study to determine what antenna configurations and construction techniques appear feasible for future system application. 

Phase I: The Phase I contractors will be asked to recommend and 

bid upon antennas whose general characteristics had been determined in the 

pre-phase I study. 

VII. FUNDING REQUIRED: 

Pre-Phase I $ 150 k 

Phase I $ 300 k 

VIII. PARTICIPATING AGENCIES: 

Sponsor: AFSSD/Aerospace 

Participant: RDT 

SSTA-1 -9 

356 

• 

fhb document conform inlotonotton olieetna the Rotten& tielenie 01 th• Undod Steles 0tthon the Otettnone 01 the Itononome 

Till* IS, SocIion 793 and 794. the tronsen.epen 01 eeh.en on Ony TOM& to On onewthotoged porton t, wob,boyd bi to.. 
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SECRET Experiment No. S-8 

RENDEZVOUS RADAR 

I. Test Objective 

The objective of this experiment can be broken down into the following 

basic subcategories: 

a. To evaluate the components and overall performance of precision radars 

designed for spaceborne operation in both cooperative and non-cooperatiie 

modes. 

b. To measure the effects of target motion and scintillation during 

close-in tracking. These measurements will establish a requirement on or 

for terminal guidance in vehicles designed to station-keep or dock with 

uncooperative or inoperative satellites. 

c. To test and evaluate the radar as an auxiliary, or emergency space 

navigation sensor using the radar as an altimeter and in conjunction with 

earth transponder beacons. 

d. To test and evaluate the radar as an emergency communication device 

for space/ground or space/space communications. 

e. Test and evaluate the role of man during terminal acquisition and 

honing and determine his advantages, disadvantages or best role as a 

controlling device during the terminal rendezvous maneuver. 

II. Importance of the Test 

Presently there exists no space qualified radars that viii operate in the 

cooperative and non-cooperative modes. Since this system will become a primary 

development and test item for any future space mission requiring rendezvous 

(inspection, resupply, rescue, etc.) the present experiment will not only 

carefully define the radars capabilities, with or without man, but will also 

cut down future costs or lead times in operational hardware development. 

FUrthermore, the MOL offers the unique advantages of man/unmanned operation 

and maneuverable targets like Gemini or the GTV which can operate in the 

cooperative or noncooperative modes. Since the MOL is also a precisely 

tracked test vehicle baying man aboard, the full capability of the precision 

radar as a self-contained navigation and emergency communication/command 

device can be determined. 

SECRET SSTA-1 -9 

357 

docvnient contains information *Resting Ow retie'sl detente of the United States within the evening of the Espionage Sews, Title 

Ig. U s c sw,on 793 and 791. the transmission Of reselotien of which in any nia,Ine, to an i.insethorised person Is prohibited by law. 
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Exp No. S-8 SECRET 

III. Description of the Experiment 

a. Configuration of Test Items: 

(1) Radar: Characteristics of this equipment will depend on the 

selected design, but the basic radar should have the capability to provide 

range and angle data (with associated rates)from 100 nm to 30 feet or less!' 

against an uncooperative target of 1 or 2 square meters in cross section. 

Electrical characteristics (PRF, frequency, wave form, etc.) should be 

tailored to optimize the MOL mission after definition studies. The radar 

should include provisions to operate with a matched transponder for 

cooperative tracking of ground and satellite beacons and be capable of 

complete manual or_automatic control by the astronaut. A secondary mode 

should be provided for tracking at ranges below 2000 ft. 

For planning purposes the following physical characteristics should 

be considered representative: 

(a) Weight 300 lbs 

(b) Input power - 1800 watts primary mode, 50 watts secondary 

mode 

Antenna - 5 ft parabolic 

d Volume - 4 ft3 stowed -20 ft3 with antenna erected. 

(2) Target: The target should be either a Gemini vehicle or a 

GTV, so that cooperative and non-cooperative operation can be tested and 

compared. Target and/or MOL maneuverability will be required to complete 

the rendezvous maneuvers. 

(3) Associated Flight Equipment: A control and display console will 

be required for complete manual control and adjustment by the astronaut. 

Beacons and radar matched communications electronics will be required at the 

MOL.tracking sites for the navigation and communications tests. 

(4) AGE: Standard functional check equipment will be required for 

factory and launch facility installation. 

b. Once the MOL is manned, all aspects of the experiment can be started 

in an order that best suits the planned mission profile. The following test 

series indicates the test content only and not an established priority. 

During the first several orbits, the radar is warmed up and 

interrogates known ground transponders providing range, range rate, lineof-sight, LOS rate, and orbit altitude data to both man and computer. The 

results of the on-board computer calculations are then compared with ground 

SSTA -1-9 

358 SECRET 

This deo/moot contains Informsticot •i.ctinq the national defense of the United Pon within the meaning of the Isplonecie tsars. Title 

111, U.S.C., Soctlon 793 and 794, the frintrnIssion or revelation of which in any manner to an unouthorlied parson Is prohibited by law. 
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Exp No. S-8 

ephemeris. Mans calculations,along with attitude references gained from 

computed position and sequential transponder readings, could also establish 

the applicability of using the radar as an emergency positioning and re-entry 

system. 

The next sequence will be established during the first rendezvous. 

If the target is a Gemini vehicle or or GTV, tracking should be established 

alternately in the cooperative and uncooperative modes. down to a distance 

of 5000 feet. At this time tracking should be switched to the uncooperative 

mode and rendezvous (to docking if possible) completed. The effects of 

scintillation can be ascertained and corrected for during the latter terminal 

stages. The results of this sequence will definitely establish the value of 

man for rendezvous and/or docking, and will establish the feasibility, limits 

and/or penalties to be expected by automatic operation. 

At a time ccmpatible with crew duty and mission profile the emergency 

communications experiment can be completed. For purposes of this experiment 

space/ground communications should suffice. The astronaut should place the 

radar in the manual search mode and attempt to orient the antenna toward the 

known ground site. Continuous antenna reorientation will be required during 

the length of the transmissions. The manually controlled radar transmitter 

then transmits the required information in a mode most adaptable to wave 

form characteristics and design. Changes in PRF, frequency, and duty cycle, 

or amplitude modulation are possibilities to be considered in coding the 

communication. Reception can be obtained by manual control over the nominal 

transmit-receive sequence, causing continuous receiver operation. Auxiliary 

electronics will convert the received signal to audio or visual displays 

required by the astronaut. 

c. Category of Experiment: The radar and associated controls are 

category "a" equipment and will dictate part of the MOL vehicle design. 

Allowances will have to be made for the large weight, and the large stowable 

antenna. The antenna should be placed to give maximum view, both in azimuth 

and elevation when erected, and allowances made for the antenna dynamics, 

inertias, and alignment accuracies. 

From an operational standpoint remote control is acceptable but inflight maintenance may be required on the electronics making accessability 

advisable. 

d. Cost (for k units and AGE) 

Prior FY 65 FY 66 FY 67 FY 68 TOTAL 

1. mgr & Dev Unk 1.0 -TV- - 7.0 

2. Installation .3 .5 .3 1.1 

3. Ground Support 0.05 .15 .20 

SECRET SSTA -1-9 

359 

This document contains information affecting the nstlenal defense of die United Motes within lie meaning of the Ssploneoe taws, Sm. 

IS, U.S C., Searan 193 and 194, the transmission or revelation of which In ony men... town oneythotIsed person Is prohibited by law. 
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Exp No. S-8 -SECRETe. Schedule: (Assuming 1 Jul 64 start) 

Hardware available for test - July 1966 

Hardware flight readiness date - August 1967 

IV. Participating Government Agencies 

SSD/Aerospace 

Participant: RTD 

V. Additional Requirements: 

a. Special Security - None. 

b. Manning Description Summary - Only one man will be necessary for the 

space operations. He should be completely familiar with the equipment and 

its operation so that in-flight maintenance can be performed. Ground test 

support forces should be supplied mainly from contractor resources. Operational ground support for beacon tracking and communications should be 

satisfied by the manpower of existing tracking facilities. 

c. Logistics - No special logistics requirements exist since the 

contractor vill supply all hardware for flight, test and maintenance. The 

addition of this experiment will not impose additional logistics requirements 

to those already existing for tracking and communicating with the MOL 

vehicle. 

d. Facilities - No special facilities will be required. 

e. Simulation and Training - 

(1) Astronaut 

The astronaut should have a background in electronics and 

OJT at the contractor's plait for at least four months. Complete knowledge 

of the operation, adjustment and maintenance of the system is mandatory. 

(2) Ground Personnel - 

No special requirements exist as this support should come from 

contractor resources. 

(3) Equipment 

No special equipment will be needed for flight or ground 

personnel. 

SSTA-1-9 

360 

This document contains Information ofiectIng the natIonel detente of the United State. within the ',leonine of the tsplonoeo toms, Title 

IS, U.S.C., Salon 79'3 end 791, the 114Argnirsion or ryuytorion of whirls in any mannin to an unauthorized person Is prohibited by low. 
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-SECRE-Tr- Exp No. S-8 

VI General. 

Development Characteristics: Oboe the MOL mission profile, target type, 

and this experiment are defined, a normal development cycle should lead to 

hardware tailored to fit the job. No particular problems are to be expected 

unless ranges of over 100 NM are required in the non-cooperative mode. 

SECRET SSTA -1-9 361 

Shit docerneni conteins information effecting Ih• eational defense •1 the United Itetos within tItti 'whining of Ilet Ispitenege tows, Title 

18, Sortion 793 and 794, tha irenunittion or revelation .1 which In any manner to en unauthorised person Is prohibited by leer. 
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Exp No. S-8 SECRET 

ATTACHMENT A 

DESIGN CHARACur.RISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED: Spaceborne radar detection and tracking system. 

2. WEIGHT: 300 lbs 

3. VOLUME: Stored - 4 ft3. In use -20ft3 (antenna erected externally). 

4. CRITICAL DIMENSIONS - SHAPES 5 ft parabolic antenna in both stowed 

and extended configuration. _ 

4. POWER: 

Continuous - N/A 

Standby - 300 watts 

Average Operating - 1800 watts primary; 50 watts secondary 

Peak - N/A 

Duty Cycle - N/A 

5. SPARES: 

Volume - To be determined 

Quantity - To be determined 

Weight - To be determined 

6. TOOLS: 

Volume - To be determined 

Quadity - To be determined 

Weight - To be determined 

Power - To be determined 

7. HEAT OUTPUT - approximately 1300 watts during primary mode operation 

8. STABILITY: 

Moving parts - Massive antenna will be in motion during search mode 

producing torques on host vehicle 

9. VIBRATION LIMITS: None - can be built to stand expected environment 

10. SHOCK LIMITS: None - can be built to stand expected environment 

11. HAZARDS - Hi voltage 

SSTA-1-9 

362 SECRET 

This docotnent contains informstion enacting the national de ***** the UMW Stites within the theitnino of the Espionage Sews, Mi. 

I a, U.S.C., Section 793 end 794, the rronsmission or rovolation of ...hick In any mower to an so...whorled person is prohibited by law. 
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-SECRET-- Exp No. S-8 

12. TEMPERATURE LIMITATIONS: Will require active cooling if operated for more 

than 30-45 minutes in primary mode without a 3 or 

4 hour cooling period. 

13• TYPE AND RANGE OF WASUREMENT: Range and angle to target from 100 NM to 

30 ft. Range and angle rate can also be 

obtained if required. 

14. SPECIAL ENVIRONMENTAL REVIRFMENTS: Extreme precautions against RFI/EMI 

should be-taken during design and 

integration. 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: 

Precise alignment of antenna is required in all three axis. 

16. EQUIPMENT OPERATING CYCLE: 

Frequency - To be determined 

Time Duration - To be determined 

17. EQUIPMENT LOCATION REQUIREMENTS - Antenna should be positioned to provide 

minimum obstruction to view in both 

azimuth and elevation. 

113. SPECIAL MOUNTINGS REQUIREMENTS: 

Antenna - May require extendable or foldable boom to position antenna 

to the operating configuration. Mountings, brackets, and etc will 

have to handle a dynamic 5 ft diameter parabolic antenna and still 

maintain precise alignment accuracies. 

19. PRESSURE VESSELS - fluids, gasses, etc. N/A 

20. ELECTRO MAGNETIC INTERFERENCE (spurious generation, special shielding 

req, etc.) 

Special shielding, isolation and all other precautions are required to 

prevent EMI emanations. 

21. MAINTENANCE REQUIREMENTS: 

Ground - Factory only. Calibration, alignment and checkout can be done 

in the field. 

Space - Modular change of electronics and calibration only. 

SECRET SSTA-1 -9 

363 

This docomoht contains infoohotion *Mooing rho notions! &time of it.. Ltoltod Stem within rho owning of tho flpionoge lows, TM. 

Saction 797 and 791, Ma transmission or rovalation of which in any marmot to on onouthotItod porton is prohlbitod by low. 
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Exp No. S-8 

ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. RECORDIN3 MEDIA: 

a. Tape - To be determined 

b. Film - To be determined 

c. Other - N/A 

2. HANDLING: Special dolly required for ease in handling. 

3. PACKAGING: Standard MIL Spec requirements are sufficient. 

11. CALIBRATION - alignment, deployment: Flight control console should contain 

controls for in-flight calibration; AGE and factory test 

equipment for ground operations. 

5. JIGS AND FIXTURES: None 

6. NUMBER OF LEADS FROM OUTSIDE TO. INSIDE STATION: Approximately 6 

7. SENSORS (Transducer - Output Signals): To be determined 

8. TRAINERS/SIMULATORS: N/A 

9. INSTRUMENTATICH - cockpit and/or laboratory(note effect of time sharing 

instruments with other experiments.): A full control console should be 

provided to allow monitoring in the automatic mode, and operation in 

the manual mode. 

10. RELATED SUPPORT EQUIPMENT: 

a. Targets - Anechoic chambers required for ground test in active mode. 

- A Gemini or GTV is required for flight tests. 

b. Ground Stations - Should be equipped with transponders and receivers/ 

transmitters compatible with the radar system. 

c. Tracking - N/A 

d. Handling Equipment - N/A 

11. AGE: Standard contractor supplied AGE will be required for ground checkout and maintenance. 

12. ENVIIONMENTAL TEST EQUIPMENT: Standard chambers and shakers available 

at contractors facilities are sufficient. 

13. FACILITIES: No special facilities required. 

SS TA -1 -9 

364 -SECRET-- 

This docornent contains intonnation dialing the nations! defense of the United States within the meaning of the Esplanade taws. title 

U.S.C.. Section 793 and 794, the transmission or revelation of which in any manner lo an vnawthorized pitman if prohibited by law. 
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RELEASE 1 JULY 2015 

Exp No. S-8 

ATTACHMENT C 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired): 

a. Altitude • To be determined 

b. Inclincation - To be determined 

c. Epoch - To be determined 

d. Ellipticity - To be determined 

2. PLANE CHANGE - N/A 

3. ALTITUDE CHANGE - N/A 

4. TIME ON ORBIT - To be determined 

5. TEST DURATION - To be determined 

6. TOTAL NUMBER OF TESTS - To be determined 

7. TEST FREQUENCY - N/A 

8. INTERVAL BETWEEN TESTS - To be determined 

9. CREW TASK LOADS - man hours - To be determined 

10. CREW TASK FREQUENCY - To be determined 

11. FIELD OF VIM REQUIREMENTS - Antenna should be mounted to provide minimum 

obstruction to view in both azimuth and 

elevatidn. 

12. GROUND CONTROL LIAISON DURATION - To be determined 

13. GROUND CONTROL LIAISON FREQUENCY - To be determined 

14. EXTERNAL TEST ITEMS: 

a. Launched from station - None 

b. Launched from Resupply - None 

c. Launched from ground Gemini or GTV targets 

15. QUALIFICATION TESTS (other than space) 

a. Ground - To be determined 

b. Atmosphere - N/A 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT - To be determined 

17. HANDLING PROCEDURES - To be determined 

SSTA -1 -9 

365 

This document contains Information &Etienne Mil n111109•1 009949 el if* UMW States within Me ineehing of Me Espionage laws, Lips 

IS. Section 793 and 794, tM tronsonission or reeelation of which In one manner to an onavilmriaed person Is prcAtigited by 
Integration& Installation 

Simulators/Trainera 

DataReduction 

Qg

C 

Other(Ground beacons,etc) 

Exp No. S.-8 

ri 

SSTA-1-9 

366 

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RELEASE 1 JULY 2015 

Exp No. S-8 

ATTACHMENT E 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required: One required 

(1) Man's function 

(a) As part of teat: Operates system in manual control during 

space positioning, emergency communication, and rendezvous sequence a. 

(b) As technician osnductiag test: Monitors automatic control 

and provides maintenance. 

b. Crew skill requirements: Background in electronics and 4 months 

OJT at contractor's plant required. 

c. Manpower profile: To be determined 

d. Critical functions: to be determined 

e. fork positions: Remote control is acceptable except for maintenance 

which requires accessibility to electronics. 

f. Time controlled tasks: to be determined 

g. Human performance measures: Comparisons of manual and automatic 

performance during rendezvous. Parameters are time and velocity required 

for completion 

h. Physiological and psychological measures: To be determined 

i. Selection factors: See lb above 

j. Training requirements: See lb above 

2. GROUND PERSONNEL 

Number required: To be determined 

SECRET SSTA-1-9 

367 

this document contains information enacting the 'Wiens! defense of the United Sleet within the meaning of the Espionage laws, title 

TB U 5 C Sect.00 793 end 79d. the transmission or fOvilet;en of which in any manner to en uoeuthorized person is prohibited by law. 
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ATTACHMENT F 

COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE: To be.determined 

2. FUNCTIONS TO BE MEASURED: To be determined 

3. TYPE OF ANALYSIS REQUIRED: To be determined 

4. PICTORIAL DATA REQUIRED: Target position vereue time at rangee of 

2,000 feet to rendezvous. 

5. REAL TIME MONITORING REQUIREMENT: N/A 

6. DATA EDITING OR COMPRESSION: N/A 

7. READ-OUT TIME: To be determined 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS: To be determined 

9. MANUAL AND/OR AUTOMATIC CONTROL: To be determined 

10. SIMULTANEITY: N/A 

11. GROUND COMMANDS REQUIRED: To be determined 

SSTA -1 -9 

368 SECRET 

MisAw.m.mommInsWommlonaleolololvonokiml 41•1400 el Oa UMW SIMI with* ft *Nab% Si the Ilsolorogs taw% Mill. 

19, SO{Ii0I1 M eed 794, the trsosenisskto reyeletloo of which In any rallaflit 111 M1 IA&01101111141 person Is prohibited by taw. 
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Exp No. S-8 

ATTACHMENT G 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME: 37 months from start 

2. FINAL DEFINITIVE TEST DESIGN TIME: To be determined 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED: Two units should be ground 

tested and one flight tested. 

4. TYPE OF DEVELOPMENT TEST ITEMS: 

a. Vacuum Chamber 

b. Shaker 

To be determined - Standard contractor test 

c. Thermal facility now in existence should suffice. 

d. Acoustic 

e. Simulators - N/A 

f. Aircraft - N/A 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME: 12 months from start 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test: Two 

b. Atmospheric Test: N/A 

c. Space Test: Two (one as flight back up) 

7. DATE AVAILABLE FOR TESTS: August, 1967 

8. CURRENT DEVELOPMENT STATUS: All components and techniques have been 

previously developed. 

SECRET SSTA -1-9 369/370 

this document contains information affecting the national Mena of the United Stoles within Me meaning of the Ispi 00000 LIMO, Till. 

U.S.C., Section 793 and 794, the 1,11.11,111110A Of revolatten of which in .ny manner to .n unsotherized person Is prohibited by taw. 
NRO APPROVED FOR 

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--SECRET- Experiment No. S-9 

MANUALLY CONTROLLED TV AND ORBITAL INSPECTION 

PHOTOGRAPHY OF EXTRAVEHICULAR OBJECTS 

I. Test Objectives: 

Primary: a. Evaluation of man's ability to select and control in 

space photographic conditions to obtain best photographs of all target 

aspects under varying orbital lighting conditions without use of artificial 

illumination, (i.e., obtain target details in deep sun Shadow areas utilizing 

available earth shine), 

- b. Evaluation of man's ability to make on the spot evaluations cA electronically displayed photographic results for selection of 

best photographs for electronic transmission to ground stations and/or 

reprogramming of camera controls and photographic geometry for optimum 

natural illumination conditions. 

Secondary: a. Evaluation of the relationships between the electronic 

transmission of photographs to a central control station for further 

interpretation and the ability of a central control station to direct 

and/or control photographic conditions of either manned or unmanned rendezvous inspections. 

b. The collection of both space taken photographs and their 

electronic transmitted reproductions as intelligence background data for use 

in either the interpretation of future satellite inspection photographs or 

to refine future photographic equipment and transmission performance specifications to satisfy image quality needs for intelligence interpretation. 

c. The evaluation and/or use of a prototype rendezvous 

inspection photographic sensor as supplementary MOL equipment for the 

permanent photographic recording of extravehicular experiments, rendezvous 

operations, and man's extravehicular activity with nearby or tether experimental objects. 

II. Importance of Test: 

This test will provide the data required to establish the operational 

and equipment limitations of unmanned versus manned rendezvous inspection 

photography. The dual lens camera concept with simultaneous image recording 

on alternate frames of the same roll of film is intended to provide maximum 

operational capability in a minimum equipment package. It also contains in 

the same unit film development and electronic readout of the developed film. 

Camera coverage consists of a 40' field of view with target resolution 

at 2,000 ft. and a central 8.5* field of view with resolution at 2,000 

ft. Intended to work with this unit is a TV camera utilizing a sec-vidicon 

in conjunction with a turret lens and an 0.6 microsecond pulse illumination 

-SECRET- SSTA -1 -9 

371 

71, dot.otnent contains •nlottnenon antchno the n•nonal Oen,. ea oho Untied Slants within the rn••ntrt9 of lb. Ispionege 111111 

IC II ( ,.0.% 7C,7 44"I 191 the tra,tn.7s.on a. ........or. yl adnah in an, manner to an oneothot.aect ',erten ta otol,toted by tyyy 
NRO APPROVED FOR 

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Exp No. S-9 SECRET 

unit for nighttime operation. Manual control of actual picture taking iv 

accomplished by means of viewing the TV monitor. However, the revolution 

capability of the TV monitor is much less resulting in less intelligence 

detail than that obtained with the photographic unit. The full operational 

significance and limitations of this capability will be established by this 

experiment. In addition, it will provide experimental evidence of man's 

capability to receive, process, and evaluate information and then make command 

decisions during satellite inspection on what courses of action to take while 

in a space environment. This experiment will also provide actual data to 

determine the required in-space performance necessary to produce photographs 

containing significant detail for use in intelligence interpretation. As a 

result this experiment will be simultaneously accumulating intelligence 

background data on satellite inspection activities. 

III. Description of the Experimrnt: 

Normally, in an actual inspection vehicle this combination of photographic 

unit and TV camera-illuminator would be in a body fixed mounting located in 

an unpressurized area with aperatures for the required fields of view. This 

experiment, however, contemplates the use of prototype inspection equipment 

as a supplemental TV monitor and photographic recorder for other extravehicular experiments. As such it requires consideration of a more flexible 

mounting within MOL. The devices could be stored in the work area during 

ascent to orbit. Once in orbit the devices could then be mounted on an 

extension protruding from the MOL vehicle. The desirability of manual 

assembly or automatic self-erection of the extension as an expanding boom 

is yet to be determined. The extension would hold the TV camera and photographic unit away from the vehicle and allow orientation of its field of 

view toward the experimental area of interest. Electrical control of mounting platforms orientation in elevation and azimuth with respect to the MOL 

vehicle is desirable. Controls and visual display equipment would be located 

in the pressurized area. Direct viewing for visual monitoring from the 

pressurized vehicle is desirable to allow simultaneous visual observation 

of both the equipment and the extravehicular experimental area. 

The equipment would be first checked out operationally by taking photographs of the MOL vehicular extremities and viewing the processed film 

frames on the electronic readout display. Fifteen minutes of film processing 

time is required after picture taking before photographic readout can be 

initiated. This experiment would then be conducted in conjunction with 

other extravehicular experiments and consist of an astronaut utilizing the 

equipment to monitor and record the experiments. Prime interest lies in 

photographic recording of the following experiments: (1) decoy deployment, 

(2) experiments and activities with a remote maneuvering unit, (3) MOL 

rendezvous experiments concerning simulated or actual resupply, fuel 

transfer, space rescue, and/or docking, (4) an inspection oriented MOL 

rendezvous experiment with either another in-space operating MOL or 

SSTA -1 -9 

372 SECRET 

This doewhent toeta:ns infoentvion afl ectan9 the nefienel do ,•..• of she United States within the moaning 01 the tsponne laws. TWO 

18 U 5 C . Secv.., 793 eed 794. .he on 97 ih any manner tO an unau,horiled 0e7son .1 ohah;b•ted by le. 
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SECRET Exp No. S-9 

previously expended MOL section. These other experiments would be partially 

modified in procedure to allow favorable orientation of the camera, experimental objects, sun, and earth shine to effect inspection simulation while 

monitoring and recording the conduct of the experiments. Provisions will 

have to be made to allow in-orbit realignment of the geometric relationships 

between the camera, experimental objects, and natural illumination. The 

determination of the required in-orbit realignment would be made by the MOL 

crew in conjunction with the ground control station after evaluation of the 

electronic displays of the photographic images. Continual analysis by the 

ground control station would provide the MOL crew with instructions for 

appropriate realignment and/or procedure modification of succeeding tests. 

This would effect minimum interference with the conduct of the extravehicular experiments and yet provide maximum data for this experiment. It 

is recognized that it is possible to adapt existing off-the-shelf photographic 

units, TV cameras, and illuminator units to accomplish the experiment observation function for a particular MOL station. However, although these equipments 

with their limited performance may fill MOL's immediate observation requirements, they generally would be heavy, unreliable and too limited in performance 

capability for ensuing military space missions. Since the development lead 

time requirements of this proposed equipment is timely to MOL, it is proposed 

that, to achieve the maximum return on our investment, preference be given 

to the development and utilization of this equipment on MOL. 

a. Configuration of Test Items 

The nature of this experiment is such that the equipment items can 

serve a dual function, i.e., obtain data for this experiment and also 

provide photographic coverage of other extravehicular MOL experiments. 

Consequently, the ascent storage location in MOL as well as the assembled 

external location will be of prime concern in the design of a particular 

MOL station. Known data regarding the equipment elements is included in 

Attachment A. However, a study will be required to determine which MOL 

flights the equipment would go on, its impact upon and relationship with 

the other planned experiments, which flights require the extension platform 

versus simple exterior mounting, and/or the advisability of rendezvous with 

a previously expended MOL section for removal and utilization of equipments 

such as this photographic unit, TV camera unit and boom extension. 

b. Test Supoort Equipment Required 

Known details are included in Attachment B. 

c. Test Procedure 

Since this experiment is dependent on other on-board extravehicular 

experiments, detailed procedures cannot be described until it is decided to 

SSTA-1 -9 

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This document contains informal on .Hotting IM nolonsl &tints of the tOollod SIMI within ttio moaning of the hplimn. Saw', 11th 

It u S C.. Symms 793 and 704, the transmission or revelation of which In any manna to on unowthoriced person It prohibited by law. 
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include and and integrate it into a particular MOL flight. Then the procedures 

for other planned experiments can be reviewed and appropriately modified 

to meet the objectives of this experiment. The desired results will evolve 

from ground analysis of the transmitted images, in-flight photographic 

conditions, and the recovered film. Aa a consequence, the desired results 

do not depend upon the specific procedures employed to obtain pictures but 

depend upon the objects within camera fields of view and the geometric 

relationships of the natural illumination at the time of photography. It 

is anticipated that the required equipment for this experiment will become 

part of MOL crews experiment observation and recording equipment. Therefore, 

experience of the crew in taking and reviewing the on-board photographs may 

dictate modifications in planned procedures and timing of the other experiments in order to obtain the best photographic recording and observation 

conditioning for the experiments. 

d. Category of Experiment 

This experiment is considered to be in Category A. It affects the 

capability of MOLts photographic recording and monitoring of extravehicular experiments. It requires the MOL vehicle design to include 

provisions for internal storage during ascent of exterior mounted equipment 

elements which are later assembled in orbit by the MOL crew and attached 

to the MOL. Particular attention to the electrical connectors for vacuum 

plug in as well as methods of applying power to exterior plugs will be 

required. 

e. Costs and Schedules 

Engineering development of the inspection photographic unit and 

the associated inspection TV camera with its nighttime illuminator requires 

a forty (40) month lead time for both items. If go-ahead is given by 

August 1964, then the first flight units could be delivered for installation on a MOL station by April 1967 for the TV camera and illuminator and 

by July 1967 for the photographic unit. Available data on costs and 

schedules: (6 flight units) 

Photographic Unit FY 65 FY66 FY FY68 

Eng & Devel 

Installation See Attachment D 

Ground Support 

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this dotvment contains Information allotting the national d I the United Slates within the meaning of the isgloneoe taws, fill. 

U.S.C., Section 793 and 794, the transmission or revelation of which In any manner to in stheethorlsed person It prohibited by law. 
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SECRET- Edcp No. S-9 

TV Camera and IlluminRtor FY 65 FY 66 FY 67 FY 68 

Eng & Development $375,000 $555,000 $8k9,000 $75,000 

Installation To be determined in relation to MOL. 

Ground Support To be determined in relation to MOL, 3 sets 

of aerospace ground equipment are included 

in the engineering and development cost 

figures. 

IV. Participating Government Agencies: 

Sponsor - SSD 

Participant: RTD 

Test Equipment Acquisition - SSD 

V. Additional Requirements: 

a. Special Security - To be specified. 

b. Manning Description Summary - To be specified. 

c. logistics - To be determined. 

d. Facilities - To be determined. 

e. Simulation and Training - 

(1) Astronaut: Should be trained as technician to operate the 

equipment but must be given scientific training in photography and illumination effects as veil as photo interpretation. Simulation of equipment 

control and extra-vehicular experiment control in a MOLdmulator will be 

highly desirable. Need to develop astronaut skills in his ability to 

simultaneously observe, record, and control planned extra-vehicular experiments, when conceivable malfunctions and erratic experiment conditions 

occur, such as drifting equipment, meteorite impacts, sunlight to earth 

shadow traversals, and/or miscellaneous power fluctuations or failures. 

(2) Ground Personnel: Training in equipment checkout, photointerpretation of transmitted results, ground command of automatic equipment operation, i.e., for advising astronaut and simulating ground 

command control -of unmanned rendezvous inspection conditions. 

(3) Equipment: To be determined. 

SSTA -1 -9 

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cont.;n, alilectino rho national detente el h. United Staiot within the meaning of the tiPehail• Laws, rm. 

u s c., 3.ocrion 703 and 794, rho tronvnitsion or revolnlion of which in any mann., 10 an unautherited person is prohibited by law. 
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Exp No. S-9 -SECRETVI. General: 

a. Communications and Data Handling - To be determined for maximum 

evaluation of the control of manned and unmanned rendezvous inspection 

capabilities. 

b. Development Characteristics - To be determined to establish 

compatibility between MOL and the rendezvous inspection sensor package 

Advance Technology Development Progrma. • 

SSTA-1-9 

376 -SECRETThis does...need contains InfOrmetion aflettinp the motional defense •f the United States within the meaning of the tape law.. Title 

Is, u.S.G.. Section 793 and 794, the transmission or revelation of which In any wanner to en onaothorised person Is prohibited by law. 
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SECRET- Exp No. S-9 

ATTACHMENT A 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. DQUIPMENT TO BE TESTED: Dual lens rendezvous inspection camera with 

electronic film readout and inspection TV 

camera with illuminator. 

2. WEIGHT: Photographic unit - 175 lbs 

TV camera 35 lbs 

TV illuminator 75 lbs 

Extension platform - 80 lbs 

Display and controls - J lbs 

Total - 395 lbs 

3. VOLUME: 

Stored In Use • 

Interior Exterior 

Photographic unit 5.0 ft3 1•1 5.0 ft., 

TV camera 0.2 ft3 el MD • 0.2 ft-2 

TV illuminator 1.6 ft3 1.6 ft3 

Extension platform 3.0 ft3 3.o ft3 

4 Display and Controls 1.5 ft3 1.5 ft3 =7 Total 11.3 T.15-CC3 9.8 ft4. POWER: 

a. Continuous - To be determined for temperature control requirements. 

b. Standby - To be determined. 

c. Average operating - 285 watts. 

d. Peak - 380 watts. 

e. Duty cycle - To be determined, may depend pritarily on operator 

control and related extra-vehicular experiments or 

objects to be photographed. 

5. SPARES: 

a. 4 film refills: Volume 2 ft3 

Weight 60 lbs 

b. Miscellaneous: Volume 1 ft, 

Weight 30 lbs 

6. Tools: 

Assembly, film refill' Volume 2 ft3 

and minor repair: Weight 30 lbs 

-SECRET-- 

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Thic poc,e, coetoiwtmformation seycling the national Patens* of the United 31ohts within Mg mooning of the Espionage laws, 7111. 

U.S.C., Smtion 793 ...d 794, the hoesmissiett or ,..Allen of which in any manner to an tonautherlsed omen Is prehlbilod by low. 
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7. HEAT OUTPUT: To be determined. 

8. STABILITY: Requirements for controllable platform to be determined. 

9. VIBRATION LIMITS: To be determined. 

10. SHOCK LIMITS: To be determined. 

•■•••••• 

11. HAZARDS: To be determined concerning film processing unit and its 

refill as well as external inflight electrical connections. 

12. TEMPERATURE LIMITATIONS: To be determined. 

13. TYPE AND RANGE OF MEASUREMENT: Photographic unit-temperatures, pressure, 

and processing chamber humidity; go no-go 

indicators on shutter mechanisms, film 

advance and take-up, readout mechanisms, 

and readout section BIMAT sticking or 

jam. The interior film readout display 

is the primary use item for photographic 

quality evaluation. 

14. SPECIAL ENVIRONMENT REQUIREMENTS: To be determined, none expected. 

15. ORIENTATION AND POSITION ACCURACY REQUIRFWATS: 

a. Station - .016 radian/sec max. tolerable angular velocity during 

picture taking. 

b. Equipment - Astronaut control of field-of-view pointing. 

16. EQUIPMENT OPERATING CYCLE: As determined by operator control. 

17. EQUIPMENT LOCATION REQUIREMS: 

The external mounting plate or extension boom and platform should be 

located such that (1) direct viewing of both the equipment and extravehicular experiment area is possible from the pressurized control area, 

(2) the MOL's TV monitoring camera can be also mounted on same platform, 

(3) at least one extremity of MOL vehicle can be photographed. 

18. Special mountings requirements: A specially designed equipment and/or 

boom extension mounting plate on MOL's exterior is required to allow 

in orbit assembly and electrical connection. 

19. PRESSURE VESSELS: To be determined, none expected. 

20. ELECTRO MAGNETIC INTERFERENCE: To be determined. 

21. MAINTENANCE REQUIREMENTS: Ground - To be determined; Space - To be 

determined. 

SSTA-1 -9 

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This &aperient contains Information electing the nationat d 1 the United States within the meaning el the Espionage Law', Title 

II, U.S.C., Section 793 and 794, Po trensmIssion Of tevetelkol of which In any mintier to M oriewhorIged person Is prohibited by few. 
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SECRET Exp No. S-9 

ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA: 

a. Tape . Video tape for temporary storage of several frames of both 

the electronic film readout pictures and selected TV imaging. 

Capability of transmission from tape to ground stations is 

required in the event of photographic unit malfunction or 

BIMAT sticking to film prevents recycling of picture readout.• 

Temporary storage of units temperature and pressure reading 

is desirable. 

b. Film - To be determined, possibly film recording of TV images. 

c. Other - 

2. HANDLING - To be determined. 

3. PACKAGING - To be determined, expect special tie down and possible shock 

absorption pad for ascent to orbit. 

4. CALIBRATION - Field-of-view alignment with adjacent TV monitoring camera 

may be required. 

5. JIGS AND FIXTURES - To be determined. 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION - To be determined. 

7. SENOORS - To be determined. 

8. TRAINERS/SIMULATORS - To be determined. 

9. INSTRUM]NTATION - To be determined. 

10. RFIATED CUPPORT EQUIPMENT: 

a. Targets - 1 decoy minimum, others to consist of planned extravehicular experiments, plus a photographic test target 

consisting of a corner reflector with detailed designs 

on it. 

b. Ground station - To be determined, none expected. 

c. Tracking - Line-of-sight and range information needed from MOL 

on-board equipment. 

d. Handling Equipment - To be determined, as concerns resupplying 

film to the photographic unit, and recovery 

of film at the termination of the MOL flight. 

SSTA -1-9 

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This elect/them catteles inlorthetion dittoing the national detente of the Unites, S within Oho mooning et the IsthonsOts Lew*, Title 

111. U.S.C., Socha. 7,3 and 791, the owsreitsioe or revelation of whish in any manner to an wwethorited person Is prohibited by tow. 
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Exp No. S-9 

11. AGE - To be determined. 

12. ENVIRONMENTAL TEST A space simulation chamber for operational ground 

test of assembled extension boom platform, visible 

TV camera unit and photographic Lit. Primary 

concern is vacuum and thermal effects on photographic 

unit and the controllable platform. 

13• FACILITIES - To be determined. 

SSTA -1-9 

380 SECRET 

mla devonont contains Inforrnohyn effecting thy nallenal defame el the fnMtsd SIMI within th4 moaning of the holawit taws, TIII• 

U.S.C., Section 793 and 794, the trenunission or revelation of which In any wow.., 10 on unavilwolz.41 pmon Is prehrbbeel by law. 
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-SEGREfExp No. 3-9 

ATTACHMENT D (Revised) 

(Photography - TV Manually Controlled) 

Cost Data 

Dual Lens Camera with Readout 

(K $1,000.00) 

1761 FY 66 F1_62 FY 68 

Phase I 275K 

Phase II 

RTDE 1,200K 2,510K 1,540K 

AGE 70K 690K 760K 

lst flight unit 830K, 

1,545K 3,200K 3,130K 

Additional Fit Units 

2nd —222E 60K 

1,630K WC 

3rd 

4th 375K WI 

4,005K 245K 

5th_ 695. 

805K 

bth 560K 

1,365K 

SSTA-1-9 

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CONFIDENTIAL 

Exp No. S-9 

ATTACHMENT D (Revised) 

(Photography - TV Manually Controlled) 

Cost Data 

SEC Vidioon TV and Pulsed TV Illuminator 

(K •• $1,000.00) 

FY 65 FY 66 562 FY 68 

Phase I 300K 

Phase II 

RTDE 285K 825K 4.15K 

AGE 116K 84K 

1st flight unit ,.MC., 

5851 9 4 3. K 6 4 9 lc 

2nd ELK 

774K 

3rd _ZOK 

844K 

4th 1.251 

180K 

5th 1221 

305K 

6th 430K 

CONFIDENTIAL SSTA-1 -9 

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Exp No. S-9 --COWIDE4RIAL-- 

ATTACHMENT D (Revised) 

COST DATA 

FLIGHT CONTROL CONSOLE FOR TV CONTROL= PHOTOGRAPHY 

(K i• $1,000.00) 

nal FT 66 Fir 67 irr 68 

Phase I 150K 

Phase II 

RTDE 

lst flight unit 

TOTAL 

680K 420K vol 

150K UZI 690K 

100K 

790K 

box kas 

850K 40K 

20K 80K 

870K 120K 

5th 

6th 

100K 

220K 

100K 

320K 

2nd 

3rd 

4th 

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ATTACHMENT D (Revised) 

Funding Summary (Photography — TV Manually Controlled) 

Integration & Installation Cost Estimates for Flights 

(K ii $1,000.00) 

F142 Fr 68 

#3, #4, 

.112 F

#5 and #6 

TOTAL 

Coordinate Integration 100K 100K 100K 300K 

Interfacing and Layout Designs 400K 275K 675K 

(2 vehicles) 

Special Studies & Experiments 240K 160K 400K 

Vehicle Interfacing Fabrication 1,850K 750K 2,600K 

Equipment Installation & Checkout •••■• . 360K 840K 1.40K ww■ 

TOTAL 740K 2,745K 1,690K 5,175K 

Data Processing Cost Estimates 

Fr 68 FY 69 TOTAL 

Analysis & Evaluation of Ground 500K 500K 1,000K 

Control, Simulator & Astronaut 

Training for Data Handling 

Initial Photo Set Ups and 200K 200K 

Trial Runs 

Flight & Post Flight Data 550K 550K 

Processing & Analysis 

TOTAL 700K 1,050K 1,750K 

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Experiment No. 5-10 

MAPPING AND GEODETIC SURVEY FOR IDENTIFIED POINTS 

I. Teat Objective 

This experiment will achieve a great improvement fn the knowledge of the 

ties between the various major continental data. The results will contribute 

directly to a more precise knowledge of the location of positions on the earth's 

surface. 

II. Importance of the Test 

Present estimates of the uncertainty of positional errors of some of the 

unmapped areas of the earth's surface are as large as 2000 to 5000 ft. In some 

special cases the errors noted are as large as 10,000 ft. These errors are 

greater than acceptable for intermediate range ballistic missiles and constitute 

a problem for intercontinental range ballistic missiles. Because of the difficulty 

of flying over portions of the earth's surface in an airplane or balloon, only a 

satellite is acceptable for accurately mapping these unknown regions. The ANNA 

satellite which was successful in mapping areas with an extensive cooperative 

ground based observing system, considerably improved geodetic knowledge. However, 

in large areas, such as the Soviet Union and China, where such cooperation is 

not probable, good positional accuracy has not been realized. 

For a manned spacecraft such as MOL, whose ephemeiikis accurately known 

and where_the principal errors contributing to a mapping operation are of the 

order of a few hundred ft., one can condUct a complete mapping of any region. 

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The uncertainty in such a map will be the uncertainties in the spacecraft 

ephemeris and the ability of a man to accurately point a camera and laser radar 

at a well identified point on the ground. The experiment described here will 

satisfy an immediate military requirement of locating positions on the earth 

to within a few hundred ft. It will provide a secondary scintific purpose by 

accurately relating major datums of the continents and improving the present 

knowledge of geodesy. It will greatly assist in assessing man's capability 

of performing an experiment in space. 

III. Description of the Experiment 

The experiment will determine the position of permanent land marks such 

as rivers, lakes, continental boundaries, and distinguishing terrain, by measuring 

their absolute position and the separation distance between bench marks. These 

measurements are obtained from an accurately determined ephemeris of the spacecraft and devices for measuring the range' from the spacecraft to the point of 

interest and the angle of the spacecraft with the radius from the center of 

coordinates. This will determine the angle and radius of the point with respect 

to a primary datum which is already established. The uncertainties in the 

ephemeris and in the range and angle measuring devices are such that the 

positional accuracy can be made as low as several hundred ft. 

The experiment consists of a special camera which photographs a point on 

the ground and simultaneously the star field along the line of sight. The 

range from the spacecraft to the point is determined by means of a giant pulse 

ruby laser and counter. This determines the absolute position of a point with 

respect to the spacecraft ephemeris. Points of separation between two objects 

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can be determined with the camera and a crystal clock which determines the transit 

time between the two points. This will permit an extensive mapping of a region 

with high internal precision and with accurate reference to an external datum 

point. The most significant problem that is expected to be encountered in this 

measurement is that of identifying the targets on the ground with sufficient 

accuracy for mapping purposes. However, with the aid of an auxiliary optical 

system which will be a part of the spacecraft, it is expected that this problem 

will be resolved. 

a. Configuration of Test Items 

The principal items of test equipment to be used for the geodetic 

experiment are: (1) a camera which viii simultaneously photograph a pgsition 

on the ground with sufficient resolution to identify the object photographed 

on which is superimposed the star field on the optical axis, (2) a laser range 

device which consists of a capacitor, high voltage power supply, electronic 

circuitry, and ruby laser will determine the range from the spacecraft to the 

ground, and (3) a 50 megacycle counter to measure the transit time of the light 

pulse from the spacecraft to the ground and back. In addition, the separation 

distance between two points on the ground can be accurately determined by using 

the camera and a precision crystal clock to determine the transit time between 

the points. Since the camera is required to observe the earth, it will be necessary 

to locate this item and the laser head on the MOL in such a fashion as to permit 

it to view simultaneously the ground and the star field. Attachment I gives the 

design characteristic details. 

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Physical dimensions of the equipment are as follows: 

Item 

Camera 

Dimensions Wt. 

25 lbs. 

Power Volume 

6" x 12" x 12" 1 watt 0.5 cu ft 

Capacitor 8" x 8" x 8" 36 " None 0.3 " " 

Paver Supply 2" x 4" x 6" 2 " 2 watt 0.03 " " 

& Electronics 

Laser Head & 4" x 4" x 5" 1 " None 0.05 " " 

Mirror 

Counter & Clock 5" x 17" x 19" 43 " 100 watt 0.93 " " 

These items may be placed at any convenient spot on the vehicle where the camera 

and laser head have a view of the ground. 

b. Test Support Equipment Required 

(1) Spacecraft 

In addition to the equipment described, the support of an auxiliary 

optical system to identify objects on the ground and to point 

the camera and laser at the some point is required. 

(2) AGE 

Range support to accurately establish an ephemeris for the 

vehicle and checks on the crystal clock on board to maintain 

time accuracies to 1 millisecond are required. Attachment II 

-describes the test support equipment in detail. 

c. Test Procedure 

It is planned to observe a large network of identified objects on the 

ground to establish a map which is internally accurate tram the clock measurements 

and to relate one or more points of the map to one of the major datums in the 

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United States. To accomplish this, the astronaut will have to identify major 

and minor land marks which are permanent such as large lakes, rivers, cities, 

or other distinguishing terrain. Attachment III describes the test operating 

factors. Man's contribution to the experiment is in the identification of and 

selection of significant areas and objects,to be mapped. He vill be utilized to 

the maximum extent possible in making decisions on the importance of the objects 

he identifies for mapping and the care with which he makes the measurement. His 

contribution will be measured by the quality of the map he produces. 

d. Category of Experiment 

This experiment is expected to be a Category Al experiment in that it 

contributes to the Min objectives, but does not exert a significant influence 

on the design characteristics of the laboratory. 

e. Cost 

Engineering and Development 

FYI FY66 116/ FY68 FY69 Total 

(1) 

150K 150K 150K 100K 100K 650K 

(2) Installation 

25K 25K 100K 100K 100K 350K 

(3) Ground Support 

100K 100K 

f. Schedule 

(1) Hardware and Software Available for Test 

Prototype hardware will be constructed during FY65 and 

available for test during FY66. 

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(2) Hardware and Software Flight Readiness Date 

Flight ready equipment will be available beginning with FY67, 

tested and flight qualified. 

IV. Participating Government Agencies Sponsor: SSD/Aerospace 

It is expected that the agencies concerned with geodesy and mapping such 

as were utilized in the ANNA satellite vill be active participants in conducting, 

monitoring, and evaluating the experiment. Since the information obtained vill 

be of interest to all agencies, agency responsibility similar to ANNA will be 

required. Test equipment should be acquired by a single agency with a concurrence 

of all participating agencies. 

V. Additional Requirements 

a. Special Security' 

Special processing of the data will be required in view of its 

importance to identification of possible target areas in the Soviet Union and 

China land areas. 

b. Lo sties 

No special requirements. 

c. Facilities 

Existing facilities can be used for the experiment integration. 

Coordination with the national range, and SSD satellite network will be required 

to obtain an accurate ephemeris. It is expected that training of the astronaut 

vill require use of a flight simulator, but only for the purposes of instructing 

the astronaut in the use of the quipment. 

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d. Simulation and Training( 

(1) Astronaut 

The astronaut must be trained to the level of a technician 

in order to achieve full effectiveness in this experiment. It is expected 

that a few weeks training in photoreconnaisance work and in astronomical 

observation techniques will be adequate to develop a capability necessary for 

the experiment. 

(2) Ground Personnel 

No requirement. 

(3) Equipment 

The equipment to be used in the experiment will be utilized 

in training the astronaut. 

VI. General 

a. Communications will be limited to discussions with specially informed 

ground based personnel on particular areas to be observed. This will involve 

someone with knowledge of the land mass expected to be surveyed. Data will be 

recorded on film and magnetic tape and will be required to be recovered with the 

re-entry vehicle. 

b. Development Characteristics 

No additional requirements. 

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ATTACHMENT I 

1. LASER RADAR AND GEODETIC CAMERA 

2. WEIGHT: 107 LBS. 

3. VOLUME: Stored 1.81 cu ft 

4. CRITICAL DIMENSIONS 

Item Dimensions 

Camera 6" x 12" x 12" 

Capacitor - 8" x 8" x 8" 

Power Supply 2" x 4" x 6" 

& Electronics 

Laser Head & 4" x x 5" 

Mirror 

Counter & Clock 5" x 17" x19" 

5. SPARES 

a. Volume: 3.62 cu ft 

b. Quantity: 2 

c. Weight: 200 lbs. 

6. TOOLS 

No requirement 

7. HEAT OUTPUT 

100 watts with 1/10 duty cycle 

8. STABILITY 

No requirement 

9. VIBRATION LIMITS 

20 g's 

10. SHOCK LIMITS 

30 g's 

In use 1.81 cu ft 

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ATTACHMENT I (cont'd.) 

11. HAZARDS 

Electrical, 10 kv power supply 

12. TEMPERATURE LIMITATIONS 

No requirement 

13. TYPE AND RANGE OF MEASUREMENT 

Ground based photographically and laser radar ranging 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS 

No requirements 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS 

Accurate ephemeris and accurate time evaluation 

16. EQUIPMENT OPERATING. CYCLE 

Several times daily -- Time duration: 15 min. 

17. EQUIPMENT LOCATION REQUIREMENTS 

Camera requires access to ground and stellar background 

18. SPECIAL MOUNTING REQUIREMENTS 

Apertures: Clear view of ground and stars 

Pulse: None 

Windows: None 

Antennae: None 

Bracketry: Mountings for camera, laser and power supply 

19. PRESSURE VESSELS 

No requirements 

20. ELECTROMAGNETIC INTERFERENCE 

No requirement 

21. MAINTENANCE REQUIREMENTS 

No requirement 

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ATTACHMENT II 

1. RECORDING MEDIA 

a. Tape recorder required to store laser range data. 

b. Film required to obtain ground and stellar photographs. 

2. HANDLING 

No requirement 

3. PACKAGING 

No requirement 

4. CALIBRATION 

Accurate crystal clock with comparison with ground clock. 

5. JIGS AND FIXTURES 

Mounting jig for camera and telescope 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION 

None 

7. SENSORS 

One photomultiplier for laser radar 

8. TRAINERS/SIMULATORS 

Flight training program for astronaut on airplane or balloon 

9. INSTRUMENTATICO 

Telescope for guiding camera and identifying ground based objects; 

may be time shared with other experiments 

10. RELATED SUPPORT EQUIPMENT 

a. Simulated ground based target 

b.. Communication with specialists on ground 

c. Accurate tracking to establish very good ephemeris 

d. Film recovery and processing required 

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ATTACHMENT II (cont'd.) 

11. AGE 

Time calibration and position indicating equipment 

12. ENVIRCOMENTAL TEST EQUIPMENT 

No requirement 

13. FACILITIES 

No requirement 

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A1TACEMENT III 

1. ORBITAL PARAMETERS 

a. Altitude: 200 sl 

b. Inclination: Polar desired or high latitude equitorial 

c. Epoch: No requirement 

d. Ellipticity: Circular preferred 

2. PLANE CHANGE 

No requirement 

3. _Ammon CHANGE 

No requirement 

4. TIME ON ORBIT 

30 days desired 

5. TEST DURATION 

3 days 

6. TOTAL NUMBER OF TESTS 

100 

7. TEST FREQUENCY 

Daily 

8. INTERVAL BETWEEN TESTS 

' When orbit permits survey of area to be mapped 

9. CREW TASK LOADS 

.3 of a mom month 

10. CREW TASK FREQUENCY 

Daily 

11. FIELD OF VIEW REQUIREMENTS 

2 degrees view of earth and stars 

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ATTACHMENT III (cont'd.) 

12. GROUND CONTROL LIAISON DURATION 

10 minutes 

13. GROUND CONTROL LIAISON FREQUENCY 

Each orbit 

14. EXTERNAL TEST ITEMS 

No requirement 

15. QUALIFICATION TESTS 

a. Shock and vibration for launch. Life test for laser and power 

supply. 

b. No requirement 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT 

Photographs taken of terrain during passage over territory to be 

mapped. Check of clock and ephemeris on each orbit to maintain 

precise ephemeris. Removal and return of film at conclusion of 

flight. 

17. HANDLING PROCEDURES 

Recovery of film and magnetic tape record and special processing. 

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ATTACHMENT IV 

FUNDING SUICARY 

BUDGET REQUVOLMINTS BY FISCAL YEAR 

PRIOR FY 65 FY 66 FY 67 - FY 68 FY 69 TOTAL 

Engineering, Developmental 

Environmental Testing 150K 15CIC 150K 100K 100K 650K 

Integration and Installation 25K 25K 100K 100K 100K 350K 

AGE 100K 100K 200K 

Simulators/Trainers 100K 100K 

Data Reduction 100K 100K 200K 

Equipment Rework 100K 100K 

Other 

TOTAL 1,600K 

Source of Nadi - Hitch Line Number 

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ATTACHMENT VI 

1. DATA RATE 

Ten photographs recorded each orbit. Transit time between ten points 

recorded each orbit. 

2. FUNCTIONS TO BE MEASURED 

Time, position, and aspect angles. 

3. TYPE OF ANALYSIS REQUIRED 

Photoreconnaissance photographs of geographic terrain. 

4. PICTORIAL DATA REQUIRED 

Reconnaissance photographs of geographic terrain. 

5. REAL TIME MONITORING REQUIREMENT 

Crystal clock and ephemeris monitoring required. 

6. DATA EDITING OR COMPRESSION 

Data edited to correlate ephemeris, photographs, and stellar aspects. 

7. READ-OUT TIME 

Data read-out on passage over ground support station• 

8. 'REQUIREMENTS FOR PERMANENT DATA RECORDS 

Photograph and aspect records permanently recorded. 

9. MANUAL AND/OR AUTOMATIC CONTROL ' 

Manual control of camera; automatic control of time. 

10. SIMULTANEITY 

All events require correlation in time. 

11. GROUND COMMANDS REQUIRED 

Identification of proper targets to be photographed; correlated with 

ground. 

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ATTACHMENT VII 

1. DEVELOPMENT TIME 

Development time required to design and build camera and laser radar; 

approximately two years. 

2. FINAL DEFINITIVE TEST DESIGN TIME 

One year required for final flight model. 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED 

Several ground and flight tests to familiarize astronaut with operation 

of equipment. 

L. TYPE OF DEVELOPMENT TEST ITEMS 

a. Vacuum test required if camera operates outside of spacecraft. 

b. Shock and vibration test for booster. 

c. Thermal cycling dependent on location of camera on spacecraft. 

d. Normal vibration during boost to orbit. 

e. Star field and terrain radiance simulation for ground based training 

of astronaut. 

f. Aircraft flights to familiarize astronaut vitt equipment and flight 

condition. 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME 

One year to develop stellar/terrain simulator. 

6. NUMBER OF TEST ARTICLES REQUIRED 

a. One ground teat instrument required. 

b. One instrument for aircraft test. 

c. Four instruments required for flight qualification, prototype 

installation, flight instrument and back-up. 

7. DATE AVAILABLE FOR TESTS 

FY67 

8. CURRENT DEVELOPMENT STATUS 

Proposed only. 

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C vrt r 

Additional instruments are rectangular boxes whose dimensions are given 

on page 4. These instruments can be made to conform with available racks. 

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-BRET- Experiment No. S-11 

DETERMINATION OF MASS OF ORBITING BODIES 

PART 1 

I. Test Objective 

This experiment is directed towards the proving of a system of 

mass measurement under a Zero G condition. It will allow man to perform the aiming and firing functions and will allow his assessment 

of the results as indicated by spaceborne equipment. 

II. Importance of the Test 

This test is required in order to demonstrate under operational 

conditions, i.e., space environment, the performance and accuracy of 

the rocket propelled net as a method of mass measurement. The size 

of the expanded net,siming accuracy requirements and atmospheric 

interferences make it necessary to do this test in space. This test 

will demonstrate man's abilities to meet the required aiming accuracy 

and to perform the translation of range rate into mass. 

III. Description of the Experiment 

The test will be the firing of a rocket-propelled net which 

will expand once it has left the parent vehicle and will proceed to 

the target approximately 2000' per record and w!_11 impart Its maaentua 

to the target by wrapping; itself around. It has been determined that 

this method of masa measurement will give an accurate measurement of 

the target mass to 10% with targets weighing up to 10,000 pounds. 

The only foreseeable problem is that the exhaust from the rocket may 

obscure the photographic equipment utilized to record the experiment. 

This obscuration should be fairly short. 

a. Configuration of Test Items 

The net to be utilized will weigh approximately 5 pounds 

and the case and solid propellant an additional li pounds. It is 

expected that the launch tube will not weigh in excess of an additional 5 pounds, giving a total system weight of 11 pounds. (See 

Attachment A.) 

b. Test Support Equipment Required 

Use of the radar system aboard the MOL will be required 

to measure the change in relative velocities between the MOL and 

target. Use of available camera equipment will also be required to 

record the net impact on the target vehicle. No specific AGE requirements have been determined. (See Attachment B.) 

--SECRET-- 

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c. Tact Ta PrIceduro 

At the beginning of the toot the man may be required to 

load the rocket device into the launcher. He will then aim the 

launcher with the use of an optical aiming device having at least 

ono decree accuracy and electrically fire the rocket. The aiming 

and firing will most likely be done in the environmentally controlled 

section of MOL. The not will impinge on the target in approximately 

to second after firing. At this time the man will be required 

to consult range rate displays available to him and correlate the 

change in range rate from before the experiment to after the oxperiment 

to I. chart indicating approximate masa. It would bo desirable to have 

the camera available on the MOL aligned at the some time with the 

optical aiming device and have the camera start filming the experiment 

electrically simultaneously with the rocket firing. Since the target 

mass will be known a check can be made after the experiment is over on 

the accuracies attained by this method of mass measurement. 

d. Category of Experiment 

This experiment falls in Category B as defined in the 

sample format. 

e. Cost (Budget Requirements by Fiscal Year) 

Prior FY 65 Fl 66 17 67 TOTAL 

(1) Engineering & 

Development 

(2) Installation .15 .158 .472 .12 .9 

(3) Ground Support 

TOTAL .15 .158 .472 .12 .9 

Phase I Phase II 

f. Schedule 

• (1) The first prototype equipment should be available in 

early 1966 with the first flight article available is Ootober of the 

same year. These dates are predicated upon an April 1965 go-ahead 

for Phase II. 

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IV. Participating Government Agencies 

Sponsor: SSD/Aerospace 

Test Equipment Acquisition: To be acquired as part of the 

system. 

V. Additional Requirements 

a. Special Security - None. 

b. Henning Description Summary - See Attachment E. 

c. Logistics - To be determined. 

d. Facilities 

A vertical test facility fairly simple in nature will be 

required to test net deployment. It appears all other tests can be 

conducted with the existing facilities. 

e. Simulation and Training 

Familiarization with the optical aiming device will be 

required for the astronaut. 

VI. General 

a. Communications and Data Handling Requirement - See 

Attachment P. 

b. Development Characteristics See Attachment G. 

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ATTACHMENT A 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. Equipment to be Tested - Rocket Propelled Net Device 

2. Weight - 6.5 lbs and a small rocket launcher - less than 5 lbs 

3. Volume - Stored - small to be determined 

Critical Dimensions - None 

4. Power - Requires use of existing radar - negligible power required 

for firing circuit 

5. Spares - 

a. Volume - small to be determined 

b. Quantity - 1 or 2 extra net cartridges may be carried 

c. Weight - 13 lbs if spares are carried 

6. Tools - No requirement 

7. Heat Output - Negligible - fired outside MOL 

8. Stability - Required to permit aiming to 1 degree 

a. Moving Parts - Barrel to cartridge 

9. Vibration Limits - to be determined - not considered critical 

10. Shock Limits - to be determined 

11. Hazards (Those Normally Associated With Solid Rocket Firing) 

12. Temperature Limitations - to be determined 

13. Type and Range of Measurement - Net is fired when MOL is 500.- 

1000 feet from target. Radar range measurements will indicate 

momentum transferred to target. Range rate change is required 

to 1 ft/second. 

14. Special Environmental Requirements - None 

15. Orientation and Position Accuracy Requirements - 

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Station - Stabilized 

Equipment - Aiming to 1 degree accuracy 

16. Equipment Operating Cycle - that of the radar 

17. .Equipment Location Requirements - may require storage within 

MOL prior to use 

18. Special Mountings Requirements - Rocket tube should be mounted 

externally. The location should be such that the astronaut can 

load it if necessary. 

19. Pressure Vessels - None 

20. Electro Magnetic Interference - None 

21. Maintenance Requirements - 

Ground - Maintenance and care of firing circuit 

Space - None identifiable 

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---SECRETATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA - 

a. Tape - may be required to record range rate data 

b. Film - should be used to record experiment 

c. Other - astronaut will be required to record results 

2. HANDLING (SPECIAL EQUIPMENT REWIRED TO HANDLE ITEMS BEING TESTED - 

None 

3. PACKAGING - 

4. CALIBRATION - must be boresighted with aiming device 

5. JIGS AND FIXTORIS - to be determined 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION - to be determined. 

Will concern electrical firing circuits. 

7. SENSORS (Transducer - Output Signals) 

8. TRAINER /SIMULATORS - to be determined 

9. INSTRUMENTATICU - Laboratory. Radar range rate during short 

duration of the test must be displayed to the astronaut. 

10. RELATED SUPPORT EQUIPMENT - 

a. Targets - A target of known mass must be available at a range 

between 500 and 1000 feet. 

b. Ground Stations - no requirement 

c. Tracking - Must be accomplished by MOL ATE to 1 ft/second 

d. Handling Equipment - No special requirement 

11. AGE - to be determined. However, the lack of equipment complexity 

will make the requirement small. 

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12. ENVIRONMENTAL TIEST/EWIPMENT - Will require scale model vac 

chamber firing teats. 

13. FACILITIES - A vertical test facility will be required during 

development for net deployment and impact tests. 

SW 

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ATTACHMENT C 

TEST OPERATING CHARACTERISTICS 

1. Orbital Parameters (Desired) - No special requirements 

2. Plane Change - No requirement 

3. Altitude Change._- No requirement 

4. Time On Orbit - No special requirement 

5. Test Duration - Less than 1 minute 

6. Total Number of Tests - 1 required - more may be possible and 

desirable 

7. Test Frequency - no set frequency 

8. Interval Between Tests - Not critical 

9. Crew Task Loads - man hours not to exceed 1 man-hour 

10. Crew Task Frequency - to be determined 

11. Field of View Requirements - Astronaut must see target through 

optical aiming device 

12. Ground Control Liaison Duration - Not required 

13. Ground Control Liaison Frequency - Not required 

14. External Test Items - 

a. Launched From Station - Net will be launched from MOL against 

any available target 

15. Qualification Tests (Other Than Space) - 

a. Ground - Launch rocket must be tested for spin and firing. 

Net deployment tests are also required. 

16. Sequence of Events as They Occur During Flight - &act sequence 

to be determined 

17. Handling Procedures - Those associated with solid rocket handling 

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8 

8 

U' 

. ; 

0 

5 

15 g 1 

m 4 E 

t 

, 

A g 1,4 2 • g . .1 -° t 4, 

1 

t , 2 1 

P 1 1 i I. 

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ATTACHMENT E 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required - One astronaut will be required to aim the 

rocket tube at the target to within one degree of accuracy. 

(1) Man's function - In addition to the aiming requirement, 

the astronaut will be required to interpret the range rate data available concerning the target and relate this information to the target 

measured mass. Since the mass of the target will most likely be known, 

the astronaut may also be able to determine the accuracy of the test 

conducted. 

b. Crew skill requirements - The astronaut will require sufficient 

skill with the aiming device to meet the one degree requirement. 

c. Manpower profile - One astronaut for a period of approximately 

5 minutes. 

d. Critical functions - aiming to within one degree and determincation of range rate to one foot per second. 

e. Work positions - The astronaut will most probably work in 

the environmentally controlled section. He may, however, be required 

to leave this section in order to load or reload the rocket launcher. 

f. Time controlled tasks - to be determined. 

g. Human performance measures - to be determined. 

h. Physiological and Psychological measures - to be determined. 

i. Selection factors - no special requirements. 

j. Training requirements - familiarization with the equipment 

involved. 

2. GROUND PERSONNEL 

No ground personnel requirements are directly relatable to the 

teat. 

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ATTACHMENT F 

Ca4MUNICATIONS AND DATA HANDLING 

1. Data Rate - Range rate measurements are required during the 

period of the test. 

2. Functions to be Measured - Range rate. 

3. Type of Analysis Required - Correlation of range rate to mass 

and analysis of the determined mass with the known mass of the 

target. 

4. Pictorial Data Required - Film records are required of the 

experiment to show net impact. 

5. Real Time Monitoring Requirement - No requirement. 

6. Data Editing or Compression - No requirement. 

7. Read-Out Time - No requirement. 

8. Requirements For Permanent Data Records - See 4. above. 

9. Manual and/or Automatic Control - Both methods of operation should 

be available to the astronaut. 

10. Simulaneity - Not required. 

11. Ground Commands Required - Not required. 

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DEVELOPMENT CHARACTERISTICS 

1. Development Time - On a three-time estimate system a total of 

24 months is the most likely development time. The most pessimistic 

time is approximately 30 months and the most optimistic time is 18 

months. These times include both Phases I and II. In all cases 

Phase I will require 5 months. 

2. Final Definitive Test Design Time - To be determined. 

3. Number of Ground or Flight Tests Required - To be determined. 

4. Type of Development Test Items - 

a. Vacuum Chamber - Scale model fired will be required to 

verify rocket and meet performances in a vacuum. 

5. Support Equipment Development Time - To be determined. 

6. Number of Test Articles Required For: 

a. Ground Test - To be determined. 

b. Atmospheric Test - To be determined. 

c. Space Test - One. 

7. Date Available For Tests - Prototype will be available in early 

1966 with the first flight model available in late 1966. These 

figures are based on a Phase II go-ahead in April 1965. 

8. Current Development Status - This system was studied during the 

Phase 0 of Program 706. To date approximately $100,000 has been 

expended on mass measurement. During 706 Phase 0 this expenditure 

included preliminary designs on this and other systems. 

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DETERMINATION OF MASS OF ORBITING BODIES 

PART 2 

I. Test Objective 

This experiment is directed towards the proving of a system of 

mass measurement under a Zero G condition. It will allow man to perform the aiming and firing functions and will allow his assessment 

of the results as indicated by spaceborne equipment. 

II. Importance of the Test 

This test is required in order to demonstrate under operational 

conditions, i.e. space environment, the performance and accuracy of 

an automatic shotgun as a mass measurement device. Atmospheric conditions will affect the velocity of the pellets at the point of impact 

on the target. Space testing is necessary in order to eliminate this 

and in order to verify man's capability to aim. In addition, disposal 

of spent cartridges under a Zero G environment could be a problem. 

These cartridges must be collected from the immediate vicinity of the 

spacecraft and deposited so as not to affect this or other systems. 

Similarly, tne operation of the repeating shotgun under the prolonged 

extremes of the space environment is not determinable without a 

spaceborne experiment. This test will demonstrate man's abilities 

to meet the required aiming accuracy and to perform the translation 

of range rate into mass. 

III. Description of the bcperiment 

The test will be the firing of an automatic shotgun loaded 

with small nylon pellets which will impact the target and transfer 

momentum to it. The number of rounds to be fired is dependent upon 

the size of the target and the ability of the radar to determine 

changes in range rate. For extremely light targets, this method is 

capable of adding sufficient momentum to de-orbit them. 

a. Configuration of Test Items 

The automatic shotgun will be a gas operated device 

capable of firing up to 200 rounds. The total weight of the gun 

and ammunition is approximately 27 pounds. (See Attachment A.) 

b. Test Support Equipment Required 

Use of the radar system aboard the MOL will be required 

to measure the change in relative velocities between the MOL and 

target. Use of available camera equipment will also be required to 

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record the pellet impact on the target vehicle. No specific AGE requirements have been determined. (See Attachment B.) 

c. Test Procedure 

At the beginning of the test, the man may be required to 

load the shotgun. He will then aim the shotgun with the use of an 

optical aiming device and will electrically fire it. The aiming and 

firing will most likely be done from the environmentally controlled 

section of MOL. At this time, the man will be required to consult 

range rate displays available to him and correlate the change in 

range rate from before the experiment to after the experiment to a 

chart indicating approximate mass. Firing may be stopped when sufficient moment= has been imparted to give a measurable change in 

range rate. It would be desirable to have the camera available on 

the MOL aligned at the same time with the optical aiming device and 

have the camera start filming the experiment electrically simultaneously 

with the firing. Since the target mass will be known, a check can 

be made after the experiment is over on the accuracies attained by 

this method of mass measurement. 

d. Category of Experiment 

This experiment falls in Category Bs 

e. Cost (Budget Requirements by Fiscal Year) 

Prior FY 65 FY 66 FY 67 TOTAL 

(1) Engineering & 

Development 

(2) Installation .300 .320 .960 .72 2.3 

(3) Ground Support 

TOTAL .300 .320 .960 .72 2.3 

Phase I Phase II 

f. Schedule 

(1) The first prototype equipment should be available in 

early 1966 with the first flight article available in April or May 

of 1967. These datet are predicated upon an April 1965 go-ahead for 

Phase II. 

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IV. Participating Government Agencies 

Sponsor: SSD/Aerospace 

Test Equipment Acquisition: To be acquired as part of the 

system. 

V. Additional Regarements 

a. Special Security 

None. 

b. Manning Description Summary 

See Attachment E. 

c. Logistics 

To be determined. 

d. Facilities 

It appears all tests can be conducted with the existing 

facilities. 

e. Simulation and Training 

Familiarization with the optical aiming device will be 

required for the astronaut. 

VI. General 

a. Communications and Data Handling Requirement 

See Attachment F. 

b. Development Characteristics 

See Attachment G. 

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ATTACHMENT A 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. Equipment to be Tested: Automatic Shot Gun • 

2. Weight: 27 lbs. including 200 rounds 

3. Volume: Stored - To be determined In Use - To be determined 

4. Power for Firing Circuits only: Negligible 

5. Spares: To be determined. Some maintenance may be done for 

repair or practice 

6. Tools: To be determined. No planned requirements have been 

identified 

7. Heat Output: Not determined 

8. Stability: This device is recoil loaded. The effects of this 

recoil on the MOL will be determined 

a. Moving Parts 

9. Vibration Limits: None critical to the sensor system 

10. Shock Limits: N/A 

11. Hazards: No critical hazards should be present since the gun 

is fired outside of The Mol 

12. Temperature Limitations: Gun must be stored inside environmentally 

area until used 

13. Type and Range of Measurement: Range rate measurement is required 

to 1 ft/sec during Test period 

14. Special Environmental Requirements: Environmentally controlled 

storage for Shotgun prior to use 

15. Orientation and Position Accuracy Requirements: 

Station: The MOL must be stabilized. The degree required will be 

determined 

Equipment: Aiming accuracy is a function of shotgun barrel choke and 

must be determined during development 

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16. Equipment Operating Cycle: 

Frequency: Up to 200 firing cycles - dependant on target mass 

Tine Duration: Less than 1 minute 

17. Equipment Location Requirements: Aiming device may be in environmentally controlled area. Gun 

will be fired outside 

18. Special Mountings Requirements: 

Bracketry: To be determined 

19. Pressure Vessels: Fluids, gasses, etc. None. 

20. Electro Magnetic Interference (spurious generation, special shielding 

req, etc): None 

21. Maintenance Requirements: 

Ground: To be determined 

Space: Maintenance demonstration may be incorporated as part of the 

Test 

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ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. Recording Media 

a. Tape 

b. Film 

c. Other 

2. Handling: None 

3. Packaging: To be determined 

4. Calibration: Gun and sight must be boresighted on the ground 

5. Jiga and Fixtures: None 

6. Number of Leads from Outside to Inside Station: Only those concerned 

with firing circuit 

7. Sensors: None 

8. Trainers/Simulators: To be determined 

9. Instrumentation - cockpit and/or laboratory (note effect of time 

sharing instruments with other experiments): Range Rate data must 

be available within The MOL and displayed to the astronaut during 

the Test 

10. Related Support Ex.uipment: 

a. Targets: A Targer of known mass must be available to a range 

of approximately 150 ft. 

b. Ground Stations: None 

c. Tracking: Radar must Track the target from The MOL 

d. Handling Equipment: No special equipment required 

11. AGE: To be determined 

12. Environmental Test Equipment: To be determined 

13. Facilities: Test firing facilities are required during development. 

It may be necessary to fire in a vacuum chamber during pellet Tests. 

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ATTACHMENT C 

TEST OPERATING CHARACTERISTICS 

1. Orbital Parameters (desired): Not critical 

2. Plane Change: Not required 

3. Altitude Change: Not required 

4. Time on Orbit: 10 minutes 

5. Test duration: 10 minutes maximum 

6. Total Number of Tests: 1 

7. Test Frequency: N/A 

8. Interval Between Tests: N/A 

9. Crew Task Loads: To be determined. For practice. 

10. Crew Task Frequency: To be determined. For practice. 

11. Field of View Requirements: Sufficient to aim shotgun with remote 

device 

12. Ground Control Liaison Duration: Not required 

13. Ground Control Liaison Frequency: Not required 

14. External Test Items: Target must be available 

15. Qualification Tests Ground: Testing is required to determine 

shotgun characteristics and pellet performance during development. 

16. Sequence of Events as They Occur During Flight: Exact sequence 

to be determined. 

17. Handling Procedures: To be determined if required. 

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ATTACH1WT D 

A co:.bi..tA Attachmcnt D . is incluticd for both systems of mass 

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ATTACHMENT I 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. NUeber required - One astronaut vill be required to aim the shotgun 

at the target to an accuracy to be determined during development tests. 

(1) Men's !Unction - In addition to the aiming requirement, the 

astronaut will be required to interpret the range rate data available concerning 

the target and relate this information to the target measured mass. Since the 

mass of the target will most likely be known, the astronaut may also be able to 

determine the accuracy of the test conducted. 

b. Crew skill requirements - The astronaut vill require sufficient skill 

with the aiming device. 

c. Manpower profile - One astronaut for a period of approximately 10 minutes. 

d. Critical functions - aiming to the accuracy required and determination 

of range rate to one foot per second. 

e. Work positions - The astronaut vill most probably vork in the 

enwirmnientally controlled section. He may, hoverer, be required to leave 

this section is order to load or reload the rocket launcher. He may also 

be required to maintain the shotgun. 

f. Time controlled tasks to be determined. 

g. Human performance meeseres - to be determined. 

h. Physiological and Psychological measures - to be determined. 

i. Selection factors - no special requirements. 

J. Training requirements - familiarisation with the equipment involved. 

2. GROUND PERSONNEL 

No (crowd personnel requirements are directly relateable to the test. 

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ATTACIANDR 

counaurxons AND MA RAID1.III3 

1. Data Rate - Range rate moWsuresents are required during the period of the 

test. 

2. Functions to be Measured - Range rate. 

3. Type of Analysis Required Correlatiaa of Mtge rate to mass and analysis 

of the determined mess with the known sees ot the target. 

4. Pictorial Data Required - P11* records are Modred of the experiment to 

show pellet impact and affect oaths target. 

5. Real Time Monitoring Requirement - No requirement. 

6. Data Editing or Compression - Mo requirement. 

7. Bead-Oct Time Mo requirement. 

8. Requirements for Permanent Data Records - See 4 above. 

9. Mammal and/Cr Automatic Control • Both methods of operation should be 

available to the astromant for aiming and firiat• 

10. Simultaneity - Riot required. 

it. Ground Commends Required - Jot required. 

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ATTACHMENT(' 

DEVELOPHINT CHARACTERISTICS 

1. Development Time - On a three-time estimate system • total of 30 months 

is the most likely development time. The most pessimistic time is 

approximately 35 months and the most optimistic time is 21 months. These 

times include both Phases I and II. In all cases Phase I will require 5 

months. 

2. Final Definitive Test Design Time - TO be determined. 

3. Number of Ground or Flight Tests Required To be determined. 

h. Type of Development Test Items - 

Vacuum Chamber - Scale model firing viii be required to verify shotgun 

and pellet performances in a vacuum. 

5. Support Equipment Development Time - To be determined. 

6. Number of Test Articles Required For: 

S. Ground Test - To be determined. 

b. Atmospheric Test - To be determined. 

0. Space Test - One. 

7. Date Available for Tests - Prototype viii be available in early 1966 with 

the first flight model available in early 1967. These figures are based on 

a PhaseII.go-abead in April 1965. 

8. Current Development Status - This system vas studied during the Phase 0 of 

Program 706. To date approximately $300,000 has been expended on mass 

measurement. During 706 Phase 0 this expenditure molded preliminary 

designs on this and other systems. 

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Experiment No. S-12 

HYDROGEN REDUCTION ATMOSPHERIC REGENERATION SYSTEM 

I. Test Objective 

Evaluate component and system performance of a chemically regenerative 

atmospheric control system as an integral part of a life support system. An 

adjunct part of this experiment will be periodic monitoring of the contaminants 

within the cabin atmosphere.. 

II. Importance of Test 

This test is needed for the development of life support equipment for long 

duration manned space missions. Operation of the equipment requires verification 

in a manned system in a zero gravity field, and the use of a space vehicle, such 

as MOL, is essential. 

As mission times and the complement of manned spacecraft increase, a point 

will be reached in the not-too-distant future where the penalties for the use 

of expendable or open cycle atmospheric control systems will be excessive. Reliable high performance atmospheric regeneration systems will have to be developed 

for these long duration manned space missions. The most promising systems consist 

of reducing CO2 to H2O with hydrogen and subsequent electrolysis of the water to 

provide breathing oxygen. Two-phase operation exists in the water condenser and 

electrolysis cell which requires verification in a zero gravity field. The basic 

system will consist of a reactor subsystem and an electrolysis subsystem which 

may be operated separately to conserve power. 

III. Description of the Experiment 

The systems consists of a water and CO2 removal subsystem, a. reactor subsystem in which CO2 is reduced with hydrogen to water and methane (possibly carbon), and an electrolysis subsystem in which water is dissociated into hydrogen 

and oxygen. 

Assuming that the MOL consists of two pressurized compartments, it is proposed that the system be used to purify the atmosphere for one of the compartments as long as the system functions properly. The vehicle life support system 

should be capable of complete atmospheric control in the event of failure of the 

reduction system. 

a. Configuration of Test Items (See Attachment A) 

b. Test Support Equipment Required (See Attachment B) 

(1) Spacecraft. Miscellaneous vehicle maintenance tools 

(2) AGE. None 

c. Test Procedures (See also Attachment C) 

The system should be operated continuously to obtain operating experience. A 30 day test of this nature would be a big help in developing long 

duration atmospheric control systems for space vehicles. Temperatures,-pressures, 

flow rates and power consumption should be measured, and samples of the gas 

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stream should be periodically analyzed. A gas chromatograph or mass spectrometer 

should be used to- monitor all trace contaminants in the cabin atmosphere during 

the entire mission. 

(1) Man's Role. Man's role primarily consists of providing the "used" 

air (by normal.breiTiangrigr the system. In addition, the crew must monitor the 

system operation. 

(2) Man's Utilization. As mentioned in paragraph 1 above, man is 

utilized primarily for the purpose of loading the test system. 

(3) Testing Sequence. There is no special testing sequence. The 

system should be operated continuously with regularly scheduled monitoring and 

data recording chores. 

d. Category of Equipment (Omit) 

e. Cost (See Attachment D) 

f. Schedule 

(1) Hardware could be made available for teat in 1965. 

(2) A flight readiness date of 1967 is feasible. 

IV. Participating Government Agencies 

Interested agencies are the Aerospace Medical Research Laboratory and the 

School of Aviation Medicine, both of the Aerospace Medical Division, AFSC; the 

Flight Dynamics Laboratory of the Research and Technology Division, AFSC; and 

the NASA Laboratories at Houston, Langley and Lewis. 

V. Additional Requirements 

a. Special Security None 

b. Manning Description Summary (See Attachment E) 

c. Logistics (Omit) 

d. Facilities 

Prior ground testing is required for system development and for astronaut 

training. This is a man-rated system and should be thoroughly evaluated in a space 

station atmospheric control simulator. 

e. Simulation and Training 

(1) Astronaut. Training as a technician should be sufficient for 

this experiment. The astronaut should be trained to start-up the apparatus and 

take data, including operation of the gas chromatograph and/or mass spectrometer. 

(2) Ground Personnel. None 

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(3) Equipment. The atmospheric reduction system should be evaluated in a simulator mentioned in paragraph (d) above. 

VI. General 

a. Communications and Data Handling Requirement. (See Attachment F) 

b. Development Characteristics. (See Attachment G) 

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ATTACHMENT A 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED HYDROGEN REDUCTION ATMOSPHERIC 

REGENERATION SYSTEM 

2. WEIGHT: 150 lbs 

3. VOLUME: Stored 4.4 In use 4.4 

CRITICAL DIMENSIONS - SHAPES Cube 1.64 ft on each side 

4. POWER (watts) 

a. Continuous 550 

b. Stand-by Not known 

c. Average operating 550 (molecular sieve subsystem included) 

d. Peak 700 

e. Duty cycle Continuous at 550 watts, 700 for start-up 

5. SPARES None required 

a. Volume 

b. Quantity 

c. Weight 

6. TOOLS No unique requirements use spacecraft maintenance tools 

a. Volume 

b. Quantity 

c. Weight 

d. Power 

7. HEAT OUTPUT 550 watts 

8. STABILITY Not available 

a. Moving parts 

9. VIBRATION LIMITS Not available 

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10. SHOCK LIMITS Not available 

Possible hydrogen 

11. HAZARDS (fire, explosion, electrical, toxic., other)fire in event of reactor leak 

12. TEMPERATURE LIMITATIONS None 

13. TYPE AND RANGE OF MEASUREMENT (definition of parameters to 

be measured while test is underway). Gas pressure, temperature, flow 

rate and composition. Also system power consumption. 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS None 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: None 

Station 

Equipment 

16. EQUIPMENT OPERATING CYCLE Continuous 

Frequency 

Time Duration 

17. EQUIPMENT LOCATION REQUIREMENTS Pressurized compartment 

18. SPECIAL MOUNTINGS REQUIREMENTS None 

Apertures 

Booms 

Windows 

Antennae 

Bracketry 

19. PRESSURE VESSELS - fluids, gases, etc. Gaseous hydrogen 

20. ELECTRO MAGNETIC INTERFERENCE (spurious generation, special 

shielding required, etc.) None 

21. MAINTENANCE REQUIREMENTS 

Ground None 

Space None 

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ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape None 

b. Film None 

c . Other Chart paper 

2. HANDLING (special equipment required to handle items being tested). 

None 

3. PACKAGING None 

4. CALIBRATION - alignment, deployment None 

5. JIGS AND FIXTURES None 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION None 

7. SENSORS (TRANSDUCER - OUTPUT SIGNALS) Self contained 

8. TRAINERS/SIMULATORS Ground atmospheric control chamber 

simulator 

9. INSTRUMENTATION - cockpit and/or laboratory (note effect of time 

sharing instruments with other experiments). Built into system 

10. RELATED SUPPORT EQUIPMENT 

a. Targets None 

b. Ground Stations None 

c. Tracking None 

d. Handling Equipment None 

11. AGE None 

12. ENVIRONMENTAL TEST EQUIPMENT Gas chromatograph or mass 

spectrometer 

13. FACILITIES None 

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ATTACHMENT C 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired) 

a. Altitude 

b. Inclination 

c. Epoch 

d. Ellipticity 

No requirements 

2. PLANE CHANGE None 

3. ALTITUDE CHANGE None 

4. TIME ON ORBIT 30 days 

5. TEST DURATION Continuous 

6. TOTAL NUMBER OF TESTS One 

7. TEST FREQUENCY Continuous 

8. INTERVAL BETWEEN TESTS None 

9. CREW TASK LOADS - man hours 15 

10. CREW TASK FREQUENCY Monitor equipment and record data 

every 4 hours 

11. FIELD OF VIEW REQUIREMENTS None 

12. GROUND CONTROL LIAISON DURATION Not known 

13. GROUND CONTROL LIAISON FREQUENCY Not known 

14. EXTERNAL TEST ITEMS: None 

a. Launched from Station 

b. Launched from resupply 

c. Launched from ground 

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ATTACHMENT C (Cont'd) 

TEST OPERATING CHARACTERISTICS 

15. QUALIFICATION TESTS (other than space) 

a. Ground Complete qualification required 

b. Atmosphere None 

lb. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT No rigid 

requirement except periodic monitoring 

17. HANDLING PROCEDURES No special procedures 

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ATTACHMENT E 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required One 

(1) Man's function 

(a) As part of test Provides "used" air for system 

(b) As technician conducting test Monitor and record data 

b. Crew skill requirements. Trained as technicians 

c. Manpower Profile 4 man hours total per week for periodic (every 4 

hours) monitoring and data recording 

d. Critical Functions None 

e. Work Positions Anywhere in pressurized compartment 

f. Time Controlled Tasks None 

g. Human Performance Measures None 

h. Physiological and Psychological Measures None 

i. Selection Factors None 

Training Requirements Astronauts must be thoroughly familiar with operation of equipment 

2. GROUND PERSONNEL None 

a. Number required 

(1) Man's function 

(a) As part of test 

(b) As technician conducting test 

b. Crew Skill Requirements 

c. Manpower Profile 

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ATTACHMENT E (Cont'd) 

MANNING DESCRIPTION 

d. Critical Functions 

e. Work Positions 

f. Time Controlled Tasks 

g. Human Performance Measures 

h. Physiological and Psychological Measures 

i. Selection Factors 

j. Training Requirements 

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ATTACHMENT F 

COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE Periodic and very slow 

2. FUNCTIONS TO BE MEASURED Gas pressure, temperature, 

flow rate and composition. Also power consumption. 

3. TYPE OF ANALYSIS REQUIRED Gas composition via gas 

chromatograph 

4. PICTORIAL DATA REQUIRED None 

5. REAL TIME MONITORING REQUIREMENT None 

6. DATA EDITING OR COMPRESSION None 

7. READ-OUT TIME Not known 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS Record data 

on chart paper or telemeter to ground 

9. MANUAL AND/OR AUTOMATIC CONTROL Manual 

10. SIMULTANEITY None 

11. GROUND COMMANDS REQUIRED None 

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ATTACHMENT G 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME 3 years 

2. FINAL DEFINITIVE TEST DESIGN TIME One year 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED Not known 

4. TYPE OF DEVELOPMENT TEST ITEMS 

a. Vacuum Chamber None 

b. Shaker Yes 

c. Thermal None 

d. Acoustic None 

e. Simulators Atmospheric control system chamber require 

long duration evaluation 

f. Aircraft None 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME One year 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Teat Three 

b. Atmospheric Test None 

c. Space Test Three 

7. DATE AVAILABLE FOR TESTS Test 1965, flight test 1967 

8. CURRENT DEVELOPMENT STATUS 

a. Proposed only 

b. Project or program is approved and test item is under study, 

breadboard stage, etc. Breadboard units are now under study and development 

c. Funds expended to date. 

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Experiment No. S- 1 3 

VAPOR COMPRESSION DISTILLATION WATER PURIFICATION SYSTEM 

I. Test Objective 

Verify and evaluate operation of the system. Conduct a time study of the 

test operator. 

II. Importance of the Test 

This test is needed for the development of water recovery systems. Testing in a space vehicle, such as MOL, is required because of the gravity sensitive 

heat transfer mechanisms involved in the reclamation process. 

Waste water reclamation may be necessary for manned space vehicles having 

a mission greater than two weeks and which use a power supply other than a fuel 

cell (which produces excess water). Vapor compression distillation is attractive for military applications since it can be made compact. The operation involves boiling and condensing which will require a zero gravity test of the system. This system will provide potable water for the vehicle. 

III. Description of the Experiment 

The basic elements of the system are an evaporator, a vapor compressor and 

a condenser in which the condensation occurs at a slightly higher pressure and 

temperature than the boiling. The higher temperature which results from the vapor 

compression, together with the heat released by the condensation process, provides the heat for boiling. Impurities are collected on a liner in the evaporator which can be replaced from time to time because the system operates on a 

batch process method. Liner replacement will be required about once in two weeks. 

a. Configuration of Test Items (See Attachment A) 

b. Test Support Equipment Required (See Attachment B) 

(1) Spacecraft. None 

(2) AGE. None 

c. Test Procedure (See also Attachment C) 

The purpose of the test is to operate and verify the performance of the 

system. The system must be set up and supplied with waste water. The quantities 

of both waste water input and purified water output should be measured, and a 

chemical analysis of the purified water must be made to verify the performance. 

(1) Man's Role. The working fluid (waste water and urine) will 

be provided by the astronauts during the mission. Under these conditions the 

fluid will be produced in space under the actual diet, environmental and zero 

gravity conditions. 

(2) Man's Utilization. Monitor the performance of the system and 

provide for the working fluid as noted above. 

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(3) Testing Sequence. No special testing sequence is required. The 

system is tested in a batch manner whenever a sufficient supply of waste water has 

accumulated. 

d. Category of Experiment (Omit) 

e. Cost (See Attachment D) 

f. Schedule 

(1) Hardware could be made available for test in 1965 

(2) A hardware flight readiness date of 1966 is reasonable 

IV. Participating Government Agencies 

Interested government agencies are the Aerospace Medical Research Laboratory, 

and the USAF School of Aviation Medicine, both of the Aerospace Medical Division, 

AFSC; the Flight Dynamics Laboratory of the Research and Technology Division, AFSC; 

and NASA laboratories at Houston end Langley. 

V. Additional Requirements 

a. Special Security. None 

b. Manning Description Summary (See Attachment E) 

c. Logistics. (Omit) 

d. Facilities 

Existing facilities can be used to develop and test this water purification system. No special facilities are required, but the system should be thoroughly 

checked out on the ground. 

e. Simulation and Training 

(1) Astronaut. A minimum of training will be required and no simulation is needed. 

(2)• Ground Personnel. None 

(3) Equipment. None 

VI. General 

a. Communications and Data Handling Requirements. (See Attachment F) 

b. Development Characteristics. (See Attachment 0) 

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ATTACHMENT A 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED VAPOR COMPRESSION DISTILLATION WATER PURIFICATION SYSTEM 

2. WEIGHT: 40 lb s 

3. VOLUME: Stored 3 In use 3 

CRITICAL DIMENSIONS - SHAPES Cube 1.44 ft on each side 

4. POWER (watts) 

a. Continuous 

b. Stand-by 

c. Average operating 50 

d. Peak 100 (start up only) 

e. Duty cycle 4 to 12 hours per day 

5. SPARES Negligible 

a. Volume 

b. Quantity 

c. Weight 

6. TOOLS No special requirement 

a. Volume 

b. Quantity 

c. Weight 

d. Power 

7. HEAT OUTPUT 50 watts 

8. STABILITY Not available 

a. Moving parts 

9. VIBRATION LIMITS Not available 

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ATTACHMENT A (Cont'd) 

10. SHOCK LIMITS Not available 

11. HAZARDS (fire, explosion, electrical, toxics, other) None 

12. TEMPERATURE LIMITATIONS None 

13. TYPE AND RANGE OF MEASUREMENT (definition of parameters 

to be measured while test is underway). Water flow rates and chemical 

analysis 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS None 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: None 

Station 

Equipment 

16. EQUIPMENT OPERATING CYCLE 

Frequency Intermittent 

Time Duration 4 to 12 hours per day 

17. EQUIPMENT LOCATION REQUIREMENTS Must be accessible 

18. SPECIAL MOUNTINGS REQUIREMENTS None 

Apertures 

Booms 

Windows 

Antennae 

Bracketry 

19. PRESSURE VESSELS - fluids, gases, etc. None 

20. ELECTRO MAGNETIC INTERFERENCE (spurious generation, 

special shielding required, etc.) None 

21 MAINTENANCE REQUIREMENTS 

Ground None 

Space Replace liner in evaporator every two weeks 

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ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape 

b. Film 

c. Other Notebook 

2. HANDLING (special equipment required to handle items being tested). 

None 

3. PACKAGING None 

4. CALIBRATION - alignment, deployment None 

5. JIGS AND FIXTURES None 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION None 

7. SENSORS (TRANSDUCER - OUTPUT SIGNALS) None 

8. TRAINERS/SIMULATORS None 

9. INSTRUMENTATION - cockpit and/or laboratory (note effect of 

time sharing instruments with other experiments). None 

10. RELATED SUPPORT EQUIPMENT None 

a. Targets 

b. Ground Stations 

c. Tracking 

d. Handling Equipment 

11. AGE None 

12. ENVIRONMENTAL TEST EQUIPMENT None 

13. FACILITIES None 

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ATTACHMENT C 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired) None 

a. Altitude 

b. Inclination 

c. Epoch 

d. Ellipticity 

2. PLANE CHANGE None 

3. ALTITUDE CHANGE None 

4. TIME ON ORBIT 30 days 

5. TEST DURATION 30 days 

6. TOTAL NUMBER OF TESTS One continuous test, but of an intermittent nature 

7. TEST FREQUENCY 

8. INTERVAL BETWEEN TESTS Not applicable 

9. CREW TASK LOADS - man hours 10 

10. CREW TASK FREQUENCY Once per day 

11. FIELD OF VIEW REQUIREMENTS None 

12. GROUND CONTROL LIAISON DURATION None 

13. GRQUND CONTROL LIAISON FREQUENCY None 

14. EXTERNAL TEST ITEMS: None 

a. Launched from Station 

b. Launched from resupply 

,c. Launched from ground 

15. QUALIFICATION TESTS (other than space) 

a. Ground Unit must be fully qualified on the ground 

b. Atmosphere None 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT No special 

sequence required. 

17. HANDLING PROCEDURES No special requirements 

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Exp No. S-13 

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ATTACHMENT E 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required One 

(1) Man's function 

(a) As part of test Yes. Supplies working fluids (waste 

water and urine) 

(b) As technician conducting test Yes. Monitor test 

and make chemical analysis of purified water 

b. Crew skill requirements None 

c. Manpower Profile Once per day for 10 minutes 

d. Critical Functions None 

e. Work Positions No special requirements 

f. Time controlled Tasks None 

g. Human Performance Measures None 

h. Physiological and Psychological Measures None 

i. Selection Factors None 

.)• Training Requirements Astronaut should be familiar with 

operation of system 

2. GROUND PERSONNEL None 

a. Number required 

(1) Man's function 

(a) As part of test 

(b) As technician conducting test 

b. Crew Skill Requirements 

c. Manpower Profile 

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ATTACHMENT E (Cont'd) 

MANNING DESCRIPTION 

d. Critical Functions 

e. Work Positions 

f. Time Controlled Tasks 

g. Human Performance Measures 

h. Physiological and Psychological Measures 

i. Selection Factors 

j. Training Requirements 

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ATTACHMENT F 

COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE Very slow 

2. FUNCTIONS TO BE MEASURED Water flow rates, power consumption 

3. TYPE OF ANALYSIS REQUIRED Chemical Analysis of purified water 

4. PICTORIAL DATA REQUIRED None 

5. REAL TIME MONITORING REQUIREMENT None 

6. DATA EDITING OR COMPRESSION None 

7. READ-OUT TIME Not known 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS Permanent 

records of system performance required 

9. MANUAL AND/OR AUTOMATIC CONTROL Manual 

10. SIMULTANEITY No requirement 

11. GROUND COMMANDS REQUIRED None 

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ATTACHMENT G 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT' TIME Two years 

2. FINAL DEFINITIVE TEST DESIGN TIME One year 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED Two 

4. TYPE OF DEVELOPMENT TEST ITEMS 

a. Vacuum Chamber 

b. Shaker Yes 

c. Thermal No 

d. Acoustic No 

e. Simulators No 

f. Aircraft No 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME None 

6. NUMBER OF TEST ARTICLES REQUIRED FOR 

a. Ground Test Two 

b. Atmospheric Test None 

c. Space Test Two 

7. DATE AVAILABLE FOR TESTS 1965 

8. CURRENT DEVELOPMENT STATUS 

a. Proposed only System has been studied and proposed 

b. Project or program is approved and test item is under study, 

breadboard stage, etc. 

c. Funds expended to date. 

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Experiment No. S-14 

SUMMARY 

PASSIVE PROPELLANT SETTLING SYSTEM 

I. Test Objective 

Prove feasibility of using surface tension forces (wetted and/or non-wetted 

surfaces in conjunction with intermolecular fluid forces) to control location of 

liquids in tanks during extended periods of zero gravity. Demonstrate feasibility 

of expelling only liquid and/or only gas from a tank containing both, when 

using a fluid control device employing surface tension forces. 

II. Importance of the Test 

The purpose of this experiment is to demonstrate feasibility of the use 

of "passive" positive expulsion systems. The term "passive" is used herein 

with reference to a system that uses surface tension forces, wetted or nonwetted surfaces, screens, baffles, etc. to keep fluid at the tank outlet so 

that only one phase of fluid (liquid or gas) is expelled from the tank during 

zero gravity conditions. 

Current operational techniques of fluid control at zero gravity employ 

"active" devices such as bladders or diaphragms that physically separate the 

liquid and gas in the tank. These techniques have been acceptable for many 

applications, but are not without limitations. The "passive" fluid control 

technique holds promise of being more universally applicable and may 

eventually result in lighter weight, more reliable, and less complex systems 

than possible through "active" fluid control techniques. 

The "passive" fluid control technique will have applications in 

many areas, e.g., propellant systems, life support systems, and power systems. 

This experiment concentrates on applications to propellant systems; however, 

results will be applicable to other areas as well. 

Application of bladder or diaphragm techniques has been limited by 

existing technology to relatively small tanks; positive expulsion of propellants 

from large tanks in main propulsion systems is typically accomplished by the 

use of small also rocket firings prior to main engine ignition. "Passive" 

settling techniques promise to provide both positive expulsion of propellants 

only (no gas), and control of propellant location in the tank so that vehicle 

e.g. is predictable and unchanged at main engine ignition. 

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TV° cryogenic propellants (LOX and Lfl2) and two storable propellants 

(N20

4 and N2

) are suggested for this experiment; however, a better choice 

might be made at the time of the test. 

It is expected that tests with the cryogenic liquids will be more difficult 

than those with storable liquids due to the difference between liquid temperature and the temperature of the environment surrounding the tank. A potential 

problesiis the accumulation of frost on the outside of the cryogenic propellant 

tanks. This frost would obstruct viewing the propellant. Frost accumulation 

may be prevented by either a zero humidity atmosphere or operation in a 

depressurized section of the station. 

The cryogenic liquids, LOX and 1112, have applications in life support and 

power systems, as well as propulsion, so the more difficult nature of experiments with these liquids may be justified by the usefulness of the data. 

a. Configuration of Test Items 

See Attachment A. 

b. Test Support Equipment Required 

See Attachment B. 

c. Test Procedure 

(1) Unstow tanks and place in observation position. 

(2) Still photographs of tanks at regular intervals. 

(3) At scheduled time, man applies disturbing forces to each tank by 

manual means or by placing each tank on acceleration table;he records 

the liquid behavior with the movie camera. 

(4) Replace tank to observation position until next test requiring 

disturbing forces and continue to record still photographs. 

(5) After last test using disturbing forces (and acceleration table), 

stow tanks and conclude experiment. 

(6) Prepare camera films and recorded accelerometer data for return to 

earth. 

See Attachment C for additional detail. Man's role is delineated 

in Attachment E. 

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Tests aboard the orbiting laboratory will serve to prove feasibility 

during extended zero gravity conditions and determine effects of disturbing 

forces created by reaction control system operation and propulsion system 

on-off thrust transients. These effects cannot be observed without orbital 

flight. 

III. Description of the Experiment 

The experiment will use small transparent tanks containing the test 

liquid and the liquid control device. The liquid position control device 

in each tank will represent that configuration judged best for eventual 

application to full-scale tanks containing that particular liquid. Cameras 

will be used to record the behavior of the liquid'in each of,the tanks. 

It is desirable to test the tanked liquid behavior during stabilized 

flight in order to observe any upsetting effects on the liquid induced by 

the small correcting forces of the attitude control and translation system. 

The astronaut will manually supply disturbing forces to the tank to observe 

their effect on liquid behavior. The disturbing forces applied should range 

from those small enough to only cause slight motion of the liquid-gas interface 

to those sufficient to break that interface and cause liquid-gas mixing. The 

observer will note the time for the fluid disturbances to damp out and the 

nature of the damping action. The equilibrium configuration reached after 

liquid-gas mixing in the tank will be recorded and any deviations from the 

intended stable position of the liquid in the tank will be noted. 

If weight and volume• budgets permit, it is desirable to have an 

acceleration table on board to supply controlled disturbing forces to the 

tanks. The acceleration table would use an electric motor to give short 

term continuous acceleration at any selected level. Desirability of both 

linear and rotational accelerations should be considered in design of the 

table. Movie cameras would record the liquid behavior when it is subjected 

to small accelerations. 

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d. Category of Experiment 

Omitted 

e. Cost 

See Attachment D. 

f. Schedule 

FY 65 Evaluation and determination of passive settling 

system design concepts and prelim hardware design. 

FY 66 Development of hardVare and prototype delivery. 

0-g aircraft flights for checkout, simulation 

and training using prototype hardware. 

FY 67 Procurement of test hardware. 

Integration of Hardware with other test gear and AGE. 

FY 68 Flight readiness. 

IV. Participating Government Agencies 

Sponsor: Research and Technology Division 

V. Additional Requirements 

a. Special Security 

None 

b. Manning Description Summary 

See Attachment E. 

c. Logistics ' 

Omitted 

d. Facilities 

See Attachment 0, Sec. 4. 

e. Simulation and Training 

The astronaut-test conductor will have to be trained in the test 

procedure and versed on the general results expected from the test. Be 

will be trained using test hardware. The training will not be extensive 

and he will not have to develop unusual talents nor acquire extensive 

specialized knowledge. 

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The man assigned to ground back-up duties during the flight teat 

should be trained similarly in test procedure with the astronaut. He 

should have the specialized knowledge concerning the scientific nature of 

the test that the astronaut will not have. 

VI. General 

a. Communications and Data Handling Requirement 

See Attachment F. 

b. Development Characteristics 

See Attachment G. 

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ATTACHMENT A 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED 

LOX tank may not require 

LEli tank 4 separate 

liquids for N

2

0

4 tank test 

N

2

H

4 tank 

Movie camera 

Still camera 

Number 

(2) 

Weight 

lb 

SizQ 

fti 

1 

1 

1 

1 

1 

1 

23 

6 

27 

17 

10 

5 

0.5 

0.5 

0.5 

0.5 

0.25 

0.1 

Tank shapes will be spherical or cylindrical with ellipsoidal domes 

, on each end. 

2. WEIGHT - (as stated above) 

3. SIZE - (as stated above) 

4. POWER - no significant requirement except for optional acceleration table. 

A few watts will be required for accelerometer instrumentation. It is 

assumed cabin light will be sufficient for photography. 

a. Continuous - none 

b. Stand-by - none 

c. Average operating - 50 watts 

d. Peak - 50 watts 

e. Duty cycle - acceleration table would be used intermittently over course 

of several days. May be used from once to 3 or 4 times a day. Total 

power required is estimated to be 25 watt-hours. Duty cycle requirements 

are flexible and can be arranged to avoid high peak power drain on . 

station power supply. 

5. SPARES - none 

6. TOOLS.- none required 

7. HEAT OUTPUT - essentially zero. May be slight heat absorption if cryogenic 

fluids are used. 

8. STABILITY - very slight disturbing forces are transmitted to the space station 

when test tanks are moved to study effect on liquid behavior. 

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9. VIBRATION LIMITS - no unique requirements 

10. SHOCK LIMITS - no unique requirements 

11. HAZARDS - teat tanks must be leakproof to prevent toxic gas from escaping 

to cabin atmosphere. 

12. TEMPERATURE LIMITATIONS - normal cabin temperature range is sufficient. 

13. TYPE AND RANGE OF MEASUREMENT 

Still and movie cameras will be used to record the behavior of the 

tanked liquid. Still photography vill be used at regular intervals to 

record any changes in the position of the liquid in the tank that may occur 

as a result of extended time at 0-g conditions. The movie camera will be 

used to record liquid behavior when disturbing forces are applied to the 

tanks. 

14. SPECIAL ENVIRONMENTALRAPIREMENTS 

Tests involving cryogenic liquids may have to be done in an unpressurized 

section of the space laboratory to prevent frost accumulation from obstructing 

view of the liquid through transparent tank walls. 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS - no unique requirements 

16. EQUIPMENT OPERATING CYCLE 

Frequency - intervals of several hours; one or more times a day 

Time Duration - several days 

17. EQUIPMENT LOCATION REQUIREMENTS - locate tanks so they can be handled and 

manipulated by man. 

18. SPECIAL MOUNTINGS REQUIREMENTS - cryogenic liquids will require insulated 

tank and mounts. 

19. PRESSURE VESSELS - tanks will be pressurized from a. few psia to 2 or 3 

atmospheres. 

20. ELECTRO MAGNETIC INTERFERENCE - none 

21. MAINTENANCE REQUIREMENTS 

Ground - cryogenic liquids should not be loaded until shortly before launch. 

Space - occasional venting of cryogenic tanks may be required. 

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ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

Film - still and movie. Lpg of times of photos. 

Accelerometer readouts of disturbing forces applied to test tanks will be 

recorded for later transmission to earth or recovery with the film. 

2. HANDLING - no unique requirements 

3. PACKAGING - stowage position for tanks will be different than test position. 

No unique packaging requirements are foreseen. 

4. CALIBRATION no unique requirements 

5. JIGS AND FIXTURES - optional acceleration table requires firm hold down 

when in use, 

S. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION - none 

7. SENSORS - accelerometers 

8. TRAINERS/SIMULATORS - need 06g aircraft flights to check out test articles. 

Astronaut will require pre-flight training (see Attachment E). 

9. INSTRUMENTATION- desire direct readout pressure gage on tanks. 

10. MATED SUPPORT EQUIPMENT - none 

11. AGE - propellant (liquid) loading equipment to fill test tanks. 

12. ENVIRONKRNTAL TEST EQUIPMENT - vapor detectors and pressure gages for 

checkout of no-leak tank. 

13. FACILITIES - no substantial requirement. 

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ATTACHMENT C 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS - normal station parameters 

2. PLANE CHANGE - no requirement 

3. ALTITUDE CHANGE - no requirement 

4. TIME ON ORBIT - 0.g is required. Minimum of several days is desired. 

5. TEST DURATION - few days 

6. TOTAL NUMBER OF TESTS - few per tank (4 tanks - total of 12-16 tests is 

typical) 

7. TEST FREQUENCY - one or more per day 

8. IBTMVAL BETWEEN TESTS - about 1 day 

9. CREW TASK LOADS - total man-hours: 10 or less 

10. CREW TASK FREQUENCY 

The experiment requires one man. A typical work schedule sequence is: 

10 min/hr for 12 hours (still photography) 

1 hour full time (movie photography) 

10 min/4 hours for 2 days (still photography) 

1 hour full time (movie photography) 

10 min/4 hours for 2 days (still photography) 

1 hour full time (movie photography) 

Work intervals may be altered if desirable to improve man's overall 

work-rest schedule. 

It may be possible to make still photography operations automatic, 

thereby reducing man-hour requirements, however this would require additional 

equipment not listed. 

11. FIELD OF VIEW REQUIREMENTS - no requirements 

12. GROUND CONTROL LIAISON DURATION - total of 5-10 hours of stand-by communications 

13. GROUND CONTROL LIAISON FREQUENCY - stand-by when astronaut•is handling tanks 

and taking data during test. 

14. EXTERNAL TEST ITEMS - none 

15. QUALIFICATION TESTS - passive propellant settling system in test tanks will 

be given functional checkout in 06g aircraft flights prior to space test. 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT - see No. 10 above and III-c. 

17. BANDUNG PROCEDURES - no dangerous procedures. Handling procedures developed 

in pre-flight training. 

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ATTACHMENT B 

MANNINO DESCRIPTION 

1. ASTRONAUTS 

a. Number required - one 

Man's function - 

Man's primary function is as test conductor. He will unstow teat 

articles as necessary and place them in test position. He will do all 

photography or a major 'part of it. His ability to supply the necessary 

disturbing forces to the liquid-containing test tanks greatly simplifies 

design of the test equipment. His judgement will be beneficial in 

applying the necessary magnitude of forces to result in the desired level 

of disturbance of the liquid. He will prepare data (film) for recovery 

and place it in the return vehicle. 

It is possible that testa of passive fluid control devices could 

be done on unmanned orbital flights, but with greater complication. If 

camera films are to be the data source, provisions for recovery will have 

to be made. Video telemetry might be used with some sacrifice in 

resolution and color. It appears that a manned test would have several 

advantages for initial feasibility demonstration. Camera film (color) 

may be used as a data source; recovery is simplified. Various camera 

angles and lighting conditions would be possible. Man, having a basic 

knowledge of test objectives, could use his intelligence in selecting, 

obtaining, and recording data. He serves a very important role in 

supplying different perturbing forces to the liquid under observation 

to observe their effect on liquid behavior. 

b. Crew skill requirements - no unique skill required. Must have pre-flight 

training. 

c. Manpower Profile - see Attachment C, Section 10 

d. Critical Functions - photography and application of proper disturbing 

forces to test tanks. 

e. Work Positions - no unique requirements 

f. Time Controlled Tasks - no unique requirements 

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g. Human Performance Measures - correlation of test data with previous data 

from pre-flight training. 

h. Physiological and Psychological Measures - none 

i. Selection Factors - none 

j. Training Requirements - astronaut should be thoroughly briefed in 

expected behavior of the liquid at 0-g and the results anticipated from 

the test. He should be an observer on 0-g aircraft flights when test 

hardware is checked out. He should have ground training in the test 

procedure for the orbital test. 

2. GROUND PERSONNEL 

a. Number required - one 

Man's function - 

Ground personnel should have participating role in development of 

test equipment, astronaut training, and stand-by during flight operations. 

b. Crew Skill Requirements - technically oriented personnel experienced 

in design of test hardware, test procedure, and objectives. 

c. Manpower Profile - required during portions of test when upsetting 

forces are applied to test tanks. 

d. Critical Functions - back-up knowledge 

e. Work Positions - ground communications station 

f. Time Controlled Tasks - none 

g. Human Performance Measures - none 

h. Physiological and Psychological Measures - none 

i. Selection Factors - broad knowledge and experience in developing test 

for space flight. 

j. Training Requirements - should be trained in test procedure same as 

astronaut conducting the test. 

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ATTACHMENT F 

COMMUNICATIONS AND DATA HANDLING 

1. DATA RATE - on-board filming as indicated in Attachment C, Sec. 10. 

Ground communications as necessary and determined by astronaut. May 

require accelerometer readout to ground of disturbing forces applied 

to tanks. Readout may also be recovered in return vehicle with film. 

2. FUNCTIONS TO BE MEASURED - liquid behavior in tanks. 

3. TYPE OF ANALYSIS REQUIRED - film will indicate liquid behavior resulting 

from disturbing forces as indicated by accelerometer readouts. 

4. PICTORIAL DATA REQUIRED - camera film. 

5. REAL TIME MONITORING REQUIREMENT - stand-by communications during test. 

6. DATA EDITING OR COMPRESSION - compression of accelerometer readouts 

is desirable if telemetered to ground. 

7. READ-OUT TIME - few minutes 

8. REQUIREMENTS FOR PERMANENT DATA RECORDS - no unique requirements 

9. MANUAL AND/OR AUTOMATIC CONTROL - as indicated in III and Attachment B 

10. SIMULTANEITY - none 

11. GROUND COMMANDS REQUIRED - as necessary for recorded data readout. 

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ATTACHMENT 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME - about one year 

2. FINAL DEFINITIVE TEST DESIGN TIME 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED - few 0-g aircraft flights 

for checkout of test articles. 

4. TYPE OF DEVELOPMENT TEST ITEMS 

a. Vacuum Chamber - for leak tests and checkout of no-frost design of 

transparent cryogenic liquid tanks. 

b. Shaker - as necessary to qualify for normal vehicle environment. 

c. Thermal - none 

d. Acoustic - none - 

e. Simulators - test procedure training (little equipment required) 

f. Aircraft - 0-g flights 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME - about 6 months 

6. NUM ER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test - a few of each type of tank used in the test are necessary 

for design verification and procedural training. 

b. Atmospheric Test - none 

c. Space Test - one to four test tanks are suggested 

7. DAZE AVAILABLE FOR TESTS - 1967 

8. CURRENT DEVELOPMENT STATUS 

. Air Force Research and Technology Division and the NASA Lewis 

Research Center have funded programs for the exploration and development 

of surface tension techniques for passive propellant control systems. 

These programs have laid a foundation for the technology of liquid 

control by surface tension forces and have suggested prototype designs 

for passive control systems. These studies should be carried to 

culmination in an orbital test. 

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Experiment No. S-15 

COHERENT E-M PROPAGATION AND ANTENNA LOADING 

I. Objective: To determine phase distortion and other effects due to 

the ionosphere on e-m emanation from satellites. A secondary objective is 

to investigate the problems of antenna loading and high power r-f distribution 

in the high vacuum and temperature extremes encountered in space. 

II. Description: The experiment will consist of a series of tests de. 

signed to measure the extent of phase distortion of the ionosphere in two 

way propagation of r-f energy. Calibrated ground targets will be used. 

Measurements will be made and recorded at both the ground targets and in 

the satellite. Simultaneous measurements, performed from the ground, 

of the existing atmospheric, tropospheric and ionospheric conditions will 

be made to provide correlative data. 

The astronaut will adjust the various controls for optimum system 

performance and also vary parameters to determine loss of performance. 

An antenna and T/R unit will be required in addition to such ancillary 

equipments as tape recorders, clocks, etc. Photographs will be taken to 

determine the extent of cloud layer, moisture content and to some extent 

other boundary conditions. 

The experiment will also determine the effectiveness of various 

design for loading the antenna with high peak powers during the experimentation. 

The astronaut will make repairs and adjustments as necessary to 

complete the experimentation. 

III. Importance of Test: The tests are needed to provide basic data 

for the design and development of a high resolution radar system. 

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IV. Vehicle Requirements: 

Power: Never more than 1 kw for short 

periods 

Volume: 10 ft3 

Weights: 250 lbs 

Stabilization: .05 °/Sec 

Aperture: Window for viewing antenna and 

antenna alignment 

V. Participating Agencies: 

RTD 

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Experiment No. S-16 

SOLAR X-RAY MONITORING 

I. Test Objective 

To monitor the solar X-Ray flux in certain selected bands to indicate solar 

activity. 

II. Importance of the Test 

The WI flights will occur during a period of maximum solar activity. Studies 

of the soft X-Ray region of the solar spectrum currently being undertaken may identify certain spectrum lines which are precursors to lethal solar flares.. Since 

soft solar X-Ray radiation can only be detected from above the atmosphere, it would 

be necessary under these circumstances to provide a monitoring device for.protection 

of the astronauts. Also,.material samples exposed to space environment will receive 

a substantial integrated dose of soft X-Rays. In order to understand property 

changes, it is important to determine the energy spectrum and time history of these 

X-Rays. 

III. Description of the Experiment 

Soft X-Rays will be detected with a gas-filled thin window proportional:counter 

The transmission of•the window and filling gas determine the wavelength region over 

which the detector is sensitive. This region will be subdivided into narrow Wavelength groups by amplifying the signal and sending it through a fivi-channel pulse 

height analyzer. 

a. Configuration of Test. Items 

Since X-Rays of this energy are readily absorbed by minute quantities of 

matter, the sensor windOw must be exposed to space with a clear view of the 

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. .Ai.. .)—Its 

sun. To maximize monitoring time, the detector should be mounted on the 

solar cell panels which will be oriented toward the sun during the sunlit 

portion of the orbit. If this is not feasible, then four or five sensors 

can be dispersed along the periphery of the unpressurized module in order 

to provide suitable coverage. The detector box dimensions are 4" x 4" x 3" 

deep. The electronics box including the PHA is the same size and can be 

separated from the sensor pox by a large distance. Weight of each box 

is estimated as 25 and power consumption is 2 watts continuous. A sketch 

of the instrument is sham in Fig. 1. 

The output from the electronics box are presently planned to be analog 

vcItages. These signals will be fed in parallel to the TM system and to 

a D.C. voltmeter in the MX. The astronaut can cycle through the channels 

with a simple switch to read the voltages. A warning flight will flash 

whenever the signal exceeds a preset level. 

b. Test Support Equipment Required 

1) The TM outputs from the electronics box consist of eight analog voltages. It is desired that these voltages be recorded as frequently 

as possible (every 1 - 10 seconds) on a tape recorder which is played 

back at high speed when passing over tracking stations. 

2) No AGE is required other than that for normal TM reception at tracking 

stations. 

c. Test Procedure 

As indicated in (a), no services are required from the astronaut other 

than occasionally checking output voltages. However, if the warning light 

threshold is exceeded, the astronaut would be expected to take whatever 

precautionary measures were practicable such as remaining in capsule 

during the solar storm, keeping shielding material around himself, etc. 

d. Category of Experiment 

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o. Cost 

Cost of furnishing units for MOL should be quite low, approximately $20K 

per unit for flight-qualified hardware, (See Section VI CO). 

f. Schedule 

Hardware could be made available by the end of 1964. 

IV. Participating Government Agencies 

Sponsor: OAR 

V. Additional Requirements 

None 

VI. General 

a. Communications and Data Handling Requirement 

The data consist of 8 analog voltages which includes S counting rates, 1 

high voltage monitor, and 2 temperature sensors. It is desired that the 

counting rates be recorded every few seconds. The other functions would 

not need to be measured more than once every few minutes. 

Data stored on an on-board tape recorder would.be read-out once. per 

orbit to a ground station. The information on the ground.station.tape 

would be decommutated, digitized, converted to physicalquantities, and 

merged with satellite ephemeris. The output tape from this operation 

would then be sent• to Aerospace for further analysis. 

b. Development Characteristics 

This experiment will be completely designed, fabricated, and flown on 

Program 162 vehicles in 1964. Improvements in design will certainly be 

made for those units to be flown on MOL. However, these are expected to 

be minor and final MOL design should be finished by the end of 1964. Due 

to the relatively simple nature of the experiment, any number of required 

items can be delivered within 90 days after design freeze. 

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--eao Electronics Proportional 

Counter 

III 

Solar Radiation 

30' Conical 

Field of View 

Detector Box 

4" x 4" x 3" 

20 

From 

Sensor 

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-Input Power 

Electronics Box 

4" x 4" x 3" 

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Fig. 1. Sketch of Solar X-Ray Experiment 

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Experiment No. S-17 

MATERIALS DEGRADATION AND MALFUNCTION ANALYSIS 

I. Test Objectives 

The purpose of this experiment is to evaluate degradation and analyze any malfunction of MCE. components and materials Under actual space flight conditions. The 

spacecraft and its auxiliary equipment will be used as the object of the tests. The 

primary goal of this experiment is to determine the cause of failure or degradation, 

if it occurs. A secondary objective is to determine whether or not current strict 

specifications on materials and components can be relaxed without sacrifice in 

reliability. Maintenance and repair functions will be demonstrated by the 

astronaut. 

II. Importance of Test 

1) The MCI, vehicle affords an opportunity to study the performance 

of critical materials and components under actual space mission conditions. The 

presence of man permits an unambiguous visual observation of any degradation or 

malfunction. This includes such items as seizure of bearings, cold welding of 

metal aurfaces, discoloration of thermal control surfaces, and erosion or 

sputtering of optical surfaces. Knowledge of degradation and minor malfunctions 

would permit the optimization of equipment for following missions especially those 

of longer duration. A specific course of action must be set up which permits a 

routine check of potential trouble areas since under normal conditions such 

Observations would be made only in the case of gross malfunction. 

2) Similar investigations might also be made on selected components 

which night be expected to fail.. This would mean, for example, the inclusion of 

various substandard components in the solar cell array or thermal control system. 

Present specifications, particularly cleanliness, for such components are extremely 

rigid. Some inflight experiments have suggested that these specifications might 

be relaxed without loss in reliability. An astronaut could evaluate selected substandard components with the view of relaxing standards. For example, a filter was 

inadvertently left off one solar cell in a recent test vehicle. To date this cell 

has shown no more degradation than the cells with. the filters. This is in contradiction to laboratory experiments. Removing the filters could greatly reduce 

the cost of such arrays. A second example is the delay in launching of a vehicle 

when the solar panels and thermal control coatings were accidently flooded with 

condensant. An elaborate cleaning procedure was needed before launch costing many 

hundreds of thousands of dollars. The possibility exists that all that was needed 

was to clean the surfaces with distilled water. 

3) The role of the man will be to determine degradation or malfunction 

visually and to perform the necessary operational tasks to determine the cause. 

Even in those cases where much of the data can be obtained remotely, the astronaut 

is needed to unambiguously pinpoint the exact nature of the malfunction. In some 

cases it might be of interest to return the defective component to the ground. 

III. Description of the Experiment 

I,. This experiment must be coordinated closely with the MOD vehicle design group. 

I. meaninzful description of the experiment is possible only after such discussion. 

Tho experiment will consist of detailing a continuous observation of selected MOD 

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components, and providing the necessary equipment to evaluate same. This 

equipment might include such items as a low power microscope with camera 

attachment, a portable reflectometer and a volt-ammeter. Typical of the 

experiments which might be performed are the following. 

1) Friction. Auxiliary components such as telescopes and cameras 

will have exposed bearings. These bearings might fail or degrade in performance. 

Torque measuring devices might be simply installed which measures the extent of 

degradation. The_ astronaut would attempt by visual observation to pinpoint the 

source of the degradation or malfunction. 

2) Solar Cell Degradation. A number of test solar cells will be 

placed in the array. This will include some without UV filters, and some which 

have had specified pre-flight preparation (i.e. a calibrated dirty fingerprint). 

This cell will be monitored remotely. If degradation occurs, the astronaut 

will attempt visually to pinpoint its exact nature. 

. 3) Thermal Control Coiting Degradation. Certain portions of the 

vehicle are not particularly thermally sensitive. Thermal control coatings, 

other than that to be used on the main vehicle, will be placed in these regions. 

These test coatings should be designed to test not only the material itself 

but also application technology. 

4) Cold Welding. Exposed metal surfaces might weld. If this occurs 

the astronaut would attempt to break the veld. In the case of a hatch, for 

example, he might have to force it open. A detailed description of the position 

of the welded area,,its magnitude and perhaps a photograph of the weld would 

be made. This would be of help in preventing future malfunctions of such 

components. 

B. Cost 

This experiment is relatively low cost. Simple. diagnostic instruments 

and tools, sample components and mechanisms, and post flight analysis coats 

should total less than 100 K. 

IV. Participating Gsyermnent Agencies 

Sponsor: .ROT 

Equipment: Supplied by MOL contractor. 

V. Additional. Requirements 

. This experiment must be coordinated closely with those agencies 

responsible for the design and construction of the Mai vehicle. 

a. Special Security: tone 

b. Manning Description Summary 

1) 30 Linutes par day average for one antronant. 

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ASTRONOMICAL PHOTOGRAPHY 

I. Test Objectives 

The objective of this experiment is to obtain direct photographs of various 

astronomical objects, including the sun, planets, and selected and extra. 

galactic objects, with a resolution exceeding any previously attained. Clearly, 

the increased detail visible on these photographs would contribute greatly to 

the better understanding of these objects. Experience gained through executing 

this program of astronomical photography would contribute greatly to the planning 

of future astronomical space telescope systems. 

II. Importance of the Test 

With the growth of Man's efforts to explore space, astronomy is -rapidly 

gaining significance, not only in an intellectual sense, but in a practical sense, 

as well. A capability for contributing to astronomical knowledge, such as will 

be provided by MOIL, should certainly be taken advantage of. Orbiting a camera 

capable of extremely high resolution photography is a unique, as well as an expensive accomplishment, and the opportunity to evaluate the role man can play in 

operating what is equivalent to an astronomical observatOry in space should be 

exploited to the fullest. 

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-CONFIDENTIALMit &cement contains Infonnation ettecerq the notional Monte of the United States within the treenine M It* Ispionega Laws, 

nee If, U.S.C., Sum 793 end 794, Ow irenandulen of which In arty 111011AIR to on unevittorlzed porton I. prohibited by law. 
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III. Description of the Experiment 

A. Background 

According to present planning, a major portion of the MOL payload is to 

be assigned to a optical system, capable of high resolution. The required 

resolution far exceeds the performance of ground-based astronomical telescopes, 

which are limited by the image blurring effects produced by the atmosphere. Because 

the primary mission of the camera does not require continuous operation, the system 

offers a potential for making a highly significant contribution to astronomy, if it 

could be used for this purpose, when not otherwise employed. 

As currently envisioned, the MOL camera system would have a unique capability 

offered by no presently planned astronomical satellite payload; namely, the system 

would make it possible to utilize photography for recording astronomical data, 

thereby exploiting the high information storage capacity of a photographic emulsion, 

and its ability to record fine image detail. 

It should be pointed out that this class of experiments has no counterpart 

in the astronomical experiments which comprise the current NASA Orbiting Solar 

Observatory (050) and Orbiting Astronomical Observatory (OAO) programs. These 

experiments deal exclusively with the measurement of ultraviolet and x-ray radiation 

from the sun and astronomical sources, which can only be recorded with telescopes 

operating above the earth's atmosphere. 

The experiments we are proposing for MOL do have counterparts in the Stratoscope II program, which aims at securing the highest resolution photographs obtainable, 

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478 -CONFIDENTIAL11.4 dosven••I epees, Wet sell.• effeclIn• th. • II la s ,e. 

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and also infrared spectra of selected astronomical objects, exclusive of the sun. 

A 36-inch telescope is carried by a balloon to altitudes of approximately 80,000 

feet, where it is expected that image degradation by the atmosphere will be reduced 

to the point where resolution approaching the diffraction limit of the telescope 

will be achieved. The balloon is unmanned, the telescope being controlled from a 

ground command station. The program, devoted exclusively to astronomical studies, 

has already made two preliminary flights. 

Clearly, the importance of conducting astronomical photography with the 

MOL camera system will depend primarily upon whether the system is capable of producing results which are significantly better than the data existing at the time 

MOL is in operation. This depends to a great extent upon the results of Stratoscope II, and also upon the performance specifications finally adopted for the MOL 

camera. Finally, irrespective of the direct astronomical results, MOL provides a 

unique opportunity to experimentally evaluate whether or not the presence of man 

is desirable in future orbiting astronomical observatory systems. 

At the time of writing, MOL camera system concepts are in a fluid state, 

but it appears rather well established that a prime technical objective will be 

to explore the practical limit of resolution which can be achieved with an orbiting 

camera system. 

B. Stabilization Problem: "Snapshot" Photography 

In examining the feasibility of conducting high resolution astronomical 

photography with the MOL camera, a fundamental problem immediately presents itself. 

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This arises from the fact that vehicle orientation stability performance is being 

specified to only meet the requirements imposed by ground photography, for which 

the exposure times are not expected to exceed 0.005 sec. With the exception of the 

sun, Mercury and Venus, all other astronomical objects have lower apparent surface 

brightness than does the sunlit earth, and therefore require longer exposure time, 

(assuming same emulsion, f-stop, etc.). In order to fully exploit the optics, it is 

essential that during the exposure time, image motion relative to the film must not 

exceed a small fraction of the dimensions of the diffraction disk. This is possible 

if: 

i. Exposure times are sufficiently short. 

ii. Vehicle orientation is stabilized during an extended exposure 

to a small fraction of the optical angular resolution. 

iii. Image motion relative to the film is cancelled out to sufficient 

accuracy by some kind of device located near the focal plane of 

the system. 

Clearly, the simplest condition is (i), because it permits "snapshot" photography, imposing a minimum of special requirements on the dverall MOL system. An 

estimate of the maximum allowable exposure time can be made, assuming that the 

vehicle angular rates do not exceed 0.001 deg sec-1, a value which we have been 

given to work from. For the assumed resolution of 0.1 arc seconds, the exposure 

time cannot exceed 0.01 sec. This value can be modified by noting that is is 

directly proportional to the assumed angular resolution and inversely proportional 

to the maximum vehicle angular rate. 

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The objects suitable for such "snapshot" photography, using panchromatic 

emulsions, are severely limited in number; namely, the Moon, Mercury, Venus and 

Mars. Unfortunately, the sun is so bright that special provisions are likely to 

be required, which remove it from this category. Even "snapshot" planetary photography is likely to involve a modification of the camera system. In order to 

minimize the exposure time, it appears to be advantageous to enlarge the image by 

means of secondary magnification, which permits emulsions of lower resolving power, 

but greater sensitivity to be used. The increased sensitivity then more than compensates for the decreased image brightness associated with enlargement of the 

image. Also, a greater selection of emulsion characteristics is available in this 

sensitivity range. This happens to be practical for astronomical photography, 

because the angular field to be photographed is generally small. 

"Snapshot" photography would therefore require an auxiliary, compact camera 

assembly consisting of enlarging optics, filter holder, shutter, film holder and 

magazine, viewing eyepiece and focusing mechanism. This camera assembly would 

either be located so as to intercept the image ahead of the focal plane of the 

primary camera, or would be designed to attach to the primary camera film transport assembly. 

It is important to emphasize that although important results can be 

obtained, restricting the system to operate in this fashion imposes a severe limitation on its usefulness for astronomical work. Note that photography of Mars, 

only marginally possible with the assumed value for vehicle angular rate, would 

not be feasible if this proved to be too optimistic an estimate. 

C, Solar Heating Problem 

By making it possible to point the primary camera at the sun, the usefulness of the system would be si nificantly extended, because the sun is an especially 

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interesting object to observe with high resolution, and it presents many exciting 

problems to be studied by this means. It should also be noted that the finest 

photographs of the sun yet taken were made with a telescope of 12-inch aperture, 

so that the gains achievable with a larger aperture are evident. The principal 

problem is that of heating of the secondary mirror of the camera, which intercepts 

the highly concentrated beam from the primary mirror. The flux of radiant energy 

incident upon the secondary may exceed a value SO times normal sunlight, depending 

upon the specific geometry adopted. Unless special provisions are made, this can 

detrimentally affect the optical figure of the secondary mirror, thereby impairing 

the resolution of the camera. There exist a number of approaches to the solution 

of this problem. One method would be to incorporate some form of shutter which 

would shield the secondary. except at the instant the photograph is taken. This 

is easier said than done, when the relatively large size of the secondary is taken 

into account. A fuzed quartz, or metal (beryllium) secondary might not require 

protection. Exposure times, evert through a narrow bandpass birefringent filter, 

are sufficiently short that vehicle stability is not likely to be a problem. 

D. Extended Exposure Capability 

We now discuss the highly important subject of how exposure times in 

excess of 0.01 sec can be made, without image blurring. 

(U), requiring extremely precise vehicle stabilization, is very unlikely to 

be technically feasible. Aside from the extreme precision of pointing required, 

the problem is aggravated by the large moments of inertia of the vehicle, and the 

many sources of disturbing torques.and vibration; e.g., moving machinery, involuntary movements of the astronauts, etc. It does, however, appear to be technically 

feasible to considerably tighten up the vehicle attitude stabilization, at least 

SSTA- 1 -9 

482 IhIe document contains Inhumation affecting the national defense of the United Stoles within the mooning et m. tipionotpt Lowe, 

Title le, U.S.C.. Section 793 end 794, the tfahVIIIIIIIHN Of which In any rnanner to on wethdhoolted person Is prohibited by low. 
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Exp No. S-18 

during the period that astronomical photography is in progress, by feeding the 

control system with three-axis attitude error signals derived from a pair of 

star trackers. These star trackers need not be boresighted with the axis of the 

main camera, and could be independently oriented to acquire sufficiently bright 

stars. It would be sufficient to maintain vehicle pointing within the dynamic 

range of some form of image motion compensation device (i.e., iii). This range 

could be typically two (conceivably, three) orders of magnitude greater than the 

ultimate tracking accuracy required;, 0., 0.1 to one minute of arc. Naturally, 

the closer the vehicle can be controlled, the less severe the problem of image 

motion compensation. Factors which would contribute to making this more feasible 

would be incorporation of cold gas jets in the vehicle control system and provision 

for reducing the coupling of the astronaut to the vehicle. 

There is also a distinct possibility that the astronaut may be able to 

accomplish the same function as the star trackers; namely, it may prove to be 

feasible for him to manually supply the vehicle attitude corrective commands to 

sufficient accuracy to allow the image motion compensation device to operate. 

This would be directly analogous to the manner in which an astronomer "guides" 

his telescope on the ground by supplying corrections necessary to maintain the 

image of a preselected guide star fixed with respect to the reticle of a guiding 

eyepiece. Either the visual tracking telescope associated with the primary camera 

system, or a guiding eyepiece suitably located in the focal plane of the primary 

camera could be utilized for this purpose. It should be noted that the astronaut 

may have to supply corrections about a third axis, as well. However, in view of 

the inherent simplicity of several star trackers currently available, it is felt 

advisable to utilize such devices to relieve the astronaut from the task of 

guiding the vehicle. 

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483 

This decumeet centotre InfematIon effecting the toffee& deems of IM United Steel wIthlti the meths@ el eM Isphstoise leen, 

Tide IS, 1.11.C.,, Settles 793 and 794, the transmission of which In ens rooms, to on sewed...trod penal It prohibited by law. 
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The basic principle underlying the image motion compensation devices that 

have been referred to is to utilize some form of low inertia device, with corresponding high frequency response and low power requirement, to sense image motion 

photoelectrically, and compensate for it. The simplest requirement would be to 

compensate only for image translation along two orthogonal axes lying in the focal 

plane. Depending upon the degree of vehicle control, rotation about an axis normal 

to the focal plane may or may not be required. Either the film can be translated 

(and rotated) by means of a double slide movement, or equivalent, or the film can 

remain stationary and image motion cancelled by translating an image transfer lens, 

or by tilting a mirror or plane parallel plate about two orthogonal axes, etc. 

The problem is somewhat simplified because the field of view requiring compensation will in most cases be relatively small; i.e., less than one minute of arc. 

Also, because the primary camera optics are corrected for a relatively large field, 

the excursion of the image off the optical axis will not be detrimental. 

The problem which appears to us to be potentially the greatest source of 

difficulty in accomplishing successful image motion compensation is vibration, 

because of the high frequency components which are likely to occur, and which would 

be very difficult to sense and to compensate for. We can only point out that such 

high frequency components would create a similar problem for ground photography, 

and because of the importance of the latter, the problem will no doubt receive 

careful attention. 

The above considerations suggest a feasible scheme; namely, 

iv, Vehicle stabilization to approximately 0.1 minute of arc 

utilizing star trackers (or the astronaut) as error sensors 

in the control system, combined with an independent image 

motion compensation device to supply the ultimate correction. 

SS TA- 1 -9 

484 CONFIDENTIALl'his document contains inlewronon affecting Roe notterrel defense 04 the Urged States widen the mooning el me espienege Law., 

Title is. U.S.C., Section 797 and 794, the transmission of which In eny manner to on unauthorised person Is prohibited by low. 
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It should be noted that once the features of (iv), necessary for exposures times 

exceeding 0.01 sec, are incorporated into the MOL system, then exposure times as 

long as tens of minutes are, at least in principle, equally feasible. This is of 

profound significance, because it would then provide MOL with an essentially universal capability for astronomical work. More specifically, it would transform MOL 

from a system of limited astronomical utility into a system capable of tackling some 

of the most significant problems in astronomy. 

E. Recommended Astronomical Objectives 

The following are a number of recommendations for astronomical photography, 

with a brief description of their significance. The recommendations fall into 

essentially three categories. 

Category A. "Snapshot" photography; exposures less than 

0.01 sec; minimum number of special requirements. 

Category B. Solar photography; requires solution of the 

problem of secondary mirror heating. 

Category C. Extended exposures exceeding 0.01 sec requiring 

improved vehicle stabilization, combined with 

image motion compensation. 

No claim is made for comprehensiveness. As previously noted, only a few 

problems fall into Category A. In passing on to Categories B and C the number 

of possible problems multiplies rapidly, and it is possible to only select a number of representative problems to serve as a guide. Naturally, the final selection 

of experiments to be performed, must be limited, and will depend upon a number of 

factors over which we have no control at the present. 

1. Category A. 

a. Planets 

Direct "snapshot" photography is possible for the planets Mercury, 

Venus and Mars. High resolution planets hoto ra by can contribute in many ways. 

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This docernent conta Ins Information o Hiss-tin° tha national defertee of the United State. within the meaning of wet espienol. lave, 

tffi. 1$, U.S.C., Section 793 and 794, the ins nose ssl on of which In any manner to an unauthorised person Is prohibited by tow. 
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-CONFIDENTIALExp No. 5-18 

For example, we can hope to achieve considerably better definition of surface 

details; namely, topographic- outline and relief for Mercury and Mars. The low 

contrast features in the cloud cover of Venus can be studied, and large scale 

patterns in the cloud structure can be analyzed to determine circulation patterns, 

polar orientation, etc. The finely resolved extended crescent of Venus near conjunction can be analyzed to determine the vertical extent and non-uniformities 

of the atmosphere. Improved measurements of the diameters of the planets can 

be made, as well as of their flattening. The diameters, combined with independent 

mass determinations, lead directly to improved mean densities for the planets, 

and the flattening measurements are essential to studies of their internal structure. 

. b. The Moon 

The Moon is certainly an attractive subject for study, expecially 

because of its important role in our nation's space program. However, it must 

be noted that NASA plans to observe the Moon at close range with the Ranger television system, and with the Lunar Orbiter photographic system. Also, in connection 

with the USAF Lunar Mapping Program, the Moon is being photographed and observed 

visually with large telescopes, rather intensively. It is therefore not clear 

at the present time whether lunar photography with MOL will be able to contribute 

significantly to the existing body of lunar data. Increasing evidence of the 

occurrence of transient active lunar phenomena suggests the possibility of an 

experiment in which the astronaut examines a preselected region of the lunar surface visually through the primary telescope for signs of such activity, and if 

an event is noted to be occurring, to photograph the affected region. Another 

possibility is high resolution stereoscopic mapping. It is recommended that a 

SSTA-1 -9 

486 -CONFIDENTIALThis deponent contains Information affecting the notional Worms of the United States within the meaning et Me espionage trines, 

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Expllo. S-18 

decision as to whether or not to incorporate lunar photography in the MOL astronomical program be deferred until such time that its usefulness can be better ascertained. 

a 

2. Category B 

a. The Sun 

The sun exhibits a wealth of complex, time varying detail when 

observed both in white light, and monochromatically. Because the temporal behavior 

of the various solar features is one of the most important aspects of the problem, 

all photography should be conducted in time-lapse fashion, at intervals not exceeding 

five seconds, over as long a continuous span as possible. The field of view should 

be chosen to be as large as practical. Direct, white light photography would record 

solar disk features such as granulation, sunspot umbrae and penumbrae, pores, faculae, 

and the sharp limb of the sun. The granulation is in itself a whole subject of 

study. Of significance are the distribution of granule sizes, with emphasis on the 

smaller elements. The shapes, temporal variation (mean lifetime for an individual 

granule is of the order of 8 minutes) and brightness (temperature) differences are 

highly significant data. Temporal changes take place more slowly in the magnetically stabilized sunspots. The changes are important to observe, and the relationship of the filamentary structure of sunspot penumbrae to sunspot magnetic fields 

is a challenging problem. Little is known about structure within sunspot umbrae. 

Modification of solar granulation in the vicinity of sunspots is of significance, 

because of the predicted inhibition of convection by solar magnetic fields. Pores, 

or incipient-sunspots are important features for study, because of their relationship to the formation and disappearance of sunspots. Faculas, best observed near 

the solar limb are of interest, because they occur where the magnetic field is 

locally intensified. Also near*the'limb the configuration of sunspots and the 

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This document contains Inform/non Often. the notional shtforWo of Ito tInitosl bola within the mooning of tno il.Ol.rw,. lows. 

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Exp No. S-18 

solar granulation can be analyzed to ascertain the vertical structures of these 

features. Finally, the sharpness of the solar limb is a subject of interest, 

because it represents a very high change in opacity of solar material, taking 

place within a very small vertical distance. 

Utilization of a narrow bandpass birefringent filter tuned to 

trasmit only the H-alpha line of neutral hydrogen would greatly expand the program of solar photography, because of the variety of new features which are made 

visible by means of this device. Of primary interest is the fine structure of 

the "second limb" of the chromosphere, which is highly relevant to the understanding of the nature of the solar chromosphere. Other features of interest 

at the limb are the fine structures in prominences, active spicules, and surges. 

Important disk features are the projected spicule structure, filaments, bright 

plages, sunspot-associated fibrillar structures, microflares (and flares). 

Sequentially tuning the filter passband over the line profile during the series 

of time-lapse exposures would provide Doppler velocity information; which is 

highly desirable when it comes to interpreting the photographic record. 

3. Category C. 

a, Planets and Satellites 

Direct photography is now possible for the rest of the planets; 

namely, Jupiter, Saturn, Uranus, Neptune and Pluto. The cloud belt system of 

Jupiter will reveal a wealth of detail, as should also the famous Red Spot. In 

the case of Saturn, there exists the possibility of discovering important new 

fine structure in the ring system. Both Jupiter and Saturn have satellites with 

resolvable disks, and diameter measurements would lead to improved density and 

albedo determinations for these objects. 

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488 -CONFIDENTIALThis stocvmont contains Informanon effecting, the notlenol defense of the United States wIthIn t is moonirej of aso !salamis* lows, 

TM. IS, U.S.C.. Section 793 and 794, the transmission of whirl In SOW MON'af to on imennherlsed person Is prohibited by low. 
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Color discrimination could be achieved by combining filters and 

emulsions to isolate narrow wavelength bands in the range 0.3 to 0.7 microns. 

This would be especially effective in the study of Venus and Mars. In the case 

of Mars, blue photographs provide information on the Martian atmosphere; surface 

features are veiled, and bright, white patches of clouds are sometimes visible. 

The extensive, and rapidly changing yellowish clouds, presumably dust, which 

occasionally occur are most conspicuous on photographs taken in the yellow. 

Red and near infrared photographs provide the best views of the surface, some 

features of which exhibit marked seasonal variations. Martian surface markings 

have long been the subject of much general interest, and also controversy. 

Polarization measurements, for which photography is not well 

suited, could still be made by differential measurement of images taken through 

successive orientations of a polaroid analyzer, using narrow wavelength bands 

throughout the spectrum. Such measurements would be extremely useful in analyzing 

the properties of the atmospheres of the planets, as well as their surfaces, when 

the latter are visible. 

Ultraviolet photography of the planets below 0.3 microns has so 

far not been possible. The incident solar flux rapidly decreases towards shorter 

wavelengths, and the planet surface brightness must reflect this decrease, as well 

as that due to selective absorption in its atmosphere, when this occurs. 

MOL might very well offer the first opportunity for ultraviolet photography- of 

the planets. In this case, resolution could be sacrificed if necessary to 

achieve the longer exposure times required. One particularly novel and important 

problem in planetary ultraviolet photography is singled out for discussion in 

a later section. 

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This deoireent consul/la Odom:oleo offectino the noilervil defense of the Ufilted boles width' the mord% of tee topieereoe 

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Measurement of of the very small angular disks subtended by the 

satellites of planets is extremely difficult, and can probably be best done 

visually. The most effective instrument for this purpose is the disk micrometer, 

which is an instrument permitting disks of various known size, whose brightness 

can be adjusted to match that of the object being measured, to be placed into 

the field of view for direct comparison. This would require some special 

training for the astronaut, but the results would be of great value. Of 

especial interest would be a measurement of the apparent diameter of Pluto, 

whose currently accepted value of 0.2 arc seconds As somewhat controversial. 

c. Comets 

Photography of the nuclear region of a comet, especially if one 

should happen to approach the vicinity of_ the earth at a favorable time, would 

be of considerable interest. This is one example of many types of experiments 

which, even though arising unexpectedly, should be injected into the program 

if regarded tb be of greater importance than the experiment they might have to 

displace. 

Passing beyond the solar system, we turn to the broad field of 

stellar astronomy. Here the number of interesting problems is virtually 

unlimited. We have selected from the vast number of problems suited for investigation by means of direct photography, several which we believe to be of 

particular importance, and at the same time, well-suited for MOL. 

d. Nearby Galaxies 

The nucleus of the nearest large spiral galaxy M31, the 

Andromeda Nebula, is a "semi-stellar" object, sharply defined, with an elliptical 

SSTA-1 -9 

490 -CAMDEN-TIMThis doaffrard contains information of fscrIng the notlasal defense of the United States within the meaning of net espionage low's, 

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Exp No. S-I8 

structure of dimensions 2.5 x 1.5 arc seconds. Little is known regarding the 

nature of this object, except that observed- kinematic features suggest a very 

large concentration of mass towards the center. Improved measurements of the 

light distribution in the region of the nucleus would also help to establish 

this concentration directly. The nucleus is sufficiently bright (equivalent 

to a star of magnitude 14.S) that a series of exposures varying from seconds 

to minutes, taken in two or three colors, would provide highly interesting 

data. Some other nearby spiral sytems, such as M33, M101 and M81 should be 

studied in a similar manner. It has been suggested that in the future, these 

semi-stellar nuclei may play an important role in establishing the cosmic distance 

scale, because they may all be intrinsically similar in size, and because it 

may be possible to observe them at great distances when space telescopes of high 

resolution can take advantage of their small angular size. 

e. "Quasi-Stellar" Radio Sources • 

Perhaps the most remarkable of all astronomical objects are the 

recently discovered "quasi-stellar" radio sources, because they are the brightest 

known objects in the Universe. First discovered as strong radio sources, their 

optical spectra have recently shown them to be very distant objects of high 

excitation. Despite their extreme distances, they are relatively bright optically, 

and it has been estimated that at least two of these objects are 100 times more 

luminous than a typical galaxy, though at the same time, considerably smaller. 

Even the brightest of them, 3C 273, cannot be distinguished from a 13th magnitude 

star, except for an associated whisp. The determination of_the angular size, and 

any resolvable structure, would provide fundamental information regarding their 

nature. 

CONFIDENTIAL SSTA- 1 -9 

491 

Td, documont contoirel Inletwatien ofiwtinp the national defense of IM United liettre within tho mooning of mm bole/else leen, 

TM. 11, U.S.C., Section 793 and 794, the tranordulon of attach In any manna• to on unewhorized Immo,. Is prohibited by low. 
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f. "Seyfert Galaxies" 

Apparently related to the "quasi-stellar" radio sources are the 

"Seyfert Galaxies". These rare spiral galaxies. are characterized by very bright 

and highly condensed nuclei, whose spectra contain lines of high excitation, for 

example, Fe VII, I.P. • 102 volts. Analysis of high resolution photographs of 

the nuclei of these galaxies would be similar to that previously described for 

the nuclei of nearby, normal spirals, and would improve our basic understanding 

of the phenomenon of nuclear emission in galaxies. 

g. Extremely Faint Galaxies 

The following experiment is perhaps the most significant contribution 

which MIX could make to astronomy. Though simple in concept, the experiment would 

require the utmost in optical and tracking performance of the MOL system. On 

plates taken with the 200-inch Hale telescope, of fields situated at high galactic 

latitudes, the faintest recognizable images correspond to 24th magnitude, and are 

of galaxies situated at the limit of the observable universe. The limit in faintness is set by the combination of smearing of images due to "seeing" produced. by 

the atmosphere, and by diffuse background radiation from the night-sky. Assuming 

that MOL permits a five-fold improvement in resolution, and a two-fold reduction in 

background radiation by elimination of the atmospheric component, the ultimate 

threshold of the MOL camera operating at f/30 should be 3 magnitudes fainter than 

the limit of the 200-inch telescope. A suitably exposed direct photograph of a 

preselected field near the galactic pole, even though achieving half this theore. 

tical limiting magnitude gain, would double the distance it'Which faint galaxies 

can be observed. 

SSTA-1-9 

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The experiments we have described up to now have involved only 

direct photography. It would seem much more likely that this particular use of 

the MOL camera system would be the easiest to implement, and it has been with 

this in mind that we have emphasized direct photography of astronomical objects. 

Assuming the capability for maintaining accurate pointing of the camera over an 

extended period of time; i.e., Category C, there are a number of other uses to 

which the camera optics can be put. The most obvious are ultraviolet and infrared 

spectroscopy and photometry. The number of problems which these two areas of 

astronomical research offer are, of course, virtually unlimited. We have previously 

pointed out that NASA is very heavily engaged in preparation for measurements in 

the ultraviolet. The following are two very interesting ultraviolet experiments 

which do not appear to be included in NASA's plans. 

h. Planetary Hydrogen Coronas 

Hydrogen escaping from the earth forms an extended envelope which 

resonantly scatters solar Lyman-alpha (1216A). The surface brightness of the 

geocorona in daylight is estimated to be 2 x 10-2 erg cm-2seelsteradian-1. If 

hydrogen is escaping from other planets, they should also have coronas. For Venus 

and Mars a possible source of neutral hydrogen is the photodissociation of water 

vapor, which produces the terrestrial component. Since only 10

12 hydrogen atoms cm-2 

are required to produce an optical depth of unity, the possibility of hydrogen 

coronas for these planets exists, in spite of the relatively small abundance of 

water vapor in their atmospheres, relative to the earth. From the orbit of MOL, 

scattered Lyman-alpha radiation from these planets would be viewed through the 

diffuse Lyman-alpha radiation of the geocorona. Neglecting any variation due to 

abundance of neutral hydrogen, the relative surface brightness of the planetary 

_CONRDENTI*L-- 

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mus doamr.nt centoins Information offeettnp the notional &tones of she United flatoe tolthIn the meaning at ine espionage taws, 

ntie 111, Ssidion 703 and 791, the transmission of which in any manner to an imouthortsed person Is prohibited by law. 
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Exp No. S-18 

hydrogen coronas would scale in proportion to the incident solar Lyman-alpha flux. 

Thus the surface brightness of hydrogen coronas enveloping Venus and Mars would be 

approximately twice, and one-half, that of the geocorona, respectively. These values 

are sufficiently high for detection against the background from the geocorona. 

To isolate Lyman-alpha radiation, a slitless spectrograph camera 

producing a Lyman-alpha image of the planet, such as used by NRL to obtain a 

Lyman-alpha photograph of the sun, could be used. The efficiency of such a device 

is estimated to be 10 per cent. In this case, high resolution is not required, so 

it would be advantageous to use a LiF condensing lens to reduce the image scale 

and convert the optical system to, say, f/3. Note that the requirements for precise 

stabilization are also correspondingly relaxed. The exposure required can be 

estimated as follows. Eastman Kodak SWR film has a sensitivity at Lyman-alpha 

S• 1/E . 35 

where E is the exposure in erg cm -2 incident on the emulsion required to produce 

a density of 0.6 above gross fog. The solid angle of an f/3 system is 0.09 

steradians. Assume the transmission of all the optics is 0.5. Then the time 

in seconds required to photograph the geocorona to this density is given by 

0.02 x t x 0.5 x 0.1 x 0.09 m 1/35, 

from which t 320 sec. 

Another approach would be to photoelectrically scan the planet 

image, suitably reduced in scale by a condensing lens, using a small Lyman-alpha 

mohochromator and a photomultiplier.with a LiF window. Although a single scan 

would suffice to establish the existence of a planetary hydrogen corolla, 

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the importance of determining both extent and shape would require a number of 

carefully spaced scans to be made, from which isophotes could be traced. 

i. Lyman-Alpha from Galaxies 

Because of the cosmological red-shift, the hope of increasing the 

limits of the observable universe depends on finding strong emission lines in 

the ultraviolet spectra of distant sources. The most promising line is Lyman-alpha 

(1216A), because it is the resonance line of neutral hydrogen, and consequently, 

is the strongest line produced in any galaxy. On the other hand, because neutral 

hydrogen resonantly scatters this wavelength, Lyman-alpha cannot escape from most 

galaxies. The objects most likely to emit Lyman-alpha are the "quasi-stellar" radio 

sources, in which hydrogen must be completely ionized. This is because the possibilit• 

of detecting Lyman-alpha escaping a completely ionized galaxy depends upon whether 

or not the neutral hydrogen that may exist between the observer and the galaxy is 

in resonance. Cosmological red-shift and large random motion associated with the 

"quasi-stellar" radio sources may displace Lyman-alpha from resonance, permitting it 

to reach the earth. 

In the spectrum of the most distant "quasi-stellar" radio source 

known at present, 3C 48, Lyman-alpha should be displaced to approximately 1650A, 

as a consequence of the cosmological red-shift. An observation of the spectrum 

of this source in the 1600 to 1700A region by means of a compact, very low 

dispersion (say, 1000A mm-1) spectrograph of high optical speed (say, f/I.5) 

would establish whether Lyman-alpha is observable. The exposure time for this 

16th magnitude object should not exceed 30 minutes, with a spectrograph of this 

type. Itshould be noted that in the case of a slit spectrograph, pointing error 

SSTA- 1- 9 

495 

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ThIs document eentalne Information eflocileg the national defense of the Weed Metes rattan IM rribanIrg et IMO !aplomb. Leen, 

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Exp No. S-18 

will not affect the definition of the spectrogram, but will only increase the 

time required to obtain the desired exposure by the length of time the image is 

off the slit. 

. SECRET SSTA-1-9 • 

496 - - 

(This page is Confidential) 

This doormen. anteing Inform:Men effecting 

page 

national defame of dm Wood SION within flw mooning of Pe Isplenope Lew% 

rd. IS. U.S.C.. Section 793 and 794, do trorandision of which In ony wannw to on unovehorised person Is prohibited by low.