NRO APPROVED FOR 

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V171 F177.rfi) 

Li Lco 

"E`C-EF NRL MemorandumReport 1507 

Copy No. ri of 25 Copies 

MANNED ORBITAL LABORATORY TECHNICAL PANEL 

FIRST PRELIMINARY REPORT (U) 

DR. W. C. HALL, CHAIRMAN 

17 March 1964 

Exempt from Distribution to Defense 

Documentation Center in Accordance 

with DOD Instruction 5100.38. 

U. S. NAVAL RESEARCH LABORATORY 

Washington. D.C. fExcluded from automatic 

downgrading and declassification. 

-103';172 
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CONTENTS 

List of Figures 

List of Tables 

References 

Section I Introduction 

Section II Ocean Surveillance 

1 

6 

Section III Command and Control 20 

Section IV Communications 21 

Section V 23 

Section VI FLINT 25 

Section VII Bio-astronautics 27 

Section VIII General Science 29 

Section IX Summary 32 

• .* 

APPENDIX A 

Copies of Recommended Experiments 

as Submitted to Manned Orbital Laboratory Technical Panel 

Item No. Title Page No. 

1 An Investigation in Multi-sensor Military Surveillance A-1 

2 Comments on MOL Ocean Surveillance A-40 

3 Proposal for a Photo Interpretation Experiment 

to be Conducted in a One-man GEMINI Satellite A-42 

4 Photographic Ocean Surveillance Test Program A-49 

5 Optical Surveillance Sensor Experiment A-54 

6 MOL Forward-Looking Radar A-56 

7 Global Television Surveillance A-65 

x. t).1 t.:); ,r4.. ) 
13 

14 

15 

16 

17 

18 

19 

20 

21 

CONTENTS (CONT'D) 

Title Page No. 

Infrared Mapping A-92 

Electronic Surveillance of Ocean Targets 

for Ocean Surveillance A-116 

Identification of Ships A-130 

Beacon System A-131 

Electromagnetic Communications A-133 

 A-138 

Space Studies Using Far-Ultraviolet Image Orthicon 

Aboard a Manned Satellite A-139 

Electronic Surveillance A-167 

Project ARGUS Contributions to MOL A-171 

Heavy Particle Dosimeter A-178 

Nuclear Radiation Perspnnel Monitor for Space Flight A-184 

Orbital Plasmas Characteristics A-201 

Electron Density and Effective Temperature A-207 

Proposal for Airglow Horizon Photography From the 

Manned Orbital Laboratory A-212 

Proposal for Cosmic Ray Observations Aboard the MOL A-215 

Proposal for Direct Observation and Photography of the 

White-Light Corona of the Sun and Surveillance of the 

Sky Close to the Sun A-236 

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Item No. 

8 

9 

10 

11 

12 

22 

23 

24 Proposal for Airglow Spectroscopy From the MOL Spacecraft A-244 

25 General Science A-248 

APPENDIX B 

Complete Listing of All Proposals for Experiments Received by the 

Manned Orbital Laboratory Technical Panel B-1 
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No. 

16 

30 

31 

9 

7 

1 

3 

LIST OF FIGURES 

Figure 1 Groupings of Proposals Received for Navy Experiments 

Figure 2 Coverage Obtained with Simple Non-rotating Radar 

Antenna of Table 2 

Figure 3 Hardware Integration Concept for Ocean Surveillance 

Figure 4 MOL Engaged in Ocean 

Figure 5 Ocean Surveillance 

Figure 6 Ocean Surveillance 

Figure 7 Ocean Surveillance 

Figure 8 Communications 

Figure 9 

Figure 10 ELINT 

Figure 11 Bio-astronautics 

Figure 12 General Science A 

Figure 13 General Science B 

Surveillance 

Situation 1 

Situation 2 

Situation 3 

LIST OF TABLES 

Table 3 

Table 4 

Table 5 

Astronautic Missions of Naval Interest 

Technical Information on Space-borne Sensors Useful 

for Ocean Surveillance 

Estimated Cost for Ocean Surveillance Experiment 

Estimated Weights for Ocean Surveillance Experiment 

Over-all Summary of Experiments Recommended for MOL 

Table 1 

Table 2 

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REFERENCES 

(a) BUWEPS Secret ltr RT-11:RFS Ser 00316 of 7 Feb 1964, Subj: 

Technical Panel for Manned Orbital Laboratory Experiments; 

formation of 

(b) NRL Conf ltr 7000-9:WCH:jsk of 3 Mar 1964, Subj: Minutes of 

Meeting of Manned Orbital Laboratory Technical Panel 27-28 Feb 

1964 (U) 

(c) INS "STARLIGHT Study Summary Report - Volume I" of Sep 1962 

• ' # 

iv 
• 

.JULY 2015 

SECURITY 

This document contains information affecting the national defense of the United States Within 

the meaning of the Espionage Laws, Title 18, 

U.S.C., Sections 793 and 794. The transmission 

or revelation of its contents in any manner to an 

unauthorized person is prohibited by law. 

• ie 
NRO APPROV FOR 

RELEASE 1 JU Y 2015 

/1/ )11,i true 1-9-r-71 /51 

/ 7 h4"-1-11' 

MANNED ORBITAL LABORATORY TECHNICAL PANEL. 

FIRST PRELIMINARY REPORT 

Section I 

Introduction 

The Secretary of Defense has recently announced a manned space 

project which has been designated the Manned Orbital Laboratory (MOL). 

The Air Force is to manage this project. The MOL program is to have 

a twofold purpose; basically it is intended to assess man's utility 

and ability to perform a military mission in space; secondarily, it 

will include those military experiments which can make best use of the 

MOL vehicle and which at the same time can be accommodated. Since 

the National Aeronautics and Space Administration may also enter into 

the program, other than military experiments may be carried. The MOL 

program presents an excellent opportunity for the Navy to investigate 

and establish man's usefulness in space in the performance of naval 

missions. The investigations of the MOL program are intended to test 

or check only those components or parts of a military system which 

require the presence of man in space to determine the potential 

usefulness of the complete military system which could follow. 

At present the MOL program stands in need of justification within 

the Department of Defense kfi order to obtain the necessary approvals 

for the preparation of a complete technical development plan as a 

first step in getting the program under way. 

In order to prepare the Navy's plan for MOL experiments, by 

reference (a) the Bureau of Naval Weapons established a MOL Technical 

Panel composed of members from each bureau, the Office of Naval Research, 

the Institute of Naval Studies, and such other naval field activities 

or laboratories as were interested in or capable of making a contribution. The Naval Research Laboratory was requested to act as host 

activity and to designate the Panel chairman. The function of the 

Panel was to generate in detail a series of space experiment proposals 

suitable for flights on the MOL. A summary report recommending an 

array of experiments and supported by preliminary cost estimates, 

development schedules, experiment plans, and recommended sponsors for 

each experiment (a Navy laboratory or a contractor) was to be submitted 

to the Bureau of Naval Weapons for approval and ensuing action to 

assign specific follow-on responsibility and for funding support. 

The first meeting of the MOL Technical Panel took place on 

27-28 February 1964 at the Naval Research Laboratory under the chairmanship of Dr. W. C. Hall of the NRL. Minutes of this meeting have 

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been provided to all participants (reference [b]). Those in attendance 

at this meeting as members of the MOL Technical Panel are listed in 

reference (b). 

While further meetings of the MOL Technical Panel will be needed 

to complete the assignment of the Panel, the urgent time schedule 

now being followed in the development of the MOL program makes it advisable to submit a preliminary report at the present time. This 

preliminary report will discuss in some detail the concept for 

experiments bearing upon the Navy missions and provide all information 

that is available at the present time. It will also list briefly 

some of the more important work yet remaining to be done. The text 

of the report has not been circulated to Panel members for concurrence, 

again owing to lack of time, and hence represents the opinions and 

work of only a small number of the whole Panel. For this report, 

therefore, the Chairman alone must accept responsibility. 

The guidelines provided by the Navy for the MOL Technical Panel 

were simply the following: that ocean surveillance, anti-submarine 

warfare, and command and control missions were to be given primary 

emphasis. 

There were several approaches which could be followed by the 

Technical Panel in performing its mission. It could proceed logically 

to develop a series of experiments based upon concepts of the Navy 

mission to provide global coverage of the oceans; thus the Navy is 

required to maintain glaba3 surveillance over surface shipping. 

Similarly it needs surveillance over the globe for submarine activity. 

For both purposes it needs all-weather orbital sensors capable of 

detecting the presence of and classifying ocean going ships and submarines. In each case the same barrier to progress is reached, namely, 

the inability of the present state of the art to provide sensors in 

spacecraft capable of obtaining the necessary information for full 

performance of the mission. 

A second approach being followed by the Space Systems Division 

of the United States Air Force is to study thoroughly all suggested 

experiments which can be performed in the following general areas: 

(1) reconnaissance and surveillance; (2) other missions - including 

satellite survivability; satellite logistics, maintenance, and repair; 

and finally satellite orbital command posts; (3) bio-astronautics; 

and (4) general tests or general science. 

The approach chosen by the MOL Technical Panel is a variation 

of the second approach. Thus the MOL Panel chose to consider those 

military missions which are now possible considering the state of the 

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art, and of interest to the Navy. Each possible experiment needs to 

be reviewed critically to determine whether it involves man in an 

essential manner; it needs to be reviewed to determine whether it is 

of unique Navy interest; it needs to be reviewed to determine whether 

it is being done now by unmanned satellites. Table 1 presents a number of astronautic missions possible in the time period of 1968-1970 

and of interest to the Navy. Opposite each of the astronautic missions 

there listed may be found an appropriate comment. 

Table 1 

Astronautic Missions of Naval Interest 

Ocean Surveillance The SAMOS Program of the AF 

has been active since 1961. 

Command and Control 

General Science 

Communications 

The STARLIGHT Report recommended space-oriented command 

ships. 

NASA has OSO, OGO, OAO, and 

Explorer programs under way. 

TELSTAR, RELAY, SYNCOM, LOFTI, 

COMSAT Programs, etc., are now 

under way. 

Electronic Countermeasures Of general interest to all 

Services. 

ELINT • OD 

Meteorology Present major programs are TIROS, 

NIMBUS, and the Operational Weather 

Satellite. 

Navigation TRANSIT and the ADVANCED TRANSIT 

programs are under way. 

Bio-astronautics NASA has a series of six biosatellites planned. 

(Continued on next page) 

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(Continued from previous page) 

Orbital Defense 

Naval Ocean Data Satellites 

Precision Delivery Satellites 

Logistics, Maintenance, 

and Repair of Satellites 

Geodesy 

Anti-submarine Warfare 

The DYNASOAR Program has been 

cancelled for reasons of economy. 

NASA has a program for data collection satellites under preliminary 

study. 

No Navy mission is now foreseen. 

The ANNA Program exists to fill 

this requirement. 

The state of the art is not 

sufficiently far advanced. 

* * * 

The MOL Technical Panel received in all 89 experiment proposals, 

or topic ideas, for Navy astronautic systems. The Panel assumed 

that astronautics was to be regarded purely as a technology which 

could be used to improve the capability of the Navy to operate globally 

and maintain control of the seas. With this assumption, it arrived 

at the grouping given in Alopendix . B for these 89 experiments, and 

shown by Figure 1. It will be seen that the two groups receiving 

the greatest attention from the MOL Technical Panel members are those 

of Ocean Surveillance and General Science. 

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Section II 

Ocean Surveillance 

In view of the obvious importance of ocean surveillance to Navy 

missions a separate study group consisting of Panel representatives 

from the Institute of Naval Studies, the Applied Physics Laboratory, 

the Naval Air Development Center, the Naval Research Laboratory, the 

Naval Photographic Interpretation Center, and the Bureau of Naval 

Weapons met at the NRL to develop further this topic. The problem 

in ocean surveillance is to survey ships, harbors, and ocean lanes. 

It is necessary to detect and classify all vessels found in either 

harbors or ocean lanes. The problem is complicated by the fact that 

the oceans are vast, that the targets are continually on the move, and 

thabsood data must be obtained to be useful. Tardy, incomplete, and 

inaccurate data is of little value. It is obvious that an astronautic 

system cannot supply the total requirement but only supplement other 

means of maintaining ocean surveillance. It is probably true that 

the Navy's problem is not the same as that of the AF or the Army. 

Thus, the Navy's problem revolves around keeping track of ships on 

a global basis. The targets are relatively large but continually on 

the move. Hence, the naval requirement seems to be for a system of 

nominal resolution and very wide coverage. 

Any consideration of the problem of ocean surveillance must 

begin with an understanding of the state of the art for the available sensors. Table II gives in summary form the most essential information with respect to each possible sensor. Some changes may be 

required in the final selections. It may be necessary, for example, 

that an optical system be procured having a 96"-focal-length lens, 

rather than the 48"-focal-length lens given in the table, to secure 

the desired resolution of 12' and permit at the sane time some degradation of performance of the camera while in the spacecraft. The best 

choice for radar is similarly unsettled at the present time. Two 

possible choices are given: one with a rotating antenna system and 

one without. Note that the radar system with the non-rotating antenna 

leaves large gaps in the coverage of the earth below the spacecraft. 

See Figure 2 for coverage obtained with the simple non-rotating antenna 

proposed. 

The concept for ocean surveillance developed by the sub-panel is 

as follows: there must be advanced detection of all shipping targets 

followed by classification by the astronaut, appropriate data processing, and read-out by ground stations. 

To perform the function of detection in advance of the satellite 

the most promising sensors seemed to be radar, television, and infrared -

in that order. It is desired that this advance detection take place 

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as long as one minute in advance of the time when the spacecraft is 

over the target on the earth. At the orbital rate of travel of the 

spacecraft this corresponds to 250 miles; thus the detection range 

for the broadly scanning sensor systems should be approximately 250 

miles in advance of the spacecraft. All-weather radar systems having 

this capability can be devised. Television and infrared systems can 

provide initial detection under favorable conditions where the 

weather is clear or clouds are only thin or broken. It is recognized 

that optical systems can also perform this function when the weather 

is clear or when clouds are thin and broken; but optical systems of 

high-resolution, particularly, are not as well adapted for automatic 

searching of large areas as is radar. 

After the target has been detected the next step involves classification. Here, provided the weather is clear, a set of binoculars 

having variable magnification and directed by the astronaut to the 

coordinates indicated by the advance detection means would be used 

to find the target. If desired, then, through servo controls, the 

high-resolution camera can be caused to photograph automatically the 

target under examination by the astronaut. The pictures would be 

used for detailed study on a deferred basis. If the weather is not 

favorable, then the astronaut must depend upon other systems to determine friend from stranger. The directivity of an IFF-type interrogating device operating from the radar antenna or a separate 5-foot 

dish mounted on MOL is good enough to separate ship from ship under 

most conditions. The ELM-21:1s° can, provide from coarse to good resolution and separate "friend'' from "stranger." The same is true with 

respect to ultra-high-frequency beacons carried by friendly merchant 

shipping or aircraft. 

The third part of the ocean surveillance concept is that automatic 

position determination must be provided to the astronaut. This should 

record automatically the coordinates of any target selected by the 

astronaut. Such a system can be devised depending upon ephemeris 

data carried within the orbiting capsule, a gyro-stabilized platform 

and means for relating the position of the classification device or 

camera with respect to the MOL vehicle attitude. There must be storage 

of all classification information provided by the astronaut. It may 

involve no more than operation of push buttons: There must be capability for command read-out of all data stored at such times as when 

the MOL capsule is over a friendly ground station desiring such information. Finally, there must be means within the data processing for 

instructed search to be initiated by ground command and acted upon 

by the astronaut. The command for instructed search given by the 

ground stations may be stored automatically for delivery to the astronaut at the proper time in orbit. 

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The astronaut may at times be saturated by targets; therefore, 

data processing techniques must be employed to reduce this problem. 

Automation must be provided wherever possible. High-resolution film 

must be used to record the nature and position of selected visible 

shipping and harbors and their contents for later study and classification by the astronaut. Provisions for directed search and classification aids are needed to limit demands made upon the astronaut. The 

several factors involved in the concept of the integration of the 

hardware for this experiment are shown in Figure 3. 

Figure 4 provides a view of the MOL astronaut engaged in ocean 

surveillance using his search or detection equipment to illuminate 

areas some 250 miles in advance for detection purposes and using his 

optical and other systems for inspection of targets detected. 

Three situations have been devised to illustrate the usefulness 

of ocean surveillance capabilities which can be provided the Navy 

by a manned astronautic system. Figure 5 is the layout for the first 

situation which illustrates the problem of ocean surveillance with 

respect to Cuba. There it is required that an unfriendly country be 

kept under surveillance to determine its shipping both in ocean lanes 

and in harbors, and the departure ports as well as the terminal ports. 

In the performance of this mission the astronaut provides the following contributions: (1) he can be selective and look only for certain 

kinds of shipping; (2) he can concentrate on certain areas and spend the 

whole of the time heisoin the area of a fixed target (e.g., Havana - 

approximately two minutes) in surveillance of that target alone; 

(3) he can filter out a target from a low contrast or noisy background; 

(4) he can give rapid response to a command for search, the time 

required, if his orbit is over the target, being less than the orbital 

period; (5) he can make optimum choice of the sensors to be used; 

(6) he can optimize performance of the system by providing necessary 

adjustments; (7) he can improve reliability; (8) he can enhance 

accuracy. One further point in favor of man is that our capacity 

as a nation to orbit increasing payload, thus enabling man and his 

necessary environment to be included, seems likely to improve at a 

faster rate in the next ten years than is our capacity to orbit 

reld.able, sophisticated systems able to replace man. 

Situation 2 shown in Figure 6 depicts a condition existing when 

directed search is to be instituted by ground command In this case 

an area of the Sulu Sea is known to contain four ships in the locations marked in red in the diagram. It is also thought to contain 

two ships in the general location shown in blue on the diagram. The 

problem is to identify these unknown targets and provide their location. The instructions to the astronaut can be stored in the data . 

processing equipment of the vehicle from any ground station over which 

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the astronaut passes. At the appropriate time the astronaut will be 

given signals from his data storage to inspect the area outlined by 

the dotted lines. If he is able to use the optical systems he is 

likely to obtain ready classification of the targets. If he is forced 

to use all-weather sensors then he can determine whether the unknown 

targets are captured by his sensors, whether they are friends or 

strangers, and their positions. If he is able to detect no target 

but can see the surface areas whose coordinates are given he has provided information which may help to determine whether or not the unknown targets are submarines. 

Situation 3 is depicted in figure 7. Here the problem is to 

determine the trend in world shipping as a portent for some future 

operation of an unfriendly power. The need is to inspect something 

like twenty ports around the world, e.g., to catalog and count the 

ships in ports and in lanes to these ports. The illustration chosen 

is that of a northern port where certain lanes may be ice-closed. 

With optical equipment in suitable weather the astronaut can survey 

with high resolution the harbors and the approaches to the harbors 

and classify shipping in these areas. He can also determine which 

shipping lanes are open and which are closed by ice. If weather is 

unfavorable he can count ships which are in the lanes using equipment 

such as radar, IFF, ELINT, and beacons. At night, in favorable 

weather, he may obtain a shipping count through the television system. 

Here again man gives selectivity or the ability to look for only certain kinds of information; he gives the ability to concentrate on certain areas; he gives the -capability.for optimizing all sensors used; 

he gives rapid response; and he can correlate and filter data. In 

short, he provides more accurate, more reliable data. 

In Appendix A may be found a more complete development of the 

Ocean Surveillance Mission for MOL. Following a meeting of the subpanel on Ocean Surveillance, Dr. R. A. Summers of INS and Dr. Roscoe 

Bartlett of APL jointly prepared a report on the over-all concept. 

This is found in Appendix A as Item 1, "MOL An Investigation in MultiSensor Military Surveillance." APL. A report on the use of optical 

sensors was prepared by of NPIC.(Item 2). This 

is supplemented by other material previously prepared at NPIC and 

NADC on the problem of ocean surveillance by optical sensors 

(Items 3 and 4). The radar sensor was studied by Mr. Irving Page of 

NAL (Item 6). Mr. William Lee of NADC had submitted before the time 

of the Panel meeting a proposal for surveillance by television (Item 7). 

This has not yet been modified to incorporate the concept of advance 

scanning ahead of the MOL vehicle. NADC also submitted early a proposal for infrared mapping (Item 8). This, too, has not been modified 

to incorporate forward scan. Mr. Samuel Hubbard of the Bureau of 

Naval Weapons studied the question of surveillance by ELINT and 

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submitted an experiment (Item 9). The use of IFF for sensors was looked 

into quickly by Mr. C. V. Parker of NRL (Item 10). A very brief proposal for a beacon experiment was submitted by NADC (Item 11). On 

the urgent time scale followed in the preparation of this report little 

more could be done to reduce inconsistencies and provide a complete 

definition of the integrated plan for the Ocean Surveillance experiment. 

Table 3 is a preliminary estimate of the total cost to fund an 

ocean surveillance experiment on means for satisfying the naval mission 

requirements. In summary, it is a system utilizing radar, optical, 

television, infrared, ELINT, IFF, and beacon-type sensors. None of 

these sensors alone can do the job. All of these sensors used intelligently together can obtain great amounts of valuable information. 

An estimate of the over-all weight of hardware for the ocean surveillance experiment is included in Table 4. 

Table 4 

Weight Estimates for Ocean Surveillance Experiments 

Component Weight 

Integration and Data Processing 350 lb 

Radar 1,500 lb 

Optical Sensors.- 0 800 lb 

Television 150 lb 

Infrared 150 lb 

IFF 25 lb 

ELINT 200 lb 

Beacon 25 lb 

3,200 lb * 

*This is a preliminary estimate only. Weight for 

primary power and gyro-stabilization is not 

included. 

* * * 

There are a number of elements of the proposed ocean surveillance 

system which require further study. For example, it is necessary 

to determine whether the radar antenna can be a rotating one as is 

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;tle 

ent. 

:ion 

rpreferred or whether it must be fixed to avoid disturbing the optical 

system. Secondly, it is necessary to determine whether the radar 

antenna can provide the multiple usage capability required by the 

IFF, the ELINT, the beacon, and the radar systems. It may be necessary to provide a second antenna (perhaps a 5-foot aperture dish) 

for use by the IFF, the ELINT, and the beacon systems to classify 

the targets. Thirdly, it is necessary to determine how the optical 

cameras can be made adequately directive. (It is considered that 

an essential element of this system is that the camera should be 

quite flexible in its ability to be trained upon any point on the 

earth within 250 miles or so of the astronaut.) A fourth question 

has to do with the need for a camera of focal length of 98". 

(The 48"-focal-length camera will give the required resolution only 

if it is operating at its maximum effectiveness. To allow for some 

degradation of performance it may be necessary to use 98"-focallength optics.) The camera aperture may need to be increased from 

12 to 18 inches. Schedules are yet to be determined. Much more 

accurate cost data are required. The many interfaces between the 

various sensors must be thoroughly examined and properly related 

one to another. Also, it is necessary to determine the cost in 

effectiveness which will ensue to the over-all experiment if certain 

portions must be omitted for one reason or another. 

• or 

19 
Section III 

Command and Control 

In the specific area of Command and Control the Technical Panel 

received no experiment proposals of note. This is an unsatisfactory 

situation because there is a problem which exists in this area. The 

STARLIGHT Study (reference [c]) in particular recommended that the 

Navy develop space-oriented command ships. The obvious technical requirements for command and control posts, whether in space or on shipboard, include data sensors and processors, means for communication, 

means for presentation of information, and means for storage and response 

to direction and command. The hardware already envisioned for the MOL 

vehicle to perform the Navy ocean surveillance mission can take care 

of surveillance, data processing, and communication functions envisaged 

for the command and control function, and therefore will support the 

Command and Control mission. However, no suggestions with respect 

to specific experiments in command and control are provided herein. 

It is suggested that sponsors be sought within the Navy to develop 

a suitable command and control experiment. 

1 JULY 2015 

20 
RELEASE 1 LY 2015 

Section IV 

Communications 

PDonse 

OL 

ged 

There is much work under way on unmanned space communication 

experiments. There is still a place for special experiments, 

however. The Navy has a wide interest in global communications, 

hence the Technical Panel accepted a communications experiment proposing further work in:VLF, ELF, and HF areas. This experiment will 

check out the efficiency of global communication to a spacecraft on 

the opposite side of the earth from a ground station using VLF. 

It proposes further to measure antenna impedances and propagation 

characteristics within the frequency ranges listed. Man can be 

very useful in tuning and adjusting the equipment to optimize the 

performance of the experiment and enhance its reliability and 

accuracy. Figure 8 provides a summary of the factors involved in 

a communication experiment. Sponsors for the proposed experiment 

include the NRL and NADC. A proposal prepared by NRL (Item 12) 

as a part of the LOFTI program is included in Appendix A. 

21 

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Section VI 

FLINT 

In the area of the FLINT mission man can provide selectivity 

to examine signals which appear to be of most interest; he can filter out noise; he can provide better accuracy, and better reliability; 

and he can provide correlation of data in-put with respect to other 

information. Furthermore, the manned astronautic vehicle is the only 

manned vehicle now available for passage over foreign territory. 

It therefore enables the development of capability for selective, 

tactical, ELINT analysis which appears to be promising during the 1968-

1970 period. This is particularly so in view of the fact that man's 

capability to launch larger payloads is presently increasing faster 

than is his capability to launch highly reliable adequately sophisticated unmanned systems to obtain some kinds of information which is 

desired. At least four Navy laboratories could be selected as sponsors for a selective, tactical FLINT analysis project. These include 

the NRL, the NADC, the NMC, and the NOL (White Oak). Costs of the 

hardware needed for performing the experiment are included in the 

estimates for the ocean surveillance system; however, some additional 

funding may be required to cover costs of the sponsoring activity 

for this particular experimental area. A summary of the factors 

considered in the FLINT problem is given in Figure 10. Mr. Samuel 

Hubbard, BUWEPS, has prepared a study of the FLINT problem, Appendix A, 

Item 15. 

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NRO APP 

RELEASE 1 J 

Section VII 

Bio-astronautics 

In the mission area of Bio-astronautics there are several factors to be considered. In the first place NASA has planned the launching of a series of at least six 1,000-pound bio-satellites. These 

are to be orbited for periods extending from 3 to 30 days. It is 

also to be remembered that the directives for the MOL program state 

that work in the area of bio-astronautics is not to be overdone. 

Hence, the Panel considered that only those experiments should be 

considered for naval participation in which the Navy can make some 

unique contribution or has some special reason for performing the 

experiment. 

The summary included in Figure 11 shows that only three experiments 

were selected in the bio-astronautics area. The first one of these 

(see Appendix A, Item 16) is an extension of Project ARGUS in which 

the Navy has been making at the Naval Medical Research Institute an 

extended study of the capabilities of man to exist in small parties 

of from 2 to 15 in number for extended periods of time in deeply 

submerged vehicles which are completely cut off from mankind. In 

such a vehicle man encounters many environmental conditions which are 

like those in space. Therefore, it is considered that the Navy can 

make a considerable contribution to the national effort by relating 

and extending its ARGUS- Stadies to the MOL system. In the case of the 

remaining two experiments on nuclear radiation monitors proposed 

by the Naval Radiological Defense Laboratory (see Appendix A, Items 

17 and 18), it is considered advisable that these be included in the 

MOL vehicle because NRDL has certain advisory responsibilities to 

DOD which require it to obtain first-hand information on the space 

environment encountered by man. Also, in the case of the heavyparticle dosimeter experiment proposed by NRDL (Item 17, Appendix A) 

.recovery of records is necessary for further study. 

27 

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Section VIII 

General Science 

The Navy has much capability in the area of General Science, 

and consequently the Panel had many experiments to review. Those 

ultimately selected are thought to have potential military value. 

Considered first were experiments that are related to the MOL 

vehicle and deal with space and plasma physics. For example, the 

proposal of the NRL to study plasma surrounding the MOL vehicle 

by scatter of RF energy is indluded (Appendix A, Item 19). Similarly, 

the proposal to study by the use of probe techniques the density 

and temperature of electrons within this plasma was included 

(Appendix A, Item 20). The far-UV orthicon (Appendix A, Item 14) 

was included because of its military mission interest, its need for 

manned operation, and the inherent value of background information 

with respect to UV radiation in near-earth space vehicles. The 

airglow horizon photography (Appendix A, Item 21) was selected as 

being of value because the airglow is a major phenomena encountered 

by any optical sensor operating near the earth, and horizon sensors 

are of considerable interest. 

Of long-range interest is the cosmic radiation coming in to 

earth and its direction of origin. This would be studied in one of 

the experiments recommead4 (Appendix A, Item 22). Also, of interest 

is information on the white light corona about the sun and possible 

sky surveillance of the area near the sun (Appendix A, Item 23). 

The airglow spectroscopy made possible in the MOL vehicle is also 

considered to be a valuable experiment (Appendix A, Item 24). 

Finally, photography of the solar planets and of the geology of the 

earth using the camera planned for ocean surveillance from the MOL 

vehicle is worthwhile. (It is true, however, that the camera proposed 

will be only marginally effective for use in photography of the 

planets.) 

A much more complete study of the Navy proposals in General 

Science has been prepared by Dr. William Faust of NRL (Appendix A, 

Item 25). 

29 

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31 
Section IX 

Summary 

A preliminary report of the MOL Technical Panel has been 

prepared for submission to the Bureau of Naval Weapons as requested. 

In all, the Panel received eighty-nine proposals or ideas for 

experiments. From these were selected those experiments to be proposed for the MOL program. The number of experiments submitted in 

each area, the number recommended for support by the Navy, and the 

preliminary estimates of costs for these experiments are given in 

Table 5. 

Major interfaces between these experiments exist on data 

management, structural arrangements, vehicle stabilization and control, position determination, communications, etc. These require 

further study. 

The experiments proposed are within the state of the art and 

can be orbited in the 1968-1970 time period. They are also well 

within the payload capability of the MOL vehicle. 

Inclusion in the MOL program of experiments described here and 

intended to study means for improving the performance of naval 

missions is highly recommended. 

'Table 5 

Over-all Summary of Experiments Recommended for MOL 

Experiments Costs (Millions) 

Mission Area Reviewed Recommended FY '65 Total 

✓ Ocean Surveillance 26 L. 1 (8 parts) $2.75 $39.25 

Command and Control 2 ? ? 

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5 2 I C-I 1.50 7.0 

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Bio-astronautics 14 3 -.).. 5-lu 0.30 3.25 ..., _4-I 

General Science 35 10 a 5-22 0.70 6.85 

$6755M* 59:55M* 

*Preliminary estimates only. Not for budget purposes. 

32 
1 

RELEASE 1 J Y 2015 

The JoAns Hopkins University 

APP'Llt0 etereice 

silver kvir.11, AU'vt.'d 

Appendix A 

COPIES OF RECOMMENDED EXPERIMENTS 

AS SUBMITTED TO MANNED ORBITAL LABORATORY 

TECHNICAL PANEL 

MOL, 

AN INVESTIGATION 

IN MULTI-SENSOR 

MILITARY SURVEILLANCE 

(Title Confidential) 

Excluded from automatic 

slow11,4rading and declassification. 

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RELEASE 1 J 1 2015 

Ow Johns Nop&ino Univorsiiy 

• NYSICI 

Savor Spin. PAa yIond 

A. INTRODUCTION 

There are a number of sensors which might be used in 

satellite reconnaissance and surveillance. In many applications 

the sensors could be operated from an unmanned satellite and the 

information telemetered for ground interpretation and use. There 

are obvious limitations to such unmanned systems. The problem, 

then, for MOL is to provide an overall syhtem in a manned satellite 

which in terms of economy and usefulness is superior to the use of 

a collection of unmanned systems. It is envisioned that this system 

should complement and not supplant other ground and aircraft surveillance systems now in use (Frontispiece). Study may show, however, 

that some of the data acquisition and interpretation techniques now 

employed might be better accomplished with a manned space station. 

The intent in the following presentation is not to define the 

ultimate or even the prototype manned military space station but 

rather to define an experimental Manned Orbital Laboratory which 

will be used for conduct .9; those, experiments necessary for a definition of the prototype manned military space station. 

The most obvious use of a manned military space station is 

the surveillance of the earth for targets of military interest. This 

surveillance requires at least two separate procedures; acquisition 

and identification. To scan a meaningful percentage of the possible 

earth surface viewable from the satellite will require relatively 

low resolution devices. Once a potential target is acquired by one 

or more of the scan sensors it must then be fixed by the high resolution sensors for identification. To accomplish this fix, of course, 

will require either that the high resolution sensors be slaved to the 

low resolution sensors or that the coordinate position of the potential 

target be known from the acquisition by the scan sensors and the 

identification sensors be trained to the directed position. The 

SECRET 

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JULY 2015 

ma Johns Soo Ions Univonily 

uruco PMYSI 

SAN. Smi,q. htb•YlOnd 

method used will depend on whether one astronaut accomplishes both 

surveillance and identification or whether the two tasks are 

accomplished separately by a two man team. To accomplish identification it may be useful to provide a target image memory, as by 

photography for instance. 

Even should one man perform both surveillance and search, 

it will yet be necessary to provide a capability for target coordinate position determination so that meaningful use can be made of the 

acquisition and identification data. To accomplish this will require 

the possession of at least two and perhaps three types of information. 

It will certainly be necessary to know precisely the orbital parameter 

This can be accomplished by tracking and orbit prediction and storage 

of the predicted orbital parameters aboard the spacecraft. In additio 

it will be necessary to know the inertial coordinates of the sensors.' 

This might be accomplished by tying the sensors directly to an inertia 

platform where inertial coordinates are obtained from tracking known 

reference objects (stars, sun, horizon, etc.) orbital data and comput 

tions. It may, however, be necessary to physically separate the 

sensors from the inertial platform so that the inertial orientation o 

the spacecraft would be determined from one or more of the means for 

inertial coordinate reference location and the pointing angle of the 

sensors with the spacecraft also provided for computer use. The 

computer would define the scan center in earth based map coordinates 

from the stored orbital parameters referenced against the inertial 

platform. 

In addition, the information will be maximally useful to 

the astronaut by providing a visual display of the earth based coordi 

nate position of the target either continually or on command. The 

computer, of course, would have such information continually availabl 

on a real time basis. 

A-4 
RELEASE 

Hopkins University ---SEGRET, 

The essential information must on command be telemetered 

to the ground. To reduce the telemetry requirements it might be 

well to do some initial data processing aboard the spacecraft. 

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It is, of course, impossible at this time to define the 

desired military space station configuration. The experiments 

conducted on MOL should provide the necessary information for the 

detailed definition of the prototype military space station. 

B. ORBIT 

To provide more uniform coverage if the swath width does 

not give contiguous coverage at the equator, the period of the orbit 

should be chosen so that it is not near an exact submultiple of the 

earth's rotation period. In the range of altitudes considered 

(125-250 n.m.) there is one synchronous period of 96 minutes correspondong to a mean orbital altitude of about 185 miles. Most uniform 

coverage will be obtained with orbital altitudes either near the 

minimum 125 n.m. or the idaRimum 250 n.m. 

Since this first Laboratory experiment is not the operational system, it is not desired that complete contiguous coverage 

be obtained in each 24 hour period. 

Further since the results obtained at a given altitude are 

easily scaled for another altitude, it will be expedient to choose 

the lowest orbit which will meet the task testing needs. This would 

seem to obviously dictate the range of 120 to 150 miles. 

C. SENSORS 

1. Acquisition 

The purpose of the sensors is to present to the man as 

much information of the earth's surface as possible, limited both by 

A-5 
The John, Napkin, Unfwersily 

APPLIED IN110lCO 

SilverUminit. ,04,04M 

the ability of the instrumentation available and the ability of the 

man to assimilate these data. The sensors should include a small 

low resolution radar whose purpose is to locate the larger objects 

on the ocean, especially under cloudy conditions. Without cloud 

cover the most effective instrumentation will be visual. 

It is expected that a significant part of the target 

acquisition phase may be accomplished with the naked eye. However, 

there may be some advantage in having a low-powered binoculars at 

about three times magnification to assist in this process. There 

may be some merit in extending the spectral range of sensitivity of 

the observer by having an infrared sensitive viewing device. For 

the dark side of the earth a sensitive television camera or image 

intensifier may provide useful data. 

The acquisition process in a dense target region 

will be enhanced if the observer has an ability to check off the 

targets in turn. In addition to a cursor which he may present in 

superposition to thetscene which he uses to center on each target 

to store its location in the memory, when so located there should 

appear a superposed marker provided from the computer and memory 

which will stay locked on that target's geographic coordinates 

independent of the motion of the telescope. His attention is thus 

more easily directed to the remaining targets and his speed will be 

significantly improved. 

There is another kind of visual signal which might be 

useful. If the ground CIC is interested in certain ships, or suspects 

certain locations, or can produce predicted locations of interesting 

objects, then this information can be inserted in the memory through 

the ground command station. The observers can evaluate and update 

these targets. This mode of operation may be the only practical war: 

to perform the land surveillance, with two observers using separate.:: 

high power telescopes to provide the necessary resolution. For both, 

A-6 4 

11 
RELEASE 1 Y 2015 

The johns Hopkins University 

Art•SteD •WISICe AAAAAA 7011Y 

sityyr Spring. Marytend 

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ad land and ocean surveillance telescopes pointing position is slaved 

to the computer and programmed through the priority queues. 

arget 2. Classification and Identification 

aver, Identification instrumentation will be primarily a 

at high magnification optic system. Assuming that the acquisition 

age 

The ocean identification problem can probably be 

solved quite adequately with an optical aperture of about 8" giving 

a a resolution of about 12 ft. with a slant range of 700 miles (see 

le Figure 1). If a higher resolution were desired to make the device 

in useful for observation of ground targets, for instance, a 

;et 

ild When one considers the problem of slew- 

- y ing speeds the very great problem of providing a mounting platform 

sufficiently freeof vibration, larger aperture optical devices 

:hus become unattractive for these early experimental missions. Even a 

.1 be 24" telescope may impose overly stringent engineering requirements. 

In addition to direct visual identification proceises, there may be 

advantages to photographing certain regions to be identified later. 

;ht be This may be especially important in regions of the North Atlantic 

where the traffic density is high. Both of these visual and photoeting graphic processes may be augmented by extending their spectral sensiirough tivity at least to the near infrared. 

late 

it way 

trate 

both 

are process has identified the location of objects, the only limitation 

ty of on magnification used will be governed by the ability to mount and 

For launch a large optical system) 

—9E-GREL. 

A-7 
This Johns Hopkons University 

APPLIED 

Silver Spring, Ma,VISnd 

Under cloud cover some additional information may be 

gained from direction finding, spectral, and time pattern measurements of electromagnetic radiations from ships. The EM frequency 

spectrum extending from 100 kc to 100 kmc might be continuously 

monitored by panoramic receivers. Continuous recording of the 

receiver outputs on multitrack magnetic tape should be provided 

in addition to visual display. An alarm system would indicate to 

the operator which parts of the spectrum show unusual activity or 

when selected frequencies become active. 

These receivers would normally be connected to omnidirectional antennas. Provision should be made for direction finding 

by changing over to fixed spaced antennas at the lower frequencies 

and rotating directional antennas at the higher frequencies. 

The receivers should also have provision for more 

sensitive examination of specific parts of the spectrum, with alternative demodulation, display, and recording facilities to permit 

detailed analysis of the signal structure, identification of purpose 

of the transmission, and possibly decoding. 

To cover the spectrum from 100 kc to 100 kmc would 

require about 10 receivers; the total weight including displays, 

recording, etc., might be about 200 lbs. The weight of 10 omniantennas and 10 direction-finding antennas might run to about 100 

pounds. The power consumption should not exceed 200 watts. 

3. Minimal Optics for Ocean Surveillance 

At an orbital altitude of 150 n.m. a good eye will hav( 

a resolution of about 200 ft. at the nadir (see Figure 1). If the 

5 1 JULY 2015 

Ti.. Johns Hopkins University 

APPLIED PHYSICS LA $$$$$ DAY 

Silver Spring, Maryland 

+ maximum field coverage is -45o from this, the maximum slant range 

is about 200 n.m. and the eye resolution drops to about 300 ft. 

The complete swath is then 300 n.m. in width and at 

the orbital speed of about 4 n.m/sec. the area scan rate is 1200 

n.m.

2

/sec. This is equivalent to a square patch of about 35 n.m. on 

a side, which presents a field of view of about 13° on a side. If 

this patch is magnified in a low power wide field telescope (about 

the practical limit) the magnification will be 4.5 This calculation 

presumes that this telescope (or binocular) is mechanically scanned 

to dwell on this patch area effectively for one second, and that the 

preset program of scanning provides complete coverage of the full 

swath without significant overlap or holes. 

With a 4.5 magnification the resolution at slant ran 

becomes about 70 ft. which tends to enhance the ability to acquire 

even small ships. 

In fact this resolution may allow the acquisition 

operation to include # a coarse identification. This will be especia 

useful in a high target density region since the coarse identificat 

can then be used to provide a priority selection in the targest-toidentified queues. 

The acquisition operation is envisaged as a pointing 

operation... The observer superposes a reticule image on the scene 

and moves it into coincidence with the object and then operates a 

button which stores this targets' geographic coordinate in a memory 

This operation may include very brief identification symbology (e. 

big, fast, SE course). 

The identification phase may best be done as a sepa 

operation. The memory store feeds the objects to be identified to 

second observer on his command. He has a higher power telescope wi 

A-10 
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resolution capabilities to meet his needs. If the resolution required on the scene is 12 ft. at the oblique view then this may be 

met with a telescope aperture of about 2.5 inches. The eyepiece 

choice which preserves best light will then give a magnification of 

25 so that the field of view is 60/25 or about 2.4° which corresponds 

to approximately 50 K ft. at a slant range of 200 n.m. This field of 

view is more than sufficient to give good centering of the potential 

target. 

The job of the identification process is one which 

will profit from well disciplined training. The observer must be 

well conditioned so that the recognition process in the required 

output terminology is automatic and fast. It is envisioned that he 

controls centering to provide more accurate coordinate measures and 

then without removing his eyes from the scene taps keys (as in a 

stenotype) to characterize the target. When this is complete, he 

then signals for the next target in the waiting list and repeats. 

Acoustic signals from the computer can alert this 

observer to the need for greater speed when the queue length starts 

to build up too fast, but at the saturation density of the man 

there should be deletions from the queue to preserve only the more 

important targets as programmed by size, location, position with 

respect to the satellite, or best viewing region. 

D. COORDINATE TRANSFORMATION AND PRESENTATION 

The information obtained from the several sensors is only 

complete if the position of the object can be defined as well. It 

sould interrupt the human and decrease his effectiveness in continuing 

his search if he had to perform a complicated task of manipulation or 

computation in order to name the position of each interesting object 

he sees. Rather, this coordinate measurement job should be 

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A•Pl..SED AAAAAAA OnY 

Silver Swing, Maryland 

accomplished by automatic means so that as he centers his optics on 

an object, a push of a button will provide the coordinates of that 

object. 

The implementation of this scheme will require that a 

platform on the vehicle be oriented in a coordinate system. The 

most accurate reference will be an array of star trackers. It will 

be sufficient to have two approximately orthogonal stars being 

tracked simultaneously. Because these may, in the course of time, 

be shadowed by the earth or moon, or blinded by sunlight, earthshine or moonshine, there will need be about 6 star trackers. It 

would be wise for reasons or reliability to provide some alternate 

references. These may include, horizon trackers, sun tracker, moon 

tracker, X, Y, Z magnetometers, drift sight, gyro compass, RF array 

referenced to ground station (Cubic Corp.). The pointing direction 

of the telescope with respect to this inertial platform needs to be 

known and if time and orbital parameters are known, the complete 

gEometric relations are: Wined., To complete the system, a real-time 

digital computer can correlate these data to provide the desired 

coordinate information. This, of course, can be done for each of 

several tele.Scopes that may be in use. 

This computer is the heart of the system. It should be 

able to provide the present satellite position coordinates from 

orbital elements or from interpolation of an ephemeris provided 

from the ground. Then, referenced against the inertial platform, 

it must solve some simple geometry to define the scene center in 

earth based map coordinates. This would seem to require a modest 

unit of possibly a cubic foot volume. 

It would be useful to the crew to provide a direct analogue 

display of satellite position with respect to a globe of the earth. 

The data necessary would be available from the computer. 

A-12 
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M. Jahns Hopkins Univetsity 

APPLIED PHYSICS 

3 on i E. DATA OUTPUT AND COMMUNICATIONS 

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Communications of several types will be required in the 

MOL program. Obviously there must be means by which the astronauts 

discuss problems related to their well being and logistics with 

appropriate earth surface station. It will also be necessary to relay 

particular information resulting from the surveillance operations 

and other technical experiments carried aboard. It is desired here 

to discuss the apparent requirement of the latter and more partitularly 

those involving ocean surveillance. 

In order to transmit information gathered over a period of 

time from perhaps as many as two orbital passes it would appear to 

be mandatory to provide a storage capability and to encode the information in digital or similar manner. Retrieval of the stored information should be accomplished by ground command and rapid readout 

capability. It should not be a requirement that the astronaut be 

responsible for initiating such transmissions of information. It 

may be desirable to also continuously transmit such information in 

real time for use by friendly vessels and stations to gain an appreciation of the immediate local scene. Voice communication should be 

reserved for indicating changes in the operating modes and procedures 

which are of interest from the system planning standpoint. 

Communications between the astronaut operations relative to 

target surveillance should be in the form of symbolic visual displays 

to the greatest extent possible. These should be either superimposed 

on the field of view of the device being used or conveniently located 

at the side so as to require the minimum of eye motion. It will likely 

be necessary to supplement this with voice communication, but it would 

appear desirable to minimize this in any way possible since it is 

relatively inefficient and should be reserved for unplanned and/or 

emergency procedures. 

--StPeRCE-- 

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APPLIED PHYSICS LASORATORE 

Silver Spin, Marylond 

F. EXPERIMENTAL PLANNING 

1. Flexibility 

One purpose of the MOL flights will be to discover 

the most effective ways to conduct the mission and to this end it 

will be necessary to try various approaches to the problem. Some 

of these various methods can be determined ahead of time and planned 

for, but it will be most likely that some new approach requiring a 

new arrangement of the instrumentation may arise after launch and 

there needs, therefore, to be a sort of a building block approach 

to the whole instrumentation arrangement so that the instruments 

may be used in various combinations. 

Parts of acquisition and identification tasks will be 

assisted by what amounts to automatic programming provided by the 

computer. It is obvious, then, that we may need to reprogram this 

automatic control as the task organization changes. Since the 

essence of this wholeoexperinlent is to optimize the task performance 

of the man--machine system we may need to change the nature of the 

data presentation to the man's sensors. Some of this can be planned, 

but again, the man may need to "rebuild" parts of this instrumentatio 

2. Objectives 

Ground based simulation experiments can lead to vario 

combinations of operational methods to be experimented with. There 

are two distinctly different methods obvious at this writing which as 

need to be exploited. One method of organizing, the task may be to 

have the astronaut cover assigned sub-track swaths independent of 

each other, and another task organization may be to assign one man 

to provide the acquisition function, designating in geographic 

coordinates the potential targets, as his sole job. The second man 

would then examine these designated positions in turn with greater 

magnification to perform the identification. The efficiency of the 

whole operation can be improved if we have more detailed measures o 

the tasks involved. 

A-14 
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RELEASE LY 2015 

The Johns Nopk ■ ns Univwsity 

ArpLif0 PHYSICS 

Savor Sp,mg. Maryhond 

Analogous to the time and motion study we need to 

gather data about many kinds of tasks. In the acquisition we will 

need to know the precision of target coordinate measure. We need 

to know the statistical measure of the ability to locate and identify 

various kind of targets with varying illumination, sea state, etc., 

conditions. Related to these tasks is the question of symbolization 

or language that needs to be used to efficiently and concisely compile 

the results of the acquisition and identification. 

In general, there will be limitations in behavior of 

both the instrumentation and the man. A sensible system will only 

arise from a measure of these parameters in orbit. The task of this 

satellite system will have to be performed under the environmental 

conditions that are found to exist. For instance, there will be a 

certain number of ships that must be located on a given pass. They 

are there. The illumination may vary from high contrast to low contrast and cannot be changed. The preOure to have complete, or 

nearly complete, coverage requires that a large area be searched in 

a given time. 

The sun may be in a favorable location or it may not. 

The sea state will vary in many ways. When it is smooth enough, 

ships wakes may stand out clearly. The most perturbing thing will 

be intermittent cloud cover. Some of these problems can be simulated 

in a ground experiment. In fact, it will be essential to try to be as 

realistic as possible in this preliminary ground experiment. Many of 

the questions which we are unable to answer at the present will be 

answered through these preliminary experiments. 

man G. SPACECRAFT ORGANIZATION 

man 

ter 

the 

es of 

1. Characteristics and Stabilization 

The nature of the equipment and their use dictate some 

features of spacecraft design. It is assumed that the general:launch 

A-15 
1 JULY 2015 

The Johns Hopkins University 

APPLIED PHYSICS AAAAAA TONY 

Silver Spying, Maryland 

configuration of the MOL will be determined by mating requirements 

with the Titan III booster and the modified Gemini capsule. The 

suggested orbital configuration briefly described here then would 

be erected after injection into orbit. 

It seems clear that the spacecraft should always 

present the same face to the earth to avoid excessive complication 

in equipment design. Since high resolution sensors will demand a 

very stable platform to optimize observation and recognition, it 

would be desirable to provide the overall spacecraft with as high 

a moment of inertia as possible about each axis of rotation. In 

addition to keeping the same face of the satellite facing the 

earth it would also be desirable to know the alignment of the major 

satellite axis with the orbital path. Many of these requirements 

can be simply achieved with a gravity gradient stabilized satellite 

asymmetrical about the Z axis. This would assure one face of thesatellite to continually face the earth, would align the major axis 

of the satellite bod3.74thogorial to the Z axis in the plane of the 

orbit, would markedly increase the moments of inertia, thus providing 

a more stable platform and would much reduce the weight and power 

penalty required for stabilization as compared to an active system. 

It may also be attractive to make use of active system 

to act as vernier devices to correct for small perturbations to the 

angular rate of the spacecraft. A combination of rate sensing and 

the controlled ejection of by-products of the life support system 

may provide an inexpensive scheme for accomplishing this. Active 

systems, including inertia wheels could, of course, be used for 

spacecraft alignment for deorbiting and other special maneuver by 

simply overriding the gravity gradient torques. 

2. Power Supply 

Power generating and storing equipment must be desig 

on the basis of the complete MOL requirements. It would appear tha 

A-16 
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RELEASE 1 2015 

1h4 John% Hopkins Universily 

Ar•Lito rorsics 

Silver Spring. Moyinnd 

high level of reliability and flexibility should be guide lines in 

the power system design. While it is not felt desirable to specify 

the particular method of energy conversion at this point, consideration of use of features of the life support system may be found to 

be attractive. 

The requirements of the electronic devices associated 

with the ocean surveillance experiment may approach a value of 10 

kilowatts peak and perhaps 2 kilowatts average. This, combined with 

the balance of the MOL power needs would suggest the use of fuel 

cells or rotating machinery, for a mission of a few weeks duration. 

For an extended mission consideration may be given to a nuclear power 

source. An independent low level, emergency back up power source 

will, of course, be a requirement. 

H. GROUND STATIONS 

While it is possible that certain information of interest 

to the ocean surveillance experiment may be transmitted to the net-

- 

work of ground stations deployed about the earth for monitoring the 

astronauts' well being, the majority of information of interest to 

the ocean surveillance experiment should be relayed to one or two 

ground stations equipped primarily for that purpose. Such a station(s) 

should have the ability to command the rapid read out storage device 

abc,ird MOL, to reduce and/or distribute such information in the 

desired manner and to inject any orders in the form of a coded message 

into the spacecraft. The latter could include a request for observation of targets of known geographical position during subsequent 

orbital passes. These stations must also have a voice communication 

capability so as to receive and transmit information of a non-routine 

or unplanned nature. 

As was mentioned in a previous section, it may be desirable 

t' continuously transmit information in real time to furnish friendly 

users an appreciation of the local scene on an immediate basis. If 

A-17 
1 JULY 2015 

TM Johns Hopkins UniverilaY 

A►►ll[D POO'S 

Warn' Spring, Maryland 

this is desired, a receiving and data reduction device of a somewhat simpler character than that at the primary station would be 

provided. Such an instrument may be practical for reasonable sized 

vessels and aircraft having special interests. No transmitting 

ability would appear to be required for such an installation. 

I. CONCLUSION 

To physiologically support man in space for protracted 

periods of time will be extremely expensive and the expense will 

be further increased by his psychologic support demanding short 

duty cycle and long terrestrial furloughs. A manned military mission is justified, then, only when the objectives can be met more 

economically and in a more timely fashion than they could with unmanned systems. One must inquire, therefore, for those functions 

whose performance by the human represents a degree of excellence 

presumably not attainable competitively by unmanned systems. The 

unique human power of inquisition, observation, synthetic appraisal, 

judgment based on a'lehrned art as well as on objective parameters, 

the dynamic range of the human sensors.and the data correlation and 

rejection capability of the human brain offer an overall system 

performance that does not appear to be attainable with unmanned 

systems. For vision alone, for instance, the telemetry of the 

-necessary fidelity would require a telemetry capability an order 

(f magnitude greater than that projected as being available in the 

next five years. When color vision requirements are added the 

telemetry task increases twofold. Earth reconnaissance and surveil-, 

lance, particularly over the ocean, may well be accomplished in a 

superior fashion by a manned military space station as compared to 

unmanned systems. The MOL series of experiments should provide the 

necessary information for making a definitive analysis of the relative effectiveness and economies. 

--SEGfira, 

A-18 
ny johns Marthins Uniyetsity 

&rpm to PHYSICS 

SIbn, PAPY,•^4 

APPENDIX A 

mebe 

sized MOL STABILIZATION SYSTEM 

g 

ed 

11 

t 

misore 

unns 

ce 

The 

aisal, 

ters, 

n and 

After an appraisal of competative systems it appears that there 

would be considerable advantage in providing the MOL with gravity gradient 

attitude stabilization. 

A conceptual scheme for a boom/vehicle arrangement is shown in 

Figure 1. A 200 foot long extendible boom of approximately 4 inch diameter 

would be used with an end mass of approximately 320 lbs. Most of the 320 lbs. 

could be in the form of a damper possibly of the type that has recently been 

used by the General Electric Company on an NRL satellite. The boom would have 

3 or 4 layers of 15 mil thick beryllium copper tubing. Booms of this type 

have already been developed for spacecraft applications by the DeHavilland 

Aircraft of Canada, Ltd. If we take a set of coordinate axes for the spacecraft such that the X axis is in the direction of motion of the spacecraft, 

the Z axis is along the'extendible'boom, and the Y axis direction is taken 

to form an orthogonal set, then for this configuration the approximate 

moments of inertia will be given as follows: 

I = 40,000 slug-feet2 

I = 50,000 slug-feet2 

er 

I

z 

= 10,000 slug-feet2 

the 

rveiln a 

d to 

• the 

relaThese moments of inertia are sufficient to give an adequately large 

restoring torque under the forces of the earth's gravity gradient. Furthermore, by having I

x 

I;>=0I

z 

we not only get a restoring torque in the vertical direction, but we get an additional torque which will cause the long axis 

of the spacecraft to be aligned in the plane of the orbit. The magnitude of 

the maximum torque in the vertical direction is 0.72 inch lbs. The magnitude 

of the tozcue controlliTyaw motion of the satellite is .06 inch lbs. These 

should be appreciably larger than any other perturbing force on the satellite, 

with the possible exception of aerodynamic forces which could be made to 

supplement these restoring torques. 

A-19 
PPROVED FOR 

ASE 1 JULY 2015 

The MOWN Woken/ WI'mew, 

APPLIIII PHYSICS LA 

kelng, NW,lend 

One problem that might be encountered is due to motions of the men 

within the MOL. A fair approximation for a 150 lb. man is that he has a 

moment of inertia about his center of gravity of 20 slug-feet

2

. Should the 

man do a maneuver in which he turned 180 degrees, the ratio of his moment 

of inertia to the spacecraft's moment of inertia is so small that this would 

cause a motion of the spacecraft of something less than 0.1 degree. 

It would probably be advisable to provide the MOL with some cold 

gas jet system for additional attitude control. However, the provision of 

3 axis gravity gradient stabilization system would drastically reduce the 

demands on the cold gas jet attitude control devices. 

The telescope for ground surveillance must however be mounted on a 

gyro stabilized platform. This is because even a 0.1 degree rotation of the 

spacecraft will cause an apparent motion of something being observed on the 

earth surface that is well beyond the resolution that is desired for this 

system. 

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A-20 
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320 lbs 

3111■• X 

23' 

FIGURE 1 

CONCEPTUAL SCHEME FOR A BOOM/VEHICLE ARRANGEMENT 

I

x 

= 40,000 slug-ft 

I = 50,000 y slug-ft 

I

z 

= 10,000 slug-ft 

A-21 
OVED FOR 

1 JULY 2015 

The Johns Hopkins University 

APPLIED ►MYSIW LARD AAAAA Y 

Silver Spring, hterylend APPENDIX B 

APPLICATIONS OF THE CORNUCOPIA CONCEPT TO MOL 

Cornucopia is the name given to a novel concept for extending 

the utility of storable rocket propellants to include life support 

and other essential services in the space environment. Initial 

feasibility studies, heretofore unreported in the literature, have 

recently been conducted by The Johns Hopkins University, Applied 

Physics Laboratory under the sponsorship of the U. S. Bureau of 

Naval Weapons. The potential applications to MOL appear particularly 

attractive. 

Most of the presently contemplated manned space missions 

involve some impulsive maneuvers by the inhabited vehicle, typically 

calling for the variable impulse and multiple restart capabilities 

of liquid chemcial rockets. This could apply to the initial MOL, 

which may require small thrust producers for attitude control or 

station keeping purposes. It will certainly apply to follow-on 

missions that call for rendezvous,docking, and other maneuvers 

associated with periodic re-supply and crew transfer. It appears 

that such missions will call for earth-storable propellants and a 

two-gas cabin atmosphere, but might not justify a fully regenerative 

life support system or a nuclear power source. Such cases represent 

a considerable quantity and variety of vital fluids, including the 

liquid bi-propellants, potable water, atmospheric oxygen and nitrogen, 

any necessary coolants, and whatever reactants might be needed for 

electrical power generation. This tends to create a formidable 

over-storage problem, since the supply of each separately stored 

fluid must include some individually determined margin for uncertainty 

or emergency reserve. Also, the inherent inefficiencies of multiple 

tankage incur additional penalties in hardware weight, volume and 

complexity. Clearly, a substantial consolidation of on-board fluid 

storage requirements can pay off handsomely in terms of system 

performance and habitability. 

A-22 
The seisns Hopkins University 

LASOPATONY 

&We, Sismil. Ma,Viand 

:tendin 

)rt 

ive 

ilarly 

An extremely promising approach involves the use of 

hydrazine and hydrogen peroxide as a storable bi-propellant 

combination. Equally promising in certain applications is the 

hydrazine/nitrogen tetroxide system. The suitability and attractiveness of these liquids for space propulsion and attitude control 

is well documented, but more exciting is the abundance of potentially useful products from their oxidizer-rich combustion in a gas 

generator. Always present are interestingly large quantities of 

potable water, plus gaseous oxygen and nitrogen in virtually any 

desired proportion, depending on the selected mixture ratio. The 

released heat and kinetic energy are available for electrical 

power generation, thermal management, and a variety of mechanical 

functions. Figure 1 illustrates the foregoing in a representative 

block diagram, while Figures-2 through 5 plot the basic chemical 

and thermochemical relationships from which estimates of performance 

in specific areas may be derived. 

ins 

:ally 

Les 

Figure 6 schematically depicts one scheme for the generation and control of a two-gas cabin atmosphere in zero gravity, while 

Figures 7 and 8 indicate the mixture ratios required to maintain 

d physiologically acceptable concentrations of combustion-generated 

rtainty Impurities. 

tiple 

nd Particularly worthwhile in the MOL application would be 

luid the substantial atmospheric flush rates that accompany power generation. These high rates would effectively solve the otherwise critical 

various atmospheric compositions under widely varying conditions of 

a overboard leakage. Figure 9 presents the corresponding requirements 

itive for total reactant flow rate. Figures 10 and 11 similarly plot the 

generation rates of by-product water and thermal energy. A possible 

the side process of thermal management is suggested in Figure 12 and 

trogen, Figure 13 illustrates a method of extracting electrical power via 

for turbomachinery. The tabulated data in Figures 14 and 15, coupled 

with a fair assurance of subsequent shifting equilibria, attest to 

A-23 
JULY 2015 

The Johns Hopkins Univlenity 

APPLICO PNVIIC$ 1411 OOOOO XV 

Savor Sostno, SAstyland 

problem of contaminant build-up at no extra cost in weight or 

complexity. They would also provide a free source of additional 

low thrust (from the expelled atmosphere) that could conveniently 

be directed for attitude control or station keeping purposes. 

Another intriguing opportunity involves the integration 

of space station fluid usage with that of the shuttle vehicle. It 

appears quite reasonable and attractive to visualize the unburned 

reserve propellants aboard each arriving shuttle as usable supplies 

for station operation, and vice versa. 

It is therefore suggested that the Cornucopia concept be 

introduced into the MOL program, first as a passenger experiment, 

and perhaps later as an integral element of the space system. 

• de 

A-24 
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2. Aerial Camera. 

The camera selected for the MOL experiments, as a result of the great 

altitude (150 n.mi.), will of necessity be of the long focal length type. 

focal length shorter than 48", producing a nadir scale of 1:228,000, would 

acceptable:• To improve the photo interpretation capability a longer focal 

length would be highly desirable, and may prove to be essential. 

I 

The system resolution of the camera must be of the highest order possibli, 

with 100 lines/mm representing a minimum in-flight goal, rather than a static 

bench test rating of a lens. This stringent requirement is necessitated by f 

the small image sizes of most naval vessels on satellite photography; for ; 

example, a destroyer imaged on 96" focal length photography at the nadir woulft 

have length-width dimensions of only .00368 X .00036 feet. 

Associated factors, such as image motion, must be carefully considered to, 

prevent the introduction of serious degradation effects on the film imagery. 

3 March 1964 

MEMORANDUM 

From: M. Douglas, NPIC 

To: Dr. W. C. Hall, NRL 

Subj: Comments on MOL Ocean Surveillance 

1. Target Search. 

The astronaut should be provided with high quality binoculars or a 

telescope for target search. This viewer should have a continuously var 

(zoom) magnification capability to assist the astronaut in target evaluat 

once detection is achieved. The viewer and aerial camera should be coord 

("slaved"), so that the optical axis of each continuously tracks the same 

location on the ground. This would insure that photography of a selected 

target is obtained when the camera is activated by the astronaut. 

The astronaut should be assisted in target search by one or more sena 

such as radar or IR, which would provide advance warning and acquisition o 

targets of opportunity on the sea surface. The optical system, on command 

the astronaut, could be guided "on target" by the electronic sensor(s). 

3. Aerial Processor. 

The aerial processor is the final link in the MOL photographic system. I 

terms of photographic interpretation it is equally as important as the camera,..1 

since high quality imagery achieved by the camera can be drastically degraded' 

during the processing stage. The aerial processor ultimately selected for the 

MOL should have a proven resolution capability of 100 lines/mm or greater. 

t 

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. Summary Statement. 

It is realized that the camera and processor requirements as stated 

previously are severe. It must be recognized, however, that the photo 

interpretation requirements for ship surveillance are equally severe. Insufficient scale or image quality could quite easily result in a total lack 

of even a minimal P.I. capability with respect to shipping in the MOL. For 

other categories of Naval interest, such as ports and coastal conditions, the 

photographic requirements are much less stringent and useful information could 

be obtained with less sophisticated camera systems. These latter categories, 

by virtue of their large size and fixed position, present a greatly simplified 

reconnaissance problem. 

The present state-of-the-art in aerial reconnaissance is deemed adequate 

for the development of an MOL photographic system suitable for Navy requirements. 

. MELVIN DOUGLAS 

(If we can assist in any further way, please let us know.) 

A-41 
PROVED FOR 

EASE 1 JULY 2045 

LDLENTTA l. 

Code: 81 

File : 3900 

PROPOSAL FOR A PHOTO INTERPRETATION EXPERIMENT. 

TO BE CONDUCTED IN A ONE-MAN GEMINI SATELLITE 

1. BACKGROUND. 

Unmanned orbiting and deep space vehicles (TIROS, MARINER, RANGER, etc 

have demonstrated a capability for gross aerial surveillance and reconnais 

sance. It is reasonable to assume that in the not too distant future 

improvement in the transmission system will permit the scanning, transmissi 

and reconstitution of high quality images. However, it is felt that these 

images will not be able to match the resolution of modern film em f 

many years to come; even with the benefit of spectacaar advances. 

Further, it can be assumed that by proper programming, a reconnaissance 

satellite could obtain and transmit intelligence of a given target at a 

given time. Advance programming, however, does not readily solve the probl 

of :targets of opportunity." In addition, programming cannot readily solve 

the problem of serectivity - that is "hold" or "cancel" coverage of target 

areiF7WEIEh are obscured by weather. Human judgement may also prove valuabl 

in descrirr areas of significance vice general coverage which would 

result in large quantities of sensor records, of which only a relatively 

small amount would be of real value. 

In view of the above, it appears that it may be desirable to test the 

capabilities of a man in the space vehicle. If he can adequately interpret 

and analyze high quality sensor records and report his finding to earth, it 

may prove a valuable step in determining to what degree human judgement is 

required "on scene" in a space vehicle or whether equal value can be obtained 

by decisions made on earth from unmanned sensors. Further, it will provide 

interimi tionsinto real timeaaerations until high-resolution, 

g 

high

-- 

-s 

1iTity 1 transmission of sensor records becomes a reality. 

2. DESCRIPTION OF PROPOSED GEMINI TEST PROGRAM. 

The two-man GEMINI capsule, with photographic equipment substituted for , 

one man, would be utilized for testing the ability of an astronaut to conduct 

visual search, visual target analysis, and phog2graphirr-excknual4-sarice 

functiong_in_apace. The astronaut, with the aid of optical devices, would 

seek out and study_target.s_stialamaLintezest such as shipping and coastal 

activities, as well land targets of interest. To maintain control in the 

test program, certain pre-selected targets and areas would be assigned the 

astronaut as well as targets of opportunity, thus permitting a more definitive 

evaluation of human performance with respect to known object characteristics. 

Once objects of significance were visually acquired, the astronaut would 

activate a high quality reconnaissance camera under his direct control and 

obtain photographic coverage. Equipment for in-flight processing and viewing 

of the film would be provided to permit in-flight interpretation. The 

Downgraded at 12 year intervals; 

Not automatically declassified. A-42 ---C77112413€44-T.I.A.L.— 
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information obtained from the photography could then be transmitted to the 

cognizant ground station through standard radio communication channels, or 

could be acquired in written form upon recovery of the capsule. This 

information would be compared with that obtained from analysis of the photography at NAVPIC, and from known data on the pre-selected targets. The 

results of the test program would indicate: 

a. The value of in-flighthEELjudgement in a space surveillance 

system. 

b. The capabilities and limitations of optically-aided visual search 

and target analysis. 

c. The level of information obtainable frominflight photographic 

interpretation, when compared with ground analysis at NAVPIC. 

d. The relative merits of visual vs. photographic surveillance. 

e. The value of real time intelligence reporting. 

3. RECONNAISSANCE CONSIDERATIONS. 

a. Objects of Intelligence Interest. 

Ocean surveillance, or more specifically the location, identification, 

and course of ships is of obvious concern to the Navy. Since both manned and 

unmanned satellite surveillance systems for ship reconnaissance are being 

considered by the Navy for possible development, the performance of the 

GEMINI astronaut would provide guidance for future planning in this realm. 

An astronaut, with the aid of high quality optical viewing devices, should 

be capable of detecting shipping of varying categories and photographing 

vessels of interest. The typical dimensions of some U. S. Naval vessel 

classes are given in Table I and will be referred to in a later paragraph. 

It should be noted that ship"..s_wake is a valuahLeAetection aid in most cases 

and will be of special significance in detecting ships of small size. 

Coastal targetsx_such as ports, by their nature are geographically 

fixed anal5Fesent no great problem to surveillance from spacp. Pattern 

an ysis, not poMle wilt:individual objects such as gniff, will assist 

the astronaut in his study of coastal facilities. 

The successful detection and analysis of land targets of intelligence 

interest (new missile sites, for example) will be dependent upon the usual 

reconnaissance factors: size, shape, contrast, degree of concealment, 

associated clues (smoke, road networks, etc.) and others. Interruptions in 

the predominant land use or vegetative patterns will serve to direct the 

astronaut's attention to locales of possible military activity. 

A-43 -Celti•PIENGNZIA.L.- 
APPROVED FOR 

ASE 1 JULY 2015 

--COTrritErE. 

TABLE I 

TYPICAL U.S.N. SHIP DIMENSIONS (FEET) 

Overall Length Overall Wi 

CVA(N) 1100 252 

CVA 1039-47 252 

CGN 721 73 

CA 716 75 

CL 610 66 

DD 418 45 

SSBN 410 33 

SSN 278 31 

SS 312 27 

b. Basic Data 

The proposed GEMINI capsule will operate at an orbital altitude of 

150 nautical miles. Table II presents some pertinent photographic data wit 

respect to surveillance from this altitude. (Scale data:are for center of 

format and are approximate for high tilts). 

TABLE II 

PHOTO DATA FOR 150 N.M. ORBITAL ALTITUDE 

CAMERA TILT 

ANGLE 

SLANT ARC 12" FOCAL LENGTH 

RANGE(N./0)1 DISTANCE(N.M.)2 X SCALES Y SCALE4 

0

o 

150 0 1:912,030 

30° 174.5 87.3 1:1,060,995 

60° 322.8 279.8 1:1,962,688 

73°22'27" 1026.6 997.6 1:6,241,933 

(Apparent horizon) 

24" FOCAL LENGTH 

X SCALE Y SCALE 

- 

1:1,216,037 

1:3,648,111 

1:456,015 

1:530,498 1:608,014 

1:981,344 1:1,824,060 

1:3,120,966 

1 Distance from camera to intersection of optical axis with surface of earth. 

2Distance from ground nadir to above intersection. 

3Scale parallel to horizon. 

4Scale perpendicular to horizon. 

A-44 --eltottF41;61.4a-LA-L.— 

--"0".41411111111111111.11111101 111■

•••••""emmono...-------- _9111141111111111111111111.1111Pummor 
NRO A 

RELE 

ONI-IDEDITIAL 

The area of coverage of a photograph is dependent upon photographic 

format, focal length, camera altitude and attitude in space. Table III 

provides ground distance data with respect to the principal parallel (x axis) 

of a photograph of zero swing (70mm format). 

TABLE III 

52 

52 GROUND DISTANCE (N.M.) REPRESENTED BY PHOTO PRINCIPAL PARALLEL 

hiidt 

2015 

73 

75 i 

66 

;5 

33 

1 

7 

e of 

a wit 

of 

Tilt Angle 12" F.L. 24" F.L. 

0° 28.1 14.1 

30° 32.7 16.4 

60° . (Approx.) 60.5 (Approx.) 30.3 

Table IV indicates the image sizes of ship classes to be expected on 

photography of zero tilt at an altitude of 150 nautical miles. While it 

appears that these images would not be normally visible to the naked eye, 

it is anticipated that at least the larger ones should be detectable through.' 

high quality optical aids. A high quality camera system should provide 

image sizes which are adequate for photo interpretation. (See paragraph 3d.) 

TABLE IV 

,E4 Length 

CVA(N) .00121 

6,037 C.7% .00114 

8,111 CCN .00079 

C.+ .00079 

.... .00067 

2D .00046 

:SAN .00045 

SS\ .00031 

SS .00034 

12" F.L. 

IMAGE SIZE 

Feet 

24" F.L, 

Feet Inches Inches 

Width Length, Width Length Width Length Width 

.00028 .01452 .00336 .00241 .00055 .02892 .00660 

.00028 .01368 .00336 .00228 .00055 .02736 .00660 

.00008 .00948 .00096 .00158 .00016 .01896 .00192 

.00008 .00948 .00096 .00157 .00016 .01884 .00192 

.00007 .00804 .00084 .00134 .00014 .01608 .00168 

.00005 .00552 .00060 .00092 .00009 .01104 .00108 

.00004 .00540 .00048 .00089 .00007 .01068 .00084 

.00004 .00372 .00048 .00061 .00007 .00732 .00084 

.00003 .00408 .00036 .00068 .00006 .00816 .00072 

:h. 

c. Visual Factors. 

The limit of resolution (visual acuity) of the human eye has been the 

object of study for years. Most of the data available are the result of tests 

performed in the laboratory under controlled conditions of contrast, target 

luminance, etc. It has been found that the resolution of the eye is dependent 

upon both physical and physiological factors. In addition, the nature of the 

target being viewed has significance in the resolution level obtained. Point 

source targets indicate a normal eye resolution limit of 30 seconds of arc, 

1L A-45 
A-46 

O APPROVED FOR 

EASE1JULY2015 

—"'et+NI"F"4"ra•OULLiell.„ 

whereas line targets produce a resolution limit of about 1-2 minutes of arc 

Very low target luminance or contrast values significantly reduce the visual 

acuity of the eye. One goal of the GEMINI test program.will be to investiga 

the visual acuity of the human eye with respect to viewing the earth from a 

position in near space. Because of the small viewing scale, the astronaut 

will be assisted by an optical telescope or binoculars. 

d. Photographic Factors. 

The small photographic image size of Naval vessels (Table IV), even 

of large aircraft carriers, indicates the need for a high resolution photographic system of adequate focal length. A focal length of 24" is suitable 

for the proposed GEMINI test program, provided that sufficient resolution is 

maintained in the camera and processing components to overcome the small 

photographic scales. The use of a 12" focal length, although increasing 

ground coverage and redticing image motion problems, would severely restrict 

the quantity of information obtained from the photography. This ground 

coverage gain with 12" photography is not significant since the astronaut 

will be directing the camera towards specific objects or locales, rather 

than attempting broad area coverage. 

To obtain adequate photographic imagery, the camera system components 

utilized in the GEMINI capsule should be selected with care. Film emulsion, 

camera optics, and image motion compensation are among the many factors to be 

considered. For example, no film emulsion of less resolution than Panatomic-X 

Aerial Film would be desirable in the proposed test program. This film has a 

low contrast static resolution capability of 65 lines per millimeter. Several 

24" aerial reconnaissance lenses (Table V) are currently "on-the-shelf" or 

Navy test items and could be considered for the GEMINI program. Static 

resolutions with 50213 film are in the AWAR range of 80-100 lines per millimete 

The marriage of lens cone and camera, with IMC magazine, would require approxi 

mately three months and could be accomplished at the Aeronautical Photographic 

Experimental Laboratory, NADC Johnsville, Pa. The weight of the camera system 

and associated components would be compatible with the removal of one astronauti 

4 

Equipment for processing the exposed negatives would be installed in 

the GEMINI capsule to enable the astronaut to perform photo interpretation in 

space. This equipment should be compact, reliable, compatible with the capsulei 

environment, and capable of maintaining good image detail. Various methods 

exist for in-flight processing of aerial negatives. One non-liquid method 

developed by Kodak provides a processed negative and positive in 15-20 minutes 

and retains a resolution of 50 lines per millimeter on Plus-X film. Each inflight processor would be evaluated in detail, prior to final selection fOr 

inclusion in the GEMINI system, to assure that the previously stated requirements were met. 

Extensive flight testing of various Naval camera systems at Edwards 

Air Force Base in 1960 indicated that system resolutions of 55 lines per 

millimeter were attainable at that time with certain 70mm cameras. If this * 

resolution were achieved by the proposed 24" GEMINI system, each line of 

resolution would represent 27 feet on the ground at zero tilt. Research has 

revealed that even at a ground resolution level of 50 feet, photo interpreters 
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arc able to identify ships, storage tanks, buildings, runways, etc., and that 

some useful information may be obtained at still poorer ground resolution 

levels. Provided adequate film scale and resolution, the photography obtained 

in the GEMINI capsule should be suitable for the level of interpretation 

required for the test program. (In future systems, more sophisticated equipment could be used than that envisioned for the GEMINI capsule.) 

e. In-flight Photographic Interpretation. 

Sufficient photo interpretation equipment would be provided the 

astronaut to permit in-flight analysis of the processed photography. This 

equipment consists of a few direct viewing optical devices and other miscellaneous tools. The photo interpretation equipment is highly compact, light 

weight, and necessitates only a minimal expenditure of capsule space. A 

skeletal set of P.I. tools could consist of one variable magnification viewer 

(pocket size), a small 12" X 12" light table (one inch deep), film marker, 

pencil, .001 and .5mm scale and paper pad for notes. Since it is not reasonable to expect the astronaut to perform detailed metrical operations in this 

test program, no photogrammetric devices would be required. 

Training of the astronaut for the photo interpretation phase of the 

mission would be accomplished at NAVPIC. The training would include interpretation techniques with small scale photography and reporting procedures 

applicable to the test program. 

4. COST FACTOR. 

APEL estimate - very roughly - $30,000 (labor and parts) 

NAVPIC.estimate - very roughly - $10,000 (training and equipment) 

A-47 ---trarrirte,s147,z4.4___ 
di Resolution* 

a 

24" LENSES 

Dimensions 

25" length, 8" diameter 

25" length, 8" diameter 

7 " 2 length, 12" diameter 

28" length, 7" diameter 

e Resolution. *Area Weiehted Avera 

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A-48 ..-C-Clarazirtrterterr— 
NADC ltr 0038 4 

2/25/64 

PHOTOGRAPHIC OCEAN SURVEILLANCE TEST PROGRAM 

TEST OBJECTIVE 

To assess the capability of a high resolution photographic 

issance system to perform surveillance over ocean and coastal 

s. Determine optimum sensitized materials required as well as 

fading in the environment of a manned space vehicle. Determine 

test the optimum method for accomplishment of the final phase 

test which will be the addition of a photographic transmission 

tem with readout stations on shipboard and ground areas. A 

resolution of 12 feet, from 200 miles is considered to be 

listic at present for the photographic system. 

. DCPORTANCE OF TEST 

To achieve the maximum resolution potential of reconnaissance 

equipment installed in space vehicles for surveillance of terrestrial, 

liar and possibly other planetary bodies is one of the major objectives. 

In addition, it is planned to obtain valid data on the suitability of 

equipment provided and to determine possible further design changes 

which may be required. It will permit assessment of the performance 

of various films when used in the space environment and provide guidance for possible changes which may be required in respect to preparation of the sensitized materials i.e. emulsion characteristics, 

spectral sensitivity and etc. Also, tests of in-flight processing 

methods would be performed with fibs exposed in the laboratory using 

resolution targets as the quality determinant and processing half of 

the film on the ground and half in the space vehicle. An optimum 

in-flight processing method would be determined using wet methods 

as well as a sandwich (semi-dry) method such as Eastman Kodak Bimat 

or any other method which has been found to possess a high resolution 

potential. 

III. DESCRIPTION OF THE EXPER/MENT 

The experiment would be &Prided into a Phase I and a Phase II 

effort. Phase I would be ready for installation within 18 months 

after funding. The tests involved in this phase could be accomplished 

in one or two flights depending on the availability of astronaut time 

to devote to the required tasks. 

a. Configuration of Test Items 

PRASE 

(1) A high acuity 44" x 44" format camera equipped with 

a 46 inch focal length f/4 lenl-Walaiii-of resolving 100 lines/mm. 

:,ngradvd al 3 year intervals, 

:)..cla,sified after 12 years. A-49 
O APPROVED FOR 

ELEASE 1 JULY 2015 

—ZT717rirmattp+4,4,.... 

Such a camera, which Lecke some of the additional design features 

considered necessary, has been proposed hAtrwt yet developed by 

Chicago Aerial Industries and is designated as ibi-CA=101. However, 

certain changes would be required in the focal plane shutter nechanism 

within the camera body es well es a larger caner, body to eliminate any 

possible vignetting by a Lens of 48 inch focal length. In addition, 

changes to the basic CA-101 camera concept are required to provide for 

film flattening using compressed air (Note: very little air is required) 

provided by a prostitute's(' air container. Tice camera itself is not 

pressurised sad the air vents to the ambient atmosphere within the 

vehicle after each exposure. The camera is equipped with a rotatable 

mirror permitting an extended transverse field of view. Dependent upon 

altitude, total angular coverage desired, and forward overlap consideration 

transverse coverage of 35° could be provided by sequential pulse panning 

the camera through seven positions. The 48 inch focal length lens covers 

5° on the 41/2" x 43/4" format. Magazines of 500 feet, 250 feet end 100 feet 

file capacity are intended for use in test of various types of film. The 

lens is partially patterned after one currently under development for the 

U. S. Navy by tairchild Comore and Instrument Corporation, West Coast 

Division. See enclosure (2). 

(2) Concurrently with the above described test for Phase I, 

it is intended to perform Tumorous sensitcmetric tests or various types 

of films both inside and outside of the space vehicle using containers 

capable of providing shielding against radiation and pressure environment. 

Simultaneous monitoring of inside aid external environment will be made 

at specified intervals. The containers for film will be designed by the 

Aeronautical Photographic Experimental Laboratory (APEL) and fabricated 

either in prototype shop or under contract. 

(3) The two in-flight processing test equipments will be 

either designed and fabricated by APEL or contracted for if the workload 

should prove to be excessive during period whaa equipment nes to be 

produced. As previously noted, the in-flight processing tests could 

be performed on the first flight depending on the limitations imposed 

on the astronaut by operating the various other teat equipments installed 

in the space vehicle. 

PEE I/ 

(1) In this phase the photographic trenemicsion system is 

to be added to the camera. A new airborne scanner is currently under 

development for a 431" x 41/4" format camera system which is due to be 

delivered to APEL in 1964. This system will be tested in the A3D-2P 

aircraft, and will provide data useful in ascertaining the required 

design changes to upgrade the resolution of the system for space application. The in-flight processor being developed by CBS for this system 

could also be assessed for possible suitability in a space environment. 

It is anticipated that the current designs and prototypes for other 

in-flight processors will serve as an essential background to the 

designs for this application. 

A-50 
NRO APPR I FOR 

RELEASE 2015 

—777111015-E-N-T45,4.-._ 

(2) Specific equipments to be developed for Phase IT. 

(a) High resolution scanner to be completed during 

atm 

any 

or 

.red) 

1966-1967. 

1906-1967. 

(b) Airborne transmitter to be completed during 1966-1967. 

(c) Ground and shipboard receivers to be completed during 

le b. Test Support Equipment Required 

upon 

devotion No requirement for special test equipment other than that 

aning already available is foreseen at the time of this writing. 

covers 

0 feet c. Test Procedure 

. The 

or the (1) Man's role is estimated to be the following: 

st 

e I, 

YPes (b) Record status of environment within and outside of 

.are vehicle as tests are being conducted. 

onment. 

made (c) Perform assigned tasks required in the determination 

7 the of optimum in-flight processing methods for space usage. Cbtain 

ated orerating data and observe performance results. 

(d) In the final phase, when the photographic transmission 

,e is used, voice communication with ground and shipboard stations will 

-klood be required to advise on transmission start and finish times. 

_d (e) Although the test procedures performed by astronaut 

ed will be well within his technical competence, voice communication with 

?tailed stations will be required to advise him on possible minor difficulties 

which may arise. 

d. Category of Experiment 

is Category b is perhaps most applicable to these experiments. 

Jar Except for optical port for camera lens, availability of voice 

communication, provision for storage of special film containers 

outside the vehicle, and antenna requirement in last phase of teat 

of the photographic transmission system, it is not expected that the 

)pli- equipment for this experiment would affect the design characteristics 

system cf the m01.. 

neut. 

r e. Cost is estimated as follows: 

(1) Phase I 

(a) Maintain record of films used and perform visual 

observation at selected times when recordings are being made. 

A-51 ---CONT413F411.X.L11.6. 
.71 

OVED FOR 

EASE 1 JULY 2015 

(a) 41/2" x 41/2" High Acuity Camera Development $250,000 

(b) Controls for Camera 10,000 

(c) Spare Magazines for Camera 15,000 

(d) Cost of 48 Inch f/4 Catadioptric Lens 

(Fairchild) 80,000 

(e) Camera Equipment Installations 20,000 

(f) Camera Port 15,000 

(g) Subtotal for Camera Equipment and 

Installation 390,000 

(h) Subtotal for Coat of Film Sensitivity 

Experiment 20,000 

(i) Subtotal for Cost of in•Flight Processing 

Experiment 60,000 

(j) Cost of Contract Labor Involved in Performing 

Installation for Items (h) and (i) 20.000 

Total of (g), (h), (i) and (j) $490,000 

(2) Phase II 

(a) Specifications for the transmission system will be 

prepared upon completion of the 41/2" x 4N" format line scan system, 

which it is estimated will be evaluated in the latter part of 1964. 

It should be funded early in 1963, but at this point only a very 

broad estimate can be made relative to development cost of the 

transmission equipment which will consist of the following: 

One each • Scanner and Processor 

One each • Transmitter 

Two each • Ground Stations 

(b) Rough Estimate $950,000 

Tttal of (1) and (2) • $490,000 1- 950,000 • $1,440,000 

NOM: Detailed technical data on the requirements, configuration and 

installation of the photographic transmission system will be forwarded 

shortly. Substantial savings may be possible prior to the initiation 

of Phase II if it is found that current developments being made for the 

photographic transmission system are found to be applicable to the 

space program. In addition, small savings may also be possible by 

using available film magazines for Phase I. 

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PROVED FOR 

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--7017rrtrEt++44.1.--- BIN ltr 00432 

of 2/20/64 

Title of experiment: Optical Surveillance sensor Experi!:ient 

J. Test Obiective 

The objective of this experiment will be to determine the capacity 

and capability of the combination of a man and a semi-automatic recording 

optical surveillance sensor. 

11. Importance of the Test 

This test is required to determine the utility of a man as an integral 

portion of a single or multisensor surveillance system. The space environment 

will be required to provide a complete test and since man is required for the 

test, HOL is the appropriate test vehicle. 

111. Description of the Experiment 

The experiment will consist of a series of tests to determine the 

handling rates for automatic and manual sensor operation including target 

selection and rejection; to determine the effects of manual operation on 

sensor requirements such as field of view, pointing accuracies, resolution 

requirements, etc.; to determine the capability of man for data correlation 

by detailed observation in conjunction with an automatic gross area surveillance sensor. The problems which may be encountered are weather restrictions, 

excessive target rates, fatigue, etc. 

c. Test krocedure 

The tests envisioned will be a series of comparative tests to 

provide a basis for comparing the performance of the manned system with the 

automatic system and deternine the limits on the parameters of interest. 

This can be accomplished by using suceeding passes over the same areas or 

parallel systems of manual and automatic sensors. The determination of the 

effects of incorporating a man in the system on the sensor requirement will 

be determined by varying the operating parameters of the sensors to define 

the effective limits in both manual and automatic modes on the same or 

similar targets. 

Man is an integral part of the sensor system to be tested. He will 

be utilized as an intelligent sensor and as a technician for the comparative 

test against which his performance will be measured. 

J. Cateeory of Experiment 

This experiment will be category a. It will require at least 

openings for the optics and antennae, sensor stabilization, and support 

equiment. 

A- 54 
NR OVED FOR 

RE 1 JULY 2015 

C ("NFU) ENT LAL 

S. sal (in thousands) 

WEE 

tngineoring A 

Development 

Integration 

Installation 

Aga 

Simulators/Trainers 

Data Reduction 

tquipment Work 

Trawl 

1101. ELM FY 1967 120 FY 69 

500 750 1000 500 500 

500 1000 

200 300 200 700 

200 

300 500 

10 15 15 20 20 

PCP in Process 

18, 

3'0 /4/(es--02s76 asio I -W 

A- 55 

_VC 
OVED FOR 

LEASE 1 JULY 2015 

5307-125:IHP:lac 

6 March 1964 

SUBJECT: MOL Forward Looking Radar 

1. The Radar Division has looked at several types of radar in the frequencyrange of 300 to 10,000 Mc which will provide a forward looking capability 

and be able to detect ship size targets. Without discussing reasons at this 

time it has been decided that the frequency range of 1000 to.10,000 Mc.is 

likely to be the best compromise from the standpoint of reasonable antenna 

sizes and reasonable power requirements. Because of complexity, weight, 

and resolution limitations, electronic scanning techniques were eliminated 

from consideration. The remaining two methods are (a) Rotating antenna 

providing 360° coverage in a range band of 200 to 300 miles projected ground 11 

range, and (b) Two fixed beams canted at ±45° from the projected ground path, 

providing 2-70 mile wide ground swaths of coverage 140 to 210 mile coverage 

each side of the path. System (a) gives complete coverage of a 600 mile wide - 

swath, with 40 to 60 seconds alerting time on targets in the forward quadrant. I 

System (b) has a hole in the coverage so that only targets offset from the 

path will be detected, and the alerting time is about 30-40 seconds on those 

targets within the coverage area. 

2. Both of the above methods could be instrumented at any frequency in the 

microwave region. Weather and sea clutter considerations somewhat favor the 

low end of the region, but antenna size would favor the high end. The 

A-56 

TO : Code 7000 DATE: 

FROM : Code 5307 
NRO A 

RELEA 

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tquency 

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FOR 

2015 

E31444.QE.1=4.14.4.--- 5307-125:110:lac 

following summary sheets will list the parameters of a type (a) system at 

1500 Mc and at 3000 Mc and one type (b) system at 10,000 Mc. It is apparent 

that size, weight and power requirements are not greatly different, and if 

a rotating antenna is practical its advantages in coverage and target observation time are very significant. 

. J 

I. H. PAGi 

Consultant 

Radar Division 

A-57 CONrIDENTIAL. 
APPROVED FOR 

RELEASE 1 JULY 2015 

—Carrriftst*-T-44.1-__ 5307-125:IHP:lac 

TABLE 1 

Type (a) System -- 360° Scanning Antenna 

Frequency - 1500 Mc 3000 Mc 

Antenna - 30' x 5' 15' x 2.5' 

Horizontal beamwidth - 1.5° 1.5° 

Vertical beamwidth - 10° 10° 

+ 24 Gain - 41 2 = 32.5 db 32.5 db 

Rotation rate - 1 rps 1 rps 

Power - 50 kw peak 1 Mw peak 

200 w average 1 kw average 

Transmitter - VA131B TWT VA87 klystron 

Pulse rate - 720 per second 240 per second 

RF sequenced through 3 frequencies single frequency 

Pulse length - 5 psecs 5 psecs 

Pulse compression to .1 psec .05 psec 

Hits per scan - 3 1 

Number of scans/target - 20 20 

Modulation - grid plate 

Display - modified PPI - pulse stretched modified PPI - pulse 

stretched 

Range on 100 M2 target - 285 nautical miles 350 nautical miles 

Mean clutter return - 40 M2 equivalent 40 M2 equivalent 

Slant range - 220-310 220-310 

Weight and power - 6500 - 3 kw 11300- 6 kw 

A- 58 
RELEAS '2015 

:lac 

TABLE 2 

Type (b) System -- Fixed Antennas 

Frequency - 10,000 Mc . 

Antenna - 401X 8" - 2 required 

Beamwidths - .2° X 9° - depressed 30°- - offset 45° 

Gain - 42 41). 

Observation time - seconds 

Number of hits - = 20 

Peak per - 50 kw - 2 required 

Average power - 100 watts 2 required 

Compressed pulse - .1 psec 

Transmitted pulse - 10 p,sec 

ncy Range on 100 N5 target - 350 nautical miles 

Spot Axe.- 50' X 1 mile = 300,000 square feet = 30,000 square meters 

Equivalent mean sea clutter area ft 30 square meters 

Swath coverage FtS 140-210 wiles each.side,'about 150 miles ahead of vehicle. 

Alk$,0:f rvioort;Pr 7Lo Cnyt•-, /)Q711 

- pulse 

miles 

ent 

A- 59 —ctirriPmertrzorp— 

C751■TrirreN 5307-125:INP:lac 
O APPROVED FOR 

LEASE 1 JULY 2015 

5307-125:1RP: 

TABLE 3 

Type (a) -- Rotating Antennas 

1500 Mc 3000 Mc 

Weight Power Weight Power 

Antenna 100 lbs 50 lbs 

Transmitter 90 365 

Power supply 100 1.85 kw 200 4.0 kw 

Modulator 50 .2 100 1.0 

Receiver 25 .2 25 .2 

Frequency generator 25 .2 25 .2 

Pulse compressor 25 .1 25 .1 

Display 50 .2 50 .2 

Drive motor 25 .2 15 .1 

Packaging 100 200 

Miscellaneous 50 75 

640 lbs 2.95 kw 1,130 lbs 5.8 kw 

A-60 ---ara-TrrmaN-T-44.6— 

Sfy 'X 'IMAM 
5307-125:IHP:lac 

TABLE 4 

Type (b) -- Fixed Antennas 

Unit 

weight 

Number 

required Weight Power 

Antennas 50 lbs 2 100 lbs 

Transmitter 90 1 90 

Power supply 100 1 100 1.85 kw 

Modulator 50 1 50 .2 

Receiver 25 2 50 .4 

Frequency generator 25 1 25 .2 

Pulse compressor 25 2 50 .2 

Display 50 1 50 .2 

Packaging 100 1 100 

Miscellaneous 50 50 

665 lbs 3.05 kw 

8 kw 

A- 6 1 —C-€014F-IDZALTIAL_ 

kw 

3 2 

2 

1 

2 

1 

N 

RELEA Y 2015 

IP:la 
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Fig. 2 - PPI Display with Memory 

A-62 

- Ot•• -• -•-•IF 

O APPROVED FOR 

RELEASE 1 JULY 2015 

5307-125:IHP:lac —rarrirterEg.T.441.,_. 

N. • 44/ 

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Fig. 3 - Side View -- Type (a) System 

Fig. 4 - Bottom View -- Type (a) System 

A- 6 3 
APPROVED FOR 

EASE 1'JWLY 2015 

C ON F ID N T LA-L— 

Velocity 

A 

MOI. 

5307-125:10:lac 

ve,eP 

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Fig. 5 - Top View -- Type (b) System 

A-64 —CDT11615e14-T-124.45— 
NR OVED FOR 

REr 1 JULY 2015 

7 

AWM 

20 Feb 1964 

TITLE OF EXPERIMENT. Global Television Surveillance 

TEST OBJECTIVE. The ultimate objective is the development of a high data 

rate television global surveillance system for the night side of the earth. 

The investigation viii establish the possibility of detecting, classifying 

and identifying from satellites surface ships and surfaced submarines by 

their own lights or wakes, ambient illumination ranging from starlight to 

full moonlight, with and without searchlighting by a laser beam. Other 

objectives include the inferring of the approximate sea surface condition 

and the experimental determination of the size of the surface object that 

can be resolved. Meteorological data such as cloud cover would be available for comparison with information from weather satellites Tiros and 

Ninbue. 

Favorable results in the investigation will make possible the systematic 

development of a global surveillance system, both visual and film recorded. 

IMPORTANCE OF THE TEST. The test is needed to make visual and film 

recording measurements, to establish optimum ranges of parameters and to 

determine the merits of a potential surveillance system. 

The tests should be conducted in MOL because the presence of a man is 

required in the following: optimization of adjustments to equipment, 

modifications in the experiment, selection of scenes viewed, proper 

orientation.of the satellite including image motion comjensation and 

visual comparison with the permanent film record, with and without laser 

searchlighting. MOL will make available suitable payload and power for 

the proper prosecution of the proposed experiment. In addition, the 

astronauts can analyze, collate and interpret the sensor data from selected 

areas of interest in a minimum time. This test will help assess man's 

ability and utility as part of a visual and film recording global surveillance system, particularly on the dark side of the earth. 

It is necessary for the Navy to learn the possible nature and form some 

estimate of the effectiveness of satellite surveillance units of potential 

enemy countries. Such information would be the basis for the development 

of suitable countermeasures. 

DESCRIPTION OF THE EXPERIMENT. 'Wing the monitor of the low light level 

television coupled with the proper optical system (estimated focal length 

Clt in.), the astronauts will determine how well they can detect the 

presence of and identify lighted ships at locations known to them on the 

dark side of the earth, ambient scene illumination ranging from starlight 

to full moonlight. Throughout the experiment the ship's spatial orientation, 

--9641441:153=1A1..--, 

Downtzradeci at 3 year intervals; 

:Declassified after IL years. A - 65 
RO APPROVED FOR 

ELEASE 1 JULY 2015 

A-66 

attitude rates, velocity, altitude, location, time etc., will be recorded.: 

The experiment will be performed with various levels of laser searchlight 

illumination. Photographic film records will be tate of the scenes 

viewed. The detection system will be properly adjusted and its performanc 

optimized during the course of these tests. The experiment will be 

repeated using as targets the high contrast wakes of unlighted ships and 

the ships themselves under laser beam illumination. Having obtained experience with the detection system, the astronauts will continue the 

experiment into the search and surveillance potential phase. They may 

orient the satellite, vary searchlight intensity, focus the system, 

photograph the scene, observe it visually, communicate with ground stations 

etc., as the like to learn what they can about unspecified targets below 

them. From the film record and the astronauts' description of what they 

observed under a wide range of conditions and knowing the type and location of targets on the earth under the orbital path, it will be possible 

to determine whether the detection system is adequate and the best course 

to be pursued in improving the crude and unsystematic surveillance procedure 

a. Configuration of Test Items Estimated 

Vol.(in.3) Wt.(lbs.) 

(1) TV Camera log 4o 

(2) Camera Control Unit 1064 25 

(3) Viewing Monitor 343 5 

(4) Recording MOnitor and Photo Camera Uait 230 10 

(5) Monitor Electronics and Equipment 

Control Unit 200 a) 

(6) Experiment Control Panel 12 1 

(7) Laser Searchlight 500 30 

b. Test Support Equipment Required 

Not known at present. 

c. Test Procedure 

(1) The man will ;:urn on the detection system, adjust it for 

optimum performance, adjust searchlight illumination level, record scenes 

of interest, observe these scenes visually and simultaneously, evaluate, 

interpret and note what is observed. The man will orient the spacecraft 

and compensate for image motion as required. 

(2) and (3). See the DESCRIPTION OF THE ELPERIMENT. 
OVED FOR 

1 JULY 2015 

--"CannsiNgua,,_ 

d. Category of I:eminent 

ze 

ne 

Category b 

e. (blot 

(1) tad 

Development 

(2) Inetaletien 

(3) Ground Support 

t. Schedule 

IT65 pr66 IT67 T68 1y69 TOTAL 

50K 100K 600K 100K 50K 900K 

25K 50K 300K 25K 25K 425K 

25K 100K 50K 25K WOK 

/::;o0 39TAL 

1525K 

lure . 

Strdvare reedy for test January 1967. 

PA/W=7MM OCYZNIKINT AMC!. U. 5. Naval Air Development Center. 

ADDTTIOUL SSOISIMMITS. Security clessifiostion: COSTIDINTIAL 

Additional information vill be furnished *ma experiment is more thorough-1Y 

plenned. 

t 

A- 6 7 
O APPROVED FOR 

LEASE 1 JULY 2015 

U. S. NAVAL AIR-DEVELOPMENT etivra 

ANTI-SUBMARINE WARFARE LABORATORY 

JOHNSVILLE, PENNSYLVANIA 

AW -42 

12 Nov 196 

Proposal for EXperiment N-10 

LOW LIGHT LEVEL TELEVISION FOR PROJECT GEMINI 

INTRODUCTION 

The primary purpose of the experiment is to investigate the possibility of 

detecting from satellites the presence of surface ships by their own lights 

or wakes, ambient illumination ranging from full moon to starlight. Secondary 

goals include the inferring of the approximate sea surface condition and the 

experimental determination of the surface object size the system can resolve. 

A television monitor will be provided for visual observation while a separate 

monitor will be employed to obtain a photographic record for detailed postflight analysis. 

"Detect the presence of" is the phrase employed to esphasize that the television system, with its comparatively short focal length lens, is not 

expected to resolve even the largest ships in the sense that details can 

be seen. Rather, the energy from the various sources of light associated 

with ship targets will be processed'to provide' immediate detection capability 

for the astronaut without requiring his dark adaptation. The best resolution 

compatible with a sufficiently high detection capability will be the goal 

is the desigo.of the system. 

The experiments should indicate the effectiveness of a low light level viewing system as a visual aid for the astronaut. For example, yaw maneuvers 

using cloud references on very dark nights may be carried out. The identification of ground characteristics, such as small islands, should also be 

made easier, especially at low light levels where non-dark adapted viewing 

is of little value. A study of the photographs taken during the controlled 

experiments will help determine the merits of a low light level system for 

general target recognition. 

The detection of surface ships has military implications, since the experiment ,.. 

may reveal whether the nighttime movements of our own fleet can be regularlty 

monitored by others using cowerableLmeans. Still another area of value is 

the possible application of a similar system for examining the dark side of 

the moon where the atmosphere and airglow are absent; information obtained 

from the earth orbit experiment would be useful. 

A-68 

Jae, anlawar... 
NRO i ED FOR 

REL JULY 2015 

AW-42 

It is intended to make a three way comparison by obtaining the opinions of 

one astronaut viewing the monitor, of the other astronaut viewing the same 

scene directly, and comparing these with the photographic record. The men 

aboard Gemini will also be able to select targets of opportunity, control 

the attitude of the spacecraft, and even provide almost, complete image motion 

compensation which will be useful in evaluating the system's capabilities. 

The experiments presented would be conducted best in a manned spacecraft. 

Where the astronaut is part of the experiment or performs some selective 

function, there is no alternative to a manned vehicle. The astronaut, in 

addition, contributes valuable flexibility which may be required if changes 

in the experiments are necessitated because unexpected or =predicted 

situations arise at launch or during orbit. 

ary 

- e. 

.te 

ity 

ion 

2W1 - 

g 

ed 

r invent : 

:rly 

is 

of 

311. 

DESCRIPTION OF EXPERIMENT 

A. DETECTION OF SHIPS AND SHIP WAKES 

1. Lighted Ships. Ship lights will raise the illumination level on 

certain areas of the ship to relatively high values, 107.1 to better than one 

foot candle, compared to the ambient light, 10-2 to 10-* foot candles for 

full moon and no moon respectively. The low light level system will then be 

used to take advantage of this high concentration of light energy against 

the essentially black ocean background that will constitute most of the 

monitor presentation. Immediate detection of the bright "blip" representing 

the lighted ship should be possible with no need to dark adapt. 

2. Ship 'Wakes. In a calm sea, the wake of a ship may present a long, 

high contrast ribbon of highlights because of moonlight reflecting and 

glinting off the disturbed water. The light emanating from the wake path 

may be expected to show up on a photographic negative obtained from a monitor 

different from the less coherent variations of light produced by the undisturbed sea. The experiment will also show whether the length of the wake 

Will permit in-flight detection on the monitor screen because of continuity 

effects. In addition to length, the changing utter slopes within the wake 

should give rise to a scintillation effect. Whether this will aid in real 

time detection can also be learned during the experiment. 

3. Unlighted Ships. The focal length of the camera lens in relation to 

the orbital altitude, along with other considerations, makes detection of 

unlighted ships very unlikely, especially if there is little or no wake. .In 

general, the calmer the sea, the more likely is it that the ship can be 

detected if it is possible to do se at all, because then the ship itself 

stands out in maximum contrast with the water. The experiment may give some 

answers in terms of the ambient light' level, ship size, and sea condition. 

A-69 
PR• D FOR 

RELEASE 1 JULY 2015 

AW-42 

B. OTHER SHIP UPERIXENTS 

1. Flare and Smoke Tests. Recovery ships will display lights, release 

flares, and generate smoke for observation on the monitor. Some flare tests 

will be possible even through light cloud cover. 

2. Dye Marker Tests. The astronaut can determine the effectiveness of 

the system in revealing the extended image of a dye marker in terms of ambi 

light level, and size of the marker. Such markers may be useable as fixed 

reference points on a calm ocean, and thus aid in attitude control for other 

experiments. 

C. COARSE DRITHMINATION OF SEA CONDITION 

Photographs of the sea will be made over rough and calm areas. It my 

be possible to infer that the sea 'me very rough, rough, or very calm by 

analysing the density noise variations over an adequate number of photographs 

taken from the monitor. The experiment will also determine whether the 

scintillation effect is pronounced enough to make in-flight observations 

possible. 

D. DETERMINATION OF MISTEK MOLT:MON 

Overland photographs will be made at various light levels and ground 

haze conditions to-determine the resolution capability of the low light level 

system. Some of these photographs should be made using Image Motion Compensa 

tion which oould be supplied by the astronaut. In all cases, the attitude 

and rotation rates of the capsule should be known. 

TECHNICAL DISCUSSION 

A. OPERATIONAL DESCRIPTION 

As discussed previously, the TV system will be used to detect the presence 

of ships at sea. This will require that ships be positioned as nearly as 

possible directly under the flight path of the satellite. 

It is plOnned that the experiments be performed during orbits when the 

spacecraft will fly over these ships on the dark side of the earth. 

1. Proposed Targets 

a. Specific targets 

A-70 
Be 

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3 of 

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1.4 

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Conditions 

1) 

no trackingof targets 

2) 

dark side of earth 

1) tracking of targets 

I 2) dark side of earth 

1) 

trackingof targets 

2) 

dark side of 'earth 

1) 

select targets for tracking 

2) 

dark side of earth 

1) 

no tracking 

2) 

light side of earth 

1) 

no tracking 

2) 

darkside of earth 

1) 

select targets for tracking 

2) 

light side of earth 

1) 

select targets for tracking 

2) 

dark side of earth 

Targets 

ships and islands 

ships andislands 

ships and islands 

targets of opportunity 

calm and rough sea 

conditions 

calm and rough sea 

conditions 

land masses 

land masses 

Lengthof Experiment 

15 sec 

• 

0 

in 

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0 0

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in 

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4.0 min 

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A- 71 
NRETEAAPSPER,O,T 

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F201R5 

AW-42 

(1) ships in the recovery area 

(2) tracking network ships 

(3) island tracking stations 

(4) the sea under varying conditions 

(5) land masses (mountain ranges, rivers, cities, etc.) 

b. Targefs of opportunity - any visual targets over land or rater 

both on the dark and light side of the earth. 

2. Experimental Orbits 

Five orbits will be required for the N-10 experiments which are distributed as follows: 

a. Three for the detection of recovery and tracking ships and island 

tracking stations. 

b. One for the detection study of sea conditions. 

c. One for the detection of land targets. 

The astronauts will participate in each experiment. They will 

a. Energize the experiment equipment 

b. Maneuver the space capsule 

c. Select and track targets 

d. Record visual observations. 

Detailed instructions, more specific than those supplied, in previous briefing, A 

will be required. They will be conveyed by voice communication with the 

project monitor via the tracking network. 

3. Sequence of Events in Experiment 

The number assigned to each experiment is for identification in this 

proposal. Prior to launch, modified numbers will be assigned relating the 

experiments- to their occurrence in the flight plan. Table I presents characteristics of the experiments. 

A- 7 2 

wir 
NRO 

RELE 

iis- 

!ring, 

this 

le 

LracOR 

2015 

AW-42 

The following time diagram for the duration of an experiment illustrates a typical sequence of events. 

Side of 

dark 

light 

the earth 

20 ko 

ti 

do 65 ri 75 

t2 

 t3 t4 t5 

one orbital period 

t1 - a. turn on inertial platform providing a 30-minute warm-up period 

prior to start of the experiment 

t2 - a. turn on experiment equipment providing a 5-minute warm-up period 

b. maneuver space capsule into position required for the experiment 

and attain attitude stabilization or control 

t3 - a. final adjustment of TV system prior to start of the experiment 

t4 - a. start of the experiment 

t

5 - a. end of the experiment 

The time sequence plotted in the diagram will vary according to the location 

of the desired targets in the earth light and dark side cycle. The astronauts' 

participation time will be approximately 15 minutes for experiments 1, 2 and 

3 and 20 minutes for experiments 4 and 5. 

Table II lists the experiments giving astronaut participation, spacecraft maneuvers* equipment required and the function of the tracking network. 

4. Data 

A camera is used to photograph the output of the recording monitor. 

The photographic data rate and number of photographs to be taken are shown 

in Table III. 

A- 73 
RecoveryArea and 

TrackingNetwork 

Participation 

' 1) voice commands 

2) 

visual aids 

3) 

record attitude 

and rate data 

4) 

location of ships 

t - - 

S. 

. 

- 

••■ 

: 

Equipment 

Required 

1) 

inertial platform 

2) 

TVsystem, 

3) 

recordingcamera 

c c .. . 

8 

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1) 

visual comparisonby 

both astronauts 

2) 

recordobservations 

1) 

visual comparisons 

2) 

record observations 

3) track target 

1) visual. comparisons 

2)'recoid observations 

3) 

tracktarget 

4) 

after 1.5 sin. track 

targets of opportunity 

. 

1) track targets of 

opportunity 

Spacecraft 

Position 1) 

lookingdown 

2) 

attitude stabilized 

1) 

looking down 

2) 

attitude control 

= = f • " 

L 

• 

Experiment 

Number 

r.4 CSI rol 4 tri 

A- 7 
AW -142 

TABLE III 

Number of 

Experiment Photographic Data Bate Photos 

1 15 sec at 20 photos/see 300 

2 1.5 min at 1 photo/sec 90 

3a 1.5 min at 1 photo/sec 90 

3b 3.0 min at 1 photo/sec 180 

4a 4.0 min at 1 photo/sec 240 

4b 4.0 min at 1 photo/sec 240 

5a 4.0 min at 1 photo/sec 240 

5b 4.0 min at 1 photo/sec 240 

The reduction of the photographic data requires that for each 

experiment the following satellite information be recorded by the tracking 

network stations. 

a. Pitch, roll and yaw attitude 

b. Pitch, roll and yaw rates 

c. Linear velocity 

d. Altitude 

e. Special position 

f. Time. 

The analysis of photographs, tracking network data and the astronauts' visual 

observations during the experiment and in debriefing will be the basis for 

determining the success of the N-10 experiment. 

5• NASA Tracking Network Bele 

In addition to providing the data required for photographic correlation, NASA must provide information on the locations of the recovery area and 

tracking ships. The TV system camera has a maximum 55-mile diameter field of 

A- 75 
I 

iY 

APPROVED FOR 

LEASE 1 JULY 2015 

AW-42 

view at the surface of the earth. The ship targets will have to be position 

within this field to insure target acquisition. The ships will employ detection enhancement aids such as lights, smoke and dye markers. 

The tracking network will provide the communication link required for 

the performance of the experiment and will record on tape the astronauts' 

observations with the unaided eye and by the TV system. 

6. Astronauts' Role 

In each experiment, the spacecraft must be pointed vertically down 

and maintained in this attitude with the best precision possible. In experiments 2, 3, 4 and 5, the astronauts will track specified targets or targets 

of opportunity. 

Both astronauts must participate in the N-10 experiment to make possible comparisons between the unaided eye, the TV aided eye#and the photographic records. The astronaut viewing the scene unaided will attempt to 

become dark adapted over a specified period prior to the start of the experiment. Post-flight laboratory experiments can determine the degree of dark 

adaptation acquired by the astronaut for each experiment. 

The observers wil be required to voice record the time of target 

acquisition, relative headings, and duration of tracking. A grid pattern 

placed over the face of the presentation monitor will aid the astronaut in 

estimating tUese variables. 

7. Controls. 

It is intended that the operation of the experiment equipment be 

essentially automatic. The variables controlled automatically include the 

following: 

a. Dynamic light range 

b. Sensitivity 

ce Camera frame rate 

d. Camera record time. 

The astronaut will control the brightness level of the presentation monitor 

and select the TV camera field of view by means of a zoom lens. The adjustable 

field of view will aid in target acquisition and in target tracking. 

A- 76 

.4 

gra ,r-,:tagragerwr4V01.0111010- 
NRO AP 

RELEAS 

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15 

AW-42 

SYSTEM INFORMATION 

1, Major Components 

The major equipment components are the TV earns, the camera control 

unit, the presentation monitor, the recording monitor, the photographic 

camera, and the experiment control console. 

a. TV Camera 

The TV camera consists of a soon lens, a single stage image 

intensifier, and an image orthicon sensor. 

b. Camera Control Unit 

pos. The camera control unit provides the synchronizing circuits, video 

lobo- amplifiers, dynamic light range control circuits, and the camera power supplies. 

to 

xperi- c. Presentation Monitor 

ark II 

-ti d. Recording Monitor 

in 

The presentation monitor is a 5-inch diameter CRT and high voltage 

power supply. 

1 

e Th recording monitor is a 1-inch diameter CRT and high voltage 

power supply. 

e. Photographic Camera 

le The photographic camera is of special design for obtaining programmed sequential photographs. It is capable of recording time and exposure 

settings on the film. 

f. Experiment Control Console 

The experiment control console contains the video amplifier, 

11 

synchronizing circuits, and the experiment control circuits. 

2. System Design Characteristics 

r The system performance, electrical requirements, and physical configtable uration are based on commercially available low light level components. The 

final selection of experiment equipment will depend on investigations of the 

performance capabilities of developmental equipment and on some basic laboratory experiments. 

The possibility of detecting the presence of ships under low light 

A- 7 7 
APPROVED FOR 

ELEASE 1 JULY 2015 

AW-42 

conditions is the basis for the specification of system performance. The 

essential characteristics to be considered are 

a. Scene brightness level 

be Scene contrast 

c. System static resolution for low light conditions 

d. System dynamic resolution for low light conditions 

e. System dynamic light range control 

f. Photographic recording. 

The electrical requirements for the experiment equipment are as follows: 

a. Standby (warm-up time) 

5-minute warm-up period for filament of the image orthicon and 

monitor CRT's: 

1.5 as at 6 V 10 watts, a total of 25 minutes at 10 watts.. 

b. Average (operating) 

45 minutes at 330 watts. 

The proposed physical arrangement, weight, dimensions, and volume 

of the experiment equipment are shown in figure 1. These estimates are 

preliminary. 

A- 78 

4111111111111111111111PINIPMEMMErnmesw■ '1111111111111.11111NNIMOmene 
1/7 

No Scale Skid Well 

Section 

Item Component Dimensions Voluwe Weight 

(in) (in) (lbs) 

1. T.V. Camera .5 dia. x 28 550 30 

2. T.V. Camera 7 x 8 x 19 1064 25 

Control Unit 

3. Viewing Monitor 51/2x5V2x111/2 348 5 

4. Recording Monitor & 231 10 

Photo Camera Unit 

5. Monitor Electronics & 200 20 

Equipment Control Unit 

6. Experiment Control Panel 12 1 

2405 91 

A-79 

Fig. # . Schematic of Functional Equipment Location 

Ems. N-10 

Adapter 

Retrograde 

Section 

Adapter. 

Equipment 

Section 

a 

Section 

Cabin 
EASE 1 JULY 2015 

T.V. Camera 

Vision Cone 

Vision Earth Fi 

Cone Altitude of View 

8 (Deg) It (N.M.) D (Miles 

le 161 32 

87 17 

161 49 

87 26 15' 

Astronauts 

Vision Cone 20' 161 65 

87 35 

1 

I 

Surface of Earth 

D 

Figure . T.V. Camera's Earth Field of View 

A- 80 
park 

Side 

Earth 

Field 

ev tight 

de as ) Si 

Earth 

NRO A ED FOR 

RELE c LY 2015 

Typical Experiment Time Diagram-Sequence of Events 

Time Diagram 

20 40 

i 1 ,f 1 It1 

`\ , 1 . ti _/ t2 t341 ,

\ 

m4 

twi 

Time t5 

One Orbital Period (Min.) 

Time 

ti 

t2 

Sequence of Events 

Turn on Inertial Platform (Provide 30 min. warm-up period) 

1. Turn on Experiment Equipment (Switch #1) Provides 5 min. warm-up period 

a. Monitor Electronics and Equipment Control Unit - Standby 

b. T.V. Camera Control Unit - Standby 

c. T.V. Camera Filaments 

d. Viewing Monitor Filaments 

e. Recording Monitor Filaments 

2. Maneuver Space Capsule into position required for experiment and attain 

stabilization and control. 

1. Automatic switching on of all experiment equipment except RecordingPhoto Camera. 

2. Adjust Viewing Monitor brightness prior to start of experiment. 

Select desired experiment (Switch #2) 

Select Field of View (Switch #3) 

Start of experiment (Switch #4) - Recording Photo Camera Operation 

t7 End of experiment - Automatic Photo Camera stop 

a. Turn off Switch #1 

b. Turn off Inertial Platform 

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FOR 

LY 2015 

NAVAIRDEVCEN Johnsville, Pa. 

AW-423 

30 Dec 1963 

TELEMETRY REQUIREMENTS 

The following information should be telemetered to ground stations: 

1. Time marker indicating photo-camera start and stop times (photocamera). 

2. Iris setting (TV camera). 

3. Neutral density filter setting (TV camera). 

4. Ambient light level (measured by a separate photo-sensor) 

(camera control unit). 

5. The integrated video output of the camera and camera control 

unit. This will give rise to a D.C. level indicating the presence of or 

lack of video signal at the camera output and the camera control unit 

output. 

AGE TEST POINTS 

A. TV Camera 

1. video output (coax) 

B. TV Camera Control Unit 

1. I.O. vertical sweep current (shielded) 

2. I.O. horizontal sweep current 

3. vertical sweep signal to monitors 

4. horizontal sweep signal to monitors 11 

5. video output signal (video + blanking) (coax) 

C. Monitor Electronics and Equipment Control Unit 

1. video to viewing monitor 

2. video to recording monitor 

3. viewing CRT vertical sweep current 

1i. viewing CRT horizontal sweep current 

5. recording CRT vertical sweep current 

6. recording CRT horizontal sweep current 

(coax) 

(shielded) 

'I 

A-85 
PROVED FOR 

ASE 1 JULY 2015 

POWER, SIZE AND WEIGHT ESTIMATES 

NASA/DOD EXPERIMENT N-10 

Unit # Description (watts) (in.) (in.3) (lb. 

, 

1 TV Camera 23 5 Dia. x 28 550 

2 Camera Control Unit 77 7 x 8 x 19 1060 

3 Viewing Monitor 8 5 1/2 is 5 1/2 x 12 363 

4 Recording Monitor & 

Photographic Camera 31 MAC L/0 - 019934C 349 

5 Monitor Electronics & 

Equipment Control Unit 36 MAC L/0 - 0199333 300 

TOTAL 175 2622 83.0 

NOTES: 

1. These values are for a 3" Image Orthicon System. 

2. Weights of Units include electronics, internal mounting structures and 

boxes. 

3. Weights do not include external wiring or external mounting provisions. 

4. Cold plate weights are not included in the above weights. 

Power 

Dissipated Size Volume Wei 

33 

18. 

 13.5 

10.0 

A-86 
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NRDAPPROVED-FOR - RE. ., 

TV CAMERA COTPOL M IT - Un it :2 

1 

Sync. Vertical & Video Automatic Regulated DC 

• 

r.lenarator Horizontal Amplifier Light Power Supply ; 

Sweep Control and 

Generator FocusCurrent 

Redulator Fri.rwr. 

. 20-32VDC 

CO 

CO 

• 

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Power Dissipated (Watts) 77 

• 2 
8 

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A-89 

Structural Weight 

Total Unit 
- 
Generator 

Horizontal 

Video &Blanking to 

Viewing Monitor 

Video &Blanking to 

Recording Monitor 

8 

Distribution 

CJ 

Viewing Monitor 

Eoriz. Defl. Coils 

t3 .3 0 

0 

e0 

Recording Monitor 

forts. Defl. Coils 

Viewing Monitor 

Vert. Defl. Coils 

 Recording Monitor 

Vert. Defl. Coils 

Transistor 

Operatine' 

Potentials 

to 

t 6 

> 

CJ • en 

8 

= 0 

8 

11-4 

Power Dissipated (Wa

tts) 

0 o 0 

9 

A-91 
RO APPROVED FOR 

ELEASE 1 JULY 2015 

AWK 

17 Feb 1964 

TITLE Or EXPEsiMENT. infrared **pima 

TEST OBJECTIVE. The purpooe of this experimmst is to survey ocean and 

terrestrial features by infrared tachaisoss. 

it 

of the see surface reveal the structure of earn currents, presages of meanie-- 

"cad fronts," mod the press:ass of icebergs. Is the field of meteorology, 

cloud distributions con be mopped both day and si$it for use in weather 

predictions. Dynamics of cloud formation sae be studied becalms aesemslatioms 

of atmospheric water WPM associated with loosest and owsnescent rituals can 

be recorded by operating the set in a spectral raise eerrespendiag to new 

of the water absorption Dennis. Is the samocs of goaegy, thermal pictures 

recorded over land messes could provide informatioa as geologic structures 

by revealing their relative beatIng sad gelato' sates ever the diurnal cycle. 

The imminence of volcanic ereptiesupaght be isferred from eboarvatleas of 

"bet spots" on the serth's surface. In general, it appears that a wealth 

of information about the earth mad be learned by Walvis, it by its infra• 

red incsadesconce. Experience with airborne infrared marvimg devices has 

indicated that unexpected latersatisa is often obtained when objects are 

viewed in this different light. 

DESCRIPTION OF TIM WERIliOrT. The astroment would wisest the spacecraft 

to ems the selected areas of obeervatien. He would adjust centras for 

optima seal* carnations. With the equipment contemplated it would be 

possible to map as area appronimately 700 miles in width and resolve objects 

separated by about 1100 feet from an observation platform 200 miles slay. 

This means that features such as rivers, valleys, lairs, cities, mountains, 

coastliaes, mesas, ammo currents, weather treats, isobar's, and any other 

object whose ramperabsre differs fres its surreladdass by as appreciable 

portion of a degree ihcald become visible to the iafrared scanner. The 

form of these objects would became claw. Sy pesetas ewer the area at 

successive times be could observe asseasats of clouds, storms, *toss 

=MOMS, eta. 

031ICX OF THE TEST. Since targets observed with infrared radiation will 

bu enee with self-matted radiation, infrared mapping is particularly of 

interest OR the dark side of the earth. Data will be useful in determining 

the optimum combinations of infrared, electrreptical photographic, OF/ELTIT 

acronym radiometry, active radar and other seams for sea survaillamas. 

Experience with alrborms passive infrared napping sets has demonstrated 

their application to aleamegrephy, meteorology sad geology. Thermal pictures 

Dgpsto_, r,,.<1. :1 12 .3 I, 

Not “„1,,13,02, 31'3 I .. A-92 
N 

RE LY 2015 

The astremmut geoid compere Lateresties trims rapid processed sap 

with viand Lateceetioa. Els camemataineld be recorded ter Later comprise' 

nes with recorded data. It is expected that reseedingi et the same scene takes 

sada at sencessive intervals would ahem progress if sterns, claude. sea currents. 

iceberas. its. Appsimately four hours et latecstime talon ever awe meek 

duration would be escessery. Services et the solemnest fee this period are 

reeemmemied. 

d. Wows if Diserisent 

FT66 1167 lii8 FT69 TOTAL 

Category b 

S. 

FAS 

(1) itmlaserbis 

Developmest 100K 600K LOOK SOK SOK 900K 

(2) Isstallaties 100K LOOK 600K SOK SOK 900K 

(3) Grand Support SOK SOK 200e 2001 _SOK SSOK 

TVAL CM 2350K 

to I. battik! 

Bordner* reedy ter test January 1967. 

r 

gl1KTICIDIT)317 OMMOONFAMOICY. U. S. Nivel Air Development Coaxer. 

4 AFIDITISSW. REOUISBNI2F/S. Security

Da 

-Boleipmeat •compuTTAL 

ta - •COMFIDENTIAL 

Additional inferestioswill be turaished wises experiment is mere thoroughly 

plammod. 

a. cOefillIMMUNL44 Test Ikees 

(1) Scanner 40 pounds 

(2) Rapid Processor Assieut Devise 40 paned' 

(3) Riccardi% *miter 20 pounds 

b. TestSuseert gealammat gossiped 

L11 Vet Won st present. 

sg C. Dautamtimmt 

art 

A - 9 3 
U. S. NAVAL AIR DEVELOPMENT CENTER 

ANTI-SUBMARINE WARFARE LABORATORY 

JOHNSVILLE, PENNSYLVANIA 

AW-411 

13 Dec 1963 

CONFIDENTIAL 

TECHNICAL MEMORANDUM ADC-AW-411:PMK 

Subj: WEPTASK RT 7045001/2021/F019-05-02, Passive infrared mapping set for 

use in Gemini satellite; feasibility study of 

Ref: (a) General Electric Co. Radiation Calculator 

(b) Rand Corp. Conf Report "Fundamentals of Infrared for Military 

Applications (U)" of 31 Mar 1956 

(c) General Electric Co. Advanced Electronics Center Report R57ELC15, 

"A Procedure for Calculation of Atmospheric Transmission of 

Infrared," of 1 May 1957 

(d) NASA Technical Note NASA TN D-1850, "The Infrared Horizon of the 

' Planet Earth," of Sep 1963 

Encl: (1) NAVAIRDEVCEN Conf Conceptual Drawing of Gemini Infrared Mapping 

Set of 12 Oct 1963 

I. I#TRODUCTION 

Considerable interest exists in the possibility of placing a passive, h 

resolution, infrared mapping set in a Gemini satellite scheduled for a two-dayll 

orbital flight during December 1965. It has been proposed that such a device 

would yield information of value to the Navy on the locations and movements ..,. 

of ships and in the broad scientific fields of oceanography and. meteorology. 

It has also been proposed that the pictures generated by an infrared mapping 

set would provide visual aid to the. astronauts both day and night. The 

purpose of this memorandum is to consider the feasibility of including an 

infrared mapping set in the complement of Gemini instruments. The items to 

be discussed are (1) areas of application, (2) system design considerations, 

(3) system design parameters, (4) results to be expected, (5) conclusions, 

and (6) recommendations. 

II. AREAS OF APPLICATION 

The type of infrared mapninz set under consideration would be sensitive 

to radiation in the portion of the electromagnetic spectrum. 

Since all bodies radiate infrared energy at rates proportional to the fourth 

power of their temperatures and since the wavelength at which maximum radiation from objects on the surface of the earth is emitted occurs within this 

band, an infrared mapping set can provide thermal pictures of the surface of 

the earth at night. Since solar radiation incident upon the earth also 

Downgraded at 3 year intervals. 

Declassified after 12 years. 

A-94 catzr TnEYTIAL 
NR D FOR 

RE JULY 2015 

-41 ' 

atirIRENTTAL 

Subj: WEPTASK RT 7045001/2021/F019-05-02, Passive infrared mapping set for 

use in Gemini satellite; feasibility study of 

15, 

he 

3 

1 

high 

-day 

_vice t, 

lts 

31.14 

1 

to 

3ns, 

3, 

ive 

um. 

urth 

diahis 

e of i 

includes radiation in the band, those portions of the earth 

viewed during hours of daylight will be seen through the joint agency of 

reflected solar radiation and self-emitted radiation. 

Experience with airborne passive infrared mapping sets has demonstrated 

their application to oceanography, meteorology, and geology. Thermal pictures 

of the sea surface reveal the structure of ocean currents, presence of oceanic 

"cold fronts," and the presence of icebergs. In the field of meteorology, 

cloud distributions can be mapped both day and night for use in weather predictions. Dynamics of.cloud formation can be studied because accumulations 

of atmospheric water vapor associated with nascent and evanescent clouds can 

be recorded by operating the set in a spectral range corresponding to one of 

the water vapor absorption bands. In the science of geology, thermal pictures 

recorded aver land masses could provide information on geologic structures by 

revealing their relative heating and cooling rates over the diurnal cycle. 

The imminence of volcanic eruptions might be inferred from observations of 

"hot spots" an the earth's surface. In general, it appears that a wealth of 

information about the earth could be learned by viewing it by its infrared 

incandescence. Experience with airborne infrared mapping devices has indicated that unexpected information is often obtained when objects are viewed 

in this different light. 

III. SYSTEM DESIGN CONSIDERATIONS 

A. In the design of the infrared mapping set the following will be 

assumed: 

Altitude of satellite (h) 150 nautical miles 

Radius of earth (RE) 

Angle between equatorial plane of 

earth and the satellite's orbital 

plane 

Tangential speed of earth at 

equator (vE) 

Circular orbit for satellite of 

radius (R = RE + h) 

3.50 x 103 nautical miles 

28.5o 

903 knots 

3.65 x 103 nautical miles 

A- 9 5 CONTIDENTIAL 
SE 1 JULY 2015 

AO-411 

CONFIDENTIAL 

Subj: WEPTASK RT 7045001/2021/F019-05-02, Passive infrared mapping set for 

use in Gemini satellite; feasibility study of 

B. Orbital period of satellite 

T = 3.16 x 10-1016t7 (for T in seconds and R in cm) 

• 5.50 x 103 sec. 

= 91.8 min 

= 1.53 hr. 

C. Circumference of orbit 

C = 22-x 3.65 x 103 = 22.9 x 103 nautical miles. 

D. Orbital speed 

vs= C/T • 22.9 x 103/1.53 • 15.0 x 103 knots. 

E. Speed of satellite relative to the earth at the equator (v) 

v =Ivo- 17E1 

=vscos 28.5o = 15.0 x 0.879 x 10 

= 13.2 x 103 knots 

mo Vs sin 28.5° = 15.0 x 0.477 x 

7.16 x 103 knots 

v

Ex vE • 903 knots 

vEy 0 

V I. --\/(13.2 X 103 - 903)2 + (7.16 x 103) 14.2 x 103 knots. 

2 

A-96 CONFIDENTIAL„; 
7 X 10 

D FOR 

SE 1 JULY 2015 

AW -411 

Subj: WEPTASK RT 7045001/2021/F019-05-02, Passive infrared mapping set for 

use in Gemini satellite; feasibility study of 

F. Angular velocity of a target point on the surface of the earth 

relative to the satellite 

v/h n 14.2 x 103 n mi/hr 

1.50 x 102 n mi x 3.6 x 103 sec/hr 

■ 2.63 x 10

-2 

rad/sec 

m 26.3 milliradians/sec. 

G. It is desirable that the mapping set not scan from horizon-to-horizon 

insofar as the abrupt difference in the level of radiation from the earth and 

from the void beyond would exceed the dyfiamic range of the sensitive system 

under consideration. In addition, the information gained from viewing targets 

near the horizon would have negligible value because of loss of system spatial 

resolution associated with viewing targets at a glancing angle. A total scan 

angle of 120° is considered optimum; this will provide a sweep width of 550 

nautical miles on the surface of the earth. 

IV. SYSTEM DESIGN PARAMETERS 

Enclosure (1) illustrates the design concept of the type of infrared 

mapping set under consideration. The set consists of two units: a scanner 

and a printer. Its design is an extension of that employed successfully in 

several generations of passive airborne infrared mapping sets used by the 

NAVAIRDEVCEN; there are no radical departures from present designs and all 

of the requirements of the system are within the present state of the art. 

Since system noise equivalent temperature difference (a measure of system 

sensitivity) improves with increased detector aperture but system spatial 

resolution deteriorates with increased detector aperture, it-is apparent that 

the choice of aperture diameter is a matter of compromise. In the event that 

A- 9 7 r ONFIDENYIAL 
ASE 1 JULY 2015 

AW -411 • 

C OtirIDENTIOI 

Subj: WEPTASK RT 7045001/2021/F019-05-02, Passive infrared mapping set Zor 

use in Gemini satellite; feasibility study of 

it is decided at some later date to shift the compromise point selected to 

one that would yield either higher sensitivity or higher resolution, this 

can be accomplished readily by changing the detector aperture diameter. 

The detector is maintained at a proper operating temperature of approximately 27°K by thermal contact with a reservoir of liquid neon stored in an 

altitude-independent, attitude-independent, metal dewar container of about 

0.7-liter capacity. The dewar will be equipped with blow-off valves, that 

maintain a constant absolute pressure of slightly more than one atmosphere 

over the liquid neon. The design of these valves must be such that only 

gaseous neon may pass through them. Provision must also be made in.;the dewat 

for maintaining thermal. contact between the liquid neon and the detector in - 

a gravity-free environment. The innermost wall of the dewar will be con- -: 

structed of a good thermal conductor such as copper. In addition, a bladder ,V 

made of material that will remain flexible at low temperature will be incorporated 

gl 

in the dewar; this bladder, which will be attached to the end of .2,. 

the dower remote from the detector, will be inflated by the boiled-off neon 4. 

j gas and will force the remaining liquid neon to remain in contact with the .. 

base of the detector element. The capacity of the dewar will be adequate ',It for three to four days of operation from the time of filling it with liquid 

neon. .i 

.15 

The scanning mirror will rotate at the rate of 50 revolutions per, second 

and_ will cause the projected image of the detector aperture to scan.repeatedlyi 

across the terrain below with a locus consisting of a series of parallel lines: 

perpendicular to the direction of travel of the spacecraft. Scanning in the 

forward direction is provided by the forward motion of the vehicle. Radiation 

is accepted- only during those portions of the scan cycle that the detector is 

viewing the terrain within 460° of the vertical. The number of one-milliradian 

.resolution elements per scan will be 

120 degrees/scan x 17.45 resolution elements/degree 

= 2094 resolution elements/scan. 

For complete coverage of the terrain to be Scanned, the minimum rate of scan 

must be 

v/h (rad/sec) . 26.3 x 10-3 rad/sec = 26.3 scans/second. 

AG (rad) 1 x 10-3 rad 

Since photoconductive infrared detectors generate electrical noise whose amplitude is greatest at low audio frequencies, it is desirable to scan at a rate 

A- 9 8 
Jar 

1 

1 

ad 

Idly; z: 

inesf 

. ae 

tian 

is tr 

sdian 

mpli 

to 

JULY 2015 

AW -411 

SubJ: WEPTASK RT 7045001/2021/F019-05-02, Passive infrared mapping set for 

use in Gemini satellite; feasibility study of 

greater than 26.3 scans/second so that the bulk of the signal information 

will occur at high audio frequencies. A rate of 50 scans/second appears 

reasonable. Accordingly, the duration of the-active portion of each scan 

will be 

1200 1 1 A sec ■ second. 

360° 50 150 

The required electrical bandwidth Lf of the system will be 

= 1/2 x (number of resolution elements per second) 

2094 resolution elements/scan 

= 1/2 x 1/150 sec/scan ■ 157 x 103 cycles/second. 

The effective bandwidth Lfeff for computing system noise will be approximately.one-half the electrical bandwidth - Af because of noise averaging in 

the recording medium due to partial overlap on successive scans. 

The electrical signal generated in the detector is amplified and applied 

to the intensity control grid of a high resolution cathode ray tube. The 

electron beam of the cathode ray tube is line-scanned in synchronism with the 

scanning mirror and the resulting intensity modulated line is focused on a 

strip of continuously moving. 35 millimeter, photographic film which advances at 

a rate of 2.57 feet/hour. The film, when developed, will yield a continuoustone picture of the terrain under surveillance. The resolution characteristics of 

the type of cathode ray tube and of the size:of-the film. selected are consistent 

with the one-milliradian resolution of the scanner. The 150-foot supply of 

film is adequate for more than two-days' continuous recording. 

V. RESULTS TO BE EXPECTED 

A change in the radiant power AP (mitt) impinging on a photoconductive 

infrared detector of sensitive area a (cm`) produces an electrical output 

having a signal-to-noise ratio S/N (dimensionless) given by 

-11 

S/N itv(cm cps /watt) x AP (watt) x a

4 

 (cm ) x (Afeff) (cps ) (Eq 1) 

* where Da is the average detectivity (a figure of merit) of the detector material over the spectral range of interest and Afeff is the effective 

11 

A- 9 9 
O APPROVED FOR 

EASE 1 JULY 2015 

AW -411 

Subj: WEPTASK RT 7045001/2C21/F019-05-n, Passive infrared mapping set for 

use in Gemini satellite; feasibility study of 

electrical bandwidth over which signal and noise are being measured. Applica 

tion of this equation involves the following considerations: (1) the emissi 

of radiant power from the target, (2) the transmission of this power through 

the atmosphere, (3) the interception of a small fraction of this radiant 

power by a satellite-borne optical system, and (4) the conversion of this 

radiant power to an electrical signal by the detector and the subsequent 

amplification and recording of the signal. Each of these considerations will 

be discussed in turn. In the calculations that follow it is assumed that the;et 

targets considered behave as blackbody radiators and that the scanner optical 

system is 100% efficient. 

The change in spectral radiant emittance of a blackbody accompanying a 

change in its temperature can be determined by differentiating the Planck 

radiation equation with respect to temperature. A graph of the resulting 

function was obtained by use of reference (a) and is plotted in figure 1. 

A reference temperature of 15°C was chosen. This graph shows that, in the 

spectral range of interest, a target temperature change of le produces an 

average change in the power radiated per square centimeter of approximately 

43 microwatts per micron interval of wavelength. 

For clear sky conditions, the principal atmospheric attenuators of infra- "Ir" 

red radiation are water vapor, carbon dioxide and ozone. Reference (b) gives 

average values for the concentration of atmospheric water vapor as a function 

of altitude over eastern United States. These were plotted in figure 2. The 

area under-the curve of figure 2 was determined and used to compute the total 

amount of precipitable water vapor in a vertical column through the atmosphere. The number obtained (36.3 mm of water) was increased by about 40% to 

allow for the higher values of absolute humidity to be expected in the tropics 

and a round number of 50 mm of precipitable water. vapor was used in the transmission calculations. Figure 3 is a graph of the percent transmission of 

infrared radiation in the wavelength range of interest through 50 an of precipitable water vapor. Reference (c) was used in making the determination. 

Figure 4 is a graph of the percent transmission of infrared radiation, in 

the wavelength range of interest through an equivalent sea level path of(5 

kilometers of carbon dioxide. These transmission values were determined from 

data given in reference (c). The equivalence of the vertical path through 

the entire atmosphere to a sea level path of 5-kilometers was concluded from 

both references (b) and (c). 

The concentration of ozone in the atmosphere is a function of altitude, 

latitude, time of the year, and weather conditions (references (c) and (d)). 

Typically, the ozone layer exhibits a maximum concentration at an altitude 

in the range of 20 to 30 kilometers. The model atmosphere graph of reference 

A-100 
NR OVED FOR 

RE JULY 2015 

cONrIDENTIAT 

Subj: WEPTASK RT 7045001/2021/F019-05-02, Passive infrared mapping set for 

use in Gemini satellite; feasibility study of 

AW -411 

X4. (c) giving ozone concentration as a function of altitude was integrated to 

. ion determine a representative quantity of 2.44 mai of ozone (at standard tempera- 

.;11 tura and pressure) in a vertical column through the atmosphere. The percent 

• transmission of infrared radiation through 2.44 mm of ozone was then determined by further use of reference (c) and was plotted as a function of wavelength in figure 5. 

Lil 

:he The net transmission of infrared radiation in a vertical path through the 

atmosphere as a function of wavelength was obtained by a point-by-point multiplication of the graphs given in figures 3, 4 and 5 and is plotted in figure 6. 

An average transmission over. the spectral range of 7.7 to'13.5 microns of 397 • 

was obtained from this curve. 

The net change in spectral radiant emittance of a blackbody per Kelvin 

degree change in temperature transmitted vertically through the atmosphere 

was obtained by a point-by-point multiplication of the curves of figures 1 

and.6 and is plotted in figure 7. The integral of the function plotted in 

figure 7 over the wavelength range of 7.7 to 13.6 microns is represented by 

the symbol L in the following discussion and has the value 95.8 x 

cmz 

The incremental change in radiant power AP (watt) incident on the infrared detector element for an incremental change in extended area target 

.temperature- LT can be derived in terms of quantities defined in figure 8. 

The target area from which radiation is accepted 

A mw/12 2 - (d/2)2 h2 • 

F1 gz 

The solid angle subtended at the target by the collecting optics 

it (D/2) 

h

2 

The fraction of the power radiated normal to the target surface per steradian 

of solid angle c-2 is 1/77 Accordingly 

LP - 1/T L A, C AT L Td2 h2 7rD2 AT D2 d2 L A's A• 

. 11 4 F2 4 h2 16 F2 

(Eq 2) 

A-101 CONrIDENIIAL 

ait 

raYta 

ion 

the 

tal 

to 

tics ", 

ansein 

Tool 

A 
OVED FOR 

ASE 1 JULY 2015 

AW -411 

CONFIDENTIAL 

Subj: WEPTASK RT 7045001/2021/F019-05-02, Passive infrared mapping set for 

use in .Gemini satellite; feasibility study of 

The effective bandwidth Afeff of the system for noise considerations 

can be expressed in terms of the total time the radiation from a target is 

intercepted. For purposes of computation, consider the case in which the 

projected image of the detector on the target plane is congruent with the 

target. Then the total dwell time per picture element (including overlap on 

successive scans) is 

0) h

2 . cob 

177177 2 IT v 

where v is the speed of the spacecraft. The effective bandwidth 

Af = 1 2Ly. 2 = 4 F2 v. ef. 

' 27 • 00h Ird2 h d2 

If equations 2 and 3 are substituted into equation 1, the following 

is obtained: 

--11 2 2 *LNI S/N=i/DdD 8V 

16 F3 (v/h)31 

If SIN is set equal to unity then LT equals the noise-equivalent temperatUre difference A% and 

L\ TN 16 F3 (v/h) 1 

7r1/ D2 d2 Div L 

For the system proposed: 

F = 15.24 cm Dav 

= 8 x 109 cm cpsI/watt ✓ 

D = 8.25 cm L = 95.8 x 10-6 watt/cm2 K° 

d = 1.524 x 10-2 cm v/h = 2.63 x 10-2 rad/sec. 

Therefore L\TN 0.43K°. This means that a target who size is equal to 

A-102 CONFIDENTIAL 

• 
NROAPPRO 

RELEASE 1 J 

al 

set for 

AW -411 

subj: WEPTASR RT 7045001/2021/F019-05-02, Passive infrared mapping set for 

use in Gemini satellite; feasibility study of 

ations 

;et is 

the 

the 

trlap on 

ig 

pera1.1 to 

that of one resolution element (that is, the projected image of the detector) 

will yield a signal equal to the noise level of the system provided its temperature differs from that of the surround by 0.43 K°. 

The image of the detector element projected on the earth will have, in 

General, the shape of an ellipse whose major and minor axes will vary as 

functions of the angle of incidence. For vertical incidence the ellipse will 

reduce to a circle of 910-foot diameter; for an angle of incidence of 60° with 

respect to the vertical its approximate major and minor axes will be 3640 feet 

and 1820 feet. Since the minimum signal-to-noise ratio required for reliable 

detection of single resolution element targets is of the order of two to three, 

targets in the above size ranges will be detected at night if they exhibit 

temperature contrasts of the order of one degree or more. 

In general, but within limits, the minimum signal-to-noise ratio required 

for reliable target detection with a mapping set varies inversely as the 

square root of the area of the target, provided the target is larger than the 

resolution element. If the target is smaller than the resolution element, 

the magnitude of the signal is proportional to the ratio of the area of the 

target to the area of the resolution element. 

One can calculate the minimum temperature contrast between target and background required for reliable detection at night as a function of target size. 

Such a set of values has been computed for the proposed infrared surveillance 

set and has been plotted as a graph in figure 9, which essentially summarizes 

the foregoing calculations. 

In daytime use the set would perform largely by reflected solar radiation 

and the pictures obtained would appear such like those taken with conventional 

cameras. If a target does not behave as a blackbody radiator, that is, if it 

is reflective, its apparent temperature will be some intermediate value between 

its true temperature and the effective temperature of the sky it reflects. 

In this manner, highly reflective objects at the same temperature as their 

non-reflective surroundings may appear to be more than 1000 cooler than 

their surroundings and thereby yield intense signals. 

CONCLUSIONS 

From figure•9 and from available information obtained with airborne infrared radiometers and mapping sets, it is concluded that meaningful information 

in the areas of application (oceanography, meteorology, and geology) discussed 

in part II could be obtained by orbiting a passive infrared mapping device of 

high sensitivity and high resolution, particularly if the device could be 

operated continuously over the duration of many orbits such that many areas 

VI. 

A-103 
PROVED FOR 

ASE 1 JULY 2015 

AW -411. 

C 0NrIDENTIAL 

Subj: WEPTASR RT 7045001/2021/F019-05-02, Passive infrared mapping set f 

use in Gemini satellite; feasibility study of 

of the earth might be imaged at various times during the diurnal cycle. 

Since the proper objects of geology, oceanography, and meteorology (i. 

land, sea, and air) are the environments in which military operations take 

place, it is likely that information of indirect military value would flow 

from conducting this experiment. Cities would be recognizable from their 

street grid patterns. Paved runways of large airfields would also be rec 

nizable. The sites of near-surface nuclear explosions and of missile law 

ings may be detectable and identifiable for short periods of time after the 

events. Information on the clandestine nighttime establishment of large 

military bases and airfields may be obtainable with the orbiting infrared It 

mapping set. Large ships such as aircraft carriers would yield detectable 

signals provided their decks differ in temperature from the water by at 

least four to five degrees; however, these signals would appear on the 

pictures as point targets which would not be identifiable. Small ships 

and wakes would not be detectable. 

The relevance of this experiment to manned space flight would be limited. 

The infrared mapping set would probably not provide the earth-orbiting 

astronaut with information of value in his mission that he would not already 

possess with greater precision (such as his geographical location). Con- 40 

versely, it is not the type.of experiment that can be done only in manned 

space flight (such as human biological and psychological experiments). 

However, since it is desired ultimately to land nen on the moon and on 

other planets, it may be desirable to have thermal pictures of the earth 

for comparison with thermal pictures of these other bodies before a manned 

extra-terrestrial landing is attempted. 

It is concluded, therefore, that an orbiting passive infrared mapping - I 

set (1) would be of keen scientific interest in several fields providing 

it could be operated for extendedperiods, (2) would have indirect military 

value, and (3) would have limited relevance to manned space flight. 

VI. RECOMMENDATIONS 

It is recommended that consideration be given to placing a passive infrared mapping set in a gravity-gradient-stabilized, unmanned, earth-orbiting 

satellite for scientific exploratory purposes. The device recommended would 

have a useful life of the order of one month and it would telemeter its vide 

data to earth receiving stations. It is recommended that such work be done 

on a time scale that would permit an orderly approach to the objectives 

sought and well-considered means for circumventing the many problems anticipated so that an acceptable probability of successful operation would be 

attained. 

A - 1 0 4 COPIFIJ ENTir. 
NRO APPRO 

RELEASE 1 J 

AW -411 

u ONFIDENTIAL 

et for 

Subj: WEPTASK RT 7045001/2021/F019-05-02, Passive infrared mapping set for 

use in Gemini satellite; feasibility study of 

e. 

It is not recommended . that a passive infrared mapping set be included 

in the complement of Gemini instrumentation. 

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• 
NRO APPROVED 

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Figure 8. Definitions of Terms Used in Optical System Calculations 

A-113 

tO ;+-1,N.4.0101* 
RO APPROVED FOR 

RELEASE 1 JULY 2015 

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A-114 
NRO AP 

RELEAS 

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A-115 CONFIDENTLA L 

-'111arfr!" • 
•1:74 

APPROVED FOR 

ASE 1 JULY 2015 

9 

Title of Experiment Electronic Surveillance of Ocean Targets for 

Ocean Surveillance 

I. Test Objective 

This experiment is expected to establish the feasibility of performing 

a portion of the ocean surveillance mission by performing identification 

and position determination by intercept of electronic emissions from 

ocean shipping. 

II. Importance of the Test 

This test is required to provide complete coverage of the useable 

frequency spectrum of ocean vehicle emissions for the purpose of ocean 

surveillance. Only from an orbiting platform can adequate coverage of 

the oceans be obtained. In-as-much as elint alone is a necessary but not 

sufficient ocean surveillance medium, it requires integration and assimulation of data with all other sources (optics, radar, infra-red scaners) 

to provide a positive degree of intelligence. The output of the multisensor array necessary for effective ocean surveillance can be best 

obtained and managed by a human performing a selection, sequencing, 

rejecting, and analysis function. Provision of this additional source 

of real-time data to the astronaut attempting to manage the variety of 

tasks required for ocean surveillance will, without doubt, contribute to 

the assessment of man's ability and utility in space. 

III. Description of the Experiment 

This test involves the intercept of radio frequency emissions from 

ocean vehicles for the purpose of identification and location of shipping 

as a part of the ocean surveillance mission. It is anticipated that 

provision of such data, properly identified and displayed, to the astronaut, 

will greatly enhance the demonstration of his capability to perform an 

effective ocean surveillance experiment from space. Problem areas are 

expected to be encountered in rapid positive identification of intercept, 

suitable display devices and adequacy of intercept range. 

a. Configuration of test Items 

v 

This test can'be,implemented by zroviaion of a suitable1emm4- 

direction -troad-band antenna array wie9r;'S, and X band capability 

feeding computation and display equipments. Antenna systems to be located 

on the MOL exterior with computation equipment located as convenient within 

the MOL in pressurized or non-pressurized spaces and display equipment 

located in the ocean surveillance "information center". Further detail 

provided in attachment A. 

Excluded from automatic 

downgrading and declassification. A-116 
NRO APPR 

RELEASE 

ing 

n 

SECRET 

b. Test-Support Equipment Required 

(1) Routine test and maintenance equipment, spare parts, signal 

g

enerators, auxiliary power supplies and related equipment to support 

this test will be required in the spacecraft. 

(2) Necessary ground test equipment exclusive of that above will 

include test radar, elint simulation equipment, antenna calibration and 

alignment devices and associated equipments. Additional detail will be 

provided in Attachment B. 

c. Test Procedure 

This test will be accomplished as part of the general ocean 

surveillance test and, as such, will utilize pre-arranged target-ship 

formations stationed within knows range of the MOL orbital path. Ships 

within the test patterns will be configured with suitable radiators to 

serve as characteristic elingtaikits and the ability of the astronaut 

to identify the emitter and effect correlation with other data will be 

directly assessable. The astronaut will utilize this experiment as 

another data source and his ability to identify the signal, confirm 

location and effect correlation with other data sources will provide 

measurement of the man's contribution. A precise definition of testing 

sequence is unknown at this time. However, it is anticipated that the 

elint experiment would operate automatically and would remain active 

continuously during each test period. 

d. CateRory of Experiment 

Category B. This experiment will contribute directly to the MOL 

objectives, however, it is not expected to have appreciable effect on the 

laboratory design. 

e. Cost 

Prior FY65 FY66 FY67 FY68 FY69 TOTAL 

(1) Engineering & 100 500 1,750 1,500 800 4,650 

Development 

(2) Installation 350 1,450 1,750 3,550 

(3) Ground Support 300 350 400 1,050 

TOTAL 9,250 

f. Schedule 

(1) Hardware and software available for test beginning in FY 67. 

(2) Hardware and Software flight readiness date FY 68. 

tut, 

d 

in 

A-117 
APPROVED FOR 

LEASE 1 JULY 2015 

1V. Participating Government Agencies 

Sponsor: Department of the Navy, Bureau of Naval Weapons 

Test Equipment Acquisition: Naval Research Laboratory 

V. Additional Requirements 

a. Special Security 

Normal security procedures associated with intercept and analysis 

of uncooperative RF data. 

b. Manning Description Summary 

See Attachment E. 

c. Logistics 

This experiment can be supported from logistics point of view 

within available Department of the Navy supply system. No special logistics 

problems are anticipated. 

d. Facilities 

This experiment will require special simulation facilities as part 

of the integrated ocean surveillance mission experiment. Specific facilities 

for experiment definition and astronaut training will be required and 

provided by the experiment development program. 

e. Simulation and Training 

(1) Astronaut: To perform this portion of the ocean surveillance 

experiment the Astronaut must be a trained Elintpoiihii'ver and must have 

technician capability for equipment maintenance. Simulation testing will 

be included as a portion of the integrated ocean surveillance experiment 

simulation and training program. Navy laboratories and training facilities 

include necessary capabilities. 

(2) Ground Personnel: Ground personnel involved in simulation and 

training will be needed to provide necessary support in areas of physiological monitoring and planning, Elint instructors, training aids specialists, 

radar and electronic technicians, and project engineering and management. 

Many of these personnel will fulfill similar roles in the other experiments 

making up the integrated ocean surveillance experiment. 

(3) Equipment: Equipment required for simulation and training 

will include RF generation equipment, radar simulators, signal displays, 

communication link, environmental control, physiological testing and 

measuring equipments, etc. With few exceptions, all necessary equipment in 

this category will be available in Navy laboratories. 

A-118 
NROAPPR OR 

RELEASE 015 

SECRET 

VI. General 

a. Communications and Data Handling Equipment: Attachment F. 

b. Development Characteristics: See attachment G. 

ics 

ties 

S 

:S, 

:s 

n 

A-119 
O APPROVED FOR 

EASE 1 JULY 2015 

ATTAtTliMart. A 

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9. Vaulp,',1 :0a MI MS A c 

A-120 
NRO APP OR 

RELEAS 015 

10. SHOCK IalITS So e 11F 

11. Ii LARDS (fire, explosion, electrical, toxics, other) Ro t,k E 

eir.%prvlev,-t hay, 

12• ATORE LDLITAT/ONS E 1. A ray\ p 16' - vrt o (e' a -4: 42 s 

13. TYPE AND RANGE OF MEASUREMENT (definitions 

measured while teat is under way). 

14. SPECIAL ENV/ROINIENTAL RE.WIREI 

15. oRnaiTATION AND POSITION ACCURACY REVIREMENTS: 

Station: "I" ■ .0 -09pr..0 eat axis 

Equipment t To Mot. To terabAce. 

16. EsiUIPIENT OPERATING CYCLE 

Frequency Vikst iv't\tAtv. ee pQ r G s iwt 

Time Duration ; Appreix tvria.1e'll 2.S 1•01%ilt‘te.s c. 

17. E.MtvIENT I1 LOCATION REaTIREMENTS tic.* e.r\i l e a I n Q r n cz i( @ ",Z 

'0%setcx.‘ tor sok- rociu.A re ci IVI ececk, la.‘v elitokle 4, es< pet I k r i". 

18. SPECIAL ECUNIIESS EEXISEMENTS(/',it,:ig? 

of 

:4e-6:04tK:r d 1Z CIPCil et; 1Q19■ 41 

Antennae retestop%v. 54146e, CP( HF-d 14 F) S‘o-iti, WI 0••• vi.k4 ra dr %.„ s ...bset* ‘vItecro.pt +.(4DP 

Bracketry "NS re'i net 

19. PRESSURE VESSE4S - fluids, gasses, etc. Rey, e. 

20. ELECTRO MAGNETIC INTW.FERENCe 'spurious generaticu, special stlel.r.Ling rea, et: 

trltAciaxci The h ,•• 

21. MAILITMANCE RE.413.1' :J AVAINIS 

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SPA 

of narterwtom to bp 

Apertures 8 r- \ 

Booms 

Windows ; t.toy,e 

r N P e6ii- cif e A pe h r 6,,(6: cws 

A-121 
APPROVED FOR 

ASE 1 JULY 2015 

SECRET 

ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape - As Required 

b. Film - As Required 

c. Other - Unknown 

2. HANDLING 

Component equipment comprising this experiment will be compatible 

with manhandling and will require no special equipment. 

3. PACKAGING - To be determined 

4. CALIBRATION 

Pre-launch calibration of antenna alignment and equipment capability 

will be required. Possible post-launch calibration may be required to be 

determined. 

5. JIGS AND FIXTURES - As Required 

6. NUMBER OF LEADS FROM OUTSIDE TO INSIDE STATION 

Not known at this time. However, some quantity of antennae on the 

spacecraft exterior will require electrical connection with equipment 

within the spacecraft. 

7. SENSORS - None 

8. TRAINERS/SIMULATORS - As required 

9. INSTRUMENTATION - As required 

10. RELATED SUPPORT EQUIPMENT 

a. Targets - To be arranged within operating constraints of the 

development test activities of the fleet units. 

b. Ground Stations - Indeterminate at this time. To be accomodated 

within existing DOD ground station networks where practical. 

c. Handling Equipment - None 

A-122 SECRET 

s. 
11. AGE - 

Routine electronics ground support and evaluation equipment will 

be required and available within the Navy system. 

12. ENVIRONMENTAL TEST EQUIPMENT - None 

13. FACILITIES 

Available within the Navy laboratory system. 

e 

A-123 --5€.6-Pe.E.T.— 

NRO APP OR 

RELEASE a 2015 
PROVED FOR 

SE 1 JULY 2015 

ATTACHMENT C 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired) 

a. Altitude: 100-200 nautical miles 

b. Inclination: For purposes necessary to MOL requirements, inclinatio 

of orbit is not critical. However, an operational 

ocean surveillance capability derived from MOL type 

experiments will require near polar inclination. 

c. Epoch: Coincident with MOL launch. 

d. Elliplicity: Near Circular 

2. PLANE CHANGE: Not required 

3. ALTITUDE CHANGE: Not required 

4. TIME ON ORBIT: Thirty days 

5. TEST DURATION: Tests will be a function of time spent over ocean areas 

and in particular over pre-arranged test target complexes.1 

6. TOTAL NUMBER OF TESTS: Unknown at this time. Part of training and 

simulation program may be performed in an airborne 

laboratory which will permit better definition of 

this item. 

7. TEST FREQUENCY: To be determined as above. 

8. INTERVAL BETWEEN TESTS: As required by Astronaut duty cycle and 

experiment requirements. To be determined. 

9. CREW TASK LOADS: To be determined 

10. CREW TASK FREQUENCY: To be determined 

11. FIELD OF VIEW REQUIREMENTS: = 75 degrees across orbit track-narrow beam 

45 degrees ahead of spacecraft. 

12. GROUND CONTROL LIAISON DURATION: To be determined by overall Ocean 

Surveillance experiment. 

13. GROUND CONTROL LIAISON FREQUENCY; As 12 above 

14. EXTERNAL TEST ITEMS: None 

a. Launched from station - none 

b. Launched from resupply - none 

c. Launched from ground - none SECRET 

A-124 
NRO APP 

RELEASE 

ration 

)e 

R 

15 

A-125 

15. QUALIFICATION TESTS: 

a. Ground - Astronaut training, equipment calibration, astronaut 

calibration 

b. Atmosphere - None 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING iLIGHT: Intercept system 

operating passively will receive a series of test 

signals which will be processed and presented via 

a suitable grid display to Astronaut for 

(a) Identification and (b) for location notation of 

emitter followed by action taken with other related 

sensors. 

17. HANDLING PROCEDURES: Not Applicable 

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A-126 
j. Training Requirements - See lb and li above. 

2. GROUND PERSONNEL 

Ground personnel requirements for this experiment have not been defined, 

however it is anticipated that existing Navy organizations and personnel 

capabilities will be directly applicable. 

A-127 

NRO APP FOR 

RELEASE 2015 

SECRET 

ATTACHMENT E 

MANNING DESCRIMON 

I. ASTRONAUTS 

a. Number required - one 

(1) Man's function 

(a) As part of test - monitoring elint intercept display - tentative 

identification of ship class - decision making utilizing elint 

display output. 

(b) As technician conducting test - equipment adjustment for fine 

grain tuning - varying display parameters - adjustment and 

repair of equipment. 

b. Crew skill requirements - Electronics specialist with specialized 

training in elint signal analysis and recognition; capable of 

equipment troubleshooting and minor repair. 

c. Manpower Profile - one or two per test mission 

d. Critical Functions - None anticipated 

e. Work Positions - In ocean surveillance experiment data center for conduct 

of experiments and as required for maintenance and adjustment of 

equipment 

f. Time Controlled Tasks 

g. Human Performance Measures To be determined. 

h. Physiological and Psychological Measures - As required. To be 

determined. as means of analyzing and measuring the effect of the 

Astronauts ability to perform the work tasks on the ocean surveillance 

experiment. 

i. Selection Factors - Qualified Astronaut plus requirements of lb. above 
c. Handling Equipment - None 

A-128 

APPROVED FOR 

EASE 1 JULY 2015 

ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape - As Required 

b. Film - As Required 

c. Other - Unknown 

2. HANDLING 

Component equipment comprising this experiment will be compatible 

with manhandling and will require no special equipment. 

3. PACKAGING - To be determined 

4. CALIBRATION; 

Pre-launch calibration of antenna alignment and equipment capability 

will be required. Possible post-launch calibration may be required to be 

determined. 

5. JIGS AND FIXTURES - As Required 

6. NtlIBER Or LEADS eRaq OUTSIDE TO INSIDE STATION 

Not known at this time. However, some quantity of antennae on the 

spacecraft exterior will require electrical connection with equipment 

within the spacecraft. 

7. SENSORS - None 

8. TRAINERS/SIMULATORS - As required 

9. INSTRUMENTATION • As required 

10. RELATED SUPPORT EQUIPMENT 

a. Targets - To be arranged within operating constraints of the 

development test activities of the fleet units. 

b. Ground Stations - Indeterminate at this time. To be accomodated 

within existing DOD ground station networks where practical. 
NRO AP 

RELEAS 

R 

015 

5CCRET 

11. AC.; - 

Routine electronics ground support and evaluation equipment will 

be required and available within the Navy system. 

12. ENVIRONMENTAL TEST EQUIrMENT - None 

13. fACILITIES 

Available within the Navy laboratory system. 

e 

.lity 

the 

.ctical. 

A-129 

1111111.11111111.111r * °M.WINNWSBNII 
ROVED FOR 

EASE 1 JULY 2015 

5260-21:CVP:mp 

TO : Code 7000 DATE: 9 March 1964 

PROM : Code 5260 

10 

SUBJECT: Identification of Ships 

1. It appears very likely that the identification of ships may be carried 

out without increase in equipment carried by the ships by making use of 

Mark X (SIF) IFF equipment already installed aboard our ships and those of 

Great Britain, Canada, and possibly other NATO countries. By prearrangement with these ships, it would be possible to determine their 

individual identity by making use of the three modes of interrogation and 

over 4096 reply codes provided by the IFF system. 

2. Major technical obstacle to this project appears to be the design and 

engineering of a directional antenna to be installed aboard the satellite. 

Most promising approach would be utilization of a second feed to the radar 

antenna and similar techniques to those proposed for the radar operation. 1, 

The maximum slant range required of 350 miles will require somewhat higher 71 

effective peak power than normally provided by the nominally 200-mile range 4 

IFF system. However, the 32 db antenna gain anticipated for the radar 

antenna, if duplicated for IFF, would more than make up the deficiency in 

effective radiated power, and insure operation on both interrogation and 

reply paths. 

3. Push-button identification could be provided with the four octal-digit 

reply codes displayed on a separate small indicator by active readout 

equipment already available or, if desired, displayed on a PPI near the 

radar echo. 

4. Replies from U. S. and allied aircraft will be elicited by the same 

interrogations which produce replies from ships. Distinction between the 

two types of vehicles may be necessary by code assignment in lieu of 

recognition of their widely different velocities which may not be possible 

from a rapidly-moving satellite. 

5. Assuming that the antenna problem can be solved as part of the radar 

antenna program, the remaining equipment would be very similar to existing . 

airborne IFF equipment. Present equipment weighs 50 to 100 pounds and costs ,i 

10 to 20 thousand dollars. Microelectronic versions would weigh much less, 

cost slightly more at the present time, but less later on as production -I 

develops. ; 

o (-- /( ■ r ,' (,/, r . 41% i/C-4.,-1.■ 1 

C. V. PARKER 

, ,) 7 7 . Head, Security Systems & Aviaatioc Branch * 

Electronics Division 

Excluded from automatic 

downgrading and declassification. 

A-130 
NRO APP 

RELEASE 11 

ELSD 

10 

Beacon System 

I TEST OBJECTIVE 

To locate a ground station equipped with a simple, low 

powered UHF beacon, 

II IMPORTANCE OF TEST 

A test is needed to determine the accuracy of location. Since 

n and or ditching locations. If successful, this test could lead to the 

adoption of an automatically ejected crash beacon that would be 

• and 

llite. precisely located within several hours. Prompt location would increase 

radar 

tion. ths probability of rescue of survivors, and at the sane time obviate 

higher 

e range the need for large numbers of search aircraft. 

ar 

icy in III EQUIPMENT Ig NOL 

and 

1. UHF crystal controlled multi-channel receiver. 

2. Pulsed UW/ transmitter. 

3. Digital range indicator 

4. Digital clock indicator 

5. Data recorder 

6. Dual antenna 

IV DESCRIPTION OF TEST 

Beacon equipment would be installed in several aircraft, 

ships, and ground stations. Each beacon would operate on a separate 

crystal controlled channel. Upon interrogation from the NM, a coded 

reply on a present frequency would be transmitted. As the NOL comes 

within range of the beacon, the coded replies are received and range 

Downgraded at 1Z year intervals; 

Not automatically declassified. A-131 

arried 

of the NOL can cover an enormous area of land and sea within a few hours, 

ase of 

it le a logical vehicle to be used in search operations for air crash 

—C1071,113€.04-T-L4.1...— 

-digit 

t 

the 

same 

m the 

)ssible 

radar 

xisting 

and costs 

:h less, 

=ion 

ior. Branch 

• 
APPROVED FOR 

LEASE 1 JULY 2015 

Seaton Seaton 

and time are printed on a taps. Since the path of the )DL over the 

surface of the earth will be known from data supplied by ground tracking 

stations, range and tine inforeatioa vill.producs two possible beacon • 

locations. • MOOT en the dual antsona rill dots:visa Idlish is the 

true location. • ground station for 4:deputing true latitude sad 

longitude free tele■etarred data usay he desirable. 

z , 

• 

' 71 f 

\ 1 i 

----- .. ‘ , i I 44 /44 / /iA .7".:/:--.-. 

i J 

,•• ,d,..j .1"/ 7,'V A/ .4 . ie,,_ 4.: - . 

I — ....-. I 

I ■4 P 4 

/1-1 

If the location of the beiceii is known, range and time laureation 

can be used to carpets the path of the 

• Istisated Total Cost 

4230,000 

A- 1 32 
NRO A 

RELEA 

12 

13 March 1964 

Title of Experiment: Electromagnetic Communications 

I. Test Objective: The objectives of this experiment are threefold, namely: 

(1) To determine to what degree communication coverage from surface 

radio stations in the ELF to HF frequency range, particularly those located 

in the continental USA, is available to MOL. 

(2) To measure the impedance of radio antennas over the ELF to HF 

range in the plasma surrounding the spacecraft. 

(3) To obtain as much information as possible on the propagation 

characteristics of radio signals from ELF through HF in and through the 

ionosphere. 

II. Importance of Test: Electromagnetic signals below the HF range are 

generally presumed to be limited in usefulness to the space between the 

Earth's surface and the ionosphere. However, low frequency propagation 

in and through the ionosphere has come to be recognized (e.g. , whistler 

mode) and has been demonstrated at VLF by the .LOFTI program. This 

circumstance points to the possibility that low frequency transmissions 

may provide the answer to a vexing problem, namely communication to or 

control of spacecraft over any part of the Earth by demonstrating that 

communication over the bulge of the Earth can be provided by such transmissions. The tests described herein are also designed to investigate 

other frequency ranges up through the HF band, to enable prediction of 

the performance of transionospheric communications in these ranges and 

to provide design criteria for antenna systems for proper coupling to the 

magneto-ionic medium surrounding the spacecraft. 

III. Description of the Experiment: A major objective of this program is to 

determine the effectiveness of ELF through HF transmissions for Naval 

communication to spacecraft. It is expected that a series of simple tests 

by the astronaut will provide the necessary information. Basically the 

objectives and procedures are simple and can be carried out easily, although 

the attention of an astronaut for considerable periods may be required. 

a. Configuration of Test Items 

Items required for this program are ELF through HF receiving equipment capable of being tuned to the several U.S. and other transmitters, 

the necessary cables, headphones, loop antenna and dipole antenna (both 

of which are external to the craft), appropriate telemetry and recording 

equipment and antenna impedance measuring means used in connection 

with or integral to the receiver. 

Downgraded at 12 year intervals; 

Not automatically declassified. A-133 
APPROVED FOR 

LEASE 1 JULY 2015 

b. Test Support Equipment Required 

(1) The total weight of the spacecraft equipment is estimated to be 

about 60 pounds, with the volume about two cubic feet (antennas not erected). 

A dipole and a loop antenna attached to the MOL are needed, arranged so 

that they may be extended after orbit is achieved. 

(2) Ground support will require suitable signal generators (2 to 4), 

oscilloscopes (2), auxiliary receivers and other miscellaneous radio equipment. 

c. Test Procedure 

In the first portion of the experiment, the astronaut simply observes 

and records the signal strength of the ELF through VLF stations that he hears 

in various parts of the orbit. He tunes across these bands and records in 

broad detail what he receives. Next, he makes similar observations in the 

LF through HF range. 

He then makes observations designed to determine the impedance 

and related characteristics of the dipole and loop antennas extended 

external to the spacecraft. Such information is essential for proper design 

of antennas for coupling of a receiver or transmitter to the magneto-ionic 

medium. These observations should be programmed so that antenna 

impedance in different parts of the orbit may be determined. These 

measurements will later be related to the Langmuir probe observations of 

electron density to be made in other experiments and to orientation of the 

antennas relative to the Earth's magnetic field. 

Lastly, data for determination of the propagation characteristics 

of ELF through HF signals is collected. Observations for determination of 

the apparent direction of arrival of signals, time of arrival of signals at 

the spacecraft, etc. , are made. 

(1) The experiments are so designed that man is an essential part 

of the program. Inclusion of man in the experiments will allow determinations 

to be made from observations carried out during one or two orbits which 

would require much more elaborate instrumentation and much more time if 

an unmanned vehicle were used. 

(2) The astronaut will serve primarily as a technician in conduct 

of the prescribed experiments. 

SI 

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be 

ted) 

4), 

ipR 

15 

FY 67 FY 68 FY 69 

gn 

of 

,art 

ations 

f 

ct 

(3) In brief, the testing sequence will first require that the man 

simply observe and record signals over all parts of the globe. This will require fairly continuous monitoring of a receiver by an astronaut. The other 

experiments can be performed perhaps five to ten times during an occasional 

orbit and will require approximately a total of about 10 minutes for each 

observation. 

d. Category of Experiment 

(1) Category (b). 

e. Cost (thousands of dollars) 

FY 65 FY 66 

Ives 600 300 300 300 500 

ars f. Schedule 

Not now available. 

N. Participating Government Agencies: Sponsor - BUWEPS (Na). 

V. Additional Requirements: 

a. Security: No special security. 

b. Manning Summary: See attached sheet. 

c. Logistics: Unknown 

d. Facilities: 

Existing facilities can be used; equipment required in spacecraft can 

be brought from Laboratory to launch site for integration. 

e. Simulation and Training 

(1) Astronaut: The astronaut is not required to perform difficult 

scientific tasks and can easily be trained as a technician to carry out the 

program. A briefing of two days plus four hours of simulated training should 

be ample. Detailed experimental procedures for the astronaut to follow will 

be provided by NRL. 

(2) Ground Personnel: Ground personnel must be NRL-trained 

engineers and technicians, intimately familiar with the details of the equipment. 

VI. General; 

a. Some simple telemetry and recording facilities will be required in the 

spacecraft. Existing telemetry equipment aboard MOL can be time shared. 

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MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required: (1) 

(1) Man's function: Astronaut will function as a technician 

conducting test. 

b. Crew skill requirements 

A briefing of two days and training period of four hours should be 

sufficient. 

c. Manpower profile 

Essentially continuous attention of one astronaut will be needed 

during at least two orbits to determine the ELF through VLF coverage, with 

similar attention for LF through HF. About 75% of an astronaut's time for 

two or more orbits will be required to record the essential data in the 

antenna impedance observations. 

d. Critical functions 

Observation of signal characteristics (including apparent direction 

of arrival) and recording of antenna impedance data. 

2. GROUND PERSONNEL 

a. Number required: 2 engineers and 2 technicians 

(1) Function: Mainly technical, conducting tests, observing 

anomalous data, etc. 

b. Crew skill requirements 

Ground personnel must be highly trained relative to all aspects of 

installation, test, and operation of equipment. Laboratory people who have 

participated in the design and development of the equipment will be assigned. 

c. Manpower profile 

All ground crew members will be required to be on hand where 

needed 6 weeks prior to flight, to complete installation and test. The preflight number of personnel should drop to one as soon as all installation 

and check out is completed, but will increase to two before launch. 

d. Critical functions 

Check out. 

No special requirements for other items. 

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DESIGN CHARACTERISTICS OF EQUIPMENT 

(FOR SPACECRAFT) 

1. Equipment (to be provided by NRL): Receivers, antennas, impedance 

determination means. 

2. Weight: 60 pounds 

3. Volume: One cu. ft. (receiver and impedance determination means) plus 

one cu. ft. for antennas (unextended). The antenna packages will be 

attached to MOL and will be extensible by the astronaut. 

d 

th 

r 

tion 

s of 

have 

signed. • 

pre4. Power required: 

a. 250 milliwatts continuous 

b. 2 watts peak for 60 minutes 

5. Spares: 

a. Volume - One Cu: ft. 

b. Quantity - 1 

c. Weight - 20 lbs. 

6. Tools: No special tools required. 

7. Heat Output: Maximum, 2 watts for 60 minutes; 1/4 watt at other times. 

8. Stability: No special requirements. 

9. Vibration Limits: Vibration tested prior to installation. 

10. Shock Limits: Shock tested prior to installation. 

11. Hazards: None 

12. Temperature Limitations: 10-40o

C desired range. 

13. Type and Range of Measurement: Radio signals received, apparent direction 

of arrival, Doppler shift, time delay, antenna impedance from ELF through HF. 

14. No special environmental requirements. 

15. Orientation and Position Accuracy Requirements: Information on antenna 

attitude and spacecraft location sufficient to relate measurements in 

spacecraft to observations on the ground. 

16. Equipment Operating Cycle: Receiving equipment will be operated continuously through several orbits to initially define limits of reception. 

Other measurements can be made at intervals throughout orbit (10 per orbit). 

No special requirements for other items. 

A-137 ---C-0•14W-leettrITTL— 
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13 

BW ltr 00432 of 2/20/64 Title of Experiment: 

Excluded from automatic 

downgrading and declassification. A-138 s. 
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K-J4 

are- 

:he 

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RELEASE 15 14 

SUMMARY 

Title of Experiment: SPACE STUDIES USING FAR ULTRAVIOLET 

IMAGE ORTHICON ABOARD A MANNED. 

SATELLITE 

I. Test Objective* 

Preparation of star maps and tables giving the brightO 

ness of stars in the far ultraviolet (1230-1700 A). 

Determination of utility of far ultraviolet orthicon in 

providing dawn warning. 

Determination of utility of far ultraviolet orthicon in 

making visible subvisual auroras, day auroras and particle 

dumping zones in the earth's atmosphere. 

Determination as to whether air molecular impacts on 

solid objects moving at orbital velocity produce recordable 

intensities of far ultraviolet radiation. 

Determination as to whether gas leaks and exhausts trails 

0 

are rendered visible by 1230-1700 A orthicon device. 

II. Importance of the Test 

The star mapping program is of astronomical interest in 

that it provides a measure of the main emissions from early 

type stars. As such it provides the critical test of radiation transfer theory as applied to hot stars. It is 

*Objectives are detailed in accompanying documents: "Military 

Aspect of Far Ultraviolet Orthicon Program and Application to 

MOL," by T. A. Chubb and "Proposal for Mapping of Night Sky by 

Means of a Far Ultraviolet Image Orthicon Aboard a Manned 

Satellite," by G. T. Hicks, T. A. Chubb and H. Friedman. 

A-139 tET 
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important in estimating the total energy output of the galaxy: 

The mapping also is crucial in providing additional knowledge' 

concerning mechanisms of interstellar absorption. Militarily, 

accurate knowledge of the vastly simpler sky observable in the 

far ultraviolet combined with the far weaker sun may make 

possible simpler celestial missile guidance schemes than those 

currently available. 

0 

Tests of the 1230-1700 A far ultraviolet orthicon as regard its utility in providing dawn warning, particle dumping 

warning,detection of solid objects moving at satellite speeds, 

rl 

and detection of gas leaks and rocket wakes; these tests Ir 

all relate to orbital technology and defense of orbiting 

vehicles. 

Studies of subvisual and daytime auroras relate to the 

mechanisms producing the Van Allen Belt. 

The celestial mapping must be done in space because the 

atmosphere absorbs the radiation of interest. The technological' 

tests must be made in space because the collection of atomic and 

metastable molecules making up the upper air cannot be duplicated 

on earth and because of wall deactivation. 

The above studies can in principle be done in unmanned 

satellites. In practice, however, hand tuning and adjustment 

of the closed circuit orthicon camera chain has been found 

essential for ground based low light level television. In 

addition, photographic recording of data is required, hence 

recovery is required. 

A-140 
ogicat 

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Jicated 

lent 

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The usefulness of far ultraviolet imaging devices in space 

work cannot properly be assessed without the above types of 

test. The view of a far ultraviolet orthicon is completely 

different from the view of the human eye. Distant vision 

with far ultraviolet imaging devices has never before really 

been practical. 

III. Description of the Experiment 

The proposed experiment consists of mounting in a manned 

spacecraft a television camera chain consisting of the following components: 

A far ultraviolet sensitive orthicon and camera 

electronics mounted at the focus of a reflection - optics 

wide-angle Schwartzchild Camera. 

Camera control and monitor package modeled after the 

NaVY BX-7 closed circuit television system. 

A synchronized movie or multiple exposure camera unit 

operating at low frame speed to photograph the television 

monitor screen, as used in the NEL meteor astronomy program. 

The tests consist of the procurement of a set of photographs 

of the television raster screen made at a set of prechosen 

view direction orientations and under varying day-night conditions. Provision should also be made to permit placing of 

surfaces in the free air stream so that they may be viewed by 

the orthicon detector. 

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a. Configuration of Test Items 

The far ultraviolet orthicon and optical system consist of a single unit and must be mounted so that it can look 

outside the MOL. Communication to the inside of the spaceraft can be by a hermetic sealed wiring header. The viewing 

port should be six inches in diameter or greater. The camera 

control and monitor package consists of a separate electronic 

chassis containing a small cathode ray viewing screen. This 

unit must be mounted inside the MOL. The synchronized movie 

or multiple frame camera unit is used for photographing the 

television raster for recording of data. The camera can be 

a conventional electrically operated movie camera if desired, 

or single frames of the television raster may be individually 

71t 

a 

photographed on a simple multiple exposure camera. 

Estimated weight, power and volume for the electronics I 

of the-orthicon system are: 

30 pounds; 70 watts at 24 volt d.c. during operation; 

and 1 cubic foot. 

The total system is packageable in a voume of three 

cubic feet, with a total weight of about 40 pounds and power 

as indicated above. 

c. Test Procedure 

(1) What is man's role with relation to the experiment? 

The astronaut adjusts the orientation of the space7 

craft in accordance with a pre-chosen orientation schedule and h& 

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who also serves as a television operator. He adjusts the 

camera controls for best television image and the monitor 

for proper framing, brightness and focus. It is recommended that the astronaut be given four to six weeks 

experience in operating a ground-based closed-circuit 

television system of the same type as the flight unit 

(except for spectral range of the orthicon tube). 

e. Cost FY 65 FY 66 FY 67 FY 68 

(1) Engineering & 430 K 355 K 100 K 100 K 

Development 

(2) Installation 

(Spacecraft Costs) ... . 300 K 300 K 300 K 

(3) Ground Support 90 K 160 K 75 K 75 K 

TOTAL 520 K 815 K 475 K 475 K 

The above costs were conceived as applying toward two 

flights, one in Fiscal Year 1967 and one in Fiscal Year 1968. 

IV. Participating Government Agencies 

Sponsor: The U. S. Navy under technical direction of 

Herbert Friedman, Talbot A. Chubb, Grady T. Hicks, 

and Edward T. Byram, of the U. S. Naval Research 

Laboratory. 

e 

er 

'imenti 

iA 

spacel 

and bi 

I. 
A-144 

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IF 

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PROPOSAL 

for 

Mapping of Night Sky By Means of a 

Far Ultraviolet Image Orthicon Aboard a Manned Satellite 

Prepared by 

G. T. Hicks 

Project Scientist 

Meteor Astronomy Section 

T. A. Chubb 

Head, Upper Air Physics. Branch 

H. Friedman 

E. O. Hulburt Center for Space Research 

U. S. Naval Research Laboratory 

Washington, D. C. 20390 

10 October 1963 
NRO AP FOR 

RELEAS: 2015 

Proposal for 

Mapping of Night Sky By Means of a 

Far Ultraviolet Image Orthicon Aboard a Manned Satellite 

by the 

E. O. Hulburt Center for Space Research 

U. S. Naval Research Laboratory 

Washington, D. C. 20390 

I. INTRODUCTION 

The development of rockets and of orbiting vehicles has 

permitted a major extension of astronomical research into 

spectral regions inaccessible from the surface of the earth. 

The space astronomy studies thus far accomplished have been 

concerned mainly with the ultraviolet emission of early type 

stars and the present proposal continues this line of study. 

Past experiments in far ultraviolet astronomy have been 

made from Aerobee rockets equipped either with simple reflecting telescopes and narrow band photometers or objective 

grating spectrographs. Although considerable information has 

been obtained from the rocket flights, it has been limited 

to only the brighter ultraviolet stars. Moreover, the information has been sketchy; major portions of the sky have not 

been surveyed and major gaps in knowledge exist in those 

A-145 
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PPROVED FOR 

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portions of the sky that have been explored. The rocket 

techniques encounter severe problems in identifying 

individual stellar sources in the Vela, Puppis, Carina 

region of the Southern Milky Way, because of the high density 

of relatively bright (less than 6th magnitude) early type 

stars. Finally, the exploratory character of the early 

rocket work makes it most desirable that conclusions 

reached in these early studies be checked by other experimental techniques. 

II. SCIENTIFIC OBJECTIVE 

The scientific objective of the proposed experiment is to 

map the celestial sphere in the far ultraviolet region of 

the spectrum from about 1230-1700 R, so as to provide relative 

photometric intensities for the early type stars. The 

achievement of system sensitivities several orders of magnitude 

greater than those used in the present rocket photometer scan 

studies will be sought. 

It is not possible to predict all the scientific results 

which might develop out of a far ultraviolet orthicon mapping program, but some possibilities are listed below: 

1. Improved spectral classification of early type 

stars: It is presently known that visible photometry 
NRO AF' 

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ty 

to 

Ave 

tude 

:an 

.s 

and MK spectral classification can be used empirically 

to predict stellar brightness in the far ultraviolet. 

The observed far ultraviolet brightnesses, however, 

scatter about the empirically predicted values by about 

one stellar magnitude, suggesting that present methods 

of stellar classification may be inadequate. 

2. Tests of stellar model calculations for early 

type stars: The orthicon mapping program may not provide an immediate direct test of model theory, since 

only relative far ultraviolet stellar brightness measurements are likely to result from early orthicon requirements. 

If, however, the orthicon photometric scale is calibrated 

by rocket flights, giving data on a few stars, the 

results can then be converted to absolute flux readings. 

Even without rocket calibration, the mapping program 

should provide some check on stellar model theory, since 

it will provide photometric comparison between early A 

stars and the B and 0 stars. 

3. Measurement of interstellar absorption: If the 

expected increase in sensitivity over rocket photometer 

mapping techniques is achieved with the orthicon unit, 

stars sufficiently distant should be seen so that the 

flux arriving at the earth will have been affected by 

interstellar absorption. Brightness comparisons between 

s'\ 

A-147 
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near and far stars will then measure interstellar absorption and a comparison between light absorption in the far 

ultraviolet and in the visible should then be possible. 

Such absorption data should lead to a better understanding 

of the size distribution and character of matter in space 

and of the resulting absorption process. 

4. Far ultraviolet emission from extragalactic 

nebulae: If the expected orthicon sensitivity can be obtained, it appears that far ultraviolet emission from the 

Andromeda nebula may be detectable. Such a measurement, 

combined with presently available visible and near ultraviolet data should give a realistic measure of the relative 

importance of far ultraviolet radiation in galactic energy 

release. 

5. Emission nebulosities in the far ultraviolet: 

At present there is no good measure of the far ultraviolet 

brightness of emission nebulosities. If the far ultraviolet 

emission from such nebulosities is at all comparable with 

energy release in the visible, it should be measurable with 

the orthicon system. 

6. Far ultraviolet images of moon and planets: 

The far ultraviolet image orthicon system sensitivity should 

be adequate to detect the full moon as a source, and thereby 

to measure the albedo of the moon. Such a measurement may 

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NRO APP OR 

RELEASE 2015 

be interpretable in terms of Lunar surface characteristics. 

The optics planned for initial studies would most likely 

be designed for too wide an image angle to provide for 

study of detailed features on the Lunar surface, although 

future studies could be directed toward this goal. Detection of Jupiter may also be possible, most likely because 

of the high albedo expected in the far ultraviolet caused 

by Rahleigh scattering in its extensive H2 atmosphere. 

III. ORTHICON IMAGING VS. DIRECT PHOTOGRAPHY FOR FAR ULTRAVIOLET MAPPING FROM MANNED SATELLITES 

This choice of orthicon televsion techniques as the 

means of carrying out the far ultraviolet mapping program, 

as opposed to direct photographic mapping, is based on two 

factors. -First, we do not know how to do the work by direct 

photography. Secondly, the use of image orthicons permits 

the work to be done faster and requires less perfect vehicle 

stabilization than direct photography. This second factor 

is a result of the greater optical speed (higher sensitivity) 

of the orthicon detector as compared with film. 

The use of direct photography for mapping the night sky 

below 1700 A is difficult because there exists no satisfactory 

optical filter material which will block the visible and 

A-149 
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near ultraviolet and at the same time transmit any radiation 

in the far ultraviolet. No photographic film is available 

0 

which is sensitive to radiation below 1700 A and not sensitime to radiation in the near ultraviolet and visible regions 

of the spectrum. Because of these two factors, film and 

filter cannot provide imaging sensitivity confined to the 

1230-1700 X or similar spectral band. In contrast image 

orthicon units can be built with CsI photosurfaces which are 

quite sensitive below 1700 X while being dead tp near ultraviolet and visible radiation. 

The great sensitivity achievable with image orthicon 

detectors has been demonstrated many times. For example, 

image orthicon systems are capable of recording meteor 

trails too weak to record on visible film. With very 

modest optics, image orthicon systems have been very 

effective in picking up the ANNA satellite even when its 

light flashes were operating at very reduced intensity. At 

Organ Pass, New Mexico, orthicons have provided good images 

of extragalactic nebulae with about 16 seconds integration 

time. 

?It • 

l■rt' 

A-150 
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RELEASE 1 

IV. PROPOSED EXPERIMENT 

The proposed experiment consists of mounting in a manned 

spacecraft a television camera chain consisting of the following components: 

1. A far ultraviolet sensitive orthicon and 

camera electronics mounted at the foxus of a reflection -

optics wide-angle Schwartzchild Camera. 

2. Camera control and monitor package modeled 

after the Navy BX-7 closed circuit television system. 

3. A synchronized movie camera unit operating at 

low frame speed to photograph the television monitor 

screen, as used in the NRL meteor astronomy program. 

4. An astronaut who adjusts the orientation of 

the spacecraft in accordance with a pre-chosen 

orientation schedule and who also serves as a television 

operator; who adjusts the camera controls for best 

television image and the monitor for proper framing, 

brightness and. fou.:.s. It is recommended that the 

astronaut be given four• to six weeks experience in 

operating a ground-based closed-circuit television 

system of the same type as the flight unit (except for 

spectral range of the orthicon tube). 

ion 

ions 

ire 

!S 

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V. ESTIMATED WEIGHT AND POWER 

1ff 

Estimated weight, power and volume for the electronics 

of the orthicon system are; 

30 lbs; 70 watts at 24 volt d.c. during operation; and, 

1 cubic foot. 

The total system is packageable in a volume of three cubic 

feet, with a total weight of about 40 lbs and power as 

indicated above. 
MILITARY ASPECT 

OF FAR ULTRAVIOLET ORTHICON PROGRAM . 

AND APPLICATION TO MOL 

By 

Talbot A. Chubb 

12 February 1964 

U. S. Naval Research Laboratory 

Washington, D. C. 20390 

A-153 
MILITARY ASPECT 

OF FAR ULTRAVIOLET ORTHICON PROGRAM 

AND APPLICATION TO MOL 

CONTENTS 

I Introduction 

II Properties of Far Ultraviolet Radiation 

III Possible Applications of Far Ultraviolet Orthicon 

Technology to Furthering the MOL Mission 

1) Horizon Location 

2) Dawn Warning 

3) Detection of Dangerous Particle Zones Prior 

to Entry 

4) Angle of Attack Determination 

5) Detection of High Velocity Man-Made Objects 

by Self-Emission 

6) 

7) Application of Far Ultraviolet Orthicon 

Technology to the Rendez-vous Problem 

8) Detection and Location of Gas Leaks and 

of Rocket Exhausts 

9) Military Application of Far Ultraviolet 

Stellar Mapping Program 

A-154 
MILITARY ASPECTS OF FAR ULTRAVIOLET ORTHICON PROGRAM AND 

APPLICATION TO MOL 

I INTRODUCTION 

The Far Ultraviolet Orthicon Program was originally conseived mainly as a program for mapping the heavens in a 

0 

radiation band 1230-1700 A. As a stellar mapping device the 

system was proposed for inclusion in the Gemini program. Use 

of such a system promises to extend enormously our knowledge 

of the emission character of early type stars and also of the 

laws governing interstellar absorption. It also provides a 

unique means of detecting unusual and unexpected astronomical 

objects and of mapping emission nebulosities in the far ultraviolet. It is not beyond possibility that Doppler shifted 

Lyman a radiation might be detectable from distant receding 

galaxies. 

Although the initial applications envisaged for the far 

ultraviolet orthicon program were more or less classical 

astronomical applications, it is also apparent that there may 

also exist important military and space technological 

applications. Probably the most important of such applications 

cannot truly be recognized prior to preliminary orbital 

explorations. Nevertheless, it seems worthwhile to document 

some of the possibilities, so that they may be properly 

explored should this program be adapted as part of the MOL 

effort. 

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II PROPERTIES OF FAR ULTRAVIOLET RADIATION 

An examination of the military potentials of far ultraviolet orthicon technology must start off with an understanding of the properties of far ultraviolet radiation. In the 

body of this report we will confine our considerations to the 

spectral band 1050-1700 2, namely that region where optically 

transparent materials are available and in which sensitivity 

is provided by Cs I photosurfaces. The important region 

1700-3000 A (Cs2 Te photosurface region) is not considered, 

although it may have important application to early detection 

of high altitude missiles after their partial penetration of 

the ozone barrier below 150,000 feet. 

0 

Far ultraviolet radiation (1050-1700 A) has several 

important characteristics. First, it is strongly absorbed 

by molecular oxygen. This means visibility toward the earth 

does not extend below 80 km. This means that it cannot be 

used for earth reconnaissance. It also means that when 

applied to space surveillance, it is never interfered with 

by lights or happenings on earth. Space at orbital altitude 

is quite transparent. Secondly, it is basically a high 

energy radiation, requiring energies of more than seven 

electron volts for its production. As a result, it is 

apparently not produced by the normal chemical reactions 

A-156 
occurring in the upper air which produce the night airglow. It is produced by the sun, early type stars, 

electrical discharges, particle impacts such as occur 

in the aurora. It is produced in shock waves (particleobject impacts at these pressures) strong enough to cause 

ionization, and undoubtedly, therefore, is produced by 

meteors. A very few specific wavelengths of far ultraviolet 

radiation are resonantly scattered by atoms in the high 

atmosphere. The third important character of the near 

earth space environment relating to far ultraviolet is 

the character of the naturally occurring emitting sources. 

The set of stars emitting far ultraviolet radiation are 

far fewer and differently clustered than in the visible. 

They are much more strongly concentrated near the Milky 

Way. The_sun is far weaker in the far ultraviolet, and 

line 

its strongest emission, the Lyman plat 1216 A, is strongly 

scattered to the dark side of the earth. The result is 

that the difference between day-night illumination level 

0 

in the far ultraviolet (if one does not filter out 1216 A 

radiation and if one excludes wavelengths longer than 

1400 X) is only 600:1, in contrast to differences of the 

order of 108:1 in the visible. 

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The applications of far ultraviolet orthicon technolog 

will depend significantly on whether the systems are designe 

to accept or reject Lyman a radiation. This difference is 

the result of the "night Lyman a glow." The entire earth 

bathed in a diffuse monochromatic light at 1216 A, at an 

illumination level of 0.01 erg/cm2/sec. This single wavelength intensity is so strong that it equals about five 

times the total intensity of all visible starlight, and is 

1/600thas intense as the illumination of sunlight in a 

0 

200 A band centered at Lyman a. The diffuse glow is present 

day and night. At orbital altitude at night glow is seen 

below the satellite as well as above; the intensity looking 

down being 40% that looking up. The change in brightness 

occurs in a narrow band at the horizon. The same situation 

probably applies during the day. 

The far ultraviolet orthicon system proposed for 

Gemini excludes the Lyman a glow. At midnight such a system 

would see no airglow except that excited by auroral or other 

high energy particles or by electrical discharge or shock 

wave. As one leaves sunset or approaches dawn, however, 

such a system sees sunlit illuminated air. At altitudes as 

low as 200 km, the sunlit horizon is visible with the sun 

depressed 22 degrees below the horizontal. Thus, far ultraviolet radiation provides the earliest warning of the 

approaching blinding onset of sunlight. 

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III POSSIBLE APPLICATIONS OF FAR ULTRAVIOLET ORTHICON 

TECHNOLOGY TO FURTHERING THE MOL MISSION 

Let us now consider how far ultraviolet orthicon technology 

may be applied to furthering the MOL Mission. In discussing 

these points we will indicate any differences between the system 

proposed for . Gemini and that needed to accomplish a given objective. Where not obvious we will indicate why use of far 

ultraviolet techniques may have advantages over visible light 

techniques. Where the application is speculative we will so 

indicate. 

1) Horizon Location: A LiF window orthicon must be used. 

The advantage of a far ultraviolet system over a visible or infrared system is that in far ultraviolet 

the same order of magnitude of light level is 

encountered day and night, provided the sun is not 

directly viewed. The far ultraviolet horizon may not 

be as sharp as in IR, but the transition altitude is 

higher and not influenced by clouds. The system 

could provide an astronaut with clear up-down 

reference. 

2) Dawn Warning: Horizon view in the far ultraviolet 

provides an early dawn warning permitting shutting 

down of damageable sensitive visible systems prior 

to encountering dangerous light levels. 

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3) Detection of Dangerous Particle Zones Prior to Entry: 

This useage is based on the emission of far ultraviolet radiation by air during particle bombardment. 

It may not be important during a peacetime low 

latitude mission. Auroral activity over Canada has 

been clearly seen in far ultraviolet radiation from 

a rocket flown at Wallops Island, Virginia, at night. 

It seems probable that selective optical filtration 

could make such events visible during the day, thereby 

providing warning prior to entering the danger zone. 

It also seems possible that the lower portion 

of the STARFISH radiation zone would be visible from 

a distance in the far ultraviolet. Airglow background of visible light would make the visible 

portion of the spectrum a poor bet for detection of 

danger zones. 

4) Angle of Attack Determination: There seems to be a 

possibility that far ultraviolet orthicon viewing 

could be used to measure angle of attack. The 

method would be based on airglow or surface glow 

induced by atom impact at orbital velocity. One 

possible method would involve viewing a disk partially 

shadowed by a second smaller disk placed in front. 

A-160 
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The front disk would then intercept a portion of the 

atomic beam produced by the satellite motion through 

the air and the location of the resultant shadow in 

the atomic beam would show the angle of attack. 

This method of'angle of attack determination is 

speculative since it is not clear as to whether the 

impact zone would be bright enough for viewing. It 

is also not entirely clear that the optical method 

is competitive with ion collection schemes, which 

have been shown to work quite well, although the 

optical scheme' probably has higher potential accuracy. 

5) Detection of High Velocity Man-Made Objects by SelfEmission: The possibility of detecting man-made 

passive objects by self-emission in the far ultraviolet 

is speculative. Such detection depends on the brightness of far ultraviolet emission produced by particle 

impacts at satellite velocity, and needs orbital study, 

since the atomic oxygen upper air is not duplicatable 

on earth. It is possible that orbital wakes and trails 

might be visible. 

6) 

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7) Application of Far Ultraviolet Orthicon Technology 

to the Rendez-vous Problem: It is not clear to the 

author what is presently planned as regards solving 

the rendez-vbus problem. In considering applications 

of the far ultraviolet orthicon, we will envisage 

that rendez-vous is effected in the following manner. 

Consider Craft A actively "rendez-vousing" with 

Craft B. First,the orbital period of Craft A is 

matched to Craft B using ground based orbital 

period data and the judicious application of thrust 

parallel to zero angle of attack. Second, perigee 

and apogee altitudes and phases are adjusted by 

judicious application of thrust parallel to zero 

angle of attack. Third, the orbital location of 

Craft A is matched to that of Craft B by judicious 

application of thrust along local vertical, thereby temporarily changing the orbital period of Craft A. 

A-I62 
JULY 2015 

Craft B should now be visible from Craft A. Fourth, 

orbital plane is adjusted by judicious application 

of thrust in a horizontal direction perpendicular to 

orbital plane. Repetitive adjustments are required. 

Fifth, physical contact is made by final phase adjustment through reapplication of thrust along a vertical 

line, contacts being made from above or below. 

It seems clear that all the terminal adjustments 

in rendez-vous should be made on the basis of information available in the spacecraft from optical and 

radio means. Optical contact would appear particularly 

valuable. Assuming rendez-vous with a friendly craft, 

Craft B could easily be equipped with flash lamps 

that would make it visible at great distances. 

Since we are considering almost coplanar orbital 

planes, two such lamps mounted at the ends of rods 

extended perpendicular to the orbit would permit 

easy accurate position and direction determination 

from Craft B, at close distances. At large distances, 

use of radar techniques or of command triggering of 

flash lamps could also permit accurate position and 

direction determination. Radial velocities could be 

determined by optical or radio Doppler methods, transverse velocities by measuring angular motion rates 

relative to a coordinate system anchored to the earth's 

horizon. 

r. 

A-163 
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We now consider where far ultraviolet optical 

techniques may have advantages over visible optical 

techniques. The first advantage lies in the very much 

lower light levels that are encountered in the far 

ultraviolet during the day. These low levels should 

permit daytime viewing of suitable flash lamps by 

the orthicon system. They should also give an advantage 

to far ultraviolet Doppler systems over visible Doppler 

systems for radial velocity measurement. The second 

advantage is related, namely the greatly reduced 

optical shock problem in day-night traverses. During 

final contact phases the relatively uniform illumination by Lyman a glow may permit steady viewing of 

spacecraft B at quite adequate illumination level. 

The possibilities of horizon and angle of attack 

measurement have been mentioned. 

8) Detection and Location of Gas Leaks and of Rocket 

Exhausts: It has been lueniiiina-FFe1717)aTy that far 

ultraviolet orthicon techniques are capable of 

detecting the sunlit upper portions of the atmosphere 

prior to detection of visible manifestations of sunlight. This detection is based on the resonance 

scattering of 1300sunlight by atomic oxygen. 

Similar resonance scattering occurs when other species 

of molecules or atoms are illuminated by proper 

radiations of light. In particular molecular oxygen 

A-I64 
FOR 

ULY 2015 

shows resonance scattering at wavelengths near (just 

beyond, I believe) the long wavelength edge of the 

spectral band under consideration. Therefore, if 

the outside of a leaky spacecraft were viewed in 

sunlight through suitable optical filters, the leaking gas stream should be luminous. At other wavelengths in the far ultraviolet, leaking gas (air or 

fuel) streams should appear black by absorption. 

The contrast should be very much greater than that 

observed when NO2 leaks into air at ground level. 

Rocket exhausts and outgassing wakes should be 

similarly visible. 

9) Military Application of Far Ultraviolet Stellar 

Mapping Program: Thescrelatific program-517Eigping 

the stars in the far ultraviolet may have significant 

eventual military application per se. The reason is 

as follows: The sky in the far ultraviolet is a much 

simpler sky than in the visible. The sun itself is 

by far the dominant source, but is relatively vastly 

less dominant than in the visible. In selected far 

ultraviolet wavelength bands the sun is -of the order 

of 104 times as bright as the brightest star, as 

compared to 1010 in the visible. The far ultraviolet 

moon is an insignificant object. The two brightest 

stars are believed to be Zeta Puppis and y Velorem, 

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APPROVED FOR 

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twa Lie close together in the sky and thereby define 

a line in space. Most of the other bright ultraviolet, 

stars map out a circle in space, defining the galactic 

plane. The star Beta Copheus dominates the northern 

polar region of the sky. Thus the far ultraviolet sky, 

even as presently known provides a far different and 

simpler sky map that may have applicability to 

simpler automatic stellar navigation systems than 

thase based on visible starlight. 

A-166 
UFO 

Y 2015 

I S 

ELECTRONIC SURVEILLANCE EXPERIMENT 

A. The problem of Ocean Surveillance requires utilization of all . 

sources of information that will serve to locate and identify ocean traffic. 

Electromagnetic radiation from a vessel may be used to announce the existefIce 

of a vessel, determine its location, and perhaps establish its idenity. This 

information or any part of it provided to an Astronaut attempting to perform an 

Ocean Surveillance experiment from the MOL will be of benefit in the assessment 

of the man's ability and utility in space. 

B. Development of The Navy Plan for the Electronic Surveillance 

''xperiment. 

1. The Navy technical panel considered three electronic surveillance 

experiments that were proposed by Navy Laboratories for inclusion in the MOL. 

A general comment applicable to the experiments as proposed is that they 

were directed more toward improving capabilities in electronic surveillance 

than they were toward assessing man's capability of performing a militarily useful 

function in space. In addition, the proposals did not provide a clean explanation 

of why the man was required or why the experiment must be performed from space. 

The functions that a human operator can perform. to improve performance of 

electronic surveillance systems are well known and there is little to be gained' 

by placing a man in space to perform these functions except to measure his 

ability to perform them in space. This analysis concluded that the experiments 

as proposed would be of relatively low importance for meeting MOL requirements. 

2. However, each of the experiments included techniques and 

equipment proposals that were determined to be an essential part of the ocean 

surveillance experiment. The utilization of Clint and Comint practices and 

equipments will provide the Astronaut with another tool to better determine 

A- 167 
PROVED FOR 

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his ability to be useful in space. As result, a single experiment proposal 

was prepared to support and become a part of the integrated ocean surveilla 

experiment. ThP experiment objective is as follows: 

"This experiment is to establish the feasibility of performing a porti 

of the ocean surveillance task by effecting identification and location by 

intercept of electronic emissions from ocean shipping." 

3. This test is required to provide complete coverage of the useab 

fX 

frequency spectrum of ocean vehicle emissions for the purpose of ocean 

surveillance. Only from an orbiting platform can adequate coverage of the oc 

be obtained. In-as-much as elint alone is a necessary but not sufficient oce 

Ts:,4 

surveillance medium, it requires integration and assimulation of data weth a 

other sources (optics, radar, infra-red scanors) to provide a positive degree 

of intelligence. The output of the multi-sensor array necessary for effectiv 

ocean surveillance can be best obtained and managed by a human performing a 

selection, sequencing, rejecting, and analysis function. provision of this 

additional source .of real-time data to the astronaut attempting to manage the 

of tasks required for ocean surveillance will, without doubt, contribute to the 

assessment of man's ability and utility in space. Jhile a great deal of the 

entire ocean surveillance experiment can and will be simulated it is believed 

by the panel that only in an actual situation - over the ocean, in orbit - can 

a true measure be made of man's ability to contribute to solution of this milita 

requirement. Data rates, sequencing of data types, precise knowledge of signal 

strengths and density and many other necessary parameters are unknown and,'most 

probably, vary randonily. A research program to establish the above quantities 

for purposes of simulation of a >OL type experiment would prohibitive in cost 

and time. 

A-168 
ULY 2015 

he 

C. Development Schedule: 

A detailed development schedule for this experiment is not available 

a

nd will be generated by planned study efforts. However, the equipments involved, 

development of which would normally be the pacing item, are largely available 

and will require only re-packaging, integration into the overall experiment, 

and re-work necessitated by the resulting interface. 

D. Cost Schedule 

BUDGET 

Engineering, Developmental 

Environmental Testing 

Integration & Installation 

Age 

Simulators/Trainers 

Data Reduction 

Equipment Rework . 

Other 

TOTAL 

FUNDI 'NGSUMMARY 

REQUIREMENTS BY FISCAL 

PRIOR a 65 a 66 

• 

YEAR 

YY 67 a 68 rY 69 TOTAL. 

70 2460 

280 

60 

2300 

2060 

535 

455 

610 

870 

680 

230 

280 

30 

130 

340 

150 

5460 

1495 

6S5 

960 

370 

280 

70 3660 2230 490 9250 

Thousands of Dollars 

it 

ial 

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E. Recommendations for Further Study 

1. A study program to initiate and later support the experiment 

development is recommended. Immediately, a study is required to: (a) outl 

1. 

the anticipated interface; (b) identify the types of equipment required; 

(c) prepare a detailed experiment development and cost schedule; (d) provide 

estimates of weight, volume, power required, heat balance, spare parts and 

in-flight maintenance And test equipment. Concurrently, it will be necessar 

to analyze experimental situations to determine in-flight experiment procedur 

This type study will probably be continued at some level throughout the MOL 

program. Just prior to initiating equipment development, a simulation progr 

based on a study will be initiated. A part of the simulation study will cove 

training requirements. 

A-170 
DIR I 

16 

Enclosure 1. Description of Proposed Studies 

TITLE: Project ARGUS Contributions to MOL 

Description of Experiments: 

1. Validation test of grow composition findings fres Project ARMS, 

to deters:Lie the rellebilltiorlaboreEory finAings in predicting and 

controlling social-esetional oompatibilitY oumoig toga =whim through 

matching perecoality, temperamental, end other characteristics of individuals. Although teem members viii presumably have interacted for souse time 

on the ground and established • satisfactory zelationship, the stress of 

isolation and comilnement, separation from other sources of social Jostle. 

factions, reduced gravitational fields mod other envirommon*.al effects may 

place greater strains on interpersonal relationship, resulting is greater 

lihelibool of communication breakdowns, loss of morale, and loss of taterpersonal coordination. It therefore seem towboat that, within the 

llisitstions of available astronauts and )CL vehicles, crew composition be 

varied or coutrolled and the resulting socialomentiomil adjustment monitored 

and measured. Perforamene effectiveness of differently-composed taus vould 

than be compered to assess the value of the alfAmosative crev colDositiou 

procedures. 

2. An ememinstion of alternative crew *isms for moaned spacecraft. 

Several laboratory etuddemAave Indicated the importance a crew size in 

the determination of peritmesoce. Decsuse of the hub coot or each increment of crew size, it is important to determine the gains in effectiveness 

associated, with increased numbers of crew members. Only with this information can rational decisions be made remains the appropriate design or 

spacecraft or other small vehicles intended for long durations of manned 

operations under conditions of reduced contact with society. The ranker of 

crew sires in the MOT, prognopermits cooperative studies of crews operating 

under considerable stress with encoder missions. laboratory findings should 

be validated in MOL, and perhaps reduced to sue ntitative terms to permit 

cost-effectiveness trade-off enalyses with regard to other vehicle design 

considerations. 

3. A st of the effects of durstico of isolation under conditions 

of reduced ty. further informstion Is maid regarding theAnaild-up 

of /nave& , the accvnralstion of strain overtime. There is laboratory 

and enecdotel data indicating that, though men can perform well under 

stress for short periods of time (34 days), prolonged stress hes en 

accumulative effect which can only be compensated up to a point beyond 

which performance decrement occurs. This queetion is relevant to the 

frequency of rotation of M3L crews, end again involves cost-effectiveness 

trade-offs since each launching for crew rotation will be an expensive 

event. LeboretorIrdets can provide help in this determination, but only 

101. itself can provide conclusive ansvers. The study would involve 

alternative leoLiths of time in orbit, and intensive Aonitorin6 of physiolp,;- 

ical and behavioral data. 

A-171 
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isolation 

4. ti2.147 or territori4114:: . tmobility repirements for men in 

. The ance of thli study lies in its 

relationship to living, space and the deeign thereof. Current research in 

Project ARGUS and elsewhere sucgests the crucial role of nan's need for 

"personal space" and activity. Intensive study of these problems is 

desirable prior to the design of *)L, and should be continued in MOL to 

determine whether conditions of resumed gravity affect spatial or mobilit 

needs. The study envisioned would vary the size and arrangpmemt of crew 

living space to include provisions for individual privacy, and permit' 

variations in mobility (perhaps including the possibility of excursions 

outside the capsule). Although Beach of the basin nark could and probably, 

should be done in terrestrial laboratories, veriflostion of laboratory 

results is MICI.would be necessary for optimal design of future craned 

vehicles. 

5. An evaluative stua of psychiatric assess and screening of 

for mei vehicles. Utilisation of such paythiet 

acsesame qums as have sea ed in Operation nespernme 

be checked for adegnacy in NM. This requires gathering extensive data 

on personnel prior to their entry into the program, and a von intensive „, 

monitoring of psychiatric adjustment in awes Although obviously poor . 

psychiatric risks would be eliminated !Zeniths programs, there will 4111 

undoUbtedly be a range of personality and Character structures with which 

to work. laboratory research prior to MOIL is needed to determine the 

validity of current assessment procedures. 

6. A study of the of extaroel visual stimulation. The 

ROL conlilhe fesigneivf or wienui. transparent viniousIbrough which 

crew mashers could view earth and the stars. It could also include or 

not include television receivers for visual contact with earth. Since 

both of these may be important Oesige considerations in future syntems, 

their importance to the emotional adjustment of men should be assessed. 

The question bare is not whether man as a visual observer can make effective 

use of such contact, but rather, Ant value has it in providing him with a. 

greeter sense of contact with reality, a lesser sense of emotional disturbance, and a lesser disruption of diurnal cycles. 

7. A study of the siolificance of verbal comaunication to and from 

earth (or other oibitil vihieles). Some potentia military applications 

of menned spacecraft rd ht require crew members to maintain radio silence 

to prevent deteztion. Bovever, it is very probable that lack of commnnicsm 

tion with earth would be very threatening to crew members. The ability to 

talk end receive feedback might be very ioportent in maintaining emotional 

stability. The stuny, then, would compere the performance effectiveness 

and emotional ad4ustment of crews under conditions of complete communiestimes black-out, transmitting but not receiving, receiving but not tronabitting, and unrestricted cnamunicatioa. 

A-172 
U. A comparative study of the reliability of moaned vs. unmenned 

sytems. NneS slality to diagnose and repair malfunctioning equipment 

offers a trade-off with regard to equipment redundancy or increased 

reliability engineering Which should be critically examined. The all-toofrequent failure of space probes because of equipment failures auggeets 

that a maintenance capability in apace might be desirable. This study, 

then, could assess the increased reliability of mission accomplisbments 

uhea human maintenanee trouble-shooting and repair are utilized. Recording 

of every instance of equipsent failure repaired by men would provide useful 

information. The study mould also compare the reliability of manned vs. 

unmanned missions, either in different or the same vehicles. 

9. A etedy ofAlece-fiLitt stress. c Several unique stresses are 

involved: in epees fllotht each cannot be effectively counteracted without 

additional information. The gravity rsduction is an obvious example, but 

measures to provide artificial gravity by rotation conflicts with vestibular adjustment mecbanisms. Only in MOL does it appear feasible to collect 

the necessary data to determine the optima trade-off between performance 

decrement through verity loss and performance decrement through vestibular 

activity. The launch and re-entry stresses also appear to be significant, 

and data should be gathered to abed light on the emotional as well as 

physiological problems associated therewith. 

10. Astudy on the nemagemest of crises over suatained riods of time 

would alma ligbt on the extent to which personnel can adequate 

levels of perform:co over time. Since it is likely that crises may occur 

unpredictably and over sustained periods of time, it is critical that 

some mierstanding of the ability of astronauts and scientists in NDL to 

handle such issues be explored. Initial work would have to be of a 

laboratory nature and probably of non-expericenttal analyses' of reactions to 

crises in the actual HOL. 

Lye 

1 11. A study of the process of adepting_to space flight conditions. 

4... in spite of ahiji degree oftreining prior to NUL entry for the first 

time, it is likely that personnel viii De throudz an adaptation period 

of a physical, pnyehological and interpersonal nature. They viii have to 

adjust to the new environment. As they become more experienced in the 

situation--over repeated missions--it is likely that the adaptation period 

will speed up. To facilitate this adaptation process, it is important in 

am the early stages of experience that information about the nature of the 

o process and its rate of stabilization be understood. Little by vary of 

1 actual expericontation in orbit mould be conducted in the early stages of 

such research, but continuous data samples, retrospective reports, and 

some laboratory experimentation mould be conducted.. Subsequently, attempts 

to facilitate adaptation to space flight would be evaluated in the MOL. 

12. A study of the emotional irvasTt of icolation. Research findings 

suggest that consistently effective and appropriately oriented human 

A-173 
PPROVED FOR 

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perforeaace over tiee is dependent upon enianinine an immediate envi 

that (1) is stimelatiue to an interwediate *gee, and (2) provides coot 

ous psycholoeicallinkeee of the individual to others. Behavioral rose 

on the effects of isolation in menotonouc settinee has shovn disturbances 

in activation level, sleepine and dremeine patterns, and attentional and. 

information-proeeasin;; capabilities, an well as bizarre emotional reactions 

distortions of reality, and disturbin alterationa in self ima6e. A gene 

concept of payeholoeical isolation further suggests that some of these 

effects may occur even when an individual has duties to perform. while 

functioning as a :weber of a group. Since the JCL setting appears to pos 

uniquely certain features conducive to stress, psychological separation of 

individuals, and their remoteness from their normal world of reference, the 

collection of behavioral data an activation level, intellective processes 

and subjective emotional experiences mould be of treat scientific benefit. 

The ))L reeeerch would creatly extend and validate the ongoing research 

on isolation. 

The research would involve obtaining measures at various time during 

the mission from each MOL meaner. Insofar as feasible, physioloelcal 

=weave indicative of arousal level, sleeping and dreaming would be sat 

from coatinuoue medicsl monitoring. Periodically, MOle members would also 

take brief performance tests desigaed to detect changes in ability to recei 

and process information.' By ansverine questions and eakine ratings on 

specially deeeleped tests confidentially and privately, members would p 

indication of their emotional and subjective states. Monitorine of phys 

eieal, measures mould require standard and eeveloping techniques of trans 

placement chose signals would presumably be tele metered to earth. The 

intellectual performance and subjective reaction research would require 

private tvom.maymenwnication with each neMberj quite possibly the tests 

could be preeregorded and automatically administered from a miniature tape 

recorder on site, Which might also serve to record the man's verbal and/or 

coded respomaes. If possible, same means of visual presentation of test 

stianli, perhaps on a TV tube, would greatly increase the flexibility and 

adequacy of the tests. As a baseline against 'which to compere payehophysio 

sic 1, performance and subjective data, it %/bald be hilly desirable to 

arrange a gronebased group of control subjects. 

13. A study of the effects of moni.toriNeand feedback on performance. 

Although crew will no ciou5t be trained. to a peak level ofr individual and 

team, perfeemence efficiency, the variety of novel features in the environment . 

of MOL crew nay produce actual or perceived performance decrements. The 

extent of and the reasons for such decrements may be a MSC of concern to 

crew eeebers. Since all arevreemeers mill be subject to the same stresses, 

the value of others as eoapariaon objects will be reduced. Thus, external 

evaluations, both objective end subjective in nature, may be important in 

maintaining individual eorale and harecaious crew relations. On the other 

hand, too frequent external monitoring and evaluation over extended periods 

eay have adverse "'tale brother" type effects. Thus, laboratory and in-orbit 

studies of the effects of raonitorin sad feedback on performance over 

A-174 
extended periods are necessary to determine the optimal rate, schedule, 

quality, and other characteristics of such monitoring and feedback. 

14. Pelt logy input into non's cognitive and psychomotor 

orisen MOLtresscouatious. 2E is ceris6 that eperation within 

ecology or periods of time will impose bizarre 

stresses an the human component of the system. the results of these strews, 

in terns of subtle or pronounced alterations in perfornmoce of men during 

the course of the mission, eel well constitute the critical element in 

execution of the overall )2)L program.. Accordingly, it is proposed that 

psychopharmacological tedmiques be assessed for their value in assuring 

that man's perftemence is comaletely under cognitive control during the 

mission, both with respect to mental acuity in his tasks and his muscular 

performs:, of physical work. lb achieve this goal, the use of new drugs 

and orgenie chemicals on men, in controlled mmeentratioes, is esvisaged. 

These agents group into two types insofar as their sites of action in the 

body are concerned: (1) the first type is able to penetrate the blood-brain 

barrier and reach the centnammiees system, at uhdoh point processes of 

central excitation or depression can be drug-medistoi; (2) the second type 

is restricted by structure to operate only in the peripheral, effector areas 

of the body,, and csa trialtr neuromuscular effector systems to deliver any 

possible desired degree of Emplification of muscular contractility is the 

performance of aptysical task. 

Now, we specifically propose to enter into a double-barreleditermar 

coloGical study of structure-dose-respome relationships found in both 

classes of themicel agents, with attention focused on the ultimate criteria 

of human perforeence Worth* influence of these agents. This work 

begins on the laboratory scale, to evolve quantitative dose-response 

relationehiper.and then must proceed to the NUL testing =waste observe 

the modifications Produced in dose-effect parameters by the peculiar MDL 

stresses. In the area of dregs which alter behavior by action at the 

central level, we propose to study: (1) drugs which act as psychic energizers 

and increase the flow rate for etieuli which emerge to the peripheral neuromuscular systems;. (2) drugs such as 4-hydruaybutyric acid which act specifically at the chenoreceptor loci controlling elnewithout otherwise altering metabolism) and (3) drugs which are specifically tailored to negate 

the impel sent of abstract thinking, which might otherwise develon in a 

confined ecology subject to small-group occupancy. In the area of drui 

and chemical agents which act peripherally to alterperformanoc, we 

propose to study those Which can mechanically amplify the decree of 

nuscular coetractility, as a close function of dosage invested via the 

aerosol route. 

This work, on the ground laboratory level, will proceed thromch 

performance studies with small animals, thence into larger animals and 

primmtee, and finally into man in artificial confinement situations. 

Than, the extension to z end his performance in the MDL situation will 

be logical, and in restive. 

ED FOR 

ULY 2015 

A-175 
ROVED FOR 

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Test support equipment required 

The studies herein described have a common core of equipment 

requirements. Physiological monitoring and telemetering equipment for 

detecting EGG, EKG, skin resistance, body temperature, blood pressure, 

blood chemistry, urine content, weight, activity level and Sensory 

ability changes would be required. It would also be necessary to have 

behavioral monitoring equipment such as intercom recording or transmitting, intra-capsule television cameras and transmitters, and location-. 

sensing devices and recorders (or transmitters). For subjective emotionel reactions and cognitive functioning measurements, perhaps a 

private charactron console for presenting questions and eliciting answers could be included. Facilities for presenting standard tasks and 

tests for measurement of abilities and learning curves would also be 

desirable. AGE for receiving, recording, and reducing all of this 

data would be essential, including analog-to-digital conversion capability. A considerable amount of digital computer time for analysis 

would also be required to provide results of tests in a timely manner. 

Test procedure: 

The exact procedure for each of the studies would vary, but as 

many tests as possible would be packaged in each mission. Assuming 

six MDLs and an average rotation cycle of 60 days, 36 crews would be 

orbitted per year. This large an E would permit variation of several 

dimensions simultaneously for inter-crew comparisons, while the length 

of each mission should permit variation of several variables for 

within-mission, =Ea-crew comparisons. The test procedure would consist of determining and controlling the composition, sire, and duration of each mission by pre-experimental planning. This obviously requires working within the framework of the requirements of other 

scientific disciplines, but nonetheless should permit a powerful experimental design. within a mission, teats of visual stimulation, 

verbal communication conditions, maintenance capabilities, and 

territoriality restrictions would be programmed. Monitoring of physiological and social-emotional reactions to these experimental manipulations and to space-mission stresses would be required for all 

flights. 

Since these are exclusively life sciences studies, man's role 

as the object of study is clear. In addition, it may be necessary 

to include on each crew a man who has been trained at least to take 

blood samples, urine samples, run analyses of these, operate SEG and 

4= equipment, take blood pressures, etc. In small (2-man) vehicles, 

these would necessarily be supplemental duties for one or both of the 

astronauts, and should probably be supplemental in all cases, since 

the amount of time required for these activities should be minimal. 

A-176 
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The testing sequence cannot be determined without regard to 

other MOL activities. However, to the extent possible an experimental 

design would be utilized to produce the maximum information yield per 

observation. The interrelated nature of these studies suggests a 

series of programmed designs that permit each observation to provide 

information on several experimental variables (as, for example, in a 

nested or unfolding hypercube). 

Some terrestrial laboratory work prior to the orbital laboratory 

research is needed for methodological development, particularly in 

the areas of measurement techniques and shake-down of experimental 

procedures. An engineering systems analysis would be required to de• 

termine the design implications for MOL of some of the studies. 

Category of experiment: 

Most of the studies proposed above ill into Category 'b', contributing to the NDL objectives but without significant implications 

for the design characteristics of MX.. Studies concerned with slat, 

duration, and territoriality may have significant design implications. 

Cost (Budget Requirements by Fiscal Year) 

The following budget estimates are offerpled as very tentative 

figures, expressed in thousands of dollars. 

Prior1262 FY66 126/ 1766 au Total 

1. Engineering and 75 175 200 75 75 600 

Development 

2. Installation 100 275 275 650 

3. Ground Support la 200 200 200 M 2/a 

TOTAL 200 375 500 550 600 2,225 

Participating Government Agency: Naval Medical research Institute 

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U. S. NAVAL RADIOLOGICAL DEFENSE LABORATORY 

San Francisco, California 94135 

PROJECT PROPOSAL 

for the 

AIR FORCE SPACE SYSTEMS DIVISION 

For Implementation Aboard the Manned Orbital Laboratory (10L) 

Title of Experiment - Heavy Particle Dosimeter 

I. Test Objective 

To measure the radiation exposure during space flight'from the 

primary cosmic radiation, distinguishing between the proton component 

and the heavy charged particles. Radiation exposure from the proton 

component will be measured directly. The flax and charge distribution 

of the heavy particles will be recorded over select intervals. From 

this information the total dose contribution from charged particles 

will be determined. 

II. Importance of the Test 

It is.important to measure the total radiation exposure received 

in manned space flights. These measurements should. by complete enough 

so that the biological significance of the radiation exposUre can be 

properly evaluated. Because the biological effectiveness of the heavy 

particles in the cosmic ray environment is afferent from that of the 

proton component some means of differentia%ing between the different 

particles is necessary. It is generally rot appreciated that most 

integrating dosimeters suitable for dose measurements during space 

flights (glass, photographic emulsions, thermoluminescent phosphors) 

measure the heavy charged particles with conaiderablx reduced 

efficiency over that for high-energy protons and pais ray.. Additional detectors are therefore required to provide a Complete description 

of the cosmic ray background. 

The system to be described is intended for use in all manned space 

missions as well as in those containing biological payloads. This is a 

passive system that requires recovery. Data interpretation will be made 

at the Laboratory. 

A-178 
2015 

III. Description of the Experiment 

The detection system will contain several types of dosimeters 

together with a series of charged partidle detectors. These will 

include photographic emulsions (dosimeter film), silver phosphate glass 

and LiP dosimeters. Evaluation of the heavy component will be made 

with nuclear emulsions and with heavy particle detectors (mica and 

several plastics) of different sensitivity that will register tracks 

only if their rate of energy loss is greater than the threshold energy 

for recognizable damage in the material. 

a. Configuration of Test Items 

See attachment A. 

b. Test Support Equipment Required 

No test support equipment will be required. (No attachment 

B.) 

c. Test Procedure 

This will be a passive integrating dosimeter system that will 

require no attention once it has been positioned in the space vehicle 

or placed on the astronaut (no attachment C). Although the proposed 

system does not require the utilization of the astronaut's time it does 

serve the very important function of determining his radiation exposure 

in a complete and detailed manner. This information could be of great 

value in determining the adequacy of conventional dosimetric systems 

for future missions. . 

d. Category of Experiment 

(3) Category c. 

e. Cost 

See attachment D. 

f. Schedule 

(1) Hardware and software available for test: Dec 1964. 

(2) Hardware and software flight readiness date: Dec 1964. 

A - 1 7 9 
PROVED FOR 

SE 1 JULY 2015 

IV. Participating Government Agencies 

Sponsor: Bureau of Ships (Code 364). 

Test Equipment Acquisition: U.S. Naval Radiological Defense Lab. 

V. Additional Requirements 

a. Special Security: None. 

b. Nanning Description Summary: Not applicable. (No attachment 

S.) 

c. Lo sties: It is not understood what information is required 

over and beyond the funding summary of attachment 4. 

d. ?acuities: Existing facilities can be utilized. 

e. Simulation and Training: 

(1) Astronaut: This will be a passive dosimetry requiring no 

attention during the flight. 

(2) Ground Personnel: The only requirement on ground personnel 

is that theyInstanthe dosimeters prior to flight and recover them for 

delivery to the Laboratory. 

(3) Equipment: No additional equipment is required. 

VI. General: 

a. Communications and Data Handling Requirement. (No attachment 

F. 

b. Development Characteristics. (See attachment G.) 

A-180 
JULY 2015 

ATTACHMENT A 

DESIGN CHARACTERISTICS TEST EQUIP) NT 

1. EQUIPMENT TO BE TESTED: Charged particle dosimetry packet. 

2. WEIGHT: 3 lbs or less. 

3. VOLUME: Stored 20 in.3 or less. In use 20 in.3 or less. 

4. POWER: None. 

5. SPARES: None. 

6. TOOLS: None. 

7. HEAT OUTPUT: None. 

8. - 11.: None. 

12. TEMPERATURE LThaTATIONS: min: None. 

max: 80°F. 

13. - 16.: None. 

17. EQUIPMENT LOCATION RDWIREMENTS: Inside vehicle attached to 

Gemini capsule. Considerations 

are also given to miniature 

packets placed in the astronaut's 

clothing. 

18. - 20.: None. 

21. MAINTENANCE REQUIREMENTS: 

Ground: None. 

Space: See 12. 

A-181 
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A-182 
ROVED FOR 

1 JULY 2015 

U. S. NAVAL RADIOLOGICAL DEFENSE LABORATORY 

San Francisco, California 94135 

PROJECT PROPOSAL 

for the 

A/R FORCE SPACE SYSTEMS DIVISION 

For Implementation Aboard the Manned Orbital laboratory (MOL) 

Title of Experiment - Nuclear Radiation Personnel Monitor for Space 

Flight 

I. Test Objective 

To establish requirements and criteria needed in the development of 

a high performance nuclear radiation personnel monitor for space flight. 

II. Importance of Test 

High performance radiological hazard monitors will be important to 

military missions involving manned space flight. During these missions, 

personnel may be exposed to radiations having a wide range of intensity 

(mr/hr-kr/hr), and the radiological hazard state within the vehicle must 

be known continuously. Monitors to perform this function accurately and 

reliably oversa wide intensity range are now being developed. 

This development will require in-flight evaluations. Experience in 

the development of military radiacs has demonstrated the need for tests 

and evaluations conducted under actual field conditions in order to 

achieve necessary performance and reliability levels. Although these 

levels may be reached in large measure through design judgment and laboratory tests (based on operational experience in the field), it is the 

field evaluation that ultimately relates instrument, operator, and actual 

use conditions, thus providing a realistic assessment•of performance 

leading to the establishment of instrument requirements and criteria for 

successive application. 

The MOL will provide a means for flight evaluation of a combination 

dose and dose rate monitor designed for manned space flight. Results of 

this evaluation will yield data on calibration and man-instrument performance and reliability needed in the design and human engineering of 

high performance monitors. 

A-184 
LY 2015 

III. Description of Experiment 

A radiation monitor which continuously indicates dose rate and 

displays accumulated dose will be installed in the MOL for in-flight 

evaluation of calibration, performance, and reliability. 

a. Configuration of Test Items 

The monitor occupies a. parallelopiped volume less than 150 cu 

in. and weighs less than 32 oz. Location in the MOL is not critical but 

installation near the center of the MOL volume will be desirable. Operation will be continuous. Power required vill be less than 250 mw peak 

and may be from self-contained batteries. Bracket mounting will be used 

with no special mounting or shielding requirements. (See Atch A.) 

b. Test Support Equipment Required 

No support equipment will be required in the spacecraft or on 

the ground. (See Atch B.) 

c. Test Procedure, 

The evaluation to be performed will be functional. Dose and 

dose rate displays will be observed and recorded manually on a predetermined schedule. Scheduled calibration and instrument performance checks 

(through self-contained means) will be performed and results noted. These 

data will be used in conjunction with other radiation or environmental 

data recorded and estimated during the flight to assess performance and 

reliability. This assessment, together with operator experience and 

reaction in the use of the monitor, will be employed in establishing data 

requirements- and.design criteria for monitors in this application and 

may lead to redesign and subsequent flight evaluations. (See Atch C.) 

i

JJ 

1; 

d. Category of Experiment 

Category b. Although the experimental results will not have a 

significant influence on the design characteristics of the MOL, they will 

influence design of hazard monitors important to the capabilities of 

manned military space, missions. 

e. Cost (Budget Requirements by Fiscal Year) 

Engineering and development of the first monitor, pre-flight, 

calibration and testing, and post-flight data analysis will be conducted 

using funds already available to NRDL under BuShips Subproject SR 007 

11 01, Task 0549. Installation of the monitor and integration with the 

MOL program will require $25,000 of additional funding during FY 1965 

A-185 
APPROVEDFOR 

EASE1JULY2015 

and $15,000 during FY 1966. Budget requirements beyond the first flight 

evalyWon are anticipated but not yet defined. (See Atch D.) 

f. Schedule 

(1) Hardware and software available for test and calibration 

in 1965. 

(2) Flight readiness date: late 1965 or early 1966. 

N. Participating Government. Agencies 

Sponsor: Bureau of Ships (364) 

Test Equipment Acquisition; Current plans under Subproject SR 007 

11 01, Task 0549 will satisfy all test 

equipment requirements with exceptions 

noted in Sec V.c.(2). 

V. Additional Requirements 

a. Special Security: None 

b. Manning Description Summar,: 

(1) Astronauts: Astronaut will be part of operator-instrument 

evaluation (his impressions and reactions important to experiment 

objectives). He will observe and record monitor displays (meter and 

register) at regular intervals (not more frequently than once every 6 

hours) and will make brief performance checks periodically (approximately 

24 hour intervals). These observations and checks can be performed by a 

single crew member; however, more useful data will be obtained by involving both crew members in the evaluation. It is estimated that less than 

one minute vill be required for each observation and each performance 

check. Adherence to precise time schedules is not required, and it is 

planned that this item be included as part of the astronaut's regular 

operating schedule. (See Atch E.) 

A-186 
c. Logistics; CY 64 CY 65 •CY 66 TOTAL 

(1) Manpower (MY) 

*(a) Hardware .2 1.3 1.5 

(b) Installation .1 .1 .2 

*(c) Operation .5 .5 1.0 

(calibration, 

pre-flight 

tests, data 

analyses) 

*Provided by BuShips Subproject SR 007 011 01, Task 0549 

at USNRDL 

(2) Facilities 

Existing facilities will be used for calibration and most 

pre-flight tests. However, portions of the pre-flight tests (environmental) will be conducted in a flight simulator which must be made 

available. 

d. Simulation and Training 

(1) Astronaut: Astronaut will not require special skills. Training will be in monitor operation only. Necessary training will be short 

(several hours) and will not necessitate simulation testing. 

(2) Ground Personnel: None. 

(3) Equipment: Radiation monitor only. 

VI. General 

a. Communications and Data Handling Requirement: Data will be 

recorded manually from a single meter display (analog) and a single register (digital). No on-board data processing will be required. These 

records (together with operational notes) will be flown down with recovery 

capsule. There will be no requirement for data or voice communication to 

ground stations. (See Atch F.) 

A-187 
NRO APPROVED FOR 

ELEASE1JULY2015 

I 

b. Development Characteristics: At least one flight test is 

planned. Subsequent test will depend upon results obtained. The monitor design will be based on the current design of the NRDL Dose/Dose-rate 

Meter (AN/PDR-65) and data on radiation instrument performance in space 

being developed by the NRDL/BUSHIPS subproject. (See Atch G.) 

A-188 
DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TESTED: Combination dose and dose rate meter 

2. WEIGHT: 2 lb 

3. VOLUME: Stored 150 cu in. In use 150 cu in. 

CRITICAL DIMENSIONS - SHAPES: (See Sec. III.a.) 

4. POWER: (See Sec. III.a.) 

a. Continuous: 0.15 v 

b. Stand-by: 0.1 v 

c. Average operating: 0.15 v 

d. Peak: 0.25 v 

e. Duty cycle: Continuous 

5. SPARES: None 

a. Volume: None 

b. Quantity: None 

c. Weight: None 

6. TOOLS: None 

a. Volume None 

b. Quantity: None 

c. Weight: None 

d. Power: None 

7. HEAT OUTPUT: 0.15 w 

A-189 
PPROVED FOR 

ASE 1 JULY 2015 

8. STABILITY 

a. Moving parts: Meter and electromechanical register 

9. VIBRATION LIMITS: MIL-STD-167 (Type I) 

10. SHOCK LIMITS: MIL-S-901 

11. HAZARDS (fire, explosion, electrical, taxies, other): None 

12. TEMPERATURE LIMITATIONS: -40° - +50°C operational 

-62° - -75°C storage 

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

measured while test is underway): Dose to 200 r and dose rate to 10,000 

r/hr (gamma-proton). 

14. SPECIAL ENVIRONMENTAL REQUIREMENTS: None 

15. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: None (See Sec. 

Station: None 

Equipment: None 

16. EQUIPMENT OPERATING CYCLE 

Frequency: Continuous 

Time Duration: Contibuous 

17. EQUIPMENT LOCATION REQUIREMENTS: Lopation inside laboratory not 

critical (See sec. III.a.) 

18. SPECIAL MOUNTING REQUIREMENTS: 

Apertures: None 

Booms: None 

Windows: None 

Antennae: None 

Bracketry: Simple mounting bracket (See Sec. III.a.) 

A-190 
JULY 2015 

19. PRESSURE VESSELS: None 

20. ELECTRO MAGNETIC INTERFERENCE (spurious generation, special shielding req, etc): None 

21. MAINTENANCE REQUIREMENTS: 

Ground: None 

Space: Calibration and operation checks (See Secs. III.c. and 

V.b.(1).) 

A-191 
PROVED FOR 

E 1 JULY 2015 

ATTACHMENT B 

TEST SUPPORT EQUIPMENT 

1. RECORDING MEDIA 

a. Tape: None 

b. Film: None 

c. Other: Manual recording of monitor readings (See Secs. III.c 

and V.b.(1).) 

2. HANDLING (special equipment required to handle items being tested): 

3. PACKAGING: None 

4. CALIBRATION - alignment, deployment: Yes (See Secs. III.c. and V.b.(1) 

5. JIGS AND FIXTURES: None 

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

7. SENSORS (TRANSDUCER - OUTPUT SIGNALS): None 

8. TRAINERS/SIMUIATORS: None 

9. INSTRUMENTATION - cockpit and/or laboratory (note effect of time 

sharing instruments with other experiments); None 

10. RELATED SUPPORT EQUIPMENT: None 

a.. Targets: None 

b. Ground Stations: None 

c. Tracking: None 

d. Handling Equipment: None 

11. AGE: None 

12. ENVIRONMENTAL TEST EQUIPMENT: Yes (See Sec. V.c.(2).) 

13. FACILITIES: USNRDL with exception noted in Sec V.c.(2). 

A-192 
NRO APPROVED F R 

5 

ATTACHMENT C 

TEST OPERATING CHARACTERISTICS 

1. ORBITAL PARAMETERS (desired) 

a. Altitude: No requirements 

b. Inclination: No requirements 

c. Epoch: No requirements 

d. Ellipticity: No requirements 

2. PLANE CHANGE: None 

3. ALTITUDE CHANGE: None 

4. TIME ON ORBIT: Days 

5. TEST DURATION: Days 

6. TOTAL NUMBER OF TESTS: Depends on test duration 

7. TEST FREQUENCY: Approximately 4/day 

8. INTERVAL BETWEEN TESTS: Approximately 6 hours 

9. CREW TASK LOADS - man hours: Approximately 5 minutes/day 

10. CREW TASK FREQUENCY: Approximately-4/day 

11. FIELD OF VIEW REQUIREMENTS: No requirements 

12. GROUND CONTROL LIAISON DURATION: None 

13. GROUND CONTROL LIAISON FREQUENCY: None 

14. EXTERNAL TEST ITEMS: 

a. launched from Station: None 

b. launched from resupply: None 

c. launched from ground: On MOL 

A-193 
ROVED FOR 

1 JULY 2015 

15. QUALIFICATION TESTS (other than space): None 

a. Ground: None 

b. Atmosphere: None 

16. SEQUENCE OF EVENTS AS THEY OCCUR DURING FLIGHT: Read dose and dose 

rate displayed on monitor and record with time 

17. HANDLING PROCEDURES: Select calibration and operation.check mode of 

monitor (switch operation) and correct changes by front panel controls 

(See Sec. V.b.(1).) 

A - 1 9 4 
OVED FOR 

1 JULY 2015 

ATTACHMENT G 

DEVELOPMENT CHARACTERISTICS 

1. 

2. 

Standard 

Dosimeters Emulsion 

Heavy 

Particle 

Dosimeter 

DEVELOPMENT TIME None 

FINAL DEFINITIVE TEST DESIGN 6 months 

TIME 

None 

6 months 

9 months 

1 year 

3. NUMBER OF TESTS REQUIRED 2 2 2 

4. TYPE OF DEVELOPMENT TEST ITEMS None None None 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME None None None 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test 

b. Balloon Flights 

c. Space Test 

7. DATA AVAILABLE FOR TESTS 1965 1965 1965 

8. CURRENT DEVELOPMENT STATUS 

a. Proposed only no no yes 

b. Test item under study yes yes no 

c. Funds expended to date none 5 K none 

A-183 
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A- 19 5 
OVED FOR 

1 JULY 2015 

ATTACHMENT E 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required: 

(1) Man's function 

(a) As part of test: Yes (See See. V.b.(1).) 

(b) As technician conducting• test: Yes (See Sec. V.b.(1).) 

b. Crew Sall Requirements: See Secs. V.b.(1) and V.d.(1). 

c. Manpower Profile: See Secs. V.b.(1) and V.d.(1). 

d. Critical Functions: See Secs. V.b.(1) and V.d.(1). 

e. Work Positions: In MOL 

f. Time Controlled Tasks: Yes (See Sec. V.b.(1).) 

g. Human Performance Measurements: Yes (See Sec. V.b.(1).) 

h. Physiological and Psychological Measures: None 

i. Selection Factors: See Sec. V.d.(1). 

j. Training Requirements: See Sec. V.d.(1). 

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 

A-196 
OR 

ULY 2015 

2. GROUND PERSONNEL (Contd) 

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 

A-197 
OVED FOR 

1 JULY 2015 

ATTACHMENT F 

COMMUNICATIONS AND DATA HANDLING 

1. DATA HANDLING: ON-BOARD 

a. Functions to be measured (Categories of data, i.e., sensor data) 

(1) Data rate/frequency response: Approximately 4 readings/day 

Volume of Data: 2 data points/reading 

Accuracy required: See Sec. V.b.(1). 

(2) Form of data - analog/digital - output of transducer: Meter 

and register reading 

(3) On-board processing - human judgment - computer - data 

reduction: record data only 

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

raw/processed - permissible Ways: None 

b. Requirements for Processing and Analysis 

(1) Data reduction - data editing - data compression: No 

(2) Computation: No 

(3) Evaluation: No 

(4) Pictorial analysis: No 

(5) Real-time monitoring: Yes 

(6) Displays: Yes 

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

(1) Photographic (or other pictorial records): Yes, data log 

(2) Magnetic tape recording - analog/digital: No 

2. COMMUNICATION REQUIREMENTS 

a. Data Transmission to ground: No 

b. TWo-way communication data feedback from ground: No 

A-198 
(1) Data processing on ground 

(2) Allowable delve. 

(3) Ground transmission (one center to another) 

(4) Accuracies 

(5) Data Recording 

(6) Security - Crypto 

a• 

A-199 
PPROVED FOR 

ASE 1 JULY 2015 

--....■•••■•••••■=s01•11.1111- 

ATTACHMENT G 

DEVELOPMENT CHARACTERISTICS 

1. DEVELOPMENT TIME: Approximately 4 months 

2. FINAL DEFINITIVE TEST DESIGN TIME: Approximately 4 months 

3. NUMBER OF GROUND OR FLIGHT TESTS REQUIRED: One (See Sec. VI.b. 

4. TYPE OF DEVELOPMENT TEST ITEMS 

a. Vacuum Chamber: Yes 

b. Shaker: Yes 

c. Thermal: Yes 

d. Acoustic: No 

e. Simulators: Yes 

f. Aircraft: No 

5. SUPPORT EQUIPMENT DEVELOPMENT TIME: None 

6. NUMBER OF TEST ARTICLES REQUIRED FOR: 

a. Ground Test: One 

b. Atmospheric Test: None 

c. Space Test: One 

7. DATE AVAILABLE FOR TESTS: Approximately June 1965 

8. CURRENT DEVELOPMENT STATUS 

a. Proposed only: Yes 

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

breadboard stage, etc.: No 

c. Funds expended to date: None 

A- 200 
19 

Title of Exeriment. Orbital Plasmas Characteristics 

I. TestOblec5ve: Tha experiment would determine the size and characteristia—a filistias which attend orbital vehicles. The results will aid in 

development of improved radio detection devices for orbiting, suborbiting 

and space probe vehicles. 

II. Importance of Test: The experiment is required to develop methods of 

deteciing -oltifirg7Sittorbiting and space probe vehicles. The experiment 

rust be conducted in space since such plasmas exist only in space. They 

must be studied in MOL since no other method of obtaining the required detailed knowledge is known to exist, Knowledge is required to assess man's 

ability and utility in space, as well as to obtain information essential to 

the understanding and design of electromagnetic transmitters and receivers. 

III. DesElplion of thaxperiment: 

(1) The first part of the experiment consists of irradiating the plasma 

with beamed rf energy from a steorable antenna on MOL and observing the 

scattered radiation at ground stations. The direction and frequency of the 

beams are to be controlled from MOL, successive measurements to be based on 

results of previous measurements. 

a. Configuration of Test Items 

Key characteristics on MOL are steerable external antennas 

and tuneable rf energy sources, 200 lbs., S cu. ft. 

b, BILE222a1321Ernt Begged 

(1) Spacecraft - Scatter receiver, 50 lbs., 2 cu. ft. 

(2) AGE - Existing receiver sites 

c, Test Procedure 

(1) Necessary to select antenna directions and frequencies, 

to be selected by astronaut as experiment proceeds. 

(2) The astronaut will steer antennas and change frequencies 

to optimize scattering, thus determining spatial and electrical character.- 

istics of the plasma. 

(3) Try various antenna directions and frequencies to obtain 

scatter magnitude as function of variables. 

(2) The second part of the experiment consists of exciting the plasma 

to resonance, the exciting frequency, the coupler loading and the radiation 

pattern providing the required plasma characteristics. 

A-201 
APPROVED FOR 

EASE 1 JULY 2015 

a, Configuration of Test Iteys gmossaLsar.acar..mr&arawrorzstens.namaraarammaew 

Characteristics on MOL are extendable antennas for coupling 

to plasma and tuneable rf energy sources, 400 lbs., 5 cu. ft. Antennas 

of considerable length are expected to be required for the desired 

excitation. Lengths of the order of miles to tens of miles are envisioned 

for the early experiments. Later experiments may use much longer antennas. 

b. Test Sup ort Re uirect 

(1) Spacecraft - Antenna impedance measurement equipment. 

(2) AGE - Existing receiver sites 

c. Test Procedure 

Adjust antenna length and direction. For each case tune 

couplers for maximum loading. 

(1) Man's role - Select antenna adjustment, exciting 

frequency and adjust loading to optimize plasma excitation. 

(2) Success of experiment depends on his ability to observe 

results, then make successive studies to optimize excitation for various 

altitudes and directions. 

(3) Continuing adjustment of parameters to determine plasma 

characteristics. 

d. Category of Experiment - b 

e. Cost FY65 FY66 FY67 FY68 FY69 TOTAL 

(1) Engr. g Devel. SOK 100K 25K 25K 25K 225K 

(2) Installation SOK 50K 50K 50K 200K 

(3) Ground Support 75K 75K 75K 225K 

Total 50K 150K 150K 150K 150K 650K 

f, Schedule 

(1) Available for test - FY67 

(2) Flight readiness date - FY68 

IV, Participating Government Agencies: Sponsor - NAVY 

Test Equipment Acquisition: Navy and contractor 

V. Additional Requirements 

a. Special Security - Routine 

A-202 
LY 2015 

b, Manning Deariaton Summart- One scientist, 2 hrs/day in MOL; 

one soionT51it each ground AliEron position manned during MOL passage. 

c. leatics: CY64 CY65 CY66 TOTAL 

(1) Manpower 

(2) Hardware Development 

(3) Installation 

(4) Operation 

(5) Additional Support 

TOTAL 

d. Facili 

4101•0.1M1MNIMAIli 

ties 

1.111 

Ground Facilities - Existing - need additional receivers and 

recorders at some bases. No special facilities before flight. 

e. linalajimaryrainin 

(1) Technician or scientist with training in use of scatter 

experiments. Six months to one year training required if not experienced 

in scatter experiments and equipment. 

(2) Ground personnel - similar to above. 

(3) Tunable energy generators, steerable antennas, receivers 

and recorders. 

VI, General 

a, .....asEti_ Comennons andDataHandlinRuirement ILM,....

Communication link to ground stations required to coordinate 

frequency tuning and antenna steering. MOL data relayed to ground for 

analysis. 

b. Development Characteristics 

Proposed only. Uses commercial equipment mainly. 

A-203 
E 1 JULY 2015 

A-204 

DESIGN aIARACCERISTICS TEST EQUIPMENT 

10 EQUIPMENT REQUIRED FOR TEST 

RF energy source, steerable antennas, receiver and recorder 

2. WaGHT: 20D lbs. total 

3. VOLUW: Stored S cu.ft, In use S cuoft. 

4. POWER: 

a. Continuous - None 

b., Stand-by - None 

c. Average operating - 500 w 

d. Peak - SOO w 

Duty cycle - 2 hrs/day 

S. SPARES: 

a, Volume - 0.5 cu.ft, 

b. Quantity - 1 box 

c. Weight - 20 lbs. 

6. TOOLS: 

a. Volume - 0.1 cu.ft. 

b. Quantity - 1 set 

c. Weight - 5 lbs. 

d. Power - None 

7, HEAT OUTPUT - 450 W 

8, STABILITY - Excellent 

9, VIBRATION LIMITS - Normal for electronic equipment 

10, SHOCK LIMITS - Normal for electronic equipment 

11. HAZARDS - Electrical - negligible 

12. TEMPERATURE LIMITATIONS - Normal 

13, TYPE AND RANGE OF MEASUREMENT - RF frequency, received energy level, 

antenna direction 

14, SPECIAL ENVIRONMENTAL REQUIREMENTS - None 

IS. ORIENTATION AND POSITION ACCURACY REQUIREMENTS: S degrees, 10% 
1 JULY 2015 

160 EQUIPMENT OPERATING CYCLE • Ten minutes when over ground stations 

17, EQUIPMENT LOCATION REQUIREMENTS - External steerable antennas 

18. SPECIAL MOUNTINGS REQUIREMENTS Antennas, steerable 

19. PRESSURE VESSELS - None 

20. ELECTROMAGNETIC INTERFERENCE - Needs investigation for possible 

interference with or from other electronic equipment 

216 NAINTEnANCE REQUIREMENTS - Negligible. 

A-205 
TOT 

175 

ISO 

200 

0 

75K 

SO 

0 

6S0K' 

A- 206 

1 JULY 2015 

FUNDING SUMMARY 

BUDGET REQUIREMENTS EY FISCAL YEAR 

FY 65 FY 66 FY 67 FY 68 FY 69 

Engineering, Developmental 

Environmental Testing 50K 100K 25K 0 0 

Integration 4 Installation 0 0 SOK SOK SOK 

AGE 0 SOK SOK SOK SOK 

Simulators/Trainers 0 0 0 0 0 

Data Reduction 0 0 2SK 25K 25K 

Equipment Rework 0 0 0 25K 25K 

Other 0 0 0 0 0 

TOTAL 50K ISOK 150K 150K 150K 
)K 

iK 

JULY 2015 

20 

I. Test Oective: The purpose of this experiment is to study the plasma 

envircniontin the vicinity of MOL. Information obtained here has a direct 

bearing on the operation of all electromagnetic equipment on MOL having to 

do with transmission and reception of signals as well as the detectability 

of MOL by radar. 

II. Im ortance of Test: These experiments are required so that a knowledge 

of the environment o - IOL can be obtained which will provide information to 

be used in the design of electromagnetic equipment aboard the vessel. 

Specifically how the plasma sheath around the craft affects the design and 

operation of antennae (especially V.L.F.), as well as the radar cross-section. 

Such experiments can only be carried out in space where the proper plasma 

conditions exist on a sufficiently large scale. A study of the plasma state 

near MOL is essential to provide a working knowledge of the conditions of the 

environment in which man must live and work. 

The observations to be determined and recorded in these experiments are 

related in a great degree to phenomena of extraterrestrial origin. Because 

of this there is uncertainty in the nature of physical conditions attending 

planned observations. It is considered that the timeliness of personal 

observation, initiative and interpretation on the part of the astronaut 

will contribute significantly to the value and success of the experiments. 

Since the astronaut in general will be moving at a rate of approximately 

300 miles a minute and traversing a changing magneto-ionic medium, it is 

apparent that the judgment and skill of the astronaut would make a 

contribution to the experiment that could not be achieved without his 

help. 

The course of future similar and related experiments might be best 

determined and accomplished by other means only as a result of the flexibility provided by the astronaut in these initial MOL experiments. 

III. ......_2 DescritiorieEeriment: ..... of ....E_ The detailed experimental program is: 

(1) To study the electron energy distribution in the plasma surrounding 

the MOL. 

(2) To determine the electron and ion densities in the plasma. 

(3) To relate the above factors to the propagation and reception 

of electromagnetic waves. 

(4) To study the formation and size of the plasma sheath around MOL 

and determine how this affects (if any) the currents flowing in the MOL as 

well as in the medium and the ability of the astronauts to leave the MOL. 

A-207 
EASE 1 JULY 2015 

(5) Correlate the data with radar ground stations and NAVSPASUR to 

determine the effective radar cross-section of MOL. 

a. Configuration of Test Items 

Retractable probes will be placed at (5) different equispaced 

positions from nose to tail of the craft. Each probe will be generally of, 

the Langmuir type and designed so that its direction relative to MOL can be 

varied (20-160°) and extended to 100 meters from the craft. A multichannel 

recording electrometer will be required on board the NOL so that simultane 

recordings of the probe currents may be obtained. 

b. lestimoripment Required 

None 

A-208 
D FOR 

JULY 2015 

c. Procedure 

When the MOL is in position to allow experiments to be perfumed, 

the probes will be extended a given distance and sit at a prescribed angle. 

Reccr6ings then will be made of probe currents as a function of probe voltage. 

Such observations will be repeated for different probe lengths at the Same 

angle. After a complete set of observations are made for one probe angle 

another may be chosen and the experiments repeated. All observations should 

be done as near to one point in space as possible as the plasma conditions 

may change as a function of position and time. 

(1) Man is essential to a proper functioning of the experiments. • 

as a judgment must be made as to when or (or determined by sampling) how 

. much data should be taken. 

(2) Experiments will be essentially manual and require the complete 

attention of one astronaut at a time. 

d. Category of Experiment 

(1) Category (b). 

e. Cost 

FY 6S FY 66 FY 67 FY 68 ' FY 69 

100K 200K - mot igoic SOK 

er Sch

b ‘00 M 

f, Schedule 

available as yet. 

tV Particlatins_Government Agencies: Sponsor - 

V. Additional ReguiTements: 

a. Security: No special security. 

b. Manning Summary: See attached sheet. 

A-209 
PPROVED FOR 

SE 1 JULY 2015 

MANNING DESCRIPTION 

1. ASTRONAUTS 

a. Number required: one 

(1) Man's function: As technician conducting test. 

b. Crew skill requirements 

Some briefing will be required to acquaint the astronaut with the 

objectives of the experiment, A brief training period of an hour should 

be all that is required to provide sufficient information to the astronaut 

to operate the equipment. 

c. Manpower profile 

It is expected that approximately the full time of an astronaut for 

two complete orbits should be sufficient time to complete the experiments. 

d. Training requirements 

See (b) above. 

2. GROUND PERSONNEL 

a, Number required: 2 - 3 

(1) Man's function: To set up and test equipment. 

b. Crew skill requirements 

Crew must have intimate knowledge of equipment. 

c. Manpower profile 

It is expected that the crew will be required 6 weeks before shot 

time to finish installation, and do checkout experiments. 

d. Training Requirements 

Technicians from Laboratory will be sent to install and test apparatus. 

A- 2 1 0 
A-211 

ATTAQIMENT A 

DESIGN CHARACTERISTICS TEST EQUIPMENT 

1. Langmuir probe equipment 

2. 10 lbs. 

3. Vol. 1 cu, ft. 

4. Power: 25 watts continuous 

5, Spares: None 

6, Tools: Usual 

7, Heat Output: 25 watts 

8. Stability: Normal 

9, Vibration Limits: Normal 

10, Shock Limits: Normal 

11, HazArds: Usual for electronic equipment, 
21 

PROPOSAL FOR AIRGLOW HORIZON PHOTOGRAPHY FROM 

THE MANNED ORBITING LABORATORY 

by the 

E. 0. II ulburt Center for Space Research 

U. S. Naval Research Laboratory 

Washington, D. C. , 20390 

I. Teat Objective 

It is necJasary to have a knowledge of the altitudes at which the various 

night airglow emissions occur in order to interpret the photochemical processes that take place in the upper atmosphere. These emissions have such 

very low energy that measurements of their altitude distribution made with 

adequate spectral resolution haw, hitherto been impossible. The color 

photographs of the nightglow horizon obtained by Astronaut Cooper aboard the 

MA-9 Mercury capsule, however, established the feasibility of making spectral 

nightglow measurements from man-pointed space vehicles. 

Nightglow distributions of intensity with altitude will contribute greatly to 

the aeronomical investigation of the upper atmosphere and a comprehensive 

group of global measurements will reveal any variations that may be associated 

with latitude, longitude, or season. 

2. Importance of the Test 

The proposed measurements of nightglow altitudes are needed to provide 

for the benefit of prospective space travelers information about the character 

and variability of the nightglow background over the earth and in as large a 

A-212 
1 JULY 2015 

wavelength range as practicable, especially in the spectral regions inaccessible 

from the ground because of atmospheric absorptions. Further, such data are 

needed to evaluate the feasibility of the scheme to use the nightglow horizons 

as spatial references for nighttime navigation for man and missiles. 

It is only from a man-directed space vehicle such as the Manned Orbiting 

Laboratory that the high resolution spectrographs required for the task can be 

pointed at the nightglow horizons for time intervals long enough to give adequate 

observations. Attempts to do this job from rockets have failed for lack of 

adequate means for pointing the instruments in the proper direction for long 

enough periods of time. This experiment is one of those that appears possible 

only when performed in a manned space vehicle. 

3. Description of the Experiment 

The airgiow horizon as seen from an orbiting spacecraft appears as a 

thin line some 6 degrees skyward from the earth horizon. It is proposed 

to use a high speed camera fitted with a grating in front of the lens to form 

an objective spectrograph. The thin line of the nightglow horizon would serve 

as the spectrograph slit and as such will be imaged as a spectrum according 

to the emission lines or bands present. If all the emissions originated at the 

same altitude this "spectrum" would fall accurately on the dispersion curve 

of the instrument. Departures of the images from this normal dispersion 

curve would then be a measure of the relative altitudes of the emission. 

The overall dimensions of the spectrograph camera would be approximately 

x 3" x 4" and the total weight could be kept under 15 pounds. Only an 

A-213 
PROVED FOR 

E 1 JULY 2015 

accurate description of space available could permit more accurate specifications. Exposure times of 2 minutes or so would be controlled by a 

photoelectric exposure meter if space permits. It is contemplated that the 

astronaut would point the camera out his viewing window while the pilot kept 

the spacecraft pointed accurately► and steadily at the visible nightglow horizon, 

A quick exchange film cassette would be used for 20 to 30 exposures, or 

more if schedules and weight permit. About 300 mw of power would be 

needed only during actual pointing of the camera and operation of the shutter. 

A- 2 14 
LY 2015 

22 

(7,:r:rrAn rlso.,vati,mas Aboard thc 

Fr:7=d rrbial Laboratory (MM) 

Cocr,l.c Pay Branch, Pecleonics Divis:7.on 

3. Naval Research Laboratory 

ScientificOblectivez: 

(1) To Inve,:tiss',0 cc-:paz.itfLor, flux, and enersy spectra of the 

nucleonic contonena c the Irrtary coszic radlati(*n ontside of the earth's 

absorbins 

(2) To str.dy the prire.ry y--ay and electron components of the primary 

radiation al-Nxt vbieh linle Is n;:w • knT.:P. Directional investigation.:3 of 

y- rays (i.e., "311,ray a:trtr) will be )?.1xsucd, extltiting the aazistance 

of astronauts (cf, belo-7) • 

()) It is planned to tzlze the foraux4 ng observations as a function of 

time, and in 7.artieul4-c ti M the solar cycle. 

(lb) Uhile pumling the =In rnsrans above, thr physicists will, of course, 

be scarchirv, for rare rarticies and other novel phenomena that might conceivably apnear in the detectors wins to the absence of an air blanket or other 

overlying absorber, 

• 

(5) Some of the contemplateel exi.lerimental set-ups will permit the study 

of high-energy particles cf solar origin, expecially during solar flares. 

XT. Tmoortance cf :'1 ,TgreTi• 

The cosmic-ray compos:tion Jell outside the earth's atmt,sphere is 

deduced, at present, mainly by extraiclatton. Yet it is that composition 

which is most relevant to Iroblems in space science And astrophysids. 

A-215 
ROVED FOR 

E 1 JULY 2015 

-orif'-'v cosmic radiation in deal. 

(a) to a,17...- Pc er:;nion^t1r c7:1! .f this irrnrtant phenomenon in 

('.)) to cite rr:zrzoe s? astronauts in MOL for nanual assi 

:r.se In ex:InTj"Iellts extremel7 difficult tlthout the presence of 

Ten. 'Me tc is Ilsed advisrAly, for the plan centemplates the pert 

of several closely relea ar9el'in,

lts which will complement each other and 

enhance the re2iability of measul-c7ents made in each. 

Deser-.ion of the Ex-sc.:rent 

It is intendod to cmplcy .sverl methods of detection: nuclear resear 

emulsions, several types of countsrs, ant spark chsrbers. 

A sehematc tabulation of the experimental program is shown below: 

i

------..............------------,,------- 

i 

Detection by 

Subject 

o 

Dtect:Len by f Sxylariment e Nuclear Research 

■ Counters i Emulsions 

_........- , ....x......... 

Pr4r.ry Coric Rar. rdclei 

(Especially 2;:-;: 2) 

(Solar Partielee as yell) 

y-Pys and 1Tlectons 

7-ray astronomy 

a 

1 

i 

CereMkov 1 i Said State $ 

Scintillation 1 

Snark Chsubers •_ 

Application of 

latent techniques 

and development of 

new techniques 

including chemical 

processing in space 

• 

• • • • b. • 11 • NM IP. • • • .1 'MP • • • • • • •••■■■■••••••••■••••■•■••• 

••■••••■•■••111111.1■10.01111100•••■••■•••••■•••=•••■■•■•••■•••■•••••■ 

(a) Configuration o.falnmratus 

See Atch A. The resuirements for each of the three parts in this 

program are listed in separate columns on each attachment sheet, where 

necessary. 

A-216 
sear 

LY 2015 

(b) :oment Required 

Sec Atch B. 

(c) ncurimental Procedure 

Since our intention is to Neat least two different systems for 

detection, the operation CP each will be described separately. 

1. Detection with nualearresearch emulsions would require the astronaut to place e. package containing the emulsions outside the MOL on 

a boom which he would erect. The package would weigh 10.20 lbs.end 

would remain outside for times ranging up to several days, depending 

on the exneriment. It could be brought up to. the MOL by "ferry" and. 

returned the same way, after exposure. Its recovery is essential 

since nuclear research emulsions must be 'proceseed and then examined 

under a microscope to find the tracks produced by charged particles. 

Another extremely helpful intervention by astronauts would be the 

chemical processing of nuclear emulsion aboard the Nagwhich would 

restrict the prohibitive background of tracks that now makes it 

almost impossible to detect primary electrons or gamma rays with 

this useful detector. 

2. Detection with counters and spark chadbers ,:could most likely 

require these apparatuses to be in place on the MCI: when launched 

and to be placed into operation by the astronaut when a successful orbit 

has been aehieved. tate. could be telemetcred from counterz, but cameras 

will probably be required to photograph the spark chambee. Verieun 

A-217 
PPROVED FOR 

SE 1 JULY 2015 

servicing oparations would be required of thenstronaut such as changing film in the cameras.. Emergency in-flight repairs could alao be 

accomplished by him. Bee Atch C. 

d. Category of Experiment 

Category (1). These experiments would contribute directly to MOL 

program objectives through their need for and critical utilization 

of the astronaut's services. Among the requirements thereby imposed 

on the design characteristics of the MOL are the following: 

(1) An air lock to permit extension of apparatus on a boom 

outside of the vehicle. 

(2) Provision of a "dark-room" or dark,dcheMber space of about 

1 cubic foot for chemical processing of nuclear research emulsions. 

This requirement - while highly desirable - may be considered 

marginal. 

e. Cost 

See Atch D. 

f. Schedule 

(1) Facilities now in existence at NRL or under development 

could provide hardware and software for this program. 

(2) Same as (1). 

N. ParticiGovernment Agencies 

Sponsor: Office of Naval Research. 

Scientific Equipment Acquisition: U.S. Naval Research labors-Wry. 

A-218 
15 

Additional Requirements 

a. Special Security 

Strict environmental control on ground before launching apparatus 

either on MDL or on "ferry", . 

b. Manning Description Summary 

See Atch E. 

c. It is not clear to us that information is sought here. We shall 

try to find out, and then supply the required data. 

d. Facilities 

Existing facilities will be used for construction and pre-flight 

testing of equipment. 

e. Simulation and Traininii 

(1) Astronaut: 

(a) Emulsion experiments: Astronaut would, on occasion, 

follow prescribed mechanical and chemical procedures at the 

level of a technician. Approximately 4o hours of training 

would be required. 

(b) Electronic experiments: Astronaut would, on occasion, follow 

prescribed mechanical and electronic chedk-,out procedures. 

Some detailed knowledge of the apparatus and its workings would 

be required at the level of an electronic engineer: Approximately 100 hours of training would be required. 

A-219 
PROVED FOR 

1 JULY 2015 

e. continued ... 

(2) Ground Personnel 

(a) Emulsion experiments: No training requirements. 

(b) Electronic experiments: Personnel trained to handle 

communication-receiving equipment. Approximately 40 hours 

of technician-level training would be required. 

(5) Equipment 

No additional equipment requirements. 

VI. General 

a. Communication and Data Handling Requirement: See Atch F. 

b. Development Characteristics: See Atch a, 

A&Litional background information on this proposal and 

on the Cosmic Ray Branch can be found in the attached 

preliminary version of this pruposal. 

--••■ 

Maurice M. Ohapiro 

Principal Investigator 

A-220 
ATTACHMENT A 

DESIGN CHARACTINGSTICS TEST EQUIPMENT 

1. EQUIPMENT TO BE TASTED ANULSION 

ADNIICAL 

PROCESSING SECTRONIC 

Coreakov Spark 

Saint. Cbambe: 

P. MONT 20 lb 30 lb LA.* B.A. 

3. VOLUME: 

Stored: 1 its 1 re ire 1 Its 

In Use: 1 re 1 re 2 ft3 lo re 

CRITICAL DIMENSION - SHAPES N.A. N.A. 

4. POWER 

a. Continuous 

b. etand-by 

c. Average operating 

d. Peak 

e. Duty cycle 

m 0.1 v 

continuous 

N.A. 

5. SPARES 

a. Volume 

b. Quantity 

c. Weight 

NONE 

It 

NONE B.A. 

S. TOOLS 

a. Volume 

b. Quantity 

c. Weight 

d. Power 

. BEAT =PUT 

. STABILITY 

a. Moving parte 

. VIBRATION UNITS 

*A.A. m Act Available 

NONE 

A-221 
OVED FOR 

1 JULY 2015 

EMVLSJOU 

CLEMI(Al. 

PN103faSEA, WU:Mtn 

10 IA. 4r )01;)iS N.A. N.A. N.A. 

13. 11,5ZWW: (fir% explen, electr.l.c%1, 

-Oxirs: oth.:,..r; - • . 

NONE NONE h 

Wm, Wane 

12. TDIPERATtrfa reIRTATIONS Mict- 15'-'1' 68nr 

3.3. TYPE AND RANGE 7 MEASUREMENI NONE Temp. a 

(definition of p.cr.vneters tc' be 

measured while tent is unig:may, . 

14, SPECIAL EtIVIRMTENTAL RIV.CIRMENIS Avoid 

Raclioactiv. 

Avoid 

Badivactiv. 

Avoid 

Radicactiv 

15. ORTENTATYON An r3SIT301I ACCURACY 

RECI-JIRDIENT-S: 

Station 

Equipment 

Various 

t 30' to t 5° 

NON N.A. 

ft 

• Depending 

on exp. 

16. KGIDIENT OPERATING CxCLE 

Frequency continurius 1.2 continuous 

Time Duration 11 1-2 hrs 

17. ErgoaDKur 111CATION REQUIREWRIS Outside Inside Outside 

Vehicle Vehicle Vehicle 

18. SPEtlIAL WONTING REON:I.NDIENTS 

19. 

20. 

21. 

Apertures 

Booms 

Windows 

Antennae 

Bracketry 

PRESSURE VESSELS - fluids: gasses, 

etc. 

EIJLCTRO MAGNETIC :OM:MERE:1U 

(spurious generation; sp,?ci%1 thtelitlug 

requirements: etc.) 

MADTMANCE RETARDENTS 

Ground 

Space 

1 ft2 

10 ft 

NONE 

0 

)1S 

NONE 

See 3.2 

See 12 

NONE 

0 

0 

0 

0 

Fluids 

NONE 

NONE 

See 12 

N.A. 

II 

ft 

ft 

N.,A. 

0 

'7. 

A-222 

2. " 
ATTACIIMENIE 

TEST SUPPORT EQUIPYSNT 

CHEMICAL 

INULSION PAOCESEINO ELECTRONIC 

1. RECORDING MEDIA 

a. Tape NONE NOME TES 

b. Film Nuclear 

Emulates 

2. BANDUNG (special eqvlpm rt required 

to handle items being tested). 

11 n 

3. PACKAGING w n 

4. CALIBRATION - alignmen, deployment YES If 

5. MS AND mutt= NONE 0 

6. NUMBER OP LEADS FROM mann TO w 11 

INSIDE STATION 

7. SENSORS (TRANSDUCER - OUTPUT MEALS) w II 

8. TRAINIRS/SIMEILATORS n n 

9. INSTRUMENTATION - cockpit and/or laboratory " YES 

(note effect of time 

sharing instruments with 

other experiments). 

- 

c. Other NONE NONE Telemeter 

NONE 

TES 

N.A. 

w 

el 

n 

YES 

10. REIATED SUPPORT PQM:MT 

a. Targets NONE NONE 

b. Ground Stations 31 YES 

C. Tracking XI'S NONE 

d. Handling Equipment "11DMV" "T.ERRY" 

11. AGE 

12. ENVIRONMERTALTEST EQUIPMENT NMS NONE 

13. FACILITIES 

NONE 

YES 

it 

A-223 
Ear:15)1m 

10c1: 20C mil* 

Close to Equato 

and Polar 

Over Solar Cy 

Circular 

raltz 

DAIS 

312 bre 

Several 

Continuous 

One/Plight 

1 man hr/day 

. 2-4 4peratima 

intervals/day 

2 i Golid &Os 

Intermittent 

NO 

Yes, on MX 

• 

10. 

11. 

CREW TAM PRIEPARKIX - 2 operatin, g

intermlnpark. 

nab or vxzwisouravorrrs 2 t Solid Angle 

3-4 operating 

Intervale 

son 

12. GROUND CONTROL LIAISON EOM 101.1E 

DURATION 

13. MOUND CONTROL LIAESON 

ISIQUINCY 

14. INTRIZAL 73ST INNS: 

a. launched from Station NO NO 

b. launched from resupply M 

c. launched from gt-ound Yes, as tat 

or "Perm" 

Tesson AOL 

16. QUALIFICATION TEM (other 

than space: 

e.. Ground 

. Mmespherts 

PROVED FOR 

E 1 JULY 2015 

1. 

TEST OPERATING CHARACTERISTICS 

CHEKICAL 

PALS'ION PROaSSING 

ORBITAL PARANSTERR (desirt-d) 

a. Altitude 100-200 nu IA ti rt 

t?equ+.tersentt: 

h. Inclination Cleac •to Equatorial • 

and Raer 

• 

es Epoch Over Solar Cycle 

• d. Cixcular 

2. PLANS ORANGE NONE 

3. ALTITUDE CROW 

Tna ON ORBIT DAYS n 

5. Tiff DIIRATICff 12 hr.46 hr . 1-2 bra 

6. !OPAL NORM OP TESTS Several Several. 

7. no ramtnalcy Continuous Once/Flight 

8. /NTSINAL BIM= TINS One /14onth 

). MI TASK WADS - man bourn . 1 man hr 1 man hr 

A-224 
2015 

Chemical 

Emulsion frocessina Electronics! 

(a) Initiating (a) Xnstell 

operation emulsions 

(b) Attach to (b) Developer 

boom operation 

(c) Extend (c) Shut down 

boom operation 

16. Sequence of events as they 

occur during flight 

17. Eandlina Procedures 

(e) Retract 

boom 

Cr) Shut do= 

operation 

Included under 

16(a) and 16(f) 

Details N.A. 

Xncluded under 

16(a) and 16(c) 

Details N.A. 

(d) Exposure 

internal 

A..225 

ATrACRMENT 

MANNIIU DESCRIPTION 

1. ASTRONAVIS 

a. VuOer required 1 

(1) Man's function 

(a) Ac part of test. WIXOM 

(b) As technician conducting test Yee 

b: Crew skill requirements See V(e) 

c. Manpower Profile . 

d. Critical INactions 

e. Work Positions Infor out of JCL 

f. Time Controlled Tasks Yes 

g. Human Performance Measures None 

h. Phyaiological and Psychological Measures 

I. Selection Factors See V(e) 

Training Requirements tt 

2. GROUND PERSONNEL 

a. (umber required::EMulsion Exp. - 1; Chem. Process. y 0; Electronic 

(1) Man's function 

(a) Aa part of test Yes 

(b) As technician conducting test It 

b. Creu Skill Requirements See V(e) 

c. Manpower Profile 

d. Critical Functions 

e. Work Positions At Voice Comm. Center 

to advise Astronaut 

f. Time Controlled Tasks Yes 

g. Human Performance Measures None 

h. Physiological and Psychological Measures 

i. Selection Factors See V(e) 

A '1 •/ 
PROVED FOR 

E 1 JULY 2015 

ATTACSIENT 

CONEREECA.TIONS AND Ian NUDISM 

Electronic En). only 

1. DATA I= 

2. POTIONS TO BE MEASURED 

3. WM OF ANAL! ]8 REQUIRED 

PXCTORXAL DATA =VIM 

5. REAL TIME maw= 103QUIR4ENTIR 

6. DATA =ISM OR OWNERS:EON 

7. READ-OUT TD1E 

8. NEQUIREKIESTS FOR MEAN= DATA MOMS 

9. MANUAL AND/OR AUTOMATIC CONTROL 

10. SIMULLEARIEETY 

U. =CUED -001114A1WS REQUIRED 

1000/21n. 

Voltage pulse 

N. A. 

Oeoiuoaccpe-type photography 

Yes 

Probably compression 

• L A.

• Yes 

Manualfor Automatic 

Yes, for in-flight repairs 

A-228 
DEtrp.LOTMMT CiihrA.CTER!*.S.17.1:CS 

'eem. 

Emulniat Frocnsim Electronic 

1. DEk'EL-TITY.T ToT, None - 6 mo. 1 '. 1 yr. 

2. privAL D.77757-VvE 7:77.;7 r7s-ro ,T..17.0 

3.. Mir= OF INCIND CF. 77.17.f.r17.;:' 'MT'S TITTALIIFED 

4. rim r? 1:ErrEtt.''Fr1777 sTY,ST -,7/rMI3 

a- Vactatm Chember Yes No Yes 

b. Shaker 0 Yes It 

c. Thermal n No il 

L. Acoustic No n to 

e. Simulators n n n 

f. Aircratt tt n n 

5. SUPP072 rarcnean, IMEEOPFLUNT MS None None . I yr. 

6. NUMBER OF Ism,lartetzs mum roR: 

a. Ground Test - 2 . 1 . 4 

b. Atmospheric Test - balloon flights - 2 

..... 

., 4 

c. Space Test .. 2 e. 1 r. 4 

7. LATE AVAILABLE FOR TrsTs 1965 1965 1966 

8. CURRENT DEVELOMENT STATUS 

a. Proposed only No Yes Yes 

b. Project or program is approved and test Yes No No 

item is under study - breadboard stage, etc. 

C. Funds expended to date. 51( None None 

6 mc. - 6 mo. - 1 yr. 

. 4 

A-229 
• A- 230 

PPROVED FOR 

SE 1 JULY 2015 

Prelleinary Draft of 

Froposel for Cosmic Ray Observations AIcard the 

Z' fined Orbiting Laboratory (NOL) 

Cosmic Ray Breech, Nucleonics Division 

U., S. Naval Research Laboratory 

This is a preLiminary proposal for a 8r20.08. of observations on the 

pr nary co chic radiation designed (a) to advance significantly our knowledge of this iml;ertant phenomenon in space, and (b) to take advantage 

of the presen.e of astronauts in MOL for manual assistance in experiments 

that would be extremely difficult without the presence of men,. The time 

required for assistance by the astronaut will be minimal, but the nature 

of the help will in some instances be crucial. The term aroextuais used 

advisedly, for the plan contemplates the performance of several closely 

related experiments which will eomplement each other and greatly enhance 

the reliability of the measurements made iu each. It is intended to employ 

several methods of detection: nuclear research emulsions, several types 

of counters, and spark chambers. 

For 15 years, the Cosmic Ray Breath of the U. S= Naval Research Laboratory has been investigating various phenomena in the cosmic radiation, 

During the past decade, the emphasis has been on the composition of the 

primary radiation, together with related questions such as its energy 

spectra. Particular attention has been devoted to the heavy primary nuclei 

of the cosmic radiation (whose biological effects on man in space are as 

yet incompletely evaluated), and vital contributions have been made to our 

knowledge of this component and of primary helium, During thin decade 
the principal aim bac been to elucidate the nature of the primnry radiation itself, and its impli:ations for space science and aetrophysicr. 

The main tool in these investigations has been the photographic emulsion 

technique, in which nuclear research emulsions are used as the detectors. 

In the application of this powerful method to cosmic-ray research, the 

staff of the ,Yosmic Ray Branch in the Nucleonics Division of the U. S, 

Navel Research Laboratory is without question the most experienced group 

of physicists in the United States, The names of the investigators, together with quantitative data on their experience in this and closely related specialties, are supplied below.. A later version of this proposal, 

which will be submitted several weeks hence, will list the relevant publications of this group and supply vitae on the individual scientists, 

Our present knowledge of the heavy nuclear component of the galactic 

cosmic radiation as well as the fast heavy nuclei from the sun has come 

mainly from the exposure of emulsion stacks on high-altitude balloon 

flights and rockets. By using emulsions of various sensitivities and grain 

sizes, mucia has been learned about the charge spectrum of particles with 

Z > 2, near the top of the earth's atmosphere and above it.. Informetioa 

has also been obtained about their fluxes and energy spectra, These particles have short interaction mean free paths and, therefore, observations 

at balloon altitudes are made on an admixture of primary particles, plus 

secondary ones coming from interactions in the residual atmosphere abov,e 

the balloon. The cosmic-ray composition well outside the earth's atmosphere is deduced, at present, mainly by extrapolation. Yet it is that 

composition which is most relevant to problems in space science and 

astrophysics. 

A-231 
SE 1 JULY 2015 

clelrly the great value of visual. methods (photographic emulsion stacr, 

cloud chambers, chambers, spark chambers) in the magnum phases 

of resear,h required to operate a cloud !.taMber or bubble 

rhamber is very groat r.cmrared to that for emulsions, and is also greater 

than that for spark chamberz, One of the distinctive advantages of the 

emulsion te7tnieue in space research is that it permits the collection of 

a great deal of !.nfc=ction per unit weight. Its principal limitation is 

the requirement of recovery. kfoordingly, it is particularly desirable 

to exploit this vothod of detection in missions where recovery is essential anyway. 

Hitherto, opportunities for exposing nuclear emulsions in outer space 

have been limited because most vehicles are not recoverable. Also, with 

the exception of the Goddard Center's experiment, "SERV", these exposures 

have been "parasitic", and therefore, very little control was available 

uver conditions during exposure. For example, on the Discoverer satellites, 

exposure of one pound of emulsion is possible only under 2 gm/cm2 of 

material, which is no better than a very high balloon flight. 

With the advent of large recoverable payloads, such as those in the 

Gemini program, more suitable exposure conditions for emulsions could be 

obtained, e.g., it became feasible to expose a reasonably large stack of 

emulsions (one liter weighing approximately 10 lbs.) with no absorbing 

material between one surface of the stack and the zenith direction during err 

a 

exposure. 

a 

A-232 
The National Aeronautics k.nd Sp v* Administration has accepted our 

proposal (and a parallel one by Fichtel of the Goddard Space Flii;ht 

Center), fox. the exposure of emulsion stacks on Gemini vehicles. We are now 

actively engaXed in the design of the Gemini experiments, scheduled for 

la,„z4h in 1965. The valuable experience gained in these space exposures 

will, of course, be brought to bear on the experiments now proposed for 

the MOL. 

Scientific Objectives 

(1? To investigate the cOMposition, flux, and energy spectra of the 

nucleoni,2 aokponent• of the primary cosmic radiation outside of the earth's 

absorbinm atmosphere. This would be done with stacks of nuclear research 

emulsion and, in parallel experiments, with arrays of Cerenkov, solidstate, and s'intillation counters. 

(2) To study the prinnry 7-ray and electron components of the primary radiation about which little is now known' Directional investiga 

tions of 7-rays "gamma-ray astronomy") will be pursued, exploiting 

the assistance of astronauts (cf. below). The main detectors would be 

spark--Ihambers; however, the development of new emulsion techniques is 

being explored with a view to getting gamma ray and electron data by at 

least two different methods. 

CO It is planned to make the foregoing observations as a function 

of time, and in particular of the phase in the solar cycle, assuming that 

participation will be authorized in several flights. 

ED FOR 

ULY 2015 

111 

A-233 
(14 1ihile pursuing the main programs above, the physi:iets viii, 

of course, to seavting for rere particles and other ns7e'). OT4norierl.t 

rAeht •-onivaLly ami,wer in thu cletetor;.; aaing t.) the ab:.ewe of an air 

biao1ei. oLne: .lvcrlying aborber. 

S:..me of the contemplated ftxperimeatal bet-ups will permit the 

stuCy of high-energy particles of solar origin, especially during solar 

A schematic tabulation of the experimental program is shown below: 

....•••■•■••• ■oluremo.....m.....■rormaNfts••• ••••••• 

Subject of Experiment 

-------...........---------- 

P.:10.C.Y.S.MILLI.L.EW:a22-. 

(Especially Z > 2) 

.S4-1 -11Ellallt.e.M131 „-a111.1— 

■■•■■•■• ■•■••■•••• ■• 

Detection by 

reunions 

Detection by 

Nuclear Research Nuclear 

Cerenkov 

Solid State 

Scintillation s 

Application or 

latest tet:hniques 

and development of 

new techniques 

including chemical 

.t.1.... ay---- sandi ......48.11Z2111 i N ocessing in space 

7-ray astronomy 

1 

I 

k , tiam ix:r) 

In some of the 7.ray and electron experiments it will be particularly 

valuable to have elongated telescopic arrays of counters.. These need not 

be heavy, but should be extensible in at least one direction. The apparatus 

can be compact during ascent and descent. Then, thanks to weightlessnees 

and the help of astronauts, it can be appropriately extended during experimental runs :some of them extravehicular) without cumbersome automatic 

equipment. 

4 

A-234 

NRO APPROVED FOR 

1 JULY 2015 
3 

Another ..!xtreTc%y helpful intervere.ion by astronauts would be the 

nhemieml pro-ess1nc or nuclear emulsion aboard the MOL, which would 

strict 7roblbitive hanIssrcIrd of try'.: s that now makes ;t almost 

impossib.le to dr?tect prirzry eleztrnnr$ or am a3 rays wtth this useful 

detector, 

It is also hoped to take advantage of the possibility of returning 

stacks of emulsion to earth after an exposure of suttable duration (i.e., 

a sufficiently short exposure to minimize interfering ba3Xground):. 

Preliminary estimates of the weight, volume and power requirements 

for these experiments will be furnished shortly in a supplement to this 

preliminary draft proposal, together with information as to the type of 

orbit desired. 

The following pbysinists work in the Cosmic Bay Branch in the Nucleonics 

Division of the I% S. Naval Researnh Laboratory: 

M. M. Shapiro 

(Principal Investigator) 

R. G. Glasser 

A, J. Herz 

B. Hildebrand 

F. W. O'Dell 

N. Seeman 

R. Silberberg 

B. Stiller 

It is of interest to note that these eight scientists possess an usage_ 

of 12 years of research experierwe*in cosmic radiation and high-energy 

physics. Six of them have each had between ten and twenty years of such 

experience. 

Maurice M, Sbc piro, Principal Investigator 

A-235 
APPROVED FOR 

ASE 1 JULY 2015 

23 

7140-RT:mgw 

February 1064 

PROPOSAL FOR DIRECT OBSERVATION AND PHOTOGRAPHY OF 

THE WHITE LIGHT CORONA OF THE SUN AND SURVEILLANCE OF THE 

SKY CLOSE TO THE BUN 

by the 

E. 0. Rulburt Center for ewe Research 

U. S. Naval Research Laboratory 

Washington, D. C. , 20390 

1. Test Objective 

It is proposed to equip the Maimed Orbiting Laboratory (MOL) with a 

device which would make it possible for an astronaut visually to observe the 

sun's white light corona and also to record the corona by means of a camera. 

Briefly, the idea is to erect an occulting disk outside the MOL capsule at as 

great a distance as practical, and in front of the viewing window through which 

the astronaut looks at the outside world. To view the corona the astronaut 

would steer the capsule into a position such that the occulting disk precisely 

covers the sun and casts a complete shadow on the window. Under these conditions and in the absence of sky light the astronaut should be able to see with 

his naked eye the corona extending from the sun in much the same fashion that 

it can be seen during the total phase of a solar eclipse. With a simple camera 

placed within the shadow of the occulting disk, it should be possible to record 

the white light corona on photographic film. It would also be possible to detect 

A-236 
exiTeraely small objects, or larger but distant objects, lying close to the 

sun in angle, which would otherwise be completely invisible. 

The white light corona consists of two parts. e:1) The K-corona, produced 

by free electrons in the sun's outer atmosphere, showing almost no trace of 

Praunhofer lines, and strongly polarized, is the more intense component within 

one solar radius of the limb. This is the portion associated with the sun's 

atmosphere and varying with conditions in the sun. (2) The F-corona. due 

to scattering by dust, containing the Prannhofer lines, and nearly =polarized, 

is more intense than the K-corona far from the limb of the sun. This is the 

component which merges into the true zodiacal light, which is sometimes seen 

from the ground shortly after sunset or before sunrise along the ecliptic and 

produced by material in the plane of the earth's orbit. 

From eclipse photographs the K-corona is known to be of the greatest 

interest. The patterns and shapes presented by it are weird indeed, and are 

never the same from eclipse to eclipse. Streamers, some extending far from 

the aim, seem to outline the sun's magnetic field. Tremendous changes take 

place in the corona from year to year, and from sunspot maximum to minimum. 

There must also be short-period changes, with solar rotation and with solar 

activity. 

2. Importance of the rest 

An important possible application of the direct observation of the corona 

over a relatively long period of time is the possibility that the expulsion through 

the solar corona of the clouds of plasma that are known to reach the earth 

A-237 
PROVED FOR 

E 1 JULY 2015 

following solar flares can be observed directly. One might expect an astronaut 

to see a bright localized region develop in the solar corona and travel out through 

the corona, perhaps following a corona' streamer. The rate of travel away from 

the sun of such a mass of plasma has been estimated from radial velocities 

measured above flare surges by the Doppler effect, and from the rate of growth 

of surge prominences that oocur on the limb. The velocities, often exceed 

600 km/sec. To travel one solar radius from the limb would require 23 

minutes at 500 km/sec . it is within the realm of possibility that an astronaut, 

observing the solar corona continuously over a period of one-half hour, might 

see such an event taking place in the corona. This could very possibly serve 

as a means of forecasting the onset of a magnetic storm on the earth, or even 

serve to forecast the occurrence of a severe proton event such as would be a 

great hazard to life for an astronaut in space. if sufficient shielding were not 

provided. An early warning would give the astronaut time to turn his vehicle 

so that the shielded side would afford him maximum protection. 

It is expected, of course, that the corona will be studied automatically 

by means of orbiting ooronagraphs in unmanned satellites. The advantage to 

equipping a manned spacecraft such as MOL with the means of observing the 

corona visually is that it should be possible under such conditions for the entire 

corona to be studied oontinuouely, rather than at intervals of some 15 minutes, 

and with far greater sensitivity and resolving power than can be done with 

automatic equipment from a small satellite such as the orbiting solar observatory. 

Under these conditions, the chance of observing a small mass of plasma travelling 

A- 238 
out through the corona is much greater than with a small instrument of low 

resolving power producing intermitted records. The human eye is probably 

able to detect changes of this sort, with more sensitivity than can be done 

through inspection of telemetered data. 

Another possible application of such observations is the search for comets 

close to the sun, or possible objects near the sun. These objects cannot be 

looked for from the ground at night, of course, nor can they be seen from the 

ground if they lie very close to the sun. Dossin has reported the first 

detection of such a comet during the total phase of the solar eclipse of July 20, 

1963. With the coronagraph arrangement, provided that the occulting disk 

could be made sufficiently effective, there would be a strong possibility that 

any such objects could be detected in the field of view. 

Another application of the coronagraph might be as a defensive weapon► 

for an astronaut against an enemy astronaut who decided to approach under 

cover of the bright sun. Without a coronagraph it would be completely impossible 

for an astronaut to see another object approaching him if the sun were within 

his field of view. 

The coronagraph would make it possible to observe debris coming out of 

the vehicle with the greatest possible sensitivity. Looking close to the sun, 

the background would be black, except for the corona. But small objects, 

illuminated by sunlight, would shine with great brilliance, since scattering 

at small angles is intense. 

A-239 
3. Description of the Experiment 

The coronagraph for MOL would consist simply of an occulter placed as 

far from the capsule as possible and arranged to eclipse the sun by producing 

a perfect shadow at the viewing window through which the astronaut observes. 

Coronagraphs of this sort have not been used on the ground because of their 

unwieldy nature, since it is necessary to employ a large occulter situated at 

a very considerable distance from the observer. The effectiveness of a circular 

occulter with a smooth edge increases in proportion to the distance between the 

occulter and the observer. The moon lying at a distance of 240.000 miles is 

the perfect occulting disk, whereas a small occulter situated within a few feet 

of the observer would be of little use unless it were designed in a very special 

fashion, such as has been done for the coronagraph for the Orbiting Solar 

Observatory. The difficulty is in reducing the light diffracted from the edge 

of the occulter until it is negligible. 

The intensity of the light diffracted by the occulter can be calculated 

qualitatively as follows: The total flux. F, diffracted from the occulter edge 

is proportional to the circumference of the disk of radius R . The flux per *mit 

area received by the observer is inversely proportional to the square of the 

distance, D , between the observer and the disk, and directly proportional to 

the circumference of the disk. Thus the flux per unit area is proportional to 

FOR 

2015 

R/D2

. Since R/D must remain approximately constant, in order for the 

occulter to obscure precisely the sun, the flux per unit area is proportional 

to 1/D . 

A-240 
OR 

LY 2015 

The first proposal is to employ an occulter at a great distance from the 

capsule; the minimum useful distance is believed to be of the order of 100 ft 

and for this distance, the occulter should be approximately 1 ft in diameter. 

Greater distances would be far better. A simple occulter might be constructed 

from an opaque balloon, arranged to be propelled away from the capsule until 

held by some sort of non-flexible line. The propulsion might be effected by 

means of a small gas jet and the balloon itself might be held to the capsule by 

means of a tripod consisting of three small rods tied to the capsule in the 

neighborhood of the window at a separation of some 6 or more inches. Under 

these conditions all three rods would lie in the shadow of the balloon when it 

was pointed at the sun. If the rods were made in the form of small tubes, it 

might be possible to maintain the gas pressure in the balloon by flowing gas 

through the tubes, otherwise some vaporizable material could probably be 

used to maintain a sufficient gas pressure in the balloon to keep it forces out 

against the three legs forming the tripod. The astronaut, when using the balloon 

to obscure the sun, would be required to orient the capsule until the balloon cast 

a perfect shadow on the viewing window. He would then see the corona extending 

beyond the edge of the balloon against the black sky. 

It is entirely possible that a single occulter would not reduce the light 

diffracted from the edge of the occulter sufficiently to show the corona unless it 

were situated at a distance much greater than 100 ft. To use a 10-ft diameter 

balloon at 1000 ft is not an impossibility. A simpler solution, however, might 

be the use of a double or multiple occulter. A double occulter would consist of 

A-241 
a pair of flat disks, the one slightly larger than the other, aligned perfectly 

with the axis of the tripod. They could be propelled into position by a Jet from 

a gas bottle, and the bottle itself could be used as the mounting structure for 

the disks. 

It is difficult to estimate the weight and volume of such a system. It would 

appear possible to provide a simple occulter for use at 100 ft for less than 

10 pounds weight and a space of well under 1 on ft. The more complicated 

type would probably weigh 20 pounds. 

A second type occulter could be made in the form of a rigid spar supporting 

at its end, a metal occulting disk of a complicated nature such as is being flown 

in the Orbiting Solar Observatory. A reasonable length of spar might be 15 ft 

with an manlier supported on a short arm from the end of the spar. Gas pressure could be used to erect the spar and some kind of wire could be used to 

pull it back into the capsule. 

With a 15-ft length spar, the occulter diameter would be of the order of 

2 inches. It would be necessary to use an occulter, either of the toothed 

type employed in the Naval Research Laboratory satellite coronagraph, or 

a multiple disk occulter such as is being used by Newkirk in the coronagraph 

he is constructing for a stratosphere balloon. The weight of such an occulter 

would probably be of the order of 20 pounds and the volume when stowed is 

estimated to be a cylinder 2 ft long and 3 inches in diameter. 

The window through which the astronaut would view the corona would of 

necessity have to be quite clean. This, however, is desirable from many 

A- 242 

D FOR 

Y 2015 
other points of view. The camera for photographing the corona could be 

hand-held by the astronaut inside the window. 

No electrical power would be required for the operation of the corcmagraph. 
OR 24 

2015 7140-RT:mgw 

February 1984 

PROPOSAL FOR AIRGLOW SPECTROSCOPY FROM THE MANNED 

ORBITING LABORATORY SPACECRAFT 

by the 

E. 0. Hulburt Center for Space Research 

U. S. Naval Research Laboratory 

Washington, D. C. , 20390 

I. Test Objective 

An astronaut in Manned Orbiting Laboratory 4MOL) has the unique opportunity of flying a high resolution airglow spectrograph, and recording the 

ultraviolet spectrum of the night and day airglows on photographic film. Only 

on such a mission is there available a sufficiently long time to record these 

faint emissions at high resolution; the ability of the astronaut to point the 

instrument at the brightest part of the airglow, and then to bring back with him 

the exposed film is essential for an experiment of this type. 

The night airglow in the visible and ultraviolet has been investigated by 

the Naval Research Laboratory since 1956, using rockets and narrow-band 

filter photometry. Recently, the Johns Hopkins University and the Kitt Peak 

National Observatory have studied the day airglow with rocket-borne, scanning 

spectrometer techniques. Both methods have produced results of great aeronomical value in connection with the photochemical processes occurring in the 

A-244 
ED FOR 

ULY 2015 

upper atmosphere when solar radiation is absorbed, and afterward at night, 

when the excited atoms and molecules tend to return to their ground states. 

Tokientify fully the various atomic and molecular species present and the 

reactions involved, it Is necessary however to obtain spectra of far higher 

resolution than presently available. This is where it is necessary to resort 

to a manned vehicle such as the MOL with recovery of the photographic film. 

2. Importance of the Test 

There is a need for the Defense Department to know the complete spectral 

character of the night and day airgiow background over the spectral region 

2000 -3000 A in addition to the longer wavelength regions accessible from the 

ground. In this particular region, 2000 -3000 A the earth looks black from 

above because of absorption by the ozone layer. For this reason, there is 

much interest in airborne devices using this spectral range. The question 

"what is the ultraviolet background" is frequently asked; only partial answers 

can be given until the complete spectrum is known. 

3. Description of the Experiment 

It is proposed to furnish a high-resolving, high light-gathering power 

grating spectrograph for the MOL. The preliminary design is already available. 

The dispersion, 20 -25 A/mm should be adequate to resolve the molecular 

band structures anticipated and the 6-inch focal length f/2 camera lens would 

provide a good exposure for the night sky to be made in two or at most four 

orbits. Day airgiow spectra could be recorded in a few seconds on the other 

A-245 
hand, In order that appropriate exposure times are chosen, a photoel 

integrating system would be incorporated in the spectrograph to signal the 

astronaut when the proper exposure time had elapsed. In Lieu of integratkik, 

a precalculated table of exposure times could be used. It is anticipated that 

the astronaut would need only to point the spectrograph at the airglow horiza 

by turning the capsule, then push buttons to start exposures and actuate the 

film transport. Pointing would be done with the aid of some sort of visual 

sighting device such as a small telescope boresighted with respect to the 

spectrograph. An accuracy of pointing within 1/4° would be adequate but 1. 

. - . 

if this could not readily be achieved, increased exposure could be traded for 

-., 

less accuracy in pointing. 1 

The spectrograph would be approximately trapezoidal in shape, measuring . '.' 

about 15 inches in altitude, 11 inches at the base, 6 inches across the top 

with a depth of 4 1/4 inches. The weight will depend largely on vibration 

specifications needs and can probably be kept to within 115 pounds. It is proposed to raotmt the spectrograph inside the capsule, looking either forward or 

aft. The light path through the capsule wall would be a cone of no more than 

50 total angle with a quartz or sapphire lens of 1 1/11-inoh diameter, both 

imaging the airglow horizon on the slit and serving also as the window to 

maintain pressurization. A cap or valve of some sort would probably be 

required to protect the window from debris during the launch phase and from 

the but of re-entry. Electrical power consumption would be about 500 

watts only during times of exposure, with pulses used to operate the exposure 

D FOR 

LY 2015 
mechanism and to transport the film. 

It is emphasized that, although the equipment described could be reduced 

in size, weight, and cost at the expense of spectral resolution, only an experiment that yields data of this very high resolution is worthy of consideration 

for a TAOL; less powerful spectrographs can be flown in unmanned, less 

expensive spacecraft. 

A-Z47 -Al‘ • VA: 
23 

ED FOR 

ULY 2015 

GENERAL SCIENCE 

A. Statement of Problem 

A great number of purely scientific experiments have been proposed for MDL'. 

that would contribute both to basic scientific knowledge as well as to a better 

understanding of conditions in space. These experiments are intended to take 

advantage of the opening of a new frontier -- namely manned space flight. Thei 

importance lies in their relationship to technical developments and requirement 

for space flight. In order to understand the problems facing astronauts and 

what can be accomplished it is necessary to provide a sound basis for scientific 

hypothesis and factual scientific development. 

In response to a request, a large group of Naval organizations contributed 

a total of forty-five proposals for pure scientific experiments (including 

geodesy) which are recorded in Appendix II. The problem confronting the MDL 

technical panel was to categorize these experiments and choose those that may 

contribute to a program which could yield scientific knowledge of value. 

B. Development of Plan for Naval Experiments 

In order to develop a plan, the proposed experiments were first divided 1 into three categories. Experiments of category I consists of those which are 11 

vehicle or mission oriented. As such they do not play a major role in the 

design of the vessel but they meet the objectives of the program by demonstrating man's utility in space as well as providing urgent scientific knowledge: 

A knowledge of the environment surrounding MOL is essential to a correct design 

and utilization of electromagnetic devices, e.g., the plasma surrounding MDL 

may affect directly the operation of V.L.F. and H.F. equipment. 

The second group of experiments are not as directly related to MOL as those 

of the first category, however they are deemed to supply scientific information 

that may have a bearing on the operations of military spacecraft. For example, 

the astronaut's ability to see near the sun as determined by the solar corona 

may have a direct bearing on his survival. 

Experiments of the last category are those of general scientific interest 

which may yield useful information at little additional cost. There were in 

this category many interesting experiments that have physical implications and 

will contribute to a knowledge of the environmental conditions of space, but 

most were able to be carried out in an unmanned vehicle or simulated in some wan 

Experiments in each category were further divided into scientific fields: 

e.g., Plasma and Space Physics, Physics of Detonation, Weather and Related 

Fields, Planetology, Geodesy, and a miscellaneous group which did not obviously 

fit anywhere else. Every suggestion and proposal was carefully considered but 

the great majority of the proposals were rejected. The major reasons for . 

rejection of proposals were primarily that such experiments could more easily 

be done in an unmanned vehicle or did not satisfy the objectives of MOL. Experiments proposed for MOL by the technical panel are given in Table I, while 

Appendix I describes each experiment in detail. 

A-248 
id 

ULY 2015 

The experiments of category I are largely concerned with the environment 

of MOL. The Orbital Plasmas (Scatter) experiments will study the large plasma 

cloud accompanying MOL. Such plasmas have been detected previously and may 

lead to a large radar cross-section for MOL or to enhanced detectability in 

general. In a military operation it would be desirable to determine the 

extent of such plasma clouds and the mechanism of their production so the 

chance of detection can be reduced. The orbital plasma scatter experiments 

are designed to study the extent of the plasma trail and determine their cause. 

The Electron Density and Temperature Experiments are designed to study the 

character of the plasma in the vicinity of MOL. Because of the size of the 

space ship there may be a dense plasma (relatively) sheath developed near the 

MOL. A knowledge of the environment of MOL is essential to a correct understanding of the electromagnetic transmitting and receiving equipment aboard 

the MOL. Furthermore, the nature of the environment surrounding MOL may lead 

to deleterious effects. In particular, effects produced by the simultaneous 

application of ultra violet and a fairly warm plasma are extremely difficult 

to study in the laboratory, and the surface behavior of metals may be affected 

by the environment such that welding and/or metal working may be difficult. 

The far U.V. Image Orthicon experiments (while included under another section) 

are also discussed here for completeness. The applications of the U.V. device 

will be to determine if the trails of spacecraft formed by leaking gas containing water vapor will be visible against the universal- glow of the sky in the U.V. 

Early dawn warning may also be provided. In addition it is estimated that heavy 

air molecules striking the MOL surface at orbital velocities may produce 

recordable intensities in the far U.V. so that an estimate of the relative 

numbers of such molecules can be made. In addition to the purely mission 

oriented aspects of the U.V. system, a complete mapping of the sky in the 

1200-1700A° region can be obtained. As such it provides a measure of the main 

emissions from early type stars and may provide a critical test of radiative 

transfer theory as applied to early hot stars. Such information is essential 

to providing a more accurate record of the energy output of the galaxy and may 

provide information concerning interstellar absorption. 

The Airglow Horizon photography experiment is designed to provide information 

about the character and variability of the nightglow background over the earth 

in a large spectral range. The usefulness of such observations arise in the 

possibility of using the nightglow to determine a spatial reference for 

navigational purposes. It is only from a man-directed vehicle such as MOL 

that sufficient light can be obtained from the nightglow to provide adequate 

recording. Attempts to carry out this experiment from rockets have failed for 

lack of exposure time. 

In category II, the experiments of long range military interest are again 

primarily concerned with space physics, emphasizing a study of radiation unique 

to space. The cosmic radiation experiments will provide measurements of the 

radiation received by astronauts during long voyages as well as the particle 

radiation from solar flares. 

)eri- The aims of the Airglow Spectroscopy experiment is similar to the Airglow 

Photography experiment described in the discussion of category I, however, the 

A-249 

;1y 

it 

se 

on 

e, 

dge. 

gn 

way. 

eir 

nts 

fic 

d 
ED FOR 

LY 2015 

C.Y. o4 C.Y. 65 C.Y. 66 C.Y. 67 C.Y. 68 

.Final installs 

tion and Test 

• 

Fabrication of 

final models and 

start installation in vehicles 

Lab. Models 

Completed 

and Tested 

Start plan- Complete planning ning and initiate 

Lab. models 

.1 

Orbital plasmas (scatter) 

Llectron Density 4 Temp. 

Far U.V. Orthicon 

Airglow doriz. Photo. 

Category II 

.05 .2 .6 .4 .1 

.2 .2 .6 .4 ' .1 

included elsewhere 

.2 .2 .6 .4 • .1. 

.3 .05 

.4 .1 

.05 .10 . 

.2 .6 

included 

Cosmic Radiation 

Miite Light Corona' 

Airrlow Spectroscopy' 

Category III 

.U3 

.03 

.03 .03 .U3 .03 

.03 ..03 .03 .03 

Pnoto. of planets .03 

Geology of Earth .03 

ilitary applications are somewhat more long range. Nqwever, it should be n 

that there nay be very bright emission lines which may define the horizon. 

Another completely different application of the results may arise in Vela. Hot 

where an understanding of the high altitude emissions may be essential to a, 

detection of a clandestine nuclear explosion_im_s.pace. 

Observations of the idlite Light Corona of the sun may provide informatiokt 

pertinent to visibility of objects near the sun. In addition it is possible4 

that explosion of large amounts of plasma•from the sun may be visible which M. 

allow prediction of solar effects on the earth. 

, • 

• 

In group III, those two experiments of general scientific interest that. 

survived the considerations of the panel are priiarily astronomical in desig0 

and may contribute- with little additional cost. Both experiments are primarilt 

photographical in.nature and use the photographic equipment on MOL. Both planet 

and earthly photographs will be made. The absence of the atmosphere will contitbute to obtaining good views of the planets. Photographs of the earth will pert,: 

a more precise study of the geology of the continental structure to be made. ' 

C. Development Schedule 

All the general scientific experiments can be made to fit any reasonable 

schedule. However it is proposed that the following development be followed: 

D. The cost .schedule for the experiments are estimated as follows: 

FY 65 FY 66 FY 67 FY 68 FY 69 FY 7U 

Category 1 

A-250 
NRO AP 

RELEAS 

/e no 

1 Mote' 

) a 

ition 

Lae 

_ch ma 

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:sign 

.maril 

plan 

cont 

11 pe 

!de. 

ble 

wed: 

Y. 68 

install4-' 

end ty 

F. Recommendations for future study 

There remain several problem areas relative to the proposed experiments that 

should be mentioned and will require consideration during the design and development stage of the experiments. Several of these questions have to do with integration of the experiments while some have to do with direct questions as . to 

experimental detail. In order to delineate the problems the questions will be 

proposed experiment by experiment. 

1. Orbital Plasmas (Scatter): Problems.remain here to determine if the 

radar transmitter and antenna would serve as the radiator. Further questions 

of ground support and correlation of data also remain to be resolved. 

2. Electron density and temperature: The general techniques of this experiment are well understood, however some development will have to be carried out 

with deHaviland to provide an extendable insulated probe (uninsulated devices 

are in general use). Miniaturization of the five channel recording electrometer should prove to be only a routine laboratory job. 

3. Far U.V. Orthicon: Mounting of the T.V. camera in the MOL in the proper 

aspect will require some study. Consideration of the problem of automatic 

training of the equipment must also be considered. In general, the development 

of the T.V. system seems fairly well defined. 

4. Airglow Horizon Photography: One of the major problems associated with 

this experiment appears to be the maintenance of a stable platform during the 

exposure time of about, two minutes. It is possible that the astronaut may be 

able to maintain the spacecraft heading with sufficient accuracy to achieve 

correct exposures. However some consideration will be given to automatic training of the equipment. 

S. Cosmic Radiation: Further work will be required to clarify the experimental measurements with spark chambers. Film processing aboard the MOL is 

desirable but may be too difficult to achieve. This is desirable in order to 

prevent the nuclear emulsions from responding to extraneous particles. 

6. White Light Corona: Occulting disks and booms necessary for this experiment remain to be designed in detail as well as mechanisms to erect the occulting 

structure outside of MOL. Success of the experiment depends largely upon the 

ability of the astronaut to position the vehicle in the precise manner desired; 

studies of the positioning accuracy must therefore be carried out and compared 

with the requirements. 

7. Airglow Spectroscopy: Recommendations fur further study here are much 

the same as for the airglow photography. 

8. Photography of Planets and Geology of Earth: Here the exact experimental 

procedure must still be defined as experimental details were not written. It is 

suggested that the cognizant agency investigate the procedures to be used. As an 

aid they should consult with the U. S. Naval Observatory and Scripts Institute. 

A-251 

11111111111111.1111rIS 
D FOR 

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Title: Orbital Plasmas; Scatter Experiments 

Description of Experiment: 

The experiment consists in irradiating the plasma accompanying MOL with 

beamed r.f. from a steerable antenna mounted on WOL. Radiation scattered fr 1 

the plasma will be observed at ground stations. Direction and frequency of ' 

beams are to be controlled from MOL. 

Test Hardware: 

The experimental equipment will consist of a steerable antenna mounted on 1 

MOL with tuneable r.f. sources also aboard the vessel. It is possible that ,t 1 

existing radar antenna on MOL may be used for this purpose. The weight of th 

equipment is about SO pounds and will occupy a volume of 1.5 cu. ft. 

Test Procedure: 

The experimental procedure is as follows: 

1. The astronaut will select antenna directions and transmit for selected 

times. 

2. Astronaut will steer antennas and change frequencies to optimize 

scattering. 

3. Several antenna directions will be tried to obtain magnitude of 

scattered signal as function of variables. 

Test Objectives: 

The detailed experimental program is: 

1. To determine the size and structure of the large plasma clouds (or 

discontinuities) observed to accompany satellite, by scattering electromagnetic 

radiation. 

2. To determine the electron density and characteristics of the plasmas. 

3. To devise a theoretical explanation for the existence of the phenomena. 
Title: Electron Density and Effective Temperature 

Description of Experiment: 

These experiments are designed to study the plasma environment near AA,. 

In order to carry out this program several retractable insulated probes will 

tth be arranged around the vehicle and the probe currents observed as a function of 

1 fr applied voltage. Tests will be carried out in different parts of the orbit to 

of l observe diurnal effects. 

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Test Hardware: 

The experimental equipment will consist of retractable Langmuir probes 

arranged at five different positions along MOL such that sampling of the plasma 

can be made at different directions relative to the orbital velocity. Probes 

will consist of modified deHaviland extensible devices made so there is a thin 

layer of plastic insulation over the stainless steel. Probes will be designed 

to be extended to about 300 feet. A five-channel recording variable range 

electrometer will be required so that currents from all probes may be recorded 

simultaneously. The dynamic range of the electrometer should be designed to 

record currents from 10-10 to 10-4 amperes. 

It is estimated that recording equipment will occupy approximately 1/2 cu. 

ft. and will weigh 10 pounds. The five probes will be mounted on MOL and will 

occupy no more than 1/2 cu. ft. on the interior. 

Test Procedures: 

To carry out the desired test the astronaut will extend the five Langmuir 

probes and record the current as a function of probe voltage for different 

lengths of probes.- The probe voltage must be varied from negative to positive 

values such that the electron and ion currents both reach saturation. 

Test Objectives: The detailed experimental program is: 

1. To study the electron energy distribution in the plasma surrounding MCL. 

2. To determine the electron and ion densities in the plasma. 

3. To relate the above factors to the propagation and reception of electromagnetic waves. 

4. To study the formation, size and diurnal variation of the plasma about 

MOL. 

S. To relate the size and density of the plasma to radar cross section. 

Such experiments can only be carried out in space where the proper conditions 

exist. MOL is sufficiently larger than most satellites so that there should be 

appreciable differences from other devices. There is a great deal of uncertainty 

in the physical observations so that it is considered that personal observation, 

initiative and interpretation on the part of the astronaut will contribute to 

the success of the experiment. 

A-253 
VED FOR 

ULY201T1tle: Space Studies using Far U.V. Image Orthicon 

Description of Experiment: 

The proposed experiment is designed to study the night sky in the far U.V 

region between about 1200A° and 1700A°: To carry out this experiment it 

necessary that a U.V. sensitive orthicon and camera electronics be mounted at 

the focus of a wide angle camera and appropriate display units be in the AUL: 

The astronaut will observe and take pictures of the night sky on the T.V. disp 

under varying conditions of day and night. • 

Test Hardware: 

The basic part of the experimental equipment consists of a T.V..camera ch 

made up of the following: 

I. Far U.V. sensitive image orthicon with camera electronics. 

2. Wide angle Schwartzchild Optics (camera mounted at focus). 

3. Camera control and monitor package similar to Navy BX-7 closed 

circuit T.V. system. 

4. A synchronized movie or multiple exposure camera to photograph the 

T.V. screen. 

It is estimated that the electronics for the orthicon system weighs 30 pound 

occupies 2 cu. ft. and requires 70 watts during operation. The total system 

packageable in a volume of three cubic feet with a total weight of 40 pounds add 

power as indicated above. It is posSible that the closed circuit T.V. may be 

that used in the surveillance system. 

Test Procedures: 

The astronaut adjUsts the orientation of the spacecraft (and/or T.V. camera, 

system) in accordance with a pre-chosen schedule. He also adjusts the camera 

controls for hest T.V. image and monitor for proper framing. 

Test Objective: 

The scientific objectives of this experimental nrogra are: 

1. To determine the utility of the far U.V. orthicon syste...4 in providing 

dawn warning. 

2. To study the trail of space vehicles (especially WL) and missiles (if 

possible) to determine if there is sufficient absorption by leaking water vapor 

to leave a dark streak against the bright night sky (in U.V.). 

3. To determine intensity of radiation produced by air molecular impacts ;. 

on HOL. 

4. To study subvisual aurora, day aurora and particle dumping zones in the 

earth's atmosphere. 

5. To map the night sky in the U.V. and in particular study the emission:of: 

early type stars. It is desired to correlate the latter with radiative trans-_--

port studies as results may provide a crucial test of current stellar models. 

A-254 
NRO AP 

RELEA 

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Title: Airglow Horizon Photography 

Description of Experiment: 

The purpose of this experiment is to study the night airglow emissions from 

the upper regions of the atmosphere. As the airglow horizon as seen from an 

orbiting spacecraft appears as a line some 6° skyward from the earth's horizon 

and is very faint, long exposures must be made from a stable platform. 

Test Hardware: 

Equipment used in the experiment will be a high speed camera fitted with a 

grating in front of the lens to form an objective spectrograph. The thin line 

of the airglow will serve as the slit and be imaged as a spectrum according to 

the emission bands or lines present. The overall dimensions of the spectrograph 

camera would be approximately 9"x 3"x 4" and the total weight less than 15 

pounds. Only 300 milliwatts of power are required during actual pointing and 

operating of the camera. 

Test Procedure: 

The astronaut will point the camera out of the viewing window while the 

pilot keeps the spacecraft heading steady. Exposures will be of the order of 

two minutes. A quick change cassette would be used to obtain 20 to 50 exposures 

for a total time requirement of about an hour. 

Test Objectives: 

The objectives of this program are: 

1. To study the structure and variability of the airglow in order to 

determine its usefulness as a spatial reference for navigation of spacecraft. 

2. To study the distribution of nightglow with altitude to provide 

information for a comprehensive theory of the chemical processes taking place 

in the upper atmosphere. 

3. To determine if there is any variation of the nightglow with season 

latitude or longitude. 

A-255 
ED FOR 

LY2M5Title: Cosmic Ray Observations aboard MOL 

Description of Experiment: 

It is planned to investigate the composition, flux and energy spectra of 

the nucleonic component of the primary radiation as well as to study the pri 

y-ray and electron components. In order to carry out this program nuclear.. 

emulsions will be placed outside MOL; observations will also be made by mean 

of Cerenkov counter or spark chambers. 

Test Hardware: 

The experimental equipment consists of the following: 

1. Package of nuclear emulsion; 10-20 pounds. 

2. Erectable boom to be constructed outside MOL after orbit is achieved. 

3. Cerenkov counter with small package of electronics having a combined 

weight of 5 pounds and a volume of 1/3 cu. ft. r4. Spark chamber with small package of electronics having a combined weigh 

of 5 pounds and a volume of 1/3 cu. ft. 

Test Procedure: 

After an orbit is achieved the astronaut will erect the boom outside MOL w 

the emulsion package in place on its end. The package will remain in place 

several days. After exposure it is highly desirable that chemical processing 

of the package be carried out in MOL so that further exposure of the package 

will not take place. 

Data will also_be recorded by Cerenkov counters and spark chambers. The 

Cerenkov data will be telemetered to earth via the telemetry system on board. 

Spark chamber data will be taken by photographing the chambers during flight: 

This simply requires that the shutter of a camera integral to the spark chamber 

be activated. The astronaut will change the film in the camera after severalti 

hours exposure. 

Test Objectives: 

The detailed experimental program is: 

1. To investigate the composition, flux and energy spectra of the nucleonic 

component of the primary cosmic radiation outside earth's absorbing atmosphere. 

2. To study the primary y-ray and electron components of primary radiation. 

3. To correlate experimental data with solar phenomena. 

4. To search for rare particles and other novel phenomena that might appear 

in the detectors. 

A-256 
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Title: Direct Observation and Photography of the White Light Corona of the 

Sun and Surveillance of the Sky close to the Sun 

Description of Experiment: 

This experiment is designed to observe and photograph the solar corona from 

MIL. Occulting disks will be erected outside MOL so that the sun's disk is 

precisely covered. It will be possible to photograph the corona with a simple 

camera under these conditions and it may be possible to detect small objects_ 

lying close to the sun which would otherwise be obscured. 

Test Hardware: 

The basic coronagraph for MOL consists of a 1 ft. diameter occulter placed 

on a boom 100 ft. from MOL. For such a device it appears that the weight may 

be less than 10 pounds.and the stored volume of about 1 cu. ft. power 

requirements exist for the operation of the equipment. 

Test Procedure: 

The astronaut firgt erects the occulting disk at 100 ft. outside NOL. He 

then aligns the spacecraft precisely so that the occulter covers the disk of 

the sun. Observations and photographs of the white light solar corona are 

then made. 

Test Objectives: 

Objectives of this experiment are: 

1. To observe.the white light of the solar corona around the edges of the 

occulting disk. 

2. To photograph the solar corona. 

3. To search for objects lying near the sun's limbs. 

4. To determine if it is possible to observe the erruption of plasma from 

the sun's surface. 

S. To study the long streamers extending from the sun and estimate their 

extent. 

A-257 
Y

F

2015

°RTitle: Airglow Spectroscopy 

Description of Experiment: 

This experiment is designed to study the spectral distribution of.the ni 

and day airglow. It can only be carried out in a manned vehicle as demonstrat 

by previous attempts from rockets and satellites, as only on a manned mission 

there sufficient time to record and bring back a record of the faint emissions", 

at high resolution. A spectrograph will be on MOL and will be pointed at the 

airglow. Observations will be made either according to a table or timed by an 

integrating photometer. 

Test Hardware: 

The f-2 spectrograph to be used in these experiments is trapezoidal in shape 

measuring 15 inches in altitude, 11 inches at the base, 6 inches across the t 

with a depth of 4-1/4 inches. The weight depends largely on vibration specification needs and can be kept to within 25 pounds. Mounting of the spectrograph 

will be inside the spacecraft such that the equipment looks either forward or 

aft. The light path through the capsule wall will be a cone of no more than 5°4 

total angle with a quartz or sapphire lens of 1.5 inch diameter, both imaging 

the airglow horizon on the slot and serving as a window to maintain cabin 

pressure. Electrical power consumption would be 0.5 watt during times of 

exposure with pulses used to activate the shutter and transport the film. 

The dispersion of the spectrograph is 25A°/mm. 

Test Procedure: 

The astronaut will point the spectrograph at the airglow horizon by turning. 

the spacecraft and aligning it with an accuracy of 1/4°. (If this cannot be 

achieved increased_exposure could be traded for less pointing accuracy). 

Exposure and film transport mechanism will be actuated electrically after 

correct heading of the spacecraft has been achieved. Correct timing of the 

exposure can be carried out by means of a photoelectric integrating system. 

Test Objectives: 

Objectives of this experiment are: 

1. To record the ultraviolet spectrum of the day and nightslow. 

2. To determine the photochemical processes taking place in the upper 

atmosphere. 

3. Study the application of the results of this work to navigation nrohlems. 

A-258 
NRO A 

RELEA 

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2015 

)lens. 

A-259 

Title: Photography of Planets and Photographical Study of the Geology of 

the Earth 

Description of Experiments: 

The optical surveillance and photographic equipment aboard :4CL will be 

utilized in these experiments. Pnotogranhs of the planets will be made at 

the high resolution at different periods covering a period of about 30 days. 

Photographs of the earth will also be made to study the continential structure. 

Test Hardware: 

All the basic equipment required for these experiments will be aboard the 

spacecraft for the surveillance experiments. Additional film may have to be 

carried to record the additional observations required. 

Test Procedure: 

The astronaut will align the space vehicle and optical system such that 

selected planets may be photographed. Exposures will be carried out according 

to a table. Photographs of the earth under fairly low wide-angle resolution 

will be made. Certain portions of the earth may also'be studies under high 

resolution. 

Test Objective: 

The scientific objectives of these experiments are: 

1. To study the geology of the earth's continents. 

2. To study the shore line of continents and determine the width of 

continential shelves. 

3. To study the geology of certain islands and their structure. 

4. To determine the possibility of observing ocean currents from NUL 

by studying changes in hues. 

S. To study photographs of planets during different parts of their 

seasons (if possible). 

6. To compare results of HOE planetary photography with that frog. 

observatories. 
JL APPENDIX B 

Complete Listing of All Proposals for Experiments Received 

by the MOL Technical Panel 

No. Originator Title/Description 

1 BUWEPS "Electronic Surveillance of Ocean Targets for 

Ocean Surveillance." Intercepted electronic 

emission from ocean shipping is utilized for 

classification. 

2 NPIC "Proposal fora Photo Interpretation Experiment 

to be Conducted in a One-Man Gemini Satellite." 

In-orbit development of MOL exposed high-resolution 

film to permit photo-interpreter classification 

of "targets of opportunity." 

3 BUWEPS "Optical Surveillance Sensor Equipment." Determines feasibility of combining man and a semiautomatic recording optical surveillance sensor. 

4 NADC "Global Television Surveillance." Utilizes closed 

TV system for classification and identification 

of targets at night. 

5 NADC "Infrared Mapping." Surveys oceans and terrestrial features including weather and icebergs 

using infrared techniques. 

6 NRL "MOL Forward-Looking Radar." Proposes one of three 

radar possibilities for MOL ocean surveillance. 

7 NRL 

8 INS "Multi-Sensor Observation of Ocean-Based Target 

Complexes." Assesses the ability of satellitebased astronaut to interpret data from a variety 

of scanning and viewing sensors. 

9 APL "Ocean Surveillance." Similar to 8. 

10 171c "MOL Earth Reconnaissance and Surveillance." 

Utilizes photo interpretation and multi-sensor 

techniques to assist astronaut in determining 

which targets are of military interest. 

"Identification of Ships." PropOses use of Mark X 

(SIF) IFF equipment to assist astronaut in identification of friendly targets. 

B-1 
11 NADC "Photographic Ocean Surveillance Test Program." 

Assesses the capability of a high-resolution 

photographic reconnaissance system to perform 

surveillance over ocean and coastal areas. 

12 NRL "A Photographical Study of the Earth From Space." 

Similar to 2. 

13 BUWEPS "Visibility of Ocean Targets." Determines the 

capability of an astronaut to observe and report 

naval forces with the aid of optical devices. 

14 BUWEPS "Cooperative Shipping Surveillance Experiment." 

Effectively reduce ship densities through use 

of a cooperative system that will permit 

selected ships to identify themselves. 

15 INS "Visual Observations of Ocean-Based Target Complexes." Assesses man's visual capability for 

acquiring and identifying selected ocean targets 

and target motion from an orbital platform. 

16 NOTS "Visual Acuity Experiment." Assesses the astronaut's ability as a surveillance instrument to 

observe, describe, record, and interpret detail 

of objects and areas from an orbital platform. 

17 NRL "Infrared Scanning of Sea Surface." Analyzes 

infrared signals generated by small ocean areas 

and determines opaqueness of cloud cover. 

18 NADC "Night Surveillance." Utilizes an image intensifier direct-viewing device for observing the dark 

side of the earth from the satellite. 

19 NADC "Infrared Detection of Ballistic Missile Launchings." 

Determines critical parameters for infrared detection of ballistic missile launchings. 

20 NOTS "Infrared Sea Scanner." Similar to enclosure 7. 

21 NADC "Ocean Surveillance (Sonic-ASW)." Sonobuoy signals received in the MOL are used to classify 

ocean targets. 

22 NMC "Ocean Surveillance Radar Parametric Tests." 

Utilizes variable radar parameters in MOL to 

determine optimum configuration for radar in 

future manned satellites. 

B-2 
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23 NADC "Radar for Ocean Surveillance." Determines 

practicality of radar for ocean surveillance and 

optimizes system parameters for this and related 

applications. 

24 NOL (WO) "Buoy and Mine Field Interrogation." Determines 

the feasibility of establishing a sonobuoy or 

mine field surveillance system in MOL. 

25 NADC "Beacon System." Tests feasibility of using MOL 

in search operations for air crash or ditch victims. 

26 NRL "Manned Orbiting Laboratory Combat Information 

Center." Determines feasibility and establishes 

the technological basis for the development of 

combat information centers aboard manned orbiting satellites. 

27 BUWEPS "VLF Communications Experiment." Determines feasibility of continuous VLF communications between 

astronaut and U. S. ground stations. 

28 NADC "A VLF/HP Radio Propagation Experiment Involving 

the MOL." Investigates HF and VLF radio-wave 

propagation through different portions of the. 

ionosphere. 

"VLF-HF Electromagnetic Communications." Determines VLF communication effectiveness, measures 

VLF-HF dipole antenna impedance and measures 

propagation characteristics of VLF-HF radio signals through the ionosphere. 

BUWEPS 

NRL "Space Studies Using Far-Ultraviolet Image Orthicon 

Aboard a Manned Satellite." Measures the effectiveness of an ultraviolet image orthicon for UV 

star mapping, dawn warning, viewing subvisible 

auroras, satellite gas leaks, and exhaust trails. 

NADC 

29 NEL 

irk 

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31 

7 

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32 

B-3 
FOR 

2015 

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33 NRL "Neutron Flux and Spectrum Measurements in Space." 

Utilizes neutron flux measurement for interception 

and identification of unfriendly or aggressive 

satellites. 

34 NOL (wo) "Missile and Aircraft Signature." Proposes IR 

and visual survey including spectral distribution 

of rockets against earth background. 

35 NADC "Laser Surveillance System." Utilizes laser to 

determine cloud cover and sea state with secondary 

objective of satellite surveillance and laserilluminated photography. 

36 NADC "Basic Emitter Density and Location Experiments." 

Determines ELINT gathering capabilities of MOL. 

37 NMC "Space-borne Manned Electronics Surveillance. 

Determines ELINT gathering capabilities of MOL 

and tests vulnerability of U. S. Fleet to electronic 

surveillance from space. 

38 NRL "Selective Radio Spectrum Interception." Similar 

to Nos. 17 and 18. 

39 NOL :: .."ELINT Analysis." Analyzes MINT data in MOL 

(Corona) to determine features such as frequency diversity, 

pulse compression, and other techniques not 

easily determinable in unmanned satellites. 

40 NMRI "Project ARGUS Contributions to MOL." Utilizes 

Project ARGUS determinations to attempt resolution 

of MOL psychological problems. 

41 NADC "Comparative Evaluation of Terrestrial and Orbital 

Ratios of Potentially Useful Working Time to 

Sleeping Time." Records and measures the terrestrial 

time course and the orbital time course of sleep, 

drowsiness, and alert wakefulness of a MOL crew 

member. 

42 NRDL "Nuclear Radiation Personnel Monitor for Space 

Flight." Determines criteria for development 

of personnel radiation monitor for space flight. 

43 NRDL "Heavy Particle Dosimeter." Distinguishes between 

the protons and the heavy charged particles from 

primary cosmic radiation. 

B-4 
NRO APPROVED FOR 

44 ONR "Personnel Compatibility Predictors." Use Operation DEEPFREEZE personality prediction techniques 

for selection of MOL occupants. 

45 ONR "Vigilance and Diurnal Cycles." Explores workrest and diurnal cycle correlations. 

46 NOTS "The Behavior of Simple Spores in a Space Environment." Observes and studies the behavior of 

spores under conditions of high vacuum and radiation. 

47 ONR "Aids to Vision and Protection." Determines the 

effectiveness of filters under conditions of 

white out haze, etc., and the use of a photographic lens system for protection against "flashblind." 

48 ONR "Electromagnetic Auditory Masking." Determines 

the effects of the space environment on man's 

acoustic sensations. 

on 

Lary 

"Human Troubleshooting." Explores man's efficiency 

in MOL as a troubleshooter. 

"Human Visual Efficiency." Measures man's ability 

as an observer from the MOL. .ty, 

49 ONR 

50 ONR 

51 ONR "Environmental Odors." Investigates the effects 

of human odors and anti-perspirants upon team 

,ion effectiveness. 

tea 

strial 

10/ 

52 ONR "Gravity Retraining." Measures the efficiency 

of space-borne training simulators to recondition 

the astronaut to gravity-state prior to re-entry. 

53 ONR "Physiological Accompaniment of Gravity-Free 

State." Explores the gravity-free state in 

relation to man. 

54 NRL "Orbital Plasmas Characteristics." Determines size 

and characteristics of plasmas which will attend 

MOL. 

een 

,m 

55 NRL "Electron Density and Effective Temperature." 

Studies plasma environment in the vicinity of 

MOL. 

B-5 
FOR 

Y 2015 

56 NRL "Cosmic-Ray Observations Aboard the Manned Orbital 

Laboratory." Utilizes emulsions, counters, and spark 

chambers to measure cosmic activity as a function 

of time and solar cycle. 

57 NRI, "Proposal for Airglow Horizon Photography From the 

Manned Orbiting Laboratory." Measures airglow composi 

tion as a function of latitude, longitude, or season. 

58 NRL "Proposal for Direct Observation and Photography of 

the White Light Corona of the Sun and Surveillance 

of the Sky Close to the Sun." Measurement of the 

corona and sun surveillance are accomplished during 

a simulated eclipse utilizing an occulting disc between the sun and the MOL. 

59 NRL "Proposal for Airglow Spectroscopy From the Manned 

Orbiting Laboratory Spacecraft." A spectrograph and 

film are utilized to obtain the high-resolution ultraviolet spectrum of airglow. 

NRL "Flare Dynamics and Prediction." Studies solar flares 

by determining the hydrodynamic motion of various 

ionic species and the state of the plasma. 

61 NRL "Doppler Frequency Shift and Celestial Navigation." 

Utilizes doppler shift from three fixed earth radio 

stations to obtain the space vehicle velocity vector. 

62 ONR "General Test Experiments." Determines mode, velocity 

of propagation, and generating mechanism of the geomagnetic field through analysis of time variation 

measured in space. 

63 Scripps "Sea-State Determinations From Manned Orbital Laboratory." 

Tests the ability of an astronaut to measure and report sea state at a designated observable spot on the 

ocean surface. 

64 Nars "Measurement of Near-Space Dust Particles." Utilizes 

back scatter from a gas laser beam to determine 

particle description and population in the vicinity 

of MOL 

65 NOTS "Weather Observation and Prediction." Visual/optical 

terrestrial atmospheric conditions are reported via 

two-way radio to assist in forecasting weather trends 

on a continental basis. 

B-6 
NRO APPR 

RELEASE 1 

CECRET 

66 NOTS "Investigation of the Earth's Horizon in the Infrared." 

Utilizes measurements of the earth's IR horizon as 

a function wavelength, spatial distribution and solar 

illumination angle to determine the apparent nature 

of the earth-atmosphere-space boundary region. 

67 NOTS "Effect of Zero Gravity on Liquid Helium." Uses photographic and pressure measurement techniques, together 

with direct visual observations to determine the behavior of liquid helium under zero-gravity conditions. 

68 NOTS "Astronaut Monologue Broadcasts." Broadcasts are made 

by the astronaut to nations in their own language 

while the MOL is visible to them. 

69 NOTS "Pyrotechnic Communication Experiment." Tests the 

feasibility of a possible emergency communication 

la- system utilizing pyrotechnic charges triggered by an 

orbiting astronaut. 

-e s 

70 NOTS "Photogrammetry of the Solar Planets." RecOgnizes the 

advantage of high-quality planet photography taken 

above the earth's optically disturbing atmosphere. 

71 NOTS "Photogrammetry of the Geology of the Earth Continents." 

Provides photographs of earth continents for analysis 

by competent earthbound geophysicists. 

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_tory." 

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1 

72 NOTS "Mass Spectrometer Experiment." Categorizes and identifies ionized particles in the region of the spacecraft. 

73 NOTS "Gas Chromatograph Experiment." Utilizes a simple and 

miniature gas chromatograph to determine the gaseous 

constituents of the atmosphere surrounding the MOL 

spacecraft. 

74 NOTS "Precise Measurement of the Solar Constant." Utilizes 

astronaut operated radiometer-type instrument to obtain a more precise measure of the Solar Constant. 

75 NOTS "Airglow Experiment." Proposes measurements outside 

the atmosphere of illumination energy originating within 

the atmosphere. 

76 NOTS "Photogrammetry of Sferics." Photogrammetry of lightning occurences from above the atmosphere would assist 

the prediction and interpretation of weather. 

B-7 

rk 

1 

6403772 

Wififf/MIMINX/Mai 
Nk 

ODOI1DT 

77 NOTS "Spectral Radiance Measurements of Earth-Cloud Cover." 

A radiometer manipulated by the astronaut will yield 

spectral radiance measurements of the earth and its 

cloud cover. 

78 NOTS "Optical Surface Experiment." Studies the degradation 

of an optical reflecting surface after prolonged exposure to a hostile space environment. 

79 NOTS "Ozone Concentration Experiment." Utilizes an astronaut for ozone measurement. 

NOTS "Extra-sensory Perception Experiment." Attempts telepathic communication between the astronaut and ground 

observers. 

FOR 

2015 

81 NOTS "The Behavior of Relay and Switch Contacts After Prolonged Exposure to a Space Environment." 

82 NOTS "The Effects of High Vacuum and Intense Radiation 

Exposure of Explosives and Explosive Devices." 

83 NOTS "The Process of Detonation Physics for Conventional 

Explosives in a Space Environment." 

84 NOTS "IR and UV Spectroscopic Measurements of Stars and 

Planets From a Manned Space Laboratory." 

85 INS "Oceanographic Observations and Interpretation From 

Satellite Platforms." MOL multi-sensor data is 

integrated and interpreted by an astronaut to provide oceanographic information for operational use 

by sea-based forces. 

86 NOL (WO) "Tracking Device." Determines feasibility of a laser 

pointing and tracking device for a MOL communication, 

navigation, or weapon function. 

87 NOL (WO) "Anti-Surface Laser Weapon." Determines feasibility 

of utilizing a high-energy laser to damage sea-launched 

missiles or aircraft targets. 

88 NOL (WO) "Earth Magnetic Field." Maps earth's magnetic field 

and time variation and determines the feasibilityyof 

using this information for guidance purposes. 

89 NOL (WO) "Geodesy." Determines feasibility of using MOL for 

mapping military targets in inaccessible areas of 

the world. 

B-8 =MDT