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TAB D MICROFICH 

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CAPABILITIES OF THE MOL SYSTEM 

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I. INTRODUCTION 

The value of a long duration manned orbiting system, regardless 

of its mission, must be measured in terms of all of its capabilities, 

because inherent in man's presence is the fact that any system will 

be capable of great flexibility unless severe artificial constraints 

are placed on man and systeM. .Thus, if the manned system is designed 

as a high resolution optical intelligence gathering system, its value 

must be measured not only in terms of ground resolution, but also in 

terms of ability to return photographs of special intelligence value, 

rapidity with which intelligence can be returned to the user, flexibility to meet crisis situations, flexibility to gather different 

kinds of intelligence such as economic, arms control, tactical, 

strategic, and capability to perform other missions or accommodate 

other payloads. This value judgment must be exercised against 

development risks, times and costs, operational costa and growth _ 

potential. 

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Based upon any criterion but initial development costs, the MOL 

system is superior to an unmanned system to even meet the DORIAN. 

requirement. Furthermore, no single unmanned system could approach 

the total capabilities and growth potential of the NICE system. Thus, 

the development costs to realize all the capabilities of the MOL 

system with unmanned systems would be very much greater than for the 

 MOL system alone. Most likely such an unmanned capability would 

 never be developed because of the prohibitive costs and hence, we 

 would deprive ourselves of the wealth of mission possibilities and 

 flexibility we otherwise could have achieved with the manned MOL. 

The MOL system capabilities can be treated in four different 

 stages: 

A. Basic MOL/DORIAN system capabilities for additional missions 

without any additional equipment. 

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D. Growth potential capabilities towards higher. resolution 

and better cost effectiveness. 

B. Basic MOL/DORIAN systeM capabilities for mission enhandement with minor equipment additions or changes. 

C. Basic MOL vehicle capabilities for other than high resolution optical reconnaissance missions. 

DORIAN 

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The first case of using the MOL photographic system against an 

expanded target model which contains mobile targets, 

planets has been treated in TAB C. This tab summarizes MOL capabilities which can be achieved with varying degrees of modification 

of the present MOL baseline system. 

II. BASELINE SYSTEM WITH DORIAN PAYLOAD 

A. System Enhancement 

Several improvements to the existing system could occur 

during the next phase of the'MOL Program. Effort is now being 

expended in studies toward this end. One such effort is research 

by Owens-Illinois Glass Company involving manufacture of Cer-Vit 

material for the primary and tracking mirrors to replace.

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 fused silica. 

Cer-Vit has a very low coefficient of expansion (0.05X10 uin/in F) 

which will eliminate many of the present thermal problems and permit 

substantial weight savings in thermal protective devices. pe

has equivalent polishability characteristics and rigidity per unit r 

weight as compared to fused silica. This development will become 

particularly useful for very large optical systems leading towards 

on resolution. 

Study effort is underway to investigate techniques for 

reducing the MOL vehicle's vulnerability to hostile attack. The 

study will determine the signature and vulnerabilityof the MOL 

configuration compared to the expected threat. The spectrum of 

defense aids and operational strategies will be investigated as to 

their feasibility, constraints, effectiveness and costs. Various 

mixes of existing defense elements will be considered with particular 

emphasis on man's presence in the system. 

B. Electromagnetic Pointing System 

Studies are presently underway to develop a small, lightweight auxiliary electronic sensor system to enhance the system 

effectiveness of the primary optical sensor. The Electromagnetic 

Pointing System will be capable of identifying and locating emitters 

with sufficient accuracy to assure they fall within the field-ofview of the High Resolution Optics. Additionally, the system will 

provide and an ability 

to analyze specific signals to obtain their detailed technical 

characteristics. Overall system weight including antennas will be 

less than 300 pounds, peak power less than 250 watts, and total 

volume less than 5 cubic feet. 

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The primary employment of the Electromagnetic Pointing System (EPS) 

will be to furnish information to the operator which will increase 

mission effectiveness by giving him options of: 

1. Observing that pre-programmed photography is possible 

and appropriate in terms of the electromagnetic environment; 

2. Determining that a pre-programmed alternate target 

is more appropriate; or 

3. Determining that a non-preprogrammed "possible" 

target is more appropriate. 

In the latter two cases this action will be "appropriate" either because 

of the transitory nature of the target or the necessity for real-time 

photo and electromagnetic intercept of a target emitter. 

The technical 

analysis capability will permit the operator to obtain detailed wideband photographic recordings of complex signals on a pre-programmed 

basis. 

The design of the EPS will be such that its inclusion with 

the primary photo sensor will neither degrade its operation nor result 

in a lower reliability for the system. There will be no direct automatically controlled connections between the photo sensor and'the EPS. 

Coordination of the pointing functions of the two sensors, through the 

computer, will only be initiated upon manual command of the operator. 

C. Ship Detection 

In-house studies have defined a radar system with modest 

capabilities, power and orbit sustenance requirements which could be 

used for detection of ships on the high seas from MOL. The system-: 

can cover a swath 100 miles wide and can detect ships of the size of 

trawlers. Its weight is estimated at 400 pounds. It can enhance 

the intelligence value of the MOL mission by detecting moving targets, 

such as ships, which cannot be accurately programmed into the MOL 

target deck. It would be used in_specified limited areas to alert 

the MOL crew to obtain high resolution photographs of ships.- 

D. Astronomy 

The DORIAN optical sensor is capable of being used as a 

rather precise astronomical instrument. It can be employed for 

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planetary photography without change, as was discussed in Part II. 

In its baseline configuration, however, it has limitations for 

stellar astronomy because of stabilization problems. With improvements in the precision in pointing which are within the state-ofthe-art, however, the DORIAN sensor could provide 0.1 seconds of arc 

resolution for distant stars. One second of arc is the limit from 

the earth's surface due to atmospheric limitations. 

The refractive optical elements in the Ross corrector prevent spectral analysis and observations outside the visible range 

of the spectrum. A search for sources of ultraviolet radiation 

could be made, however, by replacing the present Ross corrector 

elements with Quarts. There exists no data on this part of the 

spectrum because of the filtering effect of the earth's atmosphere. 

In a search for unknown phenomena like this ultraviolet sensing 

mission the presence of man is indispensable. Spectroscopy could 

be accomplished by providing special adapters which could circumvent 

the Ross corrector elements. 

III. BASELINE MOL WITH OTHER PAYLOADS 

The MOL Program was approved on the basis that in addition to 

performing optical reconnaissance, other mission capabilities would 

be examined on a secondary basis. Specifically, the Ocean Surveillance and SIGINT missions were cOnsidered of great importance. The use 

of MOL as a scientific laboratory was also to be considered. A discussion of these additional uses of MOL Orbiting Vehicle follows below. 

A. Ocean Surveillance 

The objective of the MOL Ocean. Surveillance mission:under 

study is to conduct operational tests of satellite sensors and sensor 

usage concepts, in order to obtain information needed to design a 

follow-on ocean surveillance satellite system. 

The following types of sensors are being considered: 

1. High-Resolution Synthetic Aperture Side Looking Radar. 

2. Conventional Search and Detection Radar. 

3. Photo-Optical Equipment:, 

4. Passive Electronic Signal Intercept Equipment. 

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It is not yet known to what depth of detail ocean surveillance satellites mist collect information about detected targets. It 

is possible that with improved and properly integrated ground systems, 

the satellites need only supply accurate location information for 

detected targets. At the other extreme, it may be necessary for the 

satellite to classify every target as to type and identify some percentage of targets in the open ocean, and in addition frequently send 

information about conditions in selected ports and harbors throughout 

the world. 

The Ocean Surveillance system will be designed to operate in 

at least four modes according to the amount of information to be 

obtained on various test runs. The role of man in the various modes 

will range from no participation to complete integration In a manmachine combination. The four modes in order of increasing transmission requirements are: 

1. Target detection and location only. Fully automatic 

operation, with all data transmitted to ground. 

2. Fully integrated man-machine operation, with the astronauts performing image interpretation and data analysis aboard the 

satellite. 

3. Semi-automatic operation of full array of sensors, with 

man intervening for functions such as selection of targets for high 

resolution sensors, and selection and cropping of imagery for transmission to the ground. Image interpretation to be performed on the 

ground. 

4. Target detection and location, plus heading and speed 

determination (if feasible) and collection of high resolution imagery. 

Fully automatic operation, with all data to be transmitted to ground. 

B. SIGINT 

SIGINT Studies are currently underway aimed at determining 

p icate• electronic systems are 

also in the development phase as indicatedby intercepts of emitters 

identified as missile and satellite tracking radars. 

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The improbability that automatic collection systems. can be 

developed to completely cope with the complex electronic environment 

of the 1970's makes it very desirable to investigate the improvement 

in system effectiveness which can be achieved through the use of man's 

ability to make complex decisions and adjustments rapidly. 

In addition to our presently approved studies in the area of 

intelligibility we propose to investigate other areas in which it appears 

most difficult for automatic systems to - operate effectively. This will 

include the possibility of checking out and adjusting a system on orbit 

to permit it to subsequently operate automatically. 

At the conclusion of these studies it is proposed to devise a 

SIGINT system which would incorporate a number of SIGINT missions most 

effectively done by a system including man. 

C. Multi-Purpose Laboratory 

In addition to its other capabilities, MOL has the potential 

for providing a unique laboratory environment for the execution of 

specific experiments. These experiments can support the objectives of 

both NASA and the DOD. The MOL has 1,000 feet of. pressurized volume, 

and can provide up to 3,000 feet of unpressurized experiment volume in 

the Mission Module. It can carry up to 8,000 pounds of experimental 

equipment into polar orbit on 307day missions with a crew of two. 

The experiments considered of interest to the Department of. 

Defense can be grouped into the following three categOries: 

1. Those having potential for improving the ground resolution 

capability of the primary mission sensor; 

2. Those which demonstrate and test concepts and components 

necessary for advancement and growth of the primary mission capability; 

3. Those which explore future potentials leading to the 

designation of new military space objectives. 

Examples of these various categories of experiments which 

might be conducted with the'MOL for:the:Department of Defense are 

listed below: 

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Knowledge is neede z ;performance of large r. i on 

orbit. The alignment, erection, pointing and tracking, focusing, 

figure control and the behavior of materials such as beryllium, 

Cer-Vit, fused silica, pyroceram are all essential to improving 

ground resolution capability of the primary sensor. 

To establish our potential for new manned military missions, 

xperiments must be conducted in the area of communications 

Experiments to establish countermeasures against hoStile 

attack of the MOL are needed. 'Experiments to improve techniques for 

nuclear detection and arms control are also essential. 

IV. MOL GROWTH POTENTIAL 

The MOL system is well suited to grow beyond its present development program status towards greater operational utility. It can grow 

in two ways which are mutually supporting The optical sensor can be 

increased in size 

Because of the necessary weight growth 

of such a large optical system and the natural conclusion that orbital 

life longer than 30 days is more cost effective, the system will grow 

in size. The consequence of this size, weight and life growth. is that 

a bigger booster is required or the rendezvous approach be emploked. 

The large optical sensor and rendezvous are discussed in greater detail 

below: 

A. Large Optical Sensors 

Studies indicate that primary and tracking mirrors up to about 

in diameter are feasible under existing technology. Larger 

size optics will probably require new_ construction methods primarily 

due to structural rigidity, test and handling prObleMs in the earthi S 

gravitation environment. Ground resolution improves with increasing 

mirror diameters of up to about where vehicle vibration, 

atmospheric turbulence, reduced field of view, weight and other such 

system factors assume much greater significance. The present state 

of technology should permit the acquisition of optical systems capable 

of photographic ground resolution. 

The capability to achieve ground resolution can deVelop 

readily from the MOL baseline program. The development risk will be, 

inherently high but minimized by the presence of man. The need for the 

man in system operation will be definitely higher than for the present 

DORIAN system. The fabrication difficulties, complexity and costs may 

well dictate a rendezvous approach to minimize the number of sensors 

required. It is estimated conservatively that a sensor with 

ground resolution will weight a minimum of 20,000 pounds. 

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B. Long Duration and Rnclzvous 

For satellite missions involving complex, heavy, or costly 

payloads, cost effectiveness is generally improved by increasing the 

orbital lifetime. The lifetime of an integrally launched satellite 

is limited primarily by the size of expendable supplies such as fuel 

for power and propulsion, film, gas,etc., that can be injected into 

orbit with the selected booster. For a manned satellite, expendables 

such as food, water, and atmosphere and adverse physiological effects 

such as yet unknown effects of zero gravity and accumulated radiation 

dosage further limit the lifetime. In either the manned or unmanned 

case, equipment reliability is also a limiting factor,' although in 

the manned case the test, maintenance and repair capability decreases 

this probability of complete mission failure. Essentially then, 

longer life missions are obtained by larger boosters, increased equipment mean-time-to-failure, and rendezvous. 

At present rendezvous is conceived of as applicable only in 

the manned case. The operations of docking, transferring expendables, 

etc., are too complex to be accomplished completely automatically. 

Orbital rendezvous is advantageous for long life missions requirihg 

resupply of expendables, crew replacement or rescue, and assembly of 

large space objects too heavy to be injected integrally into orbit. 

The cost effectiveness trade-off of increasing booster size versus 

resupply for.satellite missions varies with the value of the payload 

remaining in orbit and the-mission lifetime. 

It has been determined that the expendables section of the 

automatic mode configuration of the baseline MOL can be sized so as 

to evolve into a follow-on configuration with minimum modifications. 

The automatic mode vehicle would be launched as the first vehicle in a 

rendeivous program. The resupply vehicle would consist of the same. 

expendables section mounted as a trailer to the Gemini B. Early in 

the program, a vehicle could be maintained on orbit continuously with 

3 and 5 launches of the mission and resupply vehicles, respectively 

Shown below is a comparisOn of the yearly "take" for 6 

launches per year of the MOL baseline; 12 launches per'year of an 

unmanned DORIAN system; and the rendezvous, approach for which the 

recurring cost per year would be lower than the other two approaches. 

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Comparison or Different Approaches 

To Meeting DORIAN Mission Requirements 

Follow-On 

Program 

12 Unmanned 6 MOL Baseline. (Cont. on-orbit) 

Flights Flights • (3 AMV 5 RRV) 

Total Number of 

Clear Photographs/ 

Year 17,500 9,700 * 20,500 * 

Total Number of 

Clear, Special 

Photographs/Year 636 1,056 2,070 

* 10% for weather improvement, assuming that the crew concentrates 

on active target indicators. 

It can be seen that, in addition to being lower in operational costs, 

the rendezvous system returns considerably more technical intelligence. 

The payload capability of the rendezvous and resupply vehicle 

on the T-III 7-segment booster would permit launch of the ground 

resolution sensor. In addition to providing improved performance and 

economics, the rendezvous system has the following attributes: 

1. Simple evolution from baseline program; 

2. Minimum development risk for resolution sensor; 

3. Continuous, on-call, operational capability. 

4. Maximum acquisition rate and readout of special intelligence photographs; 

5. Minimum recycle time (as low as one day) to photograph 

specific targets; 

6. Continuous, on-call, multi-mission sensor capabilities; 

7. Maximum returns of technical intelligence at moderate 

operational costs. 

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