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6 June 1969 

To: W. C. Williams 

Subject: MOL STG Paper 

Here is a rough draft copy of the MOL/STG paper prepared at 

the request of Lt. Col. Skantze last Monday. Skantze carried 

the data to Gen. Stewart's office Wednesday for coordination 

and he will bring a "West Coast Coordination" copy back here 

on Monday (9 June). 

C. L. Olson 
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MOL PROGRAM PERSPECTIVE 

1.0 MOL PROGRAM BACKGROUND 

1. 1 Development Program 

1. 2 System Growth Potential 

2.0 MOL FOLLOW-ON PROGRAM CONSIDERATIONS 

2. 1 Potential Mission/Payload Improvements 

2. 1. 1 Improved Payload 

2. 1. 2 Enhanced Payload 

2. 1. 3 Advanced Payload 

2. 1. 4 Man's Role in Follow-On Missions 

2. 1. 5 Mission/Payload Summary 

2. 2 Potential Flight System Improvements 

2. 2. 1 Integral Launch Concepts 

2. 2. 1. 1 Improved System (T-IIIM) 

2. 2. 1. 2 Growth System (LDC- 1) 

2. 2. 2 Resupply Concept 

2.2. 2. 1 Baseline Hardware Derivative (T-IIIM) 

2. 2. 2. 2 Advanced Subsystems Concept (T- IIIM) 

2. 3 "Test-Bed" Applications To In-Space Development 

2. 3. 1 Integral Launch Options 

2. 3. 2 Resupply Options 
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3.0 POTENTIAL APPLICATIONS OF FUTURE SPACE TRANSPORTATION 

SYSTEMS TO MOL 

3. 1 Background 

3. 2 Primary Questions Concerning MOL Role In STS 

3. 3 Possible Role in STS Operating Concepts 

3. 3. 1 Reuseable Logistics Vehicle (RLV) Resupplying An 

Orbiting Mission Module (OMM) 

3. 3. 2 Integrated Mission System (IMS) 

3. 3. 3 Space Based Operations 

4. 0 

3. 4 Studies Needed 

IMPORTANT FACTORS IN POSSIBLE MOL/ STS DECISIONS 

4. 1 Timing.:Considerations 

4. 2 System Cost/Coverage Considerations 

5.0 CONCLUSIONS 
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6 June 1969 

MOL PROGRAM PERSPECTIVE 

1.0 MOL PROGRAM BACKGROUND 

1.1 Development Program 

The Manned Orbiting Laboratory (MOL) Program was approved 

in August 1965 with the following objectives: 

O Provide operational intelligence collection at a 

resolution of 

0 Provide knowledge of the nature and value of the 

critical contributions of man to photographic 

reconnaissance and to other military related 

space missions 

These objectives have been reaffirmed by succeeding 

Secretaries of Defense and Air Force and reviewed by the 

President in May 1969. 

The basic mission of the MOL system is to gather technical 

intelligence from near-earth orbit. This is accomplished with 

a 8500 pound, 70 inch aperture focal length, optical 

system operated by a two man crew. The optical system will 

be capable of achieving a photographic ground resolution of 

from an altitude of 80 N. Mi. 

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The MOL Program is currently progressing well. It is 

totally defined, and all engineering is understood and in 

being. The Program is meeting all schedule dates, and 

detailed test results of critical components indicate that 

system performance specifications required to meet the 

resolution goal will be met or exceeded. With regard 

to the manned objective, experience to date has increased 

insight into man's ability, providing high confidence that man 

will not only make a substantial and quantifiable contribution 

to photographic reconnaissance but to other related military 

missions as well. The MOL Program is currently on schedule 

to achi_eve the first manned "all up" launch in July 1972, with 

an additional 3 manned flights to follow at 6-month intervals. 

The schedule and approved MOL funding are as indicated below. 

Table I 

MOL Funding 

Fiscal Year 70 71 72 73 74 

Launches 1 2 1 

Funding $M 525 640 550 397 136 

Achievement of all MOL Program objectives is highly 

predictable, and the system will provide a dramatic increase 

in the quality and value of satellite reconnaissance. Performance 

of the MOL crew will establish a wealth of basic understanding, 

in quantative terms, of what enhancement and flexibility man can 

bring to military space operations. 

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1. 2 MOL System Growth Potential 

In addition, the basic MOL hardware can provide an impressive 

potential for performing other military space missions, either 

with complementary payloads to the basic photographic mission 

or as completely alternate missions. Furthermore, the 

existence of a highly sophisticated space qualified manned 

laboratory can provide a test-bed capability for intensive 

in-space development of advanced military space systems. 

Therefore, on the basis of this emerging DOD manned space 

system, MOL provides a singular program opportunity to 

exploit not only the basic photographic reconnaissance mission 

with significant improvements, but also to provide DOD with a 

highly flexible means of achieving in minimum time a wide 

variety of other military space capabilities, both manned and 

unmanned. 

2. 0 MOL FOLLOW-ON PROGRAM CONSIDERATIONS 

Alternative avenues of growth capability have been defined for the MOL 

program. These have emphasized improvements in system operating 

costs, mission flexibility and performance, and effective utilization 

of man's unique contributions. Future development options in mission 

equipment, MOL operating modes, and flight system modifications 

have been appropriately combined to afford smooth and evolutionary 

transitions, on a timely basis, from the "baseline" development 

program. 

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2. 1 Potential Mission/Payload Improvements 

The Dorian equipment aboard MOL is capable of accomplishing 

a variety of DOD near-earth space missions. The MOL system 

would continue to perform its basic technical intelligence task 

but would also perform such missions as: crisis management, 

strategic, tactical, and general reconnaissance, economic 

intelligence, And, 

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should a future arms control treaty be signed, the MOL would 

be a valuable asset in monitoring the compliance of other 

nations with the terms of the treaty. This capability to perform 

• additional missions is achieved by operating the MOL vehicle 

in a rage of orbital altitudes from 70 to 400 N. Mi. and through 

modifications of the basic flight system and optical payload. 

In addition, the mission data could be made available in near 

"real-time" with the addition of a simple wide-band data readout system to the MOL. The mission capability can be further 

extended by incorporating additional payload elements into the 

MOL system. This evolution of MOL mission capability is 

summarized in Figure 1. Note that optical enhancements could 

be applied to the "baseline" Dorian or a "growth" system, and 

true multi-mission capability is inherent in the MOL growth 

concepts. 

Z. 1. 1 Improved Payload 

Recent industry studies have indicated that the Dorian 

system resolution can be increased to from 

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80 N. Mi. by modification of the tracking mirror, 

reducing the optical 

obstruction, improving the optical formula, and incorporating a central field relay lens to selectively 

double the focal length. Reducing the optical obstruction 

also yields a considerable resolution improvement 

against ground targets with a scene contrast below 2: 1. 

Special films (color, IR), used with the improved system, 

could produce ground resolutions of These 

improvements are estimated to require less than $50M 

to accomplish. The weight penalty for the improvements 

would be approximately 500 pounds. 

2. 1. 2 Enhanced Payload 

By changing the optical path of the Dorian system to 

allow additional sensor access to the image, a variety 

of infra- red and electro- optical devices can be utilized. 

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Since large, Dorian-class optical systems have limited 

fields-of-view (1° or less), a small camera providing 

good resolution with wider coverage would be of value 

in photographing "area" targets or clusters of "point" 

targets. A 10 inch aperture camera could yield 2. 5 foot 

resolution and a field-of-view in excess of 4 degrees 

(depending on film format and focal length). 

Precision targeting missions could be performed from 

the MOL by adding a small ranging laser device to 

accurately determine slant range. Such a slant range 

determination coupled with precise angular data obtained 

from a special geodetic camera could provide ground 

target position data accurate to_in latitude and 

longitude coordinates and_in altitude. These 

varied payload enhancements are estimated to cost 

approximately $30 million to develop (in addition to the 

"Improved Payload" cost) and would require about 600 

pounds of additional equipment. 

A near "real-time" mission capability can be achieved 

throught the addition of a wide-band data return system to 

the MOL. This system could operate in either the radio 

or optical spectrum and transmit to- earth direct or via a 

relay satellite. Typical of such systems is an X-Band 

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device capable of transmitting about 60 sq. in. of 

120 1/mm encrypted pictures/day direct from the 

MOL to earth or approximately 4, 500 sq. inches/day 

via a data relay satellite. The estimated cost of a 

MOL wideband system is $30 million, and is applicable 

to several alternate methods of wide-band data transmission. 

2. 1. 3 Advanced Payload 

The MOL mission equipment module volume is 

sufficient to allow the Dorian system to "grow" to 

approximately in aperture. Enhanced with 

a variety of sensors, such a system would weigh 

approximately 18,000 pounds. From 80 N. Mi. the 

system could achieve a photographic ground resolution 

However, the system could 

also be flown at 100 N. Mi. and still surpass resolutions 

achieved with the basic Dorian equipment. Such a 

growth version of Dorian could be incorporated into 

the MOL system during the post-1,975 time period. The 

MOL could then operate at higher altitudes more 

economically and with longer mission durations,and 

occasionally dip to lower altitudes to achieve maximum 

resolution. 

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Similarly, in the 1980 period a very large optical 

system ■ could be introduced. 

Rom 80 N. Mi. the system could achieve 

photographic ground resolution; or 

could be obtained from 160 N. Mi. While the 

system appears near the current state-of-the-art, the 

device would require extensive development. Such large optical systems are viewed as distant 

or "ultimate" goals in the planning of MOL growth. 

In addition to optical systems, MOL Advanced Payloads 

could also include radar and elint packages. Radar 

would give the system an capability. 

In the post- 1975 era, radar resolutions of-or 

better may be achievable. Radar could be used for 

arms control, crisis management, and surveillance 

missions. Elint devices aboard MOL could be used to 

locate active RF targets of interest. 

2.1. 4 -Man"s Role In Follow-On Missions 

Man's role in follow-on operations will continue to be 

that of "mission director" aboard the spacecraft. He 

will select sensors, acquire targets, point and track 

with the payload elements, select data for near "real-time" 

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relay to earth, and maintain critical instrument 

adjustments. Advanced payloads aboard MOL will 

generally have narrow fields-of-view. Therefore, 

a target complex will be divided into a collection of 

individual "aiming points". The crew will study each 

point to determine if the target is active or inactive 

and direct the sensor to those "aiming points" with the 

greatest intelligence value. Such crew activity will 

maximize the intelligence yield of each MOL mission. 

2. 1. 5 Mission/Payload Summary 

In summary, the long term goal of the MOL system is 

growth to a "general purpose" multi-sensor reconnaissance vehicle capable of accomplishing a variety of 

missions on demand. Representative follow-on mission 

and payload groupings are illustrated in Figure 2. 

2. 2 Potential Flight System Improvements 

Alternative means for achieving improvements in MOL system 

economics and operational utility have been identified, ranging 

from simple product upgrading of the basic vehicle system to 

more extensive modifications required for extended orbital 

operations. Characteristics of most likely flight system options 

for future MOL growth are summarized in Figure 3. Each 

flight system illustrated is also capable of operation as an 

orbital test-bed for development of DOD and NASA advanced 

mission equipment. 

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2. 2. 1 Integral Launch Concepts 

Favorable atmospheric conditions predicted for the 

Post- MOL development program period, along with 

modest uprating of T-IIIM capability, would permit 

addition of orbiting vehicle expendables sufficient for 

a 45 day mission. Orbital duration extensions beyond 

60 days, or significant increases in discretionary 

payload, could be obtained by enlarging the first core 

stage of the T-IIIM launch vehicle. 

2. 2. 1. 1 Jrnprovec1 System (T- HIM) 

The on-orbit duration of the MOL vehicle can 

be extended to approximately 45 days at 80 N. Mi. 

by expansion of the unpressurized compartment 

and addition of MOL tankage for propellant 

and cryogenic consumables. Such a modification 

could also be flown at 70 N. Mi. for 30 days or 

at 90 N. Mi. for about 90 days. Low cost modifications to the T-IIIM booster have been identified which yield adequate launch margins for 

both orbiting vehicle and payload improvements. . 

The improved MOL performance characteristics, 

including payload modifications previously 

discussed are summarized in Figure 4. Potential 

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steps toward attainment of the improved 

system performance goal are itemized in 

Figure 5, along with estimated development 

costs for each. 

MOL improvement options could be available 

within thirty- six months following ATP, and 

would afford a 50% increase in data quantity 

with up to 30% improvement in data quality. 

Estimated total cost run-outs and flight 

schedules for a typical five year program are 

shown in. Table II. 

Table II 

Block U EDMOL 

FY 70 71 72 73 74 75 76 77 78 

CY 70 71 72 / 73 74 . 75 76 77 78 

Schedule X XX t X X X X 

NR $ M 10 20 40 40 30 10 

R $ M 8 51 177 356 420 412 369 243 

Totals 10 28 91 217 386 430 412 369 243 

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79 

179 

X X 

64 

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2. 2. 1. 2 Growth System (LDC- 1) 

Substitution of a fifteen foot diameter core 

first stage in the T-IIIM would result in a 

nominal payload increase of 14, 000 pounds. 

This additional payload capability would 

permit orbital durations in excess of sixty 

days with the improved MOL payload and 

modified laboratory vehicle.. The operational 

options attainable by various off- loadings of 

this configuration are shown in Figure 6. 

(Eventual deployment of an advanced optical 

system, capable of resolution 

would also be possible with 

this MOL option. 

The growth system alternative could be 

available within 36 months from ATP. The 

estimated development costs for this system 

total $320 million of which $170 million is 

attributed to laboratory, vehicle modifications, 

$50 million to mission payload improvements, 

and $100 million booster changes. Estimated 

total cost run-outs and flight schedules for a 

typical five year program are shown in 

Table III. 

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1 I 

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FY 70 71 72 73 74 75 76 77 78 79 

CY 70 71 72 T 73 74 75 76 77 78 

Schedule X X X X X X X X X X 

NR $ M 10 40 85 85 80 20 

R $ M 8 52 181 364 430 422 378 249 66 

Totals 10 48 137 266 444 450 422 378 249 66 

2.2.2 Resupply Concept 

An attractive option for increasing discretionary payload 

capacity and obtaining long duration orbital operations 

is available throught the rendezvous /resupply approach 

with continued use of the basic T-IIIM launch vehicle. 

This mode would entail periodic crew rotation and logistic 

replenishment of a MOL rendezvous initial vehicle (IV), 

by a rendezvous resupply vehicle (RV) consisting of 

rearranged MOL hardware elements. 

2.2.2.1 Baseline Hardware Derivative (T- IIIM) 

The resupply concept consists of a orbiting 

vehicle, launched initially unmanned to the 

operational orbit and subsequently manned 

with a resupply logistics vehicle at regularly 

spaced periods. The resupplied spacecraft 

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can be used for continuous year-round mission 

operations economically since the optical payload 

is kept on orbit for very extended periods. 

By specific tailoring of the resupply expendables, 

propellant can be made available to permit 

frequent, repeated on-call reconnaissance of 

any desired area. 

Derivation of the resupply system from basic 

MOL program hardware segments is illustrated 

in. Figure 7, along with a functional description 

of the orbiting mission module and resupply 

vehicle spacecraft. 

Outstanding features of this growth alternative 

include optional operation in intermittent or 

continuous, manned or unmanned modes; plus 

the capability of adding additional sensor payloads 

which will permit multi-mission operations. 

Major characteristics of the resupply system 

concept are summarized in Figure 8. 

This system concept could be available in four 

years, at a total estimated:development cost of 

approximately $800 million. This consists of 

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$50 million in payload improvements, $350 

million in resupply vehicle development, 

$250 million in laboratory vehicle modifications, 

and $150 million for an additional launch 

facility and associated AGE. Estimated 

total cost runouts and schedules of a five 

year program are shown in Table IV. 

Table IV 

RESUPPLY OPTION 

FY 70 71 72 73 74 75 76 

CY 70 71 72 73 74 75 76 

Schedule X 6 6 X 

NR $ M 10 105 174 207 221 83 

R $ M 10 54 168 

4. 

344 397 392 

Total 10 115 228 375 565 480 392 

A 

348 

348 

77 

77 

3 

78 

234 

234 

78 

79 

79 

63 I 

63 

X Initial Vehicle 

Resupply Vehicle 

2.2.2.2 Advanced Subsystem. Concept (T- IIIM) 

A substantial reduction in the resupply expendables 

required, could be achieved by the substitution of a" 

power system for the Baseline 

cryogenic/fuel cells. By utilizing the weight saved 

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for additional propellant and discretionary 

payload, less frequent resupply would be 

required with attendant reduced operating 

costs. 

2. 3 ''Test Bed" Applications For In-Space Development 

2. 3. 1 Integral Launch Option 

The unique capability of the MOL system for test bed 

applications can be readily made available for potential 

NASA and DOD system developers at modest cost. Orbital 

durations up to 90 days are possible with the integral 

launch system. Extended operations in the neighborhood of 1 year can be obtained through the resupply 

option derived from MOL hardware. 

Crew size, pressurized compartment volume, and 

available discretionary payloads, in a variety of 

combinations is possible, depending on choice of 

operations or, missions desired. Figure 9 depicts 

two "test bed" vehicle concepts, integral launch and 

resupply systems; identifying general system characteristics 

and basic types of development testing that could be 

performed in these operating modes. 

Estimated cost to the user for a basic 30 day MOL, 

less payload elements, is approximately $142 million 

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per flight launched from WTR. 'Use of this vehicle 

would entail an initial cost for modifications of 

approximately $69 million. Extended duration modifications 

costing an additional $125 million would permit integral 

launch vehicle operations for periods up to 90 days 

on-orbit at a unit cost of $150 million per flight. Cost 

runouts and schedules for the acquisition phase and 

delivery of the first flight system are displayed on Tables 

V and VI for.the 30 day and 90 day systems respectively. 

Table V 

30 DAY VEHICLE TEST BED OPTION 

FY 70 71 72 

CY 70 71 

Schedule 

NR $ M 20 '23 

R $ M 5 22 

Total 25 45 

Table VI 

90 DAY VEHICLE TE=STBED OPTION 

FY 70 71 72 73 74 75 76 77 78 79 

CY 70 71 72 73 74 75 76 .:77 78 79' 

Schedule X 

NR $ M 10 38 55 54 53 14 

R $ M 5 23 53 59 

...........--.------ 

10 

Total 10 43 78 107 112 24 

72 

I 73 74 

12 

50 

62 

73 

56 

65 

9 

74 

X 

14 

75 

9 

75 

76 

76 

77 

7 

78 

78 

79 

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Operations at ETR are possible with addition of some 

facilities at KFC. An attendant increase in discretionary 

payloads of approximately 20% can be derived from this 

option. 

2. 3. 2 Resupply Options 

The resupply concept cost varies with requirements 

for crew size,' pressure compartment volume, and 

operational site selection. A basic two crewmen system, 

using the single compartment Laboratory (Initial Vehicle), 

less military payload element, is approximately $172 

million for Laboratory Vehicle and $110 million for the 

Resupply Vehicle launched from WTR. Cost of modifications 

to the Laboratory vehicle for one year on-orbit life and 

the repackaging/development of the Resupply Vehicle is 

estimated at $300 million. 

Additional pressurized compartment volume to support a 

crew size of four would require an additional $110 million 

in engineering development and flight test. For operations 

from ETR, certain additional launch site facilities would be 

required with an estimated cost of $120 million. These 

options can provide increased test capability and discretionary payload if desired. Cost runouts and schedules 

for system acquisition and delivery of first flight article 

are displayed on Table VII.. 

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19 

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FY 70 71 72 73 74 75 76 77 78 79 

CY 70 71 72 73 74 75 76 77 78 79 

Schedule Xo 

NR $ M 10 67 80 63 60 20 

R $ M +1,ii. 

6 

3 

26 

10 

61 

36 

68 

53 

11 

8 

Total 10 76 116 160 181 39 

X Initial Vehicle 

A Resupply Vehicle . 

3. 0 POTENTIAL APPLICATIONS OF FUTURE SPACE TRANSPORTATION 

SYSTEMS Tei MOL 

3.1 Background 

It has become increasingly clear that space transportation costs 

may constitute a limiting factor on the amount and type of space 

exploratory activities which may be undertaken in the future. 

The search for a more favorable plateau of space operations 

costs has recently stimulated significant studies, by both the 

NASA and the DOD, of concepts for economical transportation 

systems which will operate between Earth and future space stations. 

3.2 Primary Questions Concerning MOL Role In STS 

The potential development of a National space transportation 

system could offer significant advantages to future MOL mission 

operations in terms of reduced costs and increased mission 

flexibility; also, the imposition of future MOL requirements 

on such a system design could entail large impact on system 

selection. Since space transport concepts which exhibit low 

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potential operating costs will require development funds 

totaling many billions of dollars and development time spans 

approaching a decade, the central question concerns the degree 

of involvement which is appropriate to the MOL program and is 

justifiable in view of available, well defined, near-term program 

growth options. 

Subsidiary questions concern the relative desirability of various 

potential operating modes for the MOL mission with each of the 

space transportation systems currently proposed by DOD and NASA. 

These questions bear upon the relationship between the MOL 

payload module and the reuseable transport vehicle, since the 

flight configuration and operating mode eventually selected would 

have a most pronounced influence on required MOL payload 

modifications and on the adaptability of a MOL/STS system to 

future growth mission needs. Converseley, it is not evident 

that a space transport system designed primarily for efficient 

conduct of advanced manned multi-sensor reconnaissance missions 

could be utilized satisfactorily by the predicated large population 

of users with widely varying requirements. 

Informed answers to these questions must await adequate study 

of at least the MOL/STS operating concepts summarized in the 

following section. 

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3. 3 Possible Role in STS Operating Concepts 

The wide range of flight system concepts which are currently 

under consideration by NASA and DOD for potential space 

transport applications gives rise to an even more extensive 

matrix of possible MOL/STS operating modes. Some of these 

modes are illustrated in Figure 10 (along with the MOL growth 

family. Three major classes of operating concepts are 

summarized below. 

3. 3. 1 Reuseable Logistics Vehicle (RLV) Resupplying An 

Orbiting Mission Module (OMM) 

One attractive mode would entail orbiting a MOL mission 

payload module (OMM) which is capable of operating 

manned or unmanned and is storable on orbit, and 

supplying crew and expendable requirements with a 

comparatively simple reuseable logistics vehicle (RLV) 

of 10, 000 - 12, 000 pound discretionary payload capacity. 

This mode of operation is similar to that described in 

section 2.2. 2. , with the added feature of resupply vehicle 

reuseability. 

3. 3. 2 Integrated Mission System (IMS) 

An alternative operating mode would envision installation 

of a complete MOL payload and supporting equipments in 

a relatively large and complex reuseable flight system. 

If the operating mode involved ejection of the MOL 

payload and supporting equipment on orbit, with subsequent 

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autonomous functioning of the payload module, the required 

discretionary payload capacity would range from 40, 000 

pounds to 50, 000 pounds. In an operating mode based 

upon full functional integration of the MOL mission payload and flight vehicle system the required discretionary 

payload capacity would be in the 25, 000 pound to 35, 000 

pound range. 

3. 3. 3 Space Based Operations 

A third potential mode of future operation, contingent 

upon availability of a national orbiting space facility in 

,near polar orbit, would entail operation and support of 

a MOL module from the space station, either directly 

or through use of orbit-to-orbit shuttle vehicles. 

Possible advantages of this operating mode are presently 

unclear. 

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3. 4 Studies Needed 

The impact of MOL requirements on detail selection of a future 

multi-user national space transportation system is expected to 

be profound. Additionally, the potential future availability of 

a low cost flight system could exert a strong influence on the 

direction of MOL near-term follow-on program plans. Extensive 

and in-depth studies are required to assess the relative utility 

.of the potential flight systems to future MOL operations, and to 

place them in clear context with current MOL evolutionary growth 

concepts. 

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4. 0 IMPORTANT FACTORS IN POSSIBLE MOL/STS DECISIONS 

4. 1 Timing Considerations 

Under the most optimistic circumstances which might attend 

development of a future National STS, a hiatus in manned 

military space flight of three to five years would follow the 

conclusion of the currently programmed MOL flights. This 

gap is illustrated in Figure 11. Since it is clearly in the 

national interest to continue the MOL reconnaissance mission 

during this period, a minimum MOL- continuation budget 

requirement of 400-500 million dollars per year can be predicted. 

The forty-five month lead time associated with any MOL follow-on 

alternative indicates that some funds for such commitments must 

be allocated in FY 1970. These considerations, taken along with 

the evident trend toward reduction of space operations funding, 

would appear to limit any incentive for MOL consideration of 

advanced space transportation system development at this time. 

4. 2 System Cost/Coverage Considerations 

Figure 12 furnishes a brief description of the flight systems which 

form the basis for Potential MOL Program Alternatives Cost 

Summary contained in Figure 13. The latter figure displays 

total estimated additional MOL costs for nominal ten year 

operational programs in terms of percent of annual orbital 

coverage time desired. Flight systems included for comparison 

are the three MOL evolutionary derivatives and three generic 

candidates for future space transport applications. All estimated 

HANDLE VIA BYEMAN 

CONTROL SYSTEM ONLY 

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Page 24 

costs include development and operation at a launch rate defined 

by the indicated coverage requirements and by the flight system 

characteristics. Payload integration costs are included in each 

system estimate. 

The system cost summary shows that the most economic operation 

for coverages up to two months is provided by either of the 

integral launch MOL derivative systems. For coverage requirements between two months and seven months per year, the MOLderived resupply system is least costly. (The reuseable resupply 

system is excluded here due to high development cost.) The 

advanced reuseable system concepts would provide the most 

economical operation only if near-continuous orbital coverage 

over the nominal ten year period were the criterion. 

It is clear from the cost summary data, however, that availability 

of an advanced transportation system at limited acquisition cost 

to the MOL could result in future significant operating cost 

savings across the entire coverage spectrum. Therefore, MOL 

requirements should be given full consideration in system 

formulation if a National space transportation system development 

is authorized. 

5.0 CONCLUSIONS 

5.1 MOL is a viable and unique program which will develop the 

potential of man's contribution to current and future military 

space objectives. 

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ANDLE VIA BYEMAN 

5. 2 The MOL system forms a keystone upon which DOD space goals 

for the next decade should be constructed. As such, it merits 

high priority funding consideration with respect to competing 

National. programs. 

5. 3 The MOL System has growth potential to achieve a "general 

purpose" multi-sensor capability. A wide range of realistic 

future missions can be achieved with minor modifications to 

the basic MOL payload. 

5. 4 The MOE, flight system elements can be operated in a variety 

of modes consistent with future DOD mission demands, improved 

operating economics, National manned space flight goals, and 

early availability requirements. 

5.5 Deployment and operation of MOL mission payload elements 

with proposed reuseable space transport systems of the late 

seventies time period could offer significant reductions in 

annual operating cost. 

5. 6 In view of the available, well defined near-term MOL growth 

options, and of the stringent current funding environment, it 

does not appear justifiable for the MOL Program to consider 

sharing development costs for a future space transportation 

system. This conclusion is amplified by the funding commitments required to ensure continuation of the MOL reconnaissance 

capability in the post-baseline period. 

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5. 7 A study is needed to define MOL follow-on requirements in the 

context of manned and unmanned MOL evolutionary systems and 

of the program impacts which would result from potential 

availability of a National Space Transport System. Scope 

and depth of the study should be such as to permit formulation 

of a comprehensive manned military space plan, including 

defined responses to a range of possible National decisions 

for future manned space systems. 

BIF- 107- 50241- 69 

Page 26 

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