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-,c MEMORANDUM FOR THE DIRECTOR DEFENSE RESEARCH ACRD' ENGINEERING 

4 

t•a ' SUBJECT: Manned/Unmanned Comparisons in the MOL 

mmm=mmi' 4,3 

z... 

I-. Your memorandum of April 6, 1966 requested that- a study 

be made to compare the specified manned performance of the 0%. CK MOL reconnaissance-intelligence mission with the estimated 

performance of an independently-developed unmanned system. 

mememe The MOL design provides for both modes of Operation, but permits 

....... taking advantage of the man in the .system during orbital testing, 

mftmw=m 

- anj in follow-on operations for as long as this proves necessas 

cc- acsira'cle. In order to provide as detailed and valid a baiii 

--, fc..:. comparison as possible, a separate two-contractor study was 

fl.,hded based upon taking the MOL mission module as governmel* 

furnished. The results of the contracted and supplementary 

in-house studies'appear.in TAB A. 

. NIONIallmolwas. 441 

mooNolowamoma 

You asked that four particular ppints be considered ir.. this 

coz.parison. The pertinent background and study conclusions o 

each of these particular points isk.as follows: 

1. (Configure the wholly unmanned. system and its 

method of operation to provide the same quality and quantity-0 • 

reconnaissance-intelligence Information as the MOL. 

There are two significantly different ways in 

which equIvalencepf the two systems-may be considered:.'the 

WOUla be to design the unmanned - system for eoual apacec:?aft weight in orbit;the second- Would be to design the 

=an:led system for'Mission life .equal to the marred : MOL (30 

days). The first-Of these wayd wouid:,lead to. a vehicle riot: 

gl'aatiy different from the VOL ;r1ow-4 without al= in the auto 

mapic _,.ode. The potential mission` wife of.this system - would 

6C days. At the present time the longest orbital lifetime 

at-J.empted and achieved for a coililex(Pointing) reconnaissance 

sy3tam. is 8 days,- achieved on the thirtieth flight'of the 

system. GAMBIT-3 in itg:initial cOnfigurationalso :flax 

cn life but is Wogrammedtp,,achieve 16-day life at ,s:b.6,#, 

;he thirtieth flighi, which is::ichidUled to occur at. first abCV-6 

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the time of the MOL flight. In general, Ni0 experience has 

been that increased lifetime in orbit can be achieved without 

undue risk by incremental improvements injiardware and.soft- 

•• ware based ,on flight eXperienCe. • • 

. .• 

It was therefore not deemed realistic to project 

mission lifetimes muchlpeyond thirty clays for the initial 

operation of a new system in 1969-70, and the contracted studies 

vere focused on the 30-day untanned System.' However, on the: 

basis of these studies And the comprehensive data available on 

V. MOL in the Unmanned mode it was possible to. derive reasonably, valid data on an independently developed unmanned system 

:)0 days orbital life and this data is included herein. It is 

estimated that the 60-day orbitallife Would be attainable 

about three years after initiation OfOperations.withJA:neW. 

30-day system, assuming that provision had been made for this 

.growth in booster capacity, inherent subsystem life, qualific&-

tor testing, and expendables capacity%' 

2. (Assess the -difficulties and risks of obtaining 

equal intelligence content with the wholly unmanned system and 

determine the development and operating costs to achieve it. 

• Although We have included in the .mdssionmbdule 

of MOL (which would be used in either the automatic version of 

MOL or in a completely :unmanned configuration) automatic devices 

which potentially can !-give the same resolution unmanned as 

roanned, many ofthese:devites:haveeitherneverbefore been 

in orbital reconnaissance systems or represent large ektrapolations in precision, accuracy or Other :Capabilities. While' 

we believe they can ultimately be made to perform reliably 

- within desired tolerances-, we Are atthis:time by no means 

certain as to,hOW long:it might take to Achieve-this result. 

For this reason; we aSSess:the- risk of early achievetentOf 

resolution to be Considerably greater with an unmanned 

vehicle. To the extent that man's participation in the deVelop 

. ment proves to be effective, the resolution unmanned 

capability should be achieved ,earlier in the automatic mode Of 

MOL. 

•, • , - • 

Intelligence 6nterit, however:, isnot restricted 

consideratiOn:of resplutiOn. A second factor is the ne-t'!d:to 

-.)hoo3ranhtargets nObscured by'clbudttince th*:Soviet weather 

on -Lhe average phlyzabout:50:Dercent:4oud, free., :Procedures 

for weatner avoidance also contribute 

to iacreased inteliigenbe:oUtput per tdstidn, We have been.' 

examining the ways in which thaweather..factori may be compensated 

• . - - 

• - • 

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by sensing the weather ahead and taking corrective action and 

by verification of successful cioud-;free:coVerage of high 

priority targets sothat other targets may be programmed in 

successive passes.:It is iMportant to reCognite that these. 

functions may either be performed by mar•Cor:byHadditiond“Uto7 

vatic devices. .However it ls difficult,to assess from:grOUnd 

analysis and simulation alone what real benefits maybe obtained.; 

Our estimates range between 5 and 30,percent improvement 

cloud-free photographYfrem weather avOidance and verification 

procedures which are disCussed in TAB C. In view of the Uncev. 

ts.inties .conneztetiv4th the :.proper 'IMpieme,Y4tation of these 

tAce'ez OA 

i$ Zs.avi4 o.tw 

d,;) •- 

this time for automation Of- this,function.:.Boweermanual 

eNperimentatiorCand execution of this function in the early MOL 

flights Will prOvi*a_basi“or'eValuatioa and design. of suitable 

automatic devices for one or:0th ofthesefunCtions. These ._ 

devices could be incorperatedaater if-this proVes.tO be desirab 

A,third.element involved in: maximizing the 

ligence content of a mission has to do with selectively choosing 

those targets which are likely to inelude objects of highH 

intelligence value. If thelnatUre of these targets is such 

the presence Or absence of intelligence Objectives may be 

transitory (such::aS:;missiles on pads :or launchers) target 

selection cannet',beMade:- tOMAxiMiieintelligence content by 

pre-programming.; GrdUnd-SiMulationa:haVe indicated that MOL 

astronauts lo4inghead:to adternatiVetargeta c_ r 

acouisitiOnand targeting ieleseopea:May:b able -!,:o recOgnize:the 

presence of objectives with high:latelligence value at .a` target,. 

local .on. HoWevet; this again IS very:difficult to: establish 

',ground simulation (although more TealiSticsimulation ray be. 

'possible from very high. altitude aircraft)... Our estimates of the 

oPportunities for astronauts to increase thesespecIal high vz3.ue: 

technical intelligence 'outputs of a.mission indicate that faCtorS 

of between two and three May;be attainable. ,Theaffect or, the 

-total number of phOtogtapbOaken o_ total nuMber of targets 

covered during a MissiOn is negligible: This is posaible:beeaus 

the frequency with Which theietranaitoryinteiligence:gathee 

opportunitieS oeCurISrelatively lOw.;t6:percent - of the;timelbr 

a TeoresentatiVe sampling of thetargett.. ThiS is diadUised 

further in Attachment-d. 

3. .(Compare the Wholly-Uamanned system performance:.: 

the expected performanCe of:the unmanned version Of. the 'MU' as' 

evolved from the maimed: 

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4. (A. comparison should be drawn between the operatonal effectiveness of the two approaches. .) 

. As inaidated above, our studies of an unmanned', 

DORIAN system considered'a,30-day'nominal mission and a 60-day 

:loMinal mission.' The formerwould- b“aunehed by a 57segment 

while the latter would employ the 7-segment bow:Ler' 

ilar to the configuration beingPlanned for MOL. The oG-day 

mission was found to be more economical than the :30dayMiSSicing• 

poviding that the component reliability can be developed to 

acceptable levels. in:.dithor caso, the abserlee of man inilieased 

tilo development- risk and we have. estimated that A 10Uriell•tQAt 

proi;ram in the operational configuration mould be a necessity 

(see page 5 of TAB A) For oomparison,our.,planning for GAMBIT 3, 

a considerably simpler•SYst,e#, is for eight'develoPMen“lights 

, • • , : - . . 

The new developments needed to automate the system present 

an added risk during the-orbital testingphaseSOme,fUnctions, 

involving important new components'are 

• • 

Image ;motion compensation across-thelormat 

• 

Highly accUrate'•(.05 perdent) image motion sensing an 

:compensation • 

Focus - sensing 

_ . 

Remote optical:alignMent 

PrecisiotealtotatiO:naVigation 

A discussion Of the ne“eaturesappears in TAB C. All of these 

features are planned for automatic operation :during both manned 

and unmanned flights.;' the:man: will, however, be able to override 

or compensate for most of the failure modes envisioned for tins 

equipment. Out-of-specification performance in any of these 

functions cat. defeatthe objectiveof:proviaing resolution. The presence of...:4Man during the orbital development 

period not only mill•ehabIe us to intrease'the:OutpUt,::and cUality:„ 

of reconnaissance data acquired- inthls:periodbUt will assist 

In identification and correction of' equipment deficienCies.: 

• • _ 

The development cost of the 607dsyunthanne“ORMN-Is 

'estimated to be $150'billion:. The 30-day_syntem:voUldeOst 

about $1.13 billion. :The estimates are based upon appraisals 

.varying between 95 pet-cent and 105 .percent of the quoted figures, 

'depending upon'ludgmenis relating.tothe degree of difficulty in 

DORIAN/GAMBIT. 

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the development. TA3 A provides a b;eakdown of these costs 

(TAB A, Page 9). A comparison may be drawn. with GAMBIT 3, in 

which the developient cost, including the eight development . 

rlilhts, is at present estimated to be the weight 

the GAMBIT 3 on-orbit yehicle is correspondingly 1/3 that of 

f -- 30-day unmanned DORIAN. 

The recurring cost of the 60-day system would be about 

09 million and the recurring cost of the 30-day system would be 

about $45 million. 

A comparison with cost, on-orbit weight and lifetime of 

predecessor surveillance systems is of interest.. 

$/DAY* ON 

WEIGIO DAYS ON ORBIT 

SYSTEM ON ORBIT ORBIT (MILLIONS 

:GAMBIT 

GAMBIT 

GAMBIT 

• FLIGHT COST 

NUMBER (YET7JONS) 

1-25' 

26-29 

30 

GAIT 3 

GAMBIT 3* 

1-8 

8-23 

GAMBIT 3* 24 

• MOT:- 

Manned* 

MOLUnmanned* 30 -60 

Unmanned 

(30 day)* 

(DOR IAN 

Optics) 

U=anned1111 

((0 day)* • 

\DORIAN 

Optics) 

'21. 000 

$59 _ 30760 42.0 1 

*Estimates 

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In comparing each system with its predecessor, it, should be 

realized that in addition to longer life on orbit and hence more 

total photographs, the qUality of the intelligence content per 

target in terms of better resolution is steadily, increasing .as 

we go from GAMBIT to GAMBIT 3 to DORIAN. Offsetting this to some.. 

degree is the decreasing field of view which reduces the number 

of, targets in one photographic frame; this is important where 

targets are densely.clustered as in test ranges. 

The latest estimatepf..the development cost of the Trlaunch 

MOL Program is $1.818 billion (see TAB B). At the conclusion of 

the development, the system can be'operated manned or unmanned 

(automatic mode). The automatic mode can have an orbital life of. 

60 gays, subject to the same qualifications on:reliability-stated. 

above for the independent unmanned system., which would cost 

$1.50 billion through development. Compared in this manner, :,the 

differential development cost for including a manned operating 

mode and a manned development program is estimated to be 

$318 million. If the weather compensation potential of the 

manned system is realized to the extent of 20 percent, this di 

ference would be almost entirely offset by the increased 

photography collected during the development cycle. The 

additional benefits of target selection Potential in the manned 

system are not accounted for in any of, these figures. 

Before summarizing the comparisons, it is pertinent to 

discuss briefly the effect of the field of view of the DORIAN 

optical system. Optical systems have a field of view that 

diminishes with resolution, a very significant factor in mission 

planning against various target. models. 'The following table 

presents a comparisaa: 

Width, N.K., Of Area IColf:.ered - p4 

Field of Vieli Photo, Sq.141::' 

180 

90 

5 

System 

GAMBIT 

GAMBIT CUBM 

DO IAN 

The small field of view puts .a premium :on :pointing aCCuracy, : 

requiring accurate .target location end:Veryprecise navigation7 an 

attitude control. 

When pointing accuracies, equipment alignment and. adjustmen 

image motion compensation and tracking can be done unmanned ,, , 

reliably and within design SpecificationZ;.theresOlution results 

- . - 

DORIAN/GAMBIT: 
tit . 

r ' 

;0 iiI7LY • 

of all targets covered during a thirty-day mission are expected 

.to be substantiPlly the same manned and unmanned. 'However, 

because of man's ability to center images of obliquely located , 

targets and to correct for offset errors, introduced by navigation 

uncertainties, man in the system will be able to maintain peak 

resolution performance, particularly for nredesignated targets of 

high significance, while the unmanned system is more likely to 

degrade somewhat, particularly in the earlier phases of the 

program. 

Discussed below are several factors which potentially provide 

the manned system with :a superior intelligence content per &Lyon' 

orbit. 

Target Selection 

One significant potential TUnctiOn:Which'a man may nerfOrM 

is the selection, by real-time inspection., targets ofjaigh value, 

which occur relatively rarely and at random. The competing 

unmanned system Would- acquire them only7byohance and fail therebi 

to take advantage:of a majority of the oPportunities The DO 

optic's field of view Will .cover approximately one7half of a 

12,000-foot runway system. In ordertO:Insure“or instance, tha 

photographs are obtained of militariaircraft parked on the 

perimeters of sucharunWay, One:MUstteither know thAvlocation 

before the mission or in sone manner:Tindthemin real time. ::: :1 

illustrate, a -singleGAMBITor GAMBITCUBED target Can.separate, 

into two or more DORIAN targets because Of the.smOIler fieldof 

view. Not onlydb targets proliferate,fout to insure Maximum 

intelligence content,target SeleCtionbeComes mandatOry. 

plex such as Tyuratam, measuring 50X100-miles and containing 

twelve launch conviex0,S coul4 bitc.:111.tdo more than sixty indiVid 

targets. Tbssetargettare so: lOSe together. that nhOtographS' 

only a few can be takei-02n:a'siniaSS,but .by .intelligent ; 

inspection, the:Operator canSelectthOieWhich contain items 

high intelligencel.intereStOur SttdieS show that marv:oan make 

major contribution:in:this 

To estimate the:usefulness of this function, are"OresentatiVe _ . . 

DORIAN mission WaS analyzed along withoperator-reactiOn tests:O0 

a simulator. Results showed that:creWparticipation in target:- 

seleCtion could yield almost, three tinet asMAny.photographsof 

high-intelligence-v_ altetargets s.S.coUlcibe- taken:byan unmanned 

system on the same miSSion. DetailOarein Representati 

of the operations perfOrmedare: 

.a. location Of significant military- vehicles 

" b. InSpeCtion, ofSpedialradar equipment 

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c. Detection of a silo with en open door 

d. Detection of a missile being transported 

e. Technical.ly valuable view angle of new radar 

This particula-r application of a trained operator on orbit 

is representative of the potential advantage of direct viewing, 

although as noted above further exoeriments are recrUired to fully 

define and delineate such riailneci functions. The Gemini program 

hr.x.s shown that mants' eye is capable of picking out gross ground. 

patterns. Tr:hen adaoted. in MX, through a telescope designed for 

the function, this capability should. translate into a finer and 

raore discriminatory discernment. 

Quick Response Intelligerice from Readout 

Under some circn:astances the value of inte13.1.G.....-:e. 

consid.era"ely enhanced by rapid. coraminica.tion. In those eases 

in which quick response is important., a satellite-borne readout 

system is useful. The MOT, :cendoUt system will be employed:.to 

larovide t.he needed timely information by scheduling photofg.-aphy 

to be performe.d. by the operators using 'a Secondary camera on 

targets Pre-d.esintiated. or selected by theta during the approach. 

1n many cases, the readout •function would. be combined. with target 

selection. The fain. will -De processed on board and the intelligence7 

bearing portion of it will -oe transmitted over the data link. It 

N-rould be possible to, have an alternate .unranned configuration 

- designed. to per-form readout, but an

, entire ,mission would. be consume 

...each time the readout, configurat.ion is flown. The aoss of a regular 

mission could.' be tolerated. only in very ,unusual cases. 

Select On . of Cloud.-Free Targets 

..n a typical irons:rifled mission, the -photogra-chic loss is . 

50 percent from cloud cover alone. In the manned system, the 

operators can employ the SPotting scopes, which will have 'peed 

agaList targets along the pass, to determine which 

tar; e.ts are in the clear 84a, then -orient the main optics for. 

photog:caphing the clear targets. ..An extensive .stagy, performed 

1)y the Government Weather Center, of -3.52,obo frames of IC3-4 

Photography, supplemented by detailed target reporting from la, 

z*.issions, has provided a weather model,whiCh confirms that 

aL ternate mar gets, or, the average .W11,1 . ,be open for Photogravhy 

in a substantia2. percentage :of those.cases in: which the primacy 

is obscured.. 

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Additional Manned. Functions Which Can Improve Intelligence 

Information 

There are several added benefits provided by an operator 

and these are particularly valuable during exploratory experiments aimed at evaluating varied or new techniques. One 

feature, referred to above, is This ability to determine the 

best viewing angle from which a target should be photographed. 

For instance, if he is,approadhing a parked aircraft from the 

rear and the needed intelligence will come from examining the 

fore end, he can wait until ne has passed over and take a 

backward-looking picture. Tie can, on command from the ground, 

place aerial color film, infra-red film or other special films 

in the secondary camera so that their special discrimination 

characteristics can be realized. These special films may be 

of value in camouflage detection or in acquiring information on 

the nature and level of industrial plant activity. Man n=12:- 

process photographs in orbit, edit them and transmit the images 

to the ground. In, conjunction with this capability, ne can 

make judgments and render specific decisions as to the ro2. 

importance of information to be processed on orbit and -tra,. 

mitted to the ground. ' 

These contributions of the man in the system nay pro' t50 a 

• 

substantial increase in the -intelligence value of the 'rnicSion':1- 

Each individual function can, without .exception, be Perf9rme'd 

some automatic system. ,or combination of 'systems but the possibility in the manned system to 'experiment with a wide variety 

of techniques and alternatives is attractive ' and valuable in 

. time and money, lenether or not the-7SnCtiOri. is ultimately per 

formed by man or by automatic devices 

Additional Reconnaissance Capabilities 

During times of crisis, the 'MOL'...System can be tranSferred:- 

from its nominal 80-mile orbit to'anorbit of approximt.?-200, 

tc, 250 miles. In this higher orbit the. System will have access 

%11 targets in the Soviet Bloc approximately once every :three -

days, taking photographs at resolutions .of about The 

c.rew can also employ the acquisition ana tracking scones, with 

resolution of about nine feet, .for intelligence by direct 

viewing. The a.bsence or presence of aircraft, ships' in port 

cargo accumulations, 'parked vehicle-bUild-up and railroad 

r..ctivity are examples of such intellidenCe. The vehicle can 

p'ter orbits of abOut.:40../14les_ after one to twenty4one days, 

still remain in Orbit -thirty days.;permitting daily reportiactivity. of significant' value in- deterMining the :posture .and . - 

state of readiness Of. Soviet -forded:. 

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The foregoing addition:11 reconne.issaziçe capabilities can he-. 

accomplished with essentially no change to the baseline MOL 

system. 

Military Missions and Growth 

The MOL labora.tory module has sufficient flexibility to 

develop eauigaent for missions other than high resolution 

reconnaissance. New military missions, when validated., such as 

carsaunication.s intelligence or ocean surveillance, can be added 

the .MOL Program by the fabrication of new 'mission modules and,s 

minor modification.s to the la bore.tory module.. Other elements 

the system can be used without change. 

In addition to these:-milita.ry uses, the MOL has the potential 

of providing a unique la.bOratory environment for the execution .0 

scientific ecpe.me2T1s The MOL has 1,000 cubic feet of pressurized. volume and. can provide up to 3,000 Cubic - feet .((8,000 

pounds) of =pressurized, experim" ent space. 

Finally, the .MOL Program, as currently con.figUred, Is :well 

suited to allow develo:...r.t , -beyond. the a-pplications outlined in 

the foregoing pare.graph.s.. Our studies have indicated.,that .gro 

to sixty clays on orbit is feasible, as in rendezvous and res 

• iikploiting either of these "I.Z0 tcrouth areas would ultimately 

offer ootentlais for increased. cost effectiveness and vanld perMit 

by incorporating larger Sensor's, the ..irovi.sion Of ground :.ses u 

tions on the order of a.p-oroximately li of our 

studies involving applications validate that longer lifetimes on 

orbit and the use of larger higher resolution optical devices 

be greatly a.--oorPnted by inclusion .of manned missions in 'at leas 

the develotment phase. 

Ne,ither. the new military missions, .nor the scientific.experi 

nents, nor the growr.n versions, are inoluded, in the approved pr 

and except for .study, no work has 'oeen done on them They are 

• 1.zicauded. in this report for in:torDial - A.01i - only. 

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TAB A 

SUMMARY 

STUDIES OF UNMANNED DORIAN SYSTEM 

INTRODUCTION 

Studies have been conducted of a wholly unmanned satellite 

reconnaissance system which uses the DORIAN optical subsystem now 

under development for MOL. This paper summarizes the results of 

these studies. • 

The objective of the studies was to define and analyze a 

wholly unmanned system configured to yield, insofar as possible, 

the same quality and quantity of intelligence return as that anticipated for MOL. Data on the configuration, performance, schedule 

and cost were to be developed. 

The following paragraphs describe the terms of reference and 

the approach under which the studies were conducted. 

The wholly unmanned system was to involve the lowest possible 

development risk. Existing and presently projected technology, 

components and subsystems were to be used to the maximum extent 

possible. Both the TITAN IIIC five-segment and seven-segment 

boosters without transtage were studied. Numbers of recovery 

vehicles were to correspond to mission life; existing vehicles were 

to be used if possible. 

Contractor as well as.in-house studies were to be conducted. SEMMEE 

With the exception of technical information required as inputs, 

these studies were to be conducted apart from the MOL/DORIAN Program WM 

Office; however, close coordination was maintained to assure the 

greatest possible comparability with current MOL program planning, 

projections. In matters of design, management approach, etc., the .Iggift 

wholly unmanned program was to conform to usual practices for 

similar programs in the NRP. 

Stl..dy contracts were let to GE and LMSC for a 60-day study. 

The ,mtractors were•told to consider the Mission Module as a GFE 

item with the first flyable unit to be delivered in October 1969. 

The contractors were requested to provide nearly complete redundancy 

in the OCV in order to achieve the highest possible mean mission 

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life. Factors of development risk, reliability, confidence of early 

success, and costs were identified as key issues and the contractors 

were urged to emphasize them. Each contractor was able to respond 

quickly and well by reforming the teams which had performed studies 

over the past two years of the new search and surveillance system. 

Since the OCV for the wholly unmanned system appeared to be quite 

similar to that needed for a new search and surveillance system, the 

contractors were requested to consider the interrelationship carefully and to draw on their previous efforts in this area. 

Concurrently, in-house studies were conducted to provide a 

basis for careful review of the OCV design by the contractors. 

Studies of simulated operations against a DORIAN target list were 

continued and various computer runs made to provide answers to 

questions regarding weather, target access, anticipated requirements, 

etc. 

II. BASELINE SYSTEM CONFIGURATION 

Figure 1 depicts a 30-day configuration for the orbital vehicle 

of a wholly unmanned DORIAN system. The placement of the controli 

recovery, and mission support modules in this configuration is such 

that it offers the advantage of minimum structural weight and optimum 

interfaces between the modules. Additionally, this configuration is 

potentially applicable to othermissions. 

The Orbital Vehicle is flown in the opposite direction to that 

planned for the manned systeM. This may introduce an aerodynamic 

heating problem on the blunt end of the Mission Module at low perigee 

altitudes; however, this problem is not expected to be severe and, 

at worst, may require some additional heat protection. 

The performance of the baseline configuration discussed in 

Section III of this report it- bated on sufficient weight for orbit 

.keeping propellants for flights with a perigee altitude of not less 

than 80 n.mi. 

Launch would be accomplished from the Western Test Range. Onorbit operations would be conducted through the existing and 

programmed facilities of the Satellite Control Facility at Sunnyvale, 

California. On-orbit functions would be controlled in accordance 

with the following concept: 

Target coordinates read up from ground to computer. 

Ephemeris computed on ground and read up to vehicle. 

DORIAN/GAMBIT 

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Star tracker data and navigation data used to compute 

sensor pointing commands. 

Image motion sensor (V/h) tracking through main optics. 

Computer extrapolation of previous V/h data to new 

target as backup. 

Focus and alignment either closed loop or commanded from 

ground. 

Redundant backup subsystems switched in by ground command. 

Four recovery vehicles - first vehicle recovered after 

approximately one week's operation. 

Recovery would be accomplished on command in the Hawaiian area 

by the 6594th Recovery Squadron using existing or projected equipment. 

III. ESTIMATED PERFORMANCE 

The configuration described above is based on using a Mission 

Module configured for automatic mode operation "GFE" from the MOL 

program. Functions which will be accomplished automatically (i.e., 

with no assistance from the man) are: 

a. Pointing 

b. INC 

c. Film handling and recovery 

d. Alignment and focus 

e. Across format IMC 

The manned/unmanned mode was included in the MOL program 

earlier in the year and was made part of the Contract Definition 

Phase (CDP). Further progress in the CDP has tended to further 

support the validity of this technical approach. 

The critical aspects of pointing to acquire the target have 

been examined further. The precision of the navigation required is 

attainable for perigee altitudes of 80 n.mi. even in periods of 

peak solar activity. At 70 n.mi. perigee, some method of accounting 

for in-track errors due to variations in drag is needed. The precise 

DORM/GAMBIT 

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attitude reference device needed is consistent with several existing 

star tracking instruments. However, automatic star trackers and 

advanced high-accuracy horizon sensors have been a 'constant source 

of difficulty in NASA programs (the main programs using them) and great 

care will have to be exercised to balance performance and reliability. 

A camera to provide compensation for image blur across the full format 

due to in-track pointing errors has been designed in detail by Itek 

and submitted to EKC, whose initial reaction is very favorable. Image 

Motion Sensing is quite critical and exploratory development has 

continued on three parallel approaches--each of these has given indication of promising to meet unmanned system requirements although none 

constitutes flyable hardware as yet. 

The critical devices needed.for automatic operation of the 

DORIAN sensor have progressed well and offer considerable promise for 

successful operation in the automatic mode. Thus the quality (resolution) of the wholly unmanned sYstem can ultimately be expected to be 

the same as that for the manned system in the automatic mode (i.e., 

with no participation by the man but with the automatic devices 

operating reliably and within design tolerances). The cumulative 

.probability of achieving a geometric mean ground resolution is shown 

in Figure 2. As can be seen, at the nominal point' of .5 probability, 

the system should produce resolution. 

Further improvements in performance may result from technolo- • 

gical effort now under way. For example, "zero co-efficient" optical 

materials are progressing very well and development of mirrors for 

DORIAN is scheduled. If successful, a significant simplification of 

the Mission Module will result since the louvres and baffling door 

movements will not be required. Orbital testing of a drag accelerometer is scheduled and if successful will permit,adequate drag 

accounting and therefore operation as low as 70 n.mi. perigee even 

in periods of peak solar activity. 

The quantity of product to be obtained is determined largely 

a function of the non-random failures (learning factors), inherent 

by the expected mission duration. The expected mission duration is 

reliability and design life. If one considers a mature system in 

which the inherent reliability is being achieved, the effect of design 

life on expected mission duration can be seen from the following 

table. (A "mature" unmanned system is assumed to be achieved after 

ten flights.) 

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EXPECTED MISSION DURATION 

WHOLLYUNMANNED SYSTEM 

Design Life, Days 30 35 60 

OCV Reliability, Ro .91 .90 .83 

MM Reliability, Rm .81 .78 .62 

Booster Reliability, Rb .93 .93 .93 

Mean Mission Duration, Days 24 27 42 

The increased design life between 30 and 35 days involves an 

increase in expendables at the expense of reducing the weight 

contingency from 30 percent to 10 percent. 

The reliability figures, Ro and Rm represent the probability 

of successful operation for the design life. The vehicles which 

fail to achieve the full design life may achieve some lesser life 

which on the average will be approximately one-half the design life. 

Therefore, the mean mission duration, taking account of the booster 

reliability, is 

1 + RoX 1 + Rm X Rb 

MMD = Design Life 

2 2 

'An increase in design life at the same inherent reliability 

will result in a significant increase in mean mission duration. A 

mean mission duration of the order of 27 days appears reasonable for 

an unmanned system with a design life of 35 days as opposed to 24 

days for a design life of 30 days. On a straight-line reliability 

extrapolation, the 60-day mean mission duration would be 42 days. 

Experience in flighttesting satellites has shown that early 

failures may - be expected in which there are complete.mission losses. 

An estimate for:the unmanned DORIAN is that four of the first ten 

attempts would probably fail in this manner. Taking this factor 

into consideration and assessing the development difficulty, it was 

estimated that a 10-launch development test program would be 

required. 

The present configuration of the MOL includes a readout system 

in each flight vehicle. kreadout capability could be developed for 

the wholly unmanned systen and substituted for the recovery equipment in the Mission Support Module. Effort presently under way for 

possible application to GAMBIT CUBED will develop the technology and 

DORIAN/GAMBIT Page 5 of pages 

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ker 

basic components for such a readout'system and will, within the next 

few months, demonstrate the capability, film to film, in ground 

tests. This system will have the capability of reading out and reconstituting photography from the DORIAN with resolution degraded by 

about 15 percent. Some 80 frames per day could be read out to a 

single station from a circular orbit of the order of 150 n.mi. altitude. 

The readout version would represent an alternate OCV to be used 

in crisis situations or other circumstances requiring rapid response. 

In addition to development test flights for this payload, the followon program must include flights to exercise the readout capability 

on a regular basis in order to assure that the capability will be 

operational when required. However, the costs of developing this 

alternate OCV for readout have not been included in the costs of the 

unmanned system. 

IV. ESTIMATED COST AND SCHEDULES 

Schedule 

The pacing item in this program (as in the MOL program) is the 

availability of the DORIAN optical subsystem and the Mission Module. 

Therefore, a first flight date of December 1969 was assumed. This 

date is identical to the first flight with optics now planned for 

the MOL program. Assuming a go-ahead in the near future, the balance 

of the program elements of a wholly unmanned system could be available 

to meet this flight date. 

Costs 

The costs for the Mission Module were obtained directly from 

the MOL SPO and the DORIAN sensor office. 

Costing ground rules were established to insure maximum interpretability and completeness of the OCV costs submitted by the 

contractors. Segregation of costs was required and twelve categories 

were specified for costing breakouts: 

1. Program Management 

2. System Engineering 

3. Module Design 

4. Flight Hardware, by Subsystems 

5. AGE Designo .Procurement, s Checkout, and Maintenance 

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6. OV Test and Launch 

7. On-Orbit Requirements and Support 

8. Flight Evaluation 

9. Logistics and Spares 

10. Test Models 

11. Vehicle Integration 

12. Facility Contract Items 

Although a detailed system specification was not available, 

a detailed and precise performance requirement was developed to place 

specific requirements on each subsystem and the total OCV. These 

detailed requirements were developed during the first week of the 

study and were made a part of the contractual documents. 

Five full scale models were required with no refurbishment for 

flight. The total OV system, including prime mission module and 

necessary spares, were to be qualified. 

Four sets of AGE were required: one at the pad, two sets to 

be used in-house, and one set of engineering AGE for prototype 

vehicle testing. It was assumed that there would be a single pad 

at WTR and that the STC at Sunnyvale, California would accomplish 

on-orbit control. Two sets of major components, including GFP, were 

assumed as vehicle logistics spares. A flight evaluation report 

would be required five days after each R/V recovery and a summary 

report would be required 20. days after termination of flight. 

Assumptions were made that GFP subsystems would be functionally 

tested at the contractor's facility. If problems exist, the contractor will isolate the trouble to component level and defective 

components will be returned to the supplier with the subsystem made 

operational be replacement with. a good unit. 

The estimates for launch vehicle cost were made with the best 

.information from the Martin Company and other contractors and are 

consistent with the costs submitted for the plan for a new search 

and surveillance system. . 

The costs for recovery equipment represent the cost for a 

contract to supply the recovery system GFE to the OCV contractor. 

The costs are consistent with current and projected experience on 

recovery vehicles. 

DORIAN/GAMBIT 

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The estimated cost of 8GLS equipment and AGE needed by the OCV. 

contractor is based on contractor estimates and actual experience in 

other NRP programs. 

The support item includes funds for Aerospace Corporation 

support and for mission anticipated optimization based on experience 

and practice in present NRP programs. 

Table I summarizes the estimated costs of a wholly unmanned 

program for both a 30-day and a 60-day nominal mission. The development costs are the mean of estimates which varied from 95 percent to 

105 percent of the listed figure, based upon development uncertainties. 

It should be noted that the costs stated are for a ten-launch 

program; follow-on costs are predicated on a launch rate of four per 

year. 

The costs for development and flight of the alternative readout 

system discussed in Section III are not included in the cost tables. 

Cost for development readout hardware for two development flights and 

an operational ground station is estimated at $94.0 million including 

savings for recovery vehicle hardware not required. Follow-on costs 

approximate an additive increment of $2.0 million per flight for the 

readout equipment only. In order to have this readout capability on 

call for crisis situations, it would be necessary to exercise it at 

least once and probably twice a year. This would result in a serious 

degradation in the normal productivity of these surveillance missions. 

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TABLE I 

PROGRAM SUMMARY 

(Cost in Millions) 

(Development based upon 10-launch program) 

Mission ModUle 

OCV 

Launch Vehicle 

Non-Recurring Recurring 

30-day 60-day 30-day 60-day 

311 

135 

90 

311 

220 

155. 

221 

100 

93 

221 

150 

185 

SGLS 1 3 9 20 

Recovery Equipment 10 20 10 20 

Support 17 30 

Military Construction 31 31 ___ 

Subtotal 578 740 45o 626 

Contingency 10% 58 74 ' 45 63 

TOTAL 636 814 1195 689 

Follow-On 

Per Unit 

30-day 60-day 

22.1 22.1 

7.7 10.0 

9.3 16.5 

.9 1.8 

.9 1.8 

.5 1.0 

 41.4 53.2 

4.1 5.3 

45.5 58.5 

TOTAL FOR 10-LAUNCH PROGRAM 

30-day 60-day 

Non-Recurring 636 814 

Recurring 495 689 

TOTAL 1,131 1,503 

DORIAN/GAMBIT 

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TAB B 

MOL PROGRAM COST SUMMARY 

The planned total RDT&E..cost of MOL Phase II development is 

$1,818.0 million. This figure is based upon the program schedule 

shown in Figure B-1 and the annual distribution of funds shown, 

by system segment, in Figure B-2. 

The cost figures shown were derived through a methodical and 

systematic procedure which was formally instituted in January 1966, 

and which will continue through negotiation of Phase II contracts 

with all major associates. The cost estimating methodology employed 

has involved the generation of independent estimates concurrently 

with preliminary contractor-estimates, reiterations of these procedures, detailed evaluation of final. contractor proposals where such 

proposals were available, and detailed reviews of cost estimates by 

independent groups of highly-qualified individuals. The result is 

an estimate of MOL system costs which is believed to be realistic. 

It should be noted that the cost estimates shown in Figure 

B-2 provide only for the basic program. There is no allowance for 

system improvements beyond the primary optical reconnaissance mission. 111111 

While the desirability and potential of other possible military 

applications of MOL, such as SIGINT and Ocean Surveillance, have been NW 

recognized, the costs for such secondary objectives are not included 

in the estimates shown. Neither are costs included for scientific 

and technological orbital experimentation effort not related to the 

primary mission for which MOL may be particularly suited. 

To provide a basis for cost comparisons, the following estimates MIN 

of recurring costs are shown. These costs assume a 5-year opera- ONOOMB 

tional program with current baseline configuration at 1 and 6 flights MEM 

a year. 

DORIAN/GAMBIT Page 1 of pages 

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MOL Recurring Costs ($ Millions) 

Manned Mode .Unmanned Mode 

4/year 6/year 4/year 6/year 

Lab Vehicle $25.3 $23.0 $22.0 $19.8 

Mission Module 24.0 22.8 22.1 .20.8 

Gemini B 16.5 15.5 

Support Module 4.0 4.0 

Titan IIIM 17.0 15.6 17.0* 15.6*. 

Crew & Equipment 0.5 0.4 

Test/Operations 1.0 1.0 0.5 0.5 

GSE/TD - 0.5 0.4 0.5 0.5 

TOTAL $84.8 $78.7 $66.1 $61.2 

*This cost is for the 7-segment Titan IIIM which provides 41 days 

mission design life. 

DORIAN 

Page 2 of pages 

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TAB C 

BASELINE MOL EFFECTIVENESS FACTORS 

I. RELIABILITY, DEVELOPMENT RISK AND MISSION SUCCESS 

The Laboratory Module segment of the MOL is based on current 

state-of-the-art subsystems, which in large measure have been 

adapted from the Gemini and Apollo programs. The Mission Module segment, on the other hand, which contains the DORIAN high resolution 

optical sensor, represents a major advance in the state-of-the-art, 

with an attendant high development risk. Additionally, MOL, in its 

development configuration, is designed to function both in manned 

and unmanned modes; hence, it is somewhat more complex than would be 

the case if either mode were flown singly. Many new components and 

subsystems must be developed, or adapted from existing designs to 

provide for this dual capability. Important new developments are: 

A. Image Motion Compensation (IMO) across the Film Format gasses 

B. Image Tracking (V/h) Sensor 

C. Tracking Mirror Drive Servo Subsystem 

D. Acquisition and Tracking Scopes 

E. Thermal Control Door and Louver Assembly 

F. Focus Sensor 

G. Automatic Optical Alignment System 

H. Low Drag Accelerometer 

I. DORIAN Optical Assembly 

J. Re-Entry Vehicle. Launcher 

Adaptation from existing designs are required for: 

A. On-Board Computers 

B. Star Trackers 

C. Re-Entry Vehicle 

0 

DORIAN/GAMBIT 

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O 

D. Consoles, Displays and Associated Instrumentation 

E. Thermal Control System 

Because of these new engineering requirements, assurance that 

the vehicle functions reliably is a major factor in system design. 

In order to provide a basis for a reasonable projection of reliability 

values, a failure analysis of the current GAMBIT program was conducted. 

The types of failures encountered fell into two general categories. 

The first of these, about 75 percent of the total, consisted of 

failures attributable to design deficiencies, procedural errors, or 

faulty quality control, and hence were amenable to corrective action. 

The remaining 25 percent of failures fell into the second category, 

failures attributable to statistical or unknown causes. It is also of 

interest to note that all failures of the first category occurred in 

the first day on orbit, .whereas the failures in the unknown category 

were distributed throughout mission, duration. 

GAMBIT failure rates have been reduced in recent flight history 

through a sophisticated and thorough ground testing program in which 

incipient failures were detected and corrected before actual flight. 

This testing is analogous in approach, though neither as extensive 

nor similar in motivation, to the "man-rating" process which NASA 

has employed to a high degree of success, and to which MOL will be 

• subjected. 

With an intensive approach to ground testing, occurrence of 

failures of both categories can be reduced, but it is clear that 

failures of either type cannot be completely eliminated. The Mission 

Module, representing advanced state-of-the-art, can be expected to 

experience malfunctions at a higher rate than the Laboratory Module, 

for which phenomenology and technology are well in hand. 

However, the development configuration MOL is being designed 

to take the maximum advantage of the presence of man in the event 

of equipment failure. Equipment is being designed and installed 

wherever practicable to permit astronaut access for trouble shooting, 

adjustment, maintenance, repair, and replacement. The system is 

being designed to permit manual switching and override so that man 

can work around problems, choose alternate modes, or himself perform 

many of the functions for which the faulty equipment was intended.. 

He can detect malfunctions, both incipient and actual, diagnose, and 

institute corrective measures. He can also work in coordination with 

ground based technical support. This team approach, as shown by 

aircraft experience, is a powerful technique for overcoming in-flight 

problems. The recent XB-70 experience in which a nose gear failed to 

lower is an excellent case in point. Repeated consultations between 
NRO APPROVED FOR 

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flight crew and ground supported by trouble shooting in flight, permitted the diagnosis of the trouble, and a corrective action to be 

,devised to lower the nose gear. These factors are expected to be 

major contributions to the early success and maturity of the unmanned 

and manned configurations of MOL. 

Adoption of these design principles also makes it possible to 

continue a mission in the manned configuration despite alulative 

equipment failures beyond man's capacity to repair. The normal mode 

of MOL operation, either in the unmanned or manned mode, is essentially 

automatic. When man is present, automaticity is exploited by utilizing the crewmen in tasks such as selection of alternate targets of ' 

high intelligence value, selection of cloud-free alternate targets 

when primary targets are obscured, and rapid return Of important 

photographs by wideband data link. In'the event of the failure of 

automatically functioning devices during a mission, the crew can 

perform many of the necessary functions manually and hence preserve 

the capability of the vehicle to continue to collect photographic 

intelligence. The following equipment can fail cumulatively with 

little or no degradation in mission performance beyond the basic capability of the manual mode: 

A. Image Tracking (V/h) Sensor 

B. Tmage Motion Compensation (IMC) Across the Film Format 

C. Star Trackers 

D. Data Recovery Vehicle Launcher 

E. One SGLS Command and Tracking Data Link 

F. Two Fuel Cells 

G. One Cryogenic. Tank 

H. Three Pairs of Attitude Control and Translation System 

Fuel Tanks 

I. Twenty-five percent of Attitude Stabilization System 

Thrusters 

J. Automatic Mode for Orbit AdjuSt 

K. One On-Board Computer 

L. One Acquisition and TraCking Scope 

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M. Laboratory Attitude Reference System 

N. Auxiliary Computer Memory Storage 

The resulting performance in the manual mode after failure of 

the above equipment is approximately equivalent to that of the 

automatic configuration with all of its equipment functioning, except 

that overall mission photographic resolution still remains somewhat 

better in the manned mode due to man's target centering capability. ' 

A most important outcome of the flexible development and test support 

functions possible when man is present in the vehicle is that trouble 

shooting, adjustment, maintenance, repair and replacement, or actual 

manual performance of automated functions will be done on much of the 

equipment in the high development risk category. 

A numerical-reliability analysis of the Mission Module alone 

in the automatic mode results in a mature reliability figure of .892, 

although it is somewhat less (.8 to .85) early in the flight program. 

This analysis is based on a random failure rate of one failure per 

ten million hours per Active Element Group (AEG), and estimating that 

the Mission Module contains the equivalent of 10,000 AEG's in serial, 

and 19,000 in redundancy. For reference purposes, GAMBIT has an 

equivalent AEG count of 6500, and GAMBIT CUBED is estimated at about 

10,000. Clearly the Mission Module is a very complex system element. 

Reliability estimates were then computed for the MOL as a 

system, as presently configured to function in both manned and 

unmanned modes, and for a comparable wholly unmanned system, both 

using the same Mission ModUle. A comparison of the two approaches 

was then undertaken to determine the number of launches which would 

be required to complete, development programs resulting in vehicle 

designs of approximately comparable performande and reliability. It 

was determined that for a wholly unmanned system, about ten development launches completely equipped with the high resolution. optical 

sensor would be necessary as compared with the current MOL Program 

which provides for seven development launches. Of these seven 

launches, two are preliminary validation launches not equipped with, 

the optical sensor. The remaining five are equipped with the high 

resolution sensor, three in the manned automatic configuration and 

two in the unmanned automatic configuration. 

Based on these considerations, the current MOL development 

approach is considered the most effective in achieving early operationally useful intelligence collection of ground resolution 

both unmanned and manned, earlier, and with significantly decreased 

development risk than can be expected of a wholly unmanned development program. This is largely due to utilizing crewmen for 

DORIAN/GAMBIT 

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SAP-SL BYE 21192-66A 
:• • 

overcoming equipment malfunctions, for maintaining peak sensor performance, and also as on-orbit development and test engineers during 

early program phases. The automatic configuration of MOL benefits 

greatly from this development technique. 

II. QUANTITY, QUALITY AND TIMELINESS OF INTELLIGENCE RETURN 

A. Present Target Programming Operations 

In order to provide a baseline for the discussion of the 

intelligence collection and enhancement techniques realizable with 

the MOL DORIAN high resolution optical sensor, it would be useful to 

review the target programming techniques in current use for a typical 

reconnaissance system such as GAMBIT. 

The orbit for each GAMBIT mission is normally chosen to 

optimize accessibility of high priority targets selected for that 

mission, within the bounds of booster and orbital vehicle performance, 

and consistent with recovery requirements. This complex problem is 

subjected to computer analysis approximately fifteen days prior to 

flight, and results in a defined orbit and the corresponding required 

laUnch parameters. Launch injection errors may result in a slightly 

different orbit than planned; requiring that adjustments in target 

programming be made during the mission. Additionally, the spacecraft 

orbit may also be adjusted to return the vehicle to its planned nominal 

ground track. 

The spacecraft orbit parameters, and the complete mission 

target deck are combined in a computer run which prints out predicted 

ground traces over the target areas of interest. This printout 

locates and identifies all targets accessible along the ground track, 

and specifies the optimum sequential series of photographic operations 

based upon system limitations, orbital considerations, target priorities, 

and photographic. mode (mono or stereo) requirements. These computer: 

results are modified manually for weather considerations, for conservation of expendables and last minute intelligence requirement changes. 

Prior to launch, the mission target program is transmitted to the 

Satellite Test Center at Sunnyvale, California to be translated into 

vehicle commands for camera pointing data and camera on and off times. 

Commands sufficient for about one day of on-orbit operation are 

stored in the vehicle programmsr prior to launch. After the launch, 

and throughout the mission, continuously up-dated target programs 

are computed, and new commands are transmitted to the vehicle while 

it is in orbit. In this way, necessary changes in target operations 

can be accommodated to account for orbit anomalies, last minute 

intelligence requirementt,.and forecast weather conditions in the. 

target areas. The time required from the initiation of a desired 

change in the target program until new commands can be transmitted 

to the vehicle is at a minimum 32 hours. 

DORIAN/GAMBIT 

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When the, supply of spacecraft expendables (gas for stabilization and control, electrical power, and film) is limited, and when 

forecasted weather in the target area indicates that the probability 

of successful photography is low, operations against low priority 

targets are generally discontinued until conditions improve. If, 

however, the probability that low priority targets will lite cloud 

covered accumulates to about 70 percent, photographic attempts 

against these targets are normally suspended altogether. However, 

high priority targets are normally maintained in the target program 

without regard to forecasted weather. 

B. DORIAN Optical System 

The DORIAN high resolution optical system represents a 

major advance, not only in photographic art, but also in optical 

science. The size of this sensor, which requires a mission module 

35 feet long and 10 feet in diameter to contain it, is difficult to 

visualize. The prime optical' elements themselves stand taller than 

most men (they are six feet in diameter). Few astronomical telescopes 

approach this size,. and even fewer, including the 200-inch Hale 

telescope on Mt. Palomar, can match DORIAN optical quality. 

An optical system the size of the DORIAN sensor is essential 

to the achievement of ground resolution from an orbit 

altitude of 80 nautical miles. With this size, and with high resolution, the optical field of view, hence the area on, the ground 

observed by the sensor, becomes very limited. 

The GAMBIT and GAMBIT CUBED systems utilize strip cameras, 

in which film is pulled past a slit in the focal plane in synchronism 

with the satellite's apparent motion over the terrain. Strips of 

film•are typically exposed for about five seconds, which represents 

about 21 miles along the satellite path over the earth. The DORIAN 

camera, on the other hand, is a frame camera, that is the film remains 

motionless while the scene is tracked and entire frame of film is 

exposed at the same time. The DORIAN format is round, whereas both 

GAMBIT and GAMBIT CUBED are rectangular: 

Camera Field 

of View 

Nadir Frame 

Width 

Frame Width at Included Area 

Maximum Oblique per Frame 

GAMBIT 6.4° 8.95 n.mi 17.94 n.mi. 188 sq.mi. 

GAMBIT3 3.2° 4.45 n.mi. 8.95 n.mi. 93.5 sq.mi. 

DORIAN 1.1o 1.54 n.mi. 2.38 n.mi. 1.88 sq.mi. 

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It is immediately obvious that a great premium is placed on 

the accuracy of target location, and the precision to which the DORIAN 

optics can be pointed so that the target will fall in the camera field 

of view. At nadir, a 12,000 foot airfield runway cannot be contained 

in the DORIAN field of view; hence, we must now specify which end of 

the runway we wish to photograph. Two major effeCts arse from these 

circumstances; one, locations which represent One .GAMBIT or GAMBIT 

CUBED target area ,(which in itself could contain several specific 

targets) will not represent several DORIAN sized targets; and two, 

careful target selection,becomes of paramount importance because photographs of all targets which are closely clustered cannot be taken on 

a single active pass. Every effort must be made under these conditions 

to insure that each photograph is of the highest intelligence value. 

C. Selection of Active and Mobile Targets 

A. useful operational technique, that of inspecting targets 

for indications or activities of a transient nature that would yield 

photography of especially high intelligence value, can be employed 

with the manned MOL vehicle configuration. 

To assess the value of this technique an analysis was conducted which: 

a. evaluated the effect of the limited DORIAN field of 

view when superimposed on actual GAMBIT photography on the size, 

number, and character of MOL targets; 

b. determined whether certain activities or conditions 

might exist for periods of hours or a few days during which the value 

of technical intelligence would be particularly high; and, 

c. . determined whether indicators would be present which 

the crewmen could detect by examination through the acquisition and 

tracking scope. 

The extremely high resolution of the DORIAN sensor and 

its limited field of view are of overriding importance in the assessment of its coverage. This becomes evident from a sample of 140 

frames of GAMBIT photography in which 700 DORIAN sized targets were 

found. Some of these targets were larger than the available field of 

view and hence would actually become two or more targets. This 

proliferation of targets renders target selection for DORIAN of particular importance.' As. a first step, indicators of transitory 

conditions of special intelligence value that crewmen might easily 

detect were defined. Utilizing the 140 frames of GAMBIT photography 

with its 700 DORIAN sized targets: 

a. The fraction. of the targets which had potential • 

for active indicators of conditions of special intelligence value was 

estimated; and, 

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b. Of those, the fraction that would have active 

indicators present at any given time was determined. 

Missile Development & Test 

Ground Forces 

99% 

35 

7% 

11* 

Airfields 75 18- 

Radar/Communications Deployment 35 4 

Industry 5 2 J 

Missile Production & Logistics 65 1 

Nuclear Weapons 85 5 

Bw/cw 85 5 

Nuclear Materials 5 3 

Aircraft Production 75 24 

Naval Activity 65 9 

Radar/Communications 100 25. 

Major & R&D 

AVERAGE 70% 6% 

The fraction of targets for which active indicators can 

0 be defined is relatively large while the incidence of indicators is 

low. 

Because of its importance in yielding early technical intelligence data on the USSR missile.and space programs, Tyuratam has been 

studied in some detail. In addition to its specific importance, 

Tyuratam is also a typical example of other high target density 

complexes such as Sary-Shagan and Kapustin Yar which contain large 

numbers of high priority, active targets. More than 60 targets can 

be identified currently at Tyuratam and the number is increasing 

steadily. Five GAMBIT frames laid down with care will cover the 

entire Tyuratam complex. .FortY DORIAN fields of view have been 

defined, with specific locations, which would generally return the 

same "target take" as the five GAMBIT frames. With four over-flights 

per mission and two stereo pairs per over-flight, on the average, 

one DORIAN system flight'will be about equivalent to one GAMBIT system 

flight in terms of the "target take" at Tyuratam. 

An analysis was made of Tyuratam photographs of pads and 

silos: 159 pad photographs yielded 9 percent with missiles on the 

pad; 77 silo photographs yielded 21 percent with doors open. These 

are much higher incidences than would.be expected from operational. 

systems, which further emphasizes the importance of obtaining data in 

the early development phases. 

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Transient Activity Indicator Probabilities 

Possibility of L2celihood of , 

Target Categories Occurrence 

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The unmanned,MOL configuration would require times from 

months to years to develop a high probability of catching a particular missile on a pad depending upon the priority structure given to 

the forty fields of view required to cover the complex. 

However, crewmen aboard the manned configuration can 

examine targets for active indicators through their acquisition and 

tracking scopes, and can begin to yield a gain in the return of photographs of high intelligence value. An estimate of typical resolutions 

needed by the crewmen to detect active indicators was carried out 

with the following result: 

Decision 

Photo Target Indicators Resolution' 

Missile Sites Missiles Exposed 10 Ft. 

(Completed) Erection/Loading Equipment Exposed 10 

Vehicular Activity 10 

GSE Exposed 5 

Silo Door Open 5 

Special Vehicles 3 

Snow Removal 10 

Airfields 

Ground Forces, 

Major Installations 

Motor Pool 

New Aircraft 

Unusually Configured Aircraft 

Aircraft in Unusual Locations 

DiSassembled Aircraft 

Aircraft/Ground Equipment in 

Weapons Loading Areas 

Aircraft Subsystems Exposed 

Aircraft in Maintenance Docks 

Vehicle/Truck Activity around 

Aircraft 

Vehicles Present 

Vehicle Types 

15 

5 

15 

5 

10 

3 

10 

5 

5 

3 

Maintenance Activity 5 

The question of the practicality of this mode of operation 

hinges upon two points: 

a. with what resolution can the crewman examine the 

target; and, 

b. how long can he examine the target before a decision 

is required. 

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It appears that a reasonable design for.the tracking scope 

will permit the following range of operation: 

Ground Resolution 

3- 4 feet 

30 - 40 feet 

Field of View 

10 

10° 

With the particular time constants of the MOL/DORIAN system, 

the crewman will have 10 seconds to examine and judge for the presence 

of indicators (starting the examination with the target at 36° ahead 

of the vehicle and ending at 11° ahead). If the judgment is affirma-, 

tiv, a 15° stereo pair can be obtained looking aft at -5° and -20°. 

If a larger aft angle is acceptable the examination time can be 

correspondingly longer. 

0 

The specific concept of the "examination for active indicators mode," is to program the primary optics as though the MOL vehicle 

were unmanned. In addition, the two acquisition and tracking scopes 

will be programmed automatically to acquire and track two targets in 

the immediate vicinity of the target programmed for the primary optics 

(specifically, the three targets will be chosen to establish to the 

most efficient roll angle between them, thus optimizing the time to 

slew the primary mirror from one to the other). At any instant that 

a crewman makes a judgment that active indicators are present (and 

the weather is good), he interdicts the automatic program, the primary 

mirror slews to the position of the acquisition scope mirror, and a 

stereo pair is obtained. At the end of the sequence, the primary 

optics returns to the next pre-programmed target. 

and hence infrequent interdiction of the automatic program, acquisi- o 

tion of pre-programmed targets is affected only slightly. 

b. The reduction in cloud-free photographs returned in e7 

the automatic mode because of crew interdictions is offset by the 0 added number of cloud-free photographs of special intelligence value, 

even if the enhanced value of the special photographs is not taken 

into account. 

c. The ratio of cloud-free photographs of special 

intelligence value returned with crew participation is about three 

times that without crew participation. This ratio is probably 

conservative since it does not account for: (1) examining more 

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Several key points emerged from the analysis: 

a. Because of the low incidence of active indicators ? 
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than one target in the 10 second period in high target density areas 

and with possible slow panning by the crew to cover large targets 

like airfields and harbort; and, (2) possible increases due to crewman examination and judgment of weather factors. 

A digital data readout system in the MOL baseline system 

is capable of reading out 15 stereo pairs (1" x 1") to the ground 

per day. Thus the crewmen can select the target area from a frame, 

and transmit to the ground all cloud-free special photographs which 

they have acquired. The remaining capability can be used to transmit 

photographs of high priority targets taken in the pre-programmed, 

automatic mode. 

Turning again to the previous example of Tyuratam, the 

number of special photographs collected would te expected to increase 

by a factor exceeding three over an unmanned automatic mode. There 

are several reasons why the increased ratio should be realized: 

a. The targets tend to be clustered so that several 

may be examined in a single field of view or with a slight amount of 

panning. 

b. Examining launch pads for the presence of missiles 

might well be done at 10 to 20 foot resolution, thus tripling or 

quadrupling the field of view examined by the crewmen as compared to 

the main optics. 

c. The targets at Tyuratam have very little background 

clutter and the crewmen will become extremely familiar with them 

through repeated training and examination. Thus, it is expected that 

the time to examine a target will be much less than the allotted 10 

seconds. 

In general, the MOL system with crew participation can be 

expected to return two to•foirr times more special photographs from 

Tyuratam than the current return with the GAMBIT system (with the 

MOL system flying half as many flights). 

A special category of active targets deserves particular 

attention. These targets are not only transitory, but they are also 

mobile. Examples are: (a) an experimental aircraft which may operate 

from a known airfield, but its location on the airfield is not known; 

(b) a missile or space booster being transported on an access road in 

the vicinity of a target launch pad; (c) tanks, mobile missile launches 

or similar materiel in a field or a general research and development 

area; (d) trains on sidings. The specific location of these targets 

cannot be predicted with surety, but a search in the vicinity of the 

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then make a vernier centering adjustment to bring the special target 

into the primary field of view. 

Although this analysis and the results of ground simulations 

using GAMBIT photography are very promising, they cannot be regarded 

as totally valid quantitative indicators of orbital manned performance. 

In particular, the effects of the atmosphere, haze and Scintillation 

in direct viewing by the human eye is quite different than when seen 

on film. Conversely, color often provides cues not evident in black 

and white photography. Further exploration of this function from very 

high-flying aircraft will provide additional data which may validate 

the efficacy of the unaided human eye or indicate the need to introduce some contrast enhancing transfer medium to give the same effect 

as film. 

D. Selection of Cloud-Free Targets 

A function which is compatible with the selection of active 

and mobile targets is the observation of weather conditions and the 

identification of targets which are judged to be in the clear. The 

Soviet weather averages only about 50 percent cloud-free, so that 

generally one-half of the target attempts will be unsuccessful unless 

a selection method is employed. 

In the MOL, the spotting scopes are continuously directed 

automatically toward programmed targets. Employingthe scopes, the 

operators will have a device against which to exercise the weather 

option along with inspection for indicators of activity. 

In order to examine whether the weather patterns will 

permit such activity, the results of an extensive analysis were 

obtained, based upon the inspection by the Government Weather Center 

of 152,000 frames of KH-4 photography. In addition, the photography 

from more than 3,000 KH-7 camera operations was reviewed for the 

purpose of correlation. A.model of the weather conditions was then 

drawn which established the probability of finding an alternate 

target in the clear when the primary was obscured. When applied to 

a simulated DORIAN mission, these studies showed that a substantial 

improvement of about 20 percent in the production of clear photographs 

could be made by cloud-free selection methods. 

III. ALTERNATE MISSION POTENTIALS OF HIGH INTELLIGENCE VALUE 

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B. Crisis Surveillance and Tactical Targets 

The MOL can, in times of crisis, be boosted from its 80-mile 

orbit to orbits of 200 to 250 miles. The advantage of the higher 

orbits is that they permit access to all targets in the Sino-Soviet 

land mass once every two to three days or so depending upon the actual 

altitudes and orbital ellipticity selected. Altitude changes are 

accomplished by using fuel normally utilized to sustain the MOL in its 

'usual orbit. When the orbit perigee is raised, fuel expenditure for 

orbit sustenance is sharply decreased, and duration on orbit can 

remain unchanged at the normal 30 days. The maximum circular orbit 

altitude which can be attained with available fuel is about 260 

nautical miles, although the Gemini B sets a practical limit of about 

240 miles. Above this altitude, insufficient thrust is available 

from the retro-rockets (on the presumption that only five of the six 

rockets provided function properly) to de-boost the Gemini for re-entry. 

Eliptical orbits can also be selected, rotating the line of apsides, 

for example, so that apogee occurs over the area of interest. Orbital 

limits in this case are set by permissible Gemini re-entry angles, 

and, at the higher average altitudes, the Gemini de-boost capability. 

The following shows the circular orbit altitudes to which MOL can be 

boosted according to when,the change is initiated from a typical normal 

orbit (80 n.mi. perigee, 180 n.mi. apogee, inclination 80°) and the 

total mission life in days. 

30 days in the higher orbit. 

*New Circular 

In all cases, re-entry is 

Orbit Change Initiated on 

initiated after 

Orbit Altitude 1st Day 7th Day 14th Day 21st Day 

150 n.mi. 30 30 30 30 

180 n.mi. 30 30 30 30 

200 n.mi. 30 30 30 30 at 

190 n.mi. 

250 n.mi. ' 30**, 30 at 

210 n.mi. 

30 at 

200 n.mi. 

30 at 

190 n.mi. 

*NOTE: 213-6 n.mi. repeats every 2 days, 240.5 n.mi. every 3 daYs-

**Marginal. Exceeds Gemini de-boost limit. 

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The field of view of the DORIAN sensor in terms of area of 

terrain observed is increased, and its resolution decreased at higher 

altitudes. For crisis purposes, the advantage is the larger area__ 

covered per pass rather than the area per frame. 

Orbit Altitude over Nominal Area Observed 

Area of Interest Resolution at Nadir 

80 1.88 sq miles 

150 6.56 sq miles 

200 11.65 sq miles 

250 18.25 sq. miles 

In addition to the prime optical sensor, which can be 

utilized simultaneously in both photographic and visual modes, both 

of the acquisition and tracking scopes can be programmed to different 

suspect areas on the ground, multiplying the opportunity for the 

observation of activities of interest. Although acquisition and 

tracking scope resolution will fall off to about 9 feet at 250 n.mi., 

the field of view is large compared with the DORIAN sensor, and some 

categories of activity can be readily distinguished visually, such 

as: 

a. Gross estimate of large objects, such as aircraft, 

ships in port, tanks in park. 

b. Verification of the absence or presence of aircraft 

on airfields, ships in port,. cargo in port, army vehicles in camp. 

c. Estimate of whether railroad yards are empty or 

full, and if full, general class of rolling stock present. 

Hence, operated in this mode, advantage of man's flexibility and adaptability is turned to the return of urgently needed 

intelligence data on a daily basis. 

C. Visual Reconnaissance 

Apart from the support which visual observation affords the 

primary photographic mission int erms of weather avoidance, active 

and mobile target selection, and to the crisis surveillance mode in 

terms of verifying order of battle, and confirming presence or absence 

of major activity, visual reconnaissance remains a latent potential. 

It is possible that a critical examination of important targets, 

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during the high resolution photography sequence, can provide supplementary information of major value. Targets can be inspected by the 

crewmen from a continuously changing aspect. They can do simple 

counting by class of object, discriminate detail by color, classify 

activity, and detect and classify movement. The value of visual 

reconnaissance from space is difficult to assess at this point in 

time, but an assessment will result as a byproduct of other MOL 

program activities. 

D. Observation and Mapping of Mars 

It is expected that interest in the planet Mars will be 

heightened in the 1970 time period as the national space program 

looks beyond Apollo. In support of this interest, the DORIAN sensor, 

with no change in its configuration, offers a capability to examine 

and map the entire surface of Mars at about 50 n.mi. resolution. 

This is considerably better than present ground based systems (300 

n.mi.) which are handicapped by the turbidity of the earth's atmosphere. 

At present, the DORIAN sensor appears to be the largest instrument 

capable of astronomical observation .which will be in orbit during the 

time of interest. 

Astronomical and planetary observations in addition to Mars 

can also be conducted. However, the current DORIAN pointing and 

tracking system is not configured to support the long exposure times 

needed for photography of distant objects. This aspect is treated in 

more detail in TAB D. 

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TAB D 

ADDITIONAL CAPABILITIES OF TI MOL SYSTEM 

-1.., 0.-. 

4. Growth potential capabilities toward higher optical 

resolution, and increased effectiveness. 111111 

The category stage of the use of MOL has been treated in TAB 11111; 

C. This tab summarizes the latter categories stages of MOL capa- .1...r.1—,... 

bilities which can be achieved with varying degrees of modification 

.of the present MOL baseline system. 

II. BASELINE SYSTEM WITH DORIAN PAYLOAD AND MINOR EQUIPMENT 111111 

ADDITIONS MEM= 

g11111 

A. Improving the Current System IMINII 

=ERNE Improvements to the MOL/DORIAN system as now configured 

will continue as a normal'consequence of the growth of technology. 

Effort both in the application of technology, and in studies is now 

being expended to this end. 

However, there. is also existing technology which has devel 

oped to the point that serious consideration must be given to is 

application to MOL. Of major current interest is the proprietary 

ceramic-vitreous material CER-VIT manufactured by the Owens-Illinois' 

Glass Company. This paterial has a very low thermal coefficient of 

expansion (0.05 x•10-° in/in/°F). Used in place of fused silica for 

the primary asphere and tracking mirrors in the DORIAN optical 

system, it would permit,a,reduction of about 700 pounds in basic 

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. INTRODUCTION 

MOL system capabilities can be treated in four different 

categories: 

1. Basic MOL/DORIAN system capabilities for additional 

missions without changing or adding to basic equipment. 

2. Basic MOL/DORIAN system capabilities for mission 

enhancement with minor equipment additions or changes. 

3. Basic MOL vehicle capabilities for other than high 

resolution optical reconnaissance missions. 
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vehicle weight, as much sensor thermal control equipment could be 

dispensed with CER-VIT polishes as well or better than fused silica 

and, unlike fused silica, can be cast into desired configurations. 

Hence its manufacture is considerably cheaper than fused silica. 

B. Electromagnetic Pointing System 

Activities are presently underway to define and evaluate 

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, and pointing the primary optics with sufficient accuracy 

to assure that the target emitters will be contained within the 

optical field of view. 

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. 

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 

when this is an element of the target characteristics. 

2. Determining that a pre-programmed alternate 

target is more appropriate. 

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 analysisapabalaty-will permit the 

operator to obtain detailed wide-band 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 

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and the EPS. Coordination'of the pointing functions of the two 

sensors, if any, would 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 would be 

suitable used for detection of ships on the high seas. The system 

would cover a swath 100 miles wide and 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 

precise astronomical instrument., It can be employed for some 

planetary and near stellar photography without change. However, as 

the baseline configuration'is designed with attitude stabilization 

tolerances and refractive optical system components best suited to 

high resolution photography of the earth's surface, its baseline 

capability is confined to the visual spectrum, and to those objects 

sufficiently bright to permit use of short exposure times. 

Application of current state-of-the-art stabilization and 

pointing techniques would permit the sensor to resolve distant stellar 

objects to 0.1 seconds of arc, an order of magnitude improvement over 

current observations from the earth's surface which suffer from 

atmospheric limitations. The limiting visual magnitude of the DORIAN 

sensor is about 26, with a 20 minute exposure on high resolution film. 

The refractive optical elements in the baseline Ross 

corrector can be replaced by fused silica to permit access to a wider 

spectral range. The basic sensor design could also be slightly 

altered by replacing the Ross corrector with first surface reflecting 

elements to permit access to an even wider spectral range. These 

altered configurations would permit observation of ultra-violet 

sources which are denied to sensors on the earth's surface due to 

the filtering action of components of the earth's atmosphere. This 

latter configuration of the basic sensor is also capable of high 

quality spectrophotography. 

III. BASELINE MOL WITH OTHER PAYLOADS 

MOL, in addition to performing optical reconnaissance has a 

potential for fulfilling other mission capabilities. At present Ocean 

Surveillance and SIGINT missions are being studied by the Navy. 

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A. Ocean Surveillance 

The objective of the MOL Ocean Surveillance studies under 

Way is to define an experimental program for testing satellite 

sensors and sensor usage concepts, needed to obtain information for 

the design of an operational 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 

The necessary level of detail which ocean surveillance 

satellites must collect relative to detected targets has not as yet 

been established. ,It is possible that with improved and properly 

integrated ground systems, satellites need only supply accurate 

location information for detected targets. On the other hand, it 

may be necessary for the satellite to classify every target as to 

type and identify specifically some percentage of targets in the 

open ocean. In addition it may be necessary to frequently observe 

conditions in selected ports and harbors throughout the world. 

The Ocean Surveillance configurations under consideration 

are 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 man-machine combination. The four modes 

in order of increasing data transmission requirements are: 

1. Target detection and location only. Fully automatic 

operation, with all datatransmitted 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. 

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4. Target detection and location, plus heading and 

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

imagery. Fully automatid operation, with all data to be transmitted 

to ground. 

B. SIGINT 

SIGINT Studies are currently underway aimed at determining 

the feasibility of obtaining intelligible data from side-lobe and 

re-radiated energy of sophisticated communication systems. On completion of these studies, it is hoped that the technical parameters 

of a configuration can be developed which would permit the interception of this category of intelligence. It has been estimated that 

the information transmitted via soviet microwave radio relay links, 

presently not available to our intercept systems, spans both military 

and civil activities in the Soviet Union and that this condition will 

become more pronounced as these types of systems come into more and 

more general use. 

Other types of sophisticated Soviet electronic systems under 

development could yield valuable technical intelligence if intercepted. 

At the conclusion of these studies it is proposed to configure a SIGINT system which would incorporate the SIGINT missions 

considered most urgent and which can be done effectively by a manned 

system. The majority of the manned tasks which have been identified 

by current studies 

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 experimental equipment into polar orbit on 30-day 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. 

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3. Those which explore future potentials or contribute 

to development of equipment for other military space systems, either 

manned or unmanned. 

Examples of these various categories of experiments which 

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

listed below: 

Knowledge is needed on the performance of large mirrors 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, 

experiments must be coriducted in the area of communications (low 

frequency, millimeter wave, laser propagation and high frequency 

inospheric ducting)‘ and the erection and maintenance of associated 

antennas. 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 toward greater operational utility. It 

can grow in two ways which are mutually supporting. The optical 

sensor can be increased in size to approach the ultimate capability 

which is limited only by atmospheric phenomena. 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 employed.. The large optical sensor and rendezvous are 

discussed in greater detail below: 

A. Large Optical Sensors 

ftilaiPs 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 problems of structural rigidity, test and handling 

problems in the earth'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. 

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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 weigh a minimum of 

20,000 pounds. 

B. Long Duration and•Rendezvous 

For satellite missions involving complex,' heavy, or costly 

payloads, cost effectiveness is generally improVed by increasing the 

orbital lifetime. The lifetime of a satellite is limited pritarily 

by the quantity 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 reduces the 

probability of mission failure. Essentially then, longer life 

missions are obtained by larger boosters, increased equipment meantime-to-failure, and rendezvous. 

At present rendezvous is conceived of as applicable only 

in the manned case. The operations of docking, transferring expendables, etc., appear too complex to be accomplished completely 

automatically. Orbital rendezvous is advantageous for long life 

missions requiring resupply of expendables, crew replacement or 

rescue, and assembly of large, heavy objects. 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 rendezvous 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. 

The payload capability of the rendezvous and resupply 

vehicle on the T-III 7-segMent booster would permit launch of the. 

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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. 

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