gadier General, USAF 

CONTROL NO 

BY Bvi A N COPY 9 or coolcS 

CONTROL SYSTEM EXCLUDED FROM AUTOMATIC REGNADINd PAGE OF PAGES 

000 DIRECTIVE 5200.10 DOES NOT APPLY 

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1. Page 4, Para 1: The statement "50 targets per day 

can be photographed" needs clarification. The. Diamond Study 

indicated almost 2100 camera operations-in 30 days. (133 camera . 

operations per day,. about 2/3 of which were stereo.) The 

statement should indicate about 65-70 targets per day are 

expected to be photographed cloud-free. 

2. Page 24: The statement that G-3 is scheduled for 

8 development launches is a little bit misleading. We have 

described these launches to COMOR and USIB as development/ 

operational suitability. • Further, we have estimated (conservatively) that the operational product from these 8 R&D/OST 

launches will equate to at least half of the "take" from 

8 mature systems and have scheduled G's accordingly. (In the 

first G-3, the total number of targets covered was about 40% 

of what would be expected from a successful 8-day G-3. I 

hasten to add that this was 1007 of what was, anticipated from 

the first mission--5 days of camera operations, with restrictions 

on roll angles and frequency of operation). " 

3. Page 26: The omission of any "contingency" funds 

in the MOL line of the accompanying chart on page 27 probably 

needs explanation. It appears a statement justifying this L,,„ 

omission should be made on page 26 (i.e., detailed project 

definition, thus high confidence in cost estimates) needed on 

page 26. 

The preceding comments are not significant--all in all, 

this appears to be a good supplement- summary. 

Attachment 4.9- . Stewart 

BYE 21229-66 

*iv 

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BYE UM 

CONTROL SYSTEM 

DORIAN • 

To SECRET NRO APPROVED FOR 

RELEASE 1 JULY 2015 

(S) NATIONAL RECONNAISSANCE OFFICE 

WASHINGTON, D.C. 

THE NRO STAFFI, September 23, 1966 

Dr. Flax: 

I have reviewed the attached and have the following 

comments: 
NIRO kPPROVED FOR 

RELEIASE. 1 JULY 2015 

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Control System " 

MOL/DORIAN RECONNAISSANCE 

SYSTEM 

Introduction 

The attainment of ground resolution with a satellite photographic 

reconnaissance system represents a major technical achievement. The basic 

objective of the MOL Program is to deliver this performance utilizing the DORIAN 

optical photographic sensor. Of the many factors which contribute to, or affect, 

sensor performance, none is more elemental than the optical system design itself. 

The DORIAN sensor design is conservative, and draws on an extensive background 

of experience and state-of-the-art technology. However, the DORIAN sensor is 

very much larger than reconnaissance sensors we have developed previously, and 

translation of current experience and technology into the high performance required 

of DORIAN hardware is challenging. 

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Optical System Design 

The camera type selected is a tracking frame camera, which produces a number of individual photographs of a desired scene, rather than the more familiar film strip typically used in previous reconnaissance systems. A frame camera permits reduction of residual image smear to smaller values than 

appears practicable with a strip camera of similar size. This in turn permits use of a much longer 

focal length lens, reducing the effects of film grain on image quality. A desired scene may be photographed from several aspect angles on a single overflight, improving the stereographic rendition of a 

scene at preferred angles. Several different exposure times for each scene can be programmed to improve 

the image in highlight and shadowed areas. As the image in a frame camera is stationary, rather than 

moving past a slit, use of automatic devices to detect and correct residual image motion, and to correct 

for off-axis geometric image smear is greatly facilitated. In manned flights, the stationary image also 

permits direct crew observation through the main optics. 

The camera primary optical system is version of a Newtonian telescope, an inherently simple design. 

The Ross corrector lenses inserted in the light beam correct for residual abberations, and provide 

telephoto action to increase the effective focal length of the system. This telephoto Ross system is 

similar to the GAMBIT CUBED camera lens, and is capable of superior optical performance. Alignment, 

and focus tolerances are moderate. 

Fused silica mirrors of lightweight design were chosen for both of the large mirrors in the optical 

system. Other materials, particularly CER-VIT, and to a. lesser degree Pyroceram, were also considered. 

Although they offer promise for the future, these latter materials are not as thoroughly developed as 

is fused silica. Fused silica is clearly the lowest risk material, and it does deliver the required 

performance. 

Aiming the camera and its optical system at a desired scene from a moving satellite is a problem of 

major proportions with cameras the size and weight of the DORIAN sensor. Rather than moving the entire 

satellite, or gimballing the entire optical system and pointing it at a target, a simple flat mirror was 

selected for the moving element of the system. This configuration closely resembles those of both GAMBIT 

and. GA1' CUBM, except that the DORIAN flat mirror, rather than being fixed at pre-selected angles, 

actively tracks the ground scene so that the image at the film plane remains stationary. This design is 

simple, makes the most of our current experience, and simplifies access to the camera, its film supply, 

and film recovery devices. 

The above factors establish the basic performance potential of the sensor. They ret- Jlt in a. sesor 

Gay desin optimized for the attainment of ground resolution., yet are within the react' c7f 

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OPTICAL SYSTEM DESIGN 

CAMERA FRAME - REDUCED SMEAR 

- VARIABLE STEREO 

- VARIABLE EXPOSURE 

- FLEXIBLE LENS DESIGN 

- STATIONARY IMAGE , 

LENS TELEPHOTO ROSS - SIMPLE DESIGN. 

- GOOD PERFORMANCE 

- MODERATE ALIGNMENT TOLERANCE . 

- MODERATE FOCUS TOLERANCE 

MIRROR MATERIAL FUSED SILICA - STATE OF ART 

- LOW THERMAL INERTIA 

- LIGHTVvrEIGHT CONSTRUCTION 

- GOOD PERFORMANCE 

AlmiNG METHOD FLAT TRACKING r•-•(:%(1G MASS 

MIRROR 

TLE. 

-•EASY CAMERA ACCESS 

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MOL OPTICAL PAYLOAD 

The DORIAN sensor is assembled into the MOL Mission Module, 35 feet in length and 

10 feet in diameter, together with its basic supporting equipment. The camera (two cameras 

in the manned version) is supplied with 16,800 feet of film which is adequate to produce 

15,000 frames of photography, as many as 12 per target, per 30 day. mission. 60-75 cloud 

free targets per day can be photographed. Photographs have a round image format, about 

9 inches in diameter. 

Both the flat tracking mirror and the parabolic primary mirror are about six feet in 

diameter, and each weighs, even with lightweight construction, in excess of 1500 pounds. 

The basic resolution capability of the DORIAN sensor is established by the physical 

size of the major lens components and influenced by the design factors just discussed. 

The effective lens aperature, which is a function of the diameters of both the primary 

and tracking mirrors 

Best nerforma obtained at the center of the field. 

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—.‘"JAS6}1474DORIAN 

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PAYLOAD • 

kELLT:VE API:1;71;E 

1.4 nazi. FIELD OF VIEW AT 

80 H.M. ALTITUDE 

LICIT PATH FCLDIN 

FLAT 

VISUAL 

EYENECF 

FRAILF. CAPE.RAS 

ks 

.CC17.■:ECTOR LEUS 

FLAT TRACKING MIRROR 

71 INCH WA, 1E00 Ls. 

PARABOLIC MT:R.0R ASSY 

71 1NCH DIA. 1520 lbs. 

REMAINING COLiPDXEVTS 

3710 Is. 

LLAT 7r.:Arvri!ri 

VI.Eqaki; 

4O EACH SIDE 

30° FOREWARD 

40°AFT 

OLC:3I/DORIAN 

TOTAL 7C.7, 

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RESOLUTION CONSIDERATIONS 

The physical design of the DORIAN sensor determines its static performance capabilities. 

When the sensor is used in orbit, other factors come into play in the determination of its 

dynamic performance. 

To set up and maintain sensor performance in orbit, certain dynamic errors directly associated 

with the optical system and camera must be detected and corrected. These are principally on-axis 

errors caused by misalignments of optical components, by departure from best focus, and the image 

smear caused by residual motion of the Jrmge in the film plane due to differences in computed 

mirror tracking rates and actual tracking rates required. These errors occur continuously during 

flight, and must be continuously sensed and corrected. The basic optical system itself is used 

as a tool in performing these functions. 

Sensor performance in orbit is also affected by Pointing Error, which is a combination of 

several different but interdependent errors, which result in displacement of the desired target 

from the center of the sensor field of view. Unlike the previous category of errors, Pointing 

Error is not a direct function of the basic sensor design, although the sensor field of view, will 

affect its severity. It is largely due to effects external to the sensor itself, principally 

uncertainties in target location, in the exact location of the satellite in its orbit, and the precise 

attitude (and rate of change of attitude) of the satellite which carries the sensor. Target size, 

a fixed parameter, also influences the relative significance of the Pointing Error. For example, 

for large targets, it is important to keep Pointing Error sufficiently small so that none of the 

target falls outside of the field of view. Errors contributing to Pointing Error are most effectively 

minimized by careful vehicle system and ground navigation design and operation. 

Another major error is due to smear across the entire format caused by geometric factors 

associated with location of the vehicle with respect to the target. This error is discussed further 

in the following pages. 

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RESOLUTION CONSIDERATIONS 

RESOLUTION 

XIS ERRORS 

• 

TAR G ET 

s I zE 

OFF—AXIS ERROR

S 

I1flT /DORIAI' Handl,± BYEMAN 

27ystem 

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CROSS FORMAT 

IMC 

LENS 

APERATURE 

0 

FOCAL 

LENGTH 

TARGET 

LOCATION 

SENSOR 

RATE ERROR 

r 

NAVIGATION 

ERROR 

SENSOR 

ATTITUDE 

IMAGE 

VELOCITY 

ALIGNMENT 

FOCUS 
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CROSS-FORMAT IMAGE SMEAR CORRECTION 

Photographic images taken at oblique angles from the satellite will be subject to smear 

off the optical axis. That portion of a scene in the field of view farthest from the moving 

satellite will appear to move by at a slower rate than nearer portions of the scene. The 

image tracking sensor can compensate for motion at the center of the field of view, but cannot 

correct for the differential motion at the edges of the field. This will cause a fall-off of 

resolution toward the edges of the field of view which approximates 44% at moderate oblique 

angles of 20°. If a target cannot be placed with certainty in the center of the field of 

view, then additional correction must be provided. This can be done by adjusting the position 

of the slit in the camera's focal plane shutter, and, during the exposure sequence, rotating 

the camera platten to exactly match the differential image motion. This "cross-format" IMC 

device is intricate, and must be capable of exacting performance. However, its use results 

in a marked improvement in image quality for targets falling near the edge of the field of view. 

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CROSS-FORMAT IMAGE S lEAR CORRECTION 

POINTING ANGLES: 20° 0:3LIQUE, 10eFOREWARD 

DEPARTURE FROM ON—,AXIS RESOLUTION, PERCENT. 

LINES OF CONSTANT 

RESOLUTION 

DIRECTION 

OF TRAVEL 

SHEAR AND IN—TRACK 

EXPANSION CORRECTION 

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PERFORMANCE REQUIRED FOR RESOLUTION 

A summary of the functions necessary to attain resolution can be assessed in 

terms of the equipment needed to perform the functions, how well the functions must be performed, 

and the development risks involved. It becomes readily apparent that performance requirements 

for the automatic mode are quite demanding, and will require improvement over what current 

technology can provide. 

In the past year considerable progress has been made in the evolution of technically feasible 

devices needed to produce photography at resolution in the automatic mode. Although 

technically feasible, the development risk in producing flight worthy hardware remains moderately 

high, particularly for new devices for cross-format smear compensation, and image tracking. Also, 

the final performance capabilities of some devices, particularly the low drag accelerometer, will 

not be known until actual flight. 

Departures from the performance required of the automatic devices add in a cumulative fashion. 

Hence all devices must perform to specification to produce resolution. In the early 

development phases, crewmen can correct, or manually perform these essential functions while at 

the same time observing and analyzing defective equipment, so that remedial action can be taken 

for subsequent flights. This technique reduces overall development risk, and expedites the ultimate 

development of the automatic equipment. 

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PERFORMANCE REQUIRED FOR RESOLUTION 

FUNCTION EQUIPMENT 

REQUIRED 

REQ'D PERF.ORM 

AUTO MODE 

REQ'D PERF. 

MANNED MODE 

IMPROVEMENT 

REQ'D AUTO MODE 

DEVELOPMENT 

RISK 

TARGET AQUISITION SCF 

Precision Navigation Star Tracker 

Pointing 

Attitude Reference Low drag accelerometer 

I-nage Tracking Image velocity sensor 

Cross track — 2.5 N.M. 

In track — 2.5 N.M. 

Altitude 1.0 N.M. 

Not required 

Not required 

Aided tracking only 

required 

Factor of two 

None 

Factor -zTen 

New 

Low 

Moderate 

Moderate 

Moderately high 

Cross-format 

Image smear 

compensator 

50% reduction of 

smear at edge of 

field 

Not normally 

required Sn-.:Dr Correction New Moderately high 

Same New Optical System 

Al icInment 

Automotic optical 

alignrrnt system 

Primary mirror Moderately high 

Focus Some Factor of Two !!oderate Focus sensor 

-111e?t4,4=DOR IA N Handle Via BYEMAN 

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PROJECTED PERFORMANCE 

The performance of the MOL vehicle with the DORIAN sensor can be described by a series of 

curves which plot the cumulative probability that photographs taken in a typical mission will 

equal or exceed a specified ground resolution. Referring to these curves, it can be seen that 

the great majority of photographs taken with either the fully automatic mode (curve 2) or the 

manned mode flown le-LI, t'fle automatic eouipment functioning (curve 1), will have ground resolutions 

of These two curves are essentially the same, with a slight edge to the 

manned system due to a capability of crewmen to center targets in the sensor field of view. 

Curve 3 describes manned mode performance without help from automatic equipment, and again shows 

collection of the majority of photographs at ground resolution. Curves 4 

and 5 show successive degradation of performance which would result in the automatic mode with 

successive malfunctions of automatic equipment. During early development phases, crewmen aboard 

the MOL can substitute for malfunctioning equipment, and restore mission performance to the level 

of curve 3, thus insuring that the required level of performance can be maintained, until automatic 

equipment reaches the necessary level of development maturity. 

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7177,7T/DORIAN 
• 

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GEOMETRIC MEAN GROUND RESOLUTION 

/DORIAN 

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RELEASE 1 JULY 2015 Control System , 

BIMODAL SYSTEM CONFIGURATION 

To insure that the ground resolution objective is in fact obtained, it was 

considered prudent to develop MOL so that it was capable of operating in two modes - -

completely automatically without crewmen aboard, and completely automatically with crewmen 

aboard, but so configured so as to permit crewmen to overcome malfunctions. The two modes, 

with the principal exceptions of life support, film handling and recovery, and design lifetime in orbit, are essentially the same. Hence the problem observation and analysis 

performed by crewmen will, as intended, apply directly to the automatic mode. 

When crew associated components, such as the Gemini B, are replaced by a conventional 

nose fairing, a series of data recovery capsules, and similar equipment, additional payload 

weight becomes available. This weight can be utilized for additional orbit sustenance fuel, 

and other consumables permitting the automatic mode to have a mission design lifetime of 60 

days. In the automatic mode, an automatic film transport system is installed to feed exposed 

film to the data recovery capsules. In the manned mode, crewmen load the recovery capsules. 

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-51PettEtiDORIAN 

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MANNED MODE 

30 DAY DESIGN LIFE 

IMAGE TRACKING SENSOR 

IMC ACROSS FORMAT 

FOCUS SENSOR 

UTO ALIGNMENT 

LOW DRAG ACCELEROMETER 

STAR TRACKER & RATE GYRO PACKAGE 

7 

D, 

L 

IMAGE TRACKING SENSOR 

IX ACROSS FORMAT 

FOCUS SENSOR 

F ILM TRANS PORT 

UTO ALIGNMENT 

LOVI DRAG ACCELEROMETER 

STAR TRACKER & RATE GYRO PACKAGE 

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BIMODAL SYSTEM CONFIGURATION 

AUTOMATIC MODE 

60 DAY DESIGN LIFE 

- 

- - - - d IL::.1- LA 

5 

• • ____ 

.., V. 1 

-L. 

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UTILIZATION OF MAN IN THE DEVELOPMENT PHASE 

Nan's utilization in the MOL development phase centers around three principal activities. 

First. To preserve the quantity and quality of reconnaissance photography from the outset 

of the program. By being effectively functionally redundant, crewmen can perform the functions 

of most automatic equipment associated with mission photography. 

Second. To preserve effective spacecraft performance throughout a full duration mission. 

Again through functional redundance, crewmen can avoid the necessity of early mission aborts 

by replacement, repair, or manually working around vehicle system malfunctions. In this sense 

crewmen also observe and analyze the nature and characteristics of malfunctions and failures, 

both in vehicle systems, and in sensor systems. The development process is accelerated through 

this activity, accompanied with a higher confidence that solutions to in-space difficulties 

will be effective. 

Third. An experimental program to develop knowledge of how crewmen might improve quantity, 

quality, and reliability of photographic reconnaissance, and as well, to determine if use of 

crewmen would result in unique contributions to reconnaissance not otherwise attainable. 

Ground simulations have shown that crewmen are definitely of direct mission value with 

respect to the first two points. Again, simulations lead us to conclude that man may also 

provide some unique values to intelligence returned, but experimental investigations in orbit 

would clarify and quantify this value. 

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IL 17LAT [ON OF [ DEVE N T P C 

- INSURE ATTAINMENT OF USEFUL RECON:1AISSANCE CAPABILITY 

EARLY IN DEVELOPMENT PROGRAM 

- AVOID EARLY MISSION ABORTS BY REPLACEMENT, REPAIR, 

OR MANUALLY Vi'ORKING AROUND /.',ALFUI!CTIONS 

- EXPERIMENTAL INVESTIGATIONS INTO THE NATURE AND VALUE 

OF CRITICAL CONTRIBUTIONS OF MAN TO PHOTOGRAPHIC 

RECONNAISSANCE AND ENHANCEMENT OF INFORMATION CONTENT 

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DETECTING-HIGH VALUE INTELLIGENCE 

An example of a unique contribution which could result through utilization of crewmen is 

the examination of alternate targets ahead of the spacecraft. This technique becomes attractive 

because the DORIAN field of view is small compared with GAMBIT and GAMBIT CUBED. 

The probability that additional or alternate targets will appear in the field of view is 

very low. Hence a premium is placed on the selection of targets of the highest intelligence value. 

Although preliminary studies show that about 70% of all targets can exhibit transient conditions 

which are of high intelligence value, these conditions will occur at only about 6% of the targets 

at a given time. These events are sufficiently rare as to render unlikely the possibility that 

they can be predicted for specific targets, and programmed for automatic photography. However, 

if crewmen were to examine alternate targets in the spacecraft's path, and interrupt the automatic 

photography sequence if a target of exceptional high intelligence value were encountered, a 

two to three-fold increase in the collection of this category of photographs would result over 

random encounter in the automatic mode. A recent GAMBIT mission illustrated here is shown with 

DORIAN fields of view overlaid on the targets collected in the GAMBIT film frame. The programmed 

GAMBIT targets are superscribed by an "X." They proved to be inactive. Two other unprogrammed 

targets did fall in the field of view. One of these contained intelligence information of 

inestimable value. As the inset shows, this particular photograph shows SS-7 missiles exposed 

on a soft Soviet ICBM site, and confirmed the suspected re-fire capability of these sites. This 

photograph would have been missed by the DORIAN sensor if the DORIAN sensor had photographed 

the pre-programmed targets only. 

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Control Systems Jointly -,W61 6TerPryttORIAN/GPZEIIT/RUFF 

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DETECTING t IGH VALUE INTELLIGE110E 

TARGETS PROLIFERATE AT DORIAN 

FIELD OF VIEW 

DORIAN FIELD OF VIEW OPERATORS INSPECT ALTERNATE 

TARGETS 

y PROGRAMMED GAMBIT 

— TARGETS 

TARGET crni 

EXPOSED MISSILES 

• 

SIMULATIONS SHOW THE INSPECTIONS 

CAN BE DONE 

70% OF ALL TARGETS INCUR TRANSIENT 

CONDITIONS WHICH EXPOSE HIGH VALUE 

INTELLIGENCE 

MANNED MODE CAN PRODUCE 200% TO 

300% OF THE OUTPUT OF SUCH PHOTOS 

• BY RANDOM ENCOUNTER IN THE 

AUTOMATIC MODE 

Tor Sr.atET/RUFF/DORIAN/GAMBIT 

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OTHER MANNED-FUNCTIONS 

Other functions which may be enhanced, or uniquely performed by crewmen have been studied, 

and will be subjected to experimental evaluation in orbit. Most of these functions are directly 

related to increasing the value of, or the timeliness of, intelligence returned. A specific 

activity of this nature is the selection of particular photographs for processing aboard the 

vehicle, and transmitting by radio link the intelligence bearing portion of the images to the 

ground. 

The vehicle, in orbit, is immediately available for special surveillance activities during 

crisis conditions. The orbit altitude can be altered to cause, for example, the entire SinoSoviet land mass to be brought under surveillance in a repeating 3 day cycle. Crewmen aboard, 

can be highly responsive to specific intelligence needs in rapidly developing situations where 

pre-programming may not be possible. 

An alternate and interesting intelligence mission, which could be accomplished in the manned 

mode and without interference to the basic reconnaissance mission, 

Another aspect of the utilization of crewmen lies in visual reconnaissance. The values of 

this activity are very difficult to quantify at this point in time. Yet the human eye is capable 

of grasping much information which cannot be captured on film. Even simple functions such as 

color discrimination or counting, performed simultaneously with the programmed reconnaissance 

activities may have considerable value for detecting *changes in order of battle, or in establishing 

levels of activity in particular target areas. A carefully devised experimental program is being 

developed to investigate the value of this technique.: 

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OTHER MANNED FUNCTIONS 

FINDING MOBILE AND TACTICAL TARGETS 

O SELECTING PARTS OF PHOTOS FOR QUICK-RESPONSE READOUT 

O LOADING COLOR FILM AND OTHER SPECIALIZED FILM 

O SURVEILLANCE IN CRISIS CONDITIONS 

• VERIFYING TARGETS HAVE BEEN PHOTOGRAPHED 

SELECTING CLOUD-FREE TARGETS 

0 

0 CHOOSING VIEW ANGLE REVEALING MOST INTELLIGENCE 

INSPECTING, INCIDENTAL TO OTHER FUNCTIONS, MANY MORE TARGETS 

THAN CAN BE PHOTOGRAPHED. 

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WHOLLY UNMANNED SYSTEM 

The configuration shown schematically is one of several which resulted from a two-contractor 

(General Electric and Lockheed) study funded in response to the March 21, 1966 letter from the 

Director of the Budget. Although MOL is designed for a completely automatic mode of operation, 

Mr. Schultze's request was for a costing exercise on an independently-developed unmanned system. 

For study purposes, the DORIAN mission module was taken as government-furnished and it was assumed 

that all the critical automatic devices would function with the necessary precision. The tabulation 

shows a 30-day and a 60-day configuration. The 60-day design life was judged to be superior from 

the standpoint of economy and is the version most comparable to the MOL automatic mode, which also 

can achieve 60 days active orbital life. The 60-day wholly unmanned system would employ a 

7-segment Titan IIIC. 

3ECRDT/DORIAN 

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fUrb1.'i 0 L LY UNPAA NED SYS'I'F. 

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■i 

L 

DIRECTION 

OF FLIGHT 

RECOVERY 

AND MISSION 

SUPPORT MODULE 

CONTROL MODULE MISSION MODULE 

T—II1C, 5-SEG SRM T-111 C,7 -SEG SRM 

DESIGN LIFE 

WEIGHT ON ORBIT 

DATA RECOVERY VEHICLES 

DEVELOPMENT LAONCHLS 

DEVELOPMENT COST 

RECURRING COST 

30 DAYS 

21,000 pounds 

4 

10 

$1131 MILLION 

45.5 MILLION 

60 DAYS . 

32,000 pounds - 

6 "1-0 8 

10 

$1503 MILLION . 

58.5 MII.._LION 

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REACHING PROGRAM MATURITY 

The cost estimate for developing an unmanned system is based upon a 10-launch orbital 

test phase. MOL is scheduled to have only 7 launches, including the first two unmanned booster 

and GEMINI B reentry tests. The prediction of a greater number of unmanned test launches is 

supported by past experience. By comparison, GAMBIT CUBED, a much simpler design, is scheduled 

for 8 launches for development/operational suitability testing; These 8 launches are expected 

to produce an operational product equating to at least half that which would be produced by 8 

mature GAMBIT CUBED systems. The first launch of the unmanned system would be paced by the 

mission module delivery date and the test program would continue for more than a year beyond 

the MOL schedule. 

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REACHMG PRU AM P,R A T 

UNMANNED SPACECRAFT: 

o IN ORBITAL TEST PHASE, EXPECT SOME FAILURES EARLY IN THE MISSION 

o EXPECT SUCCESS RATIO TO GROW TO 70% IN 10 LAUNCHES 

• 

MANNED SPACECRAFT 

o RELATIVELY HIGH SUCCESS RATIO FROM BEGINNING 

. NUMBER OF DEVELOPMENT LAUNCHES: 

o 1AOL: 7 LAUNCHES, INCLUDING 2 BOOSTER QUALIFICATION, 3 MANNED, 

2 AUTOMATIC MODE 

o UNMANNED: 10 LAUNCHES 

COMPARATIVE SCHEDULES: 

CY 69 CY 70 CY 71 CY 72 

•

• I !B 18 • A MA 

UNMANNED j I] A )%_. I 

8:booster 1A:: manned A automatic 

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DEVELOPMENT COST COMPARISON 

The major expense items in MOL above the cost of unmanned systems are the laboratory module 

and the GEMINI B. The total unmanned mission module cost figure is higher because of the greater 

number of launches.. The control vehicle, replacing the laboratory, would be an important 

development task. The figures on this chart constitute the comparison requested by the Director 

of the Budget. Our confidence in the accuracy of MOL cost figures has improved as a result of 

Contract Definition activities, hence no contingency figures are shown. 

DORIAN 

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REL ASt 1 JULY2016 

DEVELOPMENT CO3-1 CO',12ARISON 

30 - DAY 60 - DAY 

Wholly Unmanned V/holly Unm.:nned 

(10 LAUNCHES) (10 LAUNCHES) 

MO L 

(7 LAUNCHES: 

2 Booster, 3 Manned, 

2 Unmanned) 

11.0.100....1,11r2C1.01:21. 

LABORATORY OR 

Ver.,,MMUMI:rirai.2.77.1.1=.0101•1. 

CONTROL VEHICLE. 235 370 720.4 

MISSION MODULE 532 532 426,8 

GEMINI B 216.5 

BOOSTER 183 340 312.0 

OTHER SYSTE1AS 30 . 63 31.0 

SUPPORT 17 30 48.1 

HEAT-SHIELD TEST 22.5 

MILITARY CONSTRUCTION 31 31 40.7 

CONTINGENCY 103 137 

TOTAL 1131 1503 1818.0 

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SUMMARY 

The principal points which have been dIscussed are summarized here. The detailed work of the 

past year has added confidence that the objective can be achieved, resulting from the concentrated attention which has been directed toward the major technical problems. It will be 

remembered that early in the MOL planning stages some experienced contractors expressed considerable 

doubt that an optical system of the desired performance could be built. Such doubts no longer 

exist. A similar effect on automatic system design has been noted in which increased attention 

during the past year has been productive in the evolution of concepts for new devices for 

correction of focus and image motion errors. 

The results of the cost study just completed show that the cost differential between MOL 

and an unmanned system comparable to MOL automatic mode is in conformity with the previous 

estimate ($300 - million) made in the August 24, 1965 Memorandum for the President. 

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c:".% r: r b rl f7,1 IMN, • 

1. THE MOL PROGRAM IS PROGRESSING WITH THE DEVELOPMENT OF AIIIRECONNAISSANCE SYSTEM 

2. THE OBJECTIVE CAN BE ACHIEVED WITHIN THE PROGRAM SCHEDULE. 

3. DURING THE PAST YEAR, PROMISING DESIGN.CONCEPTS HAVE EVOLVED FOR 

AUTOMATIC—MODE DEVICES. • 

THE MANNED MODE HAS THE POTENTIAL TO: 

A. EXPEDITE DEVELOPMENT OF AUTOMATIC DEVICES 

.B. REDUCE THE NUI,MER OF DEVELOPMENT LAUNCHES 

C. INCREASE IN PRODUCTION DURING DEVELOPMENT PERIOD 

D. INCREASE THE VALUE OF THE INTELLIGENCE 

5. THESE FACTORS WILL BE EVALUATED IN THE MOL PROGRAM 

6. THE MOL COST ESTIMATE IS $1.82 BILLION. A SEPARATE UNMANNED SYSTEM COMPARABLE 

TO THE MOL AUTOMATIC MODE COULD BE DEVELOPED FOR $1.5 BILLION. THE PRICE, 

THEREFORE, OF CONTINUING THE DUAL OPTION IS ABOUT $320 MILLION. 

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