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Col 

Coord. Gen Stewart 

SAFSL Approval Dr. Yarympvych 

SAYSL Sign Gen Evans 

Ca„gt Goolsby 

Flight Objectives for MOL 

PROBLEM 

SAFSLT 50945 .jdk 

Jan 27, 1967 

1. Action needs to be taken to establish general flight objectives to be 

accomplir;hed by the end of the MOL Development Program. 

DISCUSSION 

2. A proposed MOL Program:Directive on the subject has been prepared and is 

attached as Attachment 1 to Tab A. Included also, as Tab A, is a.letter of trans... 

mittal to the Deputy Director, MOL. . . 

2 The intent of MOL Program Directive 67-1 is to 

a. Guide the implementation of the entire flight test program. 

b. Orient the detailed flight test plan as to content, relationships, 

test philosophy, and contingency planning. 

L1. The letter of transmittal: 

a. Forwards the MOL Program Directive to the Deputy Director, MOL. 

b. Requests the MOL Systems Office to prepare and submit for approval 

specific detailed objectives for each of the seven flights. - 

c. Provides a suggested format which illUstrates the level of detail 

rec, uired for each flight. ••• 

RECOMMENDATION 

- • 5. That the attached proposed Plight Objectives Directive be signed and transmitted to the Deputy Director, MOL for implementation. 

• 

TrrigIVa 

- 1 Atch 

`-,:b A- Proposed ltr to Deputy Director, MOL 

atchs. . 

DI1,6 D. GO!OLSBY, CAPT, 7 UIT 

Chief; 7czt 

:e.rc:a41Ucs, S.1-SD 

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1.TIMAPK605b-FOA-"'"' 

IRELgASE 1 JULY 2015 

40, 

•FES 187 

MEMORANDUM FOR THE DEPUTY DIRECTOR, MOL 

SUBJECT: Flight Objectives for MOL 

MOL Program Directive 67-a, which is attached, contains the general 

flight objectives to be accomplished by the end of the MOL development 

program. It is directive in nature and will be used to guide the 

implementation of the entire flight test program. It is intended to 

orient the detailed flight test program as to content, relationships, 

and test philosophy. 

The stated general flight objectives need to be expanded in specific 

detail. Attachment 2 provides a. suggested format which illustrates the 

level of detail required for each flight, and differences in content 

between flights, using flights 3 and 4 as examples. It is to be 

,. emphasized that the examples are illustrative in nature and are not 

•- intended to constrain the Systems Office from establishing the actual 

content of the two flights, in context with the overall flight program. 

• 

It is requested that the Deputy. Director, MOL prepare and forward 

to the Director, MOL, for review and approval, specific detailed 

objectives for each flight, in a'format similar to that furnished. It 

is recognized that revisions to the detailed flight objectives will 

be required during the development program, as additiOnal knowledge is 

gained by flight testing. Any such changes will require approval of the 

Director, MOL prior to publication. 

• 

2 Atchs 

1. MOL Program Directive No. 67-2. 

2. Detailed Flight Objectives, Flights 3 and '1t 

Copies to: 

SAF-SL Official 

SAF-SL Read 

ECG Read • 

HARRY L. EVANS 

Major. General, USAF 

Vice Director, MOL Program 

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:1 T17 

tr °.1 CVntrui SYS= 

MANNED ORBITING LABORATORY PROGRAM DIRECTIVE 

NO. 67-2 

PLIGHT OBJECTIVES 

FOR THE 

MANNED ORBITING LABORATORY PROGRAM 

8 VIR:ARY 1967 
• .,• 

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TABLE OF CONTENTS 

I. PURPOSE 

II. INTRODUCTION 

III. GENERAL FLIGHT TEST OBJECTIVES 

IV. FLIGHT TEST PROGRAM PHILOSOPHY 

V. CONTINGENCY PLANNING 

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I. PURPOSE 

The purpose of this directive is to specify the General Test Objectives 

(GTO) of the flight test phase of the MOL Program and to define an 

orderly approach for achieving these objectives on a flight-by-flight basis. 

The document is directive in nature and is to serve as the basis for prograd 

planning and actions during the development phase of the program as well as 

in the formulation of Detailed Test Objectives (DTO) for each individual 

flight. 

The baseline plan for the flight test program contained herein assumes 

a fully successful program. Provision for contingencies which may be 

occasioned by gross failure of one or more flights is contained in Section 

Contingency Planning. 

II.. INTRODUCTION 

The objectives of the MOL Program are planned to be accomplished in a 

seven-flight program, the individual flights allocated as follows: 

Flight 1- Unmanned/Gemini B Qualification/TIIIM Development 

• 

Flight 2- Unmanned/TIIIM Development/Laboratory Structure; 

Qualification 

Flight 3- MAnned/Automatic 

Flight 4- Manned/Automatic 

Flight 5- Manned/Automatic 

Flight' 6- Automatic 

Flight 7- Automatic* 

*The option is to be preserved for flights 6 and 7,to be flown in the 

manned mode; . See Section V, Contingency Planning. 

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A. Primary Objectives: 'Agcomplishment of these objectives is 

mandatory. 

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The MOL Program centers around an Orbiting Vehicle, in which men 

will carry out reconnaissance operations for durations of 30 days. The 

Orbiting Vehicle consists of a Laboratory Module, Mission Module, Mission 

Payload and a Modified Gemini Spacecraft (Gemini B). The Orbiting Vehicle 

will be launched by a Titan IIIM from Vandenberg Air Force Base. During 

the ascent to orbit, the flight crew will be in the Gemini B. After 

achieving orbit, the crew will transfer to the Laboratory Module to perform 

the on-orbit tasks as programmed. At the end of the mission, the crew will 

return to the Gemini B, separate the Laboratory Module from the Gemini B, 

de-orbit and re-enter, and be recovered from a water landing. Proviiions 

will be made for disposal of the Laboratory and Mission Modules in a 

preselected open sea area upon completion of the mission. 

An alternate, automatic (unmanned) configuration will be provided in 

which the Orbiting Vehicle will consist of a Laboratory Module, a Mission 

Module, Mission Payload, and a Mission Support Module. 

The objective of the High Resolution Photographic.Reconnaissance System 

in MOL is to acquire photographs of high intelligence value of denied areas 

in both manned and automatic modes, achieving at least ground 

resolution in the manned mode with resolutions as close to as 

possible in the automatic mode. 

III. GENERAL FLIGHT TEST OBJECTIVES 

The objectives of the seven-flight program listed in order of priority 

are: 
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1. To demonstrate the ability of the MOL High Resolution 

Photographic Reconnaissance System to acquire photographs of high 

intelligence value in both manned and automatic modes, achieving the, highest 

possible ground resolution in all modes and Operating conditions. 

2. To obtain quantitative data which will permit assessment 

of the nature and value of critical contributions of man in increasing the 

quantity and quality of intelligence data obtained by use of the MOL 

intelligence collection system. Sufficient data will be obtained to permit 

an unequivocal comparison between optimized manned and optimized unmanned 

modes of operation. 

3. To demonstrate a 30-day capability to perform the mission 

cited in 1., above. 

B. Secondary Objectives: Accomplishment of objectives 4 through 

6 will result in substantive information to validate decisions related 

to the future of the military space program, e.g., the nature of the follow-

. on MOL program, manned/unmanned considerations, new missions, etc. These 

objectives are secondary only from the point of view that their accomplishment is not to interfere with accomplishment of the primary objectives. 

Unless subsequently added to the baseline configuration) provision for 

weight and space to provide for equipments, devices, etc., which will aid 

in accomplishment of secondary objectives will be incorporated into the 

vehicle on a space available basis. In any event, these objectives will 

be accomplished within the capability of the baseline system to do so. 

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4. To obtain data'which will permit valid assessment of 

the military worth of other possible missions in space, manned or unmanned, 

e•g•ji Crisis Surveillance, etc. 

5. To obtain quantitative data concerning optical technology 

and design for advanced systems which, if manned, can give ground resolution 

6. To collect bioastronautic data for longer duration missions. 

C. Tertiary Objectives: Accomplishment of objectives 7 and 8 

will provide valuable information of general nature pertaining to general 

military and scientific space technology. These objectives are to be 

accomplished on a non-interference basis with primary and secondary objectives. 

7. To conduct experiments which will contribute to improvement of military space technology. 

8. . To conduct experiments of scientific nature. 

IV. FLIGHT TEST PROGRAM PHILOSOPHY 

The individual flights Of the seven-flight program are to be conducted 

in a logical sequence which insures that: 

A. By the end of the flight program, all flight objectives will 

be successfully achieved, including tertiary objectives to the extent 

possible. 

B. The individual tasks assigned for accomplishment within each 

flight, and from flight to flight, are conducted in a progressive sequence 

of tasks and flights, first in establishing space worthiness qualification 

of the basic MOL system, and thence through progressive accomplishment of 

program objectives in accordance with their respective priorities. 

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C. Loss of a flight or flights, e.g., through gross failure, 

will have minimum adverse impact on accomplishment of the three top 

priority program objectives. 

Ground rules applicable to the sequential ordering of sub-tasks, 

tasks, and flights, and to the flight test program in general, are as 

follows: 

A. Safety of the crew is paramount. Therefore, establishment of 

the space worthiness of the MOL System from a human safety viewpoint will 

take precedence over conduct of mission, tasks, in the following order 

of priority: 

1. The capability of MOL Systems, subsystems„and components 

critical to the ability of the crew to successfully achieve orbit, and 

to return safely, shall be demonstrated prior to conduct of manned flight. 

2. The capability of the Orbiting Vehicle to. safely maintain the crew in orbit and to permit their safe return to earth in .the 

Gemini B will be assured prior to and during crew engagement in mission 

activity. 

3. In-orbit failures of systems, subsystems and equipments 

to the point where failure of an additional subsystem would preclude safe 

return of the crew will be cause for mission abort. 

B. The seven-flight program will be considered primarily as a 

research and development program, although the third and subsequent flights' 

are intended to produce valuable target intelligence. Conflicts during. 

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C. During initial mission flights, after the manned mode has 

been successfully demonstrated, priority will be given to successful 

demonstration of the automatic mode rather than to acquisition of real 

target photographs, unless both objectives can be accommodated concurrently. 

D. The mission plan for each manned flight will include con- • 

tingency provisions which will insure maximum beneficial utilization of 

crew duty time in furtherance of program objectives, by priority, in the 

event that in-flight failure precludes adherence to the nominal mission 

plan. 

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flight between the requirement to take photographs of actual targets and 

R&D efforts (e.g., troubleshooting) to perfect manned or unmanned mission 

equipment, which cannot be otherwise accommodated, will be resolved by 

the Program Director, with due consideration to guidance provided by the 

DNRO. 

E. Failure of man-related components during orbital test or 

inability of the crew to perform assigned tasks (where such failures do not 

involve crew safety) will not be cause for abort, as long as useful 

intelligence is being produced by the photographic reconnaissance payload. 

F. At least one 30-day manned mission will be completed prior 

to an unmanned mission unless the limiting factor turns out to be the 

inability of man to perform effectively for 30 days on orbit. 

V. CONTINGENCY PLANNING 

Accomplishment of MOL flight test objectives in the seven-flight program 

is predicated on all flights being successfully accomplished. Since there 

is a possibility that one or more flights may be unsuccessful, a contingency 

plan must be devised which insures maximum accomplishment of program 

objectives in. order_of priority, in the event that flight failures are 

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experienced. Contingency action must be based on broad consideration of 

the impact of any single flight failure or combination of several flight 

failures which would perturb the conduct and composition of the flights 

following the flight(s) that fail. A first order analysis of major flight 

failures which may occur will provide the basis for reconstituting the 

content of the subsequent flights and their timing, and assist in defining 

whatever additional resources must be planned for procurement so as to 

minimize the impact of such major failures on accomplishment of the flight 

test objectives. The additional resources for contingency actions will be 

identified as a part of the MOL follow-on program resources assuming the 

decision to proceed with a follow-on program of manned and unmanned flights 

is made by mid-CY-68 or earlier. 

General ground rules applicable to contingency planning are as follows: 

A. The capability of the Titan IIIM to safely place the allup manned MOL System into a nominal MOL orbit will be demonstrated by 

two successful unmanned flights prior to conducting a manned MOL flight. 

Minor anomalies during a flight performance demonstration will not 

necessarily preclude the flight from being considered successful, under 

this ground rule. 

B. One launch, re-entry, and recovery of a full-mission-configured 

Gemini B will be successfully demonstrated prior toconduct of a manned 

MOL flight. 

C. One successful flight demonStration of structural integrity 

of the Laboratory.Vehicle will be:accomplished prior to manned flight. 
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D. In any case, the option to fly the last two flights manned 

shall be protected, the decision will be based on flight results and the 

National Policy existing at the time. With respect to preserving this 

option, there are at least three eventualities to be considered (which, if 

they materialize, could have a severe retarding effect on the accomplishment 

of flight test objectives unless prior planning has been done to neutralize 

or minimize the impact of their occurrence): 

1. Failure of the initial unmanned Gemini B Qualification 

(GBQ) flight. 

2. Any malfunction or series of malfunctions on manned 

flights 3, 4 and 5 which would result in not having completed at least 

one 30-day manned mission prior to Flight 6. Conversely, something could 

occur to the automatic devices which would make it injudicious to fly 

Flight 6 in the automatic/unmanned mode. 

3. Manned flights may provide sufficient enhancement of 

intelligence content that the decision to go automatic/unmanned on 

Flights 6 and 7 might be inappropriate from the standpOint of intelligence 

collection. 

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FLIGHT #3 

I. MISSION TYPE: 

Demonstration of the attainment of an effective combination of man 

and machine for collection of useful reconnaissance of denied. areas. 

During this flight the system will be exercised in its normal operating 

mode. 

II. OBJECTIVES: 

A. LAUNCH VEHICLE: 

1. Demonstrate the launch preparation procedures and AGE 

adequacy for handling interfaces with a manned Gemini B and complete.- 

Laboratory Module and Mission Module. 

2. Reconfirm existence of acceptable levels of vibration), 

noise, and related environment within the orbiting vehicle as generated 

by the launch vehicle. 

3. Demonstrate the capability to safely inject the all-up 

manned orbiting vehicle into a normal MOL orbit. 

B. GEMINI B: 

1. Demonstrate the,capability to provide protection for the 

crew from the environments of ascent on-orbit re-entry, landing, and 

post-landing. 

2. Demonstrate the capability of Gemini B controls to bring 

the Laboratory Module up to a habitable state and display verification 

of habitability to crew prior to tranifer. 

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manned re-entry and landing. 

C. LABORATORY AND MISSION MODULES: 

1. Demonstrate the adequacy of crew accommodations and 

protection for a 30 day mission. 

2. Verification of satisfactory work and crew accommodation 

• ••,, 

(b) Adequacy redundant systems and switch over 

mechanism. 

ocean area. ' 

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3. Validate crew transfer procedures. 

• 

4. Demonstrate the capability to survive in a quiescent mode 

for a mission duration of 30 days and be brought back to a readiness for 

environments which fosters effective procedures, work patterns and personnel 

safety and which minimize discomfort, distraction, and any other factors 

which degrade human performance. 

3. Verification of performance of subsystems within acceptable 

tolerances. 

4. Determine maintainability, of subsystems as occasions arise 

no simulated failures): 

,' (a) .Malfunction indication, detection, and isolation 

• (c) Adequacy of sparey 

(d) Capability to adjust, replace, and/or 'repair.. 

5. Demonstrate adequacy of provisions to permit return to earth 

of data packages. " • 

6. Verification of programming and ability to cause the 

; • • 

Laboratory/Mission Modules to reenter:tor...impaCt in a,Suitablepre-selected 

. • • . 

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7. Demonstrate the capabilities for maintaining proper attitude 

and ephemeris. 

8. Demonstrate the capability of complete automatic operation, 

including fault isolation and corrective action. 

D. M1)SSION PAYLOAD: DEMONSTRATE: 

1. The structural integrity of the camera optical assembly, 

its mounts and launch locks, the tracking mirror mounts and its launCh 

locks during the launch vibration environment. 

2. The capability of the launch locks to release on orbit. 

3. Both manual and automatic initial and continuing alignment 

of the optical train elements. 

4. Proper payload operation in the thermal environment onorbit and the ability of the thermal control system to maintain 

temperatures within required limits for all operational modes. 

5. Mantled and automatic camera focus and exposure control 

through ranges required for all operational modes. 

6. Proper format, content, and imaging of the auxiliary data 

on the film edge. 

7. That the total image smear contributed by the payload 

operation is at or below acceptable values. 

8. Exchange of the primary cameras with the secondary (and 

reverse) and photographic objectives- in.minimum time. 

9. The capability to adequately perform on-board processing 

of the several types of film exposed in the secondary camera. 

10. Theuse- of the primary optics with variable magnification 

for visual obse

N

rvation of targets and verification of photographic success. 

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11. The proper operation of facilities provided for film 

handling including storage, loading and unloading the cameras, loading' 

the RV, cutting and• inspecting the film. 

E. CREW; 

1. Verification of the adequacy of man's interface with the 

MOL System in the conduct of the reconnaissance mission in both manual 

and automatic modes. 

2. Demonstrate man's ability to perform transfer, work in shirtsleeve environment in conducting missions for 30 days, retransfer to 

Gemini B, and effect safe reentry and recovery of crew and mission data. 

3. Demonstrate achievement of highest possible resolution 

photography in manned and automatic modes. 

4. Verify man's ability to enhance the value of target 

intelligence through: 

(a) Operation of secondary camera using various kinds of 

film. 

(b) Performing adjustments so as to insure peak performance 

of MOL system equipments. 

(c) Demonstrating ability to develop and process secondagy 

camera film, to select portions of film of high intelligence value, and 

to transmit the vital data to the ground in near real time using the wideband readout system. 

(d) Demonstrating the ability to load and eject from the 

orbiting vehicle the data recovery vehicle containing photographic film, 

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(e) Demonstration of the ability to reprogram the mission 

based on mission progress and updated data and commands furnished from 

the ground. 

(f) Taking high resolution photographs of unpreprogrammed 

targets of opportunity acquired through visual observation during target 

passes. 

(g) Taking corrective action to compensate for malfunctions 

of laboratory vehicle or mission module equipment. 

(h). Voice recording of significant intelligence information 

obtained through visual observation during target passes. 

5. Verify adequacy of target cueing material and method of 

display in facilitating target acquisition and pointing. 

6. Assessment of the effectiveness of man in increasing the 

quantity of quality information by conservation of sensor output 

recording media through judicious target selection. 

7. Measurement of man's well being, effectiveness, and operationaL 

techniques involving the man-machine interface including: 

(a) Man's wellbeing (adaptation and crew conditioning 

provisions for 30 day weightless operations). 

(1) Biomedical and behavioral trends. 

-(2) Zero "g" effects. 

(3) Adequacy of crew conditioning. 

(b) Man-machine-task operating techniques. 

(1) Complex task accomplishment'and assignment. 

(2). Verification of adequacy. of. time-line assignment. 

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(3) Adequacy of tethers and restraints in assisting 

performance., 

(c) Environment. 

(1) Radiation received by crew. 

(2) Adequacy of laboratory environment. 

(d) Man-pressure suit assembly adequacy. 

F. PRESSURE SUIT ASSEMBLY: 

1. Verify adequacy of the pressure suit (routine intravehicular 

operation) (pressurized and unpressurized). 

(a) Thermal, pressure, "paxtial gaseous flow, communications, telemetry data. 

(b) Don-doff and checkout for emergency operation. 

(c) Maintainability for 30 days operation. 

(d) Mobility for routine and emergency use. 

(e) 'Storage accessibility. 

(f) Suit/Laboratory Module interfaces. 

(g) Suit tethers and attachments interfaces. 

G. LAUNCH OPERATIONS: 

1. Verification of quantities and types of personnel to 

• support assembly, checkout, and launch. 

2. Verification of Laboratory Module and Mission Module AGE. 

3. Verification of assembly and modification facilities at the 

launch site to provide support of the Laboratory and Mission Modules for 

unscheduled mechanical and electrical modifications and the availability 

of appropriatd parts and technical data. 

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4. Validate that factory acceptance tests will provide the 

necessary confidence factor without considerable retest at the launch 

site. 

5. Demonstrate adequacy of training of the ground crews in 

:handling procedures and verify countdown procedures for the operation. 

6. Demonstrate the adequacy of the Launch Control Center to 

exercise control of launch countdown of an all-up manned MOL System. 

7. Demonstrate the adequacy of MCC to exercise overall control 

of countdown. 

H. FLIGHT SUPPORT: 

1. Demonstrate the adequacy of the TTC&V network to control, 

the flight for 30 days on orbit. 

2. Demonstrate the adequacy of the Mission Control Center equip, 

ment and personnel to support the MOL mission including: 

(a) Development of an optimum method of commanding, 

controlling, and monitoring the mission payload. 

(b) Change schedule and procedures to record/observe 

unforseen phenomena and targets. 

(c) , Inform crew on new and alternate procedures and 

targets to be used. 

(d) Ability to modify flight plan and schedules as needed. 

(e) Update documents containing plans and procedures of 

each orbit, schedules and flight plans and events related to mission plans. 
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3.ystain 

I. RECOVERY: 

1. Demonstrate the capability of the recovery forces to meet 

the specified times for access to and safe recovery of the crew, sensor 

recording media, and Gemini B. 

2. Verification of adequacy of medical facilities and procedures 

for end of mission assessment of flight crews. 

3. Validate procedures for handling DORIAN mission data 

recovered from Gemini B and RV and for debriefing flight crews in regards 

to intelligence information. 

J. MISCELLANEOUS: 

1. Measurement of contractors' achievements against established 

goals especially in fixed price/incentive contracts. 

III. CONFIGURATION: 

A. LAUNCH VEHICLE- MOL Operational Configuration 

1. Additions: R&D instrumentation package to obtain aeromechanical and thermal environment data. 

2. Exceptions: None 

B. GEMINI B- Operational Configuration 

1. Additions: None 

2. Exceptions: None 

C. LABORATORY AND MISSION MODULES- Manned Operation Configuration 

1. Additions: R&D instrumentation to obtain aeromechanical 

and thermal environment data. 

2. Exceptions: No experiments of scientific nature. 

D. MISSION PAYLOAD- Operational Configuration 

E. CREW- Two, fully trained 

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F. PRESSURE SUIT ASSEMBLY- MOL Operational Configuration 

1. Additions: None 

2. Exceptions: None 

0. LAUNCH SUPPORT- Operational Configuration. 

1. Additions: T2 (Apollo) instrumented ship vice "Range Tracker". 

2. Exceptions: None 

H. FLIGHT SUPPORT- Operational Configuration 

1. Additions: None 

2. Exceptions: None 

I. RECOVERY- Forces for Manned Mol Recovery 

1. Additions: None 

2. Exceptions: None 

IV. LAUNCH DATE - DECEMBER 1969 

V. FLIGHT PROFILE: 

Flight #3, the first manned mission, will be launched into a polar 

orbit from Space Launch Complex 6 at Vandenberg Air Force Base. The 

orbit will be elliptical with an apogee of 180 n.mi. and a perigee of 

80 n.mi. and an inclination of degrees. The perigee will occur in 

the northern latitudes and for initial planning shall be at approximately 

50°N latitude. The orbit will be a noon type orbit at midmission and 

the perigee shall occur on a south bound pass. The Gemini B will be 

separated at the end of mission for retro, reentry, and recovery in the 

primary recovery area in the Pacific Ocean. Providions will be made for 

Gemini B separation and emergency recovery of the flight crew in daylight 

in the event of an abort. Disposal of the LaboratOry/Mission Modules will 

be initiated by command from Mission Control at the Satellite Test Center, 

Sunnyva),F,, ,upon,comp;etion of the mission. 

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VI. FLIGHT DURATION: Thirty days 

Handle via BYEMAN 

Control System 

DORIAN 

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SAFSL Control is, 21,60-0 • 
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FLIGHT #4 

I. MISSION TYPE: 

Manned/automatic mission mode with emphasis on use of man to avoid 

early mission aborts by replacement, repair, or manwoly working around 

malfunctions or degraded subsystems.. This would include EVA. 

II. OBJECTIVES: 

A. GENERAL: 

All uncompleted objectives of Flight 3 will be completed, then 

proceed onto the specific new segment objectives below: 

B. LAUNCH VEHICLE: 

Demonstrations of capability of any hardware differences from 

the previous flight. 

C. GEMINI B: 

Demonstration of capability of any hardware differences from 

the previous flight. 

D. LABORATORY AND MISSION MODULES: 

1. Demonstration of capability of any hardware differences 

from the previous flight. 

2. Validate flight control software changes from previous flight.' 

3. Determine the ability to b& oriented for observation of 

other space vehicles and heavenly bodies. 

E. CREW: 

1. Determine the ability of man to avoid early mission aborts 

by replacement, repair or manually working around malfunctions or 

degraded subsystem performance. This will involve in-flight simulation 

Pagel of 4 pages 

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70,-0 SAFSL Control 4ei'lltc/3 • Cf7 

of a variety of subsystems malfunctions such as: 
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riiiiiJid via MOAN 

Caritrd System • • 

(a) V/H sensor, across format INC, star tracker. 

(b) DRV launches, wideband data readout. 

(c) 1 MIS command and track link, 2 fuel cells, 1 

cryogenic tank 25% of thrusters, automode V, 1 computer, 1 ATS, 

laboratory attitude reference. 

(d) All communications except single up/down voice 

link, auxiliary memory storage. 

(e) Loss of all propellant or loss of all power, or loss 

of all cryogenics, or loss of all stabilization and control, or loss of 

optics. 

2. Demonstrate the ability of the flight crew by EVA to correct 

such mission payload malfunctions as failure of the launch locks to 

release on orbit or failure of the tracking mirror door or shutters to 

operate. 

Determine the capability 

MISSION PAYLOAD: 

1. Demonstrate the adequacy of hardware and software changes 

from previous flight. 

2. _Determine the capability 

3ise :L 

F. PRESSURE SUIT ASSEMBLY: 

1. Verification of EVA adequacy: 

(a) Thermal, pressure 'partial gaseous flow, communications, 

(b) Don-doff and checkout for emergency operation. 

c) Maintainability'for 30 days operation. Mitt via BYDIAlii 

Can! System me 

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DORIAN • • FA, , 

SAFSL Control Lj_ 2.1643-4•7 

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NRO APPROVE6 'FOR 

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Contrel System • 

(d) Mobility for routine and emergency use. 

(e) Storage accessibility. 

(f) UMbilical storage and distribution system/pressure 

suit assembly. interface. 

(g) Suitability of tethers and attachments. 

G. LAUNCH OPERATIONS: 

Demonstrate adequacy in launch control center organization, 

facilities, and personnel changes since previous flight. 

H. FLIGHT SUPPORT: 

1. Validation of flight control software changes from previous 

flight. 

2. Confirm adequacy of network configuration and instrumentation 

changes found necessary, if any, from previous flight. 

I. RECOVERY: 

1. Determine effectiveness of any change in recovery forces 

and procedures made since list flight. 

III. CONFIGURATION: 

A. LAUNCH VEHICLE- Mol Operational Configuration 

1. Additions: 

2. Exceptions: 

B. GEMINI B- Operational Configuration 

1. Additions: 

2. Exceptions: 

C. LABORATORY AND MISSION MODULES- Manned Operational Configuration 

1. Additions: 

r 

2. Exceptions: 

!info via BYER! 

Cutrei System 

DORIAN 

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D. MISSION PAYLOAD- Operational Configuration 

E. CREW- Two, fully trained 

F. PRESSURE SUIT ASSEMBLY- Operational Configuration 

1. Additions: None 

2. Exceptions: None 

G. LAUNCH SUPPORT- Operational Configuration 

1. Additions: T2(Apollo) Insertion Ship vice "Range Tracker". 

2. Exceptions: 

H. FLIGHT SUPPORT- Operational Configuration 

1. Additions: 

2. Exceptions: 

I. RECOVERY- Forces for Manned MOL Recovery 

1. Additions: 

2. Exceptions: 

IV. LAUNCH DATE - APRIL 1970 

V. FLIGHT PROFILE - Same as Flight 

VI. FLIGHT DURATION Thirty days. 

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2.:11:;11Ah 

DORIAN 

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