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MANNED ORBITING 

LABORATORY PNICAEAM DIMCITM 

MOL PHASE I PROGRAM AUTHORIZATION 

NO. 65-2 

Z5 August 1965 

HEADQUARTERS UNITED STATES AIR FORCE 

WASHINGTON, D.C. 

MOL PROGRAM OFFICE 

HANDLE VIA BYEMAN 

CONTROL SYSTEM TOP SECRET 

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MOL PROGRAM OFFICE 

DIRECTIVE 65-2 

PROGRAM REQUIREMENT DOCUMENT 

THIS DOCUMENT IS AN OFFICIAL RELEASE OF THE 

MOL PROGRAM OFFICE AND ITS REQUIREMENTS ARE 

DIRECTIVE ON ALL COGNIZANT ELEMENTS OF THE MOL PROGRAM 

APPROVED 

B. A. SCHRIEVER 

General, USAF 

Director, MOL 

DORIAN SAF-SL BYE 37534-65 

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TABLE OF CONTENTS 

PURPOSE 1 

II. SCOPE 1 

III. PROGRAM OBJECTIVES 1 

IV. SYSTEM DESCRIPTION 

A. GENERAL REQUIREMENTS 2 

B. SYSTEM PERFORMANCE REQUIREMENTS 5 

V. SCHEDULES 12 

VI. FUNDING 13 

VII • PHASE I TASK SUMMARY 16 

TABLE 1 -- PLANNING SCHEDULE 16 

TABLE 2 -- PROGRAM COST ESTIMATES & 

FY FS&FP FUNDING SUMMARY 17 

ATCH #1 -- INFORMATION IN THE FINAL PHASE I REPORT 

ATCH #2 -- MEMORANDUM FOR DIRECTOR, MANNED 

ORBITING LABORATORY (MOL) PROGRAM 

DATED 25 AUGUST 1962 - AUTHORIZATION 

TO PROCEED WITH MOL PROGRAM 

DORIAN SAF-SL BYE 37534-65 

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I. PURPOSE 

This directive provides authority to initiate the Contract 

Definition Phase for the Manned Orbiting Laboratory System 

(Program 632A) and to continue with Pre-MOL activities. 

II . SCOPE 

This directive is applicable to all aspects of the MOL Program conducted by elements or agencies of the U. S. Air Force. 

In combination with approved budget authorizations, this directive 

constitutes authority for program implementation and planning. 

III. PROGRAM OBJECTIVES 

The principal and initial objective of the MOL Program is 

the development and early demonstration of an operationally useful 

high resolution optical reconnaissance system capable of achieving 

on the ground. In meeting this 

objective, provisions will be made for extending on-orbit lifetime, 

and for incorporating on a timely basis advanced optical sensors 

capable of affording resolutions on the ground 

The camera-optical system 

will be designed to be operated and serviced by man or be adapted 

to automatic unmanned operation so as to approach as closely as 

possible the performance capability of the manned system. 

DORIAN 

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• 

The development and demonstration of other military mission 

applications of MOL such as COMINT, ELINT, and Ocean Surveillance 

are secondary objectives. However, provisions for the introduction 

of these missions, both in the form of supporting experiments and 

full-scale demonstrations, will be considered in vehicle design, but 

insuring that the principal objective is not compromised. 

Accommodation of DOD and NASA scientific and technological 

experiments is a tertiary objective. Every effort will be made to 

develop and pursue an experiments program of significance and value 

to be conducted throughout the MOL Program, but without interference to principal military objectives. Although a broad spectrum of 

experimentation is encouraged, priority should be shown to those 

which support the investigation of the utility of military manned space 

flight. 

IV. SYSTEM DESCRIPTION 

A. General Requirements 

The MOL System will have.the capability to accomplish 

photographic reconnaissance missions in fulfilling the primary 

objective discussed in Section III. It will be designed to also 

accommodate, with minimum change, other mission objectives, 

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such as COMINT, ELINT, Ocean Surveillance or other general 

experimentation. Reconnaissance payloads will be launched from 

WTR on high inclination orbits to achieve the optimum reconnaissance information of the Sino-Soviet Bloc. For photographic 

missions, the perigee of these orbits may be as low as 70-80 

nautical miles and orbital plane inclinations allowing sun-synchronous 

precession in order to permit the highest possible ground resolution 

of the targets to be photographed. 

The MOL System will be capable of performing missions of at 

least 30 days duration with a 2-man flight crew. Consideration will 

be given to extending the system operating capability to durations of 

60 or 90 days using the same basic system elements. Although this 

latter requirement is not part of the basic MOL Development Program, this growth should be readily achievable in the future as the 

need arises. The initial MOL System capability will be based on 

integral launches of crew and laboratory. Rendezvous capability 

should not be precluded in growth considerations. System growth 

will also consider the possibility of accommodating larger optical 

systems which would be capable of producing a ground resolution 

presently desired. 

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Since the MOL System will be a first attempt to operate with 

crew stay times in space which are considerably longer than previously accomplished, a concentrated biomedical simulation, 

training, and monitoring program should be planned for and maintained during the early phases of the flight program to provide the 

maximum assurance of crew safety and an indication of crew 

capability limits for future missions which may be of even more 

extended duration. 

In the Contract Definition Phase and during subsequent design 

activities a detailed analysis shall be made of total system reliability, 

deliberately distinguishing between crew safety and mission success 

probability. As a design objective, the design philosophy in terms 

of redundant systems and back-up modes shall be such that no single 

failure shall cause an abort, and during an abort no single failure 

shall be fatal to either or both crew members. In addition, every 

effort will be made to maximize the probability of recovering the 

crew even if they are incapacitated. 

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Maximum use should be made of existing man-rated subsystems, 

components and facilities. Extended life capability should be achieved 

through minimum modification of existing systems by means of 

redundancy, spares, and maintainability or producfimprovement. 

Only after these avenues have been explored in this order, should new 

subsystems or components be proposed for development. Adequate 

mission program schedule assurance shall be provided by back-up 

systems which might be introduced as primary systems later in the 

program to aid in the projected second generation growth. 

B. System Performance Requirements 

The MOL System is defined as the totality of all hardware, 

software and personnel necessary to accomplish the MOL objectives, 

from launch through recovery. The major segments comprising the 

MOL System include the: 

Gemini B 

Laboratory Module 

Mission Module 

Payload 

Flight Crew and Crew Equipment 

Launch Vehicle 

Test Operations 

Facilities 

DORIAN 

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Each of these major segments consists of a number of subsystems, 

including the necessary AGE and support personnel. The Gemini B, 

Laboratory Module, Mission Module, and the Payload form the 

Orbiting Vehicle which is launched as an integral unit and is to 

function in orbit for at least 30 days. 

The Gemini B will be derived from the basic Gemini spacecraft through minimum modification and maximum utilization of 

man-rated Gemini subsystems. The Gemini B will provide crew 

support, protection and transportation during ascent and reentry. 

It will allow for safe and efficient crew passage to and from the 

laboratory module during orbital flight. In addition to the normal 

pre-launch, launch, initial laboratory manning, on-orbit checkout 

and pre-separation time periods, the Gemini B will be capable of 

supporting two crewmen, and being otherwise autonomous for a 

sufficient time in orbit after separation from the orbiting laboratory 

to achieve a controlled reentry and water landing at a pre-designated 

and prepared landing area. In addition to the crew, it will be capable 

of returning to earth substantial useful data as may be defined by 

mission requirements. 

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The Laboratory Module will provide crew and mission support 

during the entire orbital flight phase. In addition to providing adequate pressurized volume for a two-man crew and certain equipment 

accommodation, it will carry all the necessary subsystems for a 

safe and efficient autonomous operation of the Orbiting Vehicle, such 

as power, propulsion, life support, environmental control, communications, stabilization, navigation, and control fluids. It will be 

equipped with a wide bandwidth communications system capable of 

rapid relaying of selected payload output and telemetry data. It will 

provide support for the quiescent storage of the Gemini B and supply 

certain functions, such as power and environmental control, to the 

Mission Module. Every effort should be made to keep the Laboratory 

Module as standard as possible, regardless of varying mission or 

experimental demands being placed upon the Mission Module. 

The Mission Module will furnish the support of the mission payload. In the case of the optical reconnaissance sensor, it provides 

the structure, environmental control, and drive mechanisms. It 

houses the optical elements, cameras, film drives and other photographic support equipment. Astronaut access to the Mission Module 

for the purpose of optics alignment, film retrieval, maintenance and 

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possibly direct viewing will be provided. If a continuous capability 

for direct viewing cannot be easily provided, a high quality TV link 

between the primary optics image plane and the Laboratory Module 

may be utilized. Controls and displays relating to the operation of 

the primary optics, as well as the pointing and tracking scopes will 

be located in the Laboratory Module although they are to be considered part of the Mission Module System. The majority of the data 

output from the sensor system will be transported to earth by means 

of reentry capsules or the returning Gemini spacecraft. 

The primary mission payload for the initial MOL development 

program will be a camera-optical system with a telescope of at least 

60-inch aperture capable of providing a mission average ground 

resolution from an altitude of 70-80 nautical miles. 

During Contract Definition Phase two methods of providing pointing 

and tracking shall be considered: 

a. Using a suitably sized flat tracking mirror; 

b. Driving the entire telescope. 

Prior to the completion of CD? a pointing and tracking method shall be 

selected and the final recommended program plan based on this selection. 

The camera-optical system will have the capability of being 

operated by man. It will be designed in such a way as to also make 

it possible to operate unmanned by being supported by the best 

possible automatic systems for navigation, camera pointing, f.0,21:.: - 

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and image control. When in the unmanned mode, necessary optical 

alignment will be achieved by providing a capability for adjusting 

alignment remotely or automatically while in orbit rather than by 

strengthening the structure over that required for manned operation. 

Manual override and supervision capability will be incorporated in 

the automatic mode. 

In the area of growth systems studies a continuing effort shall 

be exerted to define sensor systems which use advanced techniques 

such as light weight mirror technology, new materials, Cassegrainian 

design, and figure control. These studies should be constrained to 

be primarily compatible with the basic integral launch MOL concept 

and secondarily with a rendezvous concept. Experimental programs 

will be initiated to provide early information on the precise alignment 

of the optical elements while on-orbit and on the figure control of very 

light weight mirrors. 

Component technology will be encouraged and sponsored in support 

of payloads which can accomplish the COMINT, ELINT, and Ocean 

Surveillance missions. Systems and subsystem designs studies will 

be sponsored to achieve some basis for early decisions on an optimized 

design for accomplishing these missions either in conjunction with the 

primary optical sensor system or in separate MOL flights. 

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The two astronauts comprising the Flight Crew must be highly 

proficient in all activities related to successful conduct of the entire 

30-day MOL flight profile. This means that during pre-flight training, in addition to developing spacecraft control skills, particular 

emphasis will be placed on achievement of a high state of crew proficiency in operating the primary MOL mission payload and analyzing 

results. 

The basic Launch Vehicle to be utilized for MOL will be a Titan 

IIIC uprated so that it is capable of inserting a total orbiting vehicle 

weight of at least 27,900 pounds into a 80 n. m. altitude, circular orbit, 

with an 80-degree inclination from WTR. Certain early pre-MOL test 

flights of MOL hardware may utilize the unmodified Titan IIIC with 

5-segment solid rocket motors from ETR. The Titan IIIC shall be 

suitably modified to provide the maximum of crew safety while also 

enhancing mission success. In the process of uprating the Titan III 

capability careful consideration shall be given to potential growth 

requirements of future advanced manned space flight systems. 

Mission Control will be achieved through the Satellite Test 

Center of the Satellite Control Facility. The STC can provide adequate 

and relatively inexpensive support to the. MOL Program by assignment 

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of programmed displays to a MOL Mission Control Center. Once 

the laboratory has been activated, the MOL on-orbit support shall 

be achieved with SCF tracking stations, augmented as required. 

Launch of the two Pre-MOL unmanned flights are planned 

from the Cape Kennedy AFS Integrate-Transfer-Launch (ITL) 

complex. The basic MOL development launches will be conducted 

from the ILC to be constructed at WTR. The ILC shall be designed: 

a. For subsequent expansion to ITL. 

b. For initial on-pad assembly and checkout of vehicle 

and payloads. 

c. Initial launch stand to be configured for uprated 

Titan IIIC with MOL Orbiting Vehicle. 

The recovery force will be comprised of sea, land, and air 

units and specialist teams in such quantities and at such locations 

in the recovery area or appropriate bases as is necessary to effect 

retrieval of the spacecraft and crew from a water landing. Such 

resources will be provided from existing Government sources, 

wherever possible and practicable. 

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The military program in MOL will require that data, command 

OkYll3r j. 

and voice services, and working area be secure to prevent comprising classified information. Channel capacity and reliability to support 

wide bandwidth data transmission to selected stations in CONUS, as 

well as flight crew-to-MCC voice, station control voice, telemetry 

data, command control, and tracking data transmission at all stations 

in the network will be provided. 

V. SCHEDULES 

A. MOL Contract Definition Phase will be initiated immediately 

upon receipt of budget authorization. For purpose of initial program 

scheduling, it is intended that Phase I will require approximately six 

months and will be followed shortly thereafter with Phase II development approval. 

B. Program schedules will be oriented towards achieving 

first manned flight no later than 33-36 months from Phase II Go-Ahead 

with subsequent manned flights scheduled on four-month centers through 

completion of the five manned flights presently planned for the basic 

development program. Launch of the first manned flight late in 

CY 1968 is desired. 

C. The first manned flight will be preceeded by an uprated Titan 

IIIC qualification flight from the MOL ILC at WTR. This booster development flight should preceed the first manned flight by 6 to 9 months. 

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D. The first MOL development flight which is to be unmanned 

but to include those subsystems necessary to qualify and demonstrate 

the integrity of the integrated basic vehicle will be scheduled approximately three to six months prior to the first manned flight. 

E. Follow-on flights to the basic development flights at a 

launch rate of six flights per year are to be scheduled for planning 

purposes. 

F. In addition to the above, Pre-MOL Program Planning will 

continue for an unmanned Heat Shield Qualification (HSQ) flight in 

late CY 1966 from ETR using a Titan MC R&D launch vehicle. 

A second flight with unmanned experimental payloads aimed primarily 

at military application will be tentatively planned for mid to late 1967. 

G. A Program Planning Schedule of the abOve events is shown 

in Table 1. 

VI. FUNDING 

A. Approved DOD FY FS&FP funding levels for the MOL Program Element, exclusive of payload costs , are shown in Table 2 

by FY and major appropriation. 

B. Program requirements for FY 66 and subsequent years 

will be scoped to the approved FY funding levels. More definitive 

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F. Initial funds in the amount of $4.2 million have been 

authorized by the Director, NRO for Definition Phase activities 

in support of primary and secondary MOL mission objectives as 

defined in Section III. Obligation authority to cover these activities 

will be issued by the NRO Comptroller directly to SAF-SP. 

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VII. PHASE I TASK SUMMARY 

In accordance with this directive, the MOL Systems Office will: 

A. Prepare and forward to SAF-SL for review and approval, 

prior to contract, the System Performance/Design Requirements 

General Specification for the MOL System. 

B. Prepare and forward to SAF-SL for review and approval, 

prior to contract, Phase I Work Statements for the Laboratory Module, 

Mission Module, and the Optical Sensor package. 

C. Provide SAF-SL with information copies of MOL Phase I 

Contract Work Statements and significant change notices for Titan IIIC, 

Gemini B, and Mission Control Equipment. 

D. Identify and provide SAF-SL no later than 15 September, 

1965, listing of major control milestone events to be accomplished 

during Phase I. 

E. Prepare and submit for approval no later than 1 October, 

1965 a plan for a second Pre-MOL flight with unmanned experimental 

payloads aimed primarily at supporting the primary and secondary 

MOL mission objectives as defined in Section III. 

F. Prepare and submit by 1 January 1966 recommendation 

on method for camera pointing and optical system design accompanied 

with proper trade-off analysis and study. 

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G. Prepare and submit no later than completion of Phase I, 

and sooner if possible, a comparative analysis of optical systems 

operated and serviced by man as distinguished from automatic operation with manual override capability and supervision. This comparative analysis will be measured against performance, program risk, 

costs and schedules. 

H. Prepare and submit for approval at the completion of 

Phase I a Proposed System Package Plan (PSPP) (or comparable 

final report) containing a complete technical, management, and cost 

proposal for Phase II development, and effort will be made to conform to the format and provisions detailed in AFSCM 375-4. In 

addition, the final report will include the information outlined in 

Attachment 1. 

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INFORMATION IN THE FINAL PHASE I REPORT 

The MOL Systems Office shall submit a final Phase I Report 

containing a complete technical, management and cost proposal 

for the Phase II development. The report shall contain, but shall 

not be limited to, the following items: 

1. A complete MOL System specification which technically 

defines the program requirement baseline and is organized in a 

form suitable for technical and contractual management of the 

acquisition program. 

2. Phase II Work Statements for the Laboratory Module, 

Mission Module, and the Optical Sensor Package. 

3. Summary of Associate Contractors' Operating Program 

Management Network for Phase II. 

4. Detailed cost estimates for Phase II, which include cost 

estimates for the items of the work breakdown structure, as derived 

from PERT/Cost; together with planning estimates for the period 

beyond Phase II (investment and operating cost for five years, 

including production, operation, maintenance, etc.). 

DORIAN 

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5. A milestone schedule for Phase II consistent with the 

PERT/Cost network and validated by recycling the PERT planning 

process, together with planning schedules for the period beyond 

Phase II (investment and operation for five years, including production, training, maintenance, etc.). 

6. Time-cost-performance trade-off decisions which have 

been made with respect to major alternatives, including subsystems 

and components, and back-up information showing the operational 

and cost effectiveness of these alternatives. 

7. Foreseeable technical problems and proposed solutions 

including back-up efforts, if necessary. 

8. Other problems that cannot be defined or resolved 

during CDP. 

9. A completely integrated astronaut training plan, including content and schedule. 

10. Requirements and delivery schedules for data and 

documentation. 

11. Associate contractors' commitments for managing the 

project including: 

a. Management-control and cost-control techniques, 

including reporting procedures. 

DORIAN 

STREI 

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b. Make-buy subcontracting procurement plan. 

c. Facility requirements. 

12. Contractors! proposals on the specific features on 

an incentive contract. 

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