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APPLICATION OF MOL HARDWARE FOR 

RENDEZVOUS/RESUPPLY OPERATING MODE 

CONTRACT 

DRAFT COPY 

MARCH 1967 

PREPARED FOR 

DEPUTY DIRECTOR 

MANNED ORBITING LABORATORY PROGRAM 

MOL SYSTEM PROGRAM OFFICE, USAF 

HEADQUARTERS SPACE SYSTEM DIVISION 

AIR FORCE UNIT POST OFFICE 

LOS ANGELES, CALIFORNIA 90045 
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INDEX 

PAGE NO. 

1.0 INTRODUCTION 1 

2. 0 OBJECTIVES AND APPROACH 3 

3.0 SCOPE 4 

,...... 

4. 0 TASKS 6 

5.0 GROUND RULES 10 

6. 0 SCHEDULES 12 

■ 

7. 0 CONCEPT DESCRIPTION 13 
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APPLICATION OF MOL HARDWARE FOR 

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1. 0 INTRODUCTION 

The Department of Defense Manned Orbiting Laboratory (MOL) 

Program interest in extended duration orbital manned systems is based 

upon numerous contracted and in-house studies performed over the 

past several years. Principal among the contracted efforts have been 

the SLOMAR, MODS, MTSS, OSS, and Phase Zero MOL studies. Inhouse studies have been continually pursued from the outset of the MOL 

conceptual design. The collective findings of these studies indicate that 

the basic MOL follow-on objectives of improvement in system economics, 

performance, and operating flexibility can be best achieved through 

utilization of a Rendezvous/Resupply mode. While the Baseline MOL 

program has as its objective 30 day mission duration, design provisions 

with the Baseline have been made to permit growth to 60 day mission 

duration. Thus, all practicable provisions have been made in the MOL 

Baseline hardware for effective application of the rendezvous mode in 

future growth versions of the program, and extensive systems planning 

has resulted in a specific preferred concept for possible implementation. 

With the initiation of the MOL Phase II, Engineering Development Program, 

it is now logical to conduct a preliminary design and engineering study 

of the MOL growth concept to provide sufficient planning information on 

which timely funding and schedule decisions can be made with high 

confidence. 

Apart from the fundamental basis for this effort, as outlined 

above, additional interest by the National Aeronautics and Space Agency 

and the President's Scientific Advisory Committee in the long-term 

Bioastronautics testing potential of the MOL hardware has led to considerable attention to this aspect. In view of the inherent capability 

of the projected MOL follow-on system to accomplish extended 

Bioastronautics testing, and of the economic advantage which might 
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accrue from such application, NASA requested the MOL SPO to furnish 

technical and economic information on second generation MOL systems 

concepts. Consequently, MOL planning information was submitted to 

NASA, and description of possible alternative system applications was 

briefed to NASA and PSAG personnel. Therefore, elements of the 

preferred Rendezvous/Resupply applications concept, and extensions 

of the concept for accomplishment of prolonged Bioastronautics testing, 

are included in this document for guidance. 

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2. 0 OBJECTIVES AND APPROACH 

The objective of this study is to obtain preliminary analytic and 

design substantiation of a specific concept for application of MOL 

Baseline end-items to a possible follow-on Rendezvous/Resupply system. 

The study shall be conducted in such depth and detail as to form 

an adequate basis for schedule and cost estimates, and shall be oriented 

toward definition of total system problems as well as particular hardware 

interfaces. The Contractor's study efforts shall primarily be confined 

to delineation of the system concept summarized in Section 7.0. 

Conduct of the study shall be over a period of five months. The 

study schedule and milestone dates are shown in Table I. Task numbers 

shown on the schedule relate to those tasks identified in Section 4.0. 

Overall management of the study is the responsibility of the 

Manned Orbiting Laboratory Systems Program Office (MOL/SPO). 

Technical Direction for this study will be the responsibility of 

Aerospace Corporation. Periodically, during conduct of the study, 

meetings between the Contrgctor and MOL/SPO/Aerospace will be held 

for this purpose. 

The Study Contractor shall conduct the study to the requirements 

as stated in this Work Specification. The Contractor also shall define 

the management structure for this procurement and appoint a study 

Project Manager for direct contact with the designated Air Force Project 

Officer. 
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The concept to be considered for this study involves a maximum 

application of hardware and software developed in the initial MOL 

Program. Major features of the concept include a relatively low-cost 

Rendezvous/Resupply Vehicle (RRV), derived from Baseline subsystems, 

which consists of: A Gemini B, propulsion, electrical power, life support; 

spares, and docking hardware. The function of the RRV is to furnish 

logistic support and crew rotation at approximately sixty day intervals 

to a Rendezvous Initial Vehicle (RIV) comprised of a modified Laboratory 

and Mission Module which are maintained on-orbit. 

3. 1 OPERATIONAL MODES 

Three modes of Rendezvous/Resupply system utilization shall 

be considered: 

(a) Continuous MOL Baseline mission operations. (2///hili 

(b) Continuous MOL Baseline mission operations, combin d 

with Bioastronautics Testing for up to one year orbital stays. .8) 

(c) Primary mission to be long duration Bioastronautics 

testing, with launches conducted from ETR. c) 

3.2 ORBITING VEHICLE CONFIGURATION 

The vehicle configurations studies shall include, but not 

necessarily be limited to, the following reference baselines: 

(a) In Mode A, the RIV will consist of a single compartment 

laboratory with provisions for RRV docking. The RIV will be launched 

unmanned. The RRV will provide logistic support to the baseline 

mission operations for approximately sixty day intervals. 

(b) In Mode B, the RIV will contain dual laboratory compartments with provisions for RRV docking. The RIV will be launched 

unmanned. The RRV will provide support of the baseline mission in 
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combination with prolonged Bioastronautics testing for approximately 

sixty day intervals. 

(c) In Mode C, the baseline military mission equipment and 

provisions are deleted, and the basic RRV and RIV vehicles are 

configured to most efficiently accommodate long duration Bioastronautics 

testing. 
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4.0 TASKS 

The following study tasks shall be performed for each of the 

• three modes of Rendezvous/Resupply utilization as defined in Section 3. 1. 

4. 1 

Define the operational requirements for each of the three defined 

modes of operation, including representative Bioastronautics test equipment. The scope of this definition effort will be restricted to a feview 

of the baseline mission operations and the long term Bioastronautics 

testing operations in order to identify those requirements whictisignifica.ntly impact the basic configuration of the Rendezvous Orbiting Vehicle. 

4.2 

Perform a survey of possible system configurations which 

utilize MOL hardware as a basis and which satisfy the operational 

requirements defined in Task 4.1. The system concept defined in Section 

7.0 shall be used as a base point. 

4.3 • 

Select the most promising configurations. Development risk 

and cost, compatibility with logical system evolution, flexibility, system 

performance, orbit duration/resupply variables, etc., will be defined 

for each configuration analyzed. The results of this task will be approved 

by the MOL System Program Office prior to further study. 

4.4 

Establish the operational requirements for the selected concept. 

This will include crew rotational requirements, launching requirements, 

and program support requirements. Analysis will be performed to 

establish the overall function distribution to segments of the total system. 

From this, major interfaces will be identified. 

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4. 5 

Perform a preliminary design analysis to establish basic design 

characteristics of the Rendezvous Initial Vehicle (RIV) and the Rendezvous 

Resupply Vehicle (RRV). The approach to be taken will be one of utilizing 

the MOL hardware to the greatest extent possible. The design analysis 

performed will be limited to those, areas where significant design modifications to the basic MOL hardware are required. Major modifications 

will be identified. Design analysis will be performed to determine the 

design/development feasibility and the most promising approach in the 

following specific areas: 

(a) Vehicle subsystem life extension limited to major critical 

subsystems. Analysis will include the aspects of maintenance/replacement/ 

repair, redundancy, design modification, and new design. 

(b) Evaluation of utilization of single and dual pressurized 

compartment for the RIV. 

(c) Docking structure design and compatibility with basic 

vehicle structure. Rendezvous and docking dynamics analysis will not 

be a part of this study effort. Necessary impact data will be assumed 

based upon published general studies. 

(d) Vehicle control system for Resupply Vehicle will be 

analyzed to define a basic design compatible with the operational requirements and the previously established rendezvous requirements (Item (c) 

above). 

4. 6 

Define a feasible preliminary plan for the design-development 

evolution of the RIV and RRV. This plan will include: 

(a) Definition of major development and system test requirements. 

(b) Major development facility requirements beyond those 

planned for the basic MOL program. 

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(c) Development and acquisition schedule. Information will 

be limited to major program milestones and long lead time or schedule 

risk items. 

(d) Program costs will be estimated and presented in terms. 

of Baseline MOL Program cost elements. 

4.7 

Define major program operational requirements to include 

facility requirements, gross simulation requirements, AGE requirements, 

and estimated program operations cost. 

4.8 

Provide a preliminary definition of equipment, test procedures, 

and timelines for Bioastronautic testing during prolonged orbital stay. 

(a) Physiological tests. 

(b) Psychological tests. 

(c)` Artificial gravity and/or exercise devices. 

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4. 9 

Provide results of the study in the following end items: 

(a) Mid-Study Briefing 

(b) Final Study Briefing 

(c) Final Summary Report 

4.10 

In the foregoing tasks, results of the study effort shall include 

at least the following information, as applicable to the task: 

(a) Description of vehicles, the vehicle subsystems and their 

operation. 

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(b) Preliminary design layouts of vehicle configurations 

identifying equipment locations and major mechanical/structural 

interfaces. 

(c) System level block diagrams and functional schematics. 

(d) Mass properties and c. g. location estimates. 

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5.0 GROUND RULES 

5. 1 

System to perform baseline MOL mission, with possible addition 

of complimentary payload elements. Possible use of system for long term 

Bioastronautic s testing. 

5.2 

WTR launch site; sunsynchronous orbit inclination; 80 N.M. 

perigee and optimized apogee altitude (except Mode C). 

5.3 

Five minute launch window (for purposes of sizing Resupply 

Vehicle). 

5.4 

Two man operating crew, with possible growth to four. 

5.5 

Sixty-day nominal minimum resupply cycle. 

5.6 

Hardware and software to be derived from Baseline MOL system. 

(Including T C (U)). 

5.7 

Initial (RIV) Vehicle launched unmanned for DOD or Combined 

Missions only; will not be required to perform mission operations in the 

unmanned mode. 

5. 8 

Gemini B capability to return data will be utilized. 

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5. 9 

Normal crew transfer to be Intra-Vehicular (I. V. ), except 

E. V. A. may be considered for crew-rotation on the combined basic 

and extended duration bioastronautics test mission. 

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5. 10 

EVA for maintenance/repair/replacement of components 

external to pressurized compartment. 

5. 11 

Minimum assistance by crew in post-docking connections of 

RRV to RIV. e.,, desire automatic sequences of high reliability for 

RRV/RIV interface connectors.) 

5. 12 

Maintain a high probability of mission success. The approaches 

for extending subsystem life on-orbit shall not appreciably reduce subsystem reliability from the 30'day baseline development levels. 

5.13 

Assume Rendezvous Resupply system to be ready for operational 

use in early 1973. 

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7. 0 CONCEPT DESCRIPTION 

7.1 Foreword 

Periodic resupply of and crew rotation to an Orbiting Vehicle, 

utilizing a low cost resupply vehicle, has been selected as the most 

promising approach to a cost effective MOL follow-on program. This 

section contains a summary of system concepts intended to furnish 

Contractor guidance. 

7.2 Rendezvous Initial Vehicle 

The Rendezvous Initial Vehicle (RIV) concept consist' of a 

modified Laboratory Module and a Mission Module as depicted in Figure 

1. The modifications to the Laboratory Module include adding a 

pressurized compartment, that has only selected subsystems remaining, 

to the forward end of the existing pressurized compartment; removing 

the DRV, its supports and launch tube from the pressure compartment 

and removing half the cryogenic tanks, and one fuel cell from the 

unpressurized compartment.' The required docking system hardware, 

interface connections for operation of the system, and ascent fairing 

accommodations are part ofthe docking plane modifications. The 

added pressure compartment is to be utilized primarily for storage and 

operation of items connected with crew activities such as vehicle 

maintenance, bio testing, physical conditioning and recreation. Other 

items such as sleep and food preparation and consumption stations may 

be included in this compartment. 

It is intended that the RIV vehicle be launched in the unmanned 

mode and be capable of orbit storage in a stabilized condition for periods 

of not less than 30 days. Following docking to a Resupply. Vehicle, the 

RIV is to be activated for operation in a manned mode. At the end of 

each resupply period, the RIV will be returned to the stored mode for 

replacement of the RRV and crew. 

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7.3 Rendezvous Resupply Vehicle . 

The Rendezvous Resupply Vehicle (RRV) concept consists of a 

Gemini B, a modified Laboratory Unpressurized Compartment, an 

Extended Duration Module, and subsystems developed for the Baseline 

Manned and Automatic vehicles. A pictorial representation of the RRV 

is shown on Figure 2. 

Modifications to the Unpressurized Compartment are those 

necessary to permit a structural and equipment interface with the 

Extended Duration Module. The Extended Duration Module consists of 

a structural shell, and the extended duration elements of the Power 

System, Propulsion System, Cryogenic Tank System, and Data Recovery 

System. Other components include the Crew Transfer Tunnel and 

Storage Compartment, Docking System, and their associated supporting 

structure and interconnections. All items of equipment are Baseline 

derived except the Docking System, and certain interface connections 

associated with the crew transfer tunnel, power, 02gas and fluid lines. 

It is intended that the Resupply Vehicle be capable of providing 

mission support for the crew and vehicle systems for at least sixty days 

of continuous operation in a nominal orbit of 96.4o, at an 80 N. M. perigee 

with an optimized apogee altitude. 

7.4 Rendezvous Orbiting Vehicle 

The Rendezvous Orbiting Vehicle (ROV) is the on-orbit 

assembled vehicle system consisting of a RIV and a RRV in the docked/ 

operating mode. The ROV configuration and the principle system 

element functions related to the RRV/RIV are illustrated in Figures 

3 and 4. 

Activities of the crew in the normal operating mode are to be 

"shirtsleeve. " This is accommodated by the pressurized interconnecting 

tunnel in the RRV for transfer of crew equipments, food, spare parts, 

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and film from the RRV and the dual pressurized compartment RIV. 

The dual compartment laboratory RIV permits crew activity to be 

isolated with reconnaissance mission operation conducted from the aft 

compartment and other activities, such as rest, recreation, repair, or 

bio-testing to be performed in the forward compartment. 

Following a nominal sixty day duty period, the crew is to be 

relieved and the system expendables replenished by anew RRV. 

7. 5 Mission Scenario 

A nominal Rendezvous Mission operations scenario is depicted 

in Figure 5. The initial launch timing is selected to permit optimum 

acquisition of the RIV by the RRV. Each resupply launch will be made 

such that the new RRV arrives at the ROV before exhaustion of prior 

RRV expendables. With the new RRV in a station keeping mode, the 

RIV is placed in a stored mode, after which the prior RRV disengages 

from the RIV, permitting the new RRV to dock. The RIV is then 

reactivated by the new RRV, and the prior RRV Gemini B is returned 

from orbit. 

7. 6 Potential Long Duration Bioastronautics Testing 

7. 6. 1 Combined Mission Approach 

The system configuration concept described in the foregoing 

appears to have a direct potential application to acquisition of long 

duration bioastronautics data. In this case, the forward pressurized 

compartment might be used as a substantially equipped bioastronautics 

test facility, and test data could be obtained in parallel with accomplishment of the basic MOL mission objectives. Figure 6 illustrates possible 

utilization of the basic RRV and RIV vehicles in a Combined Mission 

Mode. The operations procedures would entail unique crew exchange 

techniques, in order to build up individual crew member time on orbit. 

An approach which would permit the attainment of durations up to one. 

year on orbit, based upon progressive analysis of accumulated bio-test 

data, is summarized in Figure 7. 
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7. 6. 2 Primary Biomedical/Experiments Mission Approach 

Possible application of MOL-derived hardware to missions 

primarily oriented toward extended physiological and psychological 

testing is illustrated in Figure 8. In this concept, basic mission payload 

equipment is replaced by a modified mission module structure, and 

provisions for docking and crew transfer are made at both ends of the 

Orbiting Vehicle. The system is configured for four man crew operations. 

A nominal mission scenario for this concept is shown in Figure 9., and 

a possible crew rotation procedure is summarized in Figure 10. 
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