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This paper contains a discussion of the hardware development effort expended by the personnel of the NASA Manned Spacecraft Center in the field of environmental/thermal control and life support systems in support of the Apollo Applications Program. ...Although the Manned Spacecraft Center staff anticipated that the next space program would be an Apollo extension, it was also recognized that the detailed definition of the program would lag the requirement for basic subsystem development. ...Thus, to permit the vehicle prime contractor to proceed judiciously with the design of the spacecraft upon program definition, the MSG staff initiated an effort to provide the required subsystem advances.

Results of the Manned Spacecraft Center in-house oxygen/hydrogen reaction-control-system-engine technology program are examined, including performance evaluation (combustion efficiency, heating rates, etc.) of three basic injector concepts.

This paper is a brief review of the background of space station design effort from the time manned space flight was initiated to the present. The existing technology base for implementation of an ambitious earth-orbital operations program is briefly commented upon. Current space station designs are discussed in the light of present performance requirements. Also presented are some of the launch vehicles considered as candidates for the future. This paper reviews the design impact of accommodating many useful experiments and earth-related applications and of obtaining a space station lifetime of up to 10 years with onboard maintenance and repair activities. The necessity of management involvement on the part of many Government and private organizations is discussed, and some practical techniques which can be used to accommodate this involvement are presented.

Design requirements and operational constraints are reviewed for a small manually controlled flying vehicle which could provide astronauts with mobility for lunar exploration. Numerous flight trajectories and the vehicle performance have been analyzed and are presented. It is concluded that to attain the desired flight ranges, the flight velocities must be relatively high (200 fps or more). The range of thrust level required is determined. Flyer configuration is highly dependent on the method of control (either mechanical engine gimballing or kinesthetic control); the optimum method is still unresolved.

THE PAPER WILL present the background of Apollo Applications Program objectives, moving from 28 day missions to 56 days, to 120 days, etc., up to one year. It will discuss the concept of revisitation and reuse of hardware left in orbit and the recognition of the need for in-flight maintenance for enhancing probability of mission success. The design of the airlock module and multiple docking adapter which is aimed towards ease of module replacement, will be presented. The orbital workshop, planned for a late 1968/early 1969 launch, has a programmed set of experiments in the maintenance area, which will try to provide a baseline of astronaut capability in the maintenance area. These experiments will be discussed in detail.