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Restraint and mobility of personnel and equipment in the unique interior of Space Station Freedom will require the aid of a set of architecturally compatible yet operationally versatile and durable equipment This paper describes the development to-date of this equipment. An overview of the history of intravehicular (IVA) Restraints and Mobility Aids (R&MA) on the Skylab and the Space Shuttle provides the basis for system requirements. These system constraints and the process used to select hardware concepts are presented. Flight testing of R&MA foot restraints is shown to have provided concept verification and iteration. System considerations which provide the basis for on-orbit hardware allocations is then presented.

Fixed displacement pumps will continue to be a popular choice for hydraulic system designers for decades to come. These pumps are used in almost every industrial and mobile market segment and are generally less expensive than comparable variable displacement type pumps. Fixed displacement “Vane Type” pumps are especially popular because of their low noise characteristics as well as their inherent repair features. The demand for “Vane Type” fixed displacement pumps continues to grow in all market segments. Because of this continued demand, a new design of “fixed displacement vane pumps” is being developed. These pumps, designated the VPF Series, are targeted to offer continuous operating pressures up to 280 BAR with displacements from 40 to 215 cc/rev.

This paper discusses the process by which the initial system concept design for a remotely operated Tumbling Satellite Retrieval System (TSRS) was developed. This kit, when attached to the Orbital Maneuvering Vehicle (OMV), will retrieve spacecraft whose motion or interfaces prevent direct capture by standard OMV attachment hardware. The system concept design, which was defined by mission, system, and functional requirements, was developed under a NASA/MSFC contract, the objective of which is the development of an evaluation test article. (Detailed design and validation tests will follow.) The process started with the development of twelve “design reference mission” (DRM) retrievals. The twelve DRMs were developed from analysis of the physical and dynamic characteristics of existing and planned spacecraft. Potential TSRS configurations were then developed for accomplishing each DRM.