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The Space Station program was faced with a unique design environment-to design a common systems and payload support structure that could accommodate changeout for repair or technology growth over a 30-year lifetime. The vibration environment and weight allocation for rack structure necessitated a lightweight, yet stiff structure. The design answer was a modular rack structure using graphite/epoxy composites and selected aluminum components that could support a wide variety of systems, payload and stowage functions. A modular set of mounting locations allow the installation of a wide variety of secondary structures without permanent modifications to the rack. Aircraft-style seat track rails on the front edges of the rack permit attachment of handrails, foot restraints and accessories such as lights, fans, clipboards or computers to the rack face.

Available stowage volume on Space Station Freedom (SSF) has changed substantially since the Phase B contract was awarded in 1987. Influencing factors include rack design, element module size and layout, packaging efficiency of various stowed items and stowage tray design requirements. This paper describes the stowage volume evolutionary process from SSF program Phase B to present. Stowage design and volume allocation lessons learned that should be addressed in any new manned spacecraft design are identified and discussed.

The Space Station Freedom (SSF) configuration evolved during the past decade in response to changing requirements and resources. Early space station studies determined that an on-orbit U.S. Laboratory (Lab) module was required to accomplish mission goals. A Habitation (Hab) module was needed to support the objective of a permanently manned presence on the station. Operational requirements were met by providing resource nodes, pressurized logistics (Log) elements, and airlocks. These five elements are the basic pressurized building blocks used to construct SSF. As the SSF design matured, requirement changes were made to accommodate such considerations as launch capability, extravehicular activity (EVA) assembly time, intravehicular activity (IVA) outfitting and checkout, and other program resource constraints. These considerations resulted in design changes that were incorporated into a restructured design that will be finalized and become the SSF baseline by mid-1991.