Patent ID: 6206327
Filing Date: 2001-03-27
Classification: B64G

Abstract:
A space module for a mission configurable and scalable spacecraft bus said space module having a stackable configuration which adapts both to a payload at one end of the space module and to a mounting ring of a propulsion module at the other end of the space module, said space module comprising:a) a central hub portion of generally cylindrical shape having an outer periphery and having a hollow interior portion sized to receive a propulsion tank of a propulsion module centrally and longitudinally within the hollow interior portion;b) a plurality of spaced apart radial rib panels extending from said outer periphery of said central hub portion and defining a plurality of bays between the rib panels and the central hub portion and sized for containing subsystem components, said radial ribs panels being constructed to provide a primary structural load pathway through the space module from the mounting ring of a propulsion module to a payload;c) a base panel enclosing a lower portion of each of said bays and constructed to provide a bulkhead for connection to the mounting ring of a propulsion module,d) a top panel enclosing an upper portion of each of said bays and constructed to provide an interface with a payload; ande) a plurality of removable exposed side panels for enclosing said bays, and wherein each side panel includes an interior wall portion adapted to mount subsystem components thereon and an exposed exterior wall portion defining a radiator to remote heat generated by said subsystem components.