Abstract
A conceptual design study was performed to define a SP‐100 Space Reactor Power System (SRPS) compatible with a set of proposed first demonstration flight objectives and constraints. The principal mission objective is the confirmation and demonstration of the SP‐100 technology and its design application maturity for space missions. The objective is to be achieved by SRPS assembly, ground acceptance test, launch vehicle integration, and on‐orbit demonstration of the full range of SRPS performance capabilities. A proposed second objective is to confirm the functional integration and active interfaces of a state‐of‐the‐art electric propulsion thruster subsystem with an SRPS power source, and to demonstrate its on‐orbit performance. Key mission requirements and constraints are the following: ‐ Economical Atlas AS launch into an 1100 km orbit; ‐ SRPS gross output of 30 kWe for 3 year mission lifetime; ‐ Spacecraft mass less than 7000 kg; SRPS less than 2500 kg; ‐ Accommodate users by order of magnitude reductio...
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