Abstract
Future microspacecraft will require significant propulsive capability in order to accomplish the wide array of missions currently envisioned. The development of candidate propulsion systems including cold gas, chemical and ion thrusters will be necessary to fulfill maneuvering requirements. This study focuses on the design considerations associated with scaling propulsion systems for use on microspacecraft. Scaling issues that affect device performance as well as systems limitations of microspacecraft are presented. General considerations are presented for nozzle flows, ion formation, combustion and heat transfer at micro-scales.
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