Abstract
Electric Power Supply System (EPSS) optimal structure choice procedure is discussed for a spacecraft with an Electric Propulsion System (EPS). The spacecraft is considered as a multipurpose ship for a heavy payload (up to 20000 kg mass) transportation from a basic Low Earth Orbit to Geosynchronous Earth Orbit and back. Along with the task some scientific experiments and technological operations in space are to be performed by special equipment and hardware. Lifetime of all spacecraft systems is considered to be from 3… 5 years. For a spacecraft and a possible electric load pattern, two EPSS structural schemes are analyzed. The first scheme is based on a nuclear reactor power plant (NPP) allowing for a short time to force output power. The second scheme comprise a constant output NPP and a flywheel energy storage system (ESS). Optimal EPSS composition choice was made using system approach methodology based on a system multilevel presentation. EPSS mass and electric power calculation results for the two structural schemes are presented. The second scheme was found to be more advantageous to satisfy most of the requirements.
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