This paper presents the preliminary functional description of a solar electric propulsion spacecraft power subsystem for an Encke comet rendezvous mission in the 1980s. This description has been derived from the study of the mission requirements and constraints and the study of integrating a solar electric propulsion module with an existing spacecraft. Tradeoff studies performed in the process of selecting power subsystem parameters and performance characteristics are described. The power subsystem designs draw heavily on the designs for existing spacecraft and technology being developed in the electric propulsion research and development program supported by NASA.
Solar electric propulsion spacecraft power subsystem for an Encke comet rendezvous mission
Intersociety Energy Conversion Engineering Conference ; 1974 ; San Francisco, CA
1974-01-01
Miscellaneous
No indication
English
Comet Encke Flyby Asteroid Rendezvous Mission
AIAA | 1974
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|ENGINEERING NOTES - Comet Rendezvous Mission Design Using Solar Electric Propulsion Spacecraft
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