The paper discusses a potential application of electric propulsion to perform orbit transfer of a large spacecraft structure to geosynchronous orbit (GEO) from LEO, utilizing a nuclear reactor space power source in the spacecraft on a shared basis. The discussions include spacecraft, thrust system, and nuclear reactor space power system concepts. Emphasis is placed on orbiter payload arrangements, spacecraft launch constraints, and spacecraft LEO assembly and deployment sequences.
Nuclear electric propulsion system utilization for earth orbit transfer of large spacecraft structures
Joint Propulsion Conference ; 1980 ; Hartford, CT
1980-06-01
Conference paper
No indication
English
Halo-orbit formation in the Earth-Moon system by the electric propulsion spacecraft
American Institute of Physics | 2018
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