An arcjet propulsion system, delivering 7.5 N thrust, was defined for the SP-100 Space Reactor Power System Interim Reference Mission. Conceptual design trades and configuration studies of a spacecraft suitable for the mission were performed to the extent necessary to define propulsion system requirements and interfaces. The propulsion system design is based on the use of 30-kW, constricted arc, ammonia arcjet engines operating in parallel during orbit boost from low earth to geosynchronous orbit.


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    Title :

    Conceptual spacecraft and arcjet propulsion system design for the SP-100 interim reference mission


    Contributors:
    Zafran, S. (author) / Bell, M. W. J. (author)

    Publication date :

    1990-07-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





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