This paper summarizes the most current configuration of the Solar Electric Propulsion Stage (SEPS) design resulting from the synthesis of key tradeoff analyses. The baseline SEPS is a 21-kW propulsion-power vehicle using the Shuttle/Interim Upper Stage (IUS) launch vehicle for planetary and geosynchronous missions. The trade analyses supporting the baseline configuration include ion thruster array pattern, solar array stowage concepts, and number of thrusters and power processors (PP). In addition, an integrated thermal control and structural system was optimized and designed to meet flight loads and dynamics requirements. Payload provisions, mercury propellant refueling, and design compatibility of the SEPS and Shuttle/IUS are presented.


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    Titel :

    Design synthesis of the SEPS


    Beteiligte:
    Horio, S. P. (Autor:in) / Watkins, C. L. (Autor:in) / Shollenberger, J. M. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics, Electric Propulsion Conference ; 1975 ; New Orleans, LA


    Erscheinungsdatum :

    1975-03-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Design synthesis of the SEPS

    HORIO, S. / WATKINS, C. / SHOLLENBERGER, J. | AIAA | 1975




    SEPS solar array design and technology evaluation

    ELMS, JR., R. / YOUNG, L. | AIAA | 1975


    SEPS solar array design and technology evaluation

    Elms, R.V. / Young, L.E. | Tema Archiv | 1975