Electric propulsion using argon ion bombardment thrusters is described as a means of transferring solar power satellites from low earth orbit (LEO) to geosynchronous equatorial orbit (GEO). A portion of the satellite GaAs solar array is constructed in LEO and provides power for ascent propulsion; the remainder of the array is constructed in GEO. The electric propulsion system is returned to LEO by detaching a section of the solar array. Alternatively, an autonomous electric propulsion vehicle is assembled in LEO and transports power satellite materials to a GEO construction site. Maximum thrust per thruster and minimum argon consumption are achieved at specific impulse (Isp) 13,000 s. The thrust/power relationship leads to minimum transportation vehicle mass, including the solar array, at Isp 9,000 s. Thruster screen, accel, and discharge supplies are obtained directly from the solar array.


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    Title :

    Self-powered electric propulsion of satellite power systems


    Contributors:

    Conference:

    International Electric Propulsion Conference ; 1978 ; San Diego, CA, US


    Publication date :

    1978-04-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




    Self-powered electric propulsion of satellite power systems

    WEDDELL, J. / MCRAE, W. / CERRI, S. | AIAA | 1978


    Self-powered electric propulsion of satellite power systems

    Weddell, J.B. / McRae, W.V. / Cerri, S.T. | Tema Archive | 1978



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    ALAIN GRUWE / PHILIPPE LEDENT | European Patent Office | 2016

    Free access