A spacecraft propulsion system comprises two thrusters, each operating in accordance to a corresponding propulsion technique. A controller is configured to direct collected solar energy to heat a propellant for consumption in one of the two thrusters, or to generate electric energy for the other one of the two thrusters.


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    Titel :

    Space mission energy management architecture


    Beteiligte:
    SERCEL JOEL (Autor:in) / MITCHELL AARON (Autor:in)

    Erscheinungsdatum :

    2022-08-16


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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