A system operating in a spacecraft includes a tank storing a propellant, a thermal receiver configured to change the propellant from a first phase to a second phase by providing heat to the propellant, and an energy conversion device fluidically coupled to the tank and configured to generate electric energy using the propellant in the second phase.


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    Title :

    Space Mission Energy Management Architecture


    Contributors:

    Publication date :

    2022-10-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



    Space mission energy management architecture

    SERCEL JOEL / MITCHELL AARON | European Patent Office | 2022

    Free access

    Space Mission Energy Management Architecture

    SERCEL JOEL / MITCHELL AARON | European Patent Office | 2021

    Free access



    A Multi-Mission Space Avionics Architecture

    Chau, S. N. / Reh, K. R. / Cox, B. et al. | British Library Conference Proceedings | 1996