The invention provides a power supply control system for a Hall electric thruster of a spacecraft, and the power supply control system can be used for centralized power supply and centralized control and management. The power processing framework of the Hall electric thruster comprises an anode power module, a cathode power module and an ignition power module; each power module comprises an enable circuit; the working and turning-off of each power module are controlled through enable signals of a control unit which act on each power module in a centralized manner; the external enable signal acts on the enable control end of each power module, and the enable signal emitted under the centralized sequential control of the control unit controls each power module to work and be turned off sequentially; and therefore, the Hall electric thruster can ignite successfully, continuously and stably. Therefore, the operation control of the electric thrusting sub system can be finished under a preset timing sequence; redundancy switchover is performed by control commands, so that telemetry parameters are acquired, isolatedly-converted, and supplied to telemetering/telecontrol ports, and a telecontrol function is realized; and the power supply control and power supply efficiency of the system are effectively improved.


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    Titel :

    Power supply control system and method for Hall electric thruster of spacecraft


    Beteiligte:
    CHENG WEIMIN (Autor:in) / KANG XIAOLU (Autor:in) / ZHANG JIANYU (Autor:in) / QIAO CAIXIA (Autor:in) / WANG BO (Autor:in) / ZHANG PING (Autor:in) / ZHANG XINPING (Autor:in)

    Erscheinungsdatum :

    2016-02-03


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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