A field emission propulsion system for a spacecraft includes a control unit, a propulsion assembly, and a plurality of extractor electrode voltage sources. The propulsion assembly comprises a plurality of field emission propulsion units having an ion source with a plurality of ion emitters and extractor electrodes associated with the ion emitters and disposed in a field arrangement. The plurality of extractor electrode voltage sources, each associated with the extractor electrodes to control the same, are controlled by the control unit using an individual extractor electrode voltage.


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    Titel :

    Field emission propulsion system and method for calibrating and operating a field emission propulsion system


    Beteiligte:
    BOCK DANIEL (Autor:in) / TAJMAR MARTIN (Autor:in) / LAUFER PHILIPP (Autor:in)

    Erscheinungsdatum :

    2023-10-31


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS / F03H PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR , Erzeugung von Vortriebskraft [Schub] nach dem Prinzip des Rückstoßes, soweit nicht anderweitig vorgesehen / H01J Elektrische Entladungsröhren oder Entladungslampen , ELECTRIC DISCHARGE TUBES OR DISCHARGE LAMPS



    Field Emission Propulsion System and Method For Calibrating and Operating a Field Emission Propulsion System

    BOCK DANIEL / TAJMAR MARTIN / LAUFER PHILIPP | Europäisches Patentamt | 2020

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