A system for propelling a nanosatellite, including a pair of separated electrodes defining an ignition space therebetween a power source operationally connected to the pair of separated electrodes. Also included is a liquid propellant reservoir a pump reconnected in fluidic communication with reservoir and the ignition space and an electronic controller operationally corrected to the power source and to the pump.


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    Titel :

    Liquid-fed pulsed plasma thruster for propelling nanosatellites


    Beteiligte:
    SHASHURIN ALEXEY (Autor:in) / ZHANG YUNPING (Autor:in) / PATEL ADAM (Autor:in)

    Erscheinungsdatum :

    2023-01-17


    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



    LIQUID-FED PULSED PLASMA THRUSTER FOR PROPELLING NANOSATELLITES

    SHASHURIN ALEXEY / ZHANG YUNPING / PATEL ADAM | Europäisches Patentamt | 2020

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    SULFUR-FUELED SURFACE ARC THRUSTER FOR PROPELLING NANOSATELLITES

    Shimhanda, Senior / Hiraka, Kotaro / Inoue, Taro et al. | TIBKAT | 2021


    SULFUR-FUELED SURFACE ARC THRUSTER FOR PROPELLING NANOSATELLITES

    Shimhanda, Senior / Hiraka, Kotaro / Inoue, Taro et al. | TIBKAT | 2021


    Endurance testing of a pulsed plasma thruster for nanosatellites

    Krejci, David / Seifert, Bernhard / Scharlemann, Carsten | Elsevier | 2013