A Hall thruster for use with a condensable propellant including a plasma accelerator including an anode for providing plasma discharge, a distributor for distributing the condensable propellant in a liquid or vaporized state, and an electric circuit including a cathode for emitting electrons attracted to the anode and for neutralizing ion flux emitted from the plasma accelerator. A condensable propellant feed system includes a storage vessel for storing the condensable propellant and providing liquid condensable propellant at a controlled pressure. A condensable propellant flow controller includes a pressure reducing device for controlling the flow rate of the liquid condensable propellant. A vaporizer at or above the vaporization temperature of the liquid condensable propellant vaporizes the liquid condensable propellant at a predetermined vaporization rate and flow rate. A magnetic circuit structure includes a magnetic field source for establishing a transverse magnetic field in the plasma accelerator that creates an impedance to the flow of the electrons toward the anode to create plasma in the plasma accelerator for accelerating ionized condensable propellant through the plasma accelerator to create a flux of ions.


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    Titel :

    Hall thruster for use with a condensable propellant


    Beteiligte:
    HRUBY VLAD (Autor:in) / SZABO JR JAMES J (Autor:in) / GASDASKA CHARLES (Autor:in) / ROBIN MIKE (Autor:in)

    Erscheinungsdatum :

    10.05.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F03H PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR , Erzeugung von Vortriebskraft [Schub] nach dem Prinzip des Rückstoßes, soweit nicht anderweitig vorgesehen / B64G Raumfahrt , COSMONAUTICS



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