Dual propellant electrothermal propulsion systems with a polar propellant and a non-polar propellant are disclosed. Such a system may be used for imparting high specific impulse momentum on a spacecraft. A thruster includes a microwave source operably coupled to a heating chamber. An injector mixes polar and non-polar propellants and a nozzle at one end of the heating chamber. The thruster raises the temperature of the mixed propellants that exit the heating chamber to expand in the nozzle to generate thrust.


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    Titel :

    Dual propellant microwave electrothermal propulsion systems


    Beteiligte:

    Erscheinungsdatum :

    23.07.2024


    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



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