The invention relates to rocket engine cooling systems. A proposed electric rocket engine forced cooling system comprises a pump designed to be capable of providing a continuous flow of propellant in the cooling system; a cooling jacket on the engine parts that surrounds the electric rocket engine parts; a reservoir for storing propellant; a hydraulic accumulator; a small circle thermostatic valve; a radiator; and tubes connecting the abovementioned system elements and capable of providing propellant circulation through the cooling system circles; moreover the outlet of the pump is connected with the inlet of the cooling jacket, the outlet of which is connected with the inlet of the hydraulic accumulator, the outlet of which is connected with the inlet of the pump, and moreover the outlet of the cooling jacket is also connected with the inlet of the reservoir, the outlet of which is connected with the inlet of the hydraulic accumulator and with the inlet of small circle thermostatic valve, the outlet of which is connected with the inlet of the pump and with the inlet of the radiator, the outlet of which is connected with the inlet of the pump.


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    Titel :

    ELECTRIC ROCKET ENGINE COOLING SYSTEM


    Weitere Titelangaben:

    KÜHLSYSTEM FÜR EIN ELEKTRISCHES RAKETENTRIEBWERK
    SYSTÈME DE REFROIDISSEMENT DE MOTEUR DE FUSÉE ÉLECTRIQUE


    Beteiligte:

    Erscheinungsdatum :

    2022-04-27


    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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