Supply of a liquid component in a combustion chamber (2) of a rocket engine is controlled by a feed valve (14) provided with an obturator (22) mobile between a pen 5 position and a closed position of at least one supply pipe (18), which has an inlet (21) that communicates with a tank (13) for containing the liquid component and an outlet (17) that communicates with the combustion chamber (2); the displacement of the obturator (22) from its closed position to its open position being triggered by a pressurized fluid supplied to the outlet (17) of the supply pipe (18). 19F- FIG.3a


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    Titel :

    Rocket engine and method for controlling combustion in the rocket engine itself


    Beteiligte:
    PETRONIO DINO (Autor:in)

    Erscheinungsdatum :

    2015-08-06


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64G Raumfahrt , COSMONAUTICS



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