A rocket engine is provided with a fuel flow path (31-39), a catalyst part (51), a turbine (12), a first pump (11), a combustion chamber (21), and a nozzle (22). Hydrocarbon-based fuel flows through the fuel flow path (31-39). The catalyst part (51) is provided in the middle of the fuel flow path (31-39), and gasifies the fuel. The turbine (12) is driven by the gasified fuel. The first pump (11) supplies the fuel to the fuel flow path (31-39) by the driving of the turbine (12). The combustion chamber (21) burns the gasified fuel supplied from the fuel flow path (31-39), and an oxidizing agent. The nozzle (22) delivers combustion gas in the combustion chamber (21) and is cooled by heat exchange with part of the fuel flow path (31-39).


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    Titel :

    ROCKET ENGINE, ROCKET, AND METHOD FOR STARTING ROCKET ENGINE


    Beteiligte:

    Erscheinungsdatum :

    16.09.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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