A rocket engine with an improved solid fuel segment mainly comprises a combustion chamber, a solid fuel segment installed in the combustion chamber, and an oxidizer injector installed at one end of the combustion chamber. The solid fuel segment surrounds and forms a trajectory to allow the oxidizer injector to inject oxidizer into the trajectory, in particular, on the solid fuel segment is formed with a plurality of protrusions, between the each two protrusions are defined a recess, a flame holding hot-gas region is formed between the protrusion and the recess, so as to produce eddy current in the flame holding hot-gas region when the propellant mixture is burned inside the trajectory, such that the whole solid fuel segment can produce even regression rate and high combustion efficiency.


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    Titel :

    Hybrid rocket engine with improved solid fuel segment


    Beteiligte:
    CHEN YEN-SEN (Autor:in)

    Erscheinungsdatum :

    13.07.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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    Tsujikado, Nobuo / Koshimae, Masatoshi / Ishikawa, Rikiya et al. | AIAA | 2005


    SOLID FUEL AND HYBRID ROCKET

    KATANODA HIROSHI | Europäisches Patentamt | 2020

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