A readily combustible portion (110) includes a readily combustible exposed surface (111) that is exposed to a flow channel (CA). A combustion-resistant portion (140), which comprises a material that is more resistant to combustion than the readily combustible portion (110), covers an outer surface of the readily combustible portion (110) on the opposite side from the readily combustible exposed surface (111) in a direction orthogonal to a length direction parallel to a direction in which a hybrid rocket is propelled. The combustion-resistant portion (140) includes a thick portion (120) that serves as a stopper that prevents peeling of the readily combustible portion (110) from the combustion-resistant portion (140) in a direction from a starting end surface (100a) toward a terminating end surface (100b).


    Access

    Download


    Export, share and cite



    Title :

    Hybrid rocket


    Contributors:

    Publication date :

    2022-10-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



    HYBRID ROCKET AND INJECTOR FOR HYBRID ROCKET

    WADA YUTAKA / IKEGAMI TOMOTAKA / BABA KAIICHI et al. | European Patent Office | 2023

    Free access

    HYBRID ROCKET

    WADA YUTAKA / HASEGAWA HIROSHI / HORI KEIICHI | European Patent Office | 2020

    Free access



    Hybrid Rocket Engines

    Greatrix, David R. | Springer Verlag | 2012