This paper proposes that the addition of ammonium perchlorate to solid fuel in a hybrid gas generator becomes an effective method in improving the controllability of effluent temperature and reducing oxidizer-to-fuel ratio variations. This study also examines the fuel-rich combustion behavior of ammonium-perchlorate-added fuels to different chamber pressures, radial temperature profiles, and overall system specific impulses. To maintain the hybrid rocket engine advantages, an upper limit of ammonium perchlorate is set to be 15 wt % in solid fuel. The results proved that an ammonium perchlorate addition to solid fuel provided better controllability of effluent temperature and 4% less oxidizer-to-fuel variation. The results also suggested that, when adding ammonium perchlorate, it offered 60% less chamber pressure, 120 K reduced radial temperature variation, and 3% improved overall specific impulse while generating the same effluent temperature.


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    Titel :

    Fuel-Rich Combustion with Ammonium Perchlorate Addition in a Staged Hybrid Rocket Engine


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2017




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Lokalklassifikation TIB:    770/7040