This study investigates the flame spreading and combustion modes of a novel axial-injection end-burning hybrid rocket motor. A motor structure is designed, and experiments are conducted with both polymethyl methacrylate and polyethylene fuels. Gaseous oxygen is used as the oxidizer in the tests. Different fuel duct diameters, fuel duct numbers, and nozzle throat diameters are combined to get different oxygen velocities. Three kinds of combustion modes are observed in the tests, end burning, opposed propagating, and side burning, which are divided by two transition oxygen velocities. The ranges of the transition velocities are obtained by experiments. According to the results, end burning occurs when the oxygen velocity is above the transition velocity B; side burning occurs when the oxygen velocity is below the transition velocity A; and opposed propagating takes place when the oxygen velocity is between the two transition velocities. In addition, the experiments reveal that the fuel regression rate of the end-burning hybrid rocket motor is much lower than that of the conventional side-burning hybrid rocket motor. The success of the firing tests verifies the probability of the motor scheme and provides foundations for the development of this novel hybrid rocket motor.


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    Titel :

    Experimental Investigation of Combustion in Axial-Injection End-Burning Hybrid Rocket Motor



    Erschienen in:

    Erscheinungsdatum :

    2015




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

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