This experimental and theoretical work examines the effects of gaseous oxidizer flow rates and pressure on the regression rates of porous fuels for hybrid rocket applications using polyethylene as the porous fuel and gaseous nitrous oxide as the oxidizer as a continuation of previous work performed at the University of Alabama in Huntsville. Nominal test articles were tested using 100  μm nominal fuel pore sizes. Pressures tested ranged from 207 to 1054 kPa, and oxidizer injection velocities ranged from 7.5 to 16.8  m/s. Regression rates were determined using pretest and posttest length measurements of the solid fuel. Experimental results supported previous work demonstrating that the regression rate of the porous axial-injection, end-burning hybrid was a function of the chamber pressure as opposed to the oxidizer mass flux typical in conventional hybrids. Regression rates ranged from approximately 0.21  mm/s at 207 kPa to 1.44  mm/s at 1054 kPa. The experimental results were compared to an analytical model developed in previous work for qualitative agreement. The model showed qualitative agreement with the experimental results, indicating that it has potential for giving insight into the flame structure in this propellant combination.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Experimental Evaluation of a Nitrous-Oxide Axial-Injection, End-Burning Hybrid Rocket



    Published in:

    Publication date :

    2017




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English



    Classification :

    BKL:    55.50 Luftfahrzeugtechnik / 55.50
    Local classification TIB:    770/7040






    FUEL REGRESSION CHARACTERISTICS OF AXIAL-INJECTION END-BURNING HYBRID ROCKET USING NITROUS OXIDE

    Okuda, Ryota / Komizu, Kodai / Tsuji, Ayumu et al. | TIBKAT | 2020