In this paper, we present a novel numerical approach for predicting the fluid flow in a solid rocket motor chamber with burning propellant grain. We use a high-order technique to track the regressing grain surface. Spectral convergence toward the exact burning surface is achieved thanks to Fourier differentiation. For the computation of the internal chamber fluid flow, we make use of a body-fitted volume mesh deforming with the grain surface. We describe several methods to deform the volume mesh and to keep good mesh element quality without global remeshing. We then couple the surface and volume approaches and integrate them into a complex code for compressible, multispecies, turbulent flow simulations. Thanks to these methods, we are able to exhibit one of the first three-dimensional simulations of the internal flow in a realistic solid rocket motor coupled to complex grain surface regression. In prior work, burning grain surface methods have only been coupled with one-dimensional internal ballistics solvers. Presented as Paper 2014-3612 at the 50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Cleveland, OH, 28-30 July 2014


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    Titel :

    Accurate Computation of Grain Burning Coupled with Flow Simulation in Rocket Chamber



    Erschienen in:

    Erscheinungsdatum :

    2015




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

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



    Accurate Computation of Grain Burning Coupled with Flow Simulation in Rocket Chamber

    Gueyffier, D. / Roux, F. X. / Fabignon, Y. et al. | AIAA | 2015



    A simulation of the flow near a burning solid rocket propellant

    MA, Y. / HEUSSER, E. / SHORTHILL, R. et al. | AIAA | 1989


    ALTITUDE SIMULATION CHAMBER FOR ROCKET ENGINE TESTING

    J. W. Davis / H. W. Belen | NTIS | 1971


    Rocket Thrust Chamber

    E. F. Baehr | NTIS | 1965