A general numerical model based on the Zeldovich-Novozhilov solid-phase energy conservation result for unsteady solid-propellant burning is presented in this paper. Unlike past models, the integrated temperature distribution in the solid phase is utilized directly for estimating instantaneous burning rate (rather than the thermal gradient at the burning surface). The burning model is general in the sense that the model may be incorporated for various propellant burning-rate mechanisms. Given the availability of pressure-related experimental data in the open literature, varying static pressure is the principal mechanism of interest in this study. The example predicted results presented in this paper are to a substantial extent consistent with the corresponding experimental firing response data.


    Access

    Download


    Export, share and cite



    Title :

    Transient Burning Rate Model for Solid Rocket Motor Internal Ballistic Simulations


    Contributors:


    Publication date :

    2008




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown