To predict pressure-time and thrust-time behavior of solid rocket motors, a one-dimensional numerical model is developed. The ignition phase of solid rocket motors (time less than 0.4 sec) depends critically on complex interactions among many elements, such as rocket geometry, heat and mass transfer, flow development, and chemical reactions. The present model solves the mass, momentum, and energy equations governing the transfer processes in the rocket chamber as well as the attached converging-diverging nozzle. A qualitative agreement with the SRM test data in terms of head-end pressure gradient and the total thrust build-up is obtained. Numerical results show that the burning rate in the star-segmented head-end section and the erosive burning are two important parameters in the ignition transient of the solid rocket motor (SRM).


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Ignition Transient Analysis of Solid Rocket Motor


    Beteiligte:
    S. S. Han (Autor:in)

    Erscheinungsdatum :

    1990


    Format / Umfang :

    8 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch






    Modeling of Solid Rocket Motor Ignition Transient Revisited

    Favini, B. / DiGiacinto, M. / Serraglia, F. | British Library Conference Proceedings | 2002


    Solid Rocket Motor Ignition Transient Phenomenon and Pressure Buildup Simulation

    Wirzberger, H. / Yaniv, S. | British Library Conference Proceedings | 2007