A numerical technique is presented for optimizing a set of solid rocket motor (SRM) ignition control variables to achieve a specific requirement or set of requirements to be used in preliminary design of an SRM igniter. The mathematical model of the igniter transients uses a simplified ignition simulation routine to calculate igniter and SRM performance. The object function to be optimized (minimized) is typically the summation of the absolute values of the differences between the desired and computed thrust values of igniter characteristics, flame-spreading speeds and/or maxmum rate of pressure rise in the SRM. Optimization is obtained using a direct pattern search technique to determine the required values of the controlling variables. Examples are presented which illustrate the ability of the technique to meet practical design requirements. Computational results are show to be consistent with the static test performance of Space Shuttle SRMs. The method is capable of evaluating certain often unknown parameters, such as flame-spreading speed, from test data. (Kursetz)


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Organization of solid rocket motor igniter performance requirements


    Additional title:

    Gliededrung der Anforderungfen an die Leistungsfaehigkeit einer Zuendeinrichtung fuereinen Feststoff-Raketenmotor


    Contributors:

    Published in:

    Publication date :

    1978


    Size :

    6 Seiten, 6 Bilder, 1 Tabelle, 11 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English







    Rocket Motor Igniter, Arming Firing Device

    J. E. Hibbs / G. W. Chalmers / R. R. Durrell et al. | NTIS | 1979


    The Performance of Magnesium-PTFE-Viton Igniter in a Solid Rocket Motor

    Gocmez, A. / Ak, M. A. / Yilmaz, G. A. et al. | British Library Conference Proceedings | 2000