Dynamics design for complex mechanical systems has become an important research field and development direction at present, capturing attentions of an increasing number of engineers and scientists worldwide. Based on many advantages of the transfer matrix method for multibody system in studying multibody system dynamics, a design problem of a multiple launch rocket system is solved in this paper. Particular attention is addressed to model actions of the exhaust flow on the multiple rocket launcher, which are associated with firing order and firing intervals of rockets. Combined with a genetic algorithm, firing order and firing intervals are optimized to achieve optimum impact point dispersion reduction. The results of numerical simulation and verification tests show good agreement, while the dispersion characteristics of rockets have been improved in a low-cost way.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Dynamics design for multiple launch rocket system using transfer matrix method for multibody system




    Erscheinungsdatum :

    2016




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik
    Lokalklassifikation TIB:    275/7040



    Dynamics design for multiple launch rocket system using transfer matrix method for multibody system

    Tang, Wenbing / Rui, Xiaoting / Wang, Guoping et al. | SAGE Publications | 2016


    On modeling and dynamics of a multiple launch rocket system

    Li, Bo / Rui, Xiaoting / Wang, Guoping et al. | SAGE Publications | 2021




    Airborne rocket launch system

    LONDON ADAM P / HUNDLEY LUCAS A / DROPPERS LLOYD J | Europäisches Patentamt | 2017

    Freier Zugriff