Abstract In this study, a stability analysis of the explicit guidance laws for space launch vehicles is performed with consideration of varying thrust integrals. Among various forms of explicit guidance, linear tangent guidance in its general form is selected and six different acceleration profiles are considered for this numerical experiment. A linear system modeling which includes all of the significant dynamic elements of a space launcher is performed to analyze the effect of the characteristics of thrust integrals on stability margins. Numerical results show that in an aspect of guidance stability, it is advantageous to have thrust integrals derived from increasing acceleration profiles, such as constant thrust case, which may be considered in the development of propulsion systems. Finally, time-domain simulation with the original nonlinear models is performed to verify the approach and the result shows that the nonlinear dynamics of the system is conserved well in the linear model.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Stability analysis of explicit guidance laws for space launch vehicles with varying thrust integrals


    Beteiligte:
    Song, Eun-Jung (Autor:in) / Cho, Sang-bum (Autor:in) / Park, Chang-Su (Autor:in) / Roh, Woong-Rae (Autor:in) / Joh, Miok (Autor:in)

    Erschienen in:

    Advances in Space Research ; 48 , 1 ; 133-145


    Erscheinungsdatum :

    2011-02-22


    Format / Umfang :

    13 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch