A generalized direct simulation method using a discrete time-domain state-space approach for transient response of both open- and closed-loop nonlinear aeroelastic systems is developed. Based on a nonlinear parameter scheme that divides the nonlinear system into sublinear systems, the method first assembles a set of discrete time-domain state-space equations and then computes the transient response by switching the time-integration procedure between this set of state-space equations. In so doing, various nonlinearities in structures, aerodynamics and/or control systems can be included. The method is validated by correlating the transient response of a three-degree-of-freedom airfoil section in freeplay with the experimental and numerical results obtained by Conner et al. The stability of a strut-braced wing with buckling effects at two trim conditions is also studied, which shows that the aeroelastic stability of the present strut-braced wing is trim-condition dependent. Such results clearly could not be obtained if using a linear aeroelastic analysis.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Nonlinear response of aeroservoelastic systems using discrete state-space approach


    Weitere Titelangaben:

    Simulation der nichtlinearen Übergangsantwort eines aeroelastischen Servosystems mit einem diskreten Zustandsraumansatz


    Beteiligte:
    Chen, P.C. (Autor:in) / Sulaeman, E. (Autor:in)

    Erschienen in:

    AIAA Journal ; 41 , 9 ; 1658-1666


    Erscheinungsdatum :

    2003


    Format / Umfang :

    9 Seiten, 14 Bilder, 1 Tabelle, 26 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch