A finite element time domain model approach is presented for determining the nonlinear flutter characteristics of composite panels at elevated temperatures. The von Karman large-deflection strain-displacement relations, quasisteady first-order piston theory aerodynamics, and quasisteady thermal stress theory are used to formulate the nonlinear panel flutter infinite element equations of motion in nodal displacements. A set of nonlinear modal equations of motion of much smaller degrees of freedom for the facilitation in time numerical integration is then obtained through a nodal transformation and reduction. All five types of panel behavior - flat, buckled, limit-cycle, periodic, and chaotic motions - can be determined. Examples show the accuracy, convergence, and versatility of the present approach.


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    Title :

    Finite element time domain - Modal formulation for nonlinear flutter of composite panels


    Additional title:

    Finite Elemente Definition - Schwingungsanalyse des nichtlinearen Flatterns zusammengesetzter Platten


    Contributors:
    Zhou, R.C. (author) / Xue, D.Y. (author) / Mei, C. (author)

    Published in:

    AIAA Journal ; 32 , 10 ; 2044-2052


    Publication date :

    1994


    Size :

    9 Seiten, 12 Bilder, 15 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English