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.
Finite element time domain - Modal formulation for nonlinear flutter of composite panels
Finite Elemente Definition - Schwingungsanalyse des nichtlinearen Flatterns zusammengesetzter Platten
AIAA Journal ; 32 , 10 ; 2044-2052
1994
9 Seiten, 12 Bilder, 15 Quellen
Article (Journal)
English
Finite Element Time Domain--Modal Formulation for Nonlinear Flutter of Composite Panels
Online Contents | 1994
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