Consideration is given to a finite-element approach for determining the nonlinear flutter characteristics of 3D thin laminated composite panels using the full third-order-piston transverse-loading aerodynamic theory. The unsteady hypersonic aerodynamic theory and the von Karman large-deflection-plate theory are used to formulate the aeroelasticity problem. Nonlinear flutter analyses are performed to assess the influence of the higher-order aerodynamic theory on the structure's limit-cycle amplitude and the dynamic pressure of the flow velocity. A solution procedure is presented to solve the nonlinear panel flutter and large-amplitude free-vibration finite-element equations. Nonlinear flutter analyses are performed for different boundary support-conditions and for various system parameters. Linear finite-element flutter for isotropic and composite panels and large-amplitude isotropic panel flutter results are compared with existing classical solutions. The large-amplitude panel flutter results using the full third-order piston aerodynamic theory are presented to assess the influence of the nonlinear aerodynamic theory.
Large-amplitude finite element flutter analysis of composite panels in hypersonic flow
AIAA Dynamics Specialists Conference ; 1992 ; Dallas, TX, United States
1992-01-01
Conference paper
No indication
English
Large-Amplitude Finite Element Flutter Analysis of Composite Panels in Hypersonic Flow
Online Contents | 1993
|Large-Amplitude Finite Element Flutter Analysis of Composite Panels in Hypersonic Flow
British Library Online Contents | 1992
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