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

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

Azzouz, M.Salim / Mei, Chuh

The purpose of this paper is to provide new insights in the subject of flutter of composite curved panels. A finite element time domain modal formulation is developed to predict the post flutter responses and the flutter onset of curved panels under yawed flow angles. The first-order shear deformation theory, the Marguerre plate theory, the von Karman large deflection theory, and the quasi-steady first-order piston theory appended with SAL (static aerodynamic load) are used lin the modal formulation. The principle of virtual work is applied to develop the equations of motion of the fluttering system in structural node degrees of freedom. The system equations of motion are transformed into modal coordinates, and solved by a fourth-order Runge-Kutta numerical scheme. Time history responses, phase plots, power spectrum density plots, and bifurcation diagrams uncovered the pre/post flutter responses of curved panels. The computed stability boundary margins and onset frequencies matched very well to the ones computed by a frequency domain method presented in an earlier article. Bifurcation diagrams revealed LCO (limit-cycles oscillations) and chaotic motion. It was found that two-dimensional cylindrical panels settle in a multiplicity of LCO as the height-rise of the panel increases, whereas LCO motion characterizes the dynamic behavior of three-dimensional cylindrical panels at low height-rises.