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The purpose of the present book is to study the theoretical investigation the nonlinear dynamic behaviour of a Glare 3 hybrid composite panel and elastic rectangular isotropic plates with fully clamped boundary conditions at large deflections. The part II of this book is the study the nonlinear free vibration of hybrid composite plates made of a new aircraft structural material called Glare 3 using a new improved approach.This approach is based on a model which has been applied to the nonlinear free vibrations of beams and to nonlinear free and forced vibrations of rectangular plates. The part III is to study the geometrically nonlinear dynamic behaviour of thin elastic rectangular isotropic plates with fully clamped boundary conditions at large deflections. The geometrical nonlinearity is expressed by the nonlinear straindisplacement relationships of Von Krmn. The model has been obtained using the multimode theory based on Hamiltons principle and spectral analysis. The model is used to determine the effect of the excitation frequency and the applied level of forces on the dynamic response at large vibration amplitudes.
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