Abstract
The aim of the present paper is to describe and discuss on possible methods used in the divergence and flutter analysis of composite multilayered laminated structures. Dynamic instability is a very dangerous phenomenon and aeroelastic optimization has become an important element of the composite flight vehicle design process. A special attention is focused on the analysis of cylindrical panels and flat plates using numerical (finite element) methods. The structures with different flow angles, fibre orientations, stacking sequences and boundary condition are considered.
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