Abstract
The differential quadrature method is extended to deal with an aeroelastic problem. A structural model is presented based on Hamilton’s principle, and the piston theory is used for modeling supersonic aerodynamic loads. A solution for the flutter of a composite wing skin is obtained by using the differential quadrature method. The validity of this method is confirmed by comparing its results with FEM solutions for the natural frequencies and flutter speed. Then, a detailed parametric study is carried out to examine the influence of the thickness, area, ply-angle, and aspect ratio of composite wings skins on their supersonic flutter behavior. It is shown that the flutter speed of a composite wing skin strongly depends on the area, thickness, ply angle, and aspect ratio of the structure.
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