Aeroelastic analysis of a thin composite plate, with the effect of general and local geometric defects

In this study, the effect of laminate type and number of layers, fiber angle and modulus of elasticity in combination with the effect of global and local geometric defects has been investigated as a new combination in the field of aeroelasticity. Using the principle of virtual work, by directly integrating the problem-solving boundary, the governing equations are determined based on Kirchhoff thin-plate theory. Then, using the assumption mode method in Galerkin's theory, the partial differential equations are converted to ordinary nonlinear differential equations. The final nonlinear equations are solved using the Runge–Kutta numerical method and the time domain results are extracted to determine the flutter and post-flutter behavior of the plate. The results of the analysis showed that the geometric defect with non-uniform and asymmetric load production, the type of layering, the number of layers and mechanical loads are effective on the plane flutter boundary. The effect of local geometric defects in determining the flutter border is not necessarily destabilizing, but in some cases, depending on the size and location of the defect, it is also possible to increase the stability of the plane flutter boundary. In addition, the dynamic behavior of the plate under the effect of local geometric defects with different shapes and dimensions is very diverse and different from the of general defect (first mode shape) or shell with small curvature.