SUPERSONIC FLUTTER ANALYSIS OF THERMALLY STRESSED LAMINATED COMPOSITEFLAT PANELS

This paper deals with supersonic flutter analysis of laminated composi te panels exposed to a temperature field. The formulation includes tra nsverse shear deformation, and in-plane and rotary inertia effects. Th e aerodynamic force is evaluated by Considering the first-order high M ach number approximation to linear potential flow theory. The solution for the complex eigenvalue problem is obtained by the QR algorithm. B efore obtaining the critical aerodynamic pressure, thermal stress and buckling load are calculated. Numerical results are presented for both cross- and angle-ply laminates. A detailed parametric study is carrie d out to observe the effects of different temperature loadings, thickn ess, number of layers, lamination scheme and boundary conditions on th e flutter boundary.