Abstract
Supersonic flutter analysis of laminated composite circular cylindrical shells is investigated by using an axisymmetric shell finite element based on the field-consistency approach. The formulation includes transverse shear deformation and in-plane and rotary inertia effects. The aerodynamic force is evaluated by considering the first order high Mach number approximation to linear potential flow theory. The solution for the complex eigenvalue problem is obtained by the QR algorithm. Numerical results are presented for isotropic, orthotropic and laminated anisotropic circular cylindrical shells. A detailed parametric study is carried out to observe the effects of aspect ratio, thickness, internal pressure, axial compression, number of layers and lamination scheme on the flutter boundary.
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