Abstract
Supersonic flutter analysis of cylindrical composite panels with structural damping treatments has been performed using the finite element method based on the zig-zag layerwise shell theory. The natural frequencies and loss factors of cylindrical viscoelastic composites are computed considering the effects of transverse shear deformation. And Kumhaar's modified piston theory is applied for the calculation of aerodynamic forces. The flutter of cylindrical composite panels is analyzed considering structural damping effect. With respect to aeroelastic stabilities, various damping characteristics of unconstrained layer, constrained layer, and symmetrically co-cured sandwich laminates are compared with those of an original base panel.
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