Abstract
The flutter of a sandwich circular cylindrical shell, with the fractional order Zener constitutive relationship is studied. Based on the Donnell–Mushtari theory for facing layers and first order shear deformation theory for viscoelastic layer, the structural formulation of the sandwich cylinder is obtained and the aerodynamic pressure due to the fluid flow is evaluated by piston theory. The Lagrange method along with Rayleigh–Ritz method is implemented to derive and solve the governing equations. To determine the stability margin of three-layered cylinder the obtained set of ordinary differential equations are solved. In the following, the effects of variation of the geometric parameters such as length to radius ratio, radius to total thickness ratio and thickness of core layer, constraining layer and mechanical properties of viscoelastic material on flutter boundaries of sandwich cylindrical shell are investigated.
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