Supersonic flutter characteristics of truncated sandwich conical shells with MR core

In this paper, the supersonic flutter characteristics of truncated sandwich conical shells with the magnetorheological (MR) core and isotropic homogeneous host and constraining layers are studied. The mathematical modeling of the shell and the aerodynamic pressure sequentially are performed utilizing the first-order shear deformation theory (FSDT) and the supersonic piston theory incorporating the effects of curvature and aerodynamic damping. The set of the governing equations and associated boundary conditions are derived using Hamilton’s principle. Through an analytical solution in the circumferential direction and a numerical solution in the meridional direction via the differential quadrature method (DQM), a semi-analytical solution is provided for various boundary conditions. After validation of the presented model, the effects of various parameters on the aeroelastic stability regions of the shell are examined such as magnetic field density, semi-vertex angle, length, total thickness, and thickness of the MR core.