Abstract
Supersonic flutter analysis of truncated conical shells with arbitrary classical boundary conditions is investigated in the present study. Structural equations of motion are obtained in their integral representation using the Flügge's first-order shear deformable assumptions along with the first-order piston theory for the aerodynamic model. Effects of curvature correction and airflow's yaw angle are also included in the aerodynamic model. Using a Rayleigh-Ritz based solution algorithm, the aeroelastic system of equations is solved by a standard eigenvalue solver with quadruple precision. After verification of the presented algorithm and solution procedure, a comprehensive parametric study is performed and effects of various parameters, namely the boundary conditions, semi-vertex angle, length and thickness ratios and yaw angle of the airflow on flutter boundaries of truncated conical shells are examined.
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