Abstract
Abstract This paper investigates the supersonic aero-thermo post-buckling behaviors and limit-cycle oscillations of Functionally Graded Material (FGM) panels. In order to model the panel, the first-order shear deformation theory (FSDT) of plate is applied, and structural damping effect is considered in the supersonic airflow. Material properties are assumed to be temperature dependent, and to vary in the thickness direction of the panel according to a simple power law distribution. Also, the von-Karman strain–displacement relations are adopted to consider the geometric nonlinearity due to large deformation of the structure. Rayleigh damping coefficient is used to consider the structural damping, and the first-order piston theory is applied to model the supersonic aerodynamic loads. Newmark’s time integration method is adopted, and Guyan reduction technique is employed to get the computational efficiency. Numerical results are compared with the previous works, and the effects of structural damping on the limit-cycle oscillation of FGM panels under supersonic airflow are studied in detail.
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