Aerodynamic Analysis of a Double Elastic Panel-Cavity with One Side Exposed to Supersonic Flow

In this paper, the aeroelastic stability and nonlinear response of a structural-acoustic system that consists of two panels with an acoustic cavity between them is investigated. A non-linear higher-order shear deformation zig-zag theory is adopted to model the composite laminated panel, and the linear wave equation is employed for modeling the compressible fluid in the cavity. Based on the Piston aerodynamic theory, a theoretical approach with the finite element method for solving instability modes and the transient response of the panel-cavity aerodynamic system is suggested. The aeroelastic instability boundary under different dynamic pressures is calculated, and the influence of the stiffness ratio between the top and bottom elastic panels is analyzed.