Complicated Response Anlysis Of Panel In Subsonic Flow

The velocity of high-speed train approximately equals 0.3 Mach number. The outer skin and the window structure in high-speed train belong to the panel structure. Therefore, it is necessary to study the aeroelastic characteristics of the panel structure in subsonic flow. Based on the potential flow theory and the thin plate bending theory, the governing motion equations of the aeroelastic panel models were obtained. The differential quatrature method was used to discrete the governing motion equations, based on which the aeroelastic characteristics of two-dimensional and the three-dimensional thin panel were systematically investigated by numerical simulation method. The detailed contents are as follows:1. The vibration equation of the two-dimensional viscid-elastic thin panel was combined with the incompressible subsonic aerodynamic forces by means of potential flow theory. The cantilever panel supported at one end with a linear spring was considered. The differential quadrature method was used to discrete the equations of motion, and the eigenvalue method was applied to study the stability of the system. The influence of initial stress, viscid-elastic damping and mass ratio on the critical dynamic pressure of the panel was analyzed.2. The stability of three-dimensional orthotropic plate with simply supported boundary conditions subjected to initial stress and subsonic aerodynamic load was investigated by differential quadrature method. The eigenvalue method was applied to study the unstable way of the system. The effects of the length-width ratio, the mass ratio and the initial stress on the critical aerodynamic pressure of the panel bucking were discussed.3. The governing motion equation of viscid-elastic thin plate with the boundary conditions of nonlinear spring subjected to subsonic aerodynamic load was established. The differential quatrature method was used to discrete the coupled equations. The discrete equations were solved by numerical integration. Taking initial stress, critical aerodynamic pressure and viscid-elastic damping as bifurcation parameter, the bifurcation process of the aeroelastic system and the route to chaos were studied.