Aeroelastic Response Analysis Of Functionally Graded Material Panel

This thesis is devoted to the aeroelastic characteristics of a supersonic panel which is made of functionally graded material. Based on the Von-Karman’s geometric large-deformation thin plate theory, the aeroelastic problems of the two-dimensional panel and the three-dimensional panel are studied via differential quatrature method. The aerodynamic forces of supersonic flow are obtained by piston theory. The main works are as follows:1The changes of the components along thickness direction of functionally graded material are described by using the power law. Based on Hamilton principal, the vibration equation of the two-dimensional functionally graded material panel with both the aerodynamic force and the surface internal force, is established. Differential quatrature method is used to investigate the stability of the panel, the results of which show that the flutter phenomenon is observed in the panel system and the minimum value of flutter speed is obtained when the volume fraction of functionally graded material is linear. The influences of initial internal forces, aspect ratio and mass ratio on flutter boundary are also discussed.2Under the boundary condition of simply supported on four sides, the control equation of a three-dimensional functionally graded material panel with supersonic aerodynamic force and initial internal surface force is obtained. The dynamical stability of the system is studied by the Differential Quatrature method and the eigenvalue analysis, the results of which show that the flutter characteristics of the system are similar to those of the two-dimensional panel. The effects of initial internal forces, aspect ratio and mass ratio on the critical aerodynamic pressure are also discussed.3The flutter equation of the two-dimensional functionally graded material panel with geometric nonlinearity is obtained. The Differential Quatrature method is used to establish the correspond discrete equations of the flutter equation. Based on MATLAB. the numerical simulation method is used to solve the discrete equations of the panel system. The bifurcation behaviors of the panel system are studied taking the aerodynamic force, the initial internal force and the gradient index as the bifurcation parameter, separately.