Complicated Response Analysis Of Panel's Aeroelastic Systems

Panel flutter is a kind of self-oscillation subjected to the interaction of inertia force, aerodynamic force and elastic force. With the appearance of high-speed aerocraft and the requirement of the miniaturization, the panel-flutter analysis is become to be a hotspot of research. Of course, the panel flutter response is obtained an important attention in other engineering fields such as aviation, wind power generation, civil engineering with the development of science and engineering. Based on the Kirchhoff-love assumption and the Von-Karman's geometric large-deformation thin plate theory, the non-linear flutter of the two-dimensional and three-dimensional thin plate is systematically researched respectively with the Galerkin method and differential quadrature method. The detailed contents are as follows:1 The nonlinear dynamic equations of two-dimensional thin plate subjected to aerodynamic load are established applying the Hamilton's variational principle. A algebra criterion of Hopf bifurcation is brought forward to investigate the stability and bifurcation of the aero-elastic system. For multi-freedom system, the research of the cross section condition is one of the technical difficulties directly applying the classical Hopf theory to judge the critical point of the system. In this paper, the algebra criterion of Hopf bifurcation is applied to obtain the analytical expression of the critical velocity of the simply-supported thin plate, and the technical difficulty for direct estimation of the cross section condition is avoided. With the increase of the freedom of the system, the judgement of the solution stability of the equilibrium point becomes more difficult, so the central manifold is introduced to reduce the higy dimension system to lower dimension one, and the succeeding function method is applied to study the stability of the solution. Finally, the numerical solutions are applied to validate the correctness of the theory analysis.2 The aero-elastic dynamic behavior of the viscid-elastic panel subjected to aerodynamic heating is investigated supposing the uniformity temperature field. The temperature load is taken into account by the temperature stress. The influences the viscid damping coefficient on the flutter boundary and the amplitude of the limit-cycle are studied. Taking the aerodynamic pressure as the bifurcation parameter, the bifurcation behavior of the system is also studied.3 The aeroelastic flutter of the three-dimensional simply supported thin plate is investigated with Galerkin method, the results of which indicate that in the range of low dynamic pressure the system is steady; with the increase of the dynamic pressure, the system shows a series of period-doubling bifurcations until to chaotic motion; and in some special parameters, for a same dynamic pressure there exist two or more different limit cycles in the system depending on different initial condition respectively.4 The nonlinear dynamic behavior of the two-dimensional simply supported thin plate is investigated by differential quatrature method. As for the influence of system parameters on the critical dynamic pressures and the flutter frequencies, the results calculated with the differential quatrature method agree with those calculated with the Galerkin method. The bifurcation behaviors and the chaotic responses by means of the poincare map of the system are investigated.5 The nonlinear aerodynamic response of the three-dimensional simply supported thin plate and the composite material thin plate are studied with differential quatrature method. The period-doubling process of the system, the flutter boundary and the limit-cycle amplitude with the change of the system parameters is also studied. The changes of the flutter boundary and limit-cycle amplitude with the different laying mode of the composite material thin plate and different material are also studied.