Simulation and Nonlinear Analysis of Panel Flutter with Thermal Effects in Supersonic Flow
With the consideration of thermal effect, an improved panel flutter model equation is established to study the dynamic behaviors of panel structures on supersonic aircrafts. The governing equation is approached byGalerkinMethod, and then the resulting ordinary differential equations of the panel are obtained. By the numerical simulation, some essential nonlinear phenomena are discovered, and they play an important role in the stability of the panel in supersonic flow. Finally, Mach number and Steady temperature recovery factor are considered bifurcation parameters, Hopf bifurcation, and Pitchfork bifurcation, and other complex bifurcations at the equilibrium points are analyzed in detail, respectively, by seeking the eigenvalues of the Jacobian matrix of the dynamic system at bifurcation points. It can be concluded that there exist a rich variety of nonlinear dynamics, and they are essential for the stability of the panel in the supersonic flow.
KeywordsMach Number Hopf Bifurcation Bifurcation Diagram Supersonic Flow Bifurcation Parameter
This research is supported by Program for New Century Excellent Talents in University in China, No. NCET-07-0685.