Abstract: Considering geometric nonlinear, Based on the VonKarman’s nonlinear panel theory and elastic relation of stress and strain, the aeroelastic equation of three thin panel is structed where the aerodynamic load is calculated applying piston theory. A new method called differential quadrature method (DQM) is applied to deal with the equation, and the DQM format of the aeroelastic differential equation is established. The systemic flutter boundary is determined using Lyapunov indirect method, and the influence of systemic parameters acted on flutter boundary is analysed. Last, the influence of systemic parameters acted on flutter amplitude of panel is studied, some significative results are abtained.