非线性机翼极限环颤振的研究

The study of limit cycle flutter for airfoil with nonlinearity

在定常空气动力的作用下,对含立方非线性刚度的二元机翼颤振系统的极限环颤振进行了研究。应用中心流形理论将原四维系统降为二维,采用后继函数法对分岔点类别进行了定性的分析,从而确定平衡点的性质,并应用范式理论对分岔点处中心流形约化方程进行化简,进而研究了系统参数对极限环颤振的稳定性以及幅值的影响。

Limit cycle flutter of a two-dimensional airfoil in cubic nonlinear aeroelastic system in incompressible flow is investigated. The approach based upon the Center Manifold Theorem reduces a two degrees of freedom dynamical system into a two dimensional first order differential equations. By using the method of successor function to determine the behaviors of bifurcation points. The normal form method is applied to simplify the two-dimensional equations. Furthermore, the effects of the system parameters on the stability and amplitudes of limit cycle flutter are investigated.