将铰接式直升机桨叶挥舞、摆振及变矩铰的刚性转角作为广义坐标,采用中等变形梁理论,结合有限元法,在旋转坐标系下,根据Ham ilton 原理推导出桨叶前飞状态下的非线性周期时变动力学方程。使用拟线性化方法及New m ark 数值积分技术求解桨叶的气弹响应。对稳态解进行摄动,应用Floquet理论分析桨叶的气弹稳定性。 Using the rigid corner of articulated helicopter blade swing, shimmy and torque hinge as the generalized coordinates, the medium deformation beam theory and the finite element method are used to derive the blade forward flight state under the rotating coordinate system according to the Ham ilton principle The nonlinear periodic dynamics equations. Soliton aeroelastic response of blade using quasi - linearization method and New m ark numerical integration technique. Perturbed the steady state solution, and applied Floquet theory to analyze the aeroelastic stability of blades.