悬停状态下旋翼桨叶气动弹性稳定性分析及试验

研究直升机旋翼桨叶在悬停状态下挥舞-摆振-扭转全耦合运动的气弹稳定性。应用哈密顿原理推导桨叶运动的非线性偏微分方程, 推导气动载荷时采用了准定常气动理论, 并应用Galerkin有限元素法离散空间变量, 利用特征值分析来研究系统的稳定性。以海豚直升机为工程实例, 分析计算了其桨叶的气弹稳定性, 还进行了旋翼模型气弹稳定性试验研究, 确定旋翼结构参数对气弹稳定性的影响, 并同计算结果进行了比较, 得到了一些有意义的结论。 

STUDY ON AEROELASTIC STABILITY OF ROTOR BLADE IN HOVER

he aeroelastic stability of coupled flap-lag-torsion dynamics of rotor blades in hover is studied in this paper.According to Hamilton principle,nonlinear partial differential equations of motion for elastic flap bending and torsion of the blade are derived.The spatial dependence of the partial differential equations is discretized by use of the Galerkin finite element method.The effects of some structural parameters are taken into account,such as the collective pitch,precone,sweep,and so on.Finally,the aeroelastic stability of Dolphin's Rotor blades is analysed.The experiment shows that the aeroelastics stablity of the rotor blade in hover is influenced small by the blade sweep,but strongly by the collective pitch and precone.The experimental results verify the feasibility of the analysis and applicability to rotor design.