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研究以降低直升机旋翼激振力为目标的复合材料桨叶结构动力学减振优化设计 ,分析了桨叶结构特性及桨尖后掠角等参数对N次 /转旋翼桨毂振动载荷的影响。在建立的桨叶二维结构特性有限元分析方程中 ,计入了桨叶剖面翘曲变形的影响 ,并利用哈密尔顿原理推导了旋翼桨叶的一维非线性运动微分方程。以桨毂交变载荷为目标函数 ,直接以复合材料桨叶典型剖面构造节点数据、铺层设计参数和桨尖后掠角等为设计变量 ,引入桨叶挥舞惯量、固有频率和气弹稳定性约束 ,进行旋翼的动力学优化设计 ,并结合 3片桨叶旋翼的设计进行了算例分析 ,优化结果使 3次/转的桨毂载荷降低了 2 4 .9%～ 33%。
The dynamic design optimization of composite blade with aiming to reduce the excitation force of helicopter rotors is studied. The influence of blade structure and tip swept angle on the vibration load of N / rev rotor hub is analyzed. In the finite element analysis equation of two-dimensional structural characteristics of blade, the influence of warpage on blade profile is taken into account, and the one-dimensional nonlinear differential equation of motion of rotor blade is deduced by the Hamilton principle. Taking the alternating load of the hub as the objective function, the node data, the design parameters of the ply and the sweep angle of the tip of the composite blade are directly used as the design variables, and the waving inertia, natural frequency and the stability of the aeroelastic breeze are directly introduced , The dynamic optimization design of the rotor was carried out and the rotor blade design of three blades was analyzed. The optimized results reduced the hub load of 3 times per revolution by 24.9% ~ 33%.