带气弹稳定性约束的复合材料浆叶减振优化设计

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%。

Composite Rotor Blade Design Optimization for Vibration Reduction with Aeroelastic Constraints

The paper presents an analytical study of the helicopter rotor vibratory load reduction design optimization with aeroelastic stability constraints.The composite rotor blade is modeled by beam type finite elements, and warping deformation is taken into consideration for 2-dimension analysis, while the one-dimension nonlinear differential equations of blade motion are formulated via (Hamilton's) principle. The rotor hub vibratory loads is chosen as the objective function, while rotor blade section construction parameter, composite material ply structure and blade tip swept angle as the design variables, and autorotation inertia, natural frequency and aeroelastic stability as the constraints. A 3-bladed rotor is designed, as an example, based on the vibratory hub load reduction optimization process with swept tip angle and composite material. The calculating results show a 24.9%-33% reduction of 3/rev hub loads in comparison with the base-line rotor.