Wang Hongzhou;Liu Yong;Zhang Chenglin

National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing,210016

 The aeroelastic and modal shaping finite element dynamics model was derived from Hamilton theory. It can be analyzed the systematic structural dynamics by changing the stiffness and mass of blade section. The stiffness and mass of blade section were used as design variables, constraints on frequency placement, autorotational inertia, mass and MSP were included, the objective function was to minimize the blade vibration. Finally, compared with the optimization results of the designed model, the result shows that the optimum solution results will cause 55.4％ reduction of the 3/rev rotor blade root shears, 66.5% reduction of 4/rev rotor blade shears and 53.4% reduction of the 5/rev rotor blade shear under the constrained conditions.

基于Hamilton原理推导了模态修型减振优化的有限元动力学模型,通过修改桨叶的剖面刚度和线密度来改变结构的动力学模态。以最小振动载荷为目标函数,以桨叶剖面刚度及质量为设计变量,以桨叶的频率、自转惯量、质量及模态修型参数等为约束条件,进行了减振优化。算例表明：在约束条件都满足的情况下, 优化后,3/转的桨根剪力减小了55.4％,4/转的桨根剪力减小了66.5%,5/转的桨根剪力减小了53.4%,优化效果明显。

气弹动力学模型, 模态修型, 减振优化, 有限元模型