Multi-Objective Optimization of Helicopter Rotor Vibration Reduction by Modal Shaping

机译：模态整形减少直升机旋翼减振的多目标优化

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This chapter derives the aeroelastic and modal shaping finite element dynamics model from Hamilton theory. It analyzes the systemic structural dynamics by changing the stiffness and mass of the blade section. The stiffness and mass of blade section are used as design variables, constrains on frequency placement, autorotational inertia and modal shaping parameters are included, the multi-objective functions are to minimize the blade vibration and blade mass. The method of optimization is Adaptive Simulated Annealing. Finally, compared with the optimization result of the designed model, the result shows that the optimum solution results in a 32.2％ reduction of the 3/rev rotor blade root shear, 51.6% reduction of the 4/rev rotor blade root shear, 41.5% reduction of the 5/rev rotor blade root shear and 6.01% blade mass reduction under the control of the constrained conditions.

机译：本章从汉密尔顿理论推导了气动弹性模态成形有限元动力学模型。它通过更改叶片部分的刚度和质量来分析系统的结构动力学。叶片截面的刚度和质量用作设计变量，包括频率布置，自动旋转惯性和模态成形参数的约束，其多目标功能是使叶片振动和叶片质量最小化。优化的方法是自适应模拟退火。最后，与设计模型的优化结果进行比较，结果表明，最佳解决方案可使3 / rev转子叶片根部剪切力降低32.2％，使4 / rev转子叶片根部剪切力降低51.6％，41.5％在受限条件下，可减少5 /转转子叶片根部剪切力并减少6.01％的叶片质量。

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来源
《The 3rd international basic research conference on rotorcraft technology: Basic research advance in rotorcraft technology》|2009年|1-8|共8页
会议地点 Nanjing(CN)
作者
Hong-zhou Wang; Yong Liu; Cheng-lin Zhang;
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作者单位

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics Nanjing University of Aeronautics and Astronautics Nanjing, Jiangsu, 210016, China;

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics Nanjing University of Aeronautics and Astronautics Nanjing, Jiangsu, 210016, China;

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics Nanjing University of Aeronautics and Astronautics Nanjing, Jiangsu, 210016, China;

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正文语种 eng
中图分类 V275.1;
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机译：基于代理的直升机旋翼桨叶优化，以降低前向飞行的振动
2. Surrogate based optimization of helicopter rotor blades for vibration reduction in forward flight [J] . Glaz B, Friedmann PP, Liu L Structural and multidisciplinary optimization . 2008,第4期

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3. An optimization approach to vibration reduction in helicopter rotors with multiple active trailing edge flaps [J] . Sathyamangalam Ramanarayanan Viswamurthy, Ranjan Ganguli Aerospace science and technology . 2004,第3期

机译：具有多个主动后缘襟翼的直升机旋翼减振的优化方法
4. Multi-Objective Optimization of Helicopter Rotor Vibration Reduction by Modal Shaping [C] . Hong-zhou Wang, Yong Liu, Cheng-lin Zhang International basic research conference on rotorcraft technology . 2009

机译：通过模态塑形的直升机转子振动的多目标优化
5. Nonlinear coupled rotor-fuselage vibration analysis and higher harmonic control studies for vibration reduction in helicopters [D] . Papavassiliou, Ioanis. 1991

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7. Aerodynamic Shape Optimization of the Helicopter Main Rotor Hub Beanie, Using Advanced Multi-Objective Evolutionary Algorithms [O] . Dal Mas Lorenzo 2013

机译：使用先进的多目标进化算法优化直升机主旋翼毂无檐小便帽的空气动力学形状
8. Optimizing Tuning Masses for Helicopter Rotor Blade Vibration Reduction IncludingComputed Airloads and Comparison with Test Data [R] . Pritchard, J. I., Adelman, H. M., Walsh, J. L., 1992

机译：优化直升机旋翼叶片的调谐质量减少包括编译的空气负荷和与测试数据的比较

Multi-Objective Optimization of Helicopter Rotor Vibration Reduction by Modal Shaping

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