Multi-Objective Optimization of Helicopter Rotor Vibration Reduction by Modal Shaping
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.
Hong-zhou Wang Yong Liu Cheng-lin Zhang
National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics Nanjing University of Aeronautics and Astronautics Nanjing, Jiangsu, 210016, China
国际会议
南京
英文
1-8
2009-10-14（万方平台首次上网日期，不代表论文的发表时间）