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.
