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| Influence factors analysis for smart vibration control of a rotor wing with trailing edge flaps |
| LIU Shiming1,YANG Weidong1,YU Zhihao1,WU Jie2 |
1. National Key Laboratory of Rotorcraft Aeromechanics, College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics, Nanjing 210000, China;
2. School of Naval Architecture & Ocean Engineering,Jiangsu University of Science and Technology, Zhenjiang 212000, China |
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Abstract An aeroelastic load computation model and the optimization method of vibration control for a smart rotor wing with trailing edge flags were developed. The influences of aerodynamic forces and inertial forces of rigid body trailing edge flaps on its elastic blades system were considered. The viscous vortex particle method with the airfoil look-up table was used to compute the aerodynamic load of the rotor wing. The vibratory blade and hub loads were predicted with the force integration method. An optimal algorithm combining the steepest decent method and the golden section algorithm was derived for the defined objective function including the blade torsion and hub vibration loads. It was demonstrated that the proposed model can effectively control the vibratory loads, and the objective function can be reduced by about 70%; the torsion of elastic blades ensures the trailing edge flaps can effectively reduce vibration, while it amplifies the aerodynamic pitch moment of the trailing edge flaps, the latter brings additional blade torsional moment.
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Received: 30 October 2015
Published: 25 January 2017
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