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Volume 37 Issue 9
Sep.  2011
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Journal of Beijing University of Aeronautics and Astronautics  > 2011  >  37(9): 1147-1150.
Ding Peng, Ma Qishuang, Li Changyou, et al. Wavelet and nonlinear model based borescope image compression[J]. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(02): 214-217. (in Chinese)
Citation: Guo Junxian, Xiang Jinwu, Qin Haiyinget al. Rotor damping analysis based on helicopter dynamic requirement with rotor/fuselage coupling[J]. Journal of Beijing University of Aeronautics and Astronautics, 2011, 37(9): 1147-1150. (in Chinese)
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Rotor damping analysis based on helicopter dynamic requirement with rotor/fuselage coupling

  • 1.

    School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

  • 2. China Helicopter Research and Development Institute, Jingdezhen 333001, China

  • Received Date: 28 Apr 2010
  • Publish Date: 30 Sep 2011
    Abstract
  • The rotor damping is one of the key points for a helicopter dynamic design. An introduction to the theoretical and practical study of one of the helicopter dynamic problems, which describesd the development of the rotor damping based on the helicopter dynamic with rotor/fuselage coupling that contains the stability analysis of ground resonance and the stability of rotor/power/transmission coherent was given. Based on the dynamic requirement of rotor/frame, damping analysis of the elasto-damper and the fluid-damper, which considered the effect of the stiffness and the damping was presented. The parametric sensitivity of the damper stiffness and damping was estimated. With constraints from engine control and ground resonance, the different effect was given with various available designs.Calculating and testing results performed demonstrating that, as solution to the dynamic problem, the damping with suitable orifice design for a variable liquid damper is reasonable for the helicopter dynamic problem solution and rotor blade folding.

     

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  • [1] Ivchin V.Analysis of lag motion damping for upgraded Mil-24 main rotor blades in hover,level and maneuvering flight based on flight test results .AHS-2001-160,2001 [2] Guo Junxian,Xiang Jinwu.Composite rotor blade design optimization for vibration reduction with aeroelastic constraints[J].Chinese Journal of Aeronautics,2004,17(3):152-158 [3] Phuriwat A I,Gandhi F.Reduction of helicopter vibration through cyclic control of variable orifice damper .AHS-2002-94,2002 [4] 郭俊贤,胡茂和,艾剑波.某型直升机动力学解决方案 //第25届直升机年会会议论文集.景德镇:中国航空学会,2009:383-386 Guo Junxian,Hu Maohe,Ai jianbo.The scheme of XX helicopter dynamic problem //The 25th National Annual Conference on Helicopter.Jingdezhen:Chinese Society of Aeronautics and Astronautics,2009:383-386(in Chinese) [5] Hu Guocai,Xiang Jinwu,Zhang Xiaogu.Analytical model of elastomeric lag damper kinematic coupling and Its effect on helicopter air resonance in hover[J].Chinese Journal of Aeronautics,2002,15(1):27-32
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