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Applied Mathematics and Mechanics (English Edition) ›› 2010, Vol. 31 ›› Issue (2): 237-246.doi: https://doi.org/10.1007/s10483-010-0211-9

• Articles • 上一篇    下一篇

Nonlinear aeroelastic coupled trim and stability analysis of rotor-fuselage

胡新宇1 韩景龙2 喻梅1   

  1. 1. Department of Engineering Mechanics, College of Sciences, China University of Mining and Technology, Xuzhou 221008, Jiangsu Province, P. R. China;
    2. Institute of Vibration Engineering Research, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P. R. China
  • 收稿日期:2009-02-13 修回日期:2009-12-15 出版日期:2010-02-01 发布日期:2010-02-01

Nonlinear aeroelastic coupled trim and stability analysis of rotor-fuselage

HU Xin-Yu1, HAN Jing-Long2, YU Mei1   

  1. 1. Department of Engineering Mechanics, College of Sciences, China University of Mining and Technology, Xuzhou 221008, Jiangsu Province, P. R. China;
    2. Institute of Vibration Engineering Research, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P. R. China
  • Received:2009-02-13 Revised:2009-12-15 Online:2010-02-01 Published:2010-02-01

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摘要： Based on the Hamilton principle and the moderate deflection beam theory, discretizing the helicopter blade into a number of beam elements with 15 degrees of freedom, and using a quasi-steady aero-model, a nonlinear coupled rotor/fuselage equation is established. A periodic solution of blades and fuselage is obtained through aeroelastic coupled trim using the temporal finite element method (TEM). The Peters dynamic inflow model is used for vehicle stability. A program for computation is developed, which produces the blade responses, hub loads, and rotor pitch controls. The correlation between the analytical results and related literature is good. The converged solution simultaneously satisfies the blade and the vehicle equilibrium equations.

Abstract: Based on the Hamilton principle and the moderate deflection beam theory, discretizing the helicopter blade into a number of beam elements with 15 degrees of freedom, and using a quasi-steady aero-model, a nonlinear coupled rotor/fuselage equation is established. A periodic solution of blades and fuselage is obtained through aeroelastic coupled trim using the temporal finite element method (TEM). The Peters dynamic inflow model is used for vehicle stability. A program for computation is developed, which produces the blade responses, hub loads, and rotor pitch controls. The correlation between the analytical results and related literature is good. The converged solution simultaneously satisfies the blade and the vehicle equilibrium equations.

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