无轴承式旋翼桨叶固有振动特性分析

李学常; 李书

无轴承式旋翼桨叶固有振动特性分析

李学常,
李书

北京航空航天大学航空科学与工程学院,北京 100191

基金项目: 国家自然科学基金(10772013)

计量
- 文章访问数: 1565
- HTML浏览量: 0
- PDF量: 14
- 被引次数: 0
出版历程
- 收稿日期: 2010-05-11
- 修回日期: 2010-09-21
- 刊出日期: 2011-06-28

Natural vibration analysis of bearingless rotor blades

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

摘要

摘要: 利用传递矩阵法,研究了无轴承式旋翼桨叶的固有振动特性,计算出了套管根部固支约束和弹簧约束时旋翼振动的固有频率,并给出了套管根部变距/摆振耦合对固有频率的影响,同时也研究了不同的模型参数对固有频率的影响,最后给出了根部弹簧约束时的部分模态振型.结果表明,套管根部变距/摆振耦合对固有频率影响不大,总距角对各阶模态频率影响比较复杂,桨叶质心线到弹性轴线的距离只对高阶模态的频率略有影响.
- 无轴承式旋翼 /
- 传递矩阵法 /
- 固有振动 /
- 固有频率 /
- 模态振型
Abstract: Natural vibration characteristics of bearingless rotor blades design were investigated by transfer matrix method,and the natural frequencies of blade vibration were calculated with a fixed or spring restrained torque tube end.Coupling of pitch/lead-lag was also considered.Parametric studies were performed to examine the effects of several model parameters on vibration natural frequencies.Some flapwise and chordwise bending mode shapes were revealed.The results indicate that pitch/lead-lag coupling of the torque tube end has little influence on natural frequencies,the pitch angle of blade has complex influence on natural frequencies,and the distance of mass center from elastic axis has slight influence on high natural frequencies.
- bearingless rotor /
- transfer matrix method /
- natural vibration /

HTML

参考文献(12)

[1]	张晓谷.直升机动力学设计[M].北京:航空工业出版社,1995.
[2]	Fenaughty R R,Noehren W L.Composite bearingless tail rotor for UTTAS[J].Journal of the American Helicopter Society,1977,22(3):19-26.
[3]	Dixon P G C,Bishop H E.The bearingless main rotor[J].Journal of the American Helicopter Society,1980,25(3):15-21.
[4]	Byrnes F E,Krauss A T.Composite flexbeam for a bearingless helicopter rotor:US,5096380 .1992-03-17.
[5]	Friedmann P P.Rotory-wing aeroelastic:current status and future trends[J].AIAA Journal,2004,42(10):1953-1972.
[6]	Murthy V R,Shultz L A.Linear and nonlinear dynamic analysis of redundant load path bearingless rotor systems .NASA CR-197220,1994.
[7]	Lee A,Yuan K,Liu S L.A modified transfer matrix method for linear rotor-bearing systems[J].Journal of Applied Mechanics,1991,58(3):776-783.
[8]	Murthy V R,Joshi A M.Free vibration characteristics of multiple load path by the transfer matrix method[J].Journal of American Helicopter Society,1986,31(4):43-50.
[9]	薛海峰,向锦武,张晓谷,等.变距/摆振耦合对直升机空中共振稳定性的影响[J].中国工程科学,2007,9(9):58-62. XUE Haifeng,XIANG Jinwu,ZHANG Xiaogu,et al.Investigation of the influence of pitch/lag on helicopter air resonance stability[J].Chinese Engineering Science,2007,9(9):58-62.(in Chinese)
[10]	Houbolt J C,Brooks G W.Differential equations of motion for combined flapwise bending,chordwise bending,and torsion of twisted non-uniform rotor blades .NACA TN-3905,1957.
[11]	Jang J,Chopra I.Ground and air resonance of bearingless rotors in hover .Monterey,CA:Structures,Structural Dynamics and Materials Conference,28th,and AIAA Dynamics Specialists Conference,Technical Papers,Part 2B,1987:1068-1084.
[12]	Sivaneri N T,Chopra I.Finite element analysis for bearingless rotor blade aeroelasticity[J].Journal of American Helicopter Society,1984,29(2):42-51.