北京航空航天大学学报 ›› 2004, Vol. 30 ›› Issue (05): 438-443.

• 论文 • 上一篇    下一篇

直升机旋翼/动力/传动系统模型及耦合影响

薛海峰, 向锦武, 张晓谷   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100083
  • 收稿日期:2002-12-04 出版日期:2004-05-31 发布日期:2010-09-21
  • 作者简介:薛海峰(1970-),男,江苏盐城人,博士生, fenghaixue@eyou.com.

Coupled helicopter rotor/propulsion/transmission system torsional vibration analytical model and coupled influence investigation

Xue Haifeng, Xiang Jinwu, Zhang Xiaogu   

  1. School of Aeronautics Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2002-12-04 Online:2004-05-31 Published:2010-09-21

摘要: 为了提供有效的避免系统共振的设计措施,针对某型直升机的实际情况建立了该型号直升机的发动机、传动系统与旋翼、尾桨组成的机械扭振系统的分析模型.用特征分析和阻抗匹配方法对系统各个模态固有特性包括固有频率和振型进行了对比计算和结果分析.研究了模态固有特性在扭振系统耦合前后的变化,以及旋翼变转速对孤立桨叶和耦合后旋翼固有特性的影响,得出了避免系统共振的设计措施.

Abstract:     To get methods avoiding system resonance, a practical analytical model of a helicopter's mechanic system of torsional oscillation was developed. The torsional system consisted of the helicopter's propulsion, the transmission system, the rotor and the tail rotor. The modal properties including modal frequencies and mode shapes of the torsional oscillation system were calculated and analyzed with eigen analysis and impedance matching method. The coupled modal properties were analyzed and compared with the hub fixed isolated rotor and the coupled rotor/propulsion/transmission system. The influence to the isolated blade and the rotor of coupled torsional system though changing rotor speed was gotten. Some effective methods to avoid resonance in designing were given.

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