Vibration Reduction of a Bearingless Helicopter Rotor with Composite Tailored Couplings

摘要：

　　The study was conducted to gain some important characteristics of the influence of the blade flap-bending/torsion elastic coupling stiffness on blade root flap-shear force and vibratory hub loads of a bearingless rotor.Based on the aerodynamic force,this paper presents a loose coupled aeroelastic analytical model by finite element method.Four sets of composite rotor with different elastic couplings were designed and investigated.The results of the investigation showed that flap-bending/torsion couplings have a significant effect on the rotor vibratory hub loads and the distribution of the couplings also critical for the degree of vibration reduction.Through the present research,it has been demonstrated that structural couplings can significantly impact rotor vibration characteristics.

关键词： Bearingless helicopter rotor Vibration reduction Composite blades Tailored couplings Finite element method

作者: Yu Jin Luo Yu Liu Yong

作者单位: National Key Laboratory of Rotorcraft Aeromechanics,Nanjing University of Aeronautics and Astronautics,29 YudaoStreet,Nanjing 210016,P.R.C

会议类型: 国际会议

会议名称: 2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)

会议地点: 上海

会议语种:英文

页码: 1-8

在线出版日期: 2014-09-24（万方平台首次上网日期，不代表论文的发表时间）