Vibration Reduction of a Bearingless Helicopter Rotor with Composite Tailored Couplings

被引：1

作者：

Jin, Yu ^{[1
]}

Yu, Luo ^{[1
]}

Yong, Liu ^{[1
]}

机构：

[1] Nanjing Univ Aeronaut & Astronaut, Natl Key Lab Rotorcraft Aeromech, 29 YudaoSt, Nanjing 210016, Jiangsu, Peoples R China

来源：

2014 ASIA-PACIFIC INTERNATIONAL SYMPOSIUM ON AEROSPACE TECHNOLOGY, APISAT2014 | 2015年 / 99卷

关键词：

Bearingless helicopter rotor; Vibration reduction; Composite blades; Tailored couplings; Finite element method; STABILITY;

D O I：

10.1016/j.proeng.2014.12.672

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

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. (C) 2015 The Authors. Published by Elsevier Ltd.

引用

页码：1372 / 1379

页数：8

共 13 条

[1]

Bao J., 2004, Development of Mach scale rotors with composite tailored couplings for vibration reduction

[2]

Chopra I., 2000, HELICOPTER DYNAMICS

[3]

Dull AL., 1988, J AM HELICOPTER SOC, V33, P38, DOI DOI 10.4050/JAHS.33.38

[4]

Foye R.L., 1981, Journal of the American Helicopter Society, V26, P5