Impact of the fuselage damping characteristics and the blade rigidity on the stability of helicopter

被引：6
|
作者：
Chellil, A. [1 ]
Nour, A. [1 ]
Lecheb, S. [1 ]
Kebir, H. [2 ]
Chevalier, Y. [3 ]
机构：
[1] MB Boumerdes Univ, Dynam Engines & Vibroacoust Lab, FSI, Boumerdes, Algeria
[2] Univ Technol Compiegne, UMR CNRS UTC 7337, Roberval Lab, Compiegne, France
[3] Higher Mech Inst Paris, Engn Lab Mech Syst & Mat, Paris, France
来源：
AEROSPACE SCIENCE AND TECHNOLOGY | 2013年 / 29卷 / 01期
关键词：
Composite materials; Aeroelastic; Aerodynamic; Blade; Vibration; MODEL;
D O I：
10.1016/j.ast.2013.03.007
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
The aim of this work is to compare in the system of blade articulations, the hydraulic and elastomeric dampers in order to reduce the vibration level in the helicopter rotors. Based on an aerodynamic model, a three-dimensional model of the composite material blade was developed. Numerical calculations on the model developed taking into account the aeroelastic interaction prove that the elastomeric damper of viscoelastic type produces better results compared to other hydraulic damper. The study of the blade stability depending on the orientation of the composite fibers is an important factor to determine the rigidity of the structure. (C) 2013 Elsevier Masson SAS. All rights reserved.
引用
收藏
页码：235 / 252
页数：18
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