Adjustable stiffness structure application in helicopter vibration reduction

被引：0
|
作者：
Lin C.-L. [1 ]
Xia S.-M. [1 ]
Zhang T.-L. [2 ]
Sun X.-W. [1 ]
Zhu Y.-F. [1 ]
机构：
[1] Aircraft Design and Research Institute, AVIC Harbin Aircraft Industry Group Co. Ltd., Harbin
[2] The Military Representative Office of the Army Aviation Department in Harbin Region, Harbin
来源：
Zhendong Gongcheng Xuebao/Journal of Vibration Engineering | 2019年 / 32卷 / 06期
关键词：
Adjustable stiffness structure; Helicopter vibration; Modal analysis; Vibration reduction;
D O I：
10.16385/j.cnki.issn.1004-4523.2019.06.003
中图分类号：
学科分类号：
摘要：
Helicopter vibration has been puzzling the development and application of helicopter. Although there are many methods to solve the problem of helicopter vibration, for the current type of helicopter, due to the limitation of structure and modification scope, the conventional vibration absorber and the active vibration control technology are not suitable. In this paper, the design concept for the adjustable stiffness structure is firstly presented, it is used to eliminate the impact of manufacturing deviation on the local structure frequency and vibration mode so as to achieve the purpose of vibration reduction. With the methods of simulation analysis, ground excitation test and flight vibration test, it is verified that the adjustable stiffness structure significantly reducing the vibration level of the helicopter airframe. The work of this paper can be reference to helicopter vibration control. © 2019, Nanjing Univ. of Aeronautics an Astronautics. All right reserved.
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页码：950 / 955
页数：5
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