Stability analysis and vibration reduction design of aircraft brake induced chatter

被引：0
|
作者：
Jiang W. [1 ,2 ]
Zhang M. [1 ,2 ]
Yin Q.-Z. [1 ,2 ]
Zhu X. [1 ,2 ]
Hu X.-H. [1 ,2 ]
机构：
[1] Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
来源：
Zhendong Gongcheng Xuebao/Journal of Vibration Engineering | 2024年 / 37卷 / 05期
关键词：
bifurcation theory; brake induced vibration; nonlinear model; stability analysis; vibration reduction measures;
D O I：
10.16385/j.cnki.issn.1004-4523.2024.05.005
中图分类号：
学科分类号：
摘要：
Taking aircraft brakes as the research object，the problem of aircraft brake induced vibration was studied. Aiming at the influence of disc friction characteristics caused by the complex braking environment during aircraft skidding，a nonlinear dynamic analysis model of brake disc set was established considering the properties of the hydraulic system and disc material，with the model interface reserved for the development of new material technology. From the perspective of practical engineering research value，the influence of the above parameters on the stability of the system is studied by using numerical simulation，bifurcation theory，and other nonlinear analysis methods by considering key factors such as wheel speed，hydraulic system equivalent damping，brake disc surface damping and brake disc friction characteristics as control variables，and the range of structural parameters to keep the system stable is determined. It is convenient to parameterize the structure for rapid analysis and design. Based on the results of the model analysis，part of the causes of brake vibration were revealed，and corresponding optimization measures for vibration reduction were put forward from two aspects of structural parameters and brake control law. Then a comprehensive analysis method for aircraft brake induced flutter was formed，which provided a theoretical reference for the initial stage of aircraft brake design. © 2024 Nanjing University of Aeronautics an Astronautics. All rights reserved.
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页码：770 / 779
页数：9
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