Random dynamic load of aircraft under aircraft-pavement coupled action

被引：0
|
作者：
Dong Q. [1 ,3 ]
Zhang X. [1 ,2 ]
Bao Y. [1 ]
Cheng S. [1 ]
Zhang Y. [1 ]
机构：
[1] College of Transportation Science and Engineering, Civil Aviation University of China, Tianjin
[2] College of Civil Aviation, Nanjing University of Aeronautics and Astronautics, Nanjing
[3] School of Architectural Engineering, Tianjin University, Tianjin
来源：
Zhendong yu Chongji/Journal of Vibration and Shock | 2023年 / 42卷 / 05期
关键词：
aircraft lift; aircraft-pavement coupling; power spectral density; random dynamic loads; roughness;
D O I：
10.13465/j.cnki.jvs.2023.05.035
中图分类号：
学科分类号：
摘要：
A four-degree-of-freedom model of the aircraft main landing gears was established to accurately calculate the aircraft dynamic loads which change randomly with time and positions during the taxiing. The coupling between aircraft and pavement was analyzed. The random dynamic load of each main landing gear of B737-800 was obtained considering the influence of pavement roughness and aircraft lift by finite element simulation technology. The power spectral density of aircraft dynamic load was obtained by the Welch method, and the rule of load energy distribution in frequency domain was explored. The research results show that when the taxiing speed remains unchanged and the International Roughness Index are 1.56, 3.12, and 4.68, the peak dynamic load on each main landing gear of the B737-800 can increase by 7%. When the International Roughness Index remains unchanged and the aircraft taxiing speed increases from 10m/s to 40m/s, the dynamic load tends to decrease under the influence of aircraft lift. The increase of taxiing speed, the increase of the suspension stiffness and the increase of non-suspension stiffness all lead to the increase of the frequency of aircraft random dynamic load. With the decrease of the pavement roughness, the frequency of aircraft dynamic load remains unchanged, and only the peak value of the power spectral density increases. With the increase of the aircraft suspension damping, the peak value of the power spectral density of the dynamic load decreases obviously, but the frequency remains unchanged. However, the damping the non-suspended part effect extremely tiny on the power spectral density of random dynamic loads. © 2023 Chinese Vibration Engineering Society. All rights reserved.
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页码：287 / 294+312
相关论文
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