Analysis of Impacts of Magnetorheological Landing Gear on Aircraft Dynamics Considering Wing Flexibility

被引：0
|
作者：
Zhu H. [1 ,2 ]
Yang L. [1 ,3 ]
Zhu S. [1 ]
Fu Y. [1 ]
机构：
[1] College of Aeronautical Engineering, Civil Aviation University of China, Tianjin
[2] Aviation Special Ground Equipment Research Base, CAAC, Tianjin
[3] Engineering Technology Center, AVIC XAC Commercial Aircraft Co., Ltd., Xi'an
来源：
Hsi-An Chiao Tung Ta Hsueh/Journal of Xi'an Jiaotong University | 2022年 / 56卷 / 12期
关键词：
aircraft landing dynamics; impact dynamics; magnetorheological landinggear; rigid-flexible coupling; wing flexibility;
D O I：
10.7652/xjtuxb202212006
中图分类号：
学科分类号：
摘要：
This paper investigates the effects of wing flexibility on aircraft dynamics during the entire landing process. A drop-shock dynamic model of the nose landing gear equipped with a single-rod magnetorheological (MR) shock absorber is established and validated through a bench test. The drop-shock dynamic characteristics of the MR landing gear of the aircraft with flexible wings are investigated. Considering the internal structure dimensions of the MR shock absorber strut, pressure and flow variations, and properties of the MR fluid, a lumped parameter dynamic model for the MR landing gear considering the MR damping resistance, compressed pneumatic spring force and orifice damping force is derived. In addition, virtual prototype of the MR landing gear is built in Adams/View environment to carry out simulation research under the same drop-shock conditions as in the bench test. The comparison between the simulation and test results show that the relative errors in the peak load, vertical overload ratio, maximum stroke of the landing gear and tire compression are all about 10%. Further, the wing of a certain unmanned aerial vehicle is simplified as a cantilever beam of uniform cross-section and a rigid-flexible coupled dynamic model for the MR landing gear considering wing flexibility is established for the drop-shock dynamic analyses. According to the numerical results, the wing flexibility can reduce the peak load of the MR landing gear and the maximum stroke of the shock absorber: When the input currents of the MR shock absorber are 0 A and 1. 2 A, the peak load of the landing gear due to flexible wing deformation is respectively 0. 4% and 0. 41 % of the total in the earlier stage of the landing process, and 1. 96% and 4. 16% respectively in the later stage of the landing process. This indicates that a large part of the impact energy absorbed by flexible wing deformation is released in the later stage. In conclusion, the damping adaptation of the MR shock absorber can be realized by changing the input current, which can alleviate the impact of aircraft landing and prolong the service life of aircraft structural components to a certain extent. © 2022 Xi'an Jiaotong University. All rights reserved.
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页码：56 / 67
页数：11
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