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飞机起落架系统摆振动力学研究进展

发布日期: 2022-07-21 | 浏览次数: 178
飞机起落架系统摆振动力学研究进展

刘小川1,2,3, 刘冲冲1,2,3, 牟让科1,2,3                          

1. 中国飞机强度研究所, 西安 710065;
2. 结构冲击动力学航空科技重点实验室, 西安 710065;
3. 陕西省飞行器振动冲击与噪声重点实验室, 西安 710065

Research progress on shimmy dynamics of aircraft landing gear systems

LIU Xiaochuan1,2,3, LIU Chongchong1,2,3, MOU Rangke1,2,3        

1. Aircraft Strength Research Institute of China, Xi'an 710065, China;
2. Aviation Key Laboratory of Science and Technology on Structural Impact Dynamics, Xi'an 710065, China;
3. Shaanxi Province Key Labortary of Aircraft Vibration, Impact and Noise, Xi'an 710065, China

                                                    

摘要: 摆振是起落架支柱侧向运动与围绕支柱的扭转运动相互耦合产生的自激振动,对飞机地面滑行的操纵性与安全性等具有很大的危害,是起落架系统设计中重点关注的动力学问题之一。摆振主要有"轮胎型"和"结构型"2类,可以采用动力学理论建模、多体动力学数值分析与全尺寸物理试验等方法对起落架系统的摆振特性进行研究,已发展了线性与非线性理论建模方法和数值工具,建立起了起落架摆振试验系统,也开展了全机瞬态激励下的滑跑稳定性试验。为防止摆振问题的产生,在认识摆振机理的基础上,研究者广泛而又深入地研究了起落架设计参数、轮胎参数、机体特性等对滑跑动响应与稳定性的影响,在获得各种设计参数对起落架摆振稳定性影响的基础上,发展了摆振动力学优化设计方法和智能器件与半主动/主动控制的摆振抑制方法,并开展了试验验证或装机演示验证。结合未来飞机平台的发展和起落架技术的创新,对起落架摆振动力学问题的未来发展方向进行了展望。

关键词: 飞机滑跑, 起落架, 摆振, 减摆器, 摆振抑制

Abstract: As a self-excited vibration generated by the mutual coupling of the lateral motion and the torsional motion of the landing gear strut,shimming does great harm to the maneuverability and safety of aircraft taxiing on the ground and becomes an important dynamic problem in the design of landing gear system. There are two types of shimmy,the tire-yaw shimmy and the structural-torsion shimmy. Currently,dynamic theoretical modeling, multi-body dynamics numerical analysis and full-scale physical test could be used to study the shimmy characteristics of landing gear system. Linear and nonlinear theoretical modeling methods and numerical tools have been developed, and landing gear shimmy test systems has been established, the sliding stability tests of the aircrafts under transient excitations were also carried out. To prevent the occurrence of shimmy problems, based on the understanding of the shimmy mechanism, the researchers have extensively and deeply studied the effects of landing gear design parameters, tire parameters and aircraft fuselage characteristics on the sliding response and stability. The dynamic optimization design methods and the shimmy suppression of intelligent devices, and semi-active/active control methods are developed;the test verifications or landing gear installation demonstration verifications are carried out. Drawing upon the future development of aircraft platform and the innovation of landing gear technology, the future development direction of landing gear shimmy dynamics is prospected.

Key words: aircraft taxing, landing gear, shimmy, shimmy damper, shimmy suspension

                                                    

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