北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (1): 112-119.doi: 10.13700/j.bh.1001-5965.2015.0034

• 论文 • 上一篇    下一篇

主起落架可控变速收放作动器设计与仿真

黄辰, 贾玉红   

  1. 北京航空航天大学航空科学与工程学院, 北京 100083
  • 收稿日期:2015-01-19 出版日期:2016-01-20 发布日期:2016-01-28
  • 通讯作者: 贾玉红,Tel.:010-82314805E-mail:jiayuhong@buaa.edu.cn E-mail:jiayuhong@buaa.edu.cn
  • 作者简介:黄辰男,博士研究生。主要研究方向:飞机起落架系统设计。Tel.:15810540480E-mail:huangchen@buaa.edu.cn;贾玉红女,博士,教授,博士生导师。主要研究方向:飞机起落架系统设计。Tel.:010-82314805E-mail:jiayuhong@buaa.edu.cn

Design and simulation of controllable aircraft main landing gear operating actuator

HUANG Chen, JIA Yuhong   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2015-01-19 Online:2016-01-20 Published:2016-01-28

摘要: 传统的起落架收放液压系统在使用中缺乏可控性,按照起落架收起时飞机极限过载设计的起落架收放液压作动器在常见的小过载工况下可能产生较大的冲击。提出了一种用于主起落架的可控变速收放作动器的概念设计,使用双向比例节流阀根据过载大小调节阻尼作用。结合起落架收放机构多体模型和收放作动器液压模型,对不同过载工况下主起落架收起的动力学过程进行了仿真分析。与常规设计相比,在一定的设计约束下降低了支柱终止速度、回油压力峰值和结构冲击。研究了变速收放作动器输入压力和进回油油路阻尼相对大小对仿真结果的影响。提出了一种改进的可控变速收放作动器设计,利用惯性力的作用进一步降低了起落架收起时的作动筒载荷峰值和冲击。

关键词: 飞机起落架, 起落架收放机构, 液压作动器, 动力学仿真, 冲击

Abstract: Conventional aircraft landing gear hydraulic system has little controllability during operation. Landing gear hydraulic operating actuator designed to operate under maximum aircraft load factor during landing gear retraction may lead to more serious impact under common load factors. Conceptual design of a controllable operating actuator applied to aircraft main landing gear was raised, which employs 2-way proportional throttle valves to adjust hydraulic damping according to load factor. Multibody model of landing gear retracting device and hydraulic model of operating actuator were combined in main landing gear retraction simulation under different load factors. Controllable design generates lower strut ending speed, actuator back pressure and structural impact compared with conventional design under certain design constrains. Effects of actuator input pressure and damping relation between the input and output throttle valves on simulation results were studied. Improved design of controllable operating actuator was raised, which further lessened maximum actuator load and impact of landing gear retraction by using the effect of inertia force.

Key words: aircraft landing gear, landing gear retracting devices, hydraulic actuators, dynamic simulation, impact

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