An investigation of an active landing gear system to reduce aircraft vibrations caused by landing impacts and runway excitations

被引：41
作者：
Wang, Haitao [1 ,2 ]
Xing, J. T. [1 ]
Price, W. G. [1 ]
Li, Weiji [2 ]
机构：
[1] Univ Southampton, Sch Engn Sci, Southampton SO17 LBJ, Hants, England
[2] Northwestern Polytech Univ, Sch Aeronaut, Xian 710072, Peoples R China
来源：
JOURNAL OF SOUND AND VIBRATION | 2008年 / 317卷 / 1-2期
关键词：
D O I：
10.1016/j.jsv.2008.03.016
中图分类号：
O42 [声学];
学科分类号：
070206 ; 082403 ;
摘要：
A mathematical model is developed to control aircraft vibrations caused by runway excitation using an active landing gear system. Equations are derived to describe the integrated aircraft-active system. The nonlinear characteristics of the system are modelled and it is actively controlled using a Proportional Integral Derivative (PID) strategy. The performance of this system and its corresponding passive system are compared using numerical simulations. It is demonstrated that the impact loads and the vertical displacement of the aircraft's centre of gravity caused by landing and runway excitations are greatly reduced using the active system, which result in improvements to the performance of the landing gear system, benefits the aircraft's fatigue life, taxiing performance, crew/passenger comfort and reduces requirements on the unevenness of runways. (c) 2008 Elsevier Ltd. All rights reserved.
引用
收藏
页码：50 / 66
页数：17
相关论文
共 30 条
  • [1] Bakker E, 1995, PROG TECHNOL, V57, P439
  • [2] Catt T., 1992, 232 SDL
  • [3] Chicone C, 2006, ORDINARY DIFFERENTIA
  • [4] CURREY NS, 1998, AIAA ED SERIES
  • [5] DANIELS JN, 1996, CR201601 NASA
  • [6] Datta A., 2000, ADV IND CON
  • [7] Freymann R, 1987, R731 AGARD
  • [8] FREYMANN R, 1991, CP484 AGARD
  • [9] Fuller C., 1996, ACTIVE CONTROL VIBRA
  • [10] Testing of semiactive landing gear control for a general aviation aircraft
    Ghiringhelli, GL
    [J]. JOURNAL OF AIRCRAFT, 2000, 37 (04): : 606 - 616
123