北京航空航天大学学报 ›› 2011, Vol. 37 ›› Issue (5): 626-630.

• 论文 • 上一篇    

基于静态输出反馈的大型飞机横航向控制综合

聂璐, 向锦武   

  1. 北京航空航天大学 航空科学与工程学院, 北京 100191
  • 收稿日期:2010-11-18 出版日期:2011-05-30 发布日期:2011-05-30
  • 作者简介:聂 璐(1983-),男,安徽寿县人,博士生,nielu@ase.buaa.edu.cn.
  • 基金资助:

    国家自然基金资助项目(90916006)

Lateral flight control synthesis for large transport based on static output feedback

Nie Lu, Xiang Jinwu   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2010-11-18 Online:2011-05-30 Published:2011-05-30

摘要: 由于广泛采用轻质材料,大型飞机的结构柔性使得控制系统和结构动力学之间存在不可避免的耦合现象,控制器设计必须同时考虑结构柔性对系统反馈的贡献,并满足飞行品质、鲁棒性等目标.提出了一种利用刚体飞行动力学模型和包含弹性模态的高阶模型设计满足多种目标的控制器综合方法,首先由刚体模型设计静态输出反馈参数,满足动态响应、飞行品质和抑制阵风扰动等要求,在此基础上利用已获得的静态反馈参数针对高阶模型设计H回路成形控制器,实现对结构模态的抑制,并满足系统的鲁棒性需求.仿真结果表明:设计方法能够充分利用包含弹性模态的大型飞机飞行动力学模型的特点,满足结构模态抑制和鲁棒稳定裕度等多种需求.

Abstract: Structural flexibility of large transport results unavoidable coupling between control system and structural dynamics due to the application of large amounts of light material. Control system design for such aircraft should consider contribution from structural flexibility, and satisfy the specifications from flying qualities. To consider elastic modes in aircraft control system synthesis process, a novel H loop shaping design procedure was given. Inner loop feedback gain was calculated by rigid flight dynamic model to satisfy specifications from flying qualities requirements and atmospheric turbulence rejection. The initial static output feedback gain obtained by rigid truncated model was used as weight for the high order model. Dynamic controller was consequently given by Glover-McFarlane-s H loop shaping method to keep system stable while elastic modes are involved in the high order model. A typical numerical model and simulation in time domain were given to compare with the original design and better response shape and elastic modes suppression were shown.

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