北京航空航天大学学报 ›› 2004, Vol. 30 ›› Issue (06): 516-519.

• 论文 • 上一篇    下一篇

基于全局稳定性分析的大迎角飞控系统设计

黎康, 方振平   

  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:2003-01-20 出版日期:2004-06-30 发布日期:2010-09-21
  • 作者简介:黎 康(1974-),男,陕西咸阳人,博士生, likangkk@163.com.

High angle-of-attack control law design based on global stability analysis

Li Kang, Fang Zhenping   

  1. School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2003-01-20 Online:2004-06-30 Published:2010-09-21

摘要: 针对飞机大迎角非线性动力学系统,提出用全局稳定性分析方法指导大迎角控制律设计.首先利用非线性分叉分析方法研究了大迎角非线性动力学系统的结构稳定性问题.在此基础上,通过合理选择平衡点线化方程,采用特征结构配置方法设计调参的大迎角控制律,以使飞机的稳定飞行状态可延伸至大迎角范围.此外,还通过时域数字仿真估算了闭环系统大迎角稳定平衡点的吸引域.与其他方法相比可得到闭环控制系统的定范围渐近稳定性,而不仅是Lyapunov局部渐近稳定性.

Abstract:   A global stability analysis was presented to guide high angle-of-attack (AOA) control law design for nonlinear aircraft dynamic system. Bifurcation analysis was firstly explored to investigate the structural stability of nonlinear aircraft dynamic system at high AOA. Then by reasonably selecting equilibrium points, eigenstructure assignment was applied to design gain scheduling control law at high AOA and the extension of stable flight region to high AOA was achieved. By using time domain numerical simulations, the domains of attractor for stable equilibrium points at high AOA were estimated. In contrast to other methods, global asymptotic stability of nonlinear aircraft dynamic system is obtained other than Lyapunov local asymptotic stability.  

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