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Volume 30 Issue 06
Jun.  2004
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Journal of Beijing University of Aeronautics and Astronautics  > 2004  >  30(06): 516-519.
DONG Chao-yang, SHI Xiao-rong, ZHANG Ming-lianet al. Modelling and Fuzzy VariableStructure Control of Agile Missile[J]. Journal of Beijing University of Aeronautics and Astronautics, 2002, 28(1): 21-24. (in Chinese)
Citation: Li Kang, Fang Zhenping. High angle-of-attack control law design based on global stability analysis[J]. Journal of Beijing University of Aeronautics and Astronautics, 2004, 30(06): 516-519. (in Chinese)
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High angle-of-attack control law design based on global stability analysis

  • School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

  • Received Date: 20 Jan 2003
  • Publish Date: 30 Jun 2004
    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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