北京航空航天大学学报 ›› 2008, Vol. 34 ›› Issue (01): 31-34.

• 论文 • 上一篇    下一篇

迟滞非线性气动弹性反馈线性化自适应控制

李道春,向锦武   

  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:2006-12-30 出版日期:2008-01-31 发布日期:2010-09-17
  • 作者简介:李道春(1980-),男,山东梁山人,博士生,lidc@ase.buaa.edu.cn.
  • 基金资助:

    国家自然科学基金资助项目(10272012);教育部新世纪优秀人才基金资助项目(NCET-04-0169)

Aadptive control with feedback linearization of hysteresis nonlinear aeroelasticity

Li Daochun, Xiang Jinwu   

  1. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2006-12-30 Online:2008-01-31 Published:2010-09-17

摘要: 首先将含操纵面二元机翼的动态方程以状态空间形式描述,基于Lie导数对其进行了输入/输出局部反馈线性化;然后考虑迟滞非线性模型存在参数不确定性的情况下,利用Lyapunov稳定性理论进行了自适应控制律设计.仿真结果显示:在内动态稳定的情况下,所设计的控制律能够使开环不稳定气动弹性系统受扰后快速地回复到原来的稳定状态,并且在控制面偏转存在限制的情况下仍能实现对非线性颤振的控制.

Abstract: The question of active flutter control of prototypical aeroelastic wing section in subsonic uncompressible flow is investigated. The dynamic equations of a two-dimensional airfoil with control surface are described in state space. Then based on Lie derivative, the partial input/output feedback linearization was obtained. Suppose that there is parametric uncertainty in the hysteresis nonlinear model, Lyapunov function was used to design an adaptive control law. The simulation results show that the unstable aeroelastic system exhibit limit circle oscillation while the closed loop system, including the adaptive control law, become stable. It should be emphasized that the control law can be used only when the internal dynamics is stable. Even if there is a hard constraint on the control input, satisfactory responses can be achieved.

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