宇航学报

宇航学报 ›› 2011, Vol. 32 ›› Issue (4): 727-733.doi: 10.3873/j.issn.1000-1328.2011.04.004

• 制导、导航与控制 • 上一篇    下一篇

基于连续有限时间控制技术的导引律设计

丁世宏1,2, 李世华1, 罗生3   

  1. 1．东南大学自动化学院, 南京  210096；2. 江苏大学电气信息工程学院，镇江  212013；
    3. 中国空空导弹研究院，洛阳  471009
  • 收稿日期:2010-03-02 修回日期:2010-10-15 出版日期:2011-04-15 发布日期:2011-04-26
  • 基金资助:
    教育部博士点基金(20090092110022);-航空科学基金项目(20090112002)

Guidance Law Design Based on Continuous Finite\|Time Control Technique

DING Shi-hong1,2, LI Shi-hua1, LUO Sheng3   

  1. 1. School of Automation, Southeast University, Nanjing 210096, China;
    2. School of Electric and Information Engineering, Jiangsu University, Zhenjiang 212013, China;
    3. China Airborne Missile Academy, Luoyang  471009, China
  • Received:2010-03-02 Revised:2010-10-15 Online:2011-04-15 Published:2011-04-26

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摘要： 针对导弹末段制导问题，提出了一种基于连续有限时间控制技术的导引设计方案。首先，利用有限时间Lyapunov稳定性理论，设计出一种连续有限时间导引律。该导引律使得：当目标不作机动时，视线角速率会在有限时间内收敛到零；当目标机动时，视线角速率会收敛到原点附近的一个小邻域内。其次，考虑到有限时间控制系统在离原点较远处状态趋近平衡点速度慢的特点，在导引律中引入了线性状态反馈项来改善闭环系统的收敛性能。仿真结果表明了该方法的有效性。

关键词: 导引律, 导弹, 有限时间控制, 有限时间稳定性 

Abstract: For missile terminal guidance problem, a finite\|time guidance scheme is developed by using finite\|time control technique. First, a continuous finite\|time guidance law is designed based on the finite\|time Lyapunov stability theory. The guidance law makes the line of sight (LOS) angular rate converge to zero in finite time when the target does not maneuver. If the target performs the maneuver, the LOS angular rate will be stabilized to a small neighborhood of the origin. Then, considering that states of finite\|time control systems usually approach an equilibrium point in a slow rate when states are far from the origin, to this end, a linear state\|feedback term is introduced to the controller to improve the convergence performance of the closed loop system. Simulation results are provided to demonstrate effectiveness of the method.

Key words: Guidance law, Missile, Finite-time control, Finite-time stability

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