航空学报 > 2010, Vol. 31 Issue (10): 2018-2025

一种新型三维制导律设计的非线性方法

彭双春1, 潘亮1, 韩大鹏2, 孙未蒙3, 沈林成1   

  1. 1. 国防科学技术大学 机电工程与自动化学院 2. 国防科学技术大学 航天与材料工程学院 3. 中国人民解放军 92854部队
  • 收稿日期:2009-10-27 修回日期:2010-03-27 出版日期:2010-10-25 发布日期:2010-10-25
  • 通讯作者: 沈林成

A New 3D Guidance Law Based on Nonlinear Method

Peng Shuangchun1, Pan Liang1, Han Dapeng2, Sun Weimeng3, Shen Lincheng1   

  1. 1. College of Mechatronic Engineering and Automation, National University of Defense Technology 2. College of Aerospace and Material Engineering, National University of Defense Technology 3. No.92854 Unit, People’s Liberation Army of China
  • Received:2009-10-27 Revised:2010-03-27 Online:2010-10-25 Published:2010-10-25
  • Contact: Shen Lincheng

摘要: 结合微分几何和李群方法的优点,设计了一种非解耦的新型三维(3D)制导律。首先,基于微分几何理论,得到了导弹运动的微分几何描述方程,无需估计剩余飞行时间。然后,通过李群旋量描述,建立了视线方位角与视线角速率之间的联系。最后,在以上工作的基础上,利用李雅普诺夫稳定理论,针对导弹制导的无终端约束和有终端约束情况分别进行了相应制导律设计。该制导律不需要估算剩余飞行时间,并且能够满足终端角度约束的要求。仿真结果表明:所设计制导律能够适应于高速、大机动倾斜转弯(BTT)导弹精确制导。

关键词: 导弹, 三维制导律, 微分几何控制, 李群控制, 倾斜转弯

Abstract: This article proposes a non-decoupling three dimensional (3D) robust guidance law by combining the advantages of the differential geometry control and Lie-group control methods. First, a differential geometrical description equation is obtained based on differential geometry theory without the need to estimate the parameter of available time-to-go. Then, the relation between azimuth angle and its change rate is established through spinor description. Finally, corresponding to no ending constraints and ending constraints, guidance laws are designed respectively by using the Lyapunov stability theory, which can satisfy the restriction of ending constraints with no requirement for the estimation of time-to-go. Simulation results demonstrate that the proposed guidance law can be applied to the guidance of high-speed maneuvering bank-to-turn (BTT) missiles.

Key words: missiles, 3D guidance law, differential geometry control, Lie-group control, bank-to-turn

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