宇航学报

宇航学报 ›› 2019, Vol. 40 ›› Issue (1): 51-60.doi: 10.3873/j.issn.1000-1328.2019.01.006

• 制导、导航、控制与电子 • 上一篇    下一篇

拦截大气层内机动目标的自适应积分滑模制导律

黄景帅，张洪波，汤国建，包为民   

  1. 1. 国防科技大学空天科学学院，长沙 410073；2. 中国航天科技集团有限公司，北京 100048
  • 收稿日期:2018-03-09 修回日期:2018-05-29 出版日期:2019-01-15 发布日期:2019-01-25
  • 基金资助:

    航天科学技术基金(2017HTGF07)

Adaptive Integral Sliding Mode Guidance Law for Intercepting Endo Atmospheric Maneuvering Targets

HUANG Jing shuai, ZHANG Hong bo, TANG Guo jian, BAO Wei min   

  1. 1. College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China; 2. China Aerospace Science and Technology Corporation, Beijing 100048, China
  • Received:2018-03-09 Revised:2018-05-29 Online:2019-01-15 Published:2019-01-25

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摘要：

针对大气层内机动目标拦截的末制导问题，提出了一种自适应积分滑模制导律。基于抑制弹目视线旋转的原则，设计了一种视线转率收敛速率可调的跟踪剖面，选取跟踪误差与其积分为状态变量，采用状态有限时间收敛的积分滑模面与快速趋近律推导得到了积分滑模制导律。为了处理未知的目标机动项，提出了一种自适应算法，对目标机动项上界的平方进行估计，构成了自适应积分滑模制导律，并证明了其有限时间收敛的特性，给出了各状态变量的收敛域。最后，将制导律转换成适用于大气层内拦截的形式。仿真结果表明，所提制导律能够精确拦截机动目标，剖面跟踪误差收敛速度快，过载分布均匀，能量消耗少，并具有良好的噪声特性，易于工程实现。

关键词: 导弹制导, 机动目标, 积分滑模面, 自适应算法, 有限时间收敛

Abstract:

In terms of the terminal guidance of intercepting the endoatmospheric maneuvering targets, an adaptive integral sliding-mode guidance law is presented. Based on the principle of suppressing the rotation of the line of sight from a missile to a target, a tracking profile is designed where the convergence rate of the line of sight can be regulated. The tracking error and its integral are selected as the state variables. An integral sliding-mode surface of the states converging to zero in finite time and a rapid reaching law are used to derive an integral sliding-mode guidance law. To deal with an unknown target maneuver, an adaptive algorithm is proposed to estimate the square of the upper bound of the target maneuver, and then the adaptive integral sliding-mode guidance law is constructed. The finite-time convergence characteristic of the law is proven, and the convergence regions are given of the state variables.Finally, the guldance law is converted into the corresponding form suitable for the endoatmosphenc interception. The simulation results indicate that the proposed guidance law can precisely intercept the maneuvering targets and the convergence rate is rapid of the tracking error. The overload distribution is reasonable, and less energy is consumed. Furthermore, the law possesses good profile noise characteristics and is easy to be implemented in practice.

Key words: Missile guidance, Maneuvering target, Integral sliding-mode surface, Adaptive algorithm, Finite-time convergence

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