基于反演滑模控制的导弹制导控制一体化设计

系统工程与电子技术

基于反演滑模控制的导弹制导控制一体化设计

齐辉1, 张泽1, 韩鹏鑫2, 许江涛1, 张德伟1

(1. 哈尔滨工程大学航天工程系, 黑龙江哈尔滨 150001;
2. 中国运载火箭技术研究院研究发展中心, 北京 100076)

出版日期:2016-02-24 发布日期:2010-01-03

Integrated design of missile guidance and control based onbackstepping and sliding mode control

QI Hui1, ZHANG Ze1, HAN Pengxin2, XU Jiangtao1, ZHANG Dewei1

(1. Department of Aerospace Engineering, Harbin Engineering University, Harbin 150001, China;
2. China Academy of Launch Vehicle Technology R&D Center, Beijing 100076, China)

Online:2016-02-24 Published:2010-01-03

摘要/Abstract

摘要：

针对传统制导和控制分开设计在拦截高速机动目标时的不足,给出了一种反演滑模一体化制导控制算法。首先利用微分几何理论,建立了一体化制导控制模型;然后根据平行接近原理,基于滑模控制和反演法,设计了一种反演滑模控制的导弹制导控制一体化算法;最后基于Lyapunov理论证明了系统的稳定性。数值仿真结果表明,所给出的一体化制导控制方法能够克服未建模的不确定性和目标机动干扰,具有较强的鲁棒性。

Abstract:

Aiming at the defects that the traditional design for guidance and control is separated when intercepting highspeed maneuvering targets, an integrated algorithm for missile guidance and control based on backstepping and sliding is presented. Firstly, the integrated mode of guidance and control is established based on the differential geometry theory. Then, according to the principle of parallel approach, an integrated algorithm of guidance and control is proposed by using the method of backstepping and the sliding mode control (SMC) technique. Finally, system stability has been proved based on the Lyapunov theory. The simulation results demonstrate that the design for the integrated method of guidance and control can overcome the interference of unmodeled dynamics uncertainty and target maneuver, which has strong robustness.

齐辉1, 张泽1, 韩鹏鑫2, 许江涛1, 张德伟1. 基于反演滑模控制的导弹制导控制一体化设计[J]. 系统工程与电子技术.

QI Hui1, ZHANG Ze1, HAN Pengxin2, XU Jiangtao1, ZHANG Dewei1. Integrated design of missile guidance and control based onbackstepping and sliding mode control[J]. Systems Engineering and Electronics.