现代防御技术2025，Vol.53Issue(6)：91-100,10.DOI:10.3969/j.issn.1009-086x.2025.06.010
拦截大机动目标的加速导弹滑模末制导律
Sliding Mode Terminal Guidance Law for Accelerating Missiles to Intercept Large Maneuvering Targets
CHEN Tianyu 1TAN Xiangxia1
作者信息
- 1. Beijing Institute of Electronic System Engineering,Beijing 100854,China
- 折叠
摘要
Abstract
For the problem of intercepting a high-speed large maneuvering target with an accelerating missile,it is assumed that the missile has constant axial acceleration and adjusts its acceleration direction by controlling the attack angle.Assuming that the target exhibits a constant lateral maneuver,this paper proposes an accurate time-to-go estimation method.The sliding mode surface is designed so that the missile first corrects the initial heading error and then flies in a straight line to the target.A non-homogeneous disturbance observer is introduced to quickly estimate the acceleration of the target.A super-twisting algorithm is applied to implement the guidance law.The finite-time stability of the proposed guidance law is proved.Through the simulation comparison with the guidance to collision law,it is verified that the proposed guidance law improves the capture area of the missile.It can intercept the target whose maneuvering ability is close to that of the missile when the initial heading error is small.关键词
加速导弹/非齐次干扰观测器/超螺旋滑模/高速大机动目标/捕获域Key words
accelerating missile/non-homogeneous disturbance observer/super-twisting sliding mode/high-speed large maneuvering target/capture area分类
军事科技引用本文复制引用
CHEN Tianyu,TAN Xiangxia..拦截大机动目标的加速导弹滑模末制导律[J].现代防御技术,2025,53(6):91-100,10.
