基于滑模控制的多弹分布式视线协同制导律设计  

Multi-missile Distributed LOS Cooperative Guidance Law Design Based on Sliding Mode Control

作　　者：赵斌[1] 黄晓阳 周军[1] 郭玥 ZHAO Bin;HUANG Xiaoyang;ZHOU Jun;GUO Yue(Northwestern Polytechnical University,Institute of Precision Guidance and Control,Xi’an 710072,Shaanxi,China)

机构地区：[1]西北工业大学精确制导与控制研究所,陕西西安710072

出　　处：《空天防御》2020年第3期16-23,共8页Air & Space Defense

基　　金：国家自然科学基金(61703339);上海航天科技创新基金(SAST2019-004);中央高校基本科研业务费资助项目-学生科技创新类(3102019HTSX006)。

摘　　要：基于多智能体的协同制导通常以质点加速度作为控制输入,这种模型与通常在末制导段进行无动力飞行的战术导弹不相匹配。基于领弹-从弹编队构架,首先建立了以舵偏角为输入的关于弹目二阶视线角的分布式非线性协同制导设计模型;其次,针对运动目标拦截场景,基于滑模控制和干扰观测器设计了带有视线角约束的领弹有限时间制导律;第三,针对从弹提出了一种分布式非连续协同制导律,给出了参数自适应律,并通过Lyapunov理论证明了系统稳定性。数学仿真结果表明本文设计的方法可以使从弹-目标视线角与领弹-目标视线角趋于一致,最终实现对运动目标的精确协同打击。Multi-agent-based cooperative guidance usually uses particle acceleration as a control input.This model is not compatible with tactical missiles that usually perform unpowered flight in the terminal guidance phase.In this paper,under the leader-follower missile formation structure,firstly,a distributed nonlinear cooperative guidance law design model for the second-order line-of-sight angle of the target-missile with rudder deflection angle as input is established;secondly,based on sliding mode control and disturbance observer,a finite-time guidance law of the leader missile with line-of-sight angle constraint for the precise strike of the moving target is designed.Thirdly,a distributed discontinuous cooperative guidance law is proposed for the follower missiles,and the adaptive law of its parameters is given.The system stability is proved by Lyapunov theory.Mathematical simulation results show that the method designed in this paper can achieve the consistency of the follower-target LOS angle and the leader-target LOS angle,and finally achieve a precise and coordinated attack on the moving target.

关 键 词：协同制导 视线角一致性 自适应滑模控制 领弹-从弹制导体制 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]