考虑自动驾驶仪动态特性的多约束中制导律  

Midcourse guidance law with multiple constraints considering missile's dynamics of autopilot

作　　者：毛柏源 李君龙[1] 张锐[1] MAO Boyuan;LI Junlong;ZHANG Rui(Beijing Institute of Electronic System Engineering, Beijing 100854, China;The 2nd Academy, China Aerospace Science & Industry Corporation Limited, Beijing 100854, China)

机构地区：[1]北京电子工程总体研究所,北京100854 [2]中国航天科工集团第二研究院,北京100854

出　　处：《系统工程与电子技术》2019年第2期382-388,共7页Systems Engineering and Electronics

摘　　要：针对多约束条件下的中末制导交班问题,提出一种考虑自动驾驶仪动态特性的滑模中制导律。首先,建立了考虑自动驾驶仪一阶动态特性的弹目运动模型,根据该模型设计非奇异终端滑模面,并采用自适应滑模趋近律设计有限时间收敛的中制导律。其次,采用扩张状态观测器估计目标机动信息,并将估计值应用于非奇异滑模中制导律中。最后,基于有限时间理论分析了中制导律的有限时间收敛特性。数值仿真结果验证了所提中制导律的鲁棒性强,引起的交班误差小。A sliding mode midcourse guidance law considering the missile’s dynamics of autopilot is proposed for the transition problem from midcourse guidance to terminal guidance with multiple constraints. Firstly , a motion model between missile and target is established on the basis of the first-order missile dynamics. According to this model, a nonsingular terminal sliding mode surface is designed, and the adaptive sliding mode reaching law is used to design a finite time convergent midcourse guidance law. Secondly, the extended state observer is employed to estimate the maneuvering information of the target, and the estimated value is applied to the nonsingular sliding mode midcourse guidance law. Finally, based on the finite time theory, the finite time convergence characteristics of the midcourse guidance law are analyzed. Numerical simulation results show that the proposed midcourse guidance law has strong robustness and small handover error.

关 键 词：中制导律 自动驾驶仪 多约束 滑模控制 有限时间收敛 

分 类 号：V448.232[航空宇航科学与技术—飞行器设计]