有限时间收敛的自适应滑模协同末制导  

Adaptive sliding cooperative terminal guidance with finite-time convergence

作　　者：黄绍洧 都延丽 刘燕斌 王跃萍 刘武 HUANG Shaowei;DU Yanli;LIU Yanbin;WANG Yueping;LIU Wu(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;Xi’an Flight Automatic Control Research Institute,Aviation Industry Corporation of China,LTD.,Xi’an 710076,China)

机构地区：[1]南京航空航天大学航天学院,江苏南京211106 [2]中国航空工业集团公司西安飞行自动控制研究所,陕西西安710076

出　　处：《系统工程与电子技术》2025年第3期961-969,共9页Systems Engineering and Electronics

基　　金：国家自然科学基金(52272369);航空科学基金(20230007052004)资助课题。

摘　　要：针对多高超声速飞行器的协同末制导问题,提出一种有限时间收敛的自适应滑模协同制导方法,能够同时满足终端航迹倾角、航迹方位角及时间协同的要求。分别从俯冲和转弯平面设计有限时间收敛的滑模协同制导律,并设计滑模面自适应参数添加到制导律中。针对运动目标,对飞行器与目标间的相对航迹倾角进行系数补偿,解决打击运动目标时为减小脱靶而牺牲打击角度的问题。仿真结果表明,该协同末制导律可以使各高超声速飞行器同时满足航迹倾角约束、打击时间协同及各自的终端航迹方位角要求,且对于初始状态和气动参数偏差具有鲁棒性。Aiming at the cooperative terminal guidance problem of hypersonic vehicles,a finite-time convergent adaptive sliding mode cooperative guidance method is proposed.This method simultaneously satisfies the requirements of terminal track inclination angle,track azimuth angle,and time coordination.Finite-time convergent sliding mode cooperative guidance laws are designed separately for the dive plane and turning plane,and adaptive parameters of the sliding mode surface are incorporated into the guidance laws.For moving targets,coefficient compensation is applied to the relative track inclination angle between the vehicle and the target to resolve the issue of sacrificing the strike angle to reduce miss distance when targeting moving objects.Simulation results indicate that the cooperative guidance law enables each hypersonic vehicle to simultaneously satisfy the requirements of flight path angle constraints,timing coordination,and their respective terminal track angle,exhibiting robustness against the deviation of initial states and aerodynamic parameters.

关 键 词：多高超声速飞行器 自适应滑模 有限时间收敛 协同末制导 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]