高超声速飞行器时间协同预测校正鲁棒制导  

Time-cooperative Predictor-corrector Robust Guidance for Hypersonic Vehicles

作　　者：魏昀鹏 都延丽 王文凯 刘燕斌 WEI Yunpeng;DU Yani;WANG Wenkai;LIU Yanbin(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China)

机构地区：[1]南京航空航天大学航天学院,南京211106

出　　处：《宇航学报》2024年第3期421-432,共12页Journal of Astronautics

基　　金：国家自然科学基金(52272369);南京航空航天大学研究生科研与实践创新计划项目(xcxjh20221505)。

摘　　要：针对存在参数不确定性的多高超声速飞行器滑翔段协同制导问题,提出了一种时间协同的预测校正鲁棒制导方法。首先,基于剩余飞行时间的动态航向角误差走廊实现了横向协同制导,为调整飞行时间提供了有利条件;设计了随协同飞行任务进程变化的权值函数,将剩余飞行时间引入纵向制导的预测校正过程中,确保协同飞行任务落点和协同时间的精度。其次,基于改进无迹卡尔曼滤波估计的方法对气动参数的不确定性进行估计,通过对剩余飞行时间与剩余能量的综合分析,修正了航向角误差走廊和标称迎角剖面,以提高协同制导系统的鲁棒性能。最后,分别在标称环境和参数不确定环境下开展了仿真实验,其结果证明了该协同制导方法的可行性和鲁棒性。A time-cooperative predictor-corrector robust guidance method is presented for glide phase cooperative guidance of multiple hypersonic vehicles with uncertain parameters.Firstly,a lateral cooperative guidance law of dynamic heading angle error corridor based on remaining flight time is developed to provide favorable conditions for adjusting flight time.A weight function that adapts to the progress of collaborative flight tasks is designed and the remaining flight time is introduced into the predictor-corrector process of longitudinal guidance,which ensures the precision of collaborative flight mission landing points and collaborative time.Then,the uncertain parameters are estimated based on an improved unscented Kalman filter estimation method,and the heading angle error corridor and nominal angle of attack profile are corrected by comprehensive analysis of the remaining flight time and energy,in order to improve the robustness of cooperative guidance system.Finally,simulation tests are carried out in nominal and uncertain conditions,showing that the proposed cooperative robust guidance method possesses feasibility and robustness.

关 键 词：高超声速飞行器 预测校正 时间协同制导 鲁棒制导 无迹卡尔曼滤波 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]