基于时间权函数的落角约束导引律中剩余时间的估计方法  

Time-to-go Estimation for Time-to-go Weighted Optimal Guidance with Impact Angle Constraints

作　　者：梁勇 张友安[2] 赵贺伟 LIANG Yong;ZHANG You-an;ZHAO He-wei(Coast Defense Force College,Naval Aviation University,Yantai 264001,China;Department of Electrical and Electronic Engineering,Yantai Nanshan University,Yantai 265713,China)

机构地区：[1]海军航空大学岸防兵学院,烟台264001 [2]烟台南山学院电气与电子工程系,烟台265713

出　　处：《导航定位与授时》2020年第4期96-101,共6页Navigation Positioning and Timing

基　　金：国家自然科学基金(61273058)。

摘　　要：带导弹落角约束的导引律求解需要已知导弹飞行剩余时间。针对弯曲弹道,一般的剩余时间估计方法精度较低,在假设导弹速度一定的前提下,采用n阶多项式函数近似表示剩余路径,给出了一种基于近似闭环轨迹的实用剩余时间估计方法。仿真结果表明,剩余时间估计精度平均提高了13倍以上,且计算量可以满足实时性要求。The missile time-to-go is needed to solve the guidance law with the impact angle constraint.Because of the curved trajectory,the accuracy of the general time-to-go estimation is low.To solve the problem,a simple time-to-go estimation based on approximate closed-loop trajectory is proposed,in which the remaining path is approximately described by n-order polynomial func-tion under the assumption of a certain missile speed.The simulation results show that the time-to-go estimation accuracy is increased by more than 13 times on average and the amount of computation can meet the real-time requirement.

关 键 词：时间权函数 落角约束 导引律 剩余时间估计 

分 类 号：V448.13[航空宇航科学与技术—飞行器设计]