控制量权重可变的主动段最优中制导律  

Active Section Optimal Midcourse Guidance Law with Controlled Amount Variable Weights

作　　者：马自茹 魏明英[1] 李运迁[1] MA Zi-ru;WEI Ming-ying;LI Yun-qian(Beijing Institute of Electronic Engineering,Beijing 100854,China;The Second Research Academy of CASIC,Beijing 100854,China;Air and Space Defense Innovation Center,Beijing 100854,China)

机构地区：[1]北京电子工程总体研究所,北京100854 [2]中国航天科工集团有限公司第二研究院,北京100854 [3]空天防御创新中心,北京100854

出　　处：《现代防御技术》2018年第6期44-50,共7页Modern Defence Technology

摘　　要：在末段高层拦截弹的主动段中制导中,考虑主动段飞行中导弹的速度的变化,满足末速度的角度约束,同时要求使控制量尽可能小,为了能够实现这些约束,在指标函数中,采用时变的控制量权重系数,利用极小值原理,伪控制量的办法,得到了一种最优中制导律。仿真结果表明,这种指标函数中加入可变控制量权重的办法,在保证精度的同时,可以有效地控制控制量的大小。Considering the change of the velocity of missile in the active section flight in the guidance of the active section of the terminal high altitude interceptor,the angle constraint of the final velocity was required to meet and the control amount was required as small as possible.To realize these constraints, in the index function,an optimal guidance law by adopting the time varying control weight coefficient was obtained,using the minimum principle,as well as pseudo control method.The simulation results showed that the method of adding variable weight in this index function can control the size of the control while guaranteeing the precision.

关 键 词：末段高层 角度约束 主动段 可变权重 最优控制 极小值原理 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程] TP391.9[自动化与计算机技术—计算机应用技术]