弹载SAR末制导段轨迹控制算法  

Trajectory control arithmetic of missile-borne SAR terminal guidance

作　　者：黄伟[1] 徐建城[1] 吴华兴[2] 

机构地区：[1]西北工业大学电子信息学院,陕西西安710072 [2]空军工程大学航空航天工程学院,陕西西安710038

出　　处：《系统工程与电子技术》2016年第9期2115-2121,共7页Systems Engineering and Electronics

基　　金：国家自然科学基金(61472441)资助课题

摘　　要：针对机载合成孔径雷达(synthetic aperture radar,SAR)制导空地导弹的末制导过程,导弹的运动状态如何同时满足成像分辨率和脱靶量要求的问题,提出一种新的轨迹控制算法。通过分析SAR末制导过程,以及弹目空间几何与成像分辨率的关系,将成像分辨率要求转化为对导弹前置角的约束,将脱靶量要求转化为对导弹目标线角速度的约束。基于逆最优控制,建立含有待定系数的性能指标函数,并根据给定的系统动态性能指标确定该系数,从而得到具有时变权值系数的最优控制量,通过权值系数的调节作用以满足不同制导模式的指标要求。仿真实验证明了该算法的有效性。For the process of airborne synthetic aperture radar （S A R ） missile terminal guidance, a new trajectorycontrol arithmetic is proposed to meet the requirements of imaging resolution and the missile miss distancefor motion states of the missile. By analyzing the SA R terminal guiding process and the relation betweenmissile-target space geometry and imaging resolution, the need for imaging resolution is converted to constraintsfor motion states of the missile, and the requirement of miss distance is converted to constraints for lead angle ofthe missile. Based on inverse optimal control, performance index function containing undetermined coefficientsis build and the coefficients is calculated on the basis of dynamic performance in the control system, then optimalcontrol variable is calculated with time-variant weight coefficients which can be tuned to meet the index requirementfor different guidance modes. Simulation results demonstrate the validity of the arithmetic.

关 键 词：弹载合成孔径雷达 末制导 轨迹控制 成像分辨率 脱靶量 

分 类 号：V249[航空宇航科学与技术—飞行器设计] TJ765.3[兵器科学与技术—武器系统与运用工程]