基于BiSAR制导的战斗机最优引导律及导弹最优制导律设计  

Design of Optimal Guidance Laws of Fighter and Missile Based on BiS AR Guidance

作　　者：黄伟[1] 徐建城[1] 李俊兵[2] 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：《西北工业大学学报》2016年第3期367-373,共7页Journal of Northwestern Polytechnical University

基　　金：国家自然科学基金(61472441)资助

摘　　要：针对半主动自寻的合成孔径雷达制导导弹发射后,战斗机、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,提出一种基于逆最优控制方法的战斗机引导律和导弹制导律。将成像分辨率对战斗机及导弹运动状态的双边约束,转化为对战斗机目标线角速度的单边约束;将脱靶量转化为对导弹目标线角速度的约束,从而实现导弹运动的自主性;建立含有待定权值系数的性能指标函数,根据所建立的战斗机引导系统和导弹制导系统的动态调节时间确定该系数,逆向得出最优引导律和最优制导律,仿真结果验证了该算法的有效性。To meet the requirements of resolution at the azimuth and miss distance for motion states of Bi-SAR platforms which indicates the fighter aircraft and the semi-active homing SAR-guided missile after launch,guidance laws for the aircraft and missile based on inverse control algorithm are proposed. Two-sided constraints due to resolution for their motion states is converted to one-sided constraint for the aircraft＇s angular velocity of line of sight,and miss distance is considered as only constraint for the missile＇s angular velocity of line of sight to implement its autonomy of motion. Performance index function containing undetermined coefficients is build and the coefficients are calculated according to dynamic tuning time for both guiding systems,and their optimal guidance laws are derived inversely. Simulation results demonstrate the validity of the algorithm.

关 键 词：空对面导弹 双平台合成孔径雷达 传感器 目标 制导律 方位向分辨率 脱靶量 运动方程 约束优化 角速度 闭环控制系统 状态方程 反馈控制 控制器 动态响应 

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]