落角约束最优制导律在空地导弹上的应用  

Optimal Guidance Law with Terminal Angular Constraint Use in Air-to-ground Missile

作　　者：陈韵[1] 常燕 苗昊春 严宪军 CHEN Yun;CHANG Yan;MIAO Haochun;YAN Xianjun(School of Astronautics,Northwestern Polytechnical University,Xi'an 710072,China;Rocket Force University of Engineering,Xi* an 710025,China;Xi'an Modern Control Technology Research Institute,Xi'an 710065,China)

机构地区：[1]西北工业大学航天学院,西安710072 [2]火箭军工程大学,西安710025 [3]西安现代控制技术研究所,西安710065

出　　处：《弹箭与制导学报》2018年第5期141-144,共4页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：针对某直升机载空地导弹对终端攻击角度有多种需求,基于飞行力学原理和最优控制理论,研究一种最优制导律。推导得到的落角约束最优制导律是在传统比例导引制导律的基础上,增加与弹目相对关系及期望落角相关的修正量,能同时满足命中精度及命中角度的要求,具有形式简单,需用信息可获取,易于工程实现的特点。仿真结果表明,该制导律既能够满足高精度制导的要求,同时可实现0°～-45°的任意末端攻击落角。According to the requirement of helicopter-borne air-to-ground missiles with terminal attack angle constraint,a kind of optimal guidance law is presented based on the theory of flight dynamics and optimal control.The traditional proportional navigation guidance law is the basics of the angle constraint optimal guidance law studied in this paper and the additional item is related to the expected attack angle,so the optimal guidance law satisfies both interception and multiple impact angles,concurrently it is simple and convenient to be realized in engineering.The simulation results show that the guidance law is satisfied not only the requirements of high-precision guidance,but also the ideal impact angle between 0°to -45°.

关 键 词：直升机载空地导弹 最优制导律 落角约束 

分 类 号：TJ765.2[兵器科学与技术—武器系统与运用工程]