一种适用于靶弹落角约束的偏置比例导引律  

A biased proportional navigation guidance law applicable for impact angle control of target missile

作　　者：王广帅[1] 洪功名 秦科科 安博纳 李娜[1] Wang Guangshuai;Hong Gongming;Qin Keke;An Bona;Li Na(Beijing Electro-mechanical Engineering Institute,Beijing 100074,China)

机构地区：[1]北京机电工程研究所,北京100074

出　　处：《战术导弹技术》2023年第2期75-80,87,共7页Tactical Missile Technology

摘　　要：针对比例导引等传统制导律在实现靶弹大落角约束时存在的各种局限性,利用已有研究成果,将一种偏置比例导引律成功应用于靶弹的大落角约束问题,并结合靶弹的研制和使用特点,提出了制导律的工程化方案。根据弹目相对运动学模型,采用理论推导方法,得出了靶弹弹道期望落角与需用偏置量之间的函数关系,表明了制导律的可行性。采用弹道仿真的方法,研究了制导律的制导性能。结果表明,导引律在最大需用过载、制导精度、落角精度等关键制导性能方面符合靶弹要求,适用于靶弹的大落角约束问题。Considering that the proportional navigation guidance and other classic guidance laws are unavailable for precise impact angle control of target missile,the existing biased proportional navigation guidance is successfully applied to this challenge.According to the use characteristics of target missile,the engineering scheme of this guidance law is also proposed.Based on established missile-target relative motion model,the feasibility of this guidance law is proved by the function relationship between desired impact angle and demand bias integral quantity with mathematical derivation.The performance of the proposed guidance law is studied by trajectory simulation.Simulation results show that the biased proportional navigation guidance law is suitable for precise impact angle control of target missile in the key performance indexes,such as maximum demand acceleration,impact angle control precision and guidance precision.

关 键 词：靶弹 落角约束 偏置比例导引 弹目相对运动学 制导精度 制导律 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]