基于过重力补偿比例导引律的末端落角控制  

Terminal Impact Angle Control Based on Proportional Navigation Guidance Law with Over-Gravity Compensation

作　　者：曹晶[1] 付主木[1,2] 

机构地区：[1]河南科技大学电子信息工程学院,河南洛阳471023 [2]山东大学控制科学与工程学院,济南250061

出　　处：《火力与指挥控制》2014年第2期46-48,51,共4页Fire Control & Command Control

基　　金：国家航空科学基金资助项目(20110142003)

摘　　要：为了保证导弹对目标大角度攻击的效果,设计了一种带有过重力补偿项的比例导引制导律。在二维平面内建立弹-目相对运动数学模型,在传统的比例导引律基础上,增加了过重力补偿项并将其作为补偿指令引入制导回路,从而建立了仿真模型,分析了投放条件和过重力补偿系数对制导系统的影响。仿真结果表明,此制导律可实现近似-90°的末端落角,达到期望的性能要求,证明该方法的正确性和有效性。A kind of proportional navigation guidance law with over-gravity Compensation is designed to ensure impact angle of missile. Two-dimensional motion model for missile and target is established, the over-gravity compensation is introduced to the guidance loop, as an additional command. The model of guidance law with the over-gravity compensation is established. The effect of initial conditions and over-gravity compensation are analyzed. Finally ,the simulation results indicate that this guidance law can get nearly negative ninety degree impact angle and show the validity of the proposed method.

关 键 词：比例导引律 过重力补偿 落角 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]