拦截大机动目标导弹制导优化设计  

Design of Guidance Law for Intercept Missile with Trajectory Control Engine Intercepting Strongly Maneuvering Target

作　　者：冯令兵 陈瑞华[2] 雷泷杰[2] 

机构地区：[1]中国兵器工业第208研究所,北京102202 [2]西安机电信息技术研究所,陕西西安710065

出　　处：《计算机仿真》2016年第6期32-35,共4页Computer Simulation

摘　　要：在采用轨控式直接侧向力控制技术的拦截弹的研究中,由于拦截大机动目标时传统导引律很难使得导弹视线角速率快速收敛,容易造成脱靶。在轨控式直接侧向力控制技术的拦截弹拦截大机动目标导弹制导律设计的基础上,提出了一种合理的优化设计方案。利用轨控式拦截弹的工作特点,引入目标运动加速度以及轨控发动机延时影响因子,设计了一种改进的变结构导引规律,并通过仿真进行了验证。仿真结果表明了拦截大机动目标的轨控式拦截弹导引律设计的合理性。A design scheme of the guidance law is presented for the interceptor to intercept the maneuvering tar- get with trajectory control direct lateral force control technology. The working mode and characteristics of the inter- ceptor are introduced. Based on the theory of variable structure control, the plane interception guidance law is de- signed. By using the characteristics of the interceptor, considering the target acceleration and trajectory control en- gine delay impact factors, the design of the improved guidance law is completed. The simulation results show that the rationality of the guidance law.

关 键 词：轨控式直接侧向力控制技术 变结构控制 导引律 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]