变后掠翼导弹中制导律设计  

Midcourse Guidance Law Design of Guide Missile with Variable Sweep Wings

作　　者：赵日[1] 孙瑞胜[1] 胡鹏博[2] 

机构地区：[1]南京理工大学能源与动力工程学院,江苏南京210094 [2]南京理工大学瞬态物理国家重点实验室,江苏南京210094

出　　处：《战术导弹技术》2014年第1期86-90,共5页Tactical Missile Technology

基　　金：国家自然科学基金项目(11176012);航空科学基金项目(20110159001)

摘　　要：研究了可变后掠翼导弹的制导律问题,它在整个导弹设计过程中起着非常重要的作用;针对可变后掠翼导弹外形参数可变的特点,建立了弹道优化数学模型,并针对滑翔段弹道进行了优化设计;提出了一种基于动态虚拟目标点的滑翔中制导律,通过仿真分析验证了其可行性。研究结果可为变后掠翼导弹总体设计提供参考。The midcourse guidance law was designed for missile with variable sweep wings, which played a very important role in the whole process when designing missile. According to variable characteristic of the shape parameters, the model of trajectory optimization was built up for a swing-wing missile. And the glide trajectory was optimized. A midcourse guidance law for glide trajectory was promoted, which de- pends on tracking the motional virtual target. And the feasibility was verified through the simulation anal- ysis. The research results could provide reference to the overall design of guide missile with variable sweep wings.

关 键 词：变后掠翼导弹 弹道优化 中制导律 粒子群算法 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]