多导弹协同制导律综述  

Summary of guidance law based on cooperative attack of multi-missile method

作　　者：王建青[1] 李帆[1] 赵建辉[1] 万聪梅[1] 

机构地区：[1]北京航空航天大学仪器科学与光电工程学院,北京100191

出　　处：《飞行力学》2011年第4期6-10,共5页Flight Dynamics

摘　　要：根据制导约束条件的不同,将多导弹协同制导律划分为具有弹着时间、终端角度、终端速度分别约束,以及弹着时间与终端角度同时约束四类。系统地论述了各类导引律的方法和特点,总结和分析了其优缺点,并对其发展趋势进行了探讨,可为多导弹协同制导律的优化设计提供参考。According to the constraints in different cases for missile guidance, the multi-missile cooperation guidance law is divided into four typical kinds, which base on the different constraint conditions, such as the impact time, the terminal angle, the terminal speed, and the impact time together with the terminal angle. It is expected to specify the methods and characteristic of each guidance law and summarize their advantage and disadvantage systematically. Then, the development trends are discussed which also provide a good reference for optimizing and designing new guidance law for the multi-missile cooperative model.

关 键 词：多导弹协同 制导律 弹着时间 终端角度 终端速度 

分 类 号：TJ765.1[兵器科学与技术—武器系统与运用工程]