基于弹道制导一体化的巡航飞行器末制导方案研究  

A Method of Rectification for Star Map Distortion Based on Improved Genetic Algorithm

作　　者：穆育强[1,2] 王丹晔 孙晓松[1] 黄兴李[1] 陈新民[1] 

机构地区：[1]北京临近空间飞行器系统工程研究所,北京100076 [2]空间物理重点实验室,北京100076 [3]北京航天自动控制研究所,北京100854

出　　处：《航天控制》2012年第2期7-10,21,共5页Aerospace Control

摘　　要：以巡航飞行器为对象,重点研究高精度末制导方案。考虑到超声速飞行器制导设计与弹道设计及单机指标确定之间的紧密耦合关系,进行弹道制导一体化设计,提出弹道设计的关键点要求及导引头开机方案和要求,并通过控制系统六自由度仿真试验验证方案设计的有效性,为后续工程研制奠定了理论基础。The design of high precision terminal guidance system for cruise vehicle is focused in this paper. Regarding the close coupling relationship between guidance and instrument index, the integrating of trajectory and guidance is implemented, and requirements of the key point of trajectory design and seeker-opened plan are specified. Finally, the design is validated by the six-degree-of-freedom simulations of control system, which lays a academic foundation for the project development.

关 键 词：末制导 弹道 方案 巡航飞行器 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]