国防科技大学学报Issue(1)：95-100,6.DOI:10.11887/j.cn.201501016
动能拦截器姿控固体小火箭点火算法设计
Ignition algorithm for attitude control solid-propellant nozzles in kinetic interceptor
李广华 1张洪波 1汤国建1
作者信息
- 1. 国防科技大学 航天科学与工程学院，湖南 长沙 410073
- 折叠
摘要
Abstract
Using solid-propellant nozzles is one of the best schemes for kinetic interceptor to realize the fast response and high precision of attitude control.A mixed searching algorithm for ignition combination was presented for a novel attitude control solid-propellant nozzle in kinetic interceptor.Firstly,the configuration of solid-propellant nozzles was described and spin requirements of the kinetic interceptor were analyzed.Then the mixed searching algorithm was designed by a combination of sorting method and interval searching method.Sorting method is selected when the number of available nozzles is small and interval searching method is chosen on the contrary.Results of instruction torque approximation simulation and attitude control numerical simulation suggest that the algorithm can track the instruction torque effectively and achieve attitude tracking quickly and with a high precision.关键词
动能拦截器/固体小火箭/目标排序法/区间搜索法/混合搜索算法Key words
kinetic interceptor/solid-propellant nozzles/sorting method/interval searching method/mixed searching algorithm分类
航空航天引用本文复制引用
李广华,张洪波,汤国建..动能拦截器姿控固体小火箭点火算法设计[J].国防科技大学学报,2015,(1):95-100,6.
