摘要
提出了弹道导弹惯性 /卫星 /天文组合导航系统的方案与组合结构 ,分析并建立了组合导航系统的误差模型 ,采用了联邦滤波器进行组合导航系统导航状态的最优估计 ,并进行了组合导航系统的仿真计算。仿真结果表明采用卫星导航定位系统和天文导航系统对弹道的惯性导航系统进行辅助将大幅度提高弹道导弹的导航精度 。
The structure and scheme of ballistic missile INS/GNSS/CNS integrated navigation system has been proposed, and the error model of integrated navigation system has been analyzed and modeled. The status of navigation system has been estimated with federal filter and the simulation calculation has been progressed. The result of simulation indicates inertial navigation aided with satellite and celestial navigations can substantially improve the navigation precision and has profound practice significance.
出处
《导弹与航天运载技术》
北大核心
2004年第2期11-15,共5页
Missiles and Space Vehicles
