摘要
提出了巡航导弹卫星/惯性组合导航系统的组合结构,分析并建立了组合导航系统的误差模型,采用了卡尔曼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对巡航导弹的惯性导航系统进行辅助将大幅度提高巡航导弹的导航精度,具有重要的实际意义。
The structure of cruise missile GPS/INS integrate navigation system has been proposed, and the error model of integrate navigation system has been analyzed and modeled. The status of navigation system is estimated by kalman filters and the simulation calculation has been progressed. The result of simulation indicates inertial navigation aided with satellite can substantially improve the navigation precision and has profound practice significance.
出处
《探测与控制学报》
CSCD
北大核心
2007年第B08期31-34,共4页
Journal of Detection & Control
关键词
组合导航
惯性导航系统
卫星导航系统
卡尔曼滤波
integrated navigation
inertial navigation
satellite navigation
Kalman filtering
