摘要
以Kalman滤波为基础,通过将捷联惯导系统和星敏感器所测得的飞行器相关姿态信息进行数据融合,估计出组合导航系统的误差状态量,进而修正捷联惯导系统的位置、速度和姿态角。详细推导了捷联惯导与星敏感器组合导航的算法,并通过对仿真结果的分析证实了该方案的可行性和算法的有效性。
The Strap-down inertial navigation system and Charge Coupled Device （CCD） can provide corresponding attitude＇s data. Fusing these data, integrated navigation system＇s error state value can be estimated and the aircraft＇s position, velocity and attitude＇s angle can be corrected base on Kalman Filtering. The algorithm of integrated strap-down inertial navigation system/star sensor integrated navigation system is educed in detail. The results of computer simulation show that the proposed system is feasible and the algorithm is effective.
出处
《中国空间科学技术》
EI
CSCD
北大核心
2005年第6期19-25,29,共8页
Chinese Space Science and Technology
关键词
卡尔曼滤波
捷联式惯性导航
星敏感器
组合式导航
仿真
Kalman fihering Strapdown inertial navigation Star sensor Combined navigation Emulation
