捷联惯导与星敏感器组合导航算法研究  

Study of the Strap-down Inertial Navigation System/Star Sensor Integrated Navigation System Algorithms

作　　者：王鹏[1] 张迎春[1] 强文义[1] 张荣林[1] 

机构地区：[1]哈尔滨工业大学卫星技术研究所,哈尔滨150080

出　　处：《中国空间科学技术》2005年第6期19-25,29,共8页Chinese Space Science and Technology

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.

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 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计] TN966[电子电信—信号与信息处理]