捷联惯导/星敏感器组合导航技术研究  

Strapdown Inertial Navigation System/Star Sensor Integrated Navigation System Technique

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150001

出　　处：《航天控制》2005年第5期31-36,共6页Aerospace Control

基　　金：国家安全重大基础研究项目(973)

摘　　要：针对在捷联惯导系统中陀螺的误差存在随着时间积累而逐渐增大的缺点,提出了捷联惯导系统+星敏感器的组合导航方案,并进行了仿真及结果分析。以Kalman滤波为基础,通过将捷联惯导系统和CCD光学传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+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。To correct the gyros drift errors that increase with time in the strapdown inertial navigation system, a scheme of integrated strapdown inertial navigation system/star sensor is proposed and the simulation results are given. The strapdown inertial navigation system and charge coupled device （CCD） can provide corresponding attitude data. Fusing-these data can estimate the error state value of integrated navigation system and correct the position of aircraft, velocity and attitude angle based on Kalman filtering. The algorithm of integrated strapdown inertial navigation system/star sensor integrated navigation system is educed. Simulation results show that the proposed system is feasible and the algorithm is effective.

关 键 词：捷联惯导系统 星敏感器 组合导航 卡尔曼滤波 

分 类 号：V249.3[航空宇航科学与技术—飞行器设计]