基于SINS/星敏感器的组合导航模式  

Integrated navigation mode based on the SINS/star sensor

作　　者：王鹏[1] 张迎春[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：《东南大学学报（自然科学版）》2005年第A02期84-89,共6页Journal of Southeast University：Natural Science Edition

基　　金：国家重点基础研究发展计划(973计划)资助项目(51312)

摘　　要：针对利用捷联惯导系统导航的不足,提出了一种基于捷联惯导系统/星敏感器的新组合导航模式,来提高飞行器导航的精度和速度.利用星敏感器得到恒星星光矢量在星敏感器CCD光敏面上的星像点及其在导航星库中对应的坐标值,然后分别进行坐标变换得到星光矢量在数学平台坐标系和地理坐标系中的坐标角度值.以Kalman滤波为基础,将所得到的星光坐标角度值和姿态角速度进行数据融合,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、速度和姿态角参数.详细推导了SINS/星光的组合导航算法,并通过仿真证实了该方案可提高导航系统的精度和速度,有较好的容错性和环境适应性,具有实际使用价值.Since the shortcomings of navigation based on strap-down inertial navigation system（SINS）, a new integrated mode of navigation is presented. The new mode is based on the SINS/Star sensor to improve the precision and speed of navigation system on the aircraft. Firstly, based on the projection of starlight in charge coupled device （CCD） and the coordinate of starlight in the navigation star storeroom, the expressions of starlight vector in the math platform reference frame and the geographical reference frame are got separately through the coordinate transformation. Then the starlight vector and the rate of attitude are fused, using the Kalman filter, to estimate the error estimation of integrated navigation system which can be used to correct the aircraft＇s position, velocity and attitude. The whole algorithm of integrated navigation using SINS/Star sensor is educed in details here, and the numerical results show that the new method is effective to improve the precision and calculation speed of autonomous navigation system and to provide with better fault tolerance ability and adaptability.

关 键 词：组合导航 星敏感器 星光矢量 卡尔曼滤波 

分 类 号：V249.3[航空宇航科学与技术—飞行器设计]