基于星敏感器/光纤陀螺的卫星定姿算法  

Satellite Attitude Determination Algorithm Based on Star-sensor and FOG

作　　者：杨锋[1] 周宗锡[1] 刘曙光[1] 

机构地区：[1]西北工业大学电子信息学院,陕西西安710072

出　　处：《控制工程》2006年第4期374-376,393,共4页Control Engineering of China

基　　金：陕西省自然科学基金资助项目(N5CS0001)

摘　　要：为了达到卫星三轴姿态确定的精度要求,以某一对地定向的小卫星为研究对象,提出了基于滤波算法的星敏感器和光纤陀螺组合定姿的方案。采用四元数的方法建立卫星姿态确定模型,并采用扩展卡尔曼滤波,对得到的卫星姿态误差和陀螺漂移误差信息进行信息融合和相应的修正。仿真结果表明,即使采用中等精度的陀螺组件,也可以实现高精度定姿;并且验证了星敏感器的测量噪声和滤波周期等因素对定姿精度的影响。A filtering algorithm for high precision attitude determination of a specific satellite is presented based on star-sensors and fiber optic gyroscopes （FOG）. The model of the satellite attitude determination is set up by using quaternion. Extended Kalman filter is used to modify the estimation error of satellite attilude and estimation error of gyroscope drift and information fusion. The simulation result shows that this algorithm can provide high accuracy attitude determination with moderate precision gyroscopes, and that the measurement noise of star-sensor and filtering period may influence the attitude determination accuracy.

关 键 词：姿态确定 星敏感器 光纤陀螺 卡尔曼滤波 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]