摘要
为保证卫星姿态确定的高精度,利用星敏感器提供的姿态四元数,结合扩展卡尔曼滤波(EKF)对陀螺漂移和安装误差进行实时补偿。建立了滤波器数学模型,并通过数学仿真获得了算法的理论精度,同时分析了星敏感器安装误差对姿态确定的影响。
Aiming at determining the satellite attitude precisely, the gyros bias and misalignment were compensated in time by using the quaternion of star-sensor and extended Kalman filter. The related module of the filter was derived. The theoretic accuracy of the algorithm was acquired from the numerical simulation. The effects of the star-sensor misalignment on attitude determination were analyzed at last.
出处
《上海航天》
北大核心
2005年第4期1-5,59,共6页
Aerospace Shanghai
关键词
姿态确定
四元数
陀螺漂移
扩展卡尔曼滤波
Attitude determination
Quaternion
Gyros bias
Extended Kalman filter
