摘要
主要研究了基于陀螺和星敏感器配置的卫星姿态确定算法。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,对陀螺漂移进行实时补偿。并利用在轨数据,通过matlab数学仿真,验证了高精度滤波算法的有效性。所设计的滤波器能准确估计陀螺漂移,估计误差优于5.56×10-5(o)/s;姿态估计误差优于0.01o,从而有效抑制了姿态测量噪声。
The process of satellite attitude determination algorithm based on gyros and star-sensor scheme is studied in this paper. In order to ensure the high precision of the satellite attitude, the quaternion of star-sensor and extended Kalman filter are used for real-time compensating the gyros bias and misalignment. The availability of high accuracy filter algorithm is demonstrated by Matlab numerical simulation with satellite orbital data. The proposed filter can estimate the gyro drift accurately with the estimating error less than 5.56 ）〈 10 ^-5 °/s and the attitude estimating error less than 0.01°, which means attitude measurement noise is restrained effectively.
出处
《航天器工程》
2011年第2期29-34,共6页
Spacecraft Engineering
关键词
对地观测卫星
陀螺漂移
星敏感器
四元数
姿态确定
卡尔曼滤波
earth observation satellite
gyros bias
star sensor
quaternion
attitude determination
Kalman filter
