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| 基于陀螺和星敏感器的卫星姿态确定算法 | |
| 引用本文： | 边志强,程卫强,薛孝补,于永江. 基于陀螺和星敏感器的卫星姿态确定算法[J]. 航天器工程, 2011, 0(2): 29-34 |
| 作者姓名： | 边志强 程卫强 薛孝补 于永江 |
| 作者单位： | 上海卫星工程研究所,上海,200240 |
| 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(°)/s;姿态估计误差优于0.... |
| 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 |
Satellite Attitude Determination Algorithm Based on Gyro and Star-sensor |
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| BIAN Zhiqiang,CHENG Weiqiang,XUE Xiaobu,YU Yongjiang. Satellite Attitude Determination Algorithm Based on Gyro and Star-sensor[J]. Spacecraft Engineering, 2011, 0(2): 29-34 | |
| Authors: | BIAN Zhiqiang CHENG Weiqiang XUE Xiaobu YU Yongjiang |
| Affiliation: | (Shanghai Institute of Satellite Engineering,Shanghai 200240,China) |
| Abstract: | 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 5.56×10-5o/s and the attitude estimating error less than 0.01o,which means attitude measurement noise is restrained effectively. |
| Keywords: | earth observation satellite gyros bias star sensor quaternion attitude determination Kalman filter |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ | |