| 基于陀螺和四元数的EKF卫星姿态确定算法 |
| |
| 引用本文： | 朱庆华,李英波.基于陀螺和四元数的EKF卫星姿态确定算法[J].上海航天,2005,22(4):1-5,59. |
| |
| 作者姓名： | 朱庆华 李英波 |
| |
| 作者单位： | 上海航天控制工程研究所,上海,200233 |
| |
| 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。
|
| 关 键 词： | 姿态确定 四元数 陀螺漂移 扩展卡尔曼滤波 |
| 文章编号： | 1006-1630（2005）04-0001-05 |
| 收稿时间： | 2005-01-29 |
| 修稿时间： | 2005-01-292005-03-09 |
Extended Kalman Filter for Attitude Determination Using Gyros and Quaternion |
| |
| ZHU Qing-hua,LI Ying-bo.Extended Kalman Filter for Attitude Determination Using Gyros and Quaternion[J].Aerospace Shanghai,2005,22(4):1-5,59. |
| |
| Authors: | ZHU Qing-hua LI Ying-bo |
| |
| Abstract: | 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. |
| |
| Keywords: | Attitude determination Quaternion Gyros bias Extended Kalman filter |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
