摘要
卫星的发展趋向于微小型化 ,研究小型化、廉价和中等精度的自主导航系统是非常必要的。利用三轴磁强计量测的地磁场矢量在仪表坐标系中的分量 ,通过卡尔曼滤波器可以确定低轨道卫星的姿态。根据卫星姿态动力学模型和地磁场模型可推导卫星姿态确定滤波模型 ,进一步提出低轨道卫星姿态确定的滤波算法。仿真算例结果表明 ,三轴磁强计定姿方案可以满足中等姿态精度要求 ,在低轨道卫星自主导航中具有良好的应用前景。
Satellitestend to be micromation in future. Itis necessary to investigate small, cheap self contained navigation system with moderate precision. According to measuring data of three axis magnetometer in the body frame, the attitude of the satellite in low orbit can be determined through Kalman Filter. Combining the dynamical model of satellite s attitude with the standard model of the geomagnetic field,the filter model and arithmetic used to determine the attitude of the satellite are presented. The result of simulation shows that the project of three axis magnetometer attitude determination has a certain precision, which has an applicable future in the self contained navigation system with moderate precision attitude determination.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2001年第5期17-21,共5页
Journal of National University of Defense Technology
