摘要
针对低轨微纳卫星体积小、功耗低的设计约束,提出了基于低轨地磁的定软/定姿全磁自主导航算法。该算法仅利用三轴磁强计测量值和卫星动力学方程建立Kalman滤波器,实现了低轨微纳卫星的全自主轨道确定和姿态测量,理论仿真结果表明,该全磁导航算法精度能够满足低轨微纳卫星的一般要求。利用高精度地磁模拟器搭建了微纳卫星全磁自主导航地面仿真验证系统,对算法进行了全物理仿真测试和实验误差分析,进一步验证了全磁自主导航算法的可行性,为低轨微纳卫星提供了一种低成本、高自主、高可靠性的导航方法。
An algorithm based on the low orbit geomagnetic field for satellite single magnetic autonomous navigation is proposed in this paper due to the design constraint of small volume and low power consumption of microsat.The algorithm is only based on magnetometer vector and dynamical equation,which establishes Kalman filter and then implements autonomous orbit determination and attitude measurement.The accuracy of single magnetic navigation can meet the normal requirements of microsat verified by simulation analysis.Simulation verification system on magnetic navigation is also founded.The feasibility of geomagnetic navigation algorithms is verified by test and analysis.In conclusion,a low cost navigation method with high autonomy and reliability is provided for microsat.
出处
《导航与控制》
2016年第5期40-45,66,共7页
Navigation and Control
基金
上海航天科技创新基金(编号:SAST2015035)
江苏省自然基金青年基金项目(编号:SBK201343261)
关键词
微纳卫星
地磁定姿
KALMAN滤波
仿真验证系统
microsat
attitude determination based on geomagnetic field
Kalman filter
simulation verification system
