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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。
Aimed at the design constraints of low-lying micro / nano satellites, which are small in volume and low in power consumption, an all-magnetic autonomous navigation algorithm based on low-earth orbit magnetism is proposed. The algorithm uses Kalman filter only based on the measurements of three-axis magnetometer and satellite dynamics to realize full-autonomic orbit determination and attitude measurement of the LEO micro or nano satellite. The theoretical simulation results show that the accuracy of the all-magnetic navigation algorithm satisfies General requirements for LEO micro / nano satellites. The micro-and nano-satellite all-magnetic autonomous navigation ground simulation and verification system is established by using the high-precision geomagnetic simulator. The full physical simulation test and the experimental error analysis of the algorithm are carried out to further verify the feasibility of the all-magnetic autonomous navigation algorithm. Satellites provide a low-cost, highly autonomous, highly reliable method of navigation.