Improvement of the Long-Term Orbit Prediction for LEO Navigation Satellites Using the Inner Formation Method
Improvement of the Long-Term Orbit Prediction for LEO Navigation Satellites Using the Inner Formation Method
复制标题
DOI：
10.1109/taes.2019.2891158
复制
发表时间：
2019-01
影响因子：
4.4
通讯作者：
Zhaokui Wang;Z. Hou;Yulin Zhang
中科院分区：
文献类型：
--
作者：
Zhaokui Wang;Z. Hou;Yulin Zhang
本文提出了内编队导航卫星的概念。它在低地球轨道上运行，具有很高的自主性，使对地面支持的需求最小化。提出了一种基于状态变换矩阵的轨道拟合方法进行轨道预测，并通过仿真研究了预测误差的长期积累。讨论了用线性控制器维持轨道的燃料消耗问题。结果表明，如果将残余非引力扰动的常数分量抑制到$1\乘以10^{-13}\，\text{m}/ \text{s}^{2}$，则可以自主预测90天的轨道，精度达到米级。如果使用光学传感器和电动推进器维持轨道，5年的最大燃料消耗约为10公斤。
In this paper, the concept of the inner formation navigation satellite is proposed. It operates in the low Earth orbit with very high autonomy to make the requirement for ground support minimized. A state transformation matrix-based orbit fitting method is presented for orbit prediction, and the long-term accumulation of prediction errors is investigated by simulations. The fuel consumption for orbit maintaining with a linear controller is discussed. Results show that the orbit can be predicted autonomously to the meter-level accuracy for 90 days if the constant component of residual nongravitational disturbance can be suppressed to $1\times 10^{-13}\,\text{m}/ \text{s}^{2}$. The maximum fuel consumption for 5 years is on the order of 10 kg if optical sensors and electric thrusters are used for orbit maintaining.