大规模低轨星座的实时精密定轨技术

李桢; 施闯

doi:10.11959/j.issn.2096-8930.2024008

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大规模低轨星座的实时精密定轨技术

研究 | 更新时间：2024-06-03

- 大规模低轨星座的实时精密定轨技术
- Realtime Precise Orbit Determination Technology for LEO Mega-Constellation
- 天地一体化信息网络 2024年5卷第1期页码：76-83
- 作者机构：
  
  1. 卫星导航与移动通信融合技术工业和信息化部重点实验室，北京 100191
  2. 北京航空航天大学前沿科学技术创新研究院，北京 100191
  3. 北京航空航天大学电子信息工程学院, 北京 100191
- 作者简介：
  
  [ "李桢（1989− ），男，助理研究员，主要研究方向为航天器轨道动力学、精密定轨、空间碎片等" ]
  [ "施闯（1968− ），男，教授，博士生导师，主要研究方向为北斗/GNSS 高精度导航定位授时及其应用" ]
- 基金信息：
- DOI：10.11959/j.issn.2096-8930.2024008
  中图分类号： TP393
- 网络出版日期：2024-03，
  
  纸质出版日期：2024-03-20
- 稿件说明：
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李桢, 施闯. 大规模低轨星座的实时精密定轨技术[J]. 天地一体化信息网络, 2024,5(1):76-83.

Zhen LI, Chuang SHI. Realtime Precise Orbit Determination Technology for LEO Mega-Constellation[J]. Space-integrated-ground information networks, 2024, 5(1): 76-83.
李桢, 施闯. 大规模低轨星座的实时精密定轨技术[J]. 天地一体化信息网络, 2024,5(1):76-83. DOI： 10.11959/j.issn.2096-8930.2024008.

Zhen LI, Chuang SHI. Realtime Precise Orbit Determination Technology for LEO Mega-Constellation[J]. Space-integrated-ground information networks, 2024, 5(1): 76-83. DOI： 10.11959/j.issn.2096-8930.2024008.

摘要

在全球导航卫星系统的支撑下，分析地面集中解算和星上自主解算精密定轨的优缺点，并将高精度轨道非保守力模型应用于星上实时自主定轨算法，实现运动学和动力学定轨的分离，对于需要频繁机动的低轨卫星精密定轨具有显著优势。结果表明，辐射光压和大气阻力非保守力物理模型计算的加速度精度约5 nm/s

；采用广播星历进行定轨解算可以达到0.8 m位置精度，低轨卫星速度误差约1.1 mm/s；采用实时精密星历，位置精度可以达到8.0 cm，卫星速度精度约0.1 mm/s。低轨卫星实时精密定轨和预报方法可有效支撑大规模低轨星座的导航功能实现。

Abstract

Supported by GNSS

it analyzed the advantages and disadvantages of solving LEO satellite orbit on the ground or onboard the satellites.The high-fidelity non-conservative force models were applied to the real-time orbit determination algorithm.To separate the kinematic and dynamic orbit determination process had been a great advantage for LEO satellites with much frequent orbital maneuvers.The test results showed that the accuracy of accelerations computed from the radiation pressure and atmospheric drag non-conservation force models were around 5 nm/s

.Use the broadcast ephemeris

the real-time orbit determination algorithm could get an accuracy of 0.8 m in the satellites′ positions and 1.1 mm/s accuracy in the satellites′ velocity.When the real-time precise ephemeris of GNSS satellites were provided

the algorithm could get an accuracy of 8 cm in the LEO satellites′ position and 0.1 mm/s in the velocity.The method for real-time orbit determination and orbit prediction in this paper could be used to support the construction of navigation system with the mega-constellations.

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