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
李桢 1施闯2
作者信息
- 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;北京航空航天大学前沿科学技术创新研究院,北京 100191
- 2. 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;北京航空航天大学电子信息工程学院, 北京 100191
- 折叠
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/s2;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 ma-neuvers.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/s2.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 veloc-ity.The method for real-time orbit determination and orbit prediction in this paper could be used to support the construction of naviga-tion system with the mega-constellations.
关键词
大规模低轨星座/实时精密定轨/非保守力模型/大气阻力/辐射光压Key words
LEO mega-constellation/real-time precise orbit determination/non-conservative force models/atmospheric drag/solar ra-diation pressure引用本文复制引用
基金项目
国家重点研发计划资助项目(2023YFB3906503)
国家自然科学基金资助项目(42204033)
出版年
2024
国家科技期刊平台
NSTL
万方数据