用于天基机会信号定位的NC-LEO卫星单站TLE估计

秦红磊; 邓若凡; 吕红丽

doi:10.13700/j.bh.1001-5965.2023.0684

用于天基机会信号定位的NC-LEO卫星单站TLE估计

doi: 10.13700/j.bh.1001-5965.2023.0684

秦红磊^1, ,,
邓若凡¹,
吕红丽^{2, 3}

1.
北京航空航天大学电子信息工程学院，北京 100191
2.
陕西省组合与智能导航重点实验室，西安 710068
3.
中国电子科技集团公司第二十研究所，西安 710068

基金项目:

陕西省组合与智能导航重点实验室开放基金(SKLIIN-20190107)

详细信息

通讯作者:
E-mail：qhlmmm@sina.com

中图分类号: P228.1；TN966
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- 被引次数: 0
出版历程
- 收稿日期: 2023-10-24
- 录用日期: 2024-02-23
- 网络出版日期: 2024-03-11
- 整期出版日期: 2025-12-31

Single-station TLE estimation of NC-LEO satellite for space-based opportunistic positioning

QIN Honglei^{1
, ,},
DENG Ruofan¹,
LYU Hongli^{2, 3}

1.
School of Electronic and Information Engineering，Beihang University，Beijing 100191，China
2.
Shaanxi Key Laboratory of Integrated and Intelligent Navigation，Xi’an 710068，China
3.
Xi’an Research Institute of Navigation Technology，Xi’an 710068，China

Funds:

Foundation of Shaanxi Key Laboratory of Integrated and Intelligent Navigation (SKLIIN-20190107)

More Information

Corresponding author: E-mail：qhlmmm@sina.com

摘要

摘要:
天基机会信号定位是弹性定位、导航与授时(PNT)体系的重要部分，当前大部分定位终端所用的非合作低轨(NC-LEO)卫星轨道可靠性和精度差。为解决该问题，提出NC-LEO卫星单站两行轨道根数(TLE)估计的体系结构，通过单站提取的多普勒观测量和星座设计轨道参数获取精密TLE。同时，提出基于多初始化策略的遗传算法-岭估计的TLE估计算法，实现在先验轨道不完备和法方程病态的情况下获取精密TLE。实际试验证明：相比基于NORAD公开的TLE定位，基于所提方法获取的TLE定位精度更高。
- 天基机会信号定位 /
- 非合作低轨卫星 /
- 单站 /
- 两行轨道根数估计 /
- 轨道确定
Abstract:
The space-based opportunistic positioning is an integral part of the resilient positioning, navigation, and timing (PNT) system. At the moment, most space-based opportunistic positioning terminals depend on the non-cooperative low Earth orbit (NC-LEO) satellite’s unreliable and imprecise orbit. To address this problem, this paper presents a framework for single-station two line element (TLE) estimation of non-cooperative low Earth orbit satellites. The precise TLE is obtained using Doppler observations from a single-station and the orbital parameters for constellation design. Additionally, a TLE estimation algorithm is proposed based on a genetic algorithm-ridge estimation approach with multiple initialization strategies. This method facilitates the acquisition of accurate TLE even in situations where prior orbit information is incomplete, and when the problem is ill-conditioned. Finally, real-world tests confirm that using TLEs computed using the suggested method leads to improved accuracy when compared to placement based on NORAD’s publicly available TLEs.
- space-based opportunistic positioning /
- non-cooperative low Earth orbit satellite /
- single-station /
- two line element estimation /
- orbit determination

HTML全文

图 1 NC-LEO卫星单站TLE估计体系结构示意图

Figure 1. Diagram of single-station TLE estimation for NC-LEO satellite

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图 2 SGP4模型根据平均轨道根数计算瞬时轨道根数流程

Figure 2. Flowchart for calculating instantaneous orbital elements based on average orbital elements of SGP4 model

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图 3 不同种群规模对应的算法收敛后适应度函数MC结果

Figure 3. MC results of fitness function after algorithm convergence corresponding to different population sizes

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图 4 不同种群规模对应的升交点赤经及近地点幅角与平近点角之和的MC结果

Figure 4. MC results of ascending node right ascension and sum of argument of perigee and mean anomaly corresponding to different population sizes

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图 5 精密TLE位置、速度RMSE标准差随岭参数变化曲线

Figure 5. Curves of RMSE standard deviation of precision TLE position velocity with ridge parameters

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图 6 等定位误差面

Figure 6. Iso-position error plane

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图 7 不同方向和基线距离的定位误差

Figure 7. Position error for different directions and baseline distances

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图 8 NC-LEO卫星TLE估计系统实物图

Figure 8. Physical diagram of NC-LEO satellite TLE estimation system

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图 9 用于估计目标卫星TLE的观测多普勒

Figure 9. Observation Doppler for estimating TLE of target satellites

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图 10 目标卫星精密TLE的残差分布直方图

Figure 10. Residual distribution histogram of precision TLE for target satellite

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图 11 不同时间内基于不同方法获取的TLE定位RMSE

Figure 11. Positioning RMSE based on TLE by different methods in different time

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图 12 相比基于公开TLE，基于估计TLE定位的精度提高比例

Figure 12. Compared to positioning based on public TLE, proportion of position accuracy improvement based on estimated TLE

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表 1 2颗目标卫星的轨道参数

Table 1. Orbital parameters of two target satellites

卫星编号	一天绕地球圈数	轨道倾角/（°）	偏心率	升交点赤经/（°）	近地点幅角/（°）	平近点角/（°）	弹道系数
41919卫星	14.34220991	86.3975	0.0002160	228.0428	91.9051	26.7190	−0.00179080
43577卫星	14.34217309	86.4037	0.0002372	196.3858	100.9897	346.6261	0.00089653

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