基于商业天地基光电监测数据的空间碎片短弧初轨确定试验
doi: 10.11728/cjss2025.05.2024-0129
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劳振迪 男, 2000年9月出生于山东省滨州市, 现为山东理工大学就读硕士研究生, 主要研究方向为空间目标的机动探测、空间碎片监测. E-mail: 23507020866@stumail.sdut.edu.cn -
雷祥旭 男, 1989年1月出生于山东省泰安市, 现为山东理工大学测绘工程系讲师, 主要研究方向为空间碎片监测数据定轨编目等关键问题. E-mail: xxlei@whu.edu.cn
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Experimental Study on Short-arc Initial Orbit Determination of Space Debris Based on Commercial Space-based and Ground-based Electro-optical Monitoring Data
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摘要: 随着国内空间碎片监测设备的不断增多, 如何有效利用大量观测数据以发挥商业航天的价值, 成为一个值得深入研究的重要课题. 利用中国商业航天公司的仰望一号天基观测数据和烛龙地基观测网的数据, 开展了地球同步轨道 (GEO) 目标和低地球轨道 (LEO) 目标的初轨确定 (IOD), 并通过两行轨道根数(TLE)作为已知值来估计初轨误差. 具体结果如下: GEO目标的观测弧长约为249 s, 初轨半长轴误差为84.4 km, 倾角误差为0.40°; LEO目标的观测弧长约为40 s, 初轨半长轴误差为26.0 km, 倾角误差为0.13°. 结果表明, 本文采用的初轨确定算法是可行的, 并展示了商业航天领域中天地基光电监测设备的巨大潜力.Abstract: With the development of domestic commercial spaceflight and the increasing number of space debris monitoring equipment, how to make full use of the observed data from commercial spaceflight has become an important subject worthy of further study. Initial orbit determination of space targets is not only an important basis for space mission planning and space situational awareness, but also a prerequisite for key technologies such as satellite operations, collision warning, orbit maintenance, etc. This study uses data obtained from the Yangwang-1 space-based observatory system and the Zhulong ground-based observatory network developed by China’s commercial spaceflight companies to conduct Initial Orbit Determination (IOD) for Geosynchronous Earth Orbit (GEO) targets and Low Earth Orbit (LEO) targets, respectively. The Yangwang-1 satellite carries advanced electro-optical sensors that enable long duration, high precision continuous observations of GEO targets, while the Zhulong ground-based observation network consists of multiple electro-optical telescopes distributed at various locations across the country, capable of short arc, high frequency observations of LEO targets. In this study, we used the method of initial orbit determination based on optical goniometry observations, using the range searching method and iterative improvement strategy to estimate the initial orbits of GEO and LEO targets, and used Two-Line Element (TLE) data as a benchmark to evaluate the error of the calculated results. Experimental results show that for GEO targets, the observed arc length is about 249 s, the semi-major axis error determined by the initial orbit is 84.4 km, and the inclination error is 0.40°; For LEO targets, the observed arc is about 40 s, the semi-major axis error of the initial orbit is 26.0 km, and the inclination error is 0.13°. The results show that the method of initial orbit determination adopted in this study is feasible in the data processing of commercial spaceflight observations, and the great potential of space-based electro-optical monitoring equipment in the field of orbit determination is verified.
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图 2 不同类型空间事件数量及变化趋势(截至2023年, 以5年为时间段)
Figure 2. Number and trends of different types of space events (as of 2023, 5 year bins)
图 4 天地基监测设备中的仰望一号卫星
Figure 4. Yangwang-1 satellite in ground based and space-based monitoring equipment
图 5 天地基监测设备中的烛龙设备
Figure 5. Zhulong observatory in ground based and space-based monitoring equipment
表 1 近几年初轨确定方法及精度
Table 1. Initial orbit determination methods and precision in recent years
方法 数据来源 精度统计 基于改进Gauss方程的初轨确定新方法[17] 仿真观测数据. LEO, MEO, HEO和GEO各一条数据, 弧段长度分别为15, 120, 160, 180 s, 并分别增加5″的随机误差 半长轴误差分别为50.0, 15.0, 55.0和2.0 km 光学短弧初轨确定的轨道偏心率判定方法[18] 仿真观测数据. LEO1和LEO2的弧段长度为120 s; MEO, HEO和GEO目标的弧段长度为240 s LEO1, MEO, GEO轨道半长轴误差的均方根(RMS)值分别为55.9, 46.6, 150.2 km, 倾角误差的RMS分别为0.18°, 0.05°, 0.14°. LEO2和HEO半长轴误差的RMS分别为86.9和419.5 km, 倾角误差的RMS分别为0.16°和0.90° 多约束初轨确定算法[19] 实测数据. 2021年5月15日中国科学院国家天文台长春人造卫星观测站的GEO目标观测数据 弧长大于60 s时, 误差小于200 km的占比为93.6%; 弧长小于60 s时, 误差小于200 km的占比为65.8% 
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表 2 GEO目标信息
Table 2. Information of GEO objects
目标编号 目标名称 发射时间 国家 近/远地点高度/km 27954 GALAXY 13 (HORIZONS-1) 2003-10-01 美国 35781.6/35806.4 42763 ZHONGXING-9 A 2017-06-18 中国 35912.1/35944.7 45344 BEIDOU-3 G2 2020-03-09 中国 35774.1/35813.9
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表 3 GEO目标初轨确定文件及误差
Table 3. Initial Orbit Determination Arcs and Associated Errors for GEO Objects
序号 观测文件 弧长/s 误差 半长轴/km 偏心率 倾角/(°) 1 27954_1123062202.Dat 290 31.5 –0.00012 0.48 2 27954_1123062203.Dat 290 24.4 0.00026 0.55 3 27954_1123062204.Dat 275 25.5 –0.00007 0.52 4 42763_1123061711.Dat 90 –115.1 0.00077 0.11 5 42763_1123061712.Dat 210 –109.1 –0.00032 0.23 6 42763_1123061713.Dat 275 –112.6 –0.00055 0.42 7 42763_1123061714.Dat 255 159.9 –0.00046 0.69 8 42763_1123061715.Dat 185 –105.8 –0.00055 0.40 9 45344_1123061806.Dat 290 22.6 0.00006 0.23 10 45344_1123061807.Dat 290 24.2 0.00005 0.18 11 45344_1123061808.Dat 290 22.4 –0.00015 0.02 平均值 — 249 68.5 0.00031 0.35
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表 4 LEO目标信息
Table 4. Information of LEO objects
目标编号 目标名称 发射时间 国家 近/远地点高度/km 1328 EXPLORER 27 1965-04-29 美国 935.7/1305.6 41240 JASON-3 2016-01-17 美国 1339.2/1350.6 46984 SENTINEL-6 2020-11-21 欧洲航天局 1338.9/1350.8 47764 STARLINK-2182 2021-03-04 美国 390.7/392.5 48621 HAIYANG-2D 2021-05-19 中国 951.7/966.4 49414 STARLINK-3146 2021-11-13 美国 545.8/548.0 54754 SWOT 2022-12-16 美国 900.0/900.7 54777 STARLINK-5468 2022-12-17 美国 546.0/547.8
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表 5 LEO目标初轨确定误差
Table 5. IOD errors of LEO objects
NORAD ID 弧段数量 弧长/s 轨道根数误差 半长轴/km 偏心率 倾角/(°) 1328 2 39 134.2 0.02213 0.12 41240 31 51 17.1 0.00187 0.10 46984 21 47 19.6 0.00202 0.12 47764 2 30 16.1 0.00215 0.02 48621 11 37 18.6 0.00158 0.14 49414 1 44 13.5 0.00255 0.08 54754 6 45 12.6 0.00236 0.14 54777 1 28 2.7 0.00206 0.03 平均值 9.4 40 29.3 0.00459 0.09
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