| 日月轨道计算对TLE深空编目目标预报精度的影响 |
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| 引用本文： | 郭效忠,李佳威,沈鸣,高鹏骐,杨大陶,于欢欢,赵有.日月轨道计算对TLE深空编目目标预报精度的影响[J].天文学报,2022,63(6):68. |
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| 作者姓名： | 郭效忠 李佳威 沈鸣 高鹏骐 杨大陶 于欢欢 赵有 |
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| 作者单位： | 中国科学院国家天文台 北京 100101;中国科学院大学 北京 100049;探月与航天工程中心 北京 100190 |
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| 基金项目： | 国家自然科学基金项目(11903051), 国家重点研发计划(2020YFA0406500)资助 |
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| 摘 要： | 双行根数(Two Line Element, TLE)作为一类广泛使用的空间物体编目数据, 其预报精度和误差特性是TLE编目 在空间碎片研究中所要关注的问题之一. TLE编目需要配合SGP4/SDP4 (Simplified General Perturbations 4/Simplified Deep Space 4)模型进行轨道预报, 对深空物体来说, 主要考虑带谐项$J_2$、$J_3$、$J_4$摄动、 第三体日月摄动和特殊轨道共振问题修正等. 其中, SGP4/SDP4模型第三体摄动计算时, 对日月轨道近似采用了长期进动根数和 简单平运动的方式, 在外推10d时存在约2$^\circ$--3${^\circ
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| 关 键 词： | 天体力学 SGP4/SDP4 方法: 数据分析 |
| 收稿时间： | 2021/12/14 0:00:00 |
Analysis on Propagation Accuracy of Deep-Space TLE Objects Affected by Solar/Lunar Orbit Calculation |
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| GUO Xiao-zhong,LI Jia-wei,SHEN Ming,GAO Peng-qi,YANG Da-tao,YU Huan-huan,ZHAO You.Analysis on Propagation Accuracy of Deep-Space TLE Objects Affected by Solar/Lunar Orbit Calculation[J].Acta Astronomica Sinica,2022,63(6):68. |
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| Authors: | GUO Xiao-zhong LI Jia-wei SHEN Ming GAO Peng-qi YANG Da-tao YU Huan-huan ZHAO You |
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| Institution: | National Astronomical Observatories, Chinese Academy of Sciences, Beijing 100101;University of Chinese Academy of Sciences, Beijing 100049;Lunar Exploration and Space Engineering Center, Beijing 100190 |
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| Abstract: | Two Line Element (TLE) set is a widely used catalogue data of space objects, consequently its propagation accuracy and error characteristic became one of the concerned problems in space debris research. TLEs should be propagated with the compatible SGP4/SDP4 (Simplified General Perturbations 4/Simplified Deep Space 4) model. For a deep-space object, SGP4/SDP4 model includes $J_2$, $J_3$, $J_4$ zonal perturbations, solar/lunar third-body perturbation, and an extra treatment for 12 h/24 h orbit resonance problem. In regard to third-body perturbation, the SGP4/SDP4 model describes solar/lunar orbit with a set of time-varying elements with a simple two-body mean motion, of which there would be $2^\circ$--$3^\circ$ solar/lunar position error after a 10 d extrapolation. A modest accuracy solar/lunar orbit model has been chosen to provide a more precise position estimation at the TLE element epoch. Due to the difference between solar/lunar motion complexity, the lunar is directly modeled by its true anomaly function, while the solar is modeled by the two-body mean motion. The result that approximately $1''$--$2''$ for solar position, and $15''$--$20''$ for lunar position is achieved for a 10 d extrapolation. The laser ranging satellite Etalon 1 and Galileo 23 were taken as examples to show that the evolution of position accuracy of the TLEs could have an abnormal change during the propagation, while an ``improved'' TLE with solar/lunar orbit correction will have better performance. |
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| Keywords: | celestial mechanics SGP4/SDP4 (Simplified General Perturbations 4/Simplified Deep Space 4) methods: data analysis |
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