日月轨道计算对TLE深空编目目标预报精度的影响  

Analysis on Propagation Accuracy of Deep-Space TLE Objects Affected by Solar/Lunar Orbit Calculation

作　　者：郭效忠[1,2] 李佳威 沈鸣 高鹏骐[1] 杨大陶[1] 于欢欢 赵有[1] GUO Xiao-zhong;LI Jia-wei;SHEN Ming;GAO Peng-qi;YANG Da-tao;YU Huan-huan;ZHAO You(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)

机构地区：[1]中国科学院国家天文台,北京100101 [2]中国科学院大学,北京100049 [3]探月与航天工程中心,北京100190

出　　处：《天文学报》2022年第6期101-110,共10页Acta Astronomica Sinica

基　　金：国家自然科学基金项目(11903051);国家重点研发计划(2020YFA0406500)资助。

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10 d时存在约2◦–3◦的日月位置偏差.日月轨道计算可选用更加精确的方法来改进初始位置估计,并根据日月运动规律的不同,对太阳轨道采用平运动近似,对月球轨道采用计算真近点角近似,在外推10 d时,二者位置偏差可分别减小到约1′–2′和15′–20′范围.采用激光测距卫星Etalon 1、伽利略卫星导航系统Galileo 23卫星作为对比算例,结果分析表明二者原始的TLE编目轨道进行预报时存在明显的位置误差异常变化趋势;采用日月轨道计算改进后,重新定轨得到的“改进”编目具有更加精确的轨道预报结果.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°–3°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.

关 键 词：天体力学 SGP4/SDP4 方法:数据分析 

分 类 号：P135[天文地球—天体力学]