新一代重力卫星简化动力学精密定轨实验分析  

A new generation of gravity satellite reduced-dynamic precise orbit determination experiment and analysis

作　　者：马万军 刘根友 肖恭伟 高铭 王生亮 MA Wanjun;LIU Genyou;XIAO Gongwei;GAO Ming;WANG Shengliang(State Key Laboratory of Geodesy and Earth’s Dynamics,Innovation Academy for Precision Measurement Science and Technology,Chinese Academy of Sciences,Wuhan 430077,China;College of Earth and Planetary Sciences,University of Chinese Academy of Sciences,Beijing 100049,China)

机构地区：[1]中国科学院精密测量科学与技术创新研究院大地测量与地球动力学国家重点实验室,武汉430077 [2]中国科学院大学地球与行星科学学院,北京100049

出　　处：《测绘科学》2022年第1期24-32,共9页Science of Surveying and Mapping

基　　金：国家重点研发计划项目(2016YFB0501900);国家自然科学基金项目(41774017,41621091)。

摘　　要：针对重力卫星轨道低,大气阻力和太阳光压等较为复杂难以模型化的问题,该文基于简化动力学方法,采用GRACE-FO星载GPS双频观测数据,结合CODE提供的精密星历与钟差产品对GRACE-FO卫星进行精密定轨实验与分析。通过与美国喷气动力实验室(JPL)官方提供的事后精密轨道对比、K波段测距系统(KBR)进行星间测距数据检核以及载波相位残差分析对定轨精度进行了评估。结果表明:两颗卫星轨道与JPL提供的参考轨道比较,径向、切向、法向RMS均小于2 cm,三维位置精度(3D-RMS)小于3 cm;载波相位残差RMS为6 mm。KBR星间测距对比结果表明,JPL参考轨道的距离精度优于1 cm,本文定轨解算的距离精度优于2 cm,无明显系统性偏差存在,定轨结果可靠。Aiming at the problems of low orbit of gravity satellite,atmosphere drag and solar radiation pressure,which are more complicated and difficult to model,based on the reduced-dynamic method,this paper uses GRACE-FO satellite-borne GPS dual-frequency observation data,combined with the precision ephemeris and clock error products provided by CODE,to research precision orbit determination experiments and analysis on GRACE-FO satellites.The accuracy of orbit determination was evaluated through the JPL official post-precision orbit,K-band ranging system(KBR)for inter-satellite ranging data and GPS satellites carrier phase residual.The results show that the two satellite orbits are compared with JPL reference orbits,the radial,tangential and normal RMS values are all less than 2 cm,and the three-dimensional position accuracy(3 D-RMS)is better than 3 cm;The carrier phase residuals RMS are less than 6 mm.The results of KBR inter-satellite ranging show that the distance accuracy of the JPL orbit is better than 1 cm,and the distance accuracy calculated in this paper is better than 2 cm,there is no obvious systematic errors,and the orbit determination result is reliable.

关 键 词：GRACE-FO 简化动力学法 载波相位残差 KBR检核 

分 类 号：P228[天文地球—大地测量学与测量工程]