利用卫星两行轨道根数反演热层密度

任廷领; 苗娟; 刘四清; 李志涛

doi:10.11728/cjss2014.04.426

利用卫星两行轨道根数反演热层密度

doi: 10.11728/cjss2014.04.426

任廷领^1,2, ,,
苗娟¹,
刘四清¹,
李志涛¹

1.
中国科学院空间科学与应用研究中心北京 100190
2.
中国科学院大学北京 100049

基金项目: 国家重点基础研究发展计划项目（2012CB825606）和航天飞行动力学技术重点实验室开放基金项目（2012afdl026）共同资助

详细信息

通讯作者:
任廷领,E-mail:rtl.qd.ouc@163.com

中图分类号: P351
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- 被引次数: 0
出版历程
- 收稿日期: 2013-08-05
- 修回日期: 2014-02-17
- 刊出日期: 2014-07-15

Research on Thermospheric Densities Derived from Two-line Element Sets

1.
Center for Space Science and Applied Research, Chinese Academy of Sciences, Beijing 100190
2.
University of Chinses Acadenmy of Sciences, Beijing 100049

摘要

摘要: 两行轨道根数（TLEs）是基于一般摄动理论产生的用于预报地球轨道飞行器位置和速度的一组轨道参数，通过求解大气阻力微分方程，可反演出热层大气密度. 本文选取近圆轨道CHAMP卫星和椭圆轨道Explorer8卫星，以两行轨道根数数据为基础，计算反弹道系数，并根据不同轨道特征采用两种不同反演方法对热层大气密度进行研究. 结果表明，这两种方法反演得到的大气密度与实测值均符合较好，其中CHAMP卫星的反演结果和经验模式值相对于实测值的误差分别为7.94%和13.94%，Explorer8卫星的误差分别为9.04%和14.32%. 相比模式值，利用两行轨道根数数据反演的热层大气密度更接近于实测值，说明该方法可以作为获取大量可靠大气密度数据的一种有效途径.
- 两行轨道根数 /
- 反弹道系数 /
- 近圆轨道和椭圆轨道 /
- 热层密度反演
Abstract: Two-line Orbital Element Sets (TLEs) consist of mean orbital elements at epoch, along with the NORAD (North American Aerospace Defence Command) catalog number, international designator, epoch and additional fitting parameters. These information can be used to derive thermospheric densities through integration of differential equation for mean motion. For near-circular orbit satellites, derived thermospheric density can be seen as real density because of their stable orbit height, while for elliptical orbit satellites, thermospheric density at perigee and apogee can be different as much as several orders. So different methods were applied to derive thermospheric density according to different satellite orbits. This paper chooses CHAMP and Explorer 8 satellites, whose orbits are respectively near-circular and elliptical, as our research cases. The inverse ballistic coefficient B (B-factor) was firstly derived based on TLEs data, then thermospheric densities were derived with different methods according to different orbit characters. Finally, a comparison was made among TLEs-derived density, NRLMSISE-00 model density and observed (or reference) density. The result shows that the average error of TLEs-derived density and empirical model density with respect to observed value for CHAMP is 7.94% and 13.94% respectively, and the average error with respect to reference value for Explorer 8 is 9.04% and 14.32% respectively. This result indicates that TLEs-derived density is closer to the real density than empirical model density, and this method provides an effective way to obtain extensive and reliable atmosphere density data.
- Two-Line Element Sets (TLEs) /
- Inverse ballistic coefficient /
- Near-circular orbit and elliptical orbit /
- Derived thermospheric density

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参考文献(22)

[1]	Berger C, Biancale R Ill M, Barlier F. Improvement of the empirical thermosphere model DTM: DTM-94-A comparative review of various temporal variations and prospects in space geodesy applications[J]. J. Geod., 1998, 72(3):161-178
[2]	Bruinsma S, Thuillier G, Barlier F. The DTM-2000 empirical thermosphere model with new data assimilation and constrains at lower boundary: accuracy and properties[J]. J. Atmos. Solar-Terr. Phys., 2003, 65:1053-1070
[3]	Hedin A. MSIS-86 thermospheric model[J]. J. Geophys. Res., 1987, 92(A5):4649-4662
[4]	Hedin A E. Extension of the MSIS thermospheric model into the middle and lower atmosphere[J]. J. Geophys. Res., 1991, 96(A2):1159-1172
[5]	Picone J M, Hedin A E, Drob D P. NRLMSISE-00 empirical model of the atmosphere: Statistical comparisons and scientific issues[J]. J. Geophys. Res., 2002, 107, A12, 1468, doi: 10.1029/2002JA009430
[6]	Rhoden E, Forbes J, Marcos F. The influence of geomagnetic and solar variabilities on lower thermosphere density[J]. J. Atmos. Solar-Terr. Phys., 2000, 62:999-1013
[7]	Storz M F, Bowman B R. High accuracy satellite drag model[J]. Adv. Space Res., 2005, 36:2497-2505
[8]	Miao Juan, Liu Siqing, Li Zhitao, et al. Atmospheric density calibration using the real-time satellite observation[J]. Chin. J. Space Sci., 2011, 31(4):459-466. In Chinese (苗娟, 刘四清, 李志涛, 等. 基于实时观测数据的大气密度模式修正[J]. 空间科学学报, 2011, 31(4):459-466)
[9]	Picone J M, Emmert J T, Lean J L. Thermospheric densities derived from spacecraft orbits: Accurate processing of two-line element sets[J]. J. Geophys. Res., 2005, 110, A03301, doi: 10.1029/2004JA010585
[10]	Lean J L, Picone J M, Emmert J T, et al. Thermospheric densities derived from spacecraft orbits: Application to the Starshine satellites[J]. J. Geophys. Res., 2006, 111, A04301, doi: 10.1029/2005JA011399
[11]	Emmert J T, Picone J M, Lean J L. Global change in the thermosphere: Compelling evidence of a secular decrease in density[J]. J. Geophys. Res., 2004, 109, A02301, doi: 10.1029/2003JA010176
[12]	Emmert J T. A long-term data set of globally averaged thermospheric total mass density[J]. J. Geophys. Res., 2009, 114, A06315, doi: 10.1029/2009JA014102
[13]	Emmert J T, Picone J M, Meier R R. Thermospheric global average density trends, 1967-2007, derived from orbits of 5000 near-Earth objects[J]. Geophys. Res. Lett., 2008, 35:L05101, doi: 10.1029/2007GL032809
[14]	Yang Weilian. Accuracy evaluation of two line element[J]. Spacec. Eng., 2009, 18(3):8-13. In Chinese (杨维廉. 两行根数的精度评估[J]. 航天器工程, 2009, 18(3):8-13)
[15]	Diao Ninghui, Liu Jianqiang, Sun Congrong, et al. Satellite orbit calculation based on SGP4 model[J]. Remote Sens. Inf., 2012, 27(4):64-70. In Chinese (刁宁辉, 刘建强, 孙从容, 等. 基于SGP4模型的卫星轨道计算[J]. 遥感信息. 2012, 27(4):64-70)
[16]	Liu Wei, Miao Yuanxing. Tests of the accuracies of SGP4/SDP4 model predictions[J]. Astron. Res. Tech., 2011, 8(2):128-131. In Chinese (刘卫, 缪元兴. SGP4/SDP4模型预报可靠性分析[J]. 天文研究与技术, 2011, 8(2):128-131)
[17]	Hu Min, Zeng Guoqiang. Transformation between mean and osculating orbital elements[J]. J. Spacecr. TT&C Tech., 2012, 31(2):77-81. In Chinese (胡敏, 曾国强. 平均轨道根数与密切轨道根数的互换[J]. 飞行器测控学报, 2012, 31(2):77-81)
[18]	Hedin A E, Fleming E L, Manson A H, et al. Empirical wind model for the upper, middle, and lower atmosphere[J]. J. Atmos. Terr. Phys., 1996, 58(13):1421-1447
[19]	King-Hele D G. Satellite Orbits in an Atmosphere: Theory and Applications[M]. Glasgow: Blackie and Son Ltd, 1987
[20]	Bowman B R. True satellite ballistic coefficient determination for HASDM[C]// AIAA/AAS Astrodynamics Specialist Conference. California: Monterey, 2002
[21]	Emmert J T, Meier R R, Picone J M, et al. Thermospheric density 2002-2004: TIMED/GUVI dayside limb observations and satellite drag[J]. J. Geophys. Res., 2006, 111, A10S16, doi: 10.1029/2005JA011495
[22]	Picone J M, Hedin A E, Drob D P. NRLMSISE-00 empirical model of the atmosphere: Statistical comparisons and scientific issues[J]. J. Geophys. Res., 2002, 107, A12, 1468, doi: 10.1029/2002JA009430