Orbit determination Method and Precision Analysis of Space Object With Space-Based Camera

WANG Xiu-hong; LI Ju-feng; WANG Yan-rong

doi:10.3788/OPE.20132106.1394

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Orbit determination Method and Precision Analysis of Space Object With Space-Based Camera

更新时间：2020-08-12

- Orbit determination Method and Precision Analysis of Space Object With Space-Based Camera
- Optics and Precision Engineering Vol. 21, Issue 6, Pages: 1394-1403(2013)
- 作者机构：
  
  宇航动力学国家重点实验室2. 清华大学航天航空学院
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20132106.1394
  CLC： V529
- Received：26 December 2012，
  
  Revised：25 February 2013，
  
  Published Online：20 June 2013，
  
  Published：15 June 2013
- 稿件说明：
移动端阅览
王秀红李俊峰王彦荣. 天基照相机监测空间目标定轨方法及精度分析[J]. 光学精密工程, 2013,21(6): 1394-1403

WANG Xiu-hong LI Ju-feng WANG Yan-rong. Orbit determination Method and Precision Analysis of Space Object With Space-Based Camera[J]. Editorial Office of Optics and Precision Engineering, 2013,21(6): 1394-1403
王秀红李俊峰王彦荣. 天基照相机监测空间目标定轨方法及精度分析[J]. 光学精密工程, 2013,21(6): 1394-1403 DOI： 10.3788/OPE.20132106.1394.

WANG Xiu-hong LI Ju-feng WANG Yan-rong. Orbit determination Method and Precision Analysis of Space Object With Space-Based Camera[J]. Editorial Office of Optics and Precision Engineering, 2013,21(6): 1394-1403 DOI： 10.3788/OPE.20132106.1394.

摘要

考虑天基照相机观测中小尺寸空间目标时具有能耗低、精度高以及易于小型化实现等优势，研究了利用天基照相机监测空间目标的轨道确定和可观测性计算方法。分析了太阳同步轨道作为天基监视轨道的优点，结合目前国外的几种天基卫星轨道类型，设计了天基卫星轨道，在此基础上仿真分析了对不同轨道类型空间目标的可见观测弧段。根据目前地基光学观测设备的测轨精度和轨道动力学模型误差，添加了不同的测轨系统误差、随机误差及一定的动力学模型误差，仿真分析了对不同轨道高度空间目标的定轨精度。分析结果表明，采用6天7分钟/两天的天基光学测轨数据对近地轨道的空间目标定轨时，若测轨精度优于30，动力学模型误差小于50%，则定轨精度与美国编目轨道(TLE)精度相当。采用10分钟/天的天基光学测轨数据对地球同步轨道上的空间目标定轨时，若测轨精度优于10，动力学模型误差小于50%，则定轨精度在美国编目轨道精度范围内。

Abstract

As space-based cameras have advantages of lower energy consumption

higher accuracy

and easy to be miniaturized when they are used to observe space objects with middle or smaller sizes

this paper explores the orbit determination method and observability calculation method of space objects by space-based cameras. The advantages that the sun synchronous orbit is set as a space-based satellite orbit are analyzed and a space-based satellite orbit is designed by referencing several foreign space-based satellite orbits. Then the visible arc sections of space objects for different orbit types are simulated based on the space-based satellite orbit. According to the orbit measurement accuracy of existing space based optical observation equipment and errors of orbit dynamic model

the different system errors

random errors and dynamic model errors for the orbit measurements are added. Finally

the orbit determination precisions for space objects in different orbital altitudes are analyzed. Analysis results show that

for determining space target in low earth orbit with 6 of 7 minutes a day / two days of space-based optical measurement orbit data

the orbit determination precision is coincident with that of the United States of America cataloging (Two-line Elements

TLE) when the orbit measurement accuracy is better than 30 and the dynamic model error is less than 50%. Moreover

for determining space target in earth synchronous orbit with 10 min / day of space-based optical measurement orbit data

the orbit determination precision is in the orbit accuracy range of the United States of America cataloging when the orbit measurement accuracy is better than 10 " and the dynamic model error is less than 50%.

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references

MARSHALL H, KAPLAN．Survey of space debris reduction methods [C]．AIAA Space 2009 Conference and Exposition, A1AA2009-6619,Pasadena,2009:1-11.[2]王秀红，张荣之，高彦平.美俄卫星相撞事件及对我国在轨卫星安全影响分析[C].第五届中国空间碎片研讨会,2009,9(2):37-42.WANG X H, ZHANG R ZH, GAO Y P．Analysis on the collision event between iridium 33 and cosmos 2251 and effect on chinese satellites[C]．The Fifth Chinese Space Debris Conference, 2009,9(2):37-42.(in Chinese)[3]雷江涛，秦大国，祁先锋. 空间碎片概况研究[J]. 装备指挥技术学院学报，2007，18(5):56-60.LEI J T, QIN D G,QI X F．Sudy on general situation of space debris [J]．Journal of the Academy of Equipment Command & Technology, 2007，18(5):56-60. (in Chinese)[4]谭莹. 天基空间目标探测技术探讨[J]. 空间电子技术，2006,3(3):5-9.TAN Y. Discuss Technique Of Space Object Detect [J]. Sapce Electron Technique，2006,3(3):5-9.(in Chinese)[5]乔凯，王治乐，丛明煜. 空间目标天基地基监视系统对比分析[J]. 光学技术，2006，32(6):744-749．QIAO K, WANG ZH L, CONG M Y. Analysis on space based and ground based surveillance system to space target[J]. Optical Technique，2006，32(6):744-749.(in Chinese)[6]SHARMA J， STOKES G H, VON BRAUN C， et al.. Toward operational space-based space surveillance [J]. Lincoln Laboratory Journal，2002，13(2):309-313．[7]崔潇潇. 美国天基空间目标监视系统[J]. 国际太空，2011(7):37-43.CUI X X. America space-base surveillance system for space objects[J]. Space International，2011(7):37-43.[8]RENDLEMAN J D, RYALS R E. Spacecraft operator duty of care [C]. AIAA Space 2011 Confer-ence and Exposition，Long Beach,2011,1:28-44.[9]MONTENBRUCK O，VAN HELLEPUTTE T，KROES R， et al.．Reduced dynamic orbit determination using GPS code and carrier measure-ments[J]．Aerospace Science and Technology，2005，9:261-71.[10]BAE T S．Near real-time precise orbit determination of low earth orbit satellites using an optimal GPS triple-differencing technique[R]．Columbus：Ohio State University，2006:86-92.[11]SVEHLA D， ROTHACHER M．Kinematic and reduced-dynamic precise orbit determination of low earth orbiters [J]．Advances in Geosciences，2003(1):47-56.[12]VALLADO D, AGAPOV V．Orbit determination results from optical measurements [C]. AIAA/AAS Astrodynamics Specialist Conference，AIAA2010-7525,Ontario,2010.[13]HIROSE C, KUDO N, MATSUDE I, et al.. Valuation of the TLE prediction errors for conjunction assessment [C]. Proceedings of the International Astronautical Congress, Prague,2010.[14]CAROLIN F，SCHILDKNECHT T. Accuracy of two-line-element data for geostationary and high-eccentricity orbits [J].Journal of Guidance, Control, and Dynamics，September-October, 2012，35(5)：1483-1491.[15]CAROLIN F, SCHILDKNECHT T. Orbit propagation and validation with angle-only observations[C]. AIAA/AAS Astrodynamics Specialist Conference,Toronto,2010.[16]李济生.航天器轨道确定[M].北京：国防工业出版社，2003.LI J SH. Satellite Precise Orbit Determination[M]. BeiJing: National Defence Industry Press，2003.(in Chinese) [17]FRUH C, SCHILDKNECHT T, HINZE A, et al.. Optical observation campaign in the framework of the ESA space surveillance system precursor service [C]. Proceedings of the European Space Surveillance Conference, Marid,ESA, 2011.

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