KONG Yao, SUN Baoqi, YANG Xuhai, CAO Fen, HE Zhanke, YANG Haiyan. Precision Analysis of BeiDou Broadcast Ephemeris by Using SLR Data[J]. Geomatics and Information Science of Wuhan University, 2017, 42(6): 831-837. DOI: 10.13203/j.whugis20140856
Citation: KONG Yao, SUN Baoqi, YANG Xuhai, CAO Fen, HE Zhanke, YANG Haiyan. Precision Analysis of BeiDou Broadcast Ephemeris by Using SLR Data[J]. Geomatics and Information Science of Wuhan University, 2017, 42(6): 831-837. DOI: 10.13203/j.whugis20140856

Precision Analysis of BeiDou Broadcast Ephemeris by Using SLR Data

Funds: 

The National Natural Science Foundation of China 41104021

The National Natural Science Foundation of China 11173026

The National Natural Science Foundation of China 41574003

the West Light Foundation of the Chinese Academy of Sciences 2012ZD150

the West Light Foundation of the Chinese Academy of Sciences 2013YB10

the International Global Monitoring and Assessment System (iGMAS) 

the Public Welfare Science Research Program of Surveying, Mapping and Geoinformation 

the Science and Technology Innovation Project of Shaanxi Administration of Surveying, Mapping and Geoinformation 

More Information
  • Author Bio:

    KONG Yao, PhD, specializes in GNSS orbit determination. E-mail: michale08@163.com

  • Received Date: March 28, 2015
  • Published Date: June 04, 2017
  • Satellite Laser Ranging (SLR), is completely independent of microwave measurement, and offers an indispensable tool for external validation of GNSS broadcast ephemeris. Currently, all satellites in the BeiDou Satellite Navigation System (BDS) are equipped with laser ranging reflector arrays enabling high-precision two way ranging measurements. Based on SLR data from BeiDou satellites collected in the period April 2013 to July 2014, the broadcast ephemeris of BDS were validated using SLR data. The approximate equation of SLR residual for the BDS GEO satellites were derived, and the SLR residual characteristic for BDS IGSO and MEO satellites under different attitude modes were analyzed. The validation results show that, the orbit error of C01, C08, C10 and C11 are 0.97 m, 0.43 m, 0.41 m and 0.41 m respectively.
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