Abstract
Function for LEO kinematic orbit determination was developed and integrated into the SPODS software, which has been designed and developed at Xi’an Research Institute of Surveying and Mapping. This paper presents briefly the principle and method adopted such as observation model, error correction and parameter estimation. Since there are so many epoch-related unknown parameters, the position coordinates and clock offset of onboard receiver, an approach of Least-Square method with parameter pre-eliminating is employed for parameter estimation in data processing. A set of GPS data of GRACE-A/B during Sept. 01–09 2012 was collected and experiments were carried out to evaluate the performance. The result exhibits that, by comparing with the post precise orbit product (GNV1B) from JPL, the accuracy for R component is 0.03–0.05 m, while for T and N components are 0.02–0.04 m.
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Ruan, R., Feng, L., Wu, X. (2015). Experiment and Result of Precise Kinematic Orbit Determination for LEO Satellite. In: Sun, J., Liu, J., Fan, S., Lu, X. (eds) China Satellite Navigation Conference (CSNC) 2015 Proceedings: Volume I. Lecture Notes in Electrical Engineering, vol 340. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-662-46638-4_19
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DOI: https://doi.org/10.1007/978-3-662-46638-4_19
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