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Proceedings Paper

Orbit simulation and perturbations analysis for the European satellite GOCE
Author(s): Zhicai Luo; Bo Zhong; Jinsheng Ning; Qiong Li
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Paper Abstract

A very important factor for recovering the high accuracy Earth's gravity field is the knowledge of the GOCE satellite orbit. In this paper, a 30-day arc of the GOCE satellite orbit (called the reference orbit) was simulated using dynamic orbit integration method, and the perturbation accelerations due to the lunisolar perturbations, the Earth tides, the ocean tides, the atmospheric tides, the pole tides, the relativity effects, the atmospheric drag and the solar radiation pressure were computed along the simulated orbit according to the dynamic models. Then the maximum perturbation accelerations and their percentage contribution in the sum of all accelerations due to the aforementioned forces were given and analyzed. In addition, the various variants of the satellite orbit (called the modified reference orbits) were obtained by subtracting the selected conservative forces to the satellite motion model for the reference orbit. Finally, the motion of GOCE satellite that influenced by the conservative forces were analyzed through comparing the satellite positions between the reference orbit and the modified reference orbits. The analysis results can be as a reference for the precise orbit determination and gravity field recovery of GOCE mission.

Paper Details

Date Published: 29 December 2008
PDF: 8 pages
Proc. SPIE 7285, International Conference on Earth Observation Data Processing and Analysis (ICEODPA), 72851P (29 December 2008); doi: 10.1117/12.815352
Show Author Affiliations
Zhicai Luo, Wuhan Univ. (China)
Bo Zhong, Wuhan Univ. (China)
Jinsheng Ning, Wuhan Univ. (China)
Qiong Li, Wuhan Univ. (China)


Published in SPIE Proceedings Vol. 7285:
International Conference on Earth Observation Data Processing and Analysis (ICEODPA)
Deren Li; Jianya Gong; Huayi Wu, Editor(s)

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