| Reducing Influence of Gravity Model Error in Precise Orbit Determination of Low Earth Orbit Satellites |
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| 作者姓名： | GUO Jinlai HU Min ZHAO Qile GUO Daoyu |
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| 作者单位： | GUO Jinlai HU Min ZHAO Qile GUO Daoyu GUO Jinlai，School of Geodesy and Geomatics，Wuhan University，129 Luoyu Road，Wuhan 430079，China. |
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| 基金项目： | Funded by the Natural Science Foundation of China (No. 40504002)，the 973 Program of China (No. 2006CB701301). |
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| 摘 要： | Based on the orbit integration and orbit fitting method, the influence of the characters of the gravity model, with different precisions, on the movement of low Earth orbit satellites was studied. The way and the effect of absorbing the influence of gravity model error on CHAMP and GRACE satellite orbits, using linear and periodical empirical acceleration models and the so-called "pseudo-stochastic pulses" model, were also analyzed.
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| 关 键 词： | 低地球轨道卫星 精密轨道测量 重力模型误差 轨道拟合 |
| 文章编号： | 1009-5020（2007）02-105-06 |
| 收稿时间： | 18 April 2007 |
| 修稿时间： | 2007-04-18 |
Reducing influence of gravity model error in precise orbit determination of low Earth orbit satellites |
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| GUO Jinlai HU Min ZHAO Qile GUO Daoyu.Reducing Influence of Gravity Model Error in Precise Orbit Determination of Low Earth Orbit Satellites[J].Geo-Spatial Information Science,2007,10(2):105-110. |
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| Authors: | Guo Jinlai Hu Min Zhao Qile Guo Daoyu |
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| Institution: | (1) School of Geodesy and Geomatics, Wuhan University, 129 Luoyu Road, Wuhan, 430079, China |
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| Abstract: | Based on the orbit integration and orbit fitting method, the influence of the characters of the gravity model, with different
precisions, on the movement of low Earth orbit satellites was studied. The way and the effect of absorbing the influence of
gravity model error on CHAMP and GRACE satellite orbits, using linear and periodical empirical acceleration models and the
so-called “pseudo-stochastic pulses” model, were also analyzed.
Funded by the Natural Science Foundation of China (No. 40504002) and the 973 Program of China (No. 2006CB701301). |
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| Keywords: | precise orbit determination gravity model orbit fitting |
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