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中文摘要：
针对HY-2A卫星定轨中存在系统误差的问题,该文提出了加入经验加速度补偿系统误差。为了获得HY-2A卫星的高精度轨道,采用星载DORIS距离变率数据探索了经验加速度对定轨精度的影响。探讨了1d、3d和7d作为经验加速度周期的定轨精度差异,分析了3d作为经验加速度周期时在径向、法向和切向3个方向设置经验加速度对定轨精度的不同影响。研究结果表明：HY-2A卫星在径向和切向不存在系统误差,而在法向存在系统误差,因而在法向设置经验加速度进行力学模型补偿能够取得较好的定轨结果;3d作为经验加速度的补偿周期较为合适,不仅能够减少解算参数个数,缩短计算时间,而且径向定轨精度可达到1.00cm,满足HY-2A卫星精密定轨需求。
英文摘要：
According to the fact that there are systematic errors during the process of orbit determination of HY-2Asatellite,this paper presented a method of adding empirical acceleration to compensate orbits for these errors.In order to achieve precise orbit for HY-2Asatellite,DORIS range rate data were applied to analyze the impact of empirical acceleration on orbit determination.1day,3days and 7days orbit arcs were used as the period of empirical acceleration to determine the orbits of HY-2Asatellite,and the accuracy difference between them were investigated.Besides,the orbit accuracy were analyzed which were derived from different empirical acceleration acted on radial,along track and cross track directions respectively.The test results indicated that there were systemic error on cross track,and the optimal direction of empirical acceleration should be added on cross track;3days orbital arc was the optimal period which could reduce the number of parameters and computing time,and the radial accuracy could reach 1.00 cm and meet the needs of HY-2Asatellite.
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