Methods of rapid orbit forecasting after maneuvers for geostationary satellites
Methods of rapid orbit forecasting after maneuvers for geostationary satellites
复制标题
静止卫星机动后快速轨道预报方法
DOI：
10.1007/s11433-009-0066-5
复制
发表时间：
2009-03
期刊：
影响因子：
--
通讯作者：
Yang XuHai
中科院分区：
文献类型：
--
作者：
Shi HuLi;Feng ChuGang;Wu FengLei;Guo Ji;Ai GuoXiang;Li ZhiGang;Qiao RongChuan;Yang XuHai
地球同步（GEO）卫星可以用作导航卫星，但是存在机动频繁发生并且力难以建模的问题。基于转移定轨技术，在无机动力的情况下，采用统计定轨方法可以获得高精度的预报轨道。机动开始后，预测轨道很快就会失效，机动结束后需要很长时间才能获得有效轨道。为了提高星历的可用性，研究了机动后的快速轨道预报方法。首先，分析了GEO卫星在机动情况下的运动，该运动是基于轨道测量系统通过转移获得的观测值。当静止轨道卫星机动后处于自由状态时，利用短弧观测进行轨道预报。假设系统偏差和各站偏差均为常数，由长弧观测定轨得到。这样，用统计定轨方法只需解出6个轨道根数，就可以很快得到高精度的星历。对中国卫星一号的短弧观测轨道预报结果表明，在有跟踪网的情况下，15 min短弧观测轨道预报精度（O-C均方根值）可达5 m左右，30 min短弧观测轨道预报精度可达3 m左右。
A geostationary (GEO) satellite may serve as a navigation satellite, but there is a problem that maneuvers frequently occur and the forces are difficult to model. Based on the technique of determining satellite orbits by transfer, a predicted orbit with high accuracy may be achieved by the method of statistical orbit determination in case of no maneuver force. The predicted orbit will soon be invalid after the maneuver starts, and it takes a long time to get a valid orbit after the maneuver ends. In order to improve ephemeris usability, the method of rapid orbit forecasting after maneuvers is studied. First, GEO satellite movement is analyzed in case of maneuvers based on the observation from the orbit measurement system by transfer. Then when a GEO satellite is in the free status just after maneuvers, the short arc observation is used to forecast the orbit. It is assumed that the common system bias and biases of each station are constant, which can be obtained from orbit determination with long arc observations. In this way, only 6 orbit elements would be solved by the method of statistical orbit determination, and the ephemeris with high accuracy may be soon obtained. Actual orbit forecasting with short arc observation for SINOSAT-1 satellite shows that, with the tracking network available, the precision of the predicted orbit (RMS of O-C) can reach about 5 m with 15 min arc observation, and about 3 m with 30 min arc observation.
登录
查看更多内容
DOI：
10.1016/b978-012683630-1/50024-2
发表时间：
2004
期刊：
--
影响因子：
--
作者：
B. Tapley;B. Schutz;G. Born
通讯作者：
B. Tapley;B. Schutz;G. Born
DOI：
10.1007/s11433-009-0057-6
发表时间：
2009-03
期刊：
Science in China Series G-Physics Mechanics & Astronomy
影响因子：
--
作者：
Al GuoXiang;Yang XuHai;Feng ChuGang;Si HuLi;Qiao RongChuan;Li ZhiGang
通讯作者：
Li ZhiGang
DOI：
10.1016/b978-0-12-683630-1.x5019-x
发表时间：
2004-06
期刊：
--
影响因子：
--
作者：
B. Tapley;Bob E. Schutz;George H. Born
通讯作者：
B. Tapley;Bob E. Schutz;George H. Born
DOI：
10.1088/1009-9271/8/6/01
发表时间：
2008-01-01
期刊：
CHINESE JOURNAL OF ASTRONOMY AND ASTROPHYSICS
影响因子：
--
作者：
Ai, Guo-Xiang;Shi, Hu-Li;Cai, Xian-De
通讯作者：
Cai, Xian-De
DOI：
10.1109/freq.2007.4319209
发表时间：
2007-10
期刊：
2007 IEEE International Frequency Control Symposium Joint with the 21st European Frequency and Time Forum
影响因子：
--
作者：
Yang Xuhai;Li Zhigang;Hua Aihui
通讯作者：
Yang Xuhai;Li Zhigang;Hua Aihui