Methods of rapid orbit forecasting after maneuvers for geostationary satellites  

作　　者：YANG XuHai LI ZhiGang FENG ChuGang GUO Ji SHI HuLi AI GuoXiang WU FengLei QIAO RongChuan 

机构地区：[1]National Time Service Center(NTSC),Chinese Academy of Sciences,Xi’an 710600,China [2]National Astronomical Observatories,Chinese Academy of Sciences,Beijing 100012,China [3]Graduate University of Chinese Academy of Sciences,Beijing 100049,China [4]Beijing Aerospace Control Center(BACC),Beijing 100094,China

出　　处：《Science China(Physics,Mechanics & Astronomy)》2009年第3期333-338,共6页中国科学：物理学、力学、天文学（英文版）

基　　金：Supported by the National High Technology Research and Development Program of China (Grant No. 2006AA12Z322); the National Basic Research Program of China (Grant No. 2007CB815503);the West Light Program of Chinese Academy of Sciences (Grant No. 2007LH01)

摘　　要：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 statis-tical 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 meas-urement 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.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.

关 键 词：geostationary SATELLITE SATELLITE MANEUVER ORBIT forecasting 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]