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Methods of rapid orbit forecasting after maneuvers for geostationary satellites

Science China(Physics,Mechanics & Astronomy) 2009年第3期52卷 333-338页

作者： YANG XuHai LI ZhiGang FENG ChuGang GUO Ji SHI HuLi AI GuoXiang WU FengLei QIAO RongChuan National Time Service Center(NTSC) Chinese Academy of SciencesXi’an 710600China National Astronomical Observatories Chinese Academy of SciencesBeijing 100012China Graduate University of Chinese Academy of Sciences Beijing 100049China Beijing Aerospace Control Center(BACC) Beijing 100094China

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.

关键词： geostationary satellite satellite maneuver orbit forecasting

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An analysis of the wide area differential method of geostationary orbit satellites

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Science China(Physics,Mechanics & Astronomy) 2009年第2期52卷 310-314页

作者： CAI ChengLin1,2,3?, LI XiaoHui1 & WU HaiTao1 1 National Time Service Center, Chinese Academy of Sciences, Lintong 710600, China 2 Hunan Institute of Humanities, Science and Technology, Loudi 417000, China 3 Graduate University of Chinese Academy of Sciences, Beijing 100049, China National Time Service Center Chinese Academy of Sciences Lintong China Hunan Institute of Humanities Science and Technology Loudi China Graduate University of Chinese Academy of Sciences Beijing China

This work aims to obtain a wide area differential method for geostationary orbit (GEO) constellation. A comparison between the dilution of precision (DOP) of four-dimensional (4D) calculation including sa- tellite clock errors and ephemeris errors and that of three-dimensional (3D) calculation only including ephemeris errors with the inverse positioning theory of GPS shows the conclusion that all the 3D PDOPs are greatly reduced. Based on this, a basic idea of correcting satellite clock errors and ephem- eris errors apart is put forward, and moreover, a specific method of separation is proposed. Satellite clock errors are separated in a master station with time synchronization, and all the remaining pseu- do-range errors after the satellite clock errors have been deducted are used to work out ephemeris corrections of all GEO satellites. By a comparative analysis of user positioning accuracy before and after differential, the wide area differential method is verified to be quite valid for GEO constellation.

关键词： geostationary orbitsatellite dilution of precision satellite ephemeris errors satellite clock errors wide area differential method

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Error Analysis of Orbit Determination for the geostationary Satellite with Single Station Antenna Tracking Data

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Positioning 2011年第4期2卷 135-144页

作者： Chingiz Hajiyev Melih Ata 不详

In the study, position and velocity values of a geostationary satellite are found. When performing this, a MATLAB algorithm is used for Runge-Kutta Fehlberg orbit integration method to solve spacecraft’s position and velocity. Integrated method is the solution for the systems which mainly work with a single station. Method provides calculation of azimuth, elevation and range data by using the position simulation results found by RKF. Errors of orbit determination are analysed. Variances of orbit parameters are chosen as the accuracy criteria. Analysis results are the indicator of the method’s

关键词： Orbit Determination geostationary Satellite Single Station Antenna Error Analysis

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GEOSTIONARY METEOROLOGICAL SATELLITE FY-2 OF CHINA

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空间科学学报 1998年第S1期18卷 71-74页

作者： FANG Zong-yi DONG Chao-hua (Natzonal Satellite Meteorological Center, China Meteorological Administrution, Beijing 100081)

The first FY-2 geostationary metebrological satellite was lauched June 10, 1997flom Xichang satellite launching center by Long March-3 launching vehicle.This paper is to provide users with a brief description of the s... 详细信息

关键词： geostationary meteorological satellite Radiometer Signal charactcristics

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激光清理地球静止轨道碎片的天基平台控制方法

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系统工程与电子技术 2015年第10期37卷 2352-2357页

作者：韩威华甘庆波陈险峰朱政帆航天指挥控制中心北京100094 中国科学院光电研究院北京100094

推导了天基高能激光清理作用地球静止轨道(geostationary earth orbit,GEO)碎片的最佳角度解析关系,分析了天基平台接近碎片过程以及相对碎片空间位置和姿态的相互影响,建立了激光清理GEO碎片的天基平台的轨道姿态耦合动力学模型,考虑... 详细信息

推导了天基高能激光清理作用地球静止轨道(geostationary earth orbit,GEO)碎片的最佳角度解析关系,分析了天基平台接近碎片过程以及相对碎片空间位置和姿态的相互影响,建立了激光清理GEO碎片的天基平台的轨道姿态耦合动力学模型,考虑了终端状态、安全距离、保持连续观测、控制和状态变量幅值等约束条件,以推进燃料消耗最省为性能指标,依据极小值原理推导了耦合控制方案的最优性内部结构标准,基于hp自适应伪谱法对仿真场景进行了寻优求解和分析验证。仿真结果表明,耦合优化控制方案合理可行,对未来天基激光清理GEO碎片的工程实施具有一定参考价值。

关键词：地球静止轨道碎片清理天基激光耦合优化控制 geostationary earth orbit (GEO)

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