基于CEI定轨中整周模糊度问题处理方法的研究  

Research of Ambiguity Solution in CEI-based Orbit Determination

作　　者：李晓杰[1] 杜兰[1] 黄金[2] 

机构地区：[1]解放军信息工程大学测绘学院,郑州450052 [2]北京遥感信息研究所,北京100192

出　　处：《空间科学学报》2011年第5期659-665,共7页Chinese Journal of Space Science

基　　金：国家自然科学基金项目资助(40974019)

摘　　要：相位干涉测量是一种被动测角跟踪方法,其中的中短基线相位干涉测量(CEI)具有测角精度高、基线短、布网灵活、实时性好等特点.分析采用CEI对GEO卫星定轨时初始整周模糊度解算的可行性,由于中继卫星的初始轨道精度较低,对其定轨时必须首先解决模糊度问题.主控站具有测距功能时,利用精度较高的距离观测量来计算整周模糊度;主控站没有测距功能时,提出了固定模糊度参数的参数估计方法.仿真计算表明,系统误差小于1.0m时该方法效果较好.给出了该方法对星下点在中国上空一定经度带上的GEO卫星网的整体定轨能力,当系统误差为0.1m时,110°E卫星的迹向精度达到25m,对于80°E,140°E卫星,迹向精度分别达82m,34m.Connected-Element Interferometry （CEI） was a passive angular tracking method with the merits of high phase precision, flexible network distribution and nearly real-time processing due to short length of baselines. Firstly, feasibility of ambiguity solution in CEI-based orbit determination for GEO was analyzed. Integer ambiguity must be primarily solved in the orbit determination for TDRS because of its low initial orbit precision. It could be calculated by the high precise range measurement if the master control station could obtain range measurement, while the method of parameter estimation by fixing integer ambiguity was used without high precise range measurement. The simulation results indicated that this method was effective when the systematic error was less than 1.0m. The orbit determination precision for the satellite belt between 80°E and 140°E was gained, when the systematic error was 0.1 m, along-track positional error component of the 110°E satellite reached 25 m, while 82 m and 34 m respectively for the 80°E satellite and 140°E satellite.

关 键 词：短基线相位干涉技术 整周模糊度 中继卫星 基线阵列 

分 类 号：P228.4[天文地球—大地测量学与测量工程]