基于CEI的航天器交会对接段的轨道监控  

CEI-based Real-time Orbit Determination of Spacecraft Rendezvous and Docking in the Course of Long Distance Navigation

作　　者：李晓杰[1] 杜兰[1] 黄金[2] 潘玲[3] 

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 [3]中国人民解放军,成都610036

出　　处：《中国空间科学技术》2010年第6期24-30,共7页Chinese Space Science and Technology

基　　金：国家自然科学基金(40974019)

摘　　要：文章探讨了CEI技术在飞船交会对接远程导引段的实时监控的能力,采用单一绝对滤波器的方案进行实时轨道计算,仿真结果表明:采用滤波稳定后固定模糊度的方法可以提高轨道的滤波解精度,相对轨道位置精度可达十米级,速度精度可达厘米每秒级,满足远程导引段的精度指标。Connected the characteristic of short element interferometry （CEI） is a passive angular tracking method with baselines, flexible network distribution and nearly real-time processing.It can make real time and precise orbit determination for spacecraft rendezvous and docking. CEI based real-time orbit determination in the course of long distance navigation of spacecraft rendezvous and docking was discussed, and the method of absolute filter was adopted. The simulation results indicat that the method of fixing integer ambiguity after the filter is stable, anc can improve the orbit precision. The relative position precision can reach the magnitude of 10m and the relative velocity precision reaches the magnitude of lcm per second.

关 键 词：中短基线相位干涉测量 交会对接 整周模糊度 扩展卡尔曼滤波 航天器 

分 类 号：V526[航空宇航科学与技术—人机与环境工程]