基于CEI的飞船交会对接远程导引段的轨道确定方案  

CEI-based Scheme of Orbit Determination of a Course under Remote Guidance Leading to Spacecraft Rendezvous and Docking

作　　者：李晓杰[1] 杜兰[1] 黄金 

机构地区：[1]解放军信息工程大学测绘学院 [2]61768部队

出　　处：《天文研究与技术》2011年第1期29-35,共7页Astronomical Research & Technology

基　　金：国家自然科学基金(40974019)资助

摘　　要：探讨了CEI技术在飞船交会对接远程导引段的高精度定轨与实时监控的能力。仿真结果表明:精密定轨中采用可视弧段较长的单站可使相对位置精度达百米以内,速度达厘米/秒级。采用单一绝对扩展卡尔曼滤波器的方案进行实时轨道计算,采用滤波稳定后固定模糊度的方法可以使相对轨道位置精度达十米级,速度精度达厘米/秒级,事后及实时的轨道精度均满足远程导引段的精度指标。Rendezvous and docking between Shenzhou spaceship and target spacecraft are the goals in the next phase of Chinese space exploration. Connected-element interferometry（CEI）is a method of passively tracking directions and has the advantages of short baselines, flexible station-network distribution, and nearly real-time processing. It allows real-time precision orbit determination for spacecraft rendezvous and docking. We discuss the CEI-based orbit determination of a course under remote guidance leading to spacecraft rendezvous and docking. Our simulation results indicate that the precisions in relative positions between two spacecrafts can be within 100 m and in those relative velocities can be within about one centimeter per second if observational data from a station with long visible arcs （appearing to the spacecrafts）are used. We further use the Extended Kalman Filter to determine real-time （absolute-position）orbits. We find that the method of fixing integer ambiguity after the filtering is stable so that it sets the relative position precision to be 10 m, and sets the relative velocity precision to be within about one centimeter per second. The precisions meet the requirement for a course under remote guidance.

关 键 词：中短基线相位干涉测量 交会对接 整周模糊度 精密轨道确定 扩展卡尔曼滤波 

分 类 号：P222[天文地球—大地测量学与测量工程]