导航星座自主运行平行系统的轨道计算方法  

Orbit Calculation Method of Autonomous Navigation Constellation Parallel Systems

作　　者：刘友红[1,2] 黄文德[2] 盛利元[1] 

机构地区：[1]中南大学物理与电子学院,长沙410083 [2]国防科技大学机电工程与自动化学院,长沙410073

出　　处：《宇航计测技术》2015年第6期14-18,27,共6页Journal of Astronautic Metrology and Measurement

基　　金：国家自然科学基金资助项目(41274023)

摘　　要：构建一个能够与实际卫星导航系统长期保持时空一致的平行系统,可为导航星座自主运行提供一个监视与评估平台。针对建设该平行系统所需的高逼真轨道计算问题,引入平行系统理论的思想,在分析历史精密轨道的基础上,提出高精度轨道计算与预报方法。该方法以不断更新的精密轨道作为输入,利用PID增量式算法或时变加权法进行数据平滑,使得轨道计算结果始终与实际系统保持高度一致性。试验结果表明,该方法可使卫星轨道计算的结果与实际卫星轨道长期保持在分米量级。In order to provide a monitoring and evaluation platform for the navigation constellation autonomous operation,a parallel system consisting with real satellite navigation system is need to be constructed. To solve the orbit calculating problem of high-fidelity simulation system,the theory of parallel systems is introduced,and the high-precision orbit calculation and prediction method is proposed based on the analysis of historical precise orbit. To make the results of orbit calculation keep highly consistent with the actual system,the continuous renewal precise orbit is taken as inputs,also the time-varying weighting method or PID incremental algorithm is applied to data smoothing. The results show that the satellite orbit calculation results keep an order of decimeter with the actual orbit.

关 键 词：卫星导航 轨道计算 平行系统 时变加权法 PID增量式算法 

分 类 号：V412.4[航空宇航科学与技术—航空宇航推进理论与工程]