导航星座整网自主定轨的动力学短弧段伪逆平差法  

Autonomous Orbit Determination of Navigation Constellation Based on Short-Term Dynamics and Pseudo-Inverse Adjustment

作　　者：李灏霖 王玲[1] 黄文德[2,3] 周一帆 LI Hao-lin;WANG LingI;HUANG Wen-de;ZHOU Yi-fan(School of Electrical and Information Engineering,Hunan University,Changsha 410012,China;College of Mechatronics Engineering and Automation,National University of Defense Technology,Changsha 410073,China;Shanghai Astronomical Observatory,Chinese Academy of Sciences,Shanghai 200030,China)

机构地区：[1]湖南大学电气与信息工程学院,长沙410012 [2]国防科技大学机电工程与自动化学院,长沙410073 [3]中国科学院上海天文台,上海200030

出　　处：《宇航学报》2018年第8期863-869,共7页Journal of Astronautics

基　　金：中国博士后科学基金(2015M580365)

摘　　要：针对传统静态自由网平差进行自主定轨存在的秩亏问题,提出一种卫星动力学短弧段定轨和自由网伪逆平差理论相结合的自主定轨算法。该算法以导航星座星间链路(ISL)双向测距为基础,利用伪逆平差法,解决整网位置解算起算数据不足带来的秩亏问题;同时,利用轨道动力学建立不同历元之间状态转移关系,解决单历元平差无法对速度分量进行有效估计的问题。仿真结果表明,自主运行90天,平均用户测距精度(URE)小于1 m(2σ),优于导航星座自主运行指标要求,验证了本文算法的有效性。This paper proposes an autonomous orbit determination algorithm combining the short-term dynamics orbit determination technique and the free-net pseudo-inverse adjustment using the measurements of the bi-directional distance measurement of the inter-satellite link（ISL） in a navigation constellation. This algorithm solves the problem of the rank defect because of the lack of the start information of the position calculation by pseudo-inverse adjustment,at the same time,sets up the state transition between the epoch steps using the orbit dynamics to solve the problem of the velocity calculation. The results show that,after running autonomously for 90 days,the satellites＇ average user range error（URE）is less than 1 m（2σ）,better than the precision requirements of the autonomous operation of the navigation constellation,so the efficiency of the algorithm is verified.

关 键 词：导航星座 自主定轨 整网平差 动力学 伪逆 

分 类 号：TN967.1[电子电信—信号与信息处理]