多系统GNSS卫星轨道快速积分方法

范磊; 李敏; 宋伟伟; 施闯; 王成

doi:10.11947/j.AGCS.2016.F030

测绘学报 >

2016 , Vol. 45 >Issue S2: 93 - 100

DOI: https://doi.org/10.11947/j.AGCS.2016.F030

论文

多系统GNSS卫星轨道快速积分方法

范磊 ,
李敏 ,
宋伟伟 ,
施闯 ,
王成

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武汉大学卫星导航定位技术研究中心, 武汉 430079

范磊(1989-),男,博士生,研究方向为GNSS精密定轨理论与方法。E-mail:flei_sgg@whu.edu.cn

收稿日期: 2016-11-25

修回日期: 2016-12-20

网络出版日期: 2017-05-20

基金资助

国家重点研发计划（2016YFB0501800）；国家自然科学基金（41231174；41325015；4157040195）；湖北省自然科学重点基金（2015CFA057）

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A Rapid Orbit Integration Algorithm for Multi-GNSS Satellites

FAN Lei ,
LI Min ,
SONG Weiwei ,
SHI Chuang ,
WANG Cheng

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GNSS Research Center, Wuhan University, Wuhan 430079, China

Received date: 2016-11-25

Revised date: 2016-12-20

Online published: 2017-05-20

Supported by

The National Key Research and Development Program of China (No.2016YFB0501800);The National Natural Science Foundation of China (Nos.41231174;41325015;4157040195);The Natural Science Foundation of Hubei province (No.2015CFA057)

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摘要

快速高效且高精度的轨道数值积分算法是多系统GNSS卫星联合快速精密定轨的重要基础。本文从自适应变换Admas积分步长和多卫星同步积分两方面研究了多系统GNSS卫星轨道快速积分方法。为了验证该方法的精度和效率，利用武汉大学（WHU）与欧洲定轨中心（CODE）发布的事后精密星历进行轨道动力学拟合。试验结果表明：GPS/GLONASS/BDS/Galileo 4个系统卫星平均三维RMS均优于20 mm；在不损失传统方法精度的前提下，单颗卫星平均积分与拟合耗时仅需0.09 s，较传统逐颗卫星固定步长积分算法提升了14倍，并且随着卫星数的增加，效率提升越明显。

关键词： 全球卫星导航系统; 快速轨道积分算法; 轨道拟合; 多系统

本文引用格式

范磊 , 李敏 , 宋伟伟 , 施闯 , 王成 . 多系统GNSS卫星轨道快速积分方法[J]. 测绘学报, 2016 , 45(S2) : 93 -100 . DOI: 10.11947/j.AGCS.2016.F030

Abstract

A rapid and efficient orbit numerical integration algorithm with high accuracy is needed in multi-GNSS rapid precise orbit determination. In order to improve the compute efficiency, an adaptive step-changed Admas integration method and a synchronous integration algoritm for multi-GNSS satellites are developed in this paper. To validate the precision and efficiency of the proposed method, the multi-GNSS precise orbit products calculated by Wuhan University (WHU) and Center for Orbit Determination in Europe (CODE) are used for orbit fitting. Results show that, the average 3DRMS of GPS, GLONASS, BDS and Galileo satellites are all below 20 mm. Comparing with the traditional step-fixed orbit integraion method applied for each satellite separately, the computational efficiency of the proposed method is improved significantly:without damaging the accuracy, it takes only 0.09 s for a single satellite, which is 14 times faster than the traditional method. Besides, further improvement can be achieved when the number of satellites is increased.

Key words： GNSS; rapid orbit integration algorithm; orbit fitting; multi-system

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