北斗卫星超短弧运动学定轨方法优化与试验分析

郭睿; 陈金平; 朱陵凤; 唐桂芬; 吴晓莉

doi:10.11947/j.AGCS.2017.20160361

测绘学报 >

2017 , Vol. 46 >Issue 4: 411 - 420

DOI: https://doi.org/10.11947/j.AGCS.2017.20160361

大地测量学与导航

北斗卫星超短弧运动学定轨方法优化与试验分析

郭睿 ,
陈金平 ,
朱陵凤 ,
唐桂芬 ,
吴晓莉

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1. 北京卫星导航中心, 北京 100094;
2. 大地测量与地球动力学国家重点实验室, 湖北武汉 430077

郭睿(1982-),男,博士,高级工程师,研究方向为卫星导航、精密定轨与时间同步。

收稿日期: 2016-07-15

修回日期: 2017-02-11

网络出版日期: 2017-05-05

基金资助

国家自然科学基金（41204022；41374038）；大地测量与地球动力学国家重点实验室开放研究基金（SKLGED2017-3-3-E）

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Kinematic Orbit Determination Method Optimization and Test Analysis for BDS Satellites with Short-arc Tracking Data

GUO Rui ,
CHEN Jinping ,
ZHU Lingfeng ,
TANG Guifen ,
WU Xiaoli

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1. Beijing Satellite Navigation Center, Beijing 100094, China;
2. State Key Laboratory of Geodesy and Earth's Dynamics, Wuhan 430077, China

Received date: 2016-07-15

Revised date: 2017-02-11

Online published: 2017-05-05

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摘要

针对北斗卫星姿轨控后的轨道快速确定难题，系统地研究了基于多项式拟合和基于星历拟合两种运动学定轨方法，推导建立了相应的运动学定轨模型。同时针对接收机系统差和顽固多径问题，利用基于并置比对的接收机系统差解算方法和CNMC的多径削弱方法，实现了超短弧跟踪条件下接收机数据质量的有效控制。利用北斗GEO/IGSO/MEO卫星的实测伪距数据进行了试验验证，结果表明在10 min超短弧跟踪条件下，GEO、IGSO和MEO卫星的运动学定轨位置精度分别为3.27 m、8.19 m和5.90 m，实现了超短弧跟踪条件下的北斗卫星快速定轨，满足了卫星机动期间的北斗RDSS服务对轨道精度的需求，为北斗RDSS服务走向全球提供了技术支撑。

关键词： 北斗卫星导航系统; 精密定轨; 轨道机动; 运动学法定轨; 多径误差

本文引用格式

郭睿 , 陈金平 , 朱陵凤 , 唐桂芬 , 吴晓莉 . 北斗卫星超短弧运动学定轨方法优化与试验分析[J]. 测绘学报, 2017 , 46(4) : 411 -420 . DOI: 10.11947/j.AGCS.2017.20160361

Abstract

Rapid orbit recovery is a puzzle for the BDS satellites after orbit maneuvers. Two kinematic orbit determination methods are studied, with two orbit determination models being established. The receiver system error and serious multipath error exist in the BDS system. The co-location method is proposed to estimate and calibrate the receiver system errors. A CNMC (code noise and multipath correction) method is introduced to weaken the multipath error. Therefore the data quality is controlled efficiently for the receivers in the short tracking arc. The GEO/IGSO/MEO real data is emploied to carry out tests and validation. Using 10 min short tracking arc, the kinematic precise orbit determination accuracy is about 3.27 m for the GEOs, and 8.19 m for the IGSOs, and 5.9 m for the MEOs. Rapid orbit determination is achieved, which satisfying the orbit requirements from the BDS RDSS services. The kinematic precise orbit determination method also supports the RDSS service walking up to the global world.

Key words： BDS; precise orbit determination; orbit maneuver; kinematic precise orbit determination; multipath error

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