| 陆地导航中GNSS/陀螺仪组合实时测姿方法 |
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| 引用本文： | 甘雨,隋立芬,戚国宾,张鹤.陆地导航中GNSS/陀螺仪组合实时测姿方法[J].武汉大学学报(信息科学版),2015,40(3):379-383. |
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| 作者姓名： | 甘雨 隋立芬 戚国宾 张鹤 |
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| 作者单位： | 1信息工程大学地理空间信息学院河南 郑州 450052 |
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| 基金项目： | 国家自然科学基金资助项目(41274016,41174006,40974010)~~ |
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| 摘 要： | 在陆地导航系统中使用GNSS/INS组合导航会增加系统成本,多天线GNSS测姿精度受基线长度影响,且存在的模糊度固定问题。本文提出仅利用一个陀螺仪和单天线GNSS组合来进行实时测姿。先由单天线GNSS计算姿态角3参数,航向角为陆地导航的关键参数,为此将陀螺信息与GNSS导出的航向角进行融合。分析了单天线测姿在载体静止或低速运动时精度很差的原因,提出了在组合滤波中进行解决的方案。推导了GNSS和陀螺信息融合的滤波模型,将陀螺仪信息作为状态模型的控制输入,以GNSS航向为滤波观测值。实验结果表明,GNSS/陀螺仪组合计算的航向角精度和可靠性相对GNSS测姿结果均有很大提升。
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| 关 键 词： | 陆地导航 陀螺仪 姿态 航向角 Kalman滤波 |
| 收稿时间： | 2013-06-05 |
A Real-Time Attitude Determination Approach for Land Navigation Based on GPS/Gyroscope Integration |
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| GAN Yu;SUI Lifen;QI Guobing;ZHANG He.A Real-Time Attitude Determination Approach for Land Navigation Based on GPS/Gyroscope Integration[J].Geomatics and Information Science of Wuhan University,2015,40(3):379-383. |
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| Authors: | GAN Yu;SUI Lifen;QI Guobing;ZHANG He |
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| Institution: | 1Institute of Surveying and Mapping,Information Engineering University Zhengzhou 450052 China |
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| Abstract: | It is wasteful to use a GNSS/INS integrated system for land navigation.Multi-antenna GNSS attitude determination is closely related to the baseline length and is confronted with the ambiguity fixing problem. This paper proposes a single-antenna GNSS /gyroscope integrated attitude determination method that meets this challenge. The three attitude parameters are firstly calculated bysingle-antenna GNSS and then the key parameter in land navigation，the heading angle，the gyro information，and GNSS-derived heading are integrated. The accuracy degration problem in single-antenna GNSS during the stationary or low-velocity conditions is investigated and solved during the integration filtering process.The filtering model for GNSS/Gyro integration is derived;gyro information is used as the control input in the state model and the GNSS heading angle is measured. Experimental results show that，the accuracy and reliability of the GNSS/Gyro heading is much higher using the proposed method than that of GNSS attitude determination alone. |
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