| 航空制导炸弹挠性SINS/GPS组合导航系统研究 |
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| 引用本文： | 孙毅刚,郭新锋.航空制导炸弹挠性SINS/GPS组合导航系统研究[J].中国民航学院学报,2007,25(1):12-16. |
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| 作者姓名： | 孙毅刚 郭新锋 |
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| 作者单位： | 中国民航大学航空自动化学院 天津300300 |
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| 基金项目： | 中国民用航空总局科研项目 |
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| 摘 要： | 针对航空制导炸弹对低成本、高精度、高可靠性导航系统的需求,利用小型化挠性惯性测量组合(IMU)与高精度、高数据更新率的GPS-OEM板组成高精度、低成本的SINS/GPS组合导航系统。SINS和GPS采用速度、位置综合模式,利用Kalman滤波进行数据融合。最后对该组合导航系统进行了数学仿真试验和车载试验。研究表明,此低成本的组合导航系统具有精度高、成本低、可靠性好、体积小等优良指标。
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| 关 键 词： | 航空制导炸弹 组合导航系统 挠性惯性测量组合 |
| 文章编号： | 1001-5000(2007)01-0012-05 |
| 修稿时间： | 2006-06-30 |
Study on SINS/GPS Integrated Navigation System Based on Flexible IMU for Guidance Aerial Bomb |
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| SUN Yi-gang,GUO Xin-feng.Study on SINS/GPS Integrated Navigation System Based on Flexible IMU for Guidance Aerial Bomb[J].Journal of Civil Aviation University of China,2007,25(1):12-16. |
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| Authors: | SUN Yi-gang GUO Xin-feng |
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| Institution: | Aeronautic Automation college ,CA UC , Tianjin 300300 ,China |
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| Abstract: | In order to meet the need of guidance aerial bomb with low-cost,high-precision and high-reliability navigation system,a low-cost integrated navigation system is designed by using flexible IMU and GPS-OEM panel with higher positioning precision and data updating rate.The Kalman filter with position and velocity as measurement variables is used in the integrated navigation system.Lastly,mathematical simulation test and vehicle test are done to test the performance of the integrated navigation system.The results show that the low-cost integrated navigation system can work with better precision and perfect reliability. |
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| Keywords: | SINS/GPS |
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