| INS/GNSS/CNS组合导航系统仿真研究 |
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| 引用本文： | 敖宏奎,王宏力,张明源. INS/GNSS/CNS组合导航系统仿真研究[J]. 弹箭与制导学报, 2007, 27(5): 78-80,84 |
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| 作者姓名： | 敖宏奎 王宏力 张明源 |
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| 作者单位： | 第二炮兵工程学院,西安,710025 |
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| 摘 要： | 研究了INS／GNSS／CNS组合导航系统的原理和特点。分析并建立了组合导航系统的误差模型，采用了平台失准角、INS与GNSS的位置之差和速度之差作为观测量进行仿真计算。仿真结果表明：采用天文导航系统对弹道导弹的INS／GNSS组合导航系统进行辅助将大幅度提高导弹的导航精度，具有重要的实际意义。
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| 关 键 词： | 组合导航 惯性导航系统 卫星导航定位系统 天文导航系统 卡尔曼滤波 |
| 收稿时间： | 2006-12-13 |
| 修稿时间： | 2007-01-23 |
Simulation of INS/GNSS/CNS Integrated Navigation |
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| AO Hong-kui,WANG Hong-li,ZHANG Ming-yuan. Simulation of INS/GNSS/CNS Integrated Navigation[J]. Journal of Projectiles Rockets Missiles and Guidance, 2007, 27(5): 78-80,84 |
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| Authors: | AO Hong-kui WANG Hong-li ZHANG Ming-yuan |
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| Abstract: | The theory and characteristics of INS/GNSS/CNS integrated navigation system has been investigated, and the error model of integrated navigation system has been analyzed and modeled. The method of the error-angles of the platform,the position differences of INS and GNSS,the velocity differences of INS and GNSS has been used as measurements in simulation. The result of simulation indicates ballistie missile INS/GNSS integrated navigation system aided with celestial navigation can substantially improve the navigation precision and has profound practice significance. |
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| Keywords: | integrated navigation INS GNSS CNS Kalman filter |
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