| 基于星光导航分离陀螺仪漂移误差方法研究 |
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| 引用本文： | 郭庆树,鲜勇,刘清.基于星光导航分离陀螺仪漂移误差方法研究[J].飞行力学,2010,28(6). |
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| 作者姓名： | 郭庆树 鲜勇 刘清 |
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| 作者单位： | 第二炮兵工程学院603教研室,陕西,西安,710025 |
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| 摘 要： | 星光/惯性组合制导方式集中了两种方式的优点,可在导弹飞出大气层后通过对导航星的观测校正陀螺仪误差系数。在研究了星光导航的特点和陀螺仪误差特性的基础上,提出了通过旋转弹体观测特定位置的导航星,利用星光导航系统分离陀螺仪漂移误差系数的方法。结果表明:利用导航恒星高精度基准可以分离陀螺仪漂移误差系数,准确地确定陀螺仪漂移误差模型,对于提高导弹的精度具有重要意义。
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| 关 键 词： | 星光导航 陀螺仪漂移 误差分离 |
Study of an approach to separate gyroscope drift error based on stellar navigation |
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| GUO Qing-shu,XIAN Yong,LIU Qing.Study of an approach to separate gyroscope drift error based on stellar navigation[J].Flight Dynamics,2010,28(6). |
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| Authors: | GUO Qing-shu XIAN Yong LIU Qing |
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| Institution: | GUO Qing-shu,XIAN Yong,LIU Qing(Faculty 603,The Second Artillery Engineering College,Xi'an 710025,China) |
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| Abstract: | Stellar-inertial integrated guidance possesses the advantages of both the stellar guidance system and the inertial guidance system,and possesses the capacity of correcting the gyroscope error coefficient through observation on the navigation stars when a missile flies out of the atmosphere.Through observation on selected stars by rotating the missile,a method for separating the gyroscope drift error coefficient is proposed by the stellar navigation system,which based on studying of the characters of stellar... |
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| Keywords: | stellar navigation gyroscope drift error separation |
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