| 机载惯性/天文组合导航研究 |
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| 引用本文： | 岳亚洲,田宇,张晓冬.机载惯性/天文组合导航研究[J].光学与光电技术,2008,6(2):1-5. |
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| 作者姓名： | 岳亚洲 田宇 张晓冬 |
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| 作者单位： | 飞行自动控制研究所,陕西,西安,710065 |
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| 摘 要： | 为了满足军用机载平台导航系统对自主性、抗干扰、长航时、高可靠性的要求，设计了一种机载／天文组合导航系统。该系统以激光捷联惯导系统为核心，辅以自主性高、可靠性高的天文导航系统。试验表明，采取一定的技术措施，定位精度有望达到500m，定向精度有望达到30″。
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| 关 键 词： | 组合导航 惯性导航 天文导航 |
| 收稿时间： | 2007/10/9 |
Investigation on Airborne Inertial/Celestial Integrated Navigation |
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| YUE Ya-zhou,TIAN Yu,ZHANG Xiao-dong.Investigation on Airborne Inertial/Celestial Integrated Navigation[J].optics&optoelectronic technology,2008,6(2):1-5. |
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| Authors: | YUE Ya-zhou TIAN Yu ZHANG Xiao-dong |
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| Affiliation: | YUE Ya-zhou TIAN Yu ZHANG Xiao-dong ( Flight Automatic Control Research Institute,Xi\'an 710065,China ) |
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| Abstract: | In order to satisfy the requirements for self-contained, anti-jamming, long flight-time and high reliability, the inertial/celestial integrated navigation system was designed for the military airborne platform. The system is consisted of the laser strap-down inertial navigation unit and the celestial navigation unit. The celestial navigation unit is used to update the positioning of the inertial navigation unit with which drifts with time. The integrated system is independent of satellite navigation. The ex... |
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| Keywords: | integrated navigation inertial navigation celestial navigation |
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