| 一种亚轨道飞行器再入段组合导航方法 |
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| 引用本文： | 杨峰,程承,张共愿,程咏梅.一种亚轨道飞行器再入段组合导航方法[J].宇航学报,2010,31(3). |
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| 作者姓名： | 杨峰 程承 张共愿 程咏梅 |
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| 作者单位： | 西北工业大学自动化学院,西安,710072 |
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| 基金项目： | 国家自然科学基金重点项目，青年项目，航天科技创新基金，航空基金 |
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| 摘 要： | 针对亚轨道飞行器再入飞行段的环境特性,设计了由INS、GPS、CNS组成的容错型组合导航系统,该系统能根据不同飞行阶段选择相应的传感器组合方案,将处于运行状态且无故障的子系统信息自动地实现最优融合。仿真结果表明,所设计系统具有良好的容错性,并达到了较高的导航精度。
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| 关 键 词： | 惯性导航 亚轨道飞行器 再入返回飞行段 组合导航 |
Simulation Research of Sub-orbital Vehicle Re-entry Flight Segment Navigation Technology |
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| YANG Feng,CHENG Cheng,ZHANG Gong-yuan,CHENG Yong-mei.Simulation Research of Sub-orbital Vehicle Re-entry Flight Segment Navigation Technology[J].Journal of Astronautics,2010,31(3). |
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| Authors: | YANG Feng CHENG Cheng ZHANG Gong-yuan CHENG Yong-mei |
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| Abstract: | According to circumstance of sub-orbital vehicle re-entry flight segment, this paper designed a fault tolerant integrated navigation system consisted of INS/GPS/CNS. This system can determine different sensors combination scheme according to flight phases of sub-orbital vehicle, and realize information fusion of different sensors which are running without fault. The results of simulation show that designed navigation system has a favorable fault-tolerance feature and greatly improves the precision of navigation for sub-orbital vehicle in re-entry flight segment. |
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| Keywords: | Inertia navigation Sub-orbital vehicle Re-entry flight segment Integrated navigation system |
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