| 基于GPS/IMU/太阳敏感器的空间飞行器组合姿态确定 |
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| 引用本文： | 杨静,张洪钺,魏春岭.基于GPS/IMU/太阳敏感器的空间飞行器组合姿态确定[J].航天控制,2002,20(3):7-13. |
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| 作者姓名： | 杨静 张洪钺 魏春岭 |
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| 作者单位： | 1. 北京航空航天大学自动化学院,北京,100083
2. 北京控制工程研究所,北京,100080 |
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| 摘 要： | GPS定姿是GPS在空间飞行器上应用的一个重要方向 ,本文在建立GPS 惯性组件 太阳敏感器组合定姿系统的非线性模型的基础上 ,采用扩展卡尔曼滤波实现了该组合定姿方案。通过理论分析和仿真结果均验证了方案的可行性。为GPS定姿在空间飞行器的实际应用提供一定的参考。
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| 关 键 词： | 全球定位系统 姿态确定 空间飞行器 卡尔曼滤波 |
| 修稿时间： | 2002年4月5日 |
Spacecraft Integrated Attitude Determination Based on GPS/IMU/Sun Sensor |
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| Yang Jing Zhang Hongyue Beijing University of Aeronautics and Astronautics,Beijing Wei Chunling Beijing Institute of Control Engineezing,Beijing.Spacecraft Integrated Attitude Determination Based on GPS/IMU/Sun Sensor[J].Aerospace Control,2002,20(3):7-13. |
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| Authors: | Yang Jing Zhang Hongyue Beijing University of Aeronautics and Astronautics Beijing Wei Chunling Beijing Institute of Control Engineezing Beijing |
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| Institution: | Yang Jing Zhang Hongyue Beijing University of Aeronautics and Astronautics,Beijing 100083 Wei Chunling Beijing Institute of Control Engineezing,Beijing 100080 |
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| Abstract: | Attitude determination based on GPS is a key aspect of GPS used on spacecraft After nonlinear model of integrated attitude determination system based on GPS/IMU/Sun sensor is built, Extended Kalman filtering is used to realize integrated attitude determination Both theory analysis and simulation results validate the feasibility of this integrated attitude determination scheme It can be a reference for the GPS attitude determination applied on spacecraft attitude determination |
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| Keywords: | Global positioning system *Attitude determination Spacecraft Kalman filtering |
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