| New autonomous celestial navigation method for lunar satellite |
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| 作者姓名： | 房建成 宁晓琳 |
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| 作者单位： | School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100083，China，School of Astronautics，Beijing University of Aeronautics and Astronautics，Beijing 100083，China |
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| 基金项目： | Sponsored by the National Natural Science Foundation of China(Grant No. 60174031)，China National Space Administration |
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| 摘 要： | Celestial navigation system is an important autonomous navigation system widely used for deep space exploration missions, in which extended Kalman filter and the measurement of angle between celestial bodies are used to estimate the position and velocity of explorer. In a conventional cartesian coordinate, this navigation system can not be used to achieve accurate determination of position for linearization errors of nonlinear spacecraft motion equation. A new autonomous celestial navigation method has been proposed for lunar satellite using classical orbital parameters. The error of linearizafion is reduced because orbit parameters change much more slowly than the position and velocity used in the cartesian coordinate. Simulations were made with both the cartesiane system and a system based on classical orbital parameters using extended Kalman filter under the same conditions for comparison. The results of comparison demonstrated high precision position determination of lunar satellite using this new m
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New autonomous celestial navigation method for lunar satellite |
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| FANG Jian-cheng,NING Xiao-lin.New autonomous celestial navigation method for lunar satellite[J].Journal of Harbin Institute of Technology,2003,10(3). |
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| Authors: | FANG Jian-cheng NING Xiao-lin |
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| Affiliation: | School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China |
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| Abstract: | Celestial navigation system is an important autonomous navigation system widely used for deep space exploration missions, in which extended Kalman filter and the measurement of angle between celestial bodies are used to estimate the position and velocity of explorer. In a conventional cartesian coordinate, this navigation system can not be used to achieve accurate determination of position for linearization errors of nonlinear spacecraft motion equation. A new autonomous celestial navigation method has been proposed for lunar satellite using classical orbital parameters. The error of linearizafion is reduced because orbit parameters change much more slowly than the position and velocity used in the cartesian coordinate. Simulations were made with both the cartesiane system and a system based on classical orbital parameters using extended Kalman filter under the same conditions for comparison. The results of comparison demonstrated high precision position determination of lunar satellite using this new method. |
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| Keywords: | deep space exploration lunar satellite autonomous celestial navigation extended Kalman filter |
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