| 基于引力场不对称性的三体系统轨道自主导航 |
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| 作者姓名： | 王亚敏 刘银雪 蒋峻 孙煜坤 张永合 |
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| 作者单位： | 上海微小卫星工程中心, 上海 201203;中国科学院微小卫星重点实验室, 上海 201203,北京理工大学 宇航学院, 北京 100081,上海微小卫星工程中心, 上海 201203;中国科学院微小卫星重点实验室, 上海 201203,上海微小卫星工程中心, 上海 201203;中国科学院微小卫星重点实验室, 上海 201203,上海微小卫星工程中心, 上海 201203;中国科学院微小卫星重点实验室, 上海 201203 |
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| 基金项目： | 国家重点研发计划（2016YFB0501103） |
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| 摘 要： | 以月球背面的中继通信为背景,提出了基于三体系统引力场不对称特性的星–星测距自主定轨方案。该方案以环月极轨卫星和地–月L2点Halo轨道卫星组成中继通信网,以实现对月球两极和背面的覆盖。通过采集极轨卫星与Halo轨道卫星的测距信息,结合卡尔曼滤波在日–地–月动力学模型下获得两颗卫星的绝对轨道。数值仿真结果表明:本文方法能将导航的位置精度和速度精度分别提高到百米和厘米/秒量级。该自主导航方法还可以扩展到不规则引力场小天体附近星群运动的自主导航。
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| 关 键 词： | 星间测距 自主导航 地-月三体 中继通信 深空探测 |
| 收稿时间： | 2016/11/1 0:00:00 |
| 修稿时间： | 2016/12/6 0:00:00 |
Autonomous Navigation of Three-Body Trajectory Based on Asymmetric Gravity Field |
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| Authors: | WANG Yamin LIU Yinxue JIANG Jun SUN Yukun and ZHANG Yonghe |
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| Institution: | Shanghai Engineering Center for Microsatellites, Shanghai 201210, China;Key Laboratory of Microsatellite, Chinese Academy of Sciences, Shanghai 201210, China,School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China,Shanghai Engineering Center for Microsatellites, Shanghai 201210, China;Key Laboratory of Microsatellite, Chinese Academy of Sciences, Shanghai 201210, China,Shanghai Engineering Center for Microsatellites, Shanghai 201210, China;Key Laboratory of Microsatellite, Chinese Academy of Sciences, Shanghai 201210, China and Shanghai Engineering Center for Microsatellites, Shanghai 201210, China;Key Laboratory of Microsatellite, Chinese Academy of Sciences, Shanghai 201210, China |
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| Abstract: | In this paper,the autonomous orbital determination method with the background of communication relay net for the Moon is investigated. Two satellites,distributing on a lunar polar orbit and an Earth-Moon L2 Halo orbit,are proposed to cover the far side of the Moon and the lunar polar area. Based on the asymmetric three-body gravity field,the absolute orbital determination can be done by the sole satellite-satellite ranging. The autonomous orbital determination will contribute significantly to the autonomous management of deep space spacecraft. Numerical simulation indicates that the position error and velocity error can be reduced to the order of 100 m and 1cm/s respectively. This orbital determination method can be expanded to the autonomous navigation of multiple satellites movements around an irregular asteroid. |
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| Keywords: | satellite-to-satellite tracking autonomous navigation Earth-Moon system communication relay deep space exploration |
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