| 一种天文导航信息导引的星间链路自主定轨算法 |
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| 引用本文： | 林夏,林宝军,刘迎春,白涛,武国强.一种天文导航信息导引的星间链路自主定轨算法[J].宇航学报,2021,42(2):230-238. |
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| 作者姓名： | 林夏 林宝军 刘迎春 白涛 武国强 |
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| 作者单位： | 1. 上海微小卫星工程中心，上海 201203；2. 中国科学院微小卫星创新研究院，上海 201203；3. 中国科学院空天信息创新研究院，北京 100094； 4. 中国科学院大学计算机科学与技术学院，北京 100094；5. 上海科技大学信息学院，上海 201210 |
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| 基金项目： | 中国科学院国防科技创新重点部署项目（KGFZD13518008） |
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| 摘 要： | 针对星间链路自主定轨算法稳定性差，故障无法自主恢复等缺点，提出了一种天文导航信息导引算法，以提升星间链路自主定轨算法的稳定运行能力。算法利用天文导航极高的稳定性与完全自主性，确定星间链路建链指向，以保证星间稳定建链。并且，算法在天文导航中加入强跟踪滤波环节，使在轨道信息出现偏差以致星间链路中断时，具备快速的自主轨道确定及建链恢复能力。经仿真测试表明，卫星平稳运行时，利用本文算法，星间链路仰角及方位角指向误差均小于0.1°。而在轨道机动产生链路中断后，算法可使卫星快速恢复链路建链。仿真测试验证了天文导航信息导引算法的有效性。
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| 收稿时间： | 2020-07-06 |
An InterSatellite Link Autonomous
Navigation Algorithm Based on CelestialNavigation
Information Guidance |
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| LIN Xia,LIN Bao jun,LIU Ying chun,BAI Tao,WU Guo qiang.An InterSatellite Link Autonomous
Navigation Algorithm Based on CelestialNavigation
Information Guidance[J].Journal of Astronautics,2021,42(2):230-238. |
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| Authors: | LIN Xia LIN Bao jun LIU Ying chun BAI Tao WU Guo qiang |
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| Institution: | 1. Shanghai Engineering Center for Microsatellites,
Shanghai 201203, China; 2. Innovation Academy for Microsatellites of Chinese Academy
of Sciences, Shanghai 201203, China; 3. Aerospace Information Research
Institute, Chinese Academy of Sciences, Beijing
100094, China; 4. School of Computer Science and Technology,University of
Chinese Academy of Sciences, Beijing 100094, China; 5.
School of Information,Shanghai Tech University, Shanghai 201210, China |
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| Abstract: | To solve the weakness of the poor stability and the
weak fault recovery capability in the inter satellite link navigation
algorithm, a celestial navigation information guidance algorithm is presented. Based on the
high stability and full autonomy features, the celestial navigation information
is used to determine the inter satellite link direction
and ensure the stable inter satellite link building.
Further, the strong tracking Kalman filter method is added in the celestial
navigation algorithm. With the method, the orbital information bias can be corrected
rapidly and thus the inter satellite links can be
rebuilt. The simulation tests show that at steady state, the elevation and
azimuth orientation errors of the inter satellite links
are less than 0.1°. And when the inter satellite links break after orbit maneuver, the algorithm enables
the satellite to resume link building quickly. The simulation tests verify the
effectiveness of the celestial navigation information guidance algorithm. |
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