宇航学报

宇航学报 ›› 2021, Vol. 42 ›› Issue (2): 230-238.doi: 10.3873/j.issn.1000-1328.2021.02.011

• 制导、导航、控制与电子 • 上一篇    下一篇

一种天文导航信息导引的星间链路自主定轨算法

林夏，林宝军，刘迎春，白涛，武国强   

  1. 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
  • 收稿日期:2020-07-06 修回日期:2020-10-19 出版日期:2021-02-15 发布日期:2021-02-15
  • 基金资助:
    中国科学院国防科技创新重点部署项目（KGFZD 135 18 008）

An Inter Satellite Link Autonomous Navigation Algorithm Based on Celestial Navigation Information Guidance

LIN Xia, LIN Bao jun, LIU Ying chun, BAI Tao, WU Guo qiang   

  1. 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
  • Received:2020-07-06 Revised:2020-10-19 Online:2021-02-15 Published:2021-02-15

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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。

关键词:

卫星导航系统, 星间测距, 星敏感器, 地球敏感器, 自主定轨

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.

Key words: Satellite navigation system, Inter satellite link, Star sensor, Earth sensor, Autonomous orbit determination

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