一种天文导航信息导引的星间链路自主定轨算法  

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

作　　者：林夏 林宝军[1,2,3,4,5] 刘迎春 白涛 武国强 LIN Xia;LIN Bao-jun;LIU Ying-chun;BAI Tao;WU Guo-qiang(Shanghai Engineering Center for Microsatellites,Shanghai 201203,China;Innovation Academy for Microsatellites of Chinese Academy of Sciences,Shanghai 201203,China;Aerospace Information Research Institute,Chinese Academy of Sciences,Beijing 100094,China;School of Computer Science and Technology,University of Chinese Academy of Sciences,Beijing 100094,China;School of Information,Shanghai Tech University,Shanghai 201210,China)

机构地区：[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

出　　处：《宇航学报》2021年第2期230-238,共9页Journal of Astronautics

基　　金：中国科学院国防科技创新重点部署项目(KGFZD-135-18-008)。

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。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.

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 

分 类 号：V249.3[航空宇航科学与技术—飞行器设计]