摘要
为提高导航星座的自主导航能力,提出一种基于人工拉格朗日点太阳帆的导航卫星自主定轨方法。在导航卫星星间测距的基础上,利用太阳帆提供的空间实时位置信息,来消除导航星座的整体旋转和漂移对自主定轨的影响。选用第一类无奇点根数作为状态变量,利用EKF滤波器融合卫星动力学信息及两类测距信息进行自主定轨。利用GPS导航星座的IGS精密星历进行了仿真试验,仿真结果表明了该方法不仅能够保证导航卫星自主定轨的长期稳定性,且与结合星间测距和星间测向的自主定轨方法相比,定轨精度更高。
To improve the autonomous navigation ability of navigation constellation,a kind of autonomous orbit determination technology based on a solar sail at an artificial Lagrange point is proposed for navigation satellite.Based on crosslink range observation,real-time position information provided by the solar sail is used to eliminate the error of autonomous orbit determination caused by the overall rotation and drift of the navigation constellation.Nonsingular orbit elements are chosen as state vector when the extended Kalman filter （EKF） is designed to fuse satellite dynamics model and two kinds of observation information to determine the orbit.International GNSS service （IGS） precise ephemeris of GPS constellation is adopted to validate the method.The results of simulation show that the proposed algorithm can not only ensure the long-term stability,but also provide higher precision of orbit determination compared with the approach of combining crosslink range observation with inter-satellite orientation observation.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2014年第6期856-861,共6页
Journal of Nanjing University of Aeronautics & Astronautics
基金
国家高技术研究发展计划("八六三"计划)(2012AA121602)资助项目
国家自然科学基金(11078001)资助项目
高等学校博士学科点专项科研基金(20133218120037)资助项目
关键词
导航卫星
自主定轨
人工拉格朗日点
太阳帆
navigation constellation
autonomous orbit determination
artificial Lagrange point
solar sail
