引用本文: 李征航, 张卫星, 龚晓颖, 屈小川. 导航卫星自主定轨时轨道机动问题的处理方法[J]. 武汉大学学报 ( 信息科学版), 2011, 36(11): 1309-1313.
LI Zhenghang, ZHANG Weixing, GONG Xiaoying, QU Xiaochuan. Solution of Orbit Maneuver Problem in Autonomous Orbit Determination of Navigation Satellites[J]. Geomatics and Information Science of Wuhan University, 2011, 36(11): 1309-1313.
 Citation: LI Zhenghang, ZHANG Weixing, GONG Xiaoying, QU Xiaochuan. Solution of Orbit Maneuver Problem in Autonomous Orbit Determination of Navigation Satellites[J]. Geomatics and Information Science of Wuhan University, 2011, 36(11): 1309-1313.

## Solution of Orbit Maneuver Problem in Autonomous Orbit Determination of Navigation Satellites

• 摘要: 在各种摄动因素的作用下,导航卫星将逐渐偏离其预定轨道,因而需要通过轨道机动的方法来予以纠正。但轨道机动后,由预报轨道所提供的轨道先验信息将失去作用,这是用星间距离观测值和先验轨道信息进行导航卫星自主定轨时必须要解决的问题。提出机动后,机动卫星采用几何法来确定自己的位置,然后用动力学法来进行轨道拟合和轨道预报,在机动后第二天就能恢复正常的自主定轨。即使有多个卫星在同一天发生机动,个别卫星因可观测卫星不足4个而无法定轨,在第二天就能实现几何法定位,不会影响整个系统的导航定位功能。

Abstract: A method that using geometry to determine its position after the satellite maneuver is introducted,and then using dynamic method to fit and predict orbit.The maneuvered satellite will return to normal autonomous orbit determination the day after maneuver.Even if there are multiple satellites maneuvering in the same day,individual satellite cannot finish orbit determination due to the number of observable satellite less than four,geometric positioning method can be achieved in the second day after maneuver.It will not affect the whole system of navigation and positioning capabilities.

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