The Model Modification of Extended Kalman Filter (EKF) during Orbital Maneuver

被引：0

作者：

Pei, Jun ^{[1
]}

Shi, Huli ^{[1
]}

Hu, Zhengqun ^{[1
]}

机构：

[1] Chinese Acad Sci, Natl Astron Observ, Beijing, Peoples R China

来源：

CSNC 2011: 2ND CHINA SATELLITE NAVIGATION CONFERENCE, VOLS 1-3 | 2011年

关键词：

orbital maneuver; orbital prediction; extended Kalman filter (EKF);

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The extended Kalman filter (EKF) is an important technical method to data processing in orbital determination, but during the orbital maneuver of satellite, the original dynamic state equations model changes to result in worst orbit prediction. This paper discus a joint algorithm of EKF based on satellite orbit measurement in orbital data processing, through adjustment of the parameters and structure in EKF. It will purpose improve and enhance orbit determination accuracy of use of satellite Dynamic model during satellite maneuver.

引用

页码：564 / 567

页数：4