USE OF NONLINEARITIES FOR INCREASED OBSERVABILITY IN RELATIVE ORBIT ESTIMATION

被引：0

作者：

Wang, Jingwei ^{[1
]}

Butcher, Eric A. ^{[1
]}

Lovell, T. Alan ^{[2
]}

机构：

[1] Univ Arizona, Dept Aerosp & Mech Engn, 1130 N Mt Ave,POB 210119, Tucson, AZ 85721 USA

[2] Air Force Res Lab, Space Vehicles Directorate, 3550 Aberdeen Ave SE, Kirtland AFB, NM 87117 USA

来源：

ASTRODYNAMICS 2015 | 2016年 / 156卷

关键词：

D O I：

暂无

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

In this paper, the effects of incorporating nonlinearities in sequential relative orbit estimation are studied for a chief spacecraft in a circular orbit, assuming either range or line-of-sight measurement of the deputy from the chief. The relative motion models used in an extended Kalman filter can be categorized into four cases: first order (HCW equation), second order, third order and full nonlinear. Observability is studied analytically using Lie derivatives and numerically with the observability index and condition number obtained from employing an extended Kalman filter. The results highlight the improving benefits of using higher order nonlinear Models.

引用

页码：3525 / 3544

页数：20

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