Please use this identifier to cite or link to this item: https://doi.org/10.1155/2012/910496
Title: Implementation of a differential geometric filter for spacecraft formation orbit estimation
Authors: Goh, S.T 
Abdelkhalik, O
Zekavat, S.A
Issue Date: 2012
Publisher: Hindawi
Citation: Goh, S.T, Abdelkhalik, O, Zekavat, S.A (2012). Implementation of a differential geometric filter for spacecraft formation orbit estimation. International Journal of Aerospace Engineering : 910496. ScholarBank@NUS Repository. https://doi.org/10.1155/2012/910496
Rights: Attribution 4.0 International
Abstract: The differential geometric filter is implemented to estimate the absolute and relative positions of the spacecraft in a formation. The extended Kalman Filter is also implemented as a benchmark for the differential geometric estimation. Only relative positions between the spacecraft are measured. Relative positions are measured using a wireless local positioning system (WLPS) installed in all spacecraft. Two different scenarios are studied: (1) the observations include WLPS measurements only and (2) the observations include WLPS measurements in addition to measurements for the absolute position of one spacecraft made by a radar that takes measurements from the earth's surface. Results show that the differential geometric estimation has better stability performance and a faster convergence rate compared to the extended Kalman filter. © 2012 Shu Ting Goh et al.
Source Title: International Journal of Aerospace Engineering
URI: https://scholarbank.nus.edu.sg/handle/10635/178151
ISSN: 1687-5966
DOI: 10.1155/2012/910496
Rights: Attribution 4.0 International
Appears in Collections:Staff Publications
Elements

Show full item record
Files in This Item:
File Description SizeFormatAccess SettingsVersion 
10_1155_2012_910496.pdf2.82 MBAdobe PDF

OPEN

NoneView/Download

Google ScholarTM

Check

Altmetric


This item is licensed under a Creative Commons License Creative Commons