Celestial navigation using low earth orbit satellites without prior ephemeris information
File(s)
Accepted version
Author(s)
Shakerin, Kian A
McMahon, Jay W
Amato, Davide
Spielvogel, Andrew R
Type
Journal Article
Abstract
This paper presents a dynamic simultaneous localization and mapping approach to celestial navigation using low Earth orbit satellites. A sliding window batch filter is modified to handle dynamically evolving landmark states. A multi-step initial orbit determination process is used to initialize satellites as land marks assuming no a priori ephemeris information. Measurements of satellites are taken using an optical sensor and a navigation grade inertial measurement unit provides insight into the observer's motion. The method is applied to navigation of a ship on the Earth's surface across a variety of scenarios and parameters including observer location, sensor field of view, and sensor accuracy. Algorithm performance is evaluated using Monte Carlo analysis. Results indicate good performance and the capability to achieve a robust navigation solution with state errors below 100 m in position and 0.1 m/s in velocity.
Date Issued
2026-06-05
Date Acceptance
2026-06-01
Citation
IEEE Transactions on Aerospace and Electronic Systems, 2026, pp.1-13
ISSN
0018-9251
Publisher
Institute of Electrical and Electronics Engineers (IEEE)
Start Page
1
End Page
13
Journal / Book Title
IEEE Transactions on Aerospace and Electronic Systems
Copyright Statement
© 2026 IEEE. This is the author’s accepted manuscript made available under a CC-BY licence in accordance with Imperial’s Research Publications Open Access policy (www.imperial.ac.uk/oa-policy)
License URL
Publication Status
Unpublished
Date Publish Online
2026-06-05