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ICNPAA 2004: Mathematical Problems in Engineering and Aerospace Sciences
June 2-4, 2004
The West University of Timisoara
Timisoara, Romania

Organizers
Conference Organizer and Chair: Seenith Sivasundaram

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Low cost orbit determination using GPS
by
Rodolpho Vilhena de Moraes
DMA-FEG-UNESP
Coauthors: Aurea Aparecida da Silva, Helio Koiti Kuga

A low computer cost procedure to determine the orbit of an artificial satellite using data from an onboard GPS receiver is proposed. Pseudoranges are used as measurements to estimate the orbit via recursive least squares method. The algorithm applies orthogonal Givens rotations for solving recursive and sequentially the orbit determination problem. The advantage of this approach is stated in the body of the paper. To assess the procedure, it was applied to the TOPEX/POSEIDON satellite for data batches of one orbital period (approximately two hours) and considering force modelling due to the full JGM-2 gravity field model. When compared with the reference Precision Orbit Ephemeris (POE) of JPL/NASA, results indicate that precision better than 9 m is easily obtained, even with short batches of data.

Date received: March 23, 2004

Copyright © 2004 by the author(s). The author(s) of this document and the organizers of the conference have granted their consent to include this abstract in Atlas Conferences Inc. Document # canw-19.