Simple Orbit Determination Using GPS Based on a Least-Squares Algorithm Employing Sequential Givens Rotations | Zendy

Rodolpho Vilhena de Moraes | Zendy; Áurea Aparecida da Silva | Zendy; Hélio Koiti Kuga | Zendy

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Simple Orbit Determination Using GPS Based on a Least-Squares Algorithm Employing Sequential Givens Rotations

Author(s) -

Rodolpho Vilhena de Moraes,

Áurea Aparecida da Silva,

Hélio Koiti Kuga

Publication year - 2007

Publication title -

mathematical problems in engineering

Language(s) - English

Resource type - Journals

SCImago Journal Rank - 0.262

H-Index - 62

eISSN - 1026-7077

pISSN - 1024-123X

DOI - 10.1155/2007/49781

Subject(s) - ephemeris , orbit (dynamics) , orbit determination , algorithm , global positioning system , satellite , geodesy , least squares function approximation , computer science , gravitational field , mathematics , physics , aerospace engineering , engineering , geology , statistics , telecommunications , astronomy , estimator

A low-cost computer procedure to determine the orbit of an artificial satellite byusing short arcdata from an onboard GPS receiver is proposed. Pseudoranges are used as measurements toestimate the orbit via recursive least squares method. The algorithm applies orthogonal Givensrotations for solving recursive and sequential orbit determination problems. To assess theprocedure, it was applied to the TOPEX/POSEIDON satellite for data batches of one orbitalperiod (approximately two hours), and force modelling, due to the full JGM-2 gravity field model,was considered. When compared with the reference Precision Orbit Ephemeris (POE) ofJPL/NASA, the results have indicated that precision better than 9 m is easily obtained, even whenshort batches of data are used

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