Application of the GPS system for preliminary satellite orbit determination

dc.contributorCTA
dc.contributorUniversidade Estadual Paulista (Unesp)
dc.date.accessioned2014-05-27T11:18:17Z
dc.date.available2014-05-27T11:18:17Z
dc.date.created2014-05-27T11:18:17Z
dc.date.issued1997-12-01
dc.identifierAdvances in Space Research, v. 19, n. 11, p. 1671-1675, 1997.
dc.identifier0273-1177
dc.identifierhttp://hdl.handle.net/11449/65249
dc.identifier10.1016/S0273-1177(97)00322-0
dc.identifierWOS:A1997BJ16E00007
dc.identifier2-s2.0-0031445722
dc.identifier5651353474953307
dc.description.abstractIn this paper, we discuss a method of preliminary orbit determination for an artificial satellite based on the navigation message of the GPS constellation. Orbital elements are considered as state variables and a simple dynamic model, based on the classic two-body problem, is used. The observations are formed by range and range and range-rate with respect to four visible GPS. A discrete Kalman filter with simulated data is used as filtering technique. The data are obtained through numerical propagation (Cowell's method), which considers special perturbations for the GPS satellite constellation and a user satellite. © 1997 COSPAR. Published by Elsevier Science Ltd.
dc.languageeng
dc.relationAdvances in Space Research
dc.relation1.529
dc.relation0,569
dc.rightsAcesso restrito
dc.sourceScopus
dc.subjectGPS
dc.subjectorbit determination
dc.subjectsatellite system
dc.titleApplication of the GPS system for preliminary satellite orbit determination
dc.typeArtículos de revistas


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