Chiaradia, A. P MDa Silva Fernandes, S.Vilhena de Moraes, R. [UNESP]2014-05-272014-05-271997-12-01Advances in Space Research, v. 19, n. 11, p. 1671-1675, 1997.0273-1177http://hdl.handle.net/11449/65249In 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.1671-1675engGPSorbit determinationsatellite systemArtigo10.1016/S0273-1177(97)00322-0WOS:A1997BJ16E00007Acesso restrito2-s2.0-00314457225651353474953307