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This paper is concerned with an orbit prediction using the Euler variables. Perturbations due to the Earth's gravitational field up to the fourth zonal harmonic and the atmospheric drag with rotating & non-rotating atmosphere are considered. The method developed is illustrated by application to a typical satellite orbit. A final state of accuracy 10.3 m is obtained.

THE EFFECT OF THE EARTH'S OBLATENESS AND ATMOSPHERIC DRAG ON AN ARTIFICIAL SATELLITE IN TERMS OF THE EULER PARAMETERS