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Abstract
The solution of the motion of an artificial satellite taking into consideerations only the gravitational force of the earth will not give the exact trajectory of the satellite in this thesis, an earth centered inertial coordinate system will be used to describe the motion, the effects of some perturbing forces such as earth oblatenessatmospheric drag , and gravitational force of the moon will he considered .The perturbed equations of . motion will be numerically integrated to obtain the position and velocitty of the satellite , versus time. Components of position and velocity vectors of the satellite and the differences between those due to different perturbations and the corresponding ones due to the unperturbed motion will he also presented.