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Abstract
The goal of this thesis is to determine the initial orbit (IOD) for a satellite in a low earth orbit (LEO); and to predict of the motion of the satellite in orbit during one week. The process of (IOD) is carried out using two systems, Optical Observation system and the Radar Observation system. Numerical integration is used to predict the satellite motion in orbit during one week with and without the perturbation forces. We will focus on both the Earth’s gravitational force and atmospheric drag as perturbing forces. The atmospheric drag model uses an atmospheric density model in which the density depends on magnetic field and solar flux data. The differential equations of the satellite motion are solved using Runge-Kutta method of the fourth order having EGYPTSAT-1 as a model