This paper presents the good prediction of motion an artificial satellite using radar data under perturbation forces, the perturbed J 4 Earth's gravity and the atmospheric drag with the best atmospheric density model which depends on both Sun magnetic field and solar activity. To propagate the orbit, we have to determine the initial conditions by using at least three different values of range and their corresponding values of azimuth and elevation angles for radar data. The differential equations of satellite motion are solved using Runge-Kutta method of the fourth order with application on the radar data of EGYPTSAT-1.

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