This paper presents the good prediction of motion an artificial satellite using radar data under perturbation forces, the
perturbed J4 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.