Thesis (M.Sc.) - Cairo University - Faculty of Science - Department of Astronomy and Meterology

The main concern in the present research work is define the basic studies to determine an initial orbit (the position vector r and velocity vector v) by employing topo-centric right ascension-declination observations for a satellite at the time of interest. Additionally, define the basic studies of many perturbations forces that effects on satellite orbit which may deviate its current path tends to change its orbital elements. So, we solved equations of motion taking into account the effect of perturbed forces (Oblateness of the Earth, and Luni-solar forces) to determine the position and velocity components of satellites at any instant of time. We designed the mathematical model to employing topo-centric right ascension-declination observations for the satellite at the time of interest. Furthermore, to predict the position and velocity vectors after time. Additionally, convert the position vectors for a satellite to its corresponding latitude and longitude (ground track) by using Matlab package

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