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Abstract
The main concern in the present research work is to define the basic studies of many perturbations forces that affect on communication satellites orbit (geostationary and Molniya 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, solar radiation pressure and Loin-solar gravitation) to determine the position and velocity components of satellites at any instant of time. We designed the mathematical model to compute the position, velocity, the ground track, coverage area and the time interval for communication satellites orbit by using Matlab package. Chapter I, introduction about communication satellites, and orbital perturb- ations were discussed including survey of some relevant previous works and its aim, and in Chapters II, we studying more perturbation forces that have important effects on the artificial satellites and developing equations of motion with/without perturbation forces (oblatness, solar radiation pressure and Luni- solar perturbation) that affect communication satellites by using L.P.E. in Gauss form, while in Chapter III, satellite orbits classifications, definition of NORAD (North American Aerospace Defence Command) orbital elements, and the fundamental geometry of ground tracks were discussed. Also, the coverage area and satellite visibility time were calculated. But in Chapter IV, we formulated the equations of motion under the effect of oblatness by using Kozai method and perturbation forces (solar radiation pressure and Luni-solar perturbation) using L.P.E. in Gauss form, to determine the actual position and velocity at any instant of time. We used some examples of communication satellites orbit (geostationary and Molniya orbit) of two different types of satellite. The result were shown in tables and figures comparing the change in longitude and latitude with/without affected perturbation forces e on the artificial satellites