One of the most important subjects in the productivity of the satelliteis its guiding, controlling and tracking by ground stations. The satellite trajectory simulator is one of the tracking requirements in the ground station control unit. The satellite trajectories due time are undergone by various disturbances. This paper presents necessary formula using SGP algorithm and models the necessary calculation to simulating the disturbance effect on the orbit. The purpose of this paper is, error analyzing of this model with J2 model and two-body modelduring the third week.Error analysis and experimental test results using this algorithm show that the tracking accuracy of antenna with the 4o beam during this time is acceptable.
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