The Injection Velocity and Apogee Simulation for Transfer Elliptical Satellite Orbits
- 1 Faculty of Information Technology, Polytechnic University of Tirana, Albania
- 2 Faculty of Information Technology, Polytechnic University of Tirana, Tirana, Albania
- 3 Faculty of Information Technology, Polytechnic University of Tirana, Tirana, Albania
- 4 Faculty of Information Technology, Polytechnic University of Tirana, Tirana, Albania
Abstract
Basic resources for communication satellites are communication radio-frequencies and satellite orbits. An orbit is the trajectory followed by the satellite. The communication between the satellite and a ground station is established only when the satellite is consolidated in its own orbit and it is visible from the ground station. Different types of orbits are possible, each suitable for a specific application or mission. Most used orbits are circular, categorized as low, medium and geosynchronous (geostationary) orbits based on the attitude above the Earths surface. The launching process heading the satellite in geostationary orbit, by the first step places the satellite in a transfer orbit. The transfer orbit is elliptical in shape with low attitude at perigee, and the apogee of the geostationary orbit attitude. The apogee of the parking orbit depends on the injection velocity applied at perigee. Simulation approach of injection velocity at perigee to attain different apogees, considering an incremental step is presented in this paper.
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