Geosynchronous transfer orbit design: A practical approach

Abstract

This paper is proposing a practical approach for a Geosynchronous Transfer Orbit design. To design the intermediate orbits between the injection orbit and the Geosynchronous Orbit were used the Hohmann Transfer Orbit, Keppler 3rd Law and the propellant consumption equations. According to design, these intermediate orbits will be followed by a communication satellite during its orbital maneuver sequence ensuring its final orbital position and minimal fuel consumption. Simulation results and comparison with STK software showed that the approach can simply and effectively be used in the Geosynchronous Transfer Orbit Design.