چكيده به لاتين
Abstract:
GEO satellites are among the most applicable satellites but beside their convenient application, due to high altitude, the process of orbit reaching is a complicated and expensive one and so far a few countries have the technology. In this work osculating and averaged equations of motion of a spacecraft utilized by electric propulsion system is presented using equinoctical elements and are optimized so that the spacecraft is enabled to reach final orbit using lowest thrust possible and so very low fuel consumption. Meeting domestic and operational requirements, this method is an optimized, fast and applicable one which proposes a tranectory with lots of revolutions for a communication satellite to transfer from LEO to GEO, enabling launchers much weaker than currently active ones in placing a satellite in GEO orbit. Simulations and evaluating results demonestrates operational charactristics. In addition, by describing perturbing models and presenting their integration to dynamic equations, results' accuracy improves.
Keywords: Orbit Transfer, GEO, Fuel Minimizing, Electric Propulsion, Low-Thrust
