Electric Propulsion (EP) technology has become a hot topic for both, orbit changes and top-up as well as station-keeping. Many new platform development try to expoint the higher specific impulse and reduce the propellant budget for transfer from GTO to GEO or MEO. New concepts are being assessed for transfers from un-conventional launch orbits such as SSTO or LEO, owing to the versatility of EP. While server tools exist for fast performance assessment of such transfers, there is a lack of software tools that allow not just fast, but also high-fidelity modeling, optimization, analysis amd verification. This paper presents one methodology that was implemented at the GNC Section of the European Space Agency in order to address these short-comings and support the current projects in their definition and preliminary design phases. The methodology is robust, high-performing and alble to deal with all scenarios that are currently being discussed from an EP perspective. The paper provides an in depth assessment of the optimum EP transfer concept from a GNC systems engineering perspective. To this end, optimization solutions are showcased including AV assessment for alternative orbits- and are analysed concerning various properties. The selected EP transfer setup is not directly extracted from one particular project, but in a generic way fully representative any current undertaking with a range of 3-12 months transfer from launch orbit to MEO or GEO.
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