Electric propulsion (EP) systems offer considerably more degrees of freedom (DOFs)\nwithin the design process of aircraft compared to conventional aircraft engines. This requires large,\ncomputationally expensive design space explorations (DSE) with coupled models of the single\ncomponents to incorporate interdependencies during optimization. The purpose of this paper\nis to exemplarily study these interdependencies of system key performance parameters (KPIs),\ne.g., system mass and efficiency, for a varying DC link voltage level of the power transmission system\nconsidering the example of the propulsion system of the CENTRELINE project, including an electric\nmotor, a DC/AC inverter, and the DC power transmission cables. Each component is described by\na physically derived, analytical model linking specific subdomains, e.g., electromagnetics, structural\nmechanics and thermal analysis, which are used for a coupled system model. This approach\nstrongly enhances model accuracy and simultaneously keeps the computational effort at a low\nlevel. The results of the DSE reveal that the system KPIs improve for higher DC link voltage despite\nslightly inferior performance of motor and inverter as the mass of the DC power transmission cable\nhas a major share for a an aircraft of the size as in the CENTRELINE project. Modeling of further\ncomponents and implementation of optimization strategies will be part of future work.
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