Due to recent developments in current-soruce inverter technology the topology becomes more attractive for use in electric aircraft. However recent studies have shown that electric aircraft are unlikely to be able to operate at high voltages due to the insulation derating, meaning that higher current solutions should be evaluated. In this paper a design is presented that is intended to operate at high currents and lower voltage in order to investigate what influence this shift in operating point has on the functionalit of the inverter. Different design elements are discussed and motivated, including the topology, component selection, and current control methods. After validating the functionality through experimentation the discovered issues are explained and discussed. The design will be shown to be functional, although some of these issues do limit its performance.

In this thesis, a closer look will be taken into the design of a propulsion system of an eVTOL (electric Vertical Take-off and Landing aircraft). The primary goal of the eVTOL is to maximize the payload for a given maximum take-off weight and the eVTOL has to go into service in 2030. To make an as light weight as possible propulsion system, an investigation will be done for the propeller length and the number of rotors, which is present on a given eVTOL design. In addition to this, different drive choices will be discussed and an optimal drive choice will be made. For this drive, a closer look will be taken in efficiency optimisation. From these parameters a design example will be given using the current state-of-the-art drive technology. In addition to this possible future drive, developments will be taken into account.