In order to slow down global warming, electrification of transportation is looked into more and more.
The commercialization of electric cars was one of the first steps. Next the transportation industry will look to expand into electric aircraft too. The electric distribution propulsion system is one of the most important areas regarding the feasibility of electric aircraft. This thesis presents a design for an allelectric distribution propulsion system for the year 2038. More specifically, the power converters and safety considerations of the electric architecture will be compared and discussed in this thesis. Existing research was compared to derive optimal solutions for the aircraft requirements. Finally, the conclusion summarises the most important results obtained during the research process for this aircraft application.