Abstract

This paper presents a review of the various distributed electric propulsion architectures for the electrification of aircraft. The most viable architectures related to the sizing of components and the reduction of the overall mass of the system are presented. Different configurations that address the faults in the system and the required oversizing of components (Power electronic converters, electrical machines, circuit breakers, etc.) to maintain the thrust required by an aircraft considering the worst-case fault scenarios are discussed. A comparison of estimation of the overall mass of all these architectures considering the recent specific power values reported in the literature is also presented.

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