Electric Propulsion System Architecture

Abstract

An electric distribution architecture is described herein. In some embodiments, the electric distribution architecture for an aircraft includes at least one electrical source, a plurality of loads including at least one high energy load and at least one low energy load, and a power distribution system. The power distribution system includes a plurality of contactors configured to selectively distribute electrical power from each of the at least one electrical source to each of the plurality of loads. In some approaches, at least one first fast acting high energy protection device is electrically coupled in series with each at least one electrical source, and at least one second fast acting high energy protection device is electrically coupled in series with each of the at least one high energy loads. In some approaches, the power distribution system is devoid of any high energy protection devices.

Dependencies are inferred from the claim text.