DC-DC convertor design for the 270 volts DC ‘More Electric Aircraft’

The design of a dedicated power convertor, within a future aircraft with a 270 V dc - based Electrical Power System is considered. The power convertor is required to supply an Electronic Engine Controller (EEC), a mid-power aircraft electrical sub-system which resides in a non-pressurised environment. This is in essence a feasibility study to provide an understanding of the trade-offs involving (a) possible alternative convertor technologies, (b) extra difficulties, such as safety and the related derating of components, because the EEC resides in a non-pressured, hostile environment and (c) the commercial availability of suitable electrical componentry to ensure the DC-DC convertor characteristics satisfy the design specification.