Design Approach of an Integrated SiC-Inverter for an Electric Aircraft

Abstract

This paper describes features of an SiC-inverter for aviation. It is designed to work in an integrated manner close to the corresponding motor and propeller, sharing a common cooling system and suiting the geometrical conditions within the nacelle. Some design aspects are examined in detail, such as the distributed DC-link, serving the complex geometry of the power modules with very low stray inductance. Control strategies for the symmetrical, six-phase systems are explained. Prototype measurements are given to underline some design aspects. The complete system is designed to fulfill flight requirements and is to be approved in a wind tunnel test environment.