Design of a Triple-Redundant Electromechanical Brake System Control Unit for Aerospace Application

In the last fifteen years, the increasingly compelling performance optimization and environmental pollution containment objectives push the aerospace industry towards the concept of Hybrid Electric Powered or More Electric Aircraft. The MEA concept aims to convert today's hydraulic and pneumatic systems to more efficient and safer electric powered ones. Brake Systems represent one of the most challenging aspects of the changeover. This thesis proposes a triple-redundant fault-tolerant Electronic Control Unit design for the MAG-PoliTO-BPR Electromechanical Brake System FreME. The work describes the device, from the hardware technical requirements derived from the system level specification, through the architecture definition, to the detailed electric scheme of the Brake System Control Unit. Focus is placed on the description of internal redundancy management mechanisms to underline the compliance with safety requirements.