Search Results

This paper describes a study on electrical power management for the More Electric Aircraft (or MEA) and the More Electric Engine (or MEE). This study explored power management solutions based on an integrated engine/power control system and a permanent magnet motor. In recent years, electrical power management has emerged as a key aspect of aircraft system design. In cases in which the Electromechanical Actuator (or EMA) systems are used for flight control, the power bus systems must also be designed to dissipate the power regenerated from flight control systems. In their study, the authors focused on achieving an optimal balance between aircraft power management and operational requirements of the aero-engines. The study results suggest an effective and novel power control concept based on integrated engine control technologies that ensure stable power systems.

This paper describes a concept related to fault-tolerant design for a redundant motor control system. The design comprises components driven by an electric motor, a motor controller, and a power source, referred to as the More Electric Aero Engine (or MEE). The MEE dramatically improves the engine efficiency and reduces fuel burn and CO2 emissions. However, the MEE system must demonstrate that it can ensure engine safety and reliability before it can take the place of conventional systems. The proposed unique redundant system presented in this paper incorporates Active-Active control and multi-winding motors. Engine fuel flow is controlled by the motor speed control of the MEE electric fuel pump, which uses this redundant system. This concept provides a solution for helping to ensure engine safety and reliability, since it enables a complete one-fail operational engine fuel system for the MEE. Another key technology for the MEE system involves a power generating solution.