System Design for the More Electric Engine Incorporated in the Electrical Power Management for More Electric Aircraft

Paper #:
  • 2012-01-2169

Published:
  • 2012-10-22
DOI:
  • 10.4271/2012-01-2169
Citation:
Oyori, H., Morioka, N., Kakiuchi, D., Shimomura, Y. et al., "System Design for the More Electric Engine Incorporated in the Electrical Power Management for More Electric Aircraft," SAE Technical Paper 2012-01-2169, 2012, doi:10.4271/2012-01-2169.
Pages:
9
Abstract:
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.
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