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Oyori H.,IHI Corporation | Shimomura Y.,Sinfonia Technology Co. | Ohta Y.,Sinfonia Technology Co. | Onishi K.,Sinfonia Technology Co. | And 2 more authors.
52nd Aerospace Sciences Meeting | Year: 2014

This paper proposed a new concept of more electric architecture for aircraft and propulsion. The High-Voltage Direct Current system is anticipated as one of the optimized systems for future aircraft power system and offers numerous advantages associated with increasing electric power consumption and changing the power supply of mission-critical systems, such as flight control actuators and/or engine accessories, from conventional hydraulic and pneumatic to electric. This study introduces solutions to resolve the problem of setting up the HVDC power grid and related equipment. © 2015 American Institute of Aeronautics and Astronautics Inc. All rights reserved.


Morioka N.,IHI Corporation | Morioka N.,Mechanical Control Engineering Group | Oyori H.,IHI Corporation
50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition | Year: 2012

A MEE system targeting reduced fuel burn and CO2 emissions from an aircraft engine is being developed. It is apparent that although the MEE will achieve improved efficiency for small, medium and large turbofan engines, the weight and volume impact of the electric motor-driven components cannot be ignored for medium/large engines. This paper describes the evaluation result of the engine efficiency improvement and the weight impact on medium/large MEE. Copyright © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.


Oyori H.,IHI Corporation | Morioka N.,IHI Corporation | Morioka N.,Mechanical Control Engineering Group
50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition | Year: 2012

This paper describes a unique fault-tolerant control design concept for More Electric aero-Engine (MEE). The MEE is based on a new control system architecture for aircraft engines, introducing electrical motor-driven accessories in place of conventional accessory gearbox driven pumps or hydraulic actuators. The MEE reflects a highly advantageous approach that improves engine efficiency and reduces fuel burn and CO2 emissions. However, it raises several issues with respect to engine safety and reliability. Using a redundant motor control system for the MEE based on a unique fault-tolerant design concept, the authors sought to resolve these issues. Studies of this system and the results of tests and experiments indicate that the proposed MEE fault-tolerant design should result in a safe, highly reliable engine control system. Copyright © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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