Power flow analysis in electro-mechanical05710091

Power flow analysis in electro-mechanical05710091 -...

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Published in IET Electric Power Applications Received on 16th November 2009 Revised on 13th October 2010 doi: 10.1049/iet-epa.2009.0270 Special Section – Electrical Machines and Drives for the More Electric Aircraft ISSN 1751-8660 Power flow analysis in electro-mechanical actuators for civil aircraft A. Trentin P. Zanchetta P. Wheeler J. Clare Department of Electrical and Electronic Engineering, University of Nottingham, University Park, NG7 2RD, Nottingham, UK E-mail: andrew.trentin@nottingham.ac.uk Abstract: One of the most recent trends in the aerospace industry is the increased use of electrical power in place of hydraulic, pneumatic and mechanical power. This study presents an analytical and experimental feasibility study regarding the application of an electro-mechanical actuator for the aileron of an aircraft using a real flight proFle as a reference. The analysis is focused on the input power flow of the actuator converter, showing that the total amount of energy that would be regenerated into the aircraft power network is small and that the use of a bi-directional power flow converter has the advantage of reducing the size of the braking circuit. The investigation is carried out assuming a two-stage matrix converter as the candidate power conversion topology. However, many of the conclusions are equally applicable to other conversion topologies that are capable of bi-directional power flow. 1 Introduction The more electric aircraft concept has led to the growing use of power converters and electrical drives on modern aircraft [1–3] , making the power network a large and complex system. One of the main challenges of this new paradigm is to replace the hydraulic flight control surface actuators with electrical actuators. This paper is focused on the power flow analysis of an electro-mechanical actuator (EMA) used in an aileron application. Ailerons are attached to the wing trailing edge of a Fxed-wing aircraft and are used to control the roll of the aircraft, as shown in ±ig. 1 . The ailerons on each wing are typically operated in a complementary fashion. The combination produces a rolling moment about the aircraft’s longitudinal axis. The aileron application was chosen for this study because this is a primary flight control surface which is required for flight; the power level is typical of many aircraft actuator applications and the control surface is in constant use throughout a flight. A typical aircraft will have three actuators for each aileron, each capable of controlling the surface, to give a good level of redundancy to the system. Power regeneration into the aircraft grid from electrical equipment, such as EMAs, is not allowed by the current aerospace regulations, but it is anticipated that this restriction may be relaxed in the future. Therefore it is desirable to be able to characterise regenerative loads in order to assess their potential impact on the network. Such experimental characterisation is a rather difFcult task as it
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This note was uploaded on 05/08/2011 for the course MECHANICAL 203 taught by Professor Krishna during the Spring '11 term at Akademia Ekonomiczna w Poznaniu.

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Power flow analysis in electro-mechanical05710091 -...

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