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Design and testing of electromechanical actuator for aerospace applications

Papini, L.; Connor, P.; Patel, C.; Empringham, L.; Gerada, C.; Wheeler, P.

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Authors

L. Papini

PETER CONNOR Peter.Connor@nottingham.ac.uk
Senior Application Engineers in Industrialisation of Electrical Machines and Drives

C. Patel

LEE EMPRINGHAM LEE.EMPRINGHAM@NOTTINGHAM.AC.UK
Professor of Power Conversion Technologies

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PATRICK WHEELER pat.wheeler@nottingham.ac.uk
Professor of Power Electronic Systems



Abstract

Electromechanical actuators are gaining interest in the aerospace industry within the More Electrical Aircraft (MEA) architecture. The end-goal of fully electric aircraft includes Electromechanical actuation for flight control systems. The design and testing of a flight control system for helicopter swash-plate is presented in this work. The mechanical system is driven by electrical machines and controlled by dedicated power electronics, both of which fit challenging space requirements and environmental conditions. The predicted performances are validated by experimental testing of prototypes.

Citation

Papini, L., Connor, P., Patel, C., Empringham, L., Gerada, C., & Wheeler, P. (2018). Design and testing of electromechanical actuator for aerospace applications. In 2018 25th International Workshop on Electric Drives: Optimization in Control of Electric Drives (IWED2018) - Proceedings (1-6). https://doi.org/10.1109/IWED.2018.8321392

Conference Name 2018 25th International Workshop on Electric Drives: Optimization in Control of Electric Drives (IWED)
Conference Location Moscow, Russia
Start Date Jan 31, 2018
End Date Feb 2, 2018
Acceptance Date Dec 6, 2017
Online Publication Date Mar 22, 2018
Publication Date 2018
Deposit Date Aug 16, 2018
Publicly Available Date Mar 29, 2024
Publisher Institute of Electrical and Electronics Engineers
Pages 1-6
Book Title 2018 25th International Workshop on Electric Drives: Optimization in Control of Electric Drives (IWED2018) - Proceedings
Chapter Number 42
ISBN 978-1-5386-1201-9
DOI https://doi.org/10.1109/IWED.2018.8321392
Keywords More electric aircraft; Fault tolerant; Permanent magnet machine; Electro-mechanical actuator
Public URL https://nottingham-repository.worktribe.com/output/1036053
Publisher URL https://ieeexplore.ieee.org/document/8321392/
Additional Information © 2018 IEEE. Personal use of this material is permitted. Permission from IEEE must be obtained for all other uses, in any current or future media, including reprinting/republishing this material for advertising or promotional purposes, creating new collective works, for resale or redistribution to servers or lists, or reuse of any copyrighted component of this work in other works.

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