Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA)

Shaohong Zhu; Tom Cox; Zeyuan Xu; Chris Gerada; Chen Li

doi:10.1109/ECCE.2018.8557426

Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA)

Shaohong Zhu
, Tom Cox
, Zeyuan Xu
, Chris Gerada
, Chen Li

Nottingham Electrification Centre

Research output: Chapter in Book/Conference proceeding › Conference contribution › peer-review

13 Citations (Scopus)

Abstract

This paper studies the concerns such as architecture and reliability in the deployment of electromechanical actuator (EMA) in the actuation system for more electric aircraft (MEA). First, the reliability of the actuation system architecture such as control surface redundancy and actuator redundancy will be studied to determine an appropriate actuator architecture, with or without considering jamming. Then, the considerations for fault-tolerance and redundancy of the prime electric motor will be discussed in terms of reliability, weight, control complexity, and cost based on a direct-drive EMA designed for MEA. The comparison results demonstrate the configuration of two anti-jamming EMAs with dual three-phase drives connected in parallel can meet the requirements of the safety-critical actuation applications, promoting the deployment of fully electric actuation system on the MEA. Finally, a fault-tolerant motor with double 3-phase system designed for EMA will be presented, with performance under normal and fault conditions validated.

Original language	English
Title of host publication	2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018
Publisher	Institute of Electrical and Electronics Engineers Inc.
Pages	4607-4613
Number of pages	7
ISBN (Electronic)	9781479973118
DOIs	https://doi.org/10.1109/ECCE.2018.8557426
Publication status	Published - 3 Dec 2018
Event	10th Annual IEEE Energy Conversion Congress and Exposition, ECCE 2018 - Portland, United States Duration: 23 Sept 2018 → 27 Sept 2018

Publication series

Name	2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018

Conference

Conference	10th Annual IEEE Energy Conversion Congress and Exposition, ECCE 2018
Country/Territory	United States
City	Portland
Period	23/09/18 → 27/09/18

UN SDGs

This output contributes to the following UN Sustainable Development Goals (SDGs)

SDG 7 Affordable and Clean Energy

Free Keywords

Electromechanical actuator (EMA)
Failure probability
Fault-tolerant
Jamming
More electric aircraft (MEA)

ASJC Scopus subject areas

Energy Engineering and Power Technology
Renewable Energy, Sustainability and the Environment
Control and Optimization
Computer Networks and Communications
Hardware and Architecture
Information Systems and Management

Access to Document

10.1109/ECCE.2018.8557426

Cite this

Zhu, S., Cox, T., Xu, Z., Gerada, C., & Li, C. (2018). Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA). In 2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018 (pp. 4607-4613). Article 8557426 (2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018). Institute of Electrical and Electronics Engineers Inc.. https://doi.org/10.1109/ECCE.2018.8557426

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title = "Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA)",

abstract = "This paper studies the concerns such as architecture and reliability in the deployment of electromechanical actuator (EMA) in the actuation system for more electric aircraft (MEA). First, the reliability of the actuation system architecture such as control surface redundancy and actuator redundancy will be studied to determine an appropriate actuator architecture, with or without considering jamming. Then, the considerations for fault-tolerance and redundancy of the prime electric motor will be discussed in terms of reliability, weight, control complexity, and cost based on a direct-drive EMA designed for MEA. The comparison results demonstrate the configuration of two anti-jamming EMAs with dual three-phase drives connected in parallel can meet the requirements of the safety-critical actuation applications, promoting the deployment of fully electric actuation system on the MEA. Finally, a fault-tolerant motor with double 3-phase system designed for EMA will be presented, with performance under normal and fault conditions validated.",

keywords = "Electromechanical actuator (EMA), Failure probability, Fault-tolerant, Jamming, More electric aircraft (MEA)",

author = "Shaohong Zhu and Tom Cox and Zeyuan Xu and Chris Gerada and Chen Li",

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Zhu, S, Cox, T, Xu, Z, Gerada, C & Li, C 2018, Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA). in 2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018., 8557426, 2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018, Institute of Electrical and Electronics Engineers Inc., pp. 4607-4613, 10th Annual IEEE Energy Conversion Congress and Exposition, ECCE 2018, Portland, United States, 23/09/18. https://doi.org/10.1109/ECCE.2018.8557426

Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA). / Zhu, Shaohong; Cox, Tom; Xu, Zeyuan et al.
2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018. Institute of Electrical and Electronics Engineers Inc., 2018. p. 4607-4613 8557426 (2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018).

Research output: Chapter in Book/Conference proceeding › Conference contribution › peer-review

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T1 - Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA)

AU - Zhu, Shaohong

AU - Cox, Tom

AU - Xu, Zeyuan

AU - Gerada, Chris

AU - Li, Chen

PY - 2018/12/3

Y1 - 2018/12/3

N2 - This paper studies the concerns such as architecture and reliability in the deployment of electromechanical actuator (EMA) in the actuation system for more electric aircraft (MEA). First, the reliability of the actuation system architecture such as control surface redundancy and actuator redundancy will be studied to determine an appropriate actuator architecture, with or without considering jamming. Then, the considerations for fault-tolerance and redundancy of the prime electric motor will be discussed in terms of reliability, weight, control complexity, and cost based on a direct-drive EMA designed for MEA. The comparison results demonstrate the configuration of two anti-jamming EMAs with dual three-phase drives connected in parallel can meet the requirements of the safety-critical actuation applications, promoting the deployment of fully electric actuation system on the MEA. Finally, a fault-tolerant motor with double 3-phase system designed for EMA will be presented, with performance under normal and fault conditions validated.

AB - This paper studies the concerns such as architecture and reliability in the deployment of electromechanical actuator (EMA) in the actuation system for more electric aircraft (MEA). First, the reliability of the actuation system architecture such as control surface redundancy and actuator redundancy will be studied to determine an appropriate actuator architecture, with or without considering jamming. Then, the considerations for fault-tolerance and redundancy of the prime electric motor will be discussed in terms of reliability, weight, control complexity, and cost based on a direct-drive EMA designed for MEA. The comparison results demonstrate the configuration of two anti-jamming EMAs with dual three-phase drives connected in parallel can meet the requirements of the safety-critical actuation applications, promoting the deployment of fully electric actuation system on the MEA. Finally, a fault-tolerant motor with double 3-phase system designed for EMA will be presented, with performance under normal and fault conditions validated.

KW - Electromechanical actuator (EMA)

KW - Failure probability

KW - Fault-tolerant

KW - Jamming

KW - More electric aircraft (MEA)

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Y2 - 23 September 2018 through 27 September 2018

ER -

Zhu S, Cox T, Xu Z, Gerada C, Li C. Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA). In 2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018. Institute of Electrical and Electronics Engineers Inc. 2018. p. 4607-4613. 8557426. (2018 IEEE Energy Conversion Congress and Exposition, ECCE 2018). doi: 10.1109/ECCE.2018.8557426

Design Considerations of Fault-Tolerant Electromechanical Actuator Systems for More Electric Aircraft (MEA)

Abstract

Publication series

Conference

UN SDGs

Free Keywords

ASJC Scopus subject areas

Access to Document

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