Progress in Redundant Electromechanical Actuators for Aerospace Applications

Fawaz Yahya Annaz; Malaka Miyuranga Kaluarachchi

doi:10.3390/aerospace10090787

Progress in Redundant Electromechanical Actuators for Aerospace Applications

Fawaz Yahya Annaz^*, Malaka Miyuranga Kaluarachchi

^*Corresponding author for this work

Anglia Ruskin University

Research output: Contribution to journal › Review article › peer-review

6 Citations (SciVal)

Abstract

The power to move aircraft control surfaces has advanced from being manually generated (by the pilot and transmitted via rods and links) to electrically transmitted (via wires) to operate control surface actuators. Various hydraulic, electromagnetic, and electromechanical architectures have been developed to provide the necessary power and to maintain the expected redundancy. Numerous aircraft actuator system designs have been proposed in the past decades, but a comprehensive review has yet to be undertaken. This review paper aims to fill this gap by providing a critical review of the actuation system designs developed for a variety of aircraft. The review focuses on aircraft actuator system designs, namely: electrohydraulic actuator systems, electromechanical actuator systems, and the force-fighting effect in redundant actuation systems. The significance and operational principle of each actuator system are critically analysed and discussed in the review. The paper also evaluates the solution proposed to address force-fight equalization (or force-fight cancelation) in force or torqued-summed architectures. Future trends in redundant actuation system development with reduced force-fighting effect in aircraft actuator systems are also addressed.

Original language	English
Article number	787
Pages (from-to)	1-22
Number of pages	22
Journal	Aerospace
Volume	10
Issue number	9
DOIs	https://doi.org/10.3390/aerospace10090787
Publication status	Published (VoR) - 7 Sept 2023

Funding

The “Large Electromechanical Actuation System (LEMAS)” Program also examined the development of EMA systems for electric aircrafts. This program was jointly funded by Lucas Aerospace and the UK Department of Trade and Industry [,]. The program investigated the use of a linear ball-screw arm assembly to move the spoiler. The design initially incorporated a permanent magnet BDCM to drive the arm assembly before utilizing 4-phase switched reluctance motors.

Keywords

electromechanical actuators
force equalization
force fight
torque disparities

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10.3390/aerospace10090787

Cite this

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title = "Progress in Redundant Electromechanical Actuators for Aerospace Applications",

abstract = "The power to move aircraft control surfaces has advanced from being manually generated (by the pilot and transmitted via rods and links) to electrically transmitted (via wires) to operate control surface actuators. Various hydraulic, electromagnetic, and electromechanical architectures have been developed to provide the necessary power and to maintain the expected redundancy. Numerous aircraft actuator system designs have been proposed in the past decades, but a comprehensive review has yet to be undertaken. This review paper aims to fill this gap by providing a critical review of the actuation system designs developed for a variety of aircraft. The review focuses on aircraft actuator system designs, namely: electrohydraulic actuator systems, electromechanical actuator systems, and the force-fighting effect in redundant actuation systems. The significance and operational principle of each actuator system are critically analysed and discussed in the review. The paper also evaluates the solution proposed to address force-fight equalization (or force-fight cancelation) in force or torqued-summed architectures. Future trends in redundant actuation system development with reduced force-fighting effect in aircraft actuator systems are also addressed.",

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author = "Annaz, \{Fawaz Yahya\} and Kaluarachchi, \{Malaka Miyuranga\}",

note = "Funding Information: The “Large Electromechanical Actuation System (LEMAS)” Program also examined the development of EMA systems for electric aircrafts. This program was jointly funded by Lucas Aerospace and the UK Department of Trade and Industry [,]. The program investigated the use of a linear ball-screw arm assembly to move the spoiler. The design initially incorporated a permanent magnet BDCM to drive the arm assembly before utilizing 4-phase switched reluctance motors. Publisher Copyright: {\textcopyright} 2023 by the authors.",

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N2 - The power to move aircraft control surfaces has advanced from being manually generated (by the pilot and transmitted via rods and links) to electrically transmitted (via wires) to operate control surface actuators. Various hydraulic, electromagnetic, and electromechanical architectures have been developed to provide the necessary power and to maintain the expected redundancy. Numerous aircraft actuator system designs have been proposed in the past decades, but a comprehensive review has yet to be undertaken. This review paper aims to fill this gap by providing a critical review of the actuation system designs developed for a variety of aircraft. The review focuses on aircraft actuator system designs, namely: electrohydraulic actuator systems, electromechanical actuator systems, and the force-fighting effect in redundant actuation systems. The significance and operational principle of each actuator system are critically analysed and discussed in the review. The paper also evaluates the solution proposed to address force-fight equalization (or force-fight cancelation) in force or torqued-summed architectures. Future trends in redundant actuation system development with reduced force-fighting effect in aircraft actuator systems are also addressed.

AB - The power to move aircraft control surfaces has advanced from being manually generated (by the pilot and transmitted via rods and links) to electrically transmitted (via wires) to operate control surface actuators. Various hydraulic, electromagnetic, and electromechanical architectures have been developed to provide the necessary power and to maintain the expected redundancy. Numerous aircraft actuator system designs have been proposed in the past decades, but a comprehensive review has yet to be undertaken. This review paper aims to fill this gap by providing a critical review of the actuation system designs developed for a variety of aircraft. The review focuses on aircraft actuator system designs, namely: electrohydraulic actuator systems, electromechanical actuator systems, and the force-fighting effect in redundant actuation systems. The significance and operational principle of each actuator system are critically analysed and discussed in the review. The paper also evaluates the solution proposed to address force-fight equalization (or force-fight cancelation) in force or torqued-summed architectures. Future trends in redundant actuation system development with reduced force-fighting effect in aircraft actuator systems are also addressed.

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Progress in Redundant Electromechanical Actuators for Aerospace Applications

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