A fault tolerant electric drive for an aircraft nose wheel steering actuator

Bennett, John W.; Mecrow, B.C.; Atkinson, David; Maxwell, C.J.; Benarous, M.

doi:10.1049/cp.2010.0169

Cited by 6 publications

(3 citation statements)

References 7 publications

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“…Currently, EMA's are being utilized in thrust vector control in launchers [17,18]. EMA's are also evaluated for primary control surfaces [14,19,20], secondary flight controls [21,22] and landing gear steering [23]. A photograph of an aileron EMA is shown in Figure 1b.…”

Section: Introductionmentioning

confidence: 99%

Torque Limiters for Aerospace Actuator Application

et al. 2022

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Safety and reliability of electrical actuators are essential for success of all electric and more electric aircrafts (MEA). Torque limiters improve the reliability of electromechanical actuators (EMA) by restricting the amount of force experienced by the actuator drive train components. If transmitted torque in the shaft exceeds a limit, it gives way in a controlled manner. This protects the actuator from potential failure and jamming. In this paper, different types of existing torque limiters are investigated for their suitability in aerospace EMA application and further integration within the electric motor. They classified based on the torque transmission mechanism and each type is described in detail. Operating principle and basic characteristics are reported. Comparative evaluation of commercially available devices is presented. It is found that those based on friction based and permanent magnet are most suitable due to their good torque density, reliability and high speed capability. Further, based on the characteristics, integration of torque limiter within the actuator motor is investigated in this paper. An example actuator motor is considered for integration. Different integration options suitable for the different types of torque limiting devices are described. Reduction in overall volume is shown for the integration options. Such integration can lead to improved reliability as well as higher power density resulting in next-generation actuator electrical drives for MEA.

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Section: Introductionmentioning

confidence: 99%

Torque Limiters for Aerospace Actuator Application

et al. 2022

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“…There has been a recent increase in more-electric aircraft requiring the use of converter fed generation and load systems [1][2][3][4][5]. Whilst this trend is present in all aerospace sectors, it is perhaps most evident in Unmanned Aerial Vehicle (UAV) applications where novel technologies are driving the requirement for greater electrification of secondary systems [6].…”

Section: Introductionmentioning

confidence: 99%

“…Whilst this trend is present in all aerospace sectors, it is perhaps most evident in Unmanned Aerial Vehicle (UAV) applications where novel technologies are driving the requirement for greater electrification of secondary systems [6]. New aircraft designs typically employ multiple power electronic converter systems for power conversion and conditioning as well as utilising dc for part or all of the power distribution network in order to capitalise on efficiency, flexibility and power density benefits [3,5,7,8]. However the lightweight and effective protection of power dense, physically compact dc networks represents a significant barrier to more widespread adoption of dc power distribution for aircraft applications [7,9,10].…”

Section: Introductionmentioning

confidence: 99%

Determination of protection system requirements for DC unmanned aerial vehicle electrical power networks for enhanced capability and survivability

Fletcher

Norman

Galloway

et al. 2011

IET Electrical Systems in Transportation

111

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This version is available at https://strathprints.strath.ac.uk/33299/ Strathprints is designed to allow users to access the research output of the University of Strathclyde. Unless otherwise explicitly stated on the manuscript, Copyright © and Moral Rights for the papers on this site are retained by the individual authors and/or other copyright owners. Please check the manuscript for details of any other licences that may have been applied. You may not engage in further distribution of the material for any profitmaking activities or any commercial gain. You may freely distribute both the url (https://strathprints.strath.ac.uk/) and the content of this paper for research or private study, educational, or not-for-profit purposes without prior permission or charge.Any correspondence concerning this service should be sent to the AbstractA growing number of designs of future Unmanned Aerial Vehicle (UAV) applications utilise dc for the primary power distribution method. Such systems typically employ large numbers of power electronic converters as interfaces for novel loads and generators. The characteristic behaviour of these systems under electrical fault conditions, and in particular their natural response, can produce particularly demanding protection requirements. Whilst a number of protection methods for multi-terminal dc networks have been proposed in literature, these are not universally applicable and will not meet the specific protection challenges associated with the aerospace domain. Through extensive analysis, this paper seeks to determine the operating requirements of protection systems for compact dc networks proposed for future UAV applications, with particular emphasis on dealing with the issues of capacitive discharge in these compact networks. The capability of existing multi-terminal dc network protection methods and technologies are then assessed against these criteria in order to determine their suitability for UAV applications. Recommendations for best protection practice are then proposed and key inhibiting research challenges are discussed.

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Practical computation of di/dt for high-speed protection of DC microgrids

Rakhra

Norman

et al. 2017

2017 IEEE Second International Conference on DC Microgrids (ICDCM)

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DC microgrids have the potential to radically disrupt the distribution system market due to the benefits offered in easing the integration and control of distributed renewable energy resources and energy storage systems. However, the nonzero-crossing fault current profiles associated with short-circuited DC systems present a major challenge for protection. Isolation of faulted networks prior to the peak-current discharge of DC side capacitors may address this challenge if rapid fault detection speeds (shorter than 2ms) can be achieved. Accordingly, novel methods of utilizing the rate-of-change-of-current (di/dt) have been proposed in the literature to realize new, high-speed distance protection strategies. This paper proposes two practical methods for optimizing the numerical computation of di/dt of fault current transients and evaluates the performance of each within a MATLAB/Simulink model of a DC microgrid with artificially injected measurement noise

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A fault tolerant electric drive for an aircraft nose wheel steering actuator

Cited by 6 publications

References 7 publications

Torque Limiters for Aerospace Actuator Application

Torque Limiters for Aerospace Actuator Application

Determination of protection system requirements for DC unmanned aerial vehicle electrical power networks for enhanced capability and survivability

Practical computation of di/dt for high-speed protection of DC microgrids

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