Aircraft Electrical Landing Gear Actuation Using Dual-output Power Converter with Mutual Power Circuit Components

Wijekoon, Thiwanka; Empringham, Lee; Wheeler, Patrick; Clare, John; Whitley, C.; Towers, G.

doi:10.1109/apec.2009.4802826

Cited by 15 publications

(6 citation statements)

References 6 publications

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“…For example, in [8], the authors analyse the use of power electronics and electromechanical actuation for the steering of the nose landing gear, with the use of a dual three-phase motor. In [9], the authors show the architecture adopted for the retraction of the landing gear, which consists of a dual output power converter feeding two different motors, one utilised for the retraction and the other for the steering. In [10], the authors demonstrate the optimal design of electromechanical actuators for the retraction and extension of the landing gear of a helicopter: the analysis takes into consideration a system design level approach, in order to minimise the total weight and guarantee the required reliability.…”

Section: Application Of Electrical Drives In Aerospacementioning

confidence: 99%

Design of a five‐phase permanent‐magnet motor for the electric steering of an aircraft nose landing gear

Noia

Rizzo

2017

IET Electrical Systems in Transportation

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Recently, there has been a growing interest in reducing the number or replacing the hydraulic/pneumatic actuators utilised on aircraft with electric actuators coupled to mechanical gears, which would improve the reliability and performance. This is involved in the concept of more electric aircraft. The electrification of actuators would affect the primary and secondary flight controls, as well as the movement of flight surfaces, retraction of the landing gear, and steering of the nose landing gear, which is also considered in this study. This study considers the design of a multiphase permanent-magnet (PM) motor to be utilised for the electric steering of a commercial aircraft nose landing gear. This multiphase motor would make it possible to achieve a highly reliable actuator and, coupled with a harmonic drive, avoid the use of a multi-motor configuration. Moreover, a multiphase motor would increase the power density and efficiency of the actuator, through improving the torque ripple. The performance variation due to temperature swings is considered, and a design procedure for the PM motor is described using the worse operation case for the electric actuator. The adequate performance of the designed motor and actuator is demonstrated by means of a finite element analysis.

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Section: Application Of Electrical Drives In Aerospacementioning

confidence: 99%

Design of a five‐phase permanent‐magnet motor for the electric steering of an aircraft nose landing gear

Noia

Rizzo

2017

IET Electrical Systems in Transportation

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“…Although the tolerance of a single fault can be achieved with two motors and a clutch or speed-summing arrangement [3], a fault-tolerant motor was developed to minimise the mechanical components.…”

Section: Electromechanical Nose Wheel Steeringmentioning

confidence: 99%

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

Bennett

Mecrow

Atkinson

et al. 2010

5th IET International Conference on Power Electronics, Machines and Drives (PEMD 2010)

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This paper describes the design and testing of a dual-lane electric drive for the operation of a prototype, electromechanically actuated, nose wheel steering system for a commercial aircraft. The drive features two fully independent motor controllers, each operating one half of a three-phase motor to produce an actuator capable of full operation in the event of an electrical fault. An isolated communications link between the controllers allows for consolidation of parameters to identify faults and synchronise outputs to ensure even load sharing. A selection of results is presented from motor dynamometer performance analysis and fully loaded output tests on an Airbus hydraulic test rig at Filton, UK.

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“…According to application of a different Remote Electronic Unit will also provide a high different integrity and command with the monitoring system and interfacing to various high feedback to position with sensors also providing appropriate demands to the dual-output Motor Control system Unit [16]…”

Section: A Remote Electronic Unitmentioning

confidence: 99%

Landing Gear of an Aircraft Structure: A Review

Dubey¹,

Gupta²,

Undavalli³

et al. 2015

IJERT

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The landing gear system of an aircraft is a system. It also absorbs the energy from the impact of landing Numerical type simulation has become highly invaluable tool for the assessment of the landing gear type dynamics also as well as of aircraft landing structure gear interaction. This paper also describes the normal structure review of a simple landing-gear structure model system, and which is accurately simulates with the energy system absorbed by the gear without the adding substantial structure and complexity with the model. it carries the structure aircraft weight at all require ground operations, including, landing, take off, taxiing, and towing. In future we know that advances in computational type speed have made aircraft and high spacecraft crash simulations design using an explicit, transient type dynamic, finite element analysis (FEM) code are the more feasible. For a plane crash model type system the landing gear is also exact response is approximated work with a many strong spring where many different force applied to the different fuselage. And it is also computed in a userwritten works type. Helicopter crash type simulations which is using this approach that are compared with different necessary data is also acquired with the experimental method and data from a full structure crash structure test can be achieved by with the use of an aircraft of a composite. Depends on type of landing gear systems is also presented. Specifically, a nonlinear type model can easily developed which is simulated, and against static and dynamic data test data. Many type model includes nonlinear structure effects such as a velocity type squared related high damping, poly tropic gas law, stick-slip friction, a geometry governed with the high model structure for the high discharge type coefficients and methods, effects a nonlinear spring and damping model structure.

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Aircraft Electrical Landing Gear Actuation Using Dual-output Power Converter with Mutual Power Circuit Components

Cited by 15 publications

References 6 publications

Design of a five‐phase permanent‐magnet motor for the electric steering of an aircraft nose landing gear

Design of a five‐phase permanent‐magnet motor for the electric steering of an aircraft nose landing gear

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

Landing Gear of an Aircraft Structure: A Review

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