A prototype electrical actuator for aircraft flaps and slats

Bennett, John W.; Mecrow, B.C.; Jack, A.G.; Atkinson, David; Sheldon, Stuart; Cooper, B. S.; Mason, Greg; Sewell, C.; Cudley, D.

doi:10.1109/iemdc.2005.195699

Cited by 26 publications

(7 citation statements)

References 10 publications

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“…This allows a predicted current/speed profile to be plotted for one phase of the shorted motor and shows a close match to the measured profile. At high speeds, the resistive term becomes negligible and the current profile tends towards: L k i e = ( 5 ) which predicts a peak current of 6.4A.…”

Section: Dynamometer Test Resultsmentioning

confidence: 96%

“…With the application of a terminal short-circuit, the failed lane of the motor will exert a drag torque and the remaining lane must overcome this and provide rated torque. It can be shown that the peak of this braking torque is half the rated motoring torque [5]. In the case of the dual three-phase motor, if one lane must provide 1 p.u.…”

Section: Dual-lane Motor Drivementioning

confidence: 98%

See 1 more Smart Citation

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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Section: Dynamometer Test Resultsmentioning

confidence: 96%

Section: Dual-lane Motor Drivementioning

confidence: 98%

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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“…While reliable, mechanically linked flap systems are limited in terms of operational flexibility, and more recently distributed flap drive concepts have been proposed. [31][32][33][34][35] Potential benefits include a reduction in weight, simplication and localization of the flap system, reduction in total parts count, and possibility of Differential Flap Settings (DFS). 16 Unfortunately, the estimation of actuation loads for the high lift devices is more complex than that for the hinged control surfaces treated previously.…”

Section: B Spoilersmentioning

confidence: 99%

Development of a Sizing and Analysis Tool for Electrohydrostatic and Electromechanical Actuators for the More Electric Aircraft

Chakraborty

Jackson

Trawick

et al. 2013

2013 Aviation Technology, Integration, and Operations Conference

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This work documents the development of a MATLAB/Simulink based methodology for the sizing, simulation, analysis, and optimization of electric actuators for the primary and secondary control surfaces of a More Electric Aircraft. For a given aircraft and control surface configuration, the control surface flight loads are first evaluated taking into account their aerodynamic characteristics and the critical flight conditions relevant to each. With this information, the performance of a given actuator design can be analyzed via a simulation of the actuator and thermal dynamics. Conversely, for a given objective function and constraint set, the actuator design can be optimized through the solution of a constrained optimization problem. This work focuses on the development of the flight load estimation capability, the modeling and simulation environment, and the weight estimation method, while a separate work describes the actuator optimization problem and a study of actuator-to-surface allocation. While applicable to a wide variety of aircraft, the current work analyzes electrohydrostatic and electromechanical actuators using the Boeing 737-800 aircraft as a test case.

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“…They are especially utilized for moving control surfaces that must satisfy a reliability requirement of 10 −9 failure per hour and their performance is hardly affected even after a large number of cycles. It is only recently that electrical mechanisms have reached equivalent levels of safety and have been used to control control-surfaces in aircraft [4].…”

Section: Reliability and Environmental Constraintsmentioning

confidence: 99%