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Fault-tolerant electric drive for an aircraft nose wheel steering actuator

Fault-tolerant electric drive for an aircraft nose wheel steering actuator

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© The Institution of Engineering and Technology
Published

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

Inspec keywords: steering systems; aircraft testing; fault tolerance; dynamometers; motor drives; electromechanical actuators; electric vehicles

Other keywords: motor dynamometer performance analysis; hydraulic load rig; dual three-phase motor; aircraft nose wheel steering actuator; fault-tolerant electric drive; isolated communication link; independent motor controllers; dual-lane electric drive

Subjects: Transportation; Control gear and apparatus; Aerospace testing and simulation; Drives

References

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      • Haylock, J.A., Mecrow, B.C., Jack, A.G., Atkinson, D.J.: `Operation of a fault tolerant PM drive for an aerospace fuel pump application', Eighth Int. Conf. on Electrical Machines and Drives (Conf. Publ. No. 444), 1–3 September 1997, p. 133–137.
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