On modern rotorcraft, electro-mechanical actuators (EMAs) are progressively replacing the bulky and more expensive hydraulic and/or pneumatic systems. Although the migration towards alternative actuation solutions, reliability remains a key requirement for aerospace applications. Fault-tolerant electrical machines are often employed for ensuring the demanded reliability level. In this paper, the design of a dual three-phase winding permanent magnet synchronous machine (PMSM) for helicopter nose landing gear extension/retraction EMA is addressed. Finite element (FE) simulations are used for evaluating the PMSM performance in both healthy and faulty conditions. The compensation strategy implemented on the healthy three-phase winding, while the second one is completely shorted, is also discussed. Finally, a purposely built dual three-phase winding PMSM model is implemented in Dymola environment, where the extension/retraction EMA is simulated. Hence, EMA behaviour under both healthy and faulty conditions is analysed.

Design of Fault-Tolerant Dual Three-Phase Winding PMSM for Helicopter Landing Gear EMA / Giangrande, P.; Madonna, V.; Nuzzo, S.; Galea, M.. - (2019), pp. 1-6. (Intervento presentato al convegno 2018 IEEE International Conference on Electrical Systems for Aircraft, Railway, Ship Propulsion and Road Vehicles and International Transportation Electrification Conference, ESARS-ITEC 2018 tenutosi a gbr nel 2018) [10.1109/ESARS-ITEC.2018.8607684].

Design of Fault-Tolerant Dual Three-Phase Winding PMSM for Helicopter Landing Gear EMA

Nuzzo S.;
2019

Abstract

On modern rotorcraft, electro-mechanical actuators (EMAs) are progressively replacing the bulky and more expensive hydraulic and/or pneumatic systems. Although the migration towards alternative actuation solutions, reliability remains a key requirement for aerospace applications. Fault-tolerant electrical machines are often employed for ensuring the demanded reliability level. In this paper, the design of a dual three-phase winding permanent magnet synchronous machine (PMSM) for helicopter nose landing gear extension/retraction EMA is addressed. Finite element (FE) simulations are used for evaluating the PMSM performance in both healthy and faulty conditions. The compensation strategy implemented on the healthy three-phase winding, while the second one is completely shorted, is also discussed. Finally, a purposely built dual three-phase winding PMSM model is implemented in Dymola environment, where the extension/retraction EMA is simulated. Hence, EMA behaviour under both healthy and faulty conditions is analysed.
2019
2018 IEEE International Conference on Electrical Systems for Aircraft, Railway, Ship Propulsion and Road Vehicles and International Transportation Electrification Conference, ESARS-ITEC 2018
gbr
2018
1
6
Giangrande, P.; Madonna, V.; Nuzzo, S.; Galea, M.
Design of Fault-Tolerant Dual Three-Phase Winding PMSM for Helicopter Landing Gear EMA / Giangrande, P.; Madonna, V.; Nuzzo, S.; Galea, M.. - (2019), pp. 1-6. (Intervento presentato al convegno 2018 IEEE International Conference on Electrical Systems for Aircraft, Railway, Ship Propulsion and Road Vehicles and International Transportation Electrification Conference, ESARS-ITEC 2018 tenutosi a gbr nel 2018) [10.1109/ESARS-ITEC.2018.8607684].
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11380/1237581
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