Influence of rotor endcaps on the electromagnetic performance of high‐speed PM machine

IEEE Trans. Transp. Electrific.

Galea

2018

Self Cite

479

194

Abstract-The constant growth of air traffic, the demand for performance optimization and the need for decreasing both operating and maintenance costs have encouraged the aircraft industry to move towards more electric solutions. As a result of this trend, electric power required on board of aircraft has significantly increased through the years, causing major changes in electric power system architectures. Considering this scenario, the paper gives a review about the evolution of electric power generation systems in aircraft. The major achievements are highlighted and the rationale behind some significant developments discussed. After a brief historical overview of the early DC generators (both wind-and engine-driven), the reasons which brought the definitive passage to the AC generation, for larger aircraft, are presented and explained. Several AC generation systems are investigated with particular attention being focused on the voltage levels and the generator technology. Further, examples of commercial aircraft implementing AC generation systems are provided. Finally, the trends towards modern generation systems are also considered giving prominence to their challenges and feasibility.

Section: ) Enabling Technologiesmentioning

confidence: 99%

Electrical Power Generation in Aircraft: Review, Challenges, and Opportunities

Madonna

IEEE Trans. Transp. Electrific.

Galea

2018

Self Cite

479

194

“…Lower eddy losses are observed when the end-effect and end-windings are included, i.e. 3D-FEA, due to the end-effect leakage and stator flux-leakage, which results in lower eddy current and therefore lower losses [23][24].…”

Section: B Stator Core Lossmentioning

confidence: 99%

Design and Losses Analysis of a High Power Density Machine for Flooded Pump Applications

Al-Timimy

IEEE Trans. on Ind. Applicat.

Degano

et al. 2018

Self Cite

Abstract-This paper describes the design process of a 10 kW 19000 rpm high power density surface mounted permanent magnet synchronous machine for a directly coupled pump application. In order to meet the required specifications, a compact machine, with cooling channels inside the slots and flooded airgap, has been designed through finite element optimization. For high power density, high speed machines, an accurate evaluation of the power losses and the electromechanical performance is always extremely challenging. In this case, the completely flooded application adds to the general complexity. Therefore this paper deals with a detailed losses analysis (copper, core, eddy current and mechanical losses) considering several operating conditions. The experimental measurements of AC copper losses as well as the material properties (BH curve and specific core losses), including the manufacturing process effect on the stator core, are presented. Accurate 3D finite element models and computational fluid dynamics analysis have been used to determine the eddy current losses in the rotor and windage losses respectively. Based on these detailed analysis, the no load and full load performance are evaluated. The experimental results, on the manufactured prototype, are finally presented to validate the machine design.Index Terms-High power density, high speed, losses calculation, performance analysis, permanent magnet motors.

“…Among the electrical machines adopted in aerospace applications, permanent magnet synchronous machines (PMSMs) are a common choice for EMAs since they are characterized by high-power density and excellent efficiency [18][19][20][21][22]. In this paper, the design of a PMSM integrated into a linear geared EMA for flight control surface is presented.…”

Section: Imentioning

confidence: 99%

Design and Testing of PMSM for Aerospace EMA Applications

IECON 2018 - 44th Annual Conference of the IEEE Industrial Electronics Society

Madonna

Sala

et al. 2018

The more-electric aircraft initiative represents an important technology step-change for the aircraft industry. The reduction of both fuel consumption and environmental impact are leading to alternative solutions for actuating the flight control surfaces. The traditional hydraulic systems, are progressively being replaced with electrically powered actuators. In this scenario, electromechanical actuators are gaining an ever-increasing importance as enabling technology for next generation aircraft. This paper presents the design and testing of a permanent magnet synchronous motor driving a linear geared electromechanical actuator for commercial aircraft. The experimental results are discussed throughout the paper and compared to the finite element ones obtained at the design stage. Finally, the machine is integrated into the mechanical drivetrain and the electromechanical actuator performance is evaluated through experimental tests carried out on a purpose-built mechanical demonstrator for achieving a high technology readiness level.