Overview of Electric Motor Technologies Used for More Electric Aircraft (MEA)

Cao, Wenping; Mecrow, B.C.; Atkinson, Glynn; Bennett, John W.; Atkinson, Dave

doi:10.1109/tie.2011.2165453

Cited by 793 publications

(146 citation statements)

References 57 publications

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“…Indeed, these motors allow the development of any torque at any speed. Designing an electrical motor under aeronautical constraints is a very complicated process, as it requires to make a compromise between several aspects [18,19], for example:…”

Section: Classification Of Electric Machinementioning

confidence: 99%

“…All these methods were compared according to the mean squared error (MSE) between the raw signal and the noise-suppressed signal as well as the execution time of filtering in [26]. By definition, the normalized MSE is: (19) X is is the noisy sequence, Y the filtered sequence, n the number of samples for which X is defined and the total noise power. Based on these criteria, methods of Wavelet Denoising and High-pass Filtering are most effective.…”

Section: Noise Suppression Techniquesmentioning

confidence: 99%

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Non-Intrusive Partial Discharges Investigations on Aeronautic Motors

Billard

Abadie

Taghia

2016

SAE Technical Paper Series

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OATAO is an open access repository that collects the work of Toulouse researchers and makes it freely available over the web where possible. This is an author-deposited version published in : http://oatao.univ-toulouse.fr/ Eprints ID : 18225 Any correspondence concerning this service should be sent to the repository administrator: staff-oatao@listes-diff.inp-toulouse.fr AbstractThe present paper reports non-electrically intrusive partial discharge investigations on an aeronautic motor. Relevancy, robustness and repeatability of partial discharge testing procedures, both on insulating materials characterization and on operating aeronautic equipment are essential to ensure reliability of the aircraft systems. The aim of this paper is to be the very first step of defining such procedures and the associated test equipment.To do so, the paper will start by providing an understanding of partial discharge phenomena and will review typical more electrical aircraft architecture. Key characteristics causing partial discharge risk to increase will be highlighted. The impact of harness length, high performance power electronics and voltage level increase on insulation system is demonstrated.Then, an analysis is carried out from motor design perspective to find out which test procedure is relevant to assess each insulation system performance both at atmospheric and reduced pressures. The study helps to realize the benefits of using multiple test sample and procedure to assess insulation system performance level through the design process of the motor. It is shown that a good agreement observed between stator and representative samples. This paper will also review the ability of the non-intrusive test method to detect partial discharge with a full scope of voltage signal from AC to impulse voltage and under different pressures. The paper concludes with an analysis of results and thoughts about future work regarding motor design taking into account partial discharge risk and evolution of proposed procedure.

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Section: Classification Of Electric Machinementioning

confidence: 99%

Section: Noise Suppression Techniquesmentioning

confidence: 99%

Non-Intrusive Partial Discharges Investigations on Aeronautic Motors

Billard

Abadie

Taghia

2016

SAE Technical Paper Series

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“…Multi-stage drivetrains exist in transport applications, for example to provide propulsion on automotive and marine systems, and electrical power generation for auxiliary loads on aircraft [6]. Interaction has been observed in a range of systems, for example sub-synchronous resonance in land based power generation [7,8] causing early fatigue of mechanical components [9], challenges for wind power generation [10,11] causing gearbox failure [12], unpredicted faults in industrial processes such as mills [13], excessive vibration in electric and hybrid-electric vehicle drivetrains [2,14] increasing wear [4], and wave induced instability in marine propulsion systems [15].…”

Section: Introductionmentioning

confidence: 99%

Analysis of Electromechanical Interaction in Aircraft Generator Systems

Feehally

Damian

Apsley

2016

IEEE Trans. on Ind. Applicat.

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Abstract-The supply of electrical power is usually achieved by a generator, driven from a prime mover, by some form of mechanical drivetrain. Such an electro-mechanical system will have natural resonant modes in both the electrical and mechanical subsystems. The electrical generator provides a coupling between the subsystems, transferring not only useful power but also disturbances between electrical and mechanical domains: these disturbances may excite resonances resulting in cross-domain (electro-mechanical) interaction. This can lead to lifetime reduction in the mechanical components and instability in the electrical network, resulting in poor reliability for the wider system, and potentially catastrophic component failure. Electro-mechanical interaction is particularly critical in power generation systems onboard aircraft, because the generator is driven by a gas turbine via an inherently low-stiffness drive train. It is then critical to identify electro-mechanical interaction at the design stage so that these issues can be avoided. However, predicting the occurrence of interaction, through simulation, is challenging, requiring multi-domain models, operating with different time scales. This paper analyses an aircraft auxiliary power offtake to produce a reduced-order mechanical drivetrain model, allowing the modal frequencies to be predicted and crossdomain interactions to be modelled. A purpose-built electromechanical test platform is used to validate the model and demonstrate how electrical disturbances are passed through the generator to the mechanical system and affect the electrical network. Future research will use the test bed to demonstrate strategies for avoiding or suppressing unwanted interactions.

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“…A simplified thermal model is also grafted into the system model to effectively simulate the dynamic behavior of the machine during healthy, inter-turn SC [1][2][3][4] are increasingly being used in safety critical applications such as in aircraft and other transportation systems. In such applications the necessary system reliability level can be reached by designing for fault tolerance and hence avoiding replicating the complete drive system [5]. This generally leads to a reduced overall system weight and component count.…”

mentioning

confidence: 99%

“…A typical fault-tolerant Permanent Magnet Synchronous Machine (FT-PMSM) drive topology includes a number of design features [5][6][7][8][9][10][11][12][13] to enable a level of operation when faults [3,[13][14][15][16][17] ensue. Although such a machine drive topology, if appropriately designed, can potentially tolerate converter failures, winding open circuit failures and terminal SC failures, a winding inter-turn (a single turn) SC fault remains problematic [6].…”

mentioning

confidence: 99%