Future more electric aircraft (MEA) architectures require a new generation of power-by-wire actuators, e.g. Electro Hydrostatic Actuators (EHA). These units have to be capable of frontline operation of safety critical flight control surfaces over the entire aircraft life. Prove of robustness becomes a challenging objective. This paper illustrates the Liebherr-Aerospace EHA technology as well as methods for validation of robustness. It gives an insight regarding the design of a robust piston pump.

Les avionneurs expriment le besoin de développement de l’avion plus « électrique ». Cela se traduit par des besoins nouveaux en matière de systèmes de motorisation électrique, en termes de puissance à fournir et de partage de ressources matérielles en vue de minimiser la masse embarquée et les coûts. Parmi les études en cours sur l’évolution des machines tournantes, un intérêt particulier porte sur le développement des alterno-démarreurs de type machines synchrones sans balais et à plusieurs étages (BSSG). Celles-ci sont susceptibles de fournir un fort couple lors des phases de démarrage des réacteurs auxquelles elles sont associées. Pour ce faire, la connaissance, à tout moment, de la position du rotor est essentielle. Cependant, l'ajout d’un capteur dédié impacte la conception de la machine, rajoutant du volume, du câblage et augmentant le coût. La réalisation d'une commande dite « sensorless » permettrait de s'affranchir de l'utilisation d'un tel capteur et de simplifier le design des alterno-démarreurs.A partir d'une modélisation fine de la machine, cette thèse étudie les conditions dans lesquelles une telle commande est réalisable et analyse plusieurs techniques permettant d'y parvenir. Une nouvelle méthode d'estimation de la position du rotor, spécifique aux BSSG est proposée, puis illustrée avec des résultats expérimentaux. Cette technique est basée sur le traitement des composantes harmoniques existantes naturellement au stator de la machine et permet l'estimation de la position à l'arrêt et à très basse vitesse. Afin d'étendre l'estimation sur toute la plage de vitesse, une étude d'estimation de position par un observateur d'état à base du modèle complet de la machine en considérant les harmonique injectés (ou existantes) dans les courants du stator est proposée. Cet observateur peut s’appliquer à la machine synchrone à trois étages mais aussi à toute machine synchrone. Dans cette étude, son fonctionnement est illustré sur une machine synchrone à aimants permanents. / The aircraft manufacturers express the need to develop a more "electric" aircraft. This brings forward new requirements for the electric drive systems in terms of increasing the available on-board power and resource sharing in order to optimize the overall mass and cost. Among the ongoing studies on the evolution of motor drives, a particular interest is given to the development of multi-level brushless synchronous starter/generators (BSSG). These drives are likely to provide the high torque required to start-up the reactors to which they are associated. For this purpose, the knowledge, at any time, of the rotor position is essential. However, adding a dedicated sensor impacts on the design of the machine, increasing volume, cabling needs and cost. For this purpose, investigating on “sensorless” control laws will permit to avoid using such a sensor and to simplify the design of the Starter/Generators.Using a fine modelling of the machine, this work studies the conditions of feasibility for sensorless control and analyzes several techniques for this purpose. A new method of estimation of the shaft-position, particular to the BSSG architecture is proposed and then illustrated with experimental results. This technique is based on the processing of the existing harmonic components naturally in the stator of the machine and allows the estimation of the position at standstill and the very low speed. To extend the estimation to the whole speed range, a study of position estimation using a state observer using the complete model of the machine considering the knowledge of the existing (or injected) harmonic components in the stator currents is proposed. This observer can be applied to the brushless synchronous starter/generator but also on generic synchronous machines. In this study, its performance is illustrated on a permanent magnet synchronous machine.

Enhancing performance of power electronics converters has always been an interesting topic in the power electronics community. Over the years, researchers and engineers are developing new high performance component, novel converter topologies, smart control methods and optimal design procedures to improve the efficiency, power density, reliability and reducing the cost. Besides pursuing high performance, researchers and engineers are striving to modularize the power electronics converters, which provides redundancy, flexibility and standardization to the end users. The trend of modularization has been seen in photovoltaic inverters, telecommunication power supplies, and recently, HVDC applications. A systematic optimal design approach for modular power converters is developed in this dissertation. The converters are developed for aerospace applications where there are stringent requirement on converter form factor, loss dissipation, thermal management and electromagnetic interference (EMI) performance. This work proposed an optimal design approach to maximize the nominal power of the power converters considering all the constraints, which fully reveals the power processing potential. Specifically, this work studied three-phase active front-end converter, three-phase isolated ac/dc converter and inverter. The key models (with special attention paid to semiconductor switching loss model), detailed design procedures and key design considerations are elaborated. With the proposed design framework, influence of key design variables, e.g. converter topology, switching frequency, etc. is thoroughly studied. Besides optimal design procedure, control issues in paralleling modular converters are discussed. A master-slave control architecture is used. The slave controllers not only follow the command broadcasted by the master controller, but also synchronize the high frequency clock to the master controller. The control architecture eliminates the communication between the slave controllers but keeps paralleled modules well synchronized, enabling a fully modularized design. Furthermore, the implementation issues of modularity are discussed. Although modularizing converters under form factor constraints adds flexibility to the system, it limits the design space by forbidding oversized components. This work studies the influence of the form factor by exploring the maximal nominal power of a double-sized converter module and comparing it with that of two paralleled modules. The tradeoff between modularity and performance is revealed by this study. Another implementation issue is related to EMI. Scaling up system capacity by paralleling converter modules induces EMI issues in both signal level and system level. This work investigates the mechanisms and provides solutions to the EMI problems. / Ph. D. / As penetration of power electronics technologies in electric power delivery keeps increasing, performance of power electronics converters becomes a key factor in energy delivery efficacy and sustainability. Enhancing performance of power electronics converters reduces footprint, energy waste and delivery cost, and ultimately, promoting a sustainable energy use. Over the years, researchers and engineers are developing new technologies, including high performance component, novel converter topologies, smart control methods and optimal design procedures to improve the efficiency, power density, reliability and reducing the cost of power electronics converters. Besides pursuing high performance, researchers and engineers are striving to modularize the power electronics converters, enabling power electronics converters to be used in a “plug-and-play” fashion. Modularization provides redundancy, flexibility and standardization to the end users. The trend of modularization has been seen in applications that process electric power from several Watts to Megawatts. This dissertation discusses the design framework for incorporating modularization into existing converter design procedure, synergically achieving performance optimization and modularity. A systematic optimal design approach for modular power converters is developed in this dissertation. The converters are developed for aerospace applications where there is stringent v requirement on converter dimensions, loss dissipation, and thermal management. Besides, to ensure stable operation of the onboard power system, filters comprising of inductors and capacitors are necessary to reduce the electromagnetic interference (EMI). Owning to the considerable weight and size of the inductors and capacitors, filter design is one of the key component in converter design. This work proposed an optimal design approach that synergically optimizes performance and promotes modularity while complying with the entire aerospace requirement. Specifically, this work studied three-phase active front-end converter, three-phase isolated ac/dc converter and three-phase inverter. The key models, detailed design procedures and key design considerations are elaborated. Experimental results validate the design framework and key models, and demonstrates cutting-edge converter performance. To enable a fully modularized design, control of modular converters, with focus on synchronizing the modular converters, is discussed. This work proposed a communication structure that minimizes communication resources and achieves seamless synchronization among multiple modular converters that operate in parallel. The communication scheme is demonstrated by experiments. Besides, the implementation issues of modularity are discussed. Although modularizing converters under form factor constraints adds flexibility to the system, it limits the design space by forbidding oversized components. This work studies the impact of modularity by comparing performance of a double-sized converter module with two paralleled modules. The tradeoff between modularity and performance is revealed by this study.

In More Electric Aircraft, different power system activities are attributed to electrical means such as the start-up of the main engine. In this context, the study of the sensorless control of the Brushless Synchronous Starter Generator (BSSG) that is used to electrically start the main engine is revealed to be a very interesting issue. For long time, the elimination of the mechanical sensor was highly recommended for reliability, cost, weight, integration issues.Hence, this work aims to transpose the results obtained in the research area to an avionic testbench. It presents an adaptive sensorless technique to use when electrically starting the main engine of the aircraft. This is achieved by elaborating three different methods selected depending on the speed of the machine and based on the :- injection of a high frequency signal- use of the back-emf of the Permanent Magnet Generator (PMG)- use of the extended Kalman Filter EKFIn this work, it is shown that the …first method gives good position estimation results from standstill up to 8% of the rated speed. Then, the back-emfs of the PMG are used to detect the position of the BSSG when the speed exceeds the 8% of the rated speed. Good results are observed with this method at medium and high speed.For redundancy reasons, the EKF was also used in this work. Thus, the estimated position can be delivered via two different estimation algorithms in medium and high speed region.The implementation of the algorithm was achieved on an FPGA board since the latter can ensure a very tiny execution time. The fastness of the treatment ensures quasi-instantaneous position estimation and does not practically introduce any phase lag in the position estimation. / Aujourd'hui, l'aviation est en train de vivre des évolutions technologiques concernant surtout l'attribution de différentes fonctionnalités aux équipements électriques et ceci au détriment d'équipements hydrauliques et mécaniques assurant les mêmes fonctionnalités.Dans le cadre de l'avion plus électrique, le démarrage électrique sans capteurs mécaniques de la turbine de l'avion préoccupe les avionneurs de nos jours. Les problèmes introduits par ce capteur ont été identifiés : problèmes de coût et de poids, problèmes de fiabilité et d'intégration.Ce travail présente alors une commande sans capteurs pour la machine synchrone à trois étages à utiliser durant le démarrage électrique de l'avion. Ceci est réalisé avec trois méthodes de détection de la position selon la vitesse de rotation, basées sur :- l'injection d'un signal à haute fréquence- l'utilisation d'un filtre de Kalman étendu FKE- les fém. du PMG (Permanent Magnet Generator) La première méthode donne de bons résultats d'estimation depuis l'arrêt jusqu'à 8% de la vitesse nominale de la machine. Au-delà de cette vitesse, es valeurs des fém. du PMG deviennent assez élevées pour être utilisées dans l'estimation de la position. De bons résultats sont obtenus à moyenne et haute vitesse.Pour des questions de redondance, le FKE est aussi utilisé. Ainsi, la position estimée peut être fournie par l'un des deux algorithmes à moyenne et haute vitesse.L'implémentation de ces algorithmes est réalisée via une carte FPGA étant donné que celui-ci garantit un temps d'exécution. La rapidité de traitement garantit une estimation de la position quasi-instantanée et donc n'introduit pratiquement pas des retards dans l'estimation.

La thèse porte sur la caractérisation expérimentale des pertes singulières dans les matériaux magnétiques au sein d’actionneurs électromécaniques conçus pour le développement du programme « avion plus électrique », où la maîtrise des pertes d’énergie est un enjeu absolument majeur. Ce programme, de portée mondiale, vise, entre autre, à remplacer, dans l’avion, les actionneurs hydrauliques par des actionneurs électromécaniques, quand c’est possible.Par pertes singulières on entend toutes les pertes liées aux contraintes magnéto-mécano-thermiques liées d’une part à la mise en œuvre (découpe, assemblage contraint, isolation, traitement thermique...) des matériaux et d’autre part aux conditions réelles de fonctionnement (champ tournant, haute fréquence, saturations locales...) au sein des machines électriques (HV/HF), et qui sont très difficiles à estimer précisément de façon analytique ou via les dispositifs conventionnels de tests. Ces sollicitations influencent les caractéristiques de tôles qui peuvent s’éloigner significativement des données du fabricant (donc fausser le calcul des performances).Au début de cette thèse on s’est focalisé sur le montage d’un banc d’essai évolutif équipé de moyens de mesure directe du couple et d’une machine d’entraînement (8 ktr/min ; 42 kW) tarée par nos soins. Sur cette dernière une longue campagne d’essais a été menée pour isoler les différentes composantes de pertes, dont, par exemple, les pertes mécaniques (par frottement dans les roulements + aérodynamiques) qui ont été quantifiées via un rotor neutre. Les pertes dans les aimants sont indissociables des pertes fer, donc, elles ont été estimées par le biais d’une modélisation par éléments finis tridimensionnelle. Les pertes dans la frette de maintien sont nulles du fait qu’elle est isolante (thermo-rétractable). Le bobinage utilisé dans ce moteur est très particulier, à barres massives (remplissage de cuivre dans l’encoche jusqu’à 90%), développé dans notre laboratoire IES. Les pertes atypiques au sein de ce bobinage spécial ont été profondément abordées dans ces travaux (effet de refoulement de courants, pertes aux extrémités de la machine...).Dans la dernière partie de cette thèse, nous avons exploré le fonctionnement des machines synchrones à aimants à haute fréquence afin d’accroître la densité de puissance de nos moteurs (pour franchir la barre de 2.5 kW/kg). Pour ce faire, après une étude détaillée, nous avons proposé en premier lieu un prototype avec des matériaux standard (stator FeCo Vacodur49 0.2mm, rotor FeSi, aimants NdFeB nuance N35EH, bobinage à barres cuivre) fonctionnant à 1666 Hz, tournant à 5000 tr/min, avec une densité de puissance de 4.5 kW/kg et un rendement de 94%. En second lieu, nous avons proposé un deuxième prototype de rendement plus faible (93%) mais qui a une densité de puissance proche de 6 kW/kg avec un rotor sans fer et un bobinage en Aluminium.Avant le montage final de ce prototype modulaire, nous avons effectué des mesures de pertes magnétiques, en conditions réelles de fonctionnement d’un moteur électrique, sur une multitude de tôles FeSi et FeCo (Vacodur49, NO20, M270-35A) avec la variation de différents procédés de fabrication: isolation (vernis thermo-collant « back-lack », vernis C5), découpe (laser, électroérosion) et traitement thermique. Pareillement, toutes les pertes mises en jeu ont été séparées (mécaniques, par courants induits dans les viroles...) pour pouvoir remonter aux pertes magnétiques et, donc, enfin, quantifier empiriquement le coefficient de majoration de pertes fer. / The main aim of this thesis was to study and experimentally assess the additional iron losses in the stator (electrical lamination steel) of high performance permanent magnet synchronous machines (PMSM) designed for aircraft applications, in relation with the “more-electric-aircraft” project. This international program consists of gradually introducing electrical systems to replace onboard hydraulic and pneumatic systems, for example to power the landing gear wheels (Electric Green Taxiing System)…The extra iron losses are caused by manufacturing processes (cutting, sticking, insulation, stacking, pressing, shrink-fitting, thermal treatment …) and the real conditions of use of electrical motor (namely: rotational flux, saturation, high frequency…). Indeed, the mechanical and thermal stresses during the manufacturing steps can deteriorate the magnetic properties of the material and significantly increase the iron losses. These aspects are difficult to accurately evaluate by analytical models or standard measurements (Epstein frame…) and require experimental assessment to precisely calculate the motor efficiency.First of all, we started by developing a test bench equipped with drive motor: PMSM 8000 RPM ; 42 kW. For accurate assessment, the losses in this machine are separated on the test bench, for example, the mechanical losses (bearings loss & windage loss) have been measured at different speed with a non-magnetic rotor. Rotor magnets eddy-current losses cannot be isolated from iron losses, for this reason they have been calculated using a 3D finite element model. To limit rotor loss we then used a non-conductive retaining sleeve (heat shrink sleeve). In the winding, we used bar-wound conductors, which is an original winding technology developed in our laboratory, and whose advantage among others is the unusual copper fill factor that reaches almost 90%.Subsequently, we explored the high frequency machines (>1 kHz) in order to increase the power-to-weight ratio (cross the threshold of 2.5 kW/kg). We proposed, the following to the analytical and finite element study, a first conventional prototype with a power-to-weight ratio equal to 4.5 kW/kg with: FeCo stator (Vacodur49 0.2 mm), FeSi rotor and NdFeB magnets (N35EH), operated at 1666 Hz, 5000 RPM and 94% efficiency at full load. A second motor had been also proposed with both rotor and winding in aluminum, in this case the power-to-weight ratio reaches around 6 kW with, however, less efficiency (93%).Finally, this HF motor was tested, at no load, on the aforementioned test bench. The experiments were carried out on a multitude of FeCo and FeSi stator core samples coming from different manufacturing processes (insulation: bonding varnish and C-5 varnish; cutting: laser and EDM “Electrical Discharge Machining”; thermal treatment) in real operating conditions of a high frequency PM machine in order to experimentally obtain the famous “additional coefficient” of iron losses (Kadd).

<p>In the process of designing an electric power supply system for an aircraft, parameters like low weight and low losses are important. Reliability, robustness and low cost are other important factors. In the Saab Gripen aircraft, the design of the primary power supply of the electric flight control system was updated by exchanging a switching transistor regulator to a magnetic amplifier (magamp). By introducing a magamp design, weight was saved and a more reliable power supply system at a lower cost was achieved.</p><p> In this particular case, with the power supply of the electric flight control system in the Saab Gripen fighter, advantage could be taken of a specific permanent magnet generator (PM-generator). The frequency of the generator offered the perfect conditions for a magamp controller. A key parameter in designing magnetic amplifiers (magamps) is low losses. New amorphous alloys offer new possibilities of the technique in designing magnetic amplifiers, because of their extremely low losses.</p><p> The core losses are evaluated by studying the equations and diagrams specifying the power losses. The core losses are evaluated and compared with the copper losses in the process of optimizing low weight and low losses. For this an engineering tool is developed and demonstrated.</p><p> Evaluations of the hysteresis characteristics for the magnetic alloys, as well as modeling and simulation of the core losses, are presented in this work. The modeling of the core losses includes hysteresis losses, eddy current losses and excess losses as well as copper losses. The losses are studied dynamically during realistic operational conditions. The model can be used for any generic analysis of hysteresis in magnetic circuits. Applications of magnetic amplifiers in aircrafts have been demonstrated to be a feasible alternative</p>

L’électricité prend une place de plus en plus importante dans les systèmes énergétiques embarqués. L’électricité est une forme d’énergie très malléable, facile à transporter et réglable ou transformable avec un très faible taux de pertes. L’énergie électrique, associée à des convertisseurs statiques, est plus facile à maîtriser que, par exemple, l’énergie hydraulique et/ou pneumatique, permettant un réglage plus fin et une réduction des coûts de maintenance. L’évolution de la puissance dans les modèles avioniques est marquante. Avec le nombre croissant de charges électroniques, un avion plus électrique avec un réseau à courant alternatif inclurait un grand nombre de redresseurs AC/DC qui devront respecter les normes de qualité secteur. Une solution pour la réduction de la masse serait de préférer un réseau HVDC (High Voltage DC Bus). Sur les futurs modèles avioniques plus électriques, les concepteurs envisageront des conversions HVDC/DC à partir de l’unité appelée BBCU (Buck Boost Converter Unit). Dans ce cas d’étude, un réseau de distribution en tension continue (±270Vdc) est connecté à un réseau de sécurité basse tension (28Vdc) avec un échange bidirectionnel de puissance pouvant atteindre 10kW. Le convertisseur statique assurant cette liaison représente de nouveaux défis pour l’électronique de puissance en termes de fiabilité, sûreté, détection de panne, rendement et réduction de masse et de coût. Le dimensionnement du convertisseur doit prendre en compte une conception optimale, en aéronautique ce critère est la masse. Dans le processus de dimensionnement et d’optimisation du convertisseur, il est donc impératif de prendre en compte trois facteurs principaux : 1) l’évolution des topologies de conversion, 2) l’évolution des composants actifs et passifs et 3) l’intégration de puissance. La réunion de ces trois facteurs permettra ainsi la miniaturisation des convertisseurs statiques. Dans un premier temps, nous préciserons la démarche adoptée pour le dimensionnement d’un convertisseur en prenant en compte : les topologies actives, les filtres différentiels et le système de refroidissement. Les différents éléments qui composent le convertisseur sont décrits dans un langage informatique orienté objet. Des facteurs de performances seront également introduits afin de faciliter le choix des semi-conducteurs, des condensateurs et du dissipateur pour un convertisseur statique. Dans un deuxième temps, nous présenterons le fonctionnement d’une topologie multicellulaire DC/DC, isolée pour l’application proposée. Nous présenterons les avantages du couplage de différentes phases de ce convertisseur. Nous introduirons les différentes associations des cellules et leurs avantages, possibles grâce à l’isolement, comme la mise en série et en parallèle. Puisque la caractérisation des pertes des semi-conducteurs est essentielle pour le dimensionnement du convertisseur statique, nous proposerons deux approches : un modèle de simulation relativement simple et paramétré à l’aide de seules notices constructeurs ; et une méthode de mesure des pertes dans les semi-conducteurs qui est à la fois précise et compatible avec les composants les plus rapides. En ce qui concerne les composants magnétiques, une surface de réponse des matériaux ferrites sera présentée. Nous allons décrire, par le biais analytique et de simulation, des modèles pour la détermination du champ magnétique à l’intérieur du noyau et des ondulations de courant engendrés. Finalement, en profitant des modèles et des résultats obtenus dans les sections précédentes, nous montrerons le dimensionnement et la réalisation de chaque partie du convertisseur BBCU 100kHz / 10kW. Une perspective d’un design idéal est également présentée. / The electricity is taking a more important place in the embedded systems. The electricity is a very moldable form of energy, easy to transport and adjustable or transformed with a very low losses. The electrical energy, associated with power converters, is easier to control than hydraulic and/or pneumatic energies for example, allowing a finer regulation and a cost cutting of maintenance. The installed power in the avionic models is growing fast. With the increasing number of electronic loads, a more electrical aircraft with an AC network would include a large number of rectifiers AC/DC which will have to respect the quality standards. A solution for the reduction of the mass would be to prefer a HVDC network (High Voltage DC BUS). On the future more electrical aircrafts, the designers will be facing a HVDC/DC power conversion. This is the role of the unit called BBCU (Buck Boost Converter Unit). In our case of study, a distribution network in DC voltage (± 270Vdc) is connected to a security low-voltage network (28Vdc) which includes a bidirectional power exchanges achieving 10kW. The power converter for this connection gives new challenges for the power electronics in terms of reliability, safety, failure detection, efficiency and reduction of mass and cost. The design of the power converter needs to take into account for an optimal design. It is thus imperative to take into account three main factors: 1) the evolution of the power topologies 2) the evolution of the active and passive devices and 3) the power integration. The meeting of these three factors will allow the miniaturization of the power converters. At first, the adopted approach for designing power converters, taking into account the power topology, the differential filters and the cooling system are presented. The various elements which compose the power converter are described in an Object-Oriented Programming. The performance factors will be introduced to facilitate the choice of semiconductors, capacitors and heat-sinks. Secondly, the operation phases of a multicellular isolated DC/DC topology for the proposed application are presented. A discussion of the advantages of the magnetic coupling is also introduced. Thanks to the isolation, different associations of switching cells, series or/and parallel connection, are possible. Knowing the losses of power semiconductors is an essential step to design a power converter, thus two approaches are proposed: 1) a simulation model using a relatively simple model with the datasheets information; and 2) a losses measurement method which is precise and compatible with the fastest devices. As regards the magnetic components, a response surface of ferrite materials will be presented. Some models for the determination of the magnetic field inside the core and the current ripple are also described. Finally, by taking advantage of models and results obtained in the previous sections, the design and the realization of each party of the BBCU power converter 100kHz / 10kW is showed. A perspective of an ideal design is also presented.

This master thesis has been carried out in collaboration with Saab, Avionics Systems in Jönköping, Sweden, during the spring of 2017. The thesis investigates unidirectional rectifier topologies in aircraft and the focus has been on evaluating the power quality requirements according to the aircraft standards, in the course of the More Electric Aircraft concept. Both passive and active power factor correction topologies are considered, discussed and compared. Simulation models are designed in MATLAB/Simulink and the procedures are presented. A modular concept regarding components is discussed where different power supplies and loads are considered. The simulations present both a passive 12-pulse auto-transformer rectifier unit and an active Delta-switch rectifier fulfilling requirements for aircraft such as the total harmonic distortion of the supply current. In addition, the input power factor is close to unity and an efficiency greater than 97% is obtained. Lastly, future aspects of each topology are discussed and necessary improvements to obtain realistic simulation models are presented.

In the process of designing an electric power supply system for an aircraft, parameters like low weight and low losses are important. Reliability, robustness and low cost are other important factors. In the Saab Gripen aircraft, the design of the primary power supply of the electric flight control system was updated by exchanging a switching transistor regulator to a magnetic amplifier (magamp). By introducing a magamp design, weight was saved and a more reliable power supply system at a lower cost was achieved. In this particular case, with the power supply of the electric flight control system in the Saab Gripen fighter, advantage could be taken of a specific permanent magnet generator (PM-generator). The frequency of the generator offered the perfect conditions for a magamp controller. A key parameter in designing magnetic amplifiers (magamps) is low losses. New amorphous alloys offer new possibilities of the technique in designing magnetic amplifiers, because of their extremely low losses. The core losses are evaluated by studying the equations and diagrams specifying the power losses. The core losses are evaluated and compared with the copper losses in the process of optimizing low weight and low losses. For this an engineering tool is developed and demonstrated. Evaluations of the hysteresis characteristics for the magnetic alloys, as well as modeling and simulation of the core losses, are presented in this work. The modeling of the core losses includes hysteresis losses, eddy current losses and excess losses as well as copper losses. The losses are studied dynamically during realistic operational conditions. The model can be used for any generic analysis of hysteresis in magnetic circuits. Applications of magnetic amplifiers in aircrafts have been demonstrated to be a feasible alternative / QC 20101103

This research introduces a high-performance electric taxiing system (ETS) as a modern solution to improve the on-ground operations of today’s aircraft, which are conventionally powered through the main engines. The presented ETS is propelled by electric motors, integrated into the main landing gear of a state-of-the-art midsize commercial aircraft, and powered by an additional not quantified electrical energy storage system. The proposed system can therefore operate autonomously from any aircraft-internal power source, i.e. Auxiliary Power Unit or equivalent. The main objective of this work is to assess the energy consumption of the introduced ETS while considering energy recuperation due to regenerative braking. The ETS powertrain is sized to match modern conventional taxi performances that were seen in 36 self-recorded takeoff- and landing taxi driving profiles. A custom ETS simulation model was developed and simulated across all available driving profiles to confirm the desired powertrain performance and to predict the system’s energy consumption. For the purpose of enhancing the validity of these energy consumption predictions, a suitable motor controller is then designed by the use of MATLAB Simulink. An easy-to-implement switch loss model was created to predict the ETS motor controller efficiency map. Finally, the former energy consumption predictions were revised for the implementation of the motor controller and an estimated traction motor efficiency map. The results exhibit that the revised ETS simulation model was capable of refining the energy consumption. It was found that the ETS will consume up to 9.89 kWh on average if the full potential of the traction motors energy recuperation capabilities are being used. The simulation outcomes further demonstrate that regenerative braking offers great potential in ETS applications since more than 14 % of required traction energy could be regenerated to yield the above mentioned average energy consumption. / Thesis / Master of Applied Science (MASc)