Dans un contexte de progression du stockage d’énergie sous forme électrochimique dans les transports, notamment dans l’aéronautique, les problématiques de performance, de fiabilité, de sureté de fonctionnement et de durée de vie du stockeur sont essentielles pour utilisateurs. Cette thèse se focalise ces voltes pour l’avion plus électrique. Les technologies étudiées correspondent à des éléments commerciaux de dernière génération de type Lithium-ion (NMC/graphite+SiO, NCA/graphite, LFP/graphite, NMC/LTO), Lithium-Soufre (Li-S), supercondensateur et hybride (LiC). Une première partie de ce manuscrit s’attache à la quantification des performances des différents éléments dans l’environnement aéronautique [-20°C, 55°C] et pour l’usage aéronautique. Un modèle comportemental de type électro-thermique est développé et validé. La seconde partie est consacrée à la quantification du vieillissement des différents éléments. Les résultats de vieillissement calendaire et en cyclage actif sont présentés ainsi que ceux des tests abusifs. Une méthode d’estimation de l’état de santé (SOH) des éléments basés sur l’analyse de la capacité incrémentale (ICA) est proposée. Enfin, l’évaluation de la robustesse des éléments de stockage lors de tests de vieillissement accéléré avec un profil spécifique à l’usage aéronautique est proposé. Les modèles de vieillissement et la méthode d'estimation de SOH proposés précédemment sont utilisés ici pour évaluer l'impact de la température sur la vitesse de dégradation et pour estimer le SOH des cellules vieillies à l’aide de ce profil aéronautique. / In the context of progress in the electrochemical energy storage systems in the transport field, especially in the aeronautics, the issues of performance, reliability, safety and robustness of these elements are essential for users. This thesis is focused on these issues for the more electric aircraft. The technologies studied correspond to the latest generation commercial elements of Lithium-ion batteries (NMC/ graphite + SiO, NCA/graphite, LFP/graphite, NMC/LTO), Lithium-Sulfur (Li-S), Supercapacitor and Lithium-ion capacitors. The first part of this manuscript is dedicated to the performance quantification of the different electrochemical energy storage elements in aeronautical environment [-20°C, 55°C] and usage. An efficient and accurate electro-thermal model is developed and validated. The second part is devoted to the calendar and power cycling ageings as well as to the presentation of abuse testing results. A State Of Health (SOH) estimation based on incremental capacity analysis method is proposed. Finally, the robustness of the storage elements during accelerated ageing tests with a specific profile for the aeronautical usage is evaluated. The ageing models and SOH estimation methods proposed in the previous sections are used here to evaluate the impact of temperature on the degradation rate and to estimate the SOH of the cells with this aeronautical profile.

Le monde aéronautique a connu un essor significatif durant les premières décennies du XXe siècle. Propulsé par des avancées technologiques sans précédents, l’aéronautique fut rapidement omniprésente dans tous les secteurs de la vie et de la culture européennes. De la figure du pilote d’aéroplane émergea subtilement, puis avec force, l’image d’un homme robuste et valeureux qui personnifiait son pays. Trouvant un réceptacle favorable dans les héros nés de la Grande Guerre, les gouvernements totalitaires qui émergèrent façonnèrent le pilote comme l’avatar d’un homme idéal. L’imaginaire européen du premier tiers du XXe siècle vit alors naitre « l’homme volant », une facette de « l’homme nouveau », incarnant la grandeur de sa nation. / Aeronautics underwent a significant development during the first decades of the 20th century. Helped by new technological advancements aeronautics quickly became omnipresent in all sectors of the European life and culture. From the figure of the airplane’s pilot emerged subtly, then with strength, the image of a strong and brave man personifying his country. Finding a favorable receptacle in the Great War’s heroes, the totalitarian governments shaped the pilot as the avatar of an ideal man. The European imagination of the first third of the 20th century gave birth to the "flying man", a facet of the “new man”, embodying the greatness of its nation.

Dans les années à venir, l’industrie de l’aéronautique doit améliorer le contrôle thermique des composants et modules hautement intégrés. Les approches de refroidissement standard, utilisant l’air forcé ne sont plus utilisables. Il est donc nécessaire de développer de nouvelles technologies capables d’offrir des solutions compatibles avec ces nouvelles problématiques. Une revue bibliographique approfondie est présentée pour montrer les solutions existantes pour l’avionique. Les systèmes à changement de phase, tels que les boucles diphasiques capillaires (LHPs), sont très attractifs puisqu’ils peuvent être utilisés pour transporter la chaleur vers une grande surface d’un radiateur qui dissipera la chaleur vers le milieu ambiant. Une première famille de LHP, conçue et réalisée par la compagnie Atherm, et remplie avec du méthanol, est décrite. Deux autres familles de LHP sont également présentées. La première a été réalisée par la société ATHERM et a un condenseur et des lignes de transports modifiés, afin d’être intégrée sur une carte électronique existante. La deuxième famille, a été conçue et réalisée par l’Institut of Thermal Physics (ITP), sur la base de spécifications similaires. Un banc d’essai expérimental est conçu et réalisé pour tester ces systèmes. Les effets de la charge en fluide, baïonnette, et mèche secondaire, sont observés. Des tests d’orientation et d’accélération sont réalisés sur des LHPs intégrées dans un rack aéronautique. Même une certaine sensibilité aux orientations et accélérations est observée, les LHPs fonctionnement toujours jusqu’à l’accélération maximale testée de 6 G. Un modèle stationnaire d’une boucle diphasique basé sur une approche à plusieurs échelles est développé. Plusieurs niveaux de complexité et de précision peuvent être sélectionnés pour le modèle des composants individuels de la boucle, allant du modèle nodal au modèle 3D. Le modèle est validé avec les données expérimentales. Un bon accord entre les simulations numériques et les résultats expérimentaux est obtenu. Les résultats numériques montrent que la charge de fluide dans le réservoir affecte le comportement thermique de la LHP en modifiant la répartition des flux de chaleurs. Des gradients de température importants sont observés dans la plaque du condenseur, et un nouveau tracé de la ligne condenseur est proposé. Plusieurs modifications de l’évaporateur sont analysées. La diminution la plus importante de la résistance thermique de l’évaporateur est obtenue par une bonne disposition des rainures axiales de la mèche, associée à une semelle optimisée, ou à des rainures radiales. / In the coming years, the avionics industry will have to improve the thermal control of both existing and emerging highly integrated electronic components and modules. The standard cooling approaches using forced air are no longer applicable. It is necessary to develop new technologies being able to offer solutions compatible with those new problematic. An extensive literature review is presented to show the existing cooling solutions for avionics. Two-phase passive systems, such as LHPs are very attractive as they may be used as heat spreader, associated with a classical heat sink to dissipate the heat. A first family of LHP, designed and manufactured by the ATHERM Company and filled with methanol as the working fluid is described. Two other LHP families are also presented. The first one was manufactured by ATHERM and has modified condenser and transport line shapes, in order to be integrated into an existing electronic card. The second one was manufactured and designed by the Institute of Thermal Physics, on the same specification basis. An experimental setup is designed and built to test these LHPs. The effects of fluid fill charge, bayonet and secondary wick are observed. Orientation and acceleration tests are conducted on LHPs integrated within an avionic rack. Even if the LHPs exhibited sensitivity to orientation and acceleration, no failure of the LHP was observed up to the maximum applied acceleration (6 G). A steady state model of LHP based on a multi-level approach is developed. Various levels of complexity and precision can be selected for the model of the individual component, going from the nodal to the 3D model. The model is validated with experimental data from the laboratory tests. A good agreement is achieved between the experimental and the numerical data. The numerical results show that the fluid fill charge within the reservoir affects the thermal behavior of the LHP, by modifying the heat flux distribution. High temperature gradients are highlighted in the condenser plate and a redesign of its shape is proposed. Various modifications of the evaporator design are considered. The most important decrease of the evaporator thermal resistance is brought by a good disposition of the axial vapor grooves associated with an optimized saddle shape or radial vapor grooves.

In response to serious environmental and economic concerns, the design and production of aircrafts have been changing profoundly over the past decades with the nose-to-tail switch from metallic materials to lightweight composite materials such as carbon fibre reinforced plastic (CFRP). In this context, the present doctoral research work aimed to contribute to the development of a CFRP booster casing, a real innovation in the field initiated and conducted by Safran Aero Boosters. More specifically, this thesis addresses the matter of joining metal/CFRP hybrid structures, which are prone to possibly detrimental residual stresses.The issue is treated with an approach combining experimental characterisation and finite element (FE) simulations. The multi-layered system’s state of damage was systematically examined on hundreds of micrographs, and the outcome of this study is presented under the form of a statistical analysis. Further, the defects’ 3D morphology is investigated by incremental polishing. A number of thermal and mechanical properties are measured by diverse physical tests on part of the constituent materials, i.e. the aerospace grade RTM6 epoxy resin, the structural Redux 322 epoxy film adhesive, and AISI 316L stainless steel. They are used as input data in a FE model of the multilayer that is developed and progressively refined to obtain detailed residual stress fields after thermal loading. These results are compared to experimental data acquired by X-ray diffraction stress analysis and with the curvature-based Stoney formula. Cohesive elements are placed at specific locations within the FE model to allow simulating progressive damage. Peel tests, mode I, mode II and mixed mode I/II fracture tests are thus performed in view of measuring the joint toughness. The results of these tests are discussed and the presence of residual stress in the fracture specimens is highlighted. Key information for the calibration of the cohesive law is finally identified via inverse FE analysis of the mode I test, this being a significant step in the process of building a damage predictive FE model of the multi-layered system. / Doctorat en Sciences de l'ingénieur et technologie / info:eu-repo/semantics/nonPublished

The present research project is carried out at the von Karman Institute for Fluid Dynamics (Rhode-Saint-Genèse, Belgium) with the financial support of the European Space Agency.<p><p>The first stage of spacecrafts (e.g. Ariane 5, Vega, Shuttle) generally consists of large solid propellant rocket motors (SRM), which often consist of segmented structure and incorporate a submerged nozzle. During the combustion, the regression of the solid propellant surrounding the nozzle integration part leads to the formation of a cavity around the nozzle lip. The propellant combustion generates liquefied alumina droplets coming from chemical reaction of the aluminum composing the propellant grain. The alumina droplets being carried away by the hot burnt gases are flowing towards the nozzle. Meanwhile the droplets may interact with the internal flow. As a consequence, some of the droplets are entrapped in the cavity forming an alumina puddle (slag) instead of being exhausted through the throat. This slag reduces the performances.<p><p>The aim of the present study is to characterize the slag accumulation process in a simplified model of the MPS P230 motor using primarily optical experimental techniques. Therefore, a 2D-like cold-gas model is designed, which represents the main geometrical features of the real motor (presence of an inhibitor, nozzle and cavity) and allows to approximate non-dimensional parameters of the internal two-phase flow (e.g. Stokes number, volume fraction). The model is attached to a wind-tunnel that provides quasi-axial flow (air) injection. A water spray device in the stagnation chamber realizes the models of the alumina droplets, which are accumulating in the aft-end cavity of the motor.<p><p>To be able to carry out experimental investigation, at first the the VKI Level Detection and Recording(LeDaR) and Particle Image Velocimetry (PIV) measurement techniques had to be adapted to the two-phase flow condition of the facility.<p><p>A parametric liquid accumulation assessment is performed experimentally using the LeDaR technique to identify the influence of various parameters on the liquid deposition rate. The obstacle tip to nozzle tip distance (OT2NT) is identified to be the most relevant, which indicates how much a droplet passing just at the inhibitor tip should deviate transversally to leave through the nozzle and not to be entrapped in the cavity.<p><p>As LeDaR gives no indication of the driving mechanisms, the flow field is analysed experimentally, which is supported by numerical simulations to understand the main driving forces of the accumulation process. A single-phase PIV measurement campaign provides detailed information about the statistical and instantaneous flow structures. The flow quantities are successfully compared to an equivalent 3D unsteady LES numerical model.<p><p>Two-phase flow CFD simulations suggest the importance of the droplet diameter on the accumulation rate. This observation is confirmed by two-phase flow PIV experiments as well. Accordingly, the droplet entrapment process is described by two mechanisms. The smaller droplets (representing a short characteristic time) appear to follow closely the air-phase. Thus, they may mix with the air-phase of the recirculation region downstream the inhibitor and can be carried into the cavity. On the other hand, the large droplets (representing a long characteristic time) are not able to follow the air-phase motion. Consequently, a large mean velocity difference is found between the droplets and the air-phase using the two-phase flow measurement data. Therefore, due to the inertia of the large droplets, they may fall into the cavity in function of the OT2NT and their velocity vector at the level of the inhibitor tip.<p><p>Finally, a third mechanism, dripping is identified as a contributor to the accumulation process. In the current quasi axial 2D-like set-up large drops are dripping from the inhibitor. In this configuration they are the main source of the accumulation process. Therefore, additional numerical simulations are performed to estimate the importance of dripping in more realistic configurations. The preliminary results suggest that dripping is not the main mechanism in the real slag accumulation process. However, it may still lead to a considerable contribution to the final amount of slag.<p> / Doctorat en Sciences de l'ingénieur / info:eu-repo/semantics/nonPublished