La sécurité des biens et des personnes est, de nos jours, une préoccupation première, en particulier lorsqu'elle concerne l'usage des explosifs. Afin de répondre à ces exigences de sécurité, il est nécessaire de pouvoir prédire le comportement des ondes de pression issues d'une explosion, que ce soit à l'intérieur ou à l'extérieur du bâtiment, et leur interaction avec leur environnement. Une importante quantité d'informations sur les ondes de choc se propageant en champ libre est disponible dans la littérature, de sorte que leur comportement est maintenant bien connu. Toutefois, il y a très peu de données disponibles en littérature ouverte sur les explosions en milieu confiné. Les travaux présentés dans ce mémoire de thèse s'inscrivent dans le cadre de l'étude du comportement des ondes de choc en milieu confiné multi-chambres et de l'effet de différents paramètres tels que le volume des cellules ou la largeur du couloir sur les profils de pression à l'intérieur d'un bâtiment. La propagation de l'onde de choc est analysée par l'évolution de certains paramètres du choc (temps d'arrivée, surpression maximale et impulsion positive).Plusieurs essais à échelle réduite ont été réalisés à l'aide d'une maquette modulable, représentative d'un bâtiment pyrotechnique de plein pied, composé de quatre pièces alignées et reliées entre elles par un couloir. / Security is nowadays a real and major concern, especially when explosives are involved. To address this security issue, an accurate prediction of the behavior of shock waves caused by a detonation propagating inside or outside a building and interacting with the surrounding environment is required. Extensive knowledge regarding shock waves in free field can be found in the literature so that their behavior is now well known. However, there is very few information available in the open literature for confined configuration. This study focuses on the behavior of a shock wave within a confined multi-chamber system and on the impact of different parameters such as the size of the rooms and the width of the corridor on the pressure history inside the building. The shock wave propagation is analyzed through the evolution of some of the shock parameters (arrival time, maximum overpressure and positive impulse). Several small-scale experiments have been carried out using an adjustable model of a four-roomed single-story building. The rooms are connected to a single corridor and all on the same side. This model is representative of a pyrotechnic workshop.

Cette thèse a pour objectif d'améliorer la compréhension de la dynamique d'une interaction entre une onde de choc droite ou oblique et une couche limite laminaire ou turbulente. En particulier, nous nous sommes intéressés aux mécanismes responsables de l'apparition d'oscillations auto-entretenues basses fréquences. Ce phénomène survient dans de nombreux cas applicatifs comme dans des entrées d'air d'avions supersoniques, autour d'un profil d'aile en régime transsonique et au sein de tuyère en régime de sur-détente. La première partie de ce mémoire traite des différentes études réalisées pour déterminer la phénoménologie de ce type de dynamique. Dans un deuxième temps, nous expliquons la stratégie retenue pour effectuer notre étude qui consiste à développer un outil d'étude des instabilités, adapté à des écoulements turbulents présentant une interaction entre une onde de choc et une couche limite. Le développement d'un outil CFD linéarisé couplé à une méthode de résolution d'un problème aux valeurs propres par une approche dite sans matrice ou de « time-stepping », a permis la réalisation d'une telle étude. Après une étape de validation de notre outil, nous avons étudié des cas d'écoulements présentant une interaction entre une onde de choc et une couche limite. Trois cas en particulier ont été traités. Le premier cas correspond à une interaction entre une onde de choc oblique impactant une couche limite laminaire se développant sur une plaque plane. Ce cas est généralement qualifié dans la littérature de cas de « réflexion de choc ». Nous montrons qu'un tel écoulement est globalement stable et que sa dynamique peut être caractérisée par des mécanismes de réceptivité et par la réponse de l'écoulement vis-à-vis de perturbations extérieures. Les deux autres cas abordés dans ce travail ont été le cas d'un écoulement transsonique autour d'un profil d'aile de type NACA0012 en régime d'entrée en tremblement aérodynamique et un cas de tuyère transsonique plane de type Sajben en régime de sur-détente. Dans le premier cas, l'analyse de stabilité nous permet de mettre en évidence le phénomène de « buffet » sur le profil NACA0012, ce qui montre que le phénomène est lié à une instabilité globale linéaire . Dans le second cas, l'analyse de stabilité ne permet pas d'expliquer le phénomène auto-entretenues basses fréquences, et montre que l'écoulement est linéairement globalement stable. Dans ce cas, la dynamique est convective, transitoire et pilotée par des mécanismes de réceptivité. / The general purpose of this study is to provide a better understanding of the dynamics of an interaction between a shock wave and a laminar or turbulent boundary layer. In particular, we were interested in mechanisms responsible for the emergence of low-frequency self-sustained oscillations. This phenomenon arises in numerous industrial cases as in air inlets of supersonic aircrafts, around a profile of wing in transonic regime and within over-extended nozzle. The first part of this report handles various studies carried out to determine the phenomenology of this kind of dynamics. Secondly, we explain the strategy adopted to make our study which consists in developing a tool of study of the instabilities adapted to turbulent flows including an interaction between a shock wave and a boundary layer. The development of a linearized CFD tool coupled with a method of resolution of a eigenvalue problem by a free-matrix approach ( " time-stepping " approach), allowed the realization of such a study. After a stage of validation of our tool, we studied cases of flows including an interaction between a shock wave and a boundary layer. Three cases in particular were handled. The first case corresponds to an interaction enter an oblique shock wave impacting on a laminar boundary layer developing on a flat plate. This case is generally qualified in the literature of case as " reflected shock wave". We show that such a flow is globally stable and that the dynamics of such a flow behaves as a selective noise amplifier, the dynamic is mainly driven by receptivity mechanisms and by the response of upstream white nose disturbance. Two other cases have been studied on this work, the case of a transonic flow around a profile wing of NACA0012 type around the onset of buffet phenomenon and the case of transonic nozzle of Sajben type on over-extended regime. In the first case, the global stability analysis allows us to highlight the buffet phenomenon of on the profile NACA0012, what shows that the phenomenon is linked to a linear global instability. In the second case, the analysis of stability does not allow to explain the self-sustained low frequencies phenomenon, and shows that the flow is linearly globally stable. In this case, the dynamics is convective, passing and piloted by receptivity mechanisms.

Afin de concevoir des systèmes de propulsion innovants, l'amélioration des performances des prises d'air supersonique constitue un enjeu majeur. En particulier, les écoulements intervenant au sein des entrées d'air et/ou de diffuseurs supersoniques mettent en jeu des phénomènes complexes associés aux diverses échelles spatiales et temporelles: dynamique de la turbulence pariétale, interaction entre une onde de choc et une couche limite turbulente, décollements tridimensionnels et effets de coins. Malgré les contributions significatives et récentes des simulations numériques de haute fidélité sur les instationnarités de l'interaction onde de choc/couche limite sans paroi latérales, peu d'études numériques ont été menées sur l'influence des coins dans la dynamique de l'écoulement. En présence de parois latérales et à des nombres de Mach suffisamment élevés, l’interaction se modifie et un train de choc se forme dans le diffuseur. Dans le cadre de cette thèse, les équations de Navier-Stokes en régime compressible sont résolues à l'aide de schémas d'ordre élevé. Des simulations en régime supersonique de l'écoulement dans des diffuseurs rectangulaires de largeurs différentes sont effectuées. L'étude permet la mise en évidence de l'influence du confinement et des effets de coins. Une deuxième partie de l’étude est consacrée à la compréhension des instationnarités générées par un train de choc dans un diffuseur rectangulaire à l'aide d'outils de post-traitement avancés: décomposition modale dynamique et périodogramme. Les résultats montrent la présence d'un possible phénomène de résonance du diffuseur à des fréquences proches de celles émises par l'écoulement. / To design innovative propulsion systems, improving the performance of supersonic air intakes is a major issue. In particular, the flows through the air intakes and/or supersonic diffusers involve complex unsteady phenomena associated with various spatial and temporal scales such as: wall-bounded turbulence dynamics, interaction between a shock-wave and a turbulent boundary layer, three-dimensional separated flows and corners effects. Despite the significant contributions from recent high-fidelity simulations of unsteady shock-wave boundary layer interaction in the absence of side walls, few numerical studies were conducted with secondary flows due to corner effects. In the presence of side walls and at Mach numbers large enough, the topology of the interaction is modified and a shock-train forms in the diffuser. In this thesis, the Navier-Stokes compressible equations are solved using high-order schemes. Simulations of supersonic flows in rectangular diffusers of different widths are carried out. The study allows to highlight the influence of confinement and corners effects on the mean flow. A second part of the study is devoted to the understanding of the unsteadiness associated with a shock-train in a rectangular supersonic diffuser. For that purpose, advanced post-processing tools have been developed such as: dynamic mode decomposition and Fourier analysis. The results show the presence of a possible resonance phenomenon in the diffuser at frequencies close to those associated with the flow.

In the flying field of space transportation domain, the increased efforts involving design and development of hypersonic flight for space missions is on toe to provide the optimum aerothermodynamic design data to satisfy mission requirements. Aerothermodynamics is the basis for designing and development of hypersonic space transportation flight vehicles such as X 51 a, and other programmes like planetary probes for Moon and Mars, and Earth re-entry vehicles such as SRE and space shuttle. It enables safe flying of aerospace vehicles, keeping other parameters optimum for structural and materials with thermal protection systems. In this context, the experimental investigations on hypersonic waverider are carried out at design Mach 6. The hypersonic waverider has high lift to drag ratio at design Mach number even at zero degree angle of incidence, and this seems to be one of the special characteristics for its shape at hypersonic flight regime. The heat transfer rates are measured using 30 thin film platinum gauges sputtered on a Macor material that are embedded on the test model. The waverider has 16 sensors on top surface and 14 on bottom surface of a model. The surface temperature history is directly converted to heat transfer rates. The heat transfer data are measured for design (Mach 6) and off-design Mach numbers (8) in the hypersonic shock tunnel, HST2. The results are obtained at stagnation enthalpy of ~ 2 MJ/kg, and Reynolds number range from 0.578 x 106 m-1 to 1.461 x 106 m-1. In addition, flow visualization is carried out by using Schlieren technique to obtain the shock structures and flow evolution around the Waverider. Some preliminary computational analyses are conducted using FLUENT 6.3 and HiFUN, which gave quantitative results. Experimentally measured surface heat flux data are compared with the computed one and both the data agree well. These detailed results are presented in the thesis.

A doença aterosclerótica coronariana tem um grande impacto na morbidade e mortalidade em todo mundo. A terapia cardíaca com ondas de choque consiste em uma nova opção potencial para o tratamento de pacientes com doença coronariana crônica e angina refratária. No presente estudo, avaliamos os efeitos das ondas de choque na mecânica do ventrículo esquerdo, avaliados pela ecocardiografia com speckle tracking, assim como nos sintomas clínicos e isquemia miocárdica em pacientes com angina refratária. Estudamos, prospectivamente, 19 pacientes com angina refratária submetidos à terapia com ondas de choque com 3 sessões de tratamento por semana, realizados na primeira, quinta e nona semanas, totalizando 9 semanas de tratamento. A mecânica do ventrículo esquerdo foi avaliada por meio da determinação do strain longitudinal global e segmentar. A perfusão miocárdica foi analisada por cintilografia de perfusão miocárdica com Tecnécio-99m Sestamibi, para determinação do summed stress score (SSS). Parâmetros clínicos foram mensurados pelo escore de angina da Canadian Cardiovascular Society (CCS), escore de insuficiência cardíaca da New York Heart Association (NYHA) e qualidade de vida pelo Seattle Angina Questionnaire (SAQ). Todos os dados foram mensurados antes do início do tratamento e 6 meses após a terapia com ondas de choque. Os nossos resultados demonstraram que as ondas de choque não ocasionaram efeitos colaterais importantes e os pacientes apresentaram melhora significativa dos sintomas. Antes do tratamento, 18 (94,7%) pacientes se apresentavam com angina CCS classe III ou IV, e 6 meses após houve redução para 3 (15,8%) pacientes (p = 0,0001), associada à melhora no SAQ (38,5%; p < 0,001). Treze (68,4%) pacientes estavam em classe funcional III ou IV da NYHA antes do tratamento, com redução significativa para 7 (36,8%); p = 0,014. Nenhuma alteração foi observada no SSS global basal no acompanhamento de 6 meses (15,33 ± 8,60 versus 16,60 ± 8,06, p = 0,155) determinado pela cintilografia miocárdica. No entanto, houve redução significativa no SSS médio dos segmentos isquêmicos tratados (2,1 ± 0,87 pré versus 1,6 ± 1,19 pós-terapia, p = 0,024). O strain longitudinal global do ventrículo esquerdo permaneceu inalterado (-13,03 ± 8,96 pré versus -15,88 ± 3,43 pós-tratamento; p = 0,256). Também não foi observada alteração significativa no strain longitudinal segmentar do ventrículo esquerdo pela ecocardiografia com speckle tracking. Concluímos que a terapia com ondas de choque é um procedimento seguro para tratamento de pacientes com angina refratária, que resulta em melhor qualidade de vida, melhora na perfusão miocárdica dos segmentos tratados e preservação da mecânica ventricular esquerda / Coronary atherosclerotic disease represents a major impact on morbidity and mortality worldwide. Cardiac shock wave therapy is a new potential option for the treatment of patients with chronic coronary disease and refractory angina. In the present study, we sought to determine the effects of shock wave therapy on the left ventricular mechanics, evaluated by speckle tracking echocardiography, as well as on myocardial perfusion and symptoms of patients with refractory angina. We prospectively studied 19 patients undergoing shock wave therapy with 3 sessions per week, on the 1st, 5th and 9th weeks, for a total of 9 weeks of treatment. The left ventricular mechanics was evaluated by global longitudinal strain using the speckle tracking echocardiography. Myocardial perfusion was assessed by myocardial scintigraphy with Technetium-99m Sestamibi, for determination of summed stress score (SSS). Clinical parameters were evaluated by the Canadian Cardiovascular Society (CCS) angina score, New York Heart Association (NYHA ) heart failure score and quality of life by the Seattle Angina Questionnaire (SAQ). All data were measured prior to the treatment and 6 months after shock wave therapy. Our results demonstrated that shock wave therapy did not cause significant side effects and improved symptoms. Before treatment, 18 patients (94.7%) had CCS class III or IV angina, and 6 months later there was a reduction to 3 (15.8%), p = 0.0001, associated with improvement in SAQ ( 38.5%, p < 0.001). Thirteen (68.4%) were in NYHA class III or IV before treatment, with a significant reduction to 7 (36.8%); p = 0.014. No change was observed in the global SSS at 6-months follow-up (from 15.33 ± 8.60 baseline to 16.60 ± 8.06 post-treatment, p = 0.155). However, there was a significant reduction in the mean SSS of the treated ischemic segments (2.1 ± 0.87 pre versus 1.6 ± 1.19 post therapy, p = 0.024). The global longitudinal strain remained unchanged (-13.03 ± 8.96 pre versus -15.88 ± 3.43 6 months post-treatment, p = 0.256). In the same way, no significant difference was observed in the longitudinal strain of the left ventricular segments. We concluded that shock wave therapy is a safe procedure for the treatment of patients with refractory angina, resulting in better quality of life, improved myocardial perfusion of the treated segments, and preservation of left ventricular mechanics

Le BLEVE (Boiling Liquid Exploding Vapor Explosion) est l’un des accidents les plus craints dans l’industrie. Bien qu’il soit étudié depuis plus de soixante ans, certains dangers et situations restent mal anticipés, tels que : quelles seraient les conséquences de la surpression d’un BLEVE dans un milieu urbain confiné ? Qu’adviendrait-il si un camion de transport de GPL venait exploser sur un pont ? Ces questions nécessitent d’étudier la physique du BLEVE au plus proche du conteneur. Ce travail explore les phénomènes physiques générant la surpression aérienne en champ proche de l’explosion, en essayant de comprendre la contribution des phases du contenu (liquide et vapeur) dans les dangers en champ proche du BLEVE. Un prototype expérimental petite échelle a été conçu dans le but de reproduire les BLEVE de cuves cylindriques de manière réaliste. Vingt-quatre BLEVEs de propane ont été effectués. Un large spectre de données a été collecté lors de ces tests : surpression aérienne dans de multiples directions autour du conteneur, variations de pression dans le conteneur avant et après rupture, chargement au sol dû à l’explosion, visualisations en imagerie rapide selon un certain nombre d’angles. Les résultats montrent une dépendance forte entre les caractéristiques de la phase vapeur et la suppression maximale générée par l’explosion. La reconstruction chronologique du phénomène confirme ce résultat. Cependant, la phase liquide joue un rôle capital dans la génération du chargement au sol, qui est un danger considérable, mais peu considéré jusque-là. / Boiling Liquid Exploding Vapor Explosion (BLEVE) is one of the most feared accident in the industry. Even though it has been studied for over 6 decades, many safety questions remain poorly answered: what happens if a BLEVE occurs in a congested urban or industrial area? What if a road tanker BLEVE happens on a bridge? These questions require to look closer to the vessel. This work focuses on understanding the physics involved in overpressure generation in the near field surrounding of the vessel, to understand the contribution of the fluid phases (liquid and vapor) in the near-field hazards of a BLEVE. For this purpose, a small scale experimental prototype was designed to reproduce realistic BLEVE failure. Twenty-four propane BLEVEs were performed. A wide range of data was recorded from these tests: blast overpressure all around the vessel, transient pressure inside the vessel, ground loading under the vessel, and high speed imaging through various angles. Results give more insight on the anisotropy of the pressure field around the cylindrical vessel. It also shows a strong dependency between vapor content and maximum overpressure from the lead shock. Moreover, the chronology of the phase change observed through transient pressure measurements show that the main contributor of the maximum overpressure is the vapor phase. The phase change is studied through pressure transient in the vessel and high speed imaging, giving a better understanding of the time scales involved with this phenomenon. Finally, ground loading measurements are analyzed to give insight on the order of magnitude involved in this hazard.

5 Abstract This study is dedicated to evaluating the potential for a novel pathway of abiotic synthesis of phosphine (PH3) from phosphorus trioxide (P4O6) by a photocatalytic mechanism on aerosols. The mechanism might explain the recent possible detection of phosphine on Venus. This scenario has recently been suggested theoretically by our team based on an analogy with methane production form carbon dioxide on acidic photochemically-active surfaces of materials, which may account for a possible source of methane on Mars. Methane, just like phosphine, was suggested as an indicator of life on terrestrial planets, including Mars. The theoretical testing of photochemical phosphine generation suggests that even if this gas is present in the atmosphere of Venus it cannot be considered as an indicator of life until the suggested mechanism is excluded theoretically, or by experimental results, or direct evidence of life on Venus. This thesis will be followed by preparation of sophisticated experiments and intensive laboratory research addressing this. Furthermore, the role of nitrous oxide as another false positive biosignature was evaluated in this study. The presence of nitrous oxide can also be explained by processes other than biological, particularly on early planets. This study specifically demonstrates the...

Ce sujet de thèse s’inscrit dans le cadre des études actuellement menées au CEA/DAM concernant des schémas numériques ALE (Arbitrary-Lagrangian-Eulerian)de type « Lagrange + Projection », dans le contexte des simulations hydrodynamiques mutli-matériaux en grandes déformations. Ces schémas doivent respecter les équations de conservation de la masse, de la quantité de mouvement et de l’énergie totale.Les schémas décalés en temps et en espace sont très utilisés dans les codes industriels. Ils sont robustes et permettent une bonne approximation des comportements complexes, mais sont connus pour ne pas conserver exactement l’énergie totale. Cela pose un problème dans le traitement des chocs, sur maillages raffinés ou dans la simulation des milieux réactifs.En 2016, des travaux originaux on été proposés par A. Llor et. al. pour rendre conservatif ce type de schéma dans un contexte lagrangien (sans projection), notamment en proposant une correction pour retrouver la conservation de l’énergie totale.Le travail de cette thèse a été d’étendre ce schéma lagrangien dans un contexte ALE multi-matériaux (avec interface), en garantissant la conservation de toutes les quantités, le respect du second principe de la thermodynamique et la robustesse. De nombreux cas tests ont été menés (en 2D plan et en 2D axisymétrique) et comparés aux méthodes existantes afin de montrer la pertinence de cette approche. / This PhD subject comes within actual studies managed by CEA/DAM about ALE (Arbitrary-Lagrangian-Eulerian) schemes (with a splitting of Lagrangian and Remapping steps) in the context of hydrodynamic simulations. These numerical schemes have to respect mass, momentum and total energy conservation, which are the fundamental equations of the studied systems.Space- and Time-Staggered are widely used in industrial codes for their simplicity androbustness despite their known lack of exact energy conservation. This is a major drawbackin presence of strong shocks. Among all existing schemes, none of them meet the expectations of robustness, conservation,thermodynamic consistency (both shocks and relaxations capture), accuracy andadaptibility to complex behaviors. Recently, some novel works have been proposed by A.Llor et. al. in order to make conservative this type of scheme in a Lagrangian context (without remapping step). Current remap methods, necessary in large deformations, donot guarantee simultaneously total energy conservation and thermodynamic consistency.This work aims at extending this conservative Lagrangian space- and time-staggeredscheme to a multi-material ALE methodology, keeping its good properties (conservation,accuracy, thermodynamic consistency, robustness) intact. Classical, but demanding, test cases have been performed (both in plane and axisymmetric 2D geometries) and have been compared to existing numerical methods in order to assess the relevance of our approach.

This dissertation presents an investigation and design optimization of energy absorbent protective systems that protect the brain. Specifically, the energy absorption characteristics of the bighorn sheep skull-horn system were quantified and used to inform a topology optimization performed on a football helmet facemask leading to reduced values of brain injury indicators. The horn keratin of a bighorn sheep was experimentally characterized in different stress states, strain rates, and moisture contents. Horn keratin demonstrated a clear strain rate dependence in both tension and compression. As the strain rate increased, the flow stress increased. Also, increased moisture content decreased the strength and increased ductility. The hydrated horn keratin energy absorption increased at high strain rates when compared to quasi-static data. The keratin experimental data was then used to inform constitutive models employed in the simulation of bighorn sheep head impacts at 5.5 m/s. Accelerations values as high as 607 G’s were observed in finite element simulations for rams butting their heads, which is an order of magnitude higher than predicted brain injury threshold values. In the most extreme case, maximum tensile pressure and maximum shear strains in the ram brain were 245 kPa and 0.28, respectively. These values could serve as true injury metrics for human head impacts. Finally, a helmeted human head Finite Element (FE) model is created, validated, and used to recreate impacts from a linear impactor. The results from these simulations are used to train a surrogate model, which is in turn utilized in multi-objective design optimization. Brain injury indicators were significantly reduced by performing multi-objective design optimization on a football helmet facemask. In particular, the tensile pressure and maximum shear strain in the brain decreased 7.5 % and 39.5 %, respectively when comparing the optimal designs to the baseline design. While the maximum tensile pressure and maximum shear strain values in the brain for helmeted head impacts (30.2 kPa and 0.011) were far less than the ram impacts (245 kPa and 0.28), helmet impacts up to 12.3 m/s have been recorded, and could easily surpass these thresholds.

Shock-tube experiments are typically performed at high temperatures (≥1200K) due to test-time constraints. These test times are usually ~1 ms in duration and the source of this short, test-time constraint is loss of temperature due to heat transfer. At short test times, there is very little appreciable heat transfer between the hot gas and the cold walls of the shock tube and a high test temperature can be maintained. However, some experiments are using lower temperatures (approx. 800K) to achieve ignition and require much longer test times (up to 15 ms) to fully study the chemical kinetics and combustion chemistry of a reaction in a shock-tube experiment. Using mathematical models, analysis was performed studying the effects of temperature, pressure, shock-tube inner diameter, and test-port location at various test times (from 1 - 20 ms) on temperature maintenance. Three models, each more complex than the previous, were used to simulate test conditions in the endwall region behind the reflected shock wave with Ar and N2 as bath gases. Temperature profile, thermal BL thickness, and other parametric results are presented herein. It was observed that higher temperatures and lower pressures contributed to a thicker thermal boundary layer, as did shrinking inner diameter. Thus it was found that a test case such as 800K and 50 atm in a 16.2-cm-diameter shock tube in Argon maintained thermal integrity much better than other cases - pronounced by a thermal boundary layer ≤ 1 mm thick and an average temperature ≥ 799.9 K from 1-20 ms.