This thesis explores the role the U.S. plays in the developmental process of international nonproliferation regime. The argument of this thesis is mainly based on the power-based perspective, which assumes that the U.S., the first country to obtain nuclear technology, profoundly influences the creation and persistence of the nonproliferation regime. First of all, I discuss the debate on the theories of international regime in order to highlight the applicability of power-based approach in the research of nonproliferation regime. Secondly, I examine both the nuclear policy of the U.S. and the developmental history of nonproliferation regime, so as to explain the former¡¦s impacts over the latter. Finally, I evaluate the different means and postures of the U.S. when she confronts different violators. Through this inquiry, I attempt to expose the flaw of the nonproliferation regime: the proliferation problem is still not totally suspended even after the establishment of the nonproliferation regime. The main factor of the flaw is, nonetheless, resulted from the U.S.¡¦ misapplication of her nuclear hegemonic power and her selective proliferation policy towards different violators, although she had positively contributed to the creation and persistence of the nonproliferation regime.

In this thesis, development process of de-icing and anti-icing solutions and their flow instability characteristics are presented. In the beginning, the chemical additives in the solutions and their effects on the most critical physical properties of the solutions were investigated. Firstly, chemical additives were added to glycol and water mixtures at different weight ratios one by one in order to see their individual effects. Then, the changes in physical properties were observed when the chemicals were added to water-glycol mixture together. After that, study was focused on effect of polymer which makes the solution pseudoplastic. Further investigations on viscosity behavior of the solution at different pH values, glycol and water mixtures and surfactant weight ratios, which is used for surface tension reduction, were performed. For the investigation of flow instability characteristics of the solutions&rsquo / flows, linear stability analysis for two-layer flows is a basic tool. Firstly, the effects of main parameters on the stability of two-layer flows were observed with a parametric study. Then, the commercially available and developed de-icing and anti-icing solutions were compared according to the characteristics of unstable waves. According to the results, unstable waves on developed de-icing fluids are observed at a lower critical wind speed compared to the commercially available de-icing solution. Moreover, it flows off the wing faster due to a higher value of critical wave speed. Developed anti-icing solution has similar wave characteristics compared to commercially available anti-icing solution, except critical wave speed, which is significantly lower. However, this problem can be overcome by decreasing the viscosity of developed anti-icing solution at very low shear rates.

In this study, numerical investigations of stability and transition problems were performed for 2D compressible boundary layers over a flat plate in adiabatic wall condition. Emphasis was placed on linear stability theory. The mathematical formulation for 3D boundary layers with oblique waves including detailed theoretical information was followed by use of the numerical techniques for the solution of resulting differential system of the instability problem, consequently an eigenvalue problem. First, two-dimensional sinusoidal disturbances were analyzed at various Mach numbers including the subsonic, transonic, supersonic and even hypersonic flow speeds. In this case, the second mode (acoustic mode), namely the Mack mode, and its behavior with the increasing Mach number were visualized. The results were then compared with the available data in literature concluding with good agreements. Secondly, similar analysis was carried out for oblique waves. Here, not only the effect of flow speed but also the effect of wave orientation was demonstrated. For this purpose, instability problem was solved for several wave angles at each Mach number in the range of M=0 and M=5. In this respect, the angle at which the waves were most unstable was also obtained at each investigated flow speed. The resultant stability diagrams corresponding to M=4 and higher Mach numbers for which both first and the second modes appear revealed that plane waves were more stable than oblique waves for the Tollmien-Schlichting mode, however, this was the opposite for the acoustic mode where oblique waves were observed to be more stable. As a final step, estimation of the transition location was handled for the most unstable wave condition. Smith-Van Ingen transition method was applied as the prediction device. The results representing the influence of Mach number on transition Reynolds number were then compared with the experimental data as well as the numerical ones in literature ending up with very good agreements.

The thesis deals with comparing China and United States in terms of their potential hegemonic status. A country can be considered as a hegemonic country only if it fulfills various attributes. Its economic leadership is defined by consistency of inner market and by generated imports. Those are supported by advanced financial market and national currency, which is also considered as a world currency. Institutional scope is summarized by privileged position of its army and it defines hegemonic country as a center of innovation and technological progress.

Cette thèse concerne des systèmes hybrides et le théorème des petits-gains. Plus précisément, d'une part, nous avons calculé les lois de commande hybrides pour les systèmes non-linéaires lesquels les techniques de synthèse par backstepping ne s'applique pas et nous avons réussi à combiner les lois de commande locales et globales pour la stabilisation d'un ensemble «proche» de l'origine. La seconde contribution est sur ​​le théorème des petits-gains, en traitant avec des systèmes pour lesquels les conditions des petits-gains sont satisfaites seulement au niveau régional. Nous avons réussi à combiner ces conditions régionales pour le petit-gain pour la stabilité asymptotique et pour la presque stabilité asymptotique globale. / This theses concerns hybrid systems and small gain theorems. More precisely, firstly we computed hybrid stabilizers for nonlinear control systems for which the backstepping techniques do not apply, and we succeeded to combine local feedback laws and global controllers stabilizing a set "close" to the origin. The second contribution is on small gains theorem, by dealing with systems for which small gains conditions are satisfied only regionally. We were able to combine such region-dependent small-gain conditions for the global asymptotic stability and for the almost global asymptotic stability.

The U.S. has enjoyed global hegemonic power for over 70 years and even more so after the fall of the Soviet Union. However, some political scientists argue that it is descending and the evidence lies in the increasing power of China. An imbalance of power in the international structure has the ability to result in different outcomes. The realist theory suggests that a conflict between the U.S. and China is unavoidable, the liberal theory suggests that the economic dependency between the two makes conflict less possible, while the constructivist theory suggests that the outcome depends on the reaction of the leaders and social change. This study asks what the reaction of the President of the U.S. is to the rise of China to find out the result of this hegemonic power imbalance. By using discourse analysis, this study has analyzed the remarks of President Trump from the period of January 2017 to November 2017 in search of his reaction to the rise of China. The results of this study show that President Trump divides the world in two parts making the U.S. the protagonist and the rest of the world, including China, the antagonist in his discourse as his reaction. Due to this reaction, Trump takes nationalistic and protectionist measures against China.

本論文旨在探討二十一世紀，美國面臨中國在東亞的經營，如何維持其在東亞的霸權所作的努力。冷戰結束後，美國在國際社會成為碩果僅存的霸權。藉此優勢，美國得以遂其意志，有些甚至非其能力所及。雖然美國可確定是當今唯一的霸權，但中國挾其經濟快速起飛之利，不但在全球各地揮舞其影響力，更試圖擴大外交上的戰果。此外，中國軍事成長之快速，從軍事現代化到太空競賽，足以顯示中國將改變東亞的政治環境及地區安全。因此，中國的崛起對美國霸權，尤其在東亞，被視為一潛在的威脅。美國要如何鞏固其在東亞的霸權領導地位，自然為當前極為迫切的議題。由研究發現，美國所作的努力倍極艱辛、複雜但結果是成功的。 / After the end of the Cold War in 1991, the United States poses a unique position in the international system. As hegemony, the U.S. has the greatest stake in the existing order. Yet it also takes advantage of its position as the most powerful nation in the world to bend that order to its will and even act outside the limits of the system. It seems to confirm American hegemony, with the U.S. left as the only superpower. With its soaring rise, however, China is looming as a potential challenger to the U.S. hegemony in East Asia. China not only wields radically increasing commercial clout in all regions of the globe, but also tries to achieve diplomatic advantage with respect to the United States. Further, Beijing’s rapid, deep, and wide-ranging modernization in military capabilities ranging from diesel submarines to micro-satellites and the launching of ballistic missile destroying one of its own orbiting weather satellites will enable China to increasingly dominate the East Asian littoral. Therefore, how to maintain American hegemony especially in East Asia has become a pressing issue for the United States. The thesis uses in-depth studies of critical literature and case study to analyze the wrestle between U.S. and China in East Asian Area. From the research one can find that the effort the U.S. has made to maintain its hegemonic leadership in East Asia is hard but successful.

Le contrôle de l’instabilité de Rayleigh-Taylor (RT) est crucial pour la fusion par confinement inertiel (FCI) puisque son développement peut compromettre l’implosion et la correcte compression de la cible. En attaque directe, l’énergie fournie par l’irradiation de nombreux faisceaux laser provoque l’ablation de la couche externe de la cible (ablateur) et l’apparition résultante d’un plasma de basse densité en expansion. De ce fait, une très haute pression apparait autour de cette surface, ce qui conduit à l’accélération de la cible vers l’intérieur. On se trouve alors en présence d’un fluide de basse densité qui pousse et accélère le fluide plus dense. C’est une des situations typiques qui favorisent le développement de l’instabilité de RT. Cette thèse développe pour la première fois, dans le contexte de la FCI, une théorie linéaire de stabilité pour des structures à double front d’ablation, qui apparaissent quand des matériaux de nombre atomique modéré sont utilisés comme ablateurs. / The Rayleigh-Taylor instability is a major issue in inertial confinement fusion capable to prevent appropriate target implosions. In the direct-drive approach, the energy deposited by directed laser irradiation ablates off the external shell of the capsule (ablator) into a low-density expanding plasma. This induces a high pressure around the ablating target surface (ablation region) that accelerates the capsule radially inwards. This situation, a low density fluid pushing and accelerating a higher density one, is the standard situation for the development of the Rayleigh-Taylor instability, and therefore a potential source of target compression degradation. For moderate-Z materials, the hydrodynamic structure of the ablation region is made up of two ablation fronts (double ablation front) due to the increasing importance of radiation effects. This thesis develops for the first time a linear stability theory of double ablation fronts for direct-drive inertial confinement fusion targets.

Orientador: Gustavo Luiz Chagas Manhães de Abreu / Resumo: O presente trabalho propõe uma nova estratégia para supressão ativa robusta do fenômeno Ground Resonance (GR) em Helicópteros. O modelo clássico de análise deste fenômeno é desenvolvido para um rotor isotrópico e a análise de estabilidade é feita no domínio de Coleman, para encontrar as fronteiras de instabilidade. Também é proposta uma nova estratégia para lidar com essas fronteiras de instabilidade e suprimir o GR usando controladores com formulação descrita por conjuntos politópicos convexos. Controladores são projetados via desigualdades lineares matriciais (LMIs, Linear Matrix Inequalities), formulados de acordo com a Teoria de Estabilidade de Lyapunov. Adicionalmente, incertezas paramétricas na frequência de lead-lag das pás e a apresentação de uma falha estrutural nos atuadores são consideradas e, assim, novos controladores robustos são projetados a fim de expandir o envelope operacional da aeronave. Ainda, são considerados diferentes tipos de não-linearidades estruturais na rigidez e amortecimento do trem de pouso do helicóptero e a caracterização da estabilidade não-linear do sistema exibe oscilações em ciclo limite (LCO, Limit Cycle Oscillation), que são determinadas a partir da construção de Diagramas de Bifurcação. Utiliza-se a modelagem Fuzzy-TS do sistema para cada caso de estudo e, com base nas fronteiras de estabilidade não-linear do GR, definidas a partir dos Diagramas de Bifurcação, têm-se o projeto de controladores para supressão das LCOs do sistema. Os res... (Resumo completo, clicar acesso eletrônico abaixo) / Abstract: The present work proposes a new strategy for robust active suppression of Ground Resonance (GR) phenomenon in Helicopters. The classical model to analysis of this phenomenon is developed for an isotropic rotor and stability analysis is done in Coleman domain, to nd the boundaries of instability. It is also proposed a new strategy for dealing with these boundaries of instability and suppressing GR using controllers with polytopic convex hulls formulation. Controllers are designed via Linear Matrix Inequalities (LMIs), formulated according to the Lyapunov Stability Theory. Additionally, parametric uncertainties in the lead-lag frequency of the blades and actuators faults are considered and thus new robust controllers are designed to expand the aircraft operating envelope. Also, di erent types of structural nonlinearities in the landing gear sti ness and damping of the helicopter are considered, and the characterization of the nonlinear stability of the system exhibits Limit Cycle Oscillation (LCO), which are determined from the construction of Bifurcation Diagrams. Fuzzy-TS modeling is used for each case study and, based on the nonlinear stability boundaries of the GR, de ned from the Bifurcation Diagrams, the controllers to suppress the LCO are designed. The results of numerical simulations, discussions and conclusions are presented and show that the control strategy proposed is an attractive solution to suppress the linear and nonlinear GR problem, being able to expand the o... (Complete abstract click electronic access below) / Doutor

O som gerado por escoamentos, também conhecido como aeroacústica, tem se tornado cada vez mais importante em áreas industriais diversas desde aviação comercial até aparelhos eletrodomésticos, afetando diretamente os requisitos necessários para o desenvolvimento de novos produtos. Um caso particular é o ruído gerado por válvulas de compressores herméticos de refrigeração, sendo o compressor a principal fonte de ruído em refrigeradores domésticos. O presente trabalho tem por objetivo iniciar o desenvolvimento de uma ferramenta confiável de simulação capaz de auxiliar engenheiros na predição de problemas de aeroacústica, especialmente um que possa no futuro ser utilizado para estudar o ruído gerado pelo escoamento em válvulas de compressores herméticos. Para isso, foi desenvolvido um código para simulação numérica direta de aeroacústica. Utilizou-se processamento paralelo com decomposição de domínio para usar Simulação Numérica Direta em um tempo factível; esquemas de discretização espaciais e temporais de alta ordem para minimizar ao máximo os fenômenos de dissipação e dispersão do escoamento e das ondas acústicas e uma série de tratamentos no domínio como filtragem e estiramento da malha como também condições de contorno características com o intuito de obter uma solução adequada para estudo de aeroacústica. Assim, são apresentadas todas as etapas desenvolvidas no equacionamento, implementação e verificação. A verificação foi realizada segundo um processo matemático formal (Método das Soluções Manufaturadas) com o qual obteve-se que a ordem de precisão dos cálculos era a mesma da ordem formal dos esquemas de discretização utilizados para todas as variáveis. Também obteve-se a mesma concordância para análise do divergente da velocidade, verificando o código para simulação numérica direta de aeroacústica. Posteriormente, foram realizadas simulações de escoamentos compressíveis cisalhantes e seus resultados comparados com dados apresentados em literatura. Também foram calculadas as taxas de amplificação de perturbações e comparadas com a Teoria de Estabilidade Linear. Novamente, foram obtidos resultados satisfatórios nessas etapas, mostrando que a implementação do código DNS está verificada. / Sound generated by flow, known as aeroacoustics, is becoming more important in several industrial areas from commercial aircraft to household appliances, affecting directly the requirements to the development of new products. A particular case is the noise generated by valves of refrigeration hermetic compressors, being the compressor the main noise source in household refrigerators. This work has the goal of initiate the development of a reliable tool able to help engineers to predict aeroacoustics problems, specially one that can be used in the future to study the noise generated by the flow in valves of hermetic compressors. To do so, it was developed a numerical code to perform direct numerical simulation of aeroacoustics. It was used parallel processing with domain decomposition to use Direct Numerical Simulation in a feasible time; high order temporal and spatial discretization schemes to minimize the most the dispersion and dissipation phenomena of the flow field and of the acoustics waves and a series of treatments in the domain as filtering and mesh stretching as well as characteristics boundary conditions aiming a proper solution to study aeroacoustics. Thus, here all the steps developed in the formulation, implementation and verification are presented . The verification was done according to a formal mathematical procedure (Method of Manufactured Solutions) with which was found that the precision order of the calculations was the same of the formal order of the used discretization schemes for all variables. The same agreement was also obtained to the analysis of the divergence of the velocity, verifying the code to direct numerical simulation of aeroacoustics. Posteriorly, it were simulated shear compressible flows and the results were compared to literature data. Also, it were calculated the amplification rates of the disturbances and compared to Linear Stability Theory. Once more, it was obtained satisfactory results in these steps, showing that the implementation of the DNS code is verified.