Le travail présenté concerne l'étude des instabilités thermo-acoustiques apparaissant dans une chambre de combustion aéronautique. Le montage expérimental permet de faire varier continument les fréquences de résonances et de passer pour une même condition d'écoulement, d'un régime de combustion stable à un régime instable. La caractérisation complète d'un cas instable comprend une mesure des conditions acoustiques aux limites du banc, une analyse du comportement des phases liquide et évaporée, de celui du dégagement de chaleur instationnaire et une mesure de la fonction de transfert de la flamme. Ces travaux ont mis en évidence trois phénomènes jouant sur l’injection cyclique de carburant liquide. Les temps caractéristiques des différents phénomènes intervenant dans le couplage thermo-acoustique et une distribution spatiale de l'indice de Rayleigh sont présentés. / The purpose of this experimental study was to further our understanding of the fuel spray behavior during combustion instability phenomena in combustion chambers. An aeronautical injection system with dual kerosene lines was mounted on the LOTAR setup, which was equipped with an adjustable exhaust length. Stability maps were generated by varying the global equivalent ratio and the fuel split parameter, for two Inner Exhaust Lengths (IEL). A non-unique multiphase flow condition was found to produce stable and unstable combustion for different IELs. Each configuration was fully characterized. Acoustic boundary conditions were measured using the 2-microphone technique. Different optical techniques were used toanalyze the unsteady behavior of the liquid phase, fuel vapor, and heat release. Moreover, two techniques were exploited to study the Flame Transfer Function using velocity measurement supstream and downstream of the injection device. Altogether, these results highlighted three atomization phenomena occurring during the cycles of thermo-acoustic instabilities. The phase-averaged analysis applied on the different measurements permitted to determine thetime scales associated with each process appearing in the thermo acoustic coupling. This cyclic injection of liquid fuel into the chamber was followed by a vapor phase increase corresponding to a wave of equivalent ratio. The delay between the two phenomena was of10°. In addition, OH* emissions showed a cyclic behavior following these waves. The delay between the wave of equivalent ratio and the unsteady heat release was approximately of 25°.Finally, spatial distribution of the Rayleigh index revealed that the inner recirculation zone contributed to sustain the combustion instability.

Le procédé de rétreint fait partie de la famille des techniques de mise en forme sans enlèvement de matière. La déformation du lopin est obtenue par chocs successifs d'un ensemble de matrices disposées autour de la pièce. Ce procédé est généralement utilisé pour la réduction de section de tubes ou de barres. Dans un contexte industriel, la maîtrise des paramètres procédé et la compréhension des phénomènes sous-jacents est indispensable pour non seulement limiter le temps de développement de nouveaux produits mais aussi diminuer le nombre de rebus des références qui posent problème. L'objectif de la thèse est de répondre à ces attentes en exploitant les possibilités offertes par la simulation numérique. Dans un premier temps, les alliages étudiés ont été caractérisés mécaniquement. En effet grâce à des essais de traction et d'impact de Taylor et à l'emploi d'une méthode d'identification par analyse inverse, les paramètres de la loi d'écoulement de Johnson-Cook ont été déterminés. Dès lors différents modèles, utilisant le code Abaqus/Explicit, ont été mis en place (du 2D axisymétrique au 3D en passant des modèles en reprenant que le quart de la pièce) et la validation s'est faite grâce à des campagnes d'essais réalisés sur site. Enfin, un progiciel développé en C++ sera livré à l'industrie. Il intègre différentes fonctionnalités comme la prédiction des efforts de forge par calcul analytique. Tous ces outils numériques et analytiques ont permis de mieux comprendre le procédé en termes de chemin d'écoulement de la matière, de distribution des contraintes et déformations et de profil d'évolution d'évolution de l'effort tout au long de la mise en forme. ABSTRACT : The shrinking process is part of the family of formatting techniques without removing material. / The shrinking process is part of the family of formatting techniques without removing material.

O presente trabalho tem por objetivo definir o modal de transporte ótimo para componentes comprados que abastecem a linha de produção de uma empresa aeronáutica, ao menor custo logístico. Devido a característica do material e das exigências de órgãos e entidades responsáveis pelo ambiente industrial aeronáutico, os fornecedores são especializados e de origem internacional, pois as indústrias nacionais ainda não têm a certificação exigida para produzir tais materiais, salvo algumas poucas exceções, o que onera e torna a cadeia de suprimentos muito mais complexa. Portanto, para atingir o objetivo proposto utilizou-se um modelo heurístico, que decide o modal de transporte ótimo para transportar estes materiais de sua origem, EUA ou Europa, até seu destino que é o Brasil. / The present paper aims to define an optimum modal of transportation for acquired components used to supply the production line in a Aeronautical Company, based on the lowest logistic cost. Due to the caracteristics of such material and the special requirements of the Governamental agencies as well as the specific agencies that rule the aeronautical industrial environment, the suppliers which are in its vast majority of this net are from abroad. It happens due to the fact that the local Industry do not hold the required certification to manufacture or assemble such materials which throws the costs and its complexity much more present. Some few isolated companies constitute a exception of this general frame. Based on the exposed, to achieve the proposed goal a heuristic model was used, which defines that the best modal of transportation to transport those specific materials from its origin, USA or Europe, to your final destination in Brazil.

A língua franca utilizada na comunicação piloto-controlador ainda é pouco conhecida no meio acadêmico. Poucos estudos têm sido dedicados ao seu contexto de uso e ao mapeamento de suas características lingüísticas principais. Esta pesquisa acadêmica apresenta um estudo mais acurado da atividade de controlador de tráfego aéreo, no que se refere ao uso dessa linguagem de especialidade, além de desenvolver um estudo descritivo da língua franca utilizada na comunicação piloto-controlador para a identificação de suas características lingüísticas principais, com o recorte para a produção de material didático. Por meio da utilização do método do Professor André Camlong, a ferramenta computacional denominada STABLEX, fazemos uma análise descritiva, objetiva e indutiva de um corpus lingüístico, constituído dessa linguagem de especialidade. O que se pretende é oferecer subsídios aos professores de língua estrangeira para a produção do seu próprio material didático para o ensino dessa linguagem. É fato que, em determinados contextos de ensino, a necessidade de aprendizagem dos alunos é tão específica, que os materiais prontos para consumo, disponibilizados nas prateleiras das livrarias ou pelas editoras, não são suficientes, cabendo ao professor a tarefa de elaborá-los. No entanto, essa tarefa não tem se mostrado amistosa, já que o professor não dispõe de \"guias de orientação\", cientificamente justificáveis, para fazê-la. Assim sendo, o processo de elaboração torna-se intuitivo e empírico e, na grande maioria das vezes, restringese à adoção de fórmulas já consagradas de apresentação dos conteúdos. Acreditamos ser fundamental o correto entendimento das reais necessidades lingüísticas de um determinado público-alvo, para que haja mais condições de se estabelecerem processos mais ricos e eficientes de ensino e aprendizagem de qualquer língua estrangeira. / The lingua franca used in the communication between pilots and controllers is still not well known in the academic community. Few studies about its use and mapping of its main linguistic characteristics have been made. This theoretical research introduces an accurate study on the language used in the activity of air traffic controllers and develops a descriptive study of the lingua franca used in the communication between pilots and controllers, in order to identify its main linguistic characteristics towards material production. By using the method developed by Professor André Camlong and the computational tool STABLEX, an objective descriptive and inductive analysis of a linguistic corpus constituted by the language used in the ATC specialty has been conducted. The aim of this work is to provide language teachers with subsides for ATC material production hence helping teachers to elaborate materials that meet the very specific needs of their students based on the real needs of the stakeholders so as they can establish a more fruitful and efficient language teaching and learning process.

ABSTRACT Multidisciplinary Design Optimization of an Extreme Aspect Ratio HALE UAV Bryan J. Morrisey Development of High Altitude Long Endurance (HALE) aircraft systems is part of a vision for a low cost communications/surveillance capability. Applications of a multi payload aircraft operating for extended periods at stratospheric altitudes span military and civil genres and support battlefield operations, communications, atmospheric or agricultural monitoring, surveillance, and other disciplines that may currently require satellite-based infrastructure. Presently, several development efforts are underway in this field, including a project sponsored by DARPA that aims at producing an aircraft that can sustain flight for multiple years and act as a pseudo-satellite. Design of this type of air vehicle represents a substantial challenge because of the vast number of engineering disciplines required for analysis, and its residence at the frontier of energy technology. The central goal of this research was the development of a multidisciplinary tool for analysis, design, and optimization of HALE UAVs, facilitating the study of a novel configuration concept. Applying design ideas stemming from a unique WWII-era project, a “pinned wing” HALE aircraft would employ self-supporting wing segments assembled into one overall flying wing. The research effort began with the creation of a multidisciplinary analysis environment comprised of analysis modules, each providing information about a specific discipline. As the modules were created, attempts were made to validate and calibrate the processes against known data, culminating in a validation study of the fully integrated MDA environment. Using the NASA / AeroVironment Helios aircraft as a basis for comparison, the included MDA environment sized a vehicle to within 5% of the actual maximum gross weight for generalized Helios payload and mission data. When wrapped in an optimization routine, the same integrated design environment shows potential for a 17.3% reduction in weight when wing thickness to chord ratio, aspect ratio, wing loading, and power to weight ratio are included as optimizer-controlled design variables. Investigation of applying the sustained day/night mission requirement and improved technology factors to the design shows that there are potential benefits associated with a segmented or pinned wing. As expected, wing structural weight is reduced, but benefits diminish as higher numbers of wing segments are considered. For an aircraft consisting of six wing segments, a maximum of 14.2% reduction in gross weight over an advanced technology optimal baseline is predicted.

Current airspace regulations require the remote pilot-in-command of an unmanned aircraft systems (UAS) to maintain visual line of sight with the vehicle for situational awareness. The future of UAS will not have these constraints as technology improves and regulations are changed. An operational model for the future of UAS is proposed where a remote operator will monitor remote vehicles with the capability to intervene if needed. One challenge facing this future operational concept is the ability for a flight data system to effectively communicate flight status to the remote operator. A system architecture has been developed to facilitate the implementation of such a flight data system. Utilizing the system architecture framework, a Phase I prototype was designed and built for two vehicles in the Autonomous Flight Laboratory (AFL) at Cal Poly. The project will continue to build on the success of Phase I, culminating in a fully functional command and control system for remote UAS operational testing.

La certification des moteurs aéronautiques impose des fortes réductions des émissions polluantes. Une des solutions adoptées par les constructeurs est d'introduire la combustion pauvre dans les nouvelles chambres. Cette configuration pose des problèmes de stabilité de flamme et de ré-allumage en altitude. Le ré-allumage des moteurs doit être garanti et il y a une nécessité réelle de mieux comprendre les interactions complexes et multi-physiques guidant ce processus. Cette étude expérimentale vise les différentes phases de l'allumage aéronautique dans deux chambres swirlées, confinées diphasiques. Un foyer mono-injecteur permet d'analyser le développement du noyau de flamme dans ses premiers instants et de décrire comment les interactions avec l'écoulement local peuvent conduire à une réussite d'allumage ou à une ratée, via différents mécanismes. Une chambre multi-injecteur est dédiée à analyser la propagation de la flamme entre injecteurs pour différents espacements et carburants. / Jet engine certification undergoes more and more stringent controls that impose a strong reduction of pollutant emissions. As a response, designs move towards lean combustion, which raises difficulties relative to combustion stability and re-ignition capabilities in high altitude. The use of liquid fuels in real chambers introduces new variables into the ignition process, which involves complex simultaneous multi-physical interactions. The present experimental investigation addresses different phases of aeronautical ignition in two different confined, swirled, spray jet chambers. A single-injector facility is used to study the initial flame kernel development and interaction with the flow leading to successful ignition or misfire, following different mechanisms. A multi-injector facility enables the investigation of flame propagation between injectors, which is also governed by the local flow. Here, inter-injector distances are varied and fuels of different volatilities are tested.

This dissertation explores the role of polarization, combining, and equalization operating over frequency-selective channels to improve the reliability of wireless communications systems in terms of BER for two applications: 5G mobile networks (operating in the mmWave band and NR FR1), and aeronautical mobile telemetry systems (operating in L band). The equivalent discrete-time models for a variety of spatial combining techniques at 5G mmWave bands were derived to investigate the performance of co-located cross-polarized antenna elements when polarization diversity is used and also when a combination of spatial and cross-polarized antennas is exploited. In both cases, ML combining has the lowest BER and EPC produced the worst results. The use of co-located cross-polarized antenna elements also is examined in 5G FR1 assuming post-FFT processing of the two antenna element outputs in a mobile-to-mobile setting. The optimum strategy, in the ML sense, for incorporating the two antenna outputs is developed. The optimum combining strategy together with a FDE is compared to the traditional combining techniques: MRC, EGC, and SC, where the last two also require a FDE. Computer simulations performed over a stochastic channel model with polarization state information show that the difference between ML detection and MRC (the best performing methods) and SC with FDE (the worst performing method) is 2 dB. The similar results were observed with pilot based channel estimators, however the difference in this case was the presence of a BER floor at low values of $N_0$ and caused by channel estimation errors. In aeronautical mobile telemetry applications, the ML combiner is derived and shown to be equivalent to the summing the outputs of two filters matched to the channels in the horizontal and vertical polarization states. For historical reasons, current systems combine right-hand and left-hand circularly polarized antenna feed outputs using a MRC. To compare the two combining approaches, the aeronautical telemetry multipath channel was extended to include polarization state information. The simulation results for SOQPSK-TG with a CMA equalizer show that the post-equalizer BER for the two approaches is the same.

This dissertation explores the application of Silvester's space-time block code to the multi-index CPM called "ARTM CPM" in the IRIG 106 standard to solve the "two antenna problem"---the use of two transmit antennas to provide full spatial coverage on an airborne test article and the accompanying self interference due to different delays between the two transmit antennas and the ground-based receive antenna. A symbol-level encoding scheme is derived that allows the burst-based space-time block code to operate in a continuously streaming mode. The results show that the space-time block code can solve the two antenna problem with differential delays, but that the differential delays generate a substantial increase in the computational complexity of the detector. Complexity-reducing techniques are applied and analyzed. The results show that the complexity reductions required to produce a practically realizable detector render the bit error probability performance sensitive to the differential delay. Numerical results are presented to quantify the performance loss due to the differential delay. The use of space-time coded ARTM CPM to solve the two-antenna problem in aeronautical mobile telemetry requires estimates of the parameters that define the propagation environment. The maximum likelihood estimator problem is defined and used to motivate reduced-complexity estimators suitable for use in a real system. A modified gradient descent algorithm performs the search required to find the delay parameters. An "inner" phase lock loop operating with an "outer" frequency lock loop computes decision-directed estimates of the frequency offset. Computer simulations were used to assess the impact on bit error rate performance introduced by the estimators. The simulation results show the combined joint estimator for the delays, channel gains, and frequency offset imposes a 1.15 dB loss in performance. This loss is approximately the same as the 1.1 dB loss due to the complexity-reducing techniques used by the decoder/detector.

Lima posee museos de diversas tipologías. Unos adaptados en casas de personajes renombrados, viejas mansiones, o espacios que poseen alguna cualidad constructiva, pertenecientes a épocas anteriores pero cercanas de nuestra historia. Otros museos, en edificios imponentes, de gran tamaño hacia el exterior, pero con salas reducidas hacia interior los que generan límites definidos a la exhibición, sin haber nacido para realmente ser áreas de exhibición. El Museo Aeronáutico del Perú, fue originalmente ubicado en los dormitorios de la antigua Escuela de  Oficinales en la “Base Aérea las Palmas” y posteriormente situado en el Castillo Rospigliosi, antigua sede de logística de la FAP, en ambos casos con adaptaciones en espacios reducidos y exhibiciones limitadas. Asimismo, los aviones se encontraban ubicados en las afueras de edificios de las Fuerzas Armadas, en la calle sobre avenidas, en el Aeropuerto y en zonas del Callao, sin dar apropiadamente conocer su historia y características. El presente proyecto está concebido como un espacio especializado: Tanto cultural y de identidad referente la aviación, a hechos heroicos de personas que dieron su vida con un fin particular, de la complejidad de las maquinas que son capaces de  trasladarnos a lugares remotos y volar. Dar a conocer en verdadera magnitud las imponentes naves en un espacio adecuado de gran envergadura y luces adecuada que exhiban además la imponencia de su diseño y estructura. Generar un espacio de recreación temático, con exhibiciones estáticas al interior y dinámicas al exterior. / Lima, owns museums of various typologies. Some of them adapted in houses of renowned persons, older mansions, or at spaces that represents some constructive qualities from closer past times. Other museums, at gorgeous structures oversized outside going out, but with not so bigger inner areas, that created hard boundaries to exhibitions and limited proportions. Aeronautical Museum of Peru, was originally located at the bedrooms older area of the Peruvian Military Officers School at the well known base of Las Palmas, and later relocated at the spaniel Castillo Ropigliosi, ancient Logistic Offices of the FAP, but both of them with many restrictions to the spaces and areas to be used. Even more, air units have always been located at the street over avenues, outside of Military buildings, at the International Airport, or in El Callao zones, without let us know their true stories and characteristics. Those project has been designed as an specialized zone: Cultural and also with a proper identity, deeply referred to Peruvian aviation, including heroic actions of people that gave their own life, also referring to machines complexity, all of them that were capable to move us or to transport us, according they were used. Its also been designed in order to show us real sizes and adequate references to their flying qualities. Also to generate a thematic and recreational area, allowing us to visit statics inner exhibits, but also outer and dynamic presentations, in order to feel the power of machines. / Tesis