O objetivo deste trabalho é avaliar o processo atual de preparação de superfície para aderência de isolantes térmicos em envelopes motores foguetes de 1.000 mm de diâmetro, visando sua utilização no aço Maraging 18Ni300, tendo como parâmetros de comparação a rugosidade superficial e a resistência mecânica adesiva, obtida atualmente na interface colada metal/isolante térmico do aço 300MESR. Para isso, foram realizados experimentos de campo, com uma abordagem quantitativa, por meio da medida de rugosidade (Ra) nas superfícies de amostras de aços, submetidas a tratamento superficial mecânico de jateamento abrasivo a seco com granalha de aço de perfil angular, sendo posteriormente selecionadas e utilizadas como substrato em juntas adesivadas que, por fim, foram submetidas a ensaio mecânico de cisalhamento, para verificação da resistência mecânica adesiva. A utilização de métodos de análise estatísticos (análise de variância, teste de tukey, intervalo de confiança) aplicados aos dados coletados, permitiram estabelecer, para o processo atual uma faixa de resistência mecânica adesiva para cada aço pesquisado. Os resultados obtidos confirmam, com boa margem de segurança, que o processo atual de preparação de superfície para aderência de isolantes térmicos pode ser aplicado ao aço Maraging 18Ni300, sem que ocorra perda significativa de resistência mecânica adesiva na interface colada metal/isolante térmico. / The aim of this work is to evaluate the current process of preparing the surface for adherence of thermal insulation in rocket motor of 1,000 mm diameter, seeking their use in Maraging18Ni300 steel, taking as parameters comparison the of surface roughness and mechanical adhesive strength obtained, currently, in the bonded interface metal /heat insulator 300M-ESR steel. A field experiment was conducted with a quantitative approach, by measuring surface roughness (Ra) on the surfaces of steel samples, subjected to mechanical surface treatment of dry abrasive blasting, with steel shot with angular profile and which were, subsequently, selected and used in bonded joints that were finally submitted to mechanical shear tests to verify the mechanical adhesive strength. The use of statistical methods of analysis (variance analysis, Tukey test, confidence interval), applied to selected data, allowed to establish for the current process, a range of mechanical adhesive strength for each steel investigated. The results confirm, with a good safety margin, that the current process of preparing the surface for adhesion of thermal insulation can be applied to the Maraging18Ni300 steel, without significant loss of mechanical adhesive strength in the metal /heat insulator bonded interface.

Made available in DSpace on 2016-08-17T14:53:23Z (GMT). No. of bitstreams: 1 Dissertacao Harnoldo Castro.pdf: 2052364 bytes, checksum: 3ff44ce616ef2f1e748c29067008a2d1 (MD5) Previous issue date: 2012-12-14 / This work investigates electromagnetic disturbances that affect the power quality of the Alcântara Launch Center (CLA), supplied by the local power distribution utility company and the self-generation of the Center, emphasizing disturbances for sensitivity of electrical ground support equipment, variations in voltage and short-term transients. From a bibliographical study, the main electromagnetic phenomen apresented are related to the power quality, showing the causes, consequences and suggestions for mitigation of these events, including the reduction of inrush current, based on standard norms related to the subject. The monitoring was performed using an accurate monitoring equipment during a two-rocket launch campaign, for a better contextualization ofvoltage variations associated to short-term transients. From the records and gathered data, critical events and power quality indices associated to the distribution utility and to the generation set were analyzed, as well as the severe disturbances characterized by CBEMA curve. The results provided subsidies to improve and reduce the effects of voltage short-term and transient events. Thus an operating procedure for special processes is proposed, which can be used both in the aerospace sector as in organizations that have their processes associated to power quality. / O presente trabalho investiga distúrbios eletromagnéticos que afetam a qualidade da energia elétrica do Centro de Lançamento de Alcântara, suprido pela companhia elétrica local e pela autogeração do próprio Centro, enfatizando os distúrbios críticos para a sensibilidade elétrica dos equipamentos de apoio em solo, as variações de tensão de curta duração e os transitórios. A partir de um estudo bibliográfico, são apresentados os principais fenômenos eletromagnéticos relacionados à qualidade da energia elétrica, mostrando as causas, consequências e sugestões para mitigar tais eventos, com destaque para a redução da corrente de energização, com base nas normas internacionais relacionadas ao tema. O monitoramento foi realizado utilizando-se um equipamento de precisão durante a campanha de lançamento de dois foguetes, para melhor contextualizar as variações de tensão de curta duração e os transitórios. A partir dos registros e dados coletados foram analisados os eventos críticos e os indicadores de tensão da distribuidora local de energia elétrica, e da autogeração de energia do Centro, bem como as graves perturbações caracterizadas com a curva CBEMA. Os resultados obtidos forneceram subsídios para reduzir os efeitos dos eventos da variação de tensão de curta duração e transitórios. Assim propõe-se um procedimento operacional para processos especiais, que poderá ser usado tanto no setor aeroespacial quanto nas organizações que tenham seus processos atrelados à qualidade da energia elétrica.

This thesis examines how to find the best fit to a series of data points when curve fitting using power-exponential models. We describe the different numerical methods such as the Gauss-Newton and Levenberg-Marquardt methods to compare them for solving non-linear least squares of curve fitting using different power-exponential functions. In addition, we show the results of numerical experiments that illustrate the effectiveness of this approach.Furthermore, we show its application to the practical problems by using different sets of data such as death rates and rocket-triggered lightning return strokes based on the transmission line model.

Finding limit cycles and their stability is one of the central problems of nonlinear thermoacoustics. However, a limit cycle is not the only type of self-excited oscillation in a nonlinear system. Nonlinear systems can have quasi-periodic and chaotic oscillations. This thesis examines the different types of oscillation in a numerical model of a ducted premixed flame, the bifurcations that lead to these oscillations and the influence of external forcing on these oscillations. Criteria for the existence and stability of limit cycles in single mode thermoacoustic systems are derived analytically. These criteria, along with the flame describing function, are used to find the types of bifurcation and minimum triggering amplitudes. The choice of model for the velocity perturbation field around the flame is shown to have a strong influence on the types of bifurcation in the system. Therefore, a reduced order model of the velocity perturbation field in a forced laminar premixed flame is obtained from Direct Numerical Simulation. It is shown that the model currently used in the literature precludes subcritical bifurcations and multi-stability. The self-excited thermoacoustic system is simulated in the time domain with many modes in the acoustics and analysed using methods from nonlinear dynamical systems theory. The transitions to the periodic, quasiperiodic and chaotic oscillations are via sub/supercritical Hopf, Neimark-Sacker and period-doubling bifurcations. Routes to chaos are established in this system. It is shown that the single mode system, which gives the same results as a describing function approach, fails to capture the period-$2$, period-$k$, quasi-periodic and chaotic oscillations or the bifurcations and multi-stability seen in the multi-modal case, and underpredicts the amplitude. Instantaneous flame images reveal that the wrinkles on the flame surface and pinch off of flame pockets are regular for periodic oscillations, while they are irregular and have multiple time and length scales for quasi-periodic and chaotic oscillations. Cusp formation, their destruction by flame propagation normal to itself, and pinch-off and rapid burning of pockets of reactants are shown to be responsible for generating a heat release rate that is a highly nonlinear function of the velocity perturbations. It is also shown that for a given acoustic model of the duct, many discretization modes are required to capture the rich dynamics and nonlinear feedback between heat release and acoustics seen in experiments. The influence of external harmonic forcing on self-excited periodic, quasi-periodic and chaotic oscillations are examined. The transition to lock-in, the forcing amplitude required for lock-in and the system response at lock-in are characterized. At certain frequencies, even low-amplitude forcing is sufficient to suppress period-$1$ oscillations to amplitudes that are 90$\%$ lower than that of the unforced state. Therefore, open-loop forcing can be an effective strategy for the suppression of thermoacoustic oscillations. This thesis shows that a ducted premixed flame behaves similarly to low-dimensional chaotic systems and that methods from nonlinear dynamical systems theory are superior to the describing function approach in the frequency domain and time domain analysis currently used in nonlinear thermoacoustics.

No description available.

Syftet med föreliggande arbete är att undersöka hur företag och organisationer förvaltar sina informationssystem, om Applicerad Modell (Hafström, Nordström; 1991) innehåller de delar som krävs för en fungerande systemförvaltning samt att med ledning av erhållen information diskutera kring problem och möjligheter med systemförvaltning. Vi genomförde en litteraturstudie och intervjuade personer som är inblandade I systemförvaltningsprocessen. Resultatet av litteraturstudien presenteras genom definitioner av begrepp och resultatet av tre vägledande undersökningar. Därefter presenteras en sammanfattning av de intervjuer vi genomfört. Utifrån erhållen information utvecklar vi definitionen av systemförvaltningsbegreppet. Applicerad Modell utvecklas och resultatet blir en ny modell kallad Raket Förvaltningsmodell. Vidare diskuterar vi kring problem och möjligheter med systemförvaltning och slutligen ges synpunkter på hur man skall starta arbetet med att strukturera systemförvaltningsprocessen. / The aim with the present work is to examine how corporations and organizations maintain their information systems, if the Applied Mode! (Hafström, Nordström; 1991) contain all parts required for working system maintenance and according to this discuss problems and possibilities of system maintenance. We realized a literature study and interviewed people who are involved in the process of system maintenance. The result of the literature study is presented by definitions of conceptions and the result of three examinations. A summary of the interviews is made. From the received information we developed the definition of the system maintenance conception. Applied Mode! is developed and the result is Rocket Maintenance Model. Further on we discuss problems and possibilities of system maintenance and finally we are giving our opinion how to start the work by structuring the system maintenance process.

La surveillance et l'amélioration des modes de fonctionnement des systèmes propulsifs des lanceurs représentent des défis majeurs de l'industrie aérospatiale. En effet, une défaillance ou un dysfonctionnement du système propulsif peut avoir un impact significatif pour les clients institutionnels ou privés et entraîner des catastrophes environnementales ou humaines. Des systèmes de gestion de la santé (HMS) pour les moteurs fusée à ergols liquides (LPREs), ont été mis au point pour tenir compte des défis actuels en abordant les questions de sureté et de fiabilité. Leur objectif initial est de détecter les pannes ou dysfonctionnements, de les localiser et de prendre une décision à l’aide de Redlines et de systèmes experts. Cependant, ces méthodes peuvent induire de fausses alarmes ou des non-détections de pannes pouvant être critiques pour la sécurité et la fiabilité des opérations. Ainsi, les travaux actuels visent à éliminer certaines pannes critiques, mais aussi diminuer les arrêts intempestifs. Les données disponibles étant limitées, des méthodes à base de modèles sont essentiellement utilisées. La première tâche consiste à détecter les défaillances de composants et/ou d'instruments à l'aide de méthodes de détection et de localisation de fautes (FDI). Si la faute est considérée comme mineure, des actions de « non-arrêt » sont définies pour maintenir les performances de l'ensemble du système à un niveau proche de celles souhaitées et préserver les conditions de stabilité. Il est donc nécessaire d’effectuer une reconfiguration robuste (incertitudes, perturbations inconnues) du moteur. Les saturations en entrée doivent également être prises en compte dans la conception de la loi de commande, les signaux de commande étant limités en raison des caractéristiques ou performances des actionneurs physiques. Les trois objectifs de cette thèse sont donc : la modélisation des différents sous-systèmes principaux d’un LPRE, le développement d’algorithmes de FDI sur la base des modèles établis et la définition d’un système de reconfiguration du moteur en temps réel pour compenser certains types de pannes. Le système de FDI et Reconfiguration (FDIR) développé sur la base de ces trois objectifs a ensuite été validé à l’aide de simulations avec CARINS (CNES) et du banc d’essai MASCOTTE (CNES/ONERA). / Monitoring and improving the operating modes of launcher propulsion systems are major challenges in the aerospace industry. A failure or malfunction of the propulsion system can have a significant impact for institutional or private customers and results in environmental or human catastrophes. Health Management Systems (HMS) for liquid propellant rocket engines (LPREs), have been developed to take into account the current challenges by addressing safety and reliability issues. Their objective was initially to detect failures or malfunctions, isolate them and take a decision using Redlines and Expert Systems. However, those methods can induce false alarms or undetected failures that can be critical for the operation safety and reliability. Hence, current works aim at eliminating some catastrophic failures but also to mitigate benign shutdowns to non-shutdown actions. Since databases are not always sufficient to use efficiently data-based analysis methods, model-based methods are essentially used. The first task is to detect component and / or instrument failures with Fault Detection and Isolation (FDI) approaches. If the failure is minor, non-shutdown actions must be defined to maintain the overall system current performances close to the desirable ones and preserve stability conditions. For this reason, it is required to perform a robust (uncertainties, unknown disturbances) reconfiguration of the engine. Input saturation should also be considered in the control law design since unlimited control signals are not available due to physical actuators characteristics or performances. The three objectives of this thesis are therefore: the modeling of the different main subsystems of a LPRE, the development of FDI algorithms from the previously developed models and the definition of a real-time engine reconfiguration system to compensate for certain types of failures. The developed FDI and Reconfiguration (FDIR) scheme based on those three objectives has then been validated with the help of simulations with CARINS (CNES) and the MASCOTTE test bench (CNES/ONERA).

Dans un moteur à propergol solide, des instabilités thermoacoustiques auto-entretenues, induites par le couplage de la dynamique de la combustion des gouttes d’aluminium, libérées par la combustion du propergol, avec le champ acoustique peuvent induire des oscillations de pression.L’analyse menée tout au long de ce manuscrit repose sur un ensemble d’hypothèses simplificatrices: (i) la réponse de la combustion de gouttes d’aluminium aux perturbations acoustiques est contrôlée par l’écoulement local autour de la goutte, (ii) le processus de combustion peut être supposé quasi stationnaire pour la gamme de fréquences et les amplitudes acoustiques étudiées et (iii) la combustion de l’aluminium est brusquement arrêtée lorsque le diamètre de la goutte d’aluminium diminue en dessous d’un diamètre résiduel.L’instabilité thermoacoustique est étudiée au moyen de simulations numériques de l’écoulement dans un moteur générique et d’analyses théoriques. Le diamètre résiduel des gouttes d’aluminium après la combustion, l’amplitude de la perturbation acoustique et la durée de la combustion des gouttes d’aluminium figurent parmi les principaux paramètres modifiant l’instabilité. En outre, trois comportements de réponse de la combustion à l’acoustique sont identifiés : un comportement linéaire pour les faibles niveaux de pression acoustique puis un comportement quadratique (faiblement non-linéaire) et enfin un comportement fortement non-linéaire quand l’amplitude des oscillations augmente.Ensuite, deux aspects importants de la réponse des gouttes d’aluminium sont identifiés. Ils sont associés aux oscillations de la durée du temps de combustion des gouttes, identifiables à la frontière du nuage de gouttes, et aux fluctuations du taux d’évaporation contrôlées par la convection de l’écoulement gazeux autour de chaque goutte. Tenant compte de ces dynamiques,des expressions analytiques sont obtenues permettant de reproduire avec précision les résultats numériques des simulations de l’écoulement. Quatre nombres sans dimension qui régissent la dynamique de ces instabilités sont également identifiés. Inspiré de l’analyse théorique précédente, un modèle numérique d’ordre réduit faiblement non linéaire est finalement développé pour prédire des cycles limites. / In a solid rocket motor, self-sustained thermo-acoustic instabilities, induced by the coupling of the combustion dynamics of aluminum droplets released by the burning propellant with the acoustic field can induce pressure oscillations.The analysis conducted throughout this manuscript relies thus on a set of simplifying hypothesis by assuming (i) that the response of the combustion of aluminum droplets to acoustic perturbations is controlled by the oscillating drag exerted by the local flow around the droplet, (ii) that this unsteady combustion process can be assumed quasi-steady for the range of frequencies and acoustic amplitudes studied and (iii) that aluminum combustion is abruptly quenched when the aluminum droplet diameter falls below a residual diameter.The thermo-acoustic instability is studied first by numerical flow simulations in a generic solid rocket motor and theoretical analyses. The post-combustion residual diameter of the aluminum particles, the amplitude of acoustic perturbation and the lifetime of the burning aluminum droplets are among the main parameters altering the instability. Also, three combustion response behaviors to acoustics are identified : a linear behavior for small acoustic pressure levels followed by a quadratic behavior then a highly non-linear behavior when the pressure amplitude increases in the motor chamber. Moreover, two important features of the response of aluminum droplets are identified. They are associated to oscillations of the droplet lifetime at the boundary of the droplet cloud and to fluctuations of the droplet evaporation rate, controlled by convection. The dynamics of the droplets highly depends on gas and droplet velocity fields and on droplet diameter. Taking these features into account, yields analytical expressions that allow to reproduce with accuracy the numerical results from the flow simulations. Four dimension less numbers are then identified. They govern the dynamics of these instabilities. Inspired from the previous theoretical analysis, a weakly nonlinear low-order numerical model is finally developed to predict limit cycles.

Chronic Kidney Disease (CKD) is a common and dangerous health condition that requires early detection and treatment to be effective. Current diagnostic methods are time-consuming and expensive. In this research, we hope to construct a predictive model for CKD utilizing a combination of time series and static variables for early detection of CKD. In this study, we investigate the influence of multimodal approach by combining the predictions from multiple models that utilize different modalities. The ROCKET method is utilized for classification using time series features, whilst the Random Forest approach is employed for static data. XGBoost has been utilized to gain information about feature importance among labs and demographics-comorbidities data. In this study, we use the MIMIC-III database, adopting various strategies to handle data and class imbalance, such as stratification, balancing techniques, and backwards and forward fill for missing value imputation. The evaluation metrics for CKD and non-CKD class labels include precision, recall, F1, and accuracy. Our findings show that aggregating time series data produce contrasting results for labs compared to vitals data. We also addressed the significance of the different demographic, comorbidities and lab events features. The findings indicate that a multimodal approach did not show significant advantages over individual models when the individual models performed suboptimal. The study also found that Ethnicity is more significant than age and gender in predicting CKD. Furthermore, the study revealed some significant features from lab events and comorbidities. The study also provides some recommendations for future work to explore the potential of a multimodal approach further.

No description available.