Le crissement de frein est une nuisance sonore classique dans l’automobile. L’augmentationdes coefficients de friction et la réduction de la masse mènent aujourd’hui à de hauts niveauxvibratoires dans les fréquences auditives, et ces problèmes de qualité se traduisent par des pénalités économiques aux équipementiers, bien qu’il n’existe pas de méthode robuste de conception.La pratique industrielle repose donc sur de coûteuses phases de prototypage et d’ajustement.L’évolution de la puissance de calcul permet le calcul de grands assemblages mécaniques mais lesétudes vibratoires non-linéaires restent généralement hors de portée. Dans ce contexte, l’objectifde la thèse est de fournir, dès les phases de conception, des outils de conception numérique d’aideà la résolution du crissement.Une méthode de réduction paramétrée utilisant comme base de Rayleigh-Ritz les modes réelsdu système assemblé permet la génération de modèles réduits très compacts, avec modes réelsexacts. La méthode proposée d’ajustement des modes de composants utilise les modes libresde composants comme degrés de liberté explicites. L’étude des sensibilités et la réanalyse d’unassemblage en fonction de modifications à l’échelle d’un composant deviennent possibles. Lesétudes temporelles non-linéaires sont rendues possibles par deux développements. Un schémade Newmark non-linéaire modifié et un Jacobien fixe adapté aux vibrations de contact sontintroduits. Le frein est réduit en un superélément avec modes réels exacts et une zone nonréduite au niveau du contact.Un ensemble d’outils de conception est illustré sur un modèle industriel de frein. La stabilitéinstantanée et les trajectoires de modes complexes sont étudiées. Les interactions modales et lesphénomènes non-linéaires au sein des cycles limites sont alors mieux compris. Des corrélationstemps/fréquence sont obtenues par l’identification modale instantanée et une décompositionespace-temps. La grande utilité d’un modèle temporel d’amortissement modal est illustrée.Enfin, la modification d’un composant critique au crissement est testée et validée. / Brake squeal is a common noise problem encountered in the automotive industry. Higherfriction coefficients and weight reduction recently led to higher vibration levels in the audiblefrequency range. This quality issue becomes economic due to penalties imposed to the brakesupplier although no robust design method exists. The industrial practice thus relies on costlyprototyping and adjustment phases. The evolution of computational power allows computationof large mechanical assemblies, but non-linear time simulations generally remain out of reach.In this context, the thesis objective is to provide numerical tools for squeal resolution at earlydesign stages.Parameterized reduction methods are developed, using system real modes as Rayleigh-Ritzvectors, and allow very compact reduced models with exact real modes. The proposed ComponentMode Tuning method uses the components free/free modes as explicit degrees of freedom.This allows very quick sensitivity computation and reanalyzes of an assembly as function oflocal component-wise parameters. Non-linear time simulations are made possible through twoingredients. A modified non-linear implicit Newmark scheme and a fixed Jacobian are adaptedfor contact vibrations. The brake is reduced keeping a superelement with exact real modes anda local non-linear finite element model in the vicinity of the pad/disc interaction.A set of design tools is illustrated for a full industrial brake model. First, instant stabilitycomputations and complex mode trajectories are studied. Modal interactions and non-linearphenomena inside the limit cycles are thus well understood. Time/frequency correlations areperformed using transient modal identification and space-time decomposition. A time domainmodal damping model is also shown to be very useful. The modification of a critical componentfor squeal resolution is finally tested and validated.

Les disques aubagés, que l’on trouve dans les turbomachines, sont des structures complexes dont le comportement vibratoire est généralement déterminé par l’exploitation de conditions de symétrie dans leur configuration nominale. Cette symétrie disparaît lorsque l’on assemble plusieurs de ces disques pour former un rotor ou que l’on introduit une variabilité spatiale des paramètres mécaniques (on parle de désaccordage intentionnel ou non). Le raffinement des maillages, nécessaire à une évaluation correcte de la répartition des contraintes, conduirait à des modèles de rotor complet de taille prohibitive (plusieurs dizaines de millions de degrés de liberté). L’objectif de cette thèse est donc l’introduction de méthodologies de réduction qui par combinaison de calculs acceptables permettent d’étudier de façon fine la dynamique d’ensemble sur des modèles 3D fins multi-étages et potentiellement désaccordés. L’étude des transformations de Fourier séparées des réponses de chaque étage permet, dans un premier temps, de bien comprendre les effets de couplage inter-harmonique liés au couplage inter-disque et au désaccordage. A partir de ce constat, une première méthode utilise les résultats de calculs en symétrie cyclique et à secteur encastré pour construire un modèle de secteur exact pour certains modes dits cibles et de très bonne qualité pour les autres modes. Cette méthode est ensuite étendue au cas multi-étage en construisant des bases de réduction de secteur par combinaison de solutions mono-harmoniques. Les illustrations montrent que la méthodologie proposée permet le traitement de modèles de très grande taille, tout en restant compatible avec une grande richesse de post-traitements (calculs de modes, calculs de réponses forcées, analyses de leur contenu harmonique spatial, répartition d’énergie et effets de localisation...). La méthodologie est enfin étendue à la gestion de modèles paramétrés en vitesse de rotation. L’enrichissement des ensembles de modes cibles par des calculs à trois vitesses permet ainsi une reconstruction rapide de l’évolution des fréquences pour l’ensemble d’un intervalle. / Bladed disks found in turbomachines are complex structures whose vibration characteristics are generally determined by exploiting the symmetry properties of their nominal configuration. This symmetry no longer exists either when disks are assembled to form a rotor or when discrepancies in the mechanical parameters are introduced (intentional or unintentional mistuning). Fine meshes required to correctly evaluate stress distributions would lead to prohibitive model sizes (typically a few million degrees of freedom). The objective of this thesis is to introduce model reduction techniques that rely on the combination of separate computations of acceptable size. This provides a means for in-depth studies of the behaviour of dense 3D models of multi-stage bladed rotors with possible mistuning. At first, Fourier transforms performed separately on each individual disk allows to understand the inter-harmonic coupling induced by inter-stage coupling and mistuning. From this study, a first method uses cyclically symmetric solutions plus sector modes with fixed inter-sector interfaces to build a reduced sector model. The latter is exact for target modes and very accurate for others. This method is extended to multi-stage assemblies by employing multi-stage mono-harmonic eigensolutions. Illustrations focus on the proposed methodology that enables to deal with large scale industrial models while remaining compatible with various post-processing procedures (free or forced response computations, analysis of their spatial harmonic content, energy distributions and localization effects...). This methodology is finally extended to the handling of parametric models depending on the rotation speed. The enrichment of the initial sets of target vectors with computations at three rotation speeds enables a fast and accurate recovery of the evolution of the eigenfrequencies with respect to the rotation speed in any operating range.

Orientador: Robson Pederiva / Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecânica / Made available in DSpace on 2018-08-16T12:10:10Z (GMT). No. of bitstreams: 1 Gevinski_JakersonRicardo_M.pdf: 6622293 bytes, checksum: aec7a88489a7f8e66c0dd6e0bdc0ed0e (MD5) Previous issue date: 2010 / Resumo: O interesse de maior produtividade e baixos custos de manutenção, associados ao desenvolvimento de produtos mais otimizados fizeram aumentar a preocupação com as falhas por fadiga em equipamentos. Neste contexto, o monitoramento da tensão dinâmica em estruturas e máquinas sujeitas à vibração adquire cada vez mais importância. Com este intuito, diversos métodos para a estimativa de tensões e deformações dinâmicas que utilizam parâmetros vibracionais vêm sendo desenvolvidos. Por estes métodos, basicamente, estima-se a deformação dinâmica pela derivação espacial do deslocamento obtido pelas técnicas de análise modal. Neste trabalho, abordam-se os conceitos da teoria da elasticidade e da análise modal para a melhor compreensão dos métodos propostos na identificação de deformação a partir dos parâmetros modais. Estudam-se os conceitos da análise modal híbrida para prever o deslocamento de pontos da estrutura e os conceitos da matriz de transformação deslocamento - deformação. Com o objetivo de avaliar esses métodos, realizam-se simulações numéricas e um experimento. Este se constitui no estudo de uma viga de alumínio, onde determinam-se as deformações de flexão da mesma, a partir das acelerações medidas e utilizando o método de diferenças finitas. As simulações e experimentos apresentaram resultados relevantes e satisfatórios no campo da determinação da tensão e deformação dinâmicas em superfícies. / Abstract: The interest of greater productivity and low costs of maintenance, combined with the development of more optimized products, have raised concern about prevention of fatigue failure of equipments. In this context, the monitoring of the dynamic stress in structures and machines under vibration has become more important. With this purpose, several methods of estimation of dynamic stress and strain using vibrational parameters have been developed. Basically, results from modal analysis are transformed from the displacement space to the strain space by use spatial differential operator. The work addresses the concepts of the theory of elasticity and modal analysis for a better understanding of the proposed methods for the identification of strain from modal parameters. It studies the concepts of hybrid modal analysis to predict the displacement of structures' points and concepts of the transformation matrix displacement to strain. In order to evaluate these methods, numerical simulations and an experiment are realized. This constitutes the study of an aluminum beam which determines the bending strain from measured accelerations and using the finite difference schemes. The simulations and experiments showed satisfactory and relevant results in the field of determination of dynamic stresses and strains on surfaces. / Mestrado / Mecanica dos Sólidos e Projeto Mecanico / Mestre em Engenharia Mecânica

A determinação de características dinâmicas de estruturas aeronáuticas é um assunto extremamente importante na indústria aeroespacial, principalmente devido à demanda contínua para estruturas mais leves e conseqüentemente mais flexíveis. Neste contexto, estruturas aeroespaciais precisam ser submetidas a alguma forma de verificação modal antes do vôo, para assegurar que a aeronave é livre de fenômenos aeroelásticos indesejáveis. Esta análise freqüentemente inclui a identificação experimental de características dinâmicas como freqüência natural, fatores de amortecimento e forma dos modos usando ensaio modal. Neste trabalho foi realizado um ensaio de vibração no solo em uma asa metálica da aeronave Neiva Regente para obtenção das funções resposta em freqüência da estrutura. O método de identificação utilizado para este estudo é o Algoritmo de Realização de Sistemas – ERA. É um método de identificação considerado eficiente e poderoso, pois é capaz de identificar estruturas que apresentem comportamento dinâmico complexo. O algoritmo foi validado através de uma simulação de um modelo hipotético e de dados experimentais de uma viga de alumínio. Os resultados experimentais, porém, apresentam modos computacionais que devem ser eliminados. Para tanto foram utilizados três índices de confiança para qualificar os resultados, sendo estes: Colinearidade de Fase Modal Ponderada (MPCW), Coerência da Amplitude Modal Estendida (EMAC) e Indicador de Consistência Modal (CMI). Os modos que apresentaram melhores índices de confiança são considerados o resultado final do processo de identificação. Desta forma, o processo de identificação foi aplicado para a semi-asa da aeronave Neiva Regente. A identificação revelou-se mais difícil, basicamente devido à complexidade da estrutura somado-se a problemas de ruído, o que levou a um número pequeno de modos identificados / The determination of the dynamic characteristics of aircraft structures has become an extremely important issue in the aerospace industry, primarily due to the continuous demand for lighter and consequently more flexible structures. In this context, most aerospace structural system must be subjected to some form of modal verification prior to flight in order to ensure that the aircraft is free from any dangerous aeroelastic instability phenomena. The verification procedure often includes the experimental identification of structural characteristics such as the natural frequency, damping factors and normal modes using modal testing. In this work, a ground vibration testing (GVT) of a metallic wing of the Neiva Regente aircraft was accomplished in order to assess the frequency response functions. The basic identification method used for this study is the Eigensystem Realization Algorithm – ERA. It is an identification method, which is considered efficient and powerful, because it is capable to identify structures that present complex dynamic behaviour. The algorithm was valited through data obtained from a simulation of a hypothetical model and dynamic measurement accomplished in an aluminium beam. The experimental results, nevertheless, present computacional modes that must be removed from the model. Three confidence factors were used to qualify the results, namely the Modal Phase Collinearity – Weighted (MPCW), Extended Modal Amplitude Coherence (EMAC) and Consistent-Mode Indicator (CMI). The modes that presented higher confidence factor values were considered as the final result of the identification process. Then, the identificatin process was applied to a semi-wing of the Neiva Regente aircraft. This case has revealed a much harder identification procedure, where the complexity of the structure plus noisy data have led to a small number of identified modes

Orientador: Robson Pederiva / Tese (doutorado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecânica / Made available in DSpace on 2018-08-24T06:27:59Z (GMT). No. of bitstreams: 1 Gevinski_JakersonRicardo_D.pdf: 12693026 bytes, checksum: fe16190815edb5eee4a73ed3a84fa51d (MD5) Previous issue date: 2014 / Resumo: Máquinas e equipamentos em condições operacionais estão susceptíveis à vibração e, consequentemente, deformações e tensões. Deformações em níveis excessivos podem ocasionar falhas por fadiga, muitas vezes catastróficas. Desta forma, o monitoramento e a caracterização da distribuição da deformação dinâmica em estruturas se tornam muito importantes. Em vista da determinação da deformação dinâmica, métodos de estimação de deformação que utilizam parâmetros vibracionais foram desenvolvidos. Por estes métodos, basicamente, estima-se a deformação dinâmica a partir da informação do deslocamento, não havendo, principalmente, a necessidade da colagem de extensômetros sobre a estrutura. Nesta tese, os métodos de estimação de deformação são aplicados utilizando funções respostas em frequência e de transmissibilidade. Os métodos de estimação da deformação são avaliados a partir de simulações numéricas e experimentos. A simulação numérica é realizada em uma viga engastada, e utilizam-se os métodos da matriz de transformação, análise modal híbrida e o método direto, baseado na análise da curvatura da viga. As avaliações experimentais são realizadas em placas de alumínio com diferentes geometrias e condições de contorno. O tensor de deformação e a distribuição da deformação dinâmica são determinados utilizando sinais de aceleração medidos em diferentes pontos da superfície das placas e os métodos de estimação. Os modos de deslocamento e de deformação, necessários para aplicação dos métodos, são obtidos por elementos finitos em ANSYS®. Na transformação deslocamento-deformação, são utilizados os métodos de diferenças finitas e de elementos finitos. Os tensores de deformação estimados são comparados com os tensores de deformação medidos por meio de extensômetros. Os modos operacionais de deformação estimados foram comparados com modos simulados. As simulações e experimentos apresentam resultados relevantes e satisfatórios no campo da determinação da deformação dinâmica / Abstract: Machinery and equipment, under operating conditions, are susceptible to vibration and hence the levels of dynamic stress and strains. The consequence of excessive vibration can be catastrophic since, high levels of stress and strain, occurring in a certain period of time can cause fatigue failures. Thus, monitoring and characterization of the dynamic strain distribution in mechanical structures becomes increasingly important. In view of the dynamic strain determination, some methods have been developed to predict the dynamic strain from vibration measurements. These methods basically consist in the numerical differentiation of displacement and, in especially, to predict the strain without the use of strain gages. In this thesis, the strain predicting methods are applied using both functions frequency responses and transmissibility. The strain predicting methods are evaluated through numerical simulations and experiments. The numerical simulation is performed on a cantilever beam, and the hybrid modal analysis, transformation matrix and the direct method, based on the analysis of the curvature of the beam matrix, are used. The experimental evaluations are performed on aluminum plates with different geometries and boundary conditions. The dynamic strain tensor and the distribution of operating strain are determined using acceleration, measured at different points on the surface of the plates, and the strain predicting methods. The strain and displacement modes, required for application of the methods, are obtained by finite element in ANSYS ®. In the displacement - strain transformation, both the finite difference methods and finite elements methods are used. The predicted strain tensors are compared with the strain measured using strain gauges. The predicted operating modes were compared with simulated strain modes. Simulations and experiments show significant and satisfactory results in the field of determining the dynamic strain / Doutorado / Mecanica dos Sólidos e Projeto Mecanico / Doutor em Engenharia Mecânica

Direct measurements of external forces acting on a structure are infeasible in many cases. The Augmented Kalman Filter (AKF) has several attractive features that can be utilized to solve the inverse problem of identifying applied forces, as it requires the dynamic model and the measured responses of structure at only a few locations. But, the AKF intrinsically suffers from numerical instabilities when accelerations, which are the most common response measurements in structural dynamics, are the only measured responses. Although displacement measurements can be used to overcome the instability issue, the absolute displacement measurements are challenging and expensive for full-scale dynamic structures. In this paper, a reliable model-based data fusion approach to reconstruct dynamic forces applied to structures using heterogeneous structural measurements (i.e., strains and accelerations) in combination with AKF is investigated. The way of incorporating multi-sensor measurements in the AKF is formulated. Then the formulation is implemented and validated through numerical examples considering possible uncertainties in numerical modeling and sensor measurement. A planar truss example was chosen to clearly explain the formulation, while the method and formulation are applicable to other structures as well.

In this work, a pioneering application of the Solution Structure Method (SSM) for structural dynamics problems is presented. Vibration analysis is an important aspect of any design-analysis cycle for which reliable computational methods are required. Unlike many meshfree methods, SSM is capable of {\it exact treatment of all prescribed boundary conditions}. In addition, the method is capable of using basis functions which do not conform to the shape of the geometric model. Together, this defines an unprecedented geometric flexibility of the SSM. This work focused on the development of numerical algorithms for 2D in-plane and 3D natural vibration analysis and 2D in-plane dynamic response. The convergence and numerical properties of the method were evaluated by comparing meshfree results with those obtained using traditional Finite Element Analysis implemented in Solidworks and ANSYS. The numerical experiments presented in this work illustrate that the Solution Structure Method possesses good convergence and in some cases, such as geometries with partially fixed boundaries, this method converges much more rapidly than traditional FEA. Finally, in addition to complex boundary conditions, this method can easily handle complex geometries without losing favorable convergence properties.

Orientador: José Maria Campos dos Santos / Dissertação (mestrado) - Universidade Estadual de Campinas, Faculdade de Engenharia Mecânica / Made available in DSpace on 2018-08-28T14:26:32Z (GMT). No. of bitstreams: 1 Nascimento_FabioFialhodo_M.pdf: 3796792 bytes, checksum: 3a40db657ae4ddf5e1331783c582bd04 (MD5) Previous issue date: 2015 / Resumo: Este trabalho tem como objetivo geral investigar abordagens para a análise de incerteza em problemas de dinâmica estrutural, de forma computacionalmente eficiente, no contexto industrial. Neste sentido, utilizou-se um metamodelo, baseado no método da superfície de resposta, para simplificar a etapa do cálculo dos modos e das frequências naturais na análise de resposta em frequência da estrutura. Para viabilizar a análise de grandes modelos, a solução de elementos finitos foi realizada pelo Nastran®. O MatLab® foi utilizado para manipular os autovalores e autovetores, e calcular as FRFs. Já o processo de amostragem das variáveis, a preparação da superfície de resposta e a integração com os demais aplicativos, foram realizados por meio do Isight®. Inicialmente, a abordagem foi avaliada em um modelo simples de um para-brisa veicular, com espessura, modo de elasticidade e densidade como parâmetros incertos. Posteriormente, o método foi aplicado para um modelo de uma estrutura veicular com milhares graus de liberdade. Neste caso, as variáveis aleatórias consideradas foram espessuras de vinte peças estampadas. Todas as variáveis foram consideradas com distribuição normal. Para quantificar a incerteza na resposta dinâmica, a simulação por Monte Carlo foi conduzida em conjunto com o metamodelo. A variabilidade das frequências naturais e da FRF é comparada com o resultado do Monte Carlo direto / Abstract: This work has as general objective to investigate approaches for uncertainty analysis in structural dynamics problems in a computational efficient manner in an industrial context. In this sense, we used a metamodel based on the response surface method to simplify the process of modes and natural frequencies calculation for frequency response analysis of a structure. In order to make the process feasible for large models, the finite element solution was performed using Nastran®. MatLab® was used to manipulate the eigenvalues and eigenvectors and calculate the FRFs. Isight® was responsible for the variable sampling process, response surface preparation and integrating other applications as well. Initially, the approach was assessed in a simple model of a car windshield with its thickness, Young¿s modulus and material density as uncertain parameters. Later the method was applied to a vehicle structure model with thousands degrees of freedom. In this case, the random variables considered were thicknesses of twenty stamped parts. Gaussian distribution was considered for all variables. For the purpose of uncertainty quantification in the dynamic response, Monte Carlo simulation was performed over the metamodel. The variability of the natural frequencies and FRF is compared against to direct Monte Carlo results / Mestrado / Mecanica dos Sólidos e Projeto Mecanico / Mestre em Engenharia Mecânica

The workin this thesis deals with the development of anaeroelastic simulation tool for horizontal axis wind turbineapplications. Horizontal axiswind turbines can experience significanttime varying aerodynamic loads, potentially causing adverseeffects on structures, mechanical components, and powerproduction. The need of computational and experimentalprocedures for investigating aeroelastic stability and dynamicresponse have increased as wind turbines become lighter andmore flexible. A finite element model for simulation of the dynamicresponse of horizontal axis wind turbines has been developed.The simulations are performed using the commercial finiteelement software SOLVIA, which is a program developed forgeneral analyses, linear as well as non-linear, static as wellas dynamic. The aerodynamic model, used to transform the windflow field to loads on the blades, is a Blade- Element/Momentummodel. The aerodynamic code is developed by FFA (TheAeronautical Research Institute of Sweden) and is astate-of-the-art code incorporating a number of extensions tothe Blade-Element/Momentum formulation. SOSIS-W, developed byTeknikgruppen AB was used to develop wind time series formodelling different wind conditions. The model is rather general, and different configurations ofthe structural model and various type of wind conditions couldeasily be simulated. The model is primarily intended for use asa research tool when influences of specific dynamic effects areinvestigated. Simulation results for the three-bladed wind turbine Danwin180 kW are presented as a verification example. <b>Keywords:</b>aeroelastic modelling, rotor aerodynamics,structural dynamics, wind turbine, AERFORCE, SOSIS-W,SOLVIA / NR 20140805

In this thesis we have investigated different numerical filters for joint input and state estimation, with the aim of designing a robust algorithm capable of monitoring the continuous motion and loading in a truck chassis. The algorithm has to be able to use sparse measurements of the motion on different parts of the truck as it is excited by road induced vibrations, and transform this data into knowledge of the state in the entire system. To do this, the algorithm has to be supplied with information about the dynamic properties of the current system. In Paper A we have developed and implemented a fixed-lag smoother for joint input and state estimation in linear time-invariant dynamic structures. A fixed-lag smoother maximizes the use of information available in the measurements by allowing a small time lag in the estimation. As input, external forces as well as support motions can be computed. Furthermore, both measurement noise and model errors are accounted for and simulated as stochastic processes. The filter is firstly verified with straightforward numerical simulations of a simply supported beam, followed by a more involved simulation of a truck fuel tank. It is shown that the fixed-lag smoother performs very well, it estimates both input and states with a high accuracy even though the signals are contaminated with noise and the model contains errors. In Paper B the fixed-lag smoother is applied on real measurements. We investigate the capabilities of the proposed filter by analysing acceleration measurements from a truck side skirt excited by road induced vibrations. In this study, we focus on estimating the state in the side skirt body from a minimum number of measurement sensors. The dynamic properties of the side skirt are obtained experimentally from an operational modal analysis. It is shown that the fixed-lag smoother estimates the state very well. The results also shows that the smoothing effect is larger when fewer measurement sensors are used. / <p>QC 20160928</p>