Este trabalho é uma contribuição à análise progressiva de falhas em materiais compósitos poliméricos. Esses materiais combinam as propriedades de seus constituintes (fibra, resina polimérica e interface) de forma a melhorar o desempenho frente à utilização das fases isoladamente. A combinação de fases permite obter características como baixa densidade e elevada rigidez, que são almejadas pelo segmento aeronáutico, pois podem proporcionar um aumento de autonomia ou da capacidade de carga das aeronaves. A anisotropia inerente aos compósitos torna possível projetá-los de forma a obter-se a rigidez e a resistência desejada. Por outro lado, a anisotropia dificulta a previsão precisa dos mecanismos de falha, e conseqüentemente, do comportamento global da estrutura. Apresenta-se, assim, com base numa revisão bibliográfica criteriosa, bem como, através de resultados experimentais, a avaliação de um modelo de material fenomenológico, onde se identificam modos de falhas intralaminares. Uma vez verificad a falha por algum critério, degradam-se as propriedades do material. O modelo de material foi implementado junto ao pacote de elementos finitos Abaqus através de uma sub-rotina UMAT (\"User Material\"), escrita em Fortran. Em seguida, estudou-se o problema de um laminado em duas configurações de empilhamento (\'[0º] IND.10\' e \'[0º/90º/0º/90º/0º] IND.S\') sob flexão 3-pontos. Os resultados das simulações foram comparados com resultados experimentais, observando erros da ordem de 10%. Sendo que estes foram obtidos em função de um estudo dos parâmetros associados a solução do problema não-linear, tais como: tamanho de incremento de iteração e parâmetros associados à lei de degradação de material. Por fim, concluiu-se que o modelo de material avaliado é adequado para previsão da falha da primeira camada, bem como, da redução da rigidez estrutural e da resistência residual. Sendo que, a resposta teórica obtida se manteve parcialmente dentro dos limites inferior e superior do envelope experimental. / This work is a contribution to the progressive failure analysis in polymer composite materials. These materials combine the properties of its constituents (fiber, resin and interface) in order to improve the performance against the use of phases alone. The combination of the phases can provide characteristics such as low density and high strength, which are desired in the aeronautical segment, because it can increase the autonomy or aircraft payload. The anisotropy inherent in composites turns possible to design the material for a desired stiffness and strength. Furthermore, it turns difficult the prediction of failure mechanisms, and consequently, the overall behavior of the structure. This study presents, based on a review and experimental results, the evaluation of a phenomenological material model, which identify intralaminar failure modes. Once verified the failure by any criterion, the material properties are reduced by a degradation law. The material model was implemented in a UMAT (User Material) subroutine which linked to the finite element package Abaqus. It was applied in the study of 3-point bending problem for two stacking sequences (\'[0º] IND.10\' e \'[0º/90º/0º/90º/0º] IND.S\'). The results were compared with experimental tests, presenting a error in the order of 10%. Since that these where obtained by a study of the parameters associated to the solution of the nonlinear problem, such as: time step, and parameters associated to the material degradation laws. Finally, it was concluded that the material model is judged suitable for predicting the failure of the first ply, the reduction of structural stiffness and the residual strength. Besides, a part of the theoretical response obtained is maintained within the lower and upper limits of the experimental tests envelope.

Recentes melhorias nos processos de fabricação e nas propriedades dos materiais associadas a excelentes características mecânicas e baixo peso tornaram os materiais compósitos muito atrativos para aplicação em estruturas aeronáuticas. No entanto, mesmo novos projetos ainda são muito conservadores, pois os fenômenos de falha dos compósitos são muito complexos. Então, é estratégico entender melhor, bem como prever esses complexos mecanismos de falha, desenvolvendo modelos de materiais mais precisos que venham a diminuir o número de ensaios experimentais, gerando rapidez e economia aos projetos estruturais. Assim, este trabalho apresenta o desenvolvimento de um modelo de material baseado na Mecânica do Dano Contínuo para simular a falha progressiva de estruturas laminadas de carbono/epóxi quando submetidas a carregamentos quase estáticos e de impacto. Várias análises numéricas foram realizadas via elementos finitos, a fim de prever a falha dessas estruturas de material compósito sob essas solicitações. O modelo de dano proposto foi implementado como sub-rotinas em linguagem FORTRAN (UMAT-User Material Subroutine e, VUMAT-User Material Subroutine para simulações explícitas), que foram compiladas junto ao programa comercial de Elementos Finitos ABAQUSTM. Além disso, ensaios experimentais foram realizados, a fim de calibrar parâmetros relacionados ao modelo de material, bem como avaliar as potencialidades e as limitações do modelo de material proposto. / Recent improvements in manufacturing processes and material properties associated to excellent mechanical characteristics and low weight have become composite materials very attractive for application on civil aircraft structures. However, even new designs are still very conservative, because the composite structure failure phenomena are very complex. So, it is strategic to known better and to predict these complex failure mechanisms, developing more accuracy material models, which reduce the number of experimental tests, inducing a fast and economic structural design. Thus, this work show the development of a material model based on Continuum Damage Mechanics to simulate the progressive failure of carbon/epoxy laminate structures under quasi-static and impact loadings. Several numerical analyses were performed via Finite Element Method in order to predict the damage on composite structures under these conditions. The proposed damage model was implemented as a UMAT (User Material Subroutine) and VUMAT (User Material Subroutine for explicit simulations), which were linked to ABAQUSTM. Moreover, experiments were carried out in order to calibrate the material model parameters and to evaluate the potentialities and limitation of the proposed material model, as well.

Neste trabalho buscou-se propor e implementar um modelo de material capaz de prever o comportamento mecânico de estruturas em compósitos poliméricos reforçados (CPR). Inicialmente fez-se um levantamento bibliográfico sobre os modos de danificação intralaminar e falhas interlaminares bem como sobre formas de abordagem (analítica e numérica) para tratar esses problemas. Em seguida, foram apresentadas em detalhes as etapas experimentais executadas, descrevendo todo o procedimento de fabricação dos corpos-de-prova e os resultados obtidos a partir dos ensaios quase-estáticos de tração, compressão, cisalhamento e flexão. Com base nesses resultados e em informações provenientes da literatura, propõem-se alguns modelos de material que foram implementados em sub-rotinas FORTRAN. Tais modelos são posteriormente compilados em conjunto com um programa de elementos finitos (ABAQUS®) a fim de serem avaliados e terem seus parâmetros calibrados. Numa primeira fase, através de simulações computacionais dos ensaios de tração e compressão avaliou-se os modelos de material implementados. Numa segunda fase, os parâmetros foram calibrados tomando como base três estudos de caso (flexão, endentação e teste de impacto) envolvendo seqüências de empilhamento distintas. Após a simulação computacional desses estudos, apresentou-se a proposta de uma metodologia para avaliar problemas de impacto a baixa velocidade em estruturas laminadas. Conclui-se assim que o presente projeto de pesquisa traz contribuições inovadoras, mas também apresenta várias perspectivas de trabalhos futuros. / In this work, material models were proposed to predict the mechanical behavior of composite structures. First of all, it was done a study about damage intra-ply and inter-ply (delamination) on composite materials and about analytical and numerical approaches to solve problems of progressive damage on composite structures was performed. After, many specimens were manufactured and experimental tests (tensile, compression, shear and flexural tests) were carried out. Experimental results and information from literature were used to develop some material models, which were implemented using FORTRAN compiler. These material models were compiled with a commercial finite element program (ABAQUS®) in order to evaluate and calibrate parameters of the models. In the first step, computational simulations of tensile and compression test were carried out to evaluate material models implemented. In the second step, the parameters of the material models were calibrated using three case studies (flexural, indentation and impact test) with some staking sequences. After that, a methodology was proposed to evaluate impact problems on composite structures under low velocity. Therefore, this research project not only shows new contributions but also suggests many future investigations.

The course of polymer film functioning has been a crucial concern in the advent of packaging technology. The thesis project aims towards obtaining an understanding of mechanical properties for a class of these materials, namely LDPE and PET. A constitutive understanding of this behavior in the case of LDPE is acquired through incorporating a plastic stress strain relationship in an iterative approach with focus put on the sensitivity of a few parameters by following a simple linear curve-fit technique in a way that the global as well as the local response are predictable. FE-models also developed in this way are validated with experimental data. An inverse analysis testing validity or usefulness of DIC technique in identifying a material model is done and some discussions are drawn towards this area. A relative numerical study with respect to experimentally obtained global response for tearing of these polymers is done through use of a similar material model developed from tensile tests and the challenges faced in this area have been addressed.

The advancement in manufacturing technologies to produce high-performing engineered wood products (EWP) has allowed wood to be utilized beyond the traditional low-rise light-frame structures and to become a viable material option for much larger structures. Although glued-laminated timber (glulam) is included as a material option in the current blast code (CSA, 2012), its response to blast loading is not yet well documented. An experimental program investigating the behaviour of seventy glulam beams and columns was developed with focus on establishing the dynamic characteristics of glulam beams and columns with and without the effect of FRP reinforcement. A shock tube capable of simulating high strain rates similar to those experienced during blast was used. Thirty-eight beams with three different cross-sections were tested statically and dynamically to establish the high strain rate effects (dynamic increase factor). Six columns were also tested dynamically with axial load levels ranging from 15 to 75 % of the columns’ compression design capacity. Different retrofit configurations varying from simple tension reinforcement to U-shaped tension reinforcement with confinement using both unidirectional and bi-directional FRP were investigated on a total of twenty-six beams. A procedure capturing the strain-rate effects, variable axial load and FRP, was developed and found to be capable of predicting the flexural behaviour of the beams up to maximum resistance with reasonable accuracy when compared to experimentally obtained static and dynamic resistance curves. Implications on the design of both retrofitted and unretrofitted specimens are also discussed.

Submitted diploma thesis deals about operational deformations in the cylinder unit of turbocharged diesel engine used in commercial vehicles. Introductory part analyses combustion engines computational modelling based on finite element method. The next step is the creation of computational models for thermal-structural analyses of the piston and engine block. In order to determine material characteristics of the head gasket, experiment is performed on the OEM gasket to determine its real behaviour under compressive load. The results shows strong nonlinear behaviour which justifies the decision of making such an experiment in the first place. The results of computational models are radial deformations of the piston and cylinder liners during load conditions. The last chapter deals with the application of these results to an advanced computational piston assembly dynamics model.

Master thesis is based on a doctor thesis dealing with the behavior of reinforced concrete elements stressed shear by the author Ing. Stanislav Martinec, Ph.D. Author master thesis has the task create a spatial finally element model loading testing construction and researched the wall element. Defined finally elements model is mainly to provide proper interaction test device steel frame with the test wall element. Need for sufficiently detailed numerical analysis is necessary to define the non-linear concrete material model, that is researched element, using the extensions multiPlas for calculation software Ansys. The key output parameters, for comparison with the results of load tests, are total bevel and maximum level of applied force on the wall element. The goal is assess the effect of a steel frame, contained in finally element model, to output parameters for by non-linear numerical analysis.

Create FEM computational model additionally tensioned bridges for pedestrians and cyclists using ANSYS. Perform nonlinear analysis, design and make a comparison with standard values.

This master thesis focuses on a scaled fuselage design made from composite material. The first part deals with a description of composite materials and used material models in an explicit FEM simulation. Two types of scaled structures were designed that were subjected to drop test. Test results were compared with FEM simulation. Finally the calibration of models was carried out.

This dissertation thesis deals with the improvement of computational approaches for prediction of residual stresses in welded joints of welded structures in order to ensure greater compliance of the calculated results with the real conditions of welding and heat treatment. The improvement of computational approaches is based on application of elastic-viscoplastic material models which are able (compared with elastic-plastic material models) to take into account the viscoplastic processes ongoing during welding and heat treatment. This leads to more accurate calculated results which enter into further assessment of limit states and directly decide on the safety and lifetime of welded structures. Performed computational and experimental works, confronted with results published in the world, confirm the influence and benefit of application of elastic-viscoplastic material models in the frame of welding and heat treatment numerical analyses. Therefore elastic-viscoplastic material model is further applied in solution of practical project solved by IAM Brno. Solution of this project, whose aim is the development of repair of dissimilar metal welds (without post-weld heat treatment) in Dukovany and Temelin nuclear power plants using "Weld overlay method", has confirmed that application of elastic-viscoplastic material model leads to more accurate calculated results. For this reason the elastic-viscoplastic computational approach will be included into all future tasks of IAM Brno.