A thermo-structural model was developed to predict the failure of compressively loaded fiber-reinforced polymer (FRP) laminates during fire. The thermal model was developed as a one-dimensional heat and mass transfer model to predict the thermal response of a decomposing material. The thermal properties were defined as functions of temperature and material decomposition state. The thermal response was used to calculate mechanical properties. The structural model was developed with thermally induced bending caused by one-sided heating. The structural model predicts out-of-plane deflections and compressive failure of laminates in fire conditions. Laminate failure was determined using a local failure criterion comparing the maximum combined compressive stress with the compressive strength. Intermediate-scale one-sided heating tests were performed on compressively loaded FRP laminates. The tests were designed to investigate the effect of varying the applied stress, applied heat, and laminate dimensions on the structural response. Three failure modes were observed in testing: kinking, localized kinking, and forced-response deflection, and were dependent on the applied stress level and independent of applied heating. The times-to-failure of the laminates followed an inverse relationship with the applied stress and heating levels. The test results were used to develop a relationship which relates a non-dimensionalized applied stress with a non-dimensionalized slenderness ratio. This relationship relates the applied stress, slenderness ratio, and temperature of the laminate at failure and can be used to determine failure in design of FRP laminate structures. The intermediate-scale tests were also used to validate the thermo-structural model with good agreement. / Master of Science

This research investigates the flexural behavior of reinforced concrete (RC) beams retrofitted with fiber metal laminate (FML), an advanced hybrid material composed of alternating layers of metal and fiber-reinforced polymer (FRP) composites bonded through a thermoplastic or thermoset polymeric matrix. While FRP composites are commonly used for structural retrofits, their brittle failure mode, due to the linear elastic behavior of the fibers that cannot deform plastically, limits their effectiveness in applications requiring ductility. To address the drawbacks associated with FRP, this project proposes FML as a potential alternative. Flexural testing was conducted on seven RC beams with different configurations of FML and FRP under four-point bending. The goal of the project was finding an ideal retrofit for the RC beam that increased the peak load without a sacrificing the ductility. The beams, which were simply supported, were subjected to two point loads in order to assess their complete load-deformation behavior. Displacements and applied loads were measured at the midspan, and strain data wasrecorded along the length of the retrofits. Four beams were retrofitted with FML, two with FRP, and one served as a control specimen that did not have a retrofit. In order to prevent a premature debonding failure between the RC beam and retrofit, this study also explored different bonding methods: hybrid bonding and unbonded anchorage configurations. Four of the retrofitted beams had a hybrid bonded anchorage configuration and two had an unbonded anchorage configuration. Analytical modeling was performed to predict the behavior of RC beams with various retrofit configurations and bonding types. The modeling procedure for fully bonded retrofits followed the prescribed method in ACI 440.2R-17 that assumes full strain compatibility between the RC beam and retrofit. Due to the lack of strain compatibility for unbonded retorifts, an analytical procedure was developed to generate the moment-curvature response and is reported in Appendix D. The modeling techniques accurately predicted the load-deformation behavior observed in the experiments. The results indicated that FML is an appropriate retrofit material for RC beams, with beam behavior highly dependent on the fiber orientation within the FML. RC Beams retrofitted with fully bonded, unidirectional fibers experienced the highest strength gains but exhibited decreased ductility. In contrast, beams retrofitted with fully bonded, off-axis fibers showed moderate strength gains without a reduction in ductility. Unbonded retrofits were effective in increasing both the strength and ductility of the beams, displaying performance similar to the fully bonded retrofits fiber orientation. This study demonstrates the potential of FML as a retrofit material that offers a balance between strength enhancement and ductility. The main findings highlights the significance of fiber orientation and bonding methods in optimizing the performanae of RC beam retrofits. / Master of Science / This project explored methods to strengthen reinforced concrete (RC) beams using fiber metal laminate (FML), a material created by layering metal sheets with fiber-reinforced polymers (FRP). While FRP is commonly utilized for structural retrofits, it has significant deficiencies: its fibers are brittle and lack ductility compared to metals. FML addresses these issues by combining metals with FRP, resulting in a more ductile and reliable strengthening solution. Seven RC beams were tested by applying two-point loads near the center until failure occurred. Four of these beams were retrofitted with FML, two with FRP, and one remained unaltered as a control specimen. To prevent premature debonding failure between the RC beam and the retrofit, different bonding methods were explored: four retrofitted beams had the retrofit materials fully bonded using hybrid bonded anchorage configurations, while two featured unbonded anchorage configurations. During testing, midspan displacement, applied loads, and strain along the retrofitted areas were measured. Analytical modeling was employed to predict the behavior of RC beams with various retrofit configurations and bonding types. For the fully bonded retrofits, established guidelines from ACI 440.2R-17 were adhered to, assuming full strain compatibility between the RC beam and retrofit. Due to the lack of strain compatibility for unbonded retrofits, a new analytical procedure was developed to generate the moment-curvature response, detailed in Appendix D. These modeling techniques accurately predicted the load-deformation behavior observed in the experiments. The results demonstrated that FML is an effective material for reinforcing RC beams. Performance was largely influenced by the fiber orientation within the FML. Beams reinforced with FML having fibers aligned in one direction exhibited the greatest strength gains but reduced ductility. Conversely, beams with fibers arranged at angles achieved moderate strength increases without compromising ductility. Unbonded retrofits were also effective, enhancing both the strength and ductility of the beams in a manner consistent with fiber orientation trends. In summary, FML offers a promising method for retrofitting RC beams by balancing increased strength with maintained ductility. Fiber orientation and bonding methods are critical factors in optimizing the performance of the strengthened beams.

Optimization is a decision making process to solve problems in a number of fields including engineering mechanics. Bio-inspired optimization algorithms, including genetic algorithm (GA), have been studied for many years. There is a large literature on applying the GA to mechanics problems. However, disadvantages of the GA include the high computational cost and the inability to get the global optimal solution that can be found by using a honeybee-inspired optimization algorithm, called the New Nest-Site Selection (NeSS). We use the NeSS to find optimal parameters for three mechanics problems by following the three processes: screening, identifying relationships, and optimization. The screening process identifies significant parameters from a set of input parameters of interest. Then, relationships between the significant input parameters and responses are established. Finally, the optimization process searches for an optimal solution to achieve objectives of a problem. For the first two problems, we use the NeSS algorithm in conjunction with a third order shear and normal deformable plate theory (TSNDT), the finite element method (FEM), a one-step stress recovery scheme (SRS) and the Tsai-Wu failure criterion to find the stacking sequence of composite laminates and the topology and materials for doubly curved sandwich shells to maximize the first failure load. It is followed by the progressive failure analysis to determine the ultimate failure load. For the sandwich shell, we use the maximum transverse shear stress criterion for delineating failure of the core, and also study simultaneously maximizing the first failure load and minimizing the mass subject to certain constraints. For composite laminates, it is found that the first failure load for an optimally designed stacking sequence exceeds that for the typical [0°/90°]₅ laminate by about 36%. Moreover, the design for the optimal first failure load need not have the maximum ultimate load. For clamped laminates and sandwich shells, the ultimate load is about 50% higher than the first failure load. However, for simply supported edges the ultimate load is generally only about 10% higher than the first failure load. For the atmospheric spray process, we employ the NeSS algorithm to find optimal values of four process input parameters, namely the argon flow rate, the hydrogen flow rate, the powder feed rate and the current, that result in the desired mean particle temperature and the mean particle velocity when they reach the substrate. These optimal values give the desired mean particle temperature and the mean particle velocity within 5% of their target values. / Ph. D. / An optimization process iteratively searches for the best solution from all feasible solutions in the search space that satisfy prespecified criteria. Optimization problems consist of sets of parameters, constraints, and objective functions. Here we use a honeybee-inspired optimization algorithm, called the New Nest-Site Selection (NeSS), to find optimal parameters for three mechanics problems. In the first problem, we optimize the design of an assembly of layers of unidirectional fiber-reinforced materials called composite laminates. Because of their high specific strength and directional-dependent stiffness as compared to those of metals, the composite laminates are being increasingly used in aerospace and automotive industries. After having analyzed deformations of a composite laminate, a failure criterion is used to determine if any point in the structure has failed. The minimum load for which the failure criterion is satisfied at a point is called the first ply failure load. Here we determine the fiber orientation angle in each layer of a rectangular laminate deformed statically by transverse loads applied on the top surface that maximizes the first ply failure load. Subsequently, the load is incrementally increased for the optimally designed laminate and the strength of the failed elements is degraded till the structure cannot support any additional load. The maximum load a structure can support is called the ultimate load. It is found that for a laminate with all edges clamped, the ultimate load can be 40% more than the first ply failure load. We extend the above work to design an optimal geometry and an optimal combination of materials of the facesheets and the core that simultaneously maximizes the first failure load, minimizes the weight of a doubly curved sandwich shell, and satisfies pre-specified constraints. The doubly curved sandwich structure of interest here is comprised of two thin parallel unidirectional fiber-reinforced facesheets bonded to and enclosing a relatively thick mid-layer made of a material softer and lighter than that of the facesheets. The sandwich structures are widely used in aircraft, marine, automobile, and civilian infrastructures. It is found that optimal designs for doubly curved sandwich shells strongly depend upon how the shell edges are supported, and shells designed for the maximum first failure load need not have the maximum ultimate load. An atmospheric plasma spray process (APSP) has been successfully used to coat components for gas turbines, airframe, engines and drive trains, and silicon chips. In the APSP, coating powder is injected into the plasma, which is a mixture of ionized gases such as argon, hydrogen, and helium, through a powder port generally oriented perpendicular to the plasma jet axis. Through interactions with the plasma jet, the particles are accelerated, heated and partially melted before they strike the substrate and are deposited on it to form a coating. It is believed that the coating properties and its quality depend on the particles’ temperature and velocity when they hit the substrate. Here we determine optimum values of four input parameters, namely, the argon flow rate, the hydrogen flow rate, the current, and the powder feed rate to achieve the desirable mean particles’ temperature and the mean particles’ velocity. It is found that the four processes input parameters can be optimized to attain particles’ characteristics within 5% of their prespecified desired values.

No / This paper presents the details of a methodology for predicting the thermoelastic properties degradation in general symmetric laminates with uniform ply cracks in some or all of the 90° layers. First, a stress transfer method is derived by using the concept of state space equation. The laminate can be subjected to any combination of in-plane biaxial and shear loading, and the uniform thermal loading is also taken into account. The method takes into account all independent material constants and guarantees continuous fields of all interlaminar stresses across interfaces between material layers. By this method, a laminate may be composed of an arbitrary number of monoclinic layers and each layer may have different material property and thickness. Second, the concept of the effective thermoelastic properties of a cracked laminate is introduced. Based on the numerical solutions of specially designed loading cases, the effective thermoelastic constants of a cracked laminate can be obtained. Finally, the applications of the methodology are shown by numerical examples and compared with numerical results from other models and experiment data in the literature. It is found that the theory provides good predictions of the thermoelastic properties degradation in general symmetric laminates.

V současnosti je velmi aktuálním tématem generování elektrické energie z alternativních zdrojů, zejména z vibrací. Zařízení, která přeměňují mechanickou energii na elektrickou, využívají často ke své činnosti piezoelektrický jev. Pro optimální nastavení takového elektromechanického měniče pro danou aplikaci je třeba mít k dispozici výpočtový model, který bude schopný postihnout všechny klíčové aspekty jeho provozu. Tato práce se tedy zabývá vytvořením takovéhoto nástroje, který je schopen komplexně popsat elektromechanickou odezvu studovaného piezoelektrického měniče energie v podobě vetknutého, vícevrstvého keramického nosníku s piezoelektrickými vrstvami. Uvažovaná vícevrstvá konstrukce je během své činnosti vystavena kinematickému buzení a je rovněž zatížena tepelnou zbytkovou napjatostí vznikající při její výrobě. Vytvořený výpočtový model využívá klasickou laminátovou teorii k určení statické elektromechanické odezvy dané konstrukce. Elektromechanická odezva při kmitání uvažované konstrukce v ustáleném stavu je získána s využitím Hamiltonova variačního principu a teorie kmitání prutů. Vytvořený výpočtový model je dále schopen odhadnout zdánlivou lomovou houževnatost dané vícevrstvé konstrukce pomocí metody váhových funkcí. Výstupy vytvořeného výpočtového modelu jsou ověřeny s využitím numerických simulací na bázi MKP a dostupných experimentálních výsledků. V diplomové práci je následně vytvořený výpočtový model aplikován při hledání optimálního rozložení jednotlivých vrstev konkrétního vícevrstvého nosníku s cílem maximalizovat jeho elektrický výkon a odolnost vůči šíření povrchových trhlin, resp. vzniku křehkého lomu. Tohoto cíle je dosaženo pomocí vhodného rozložení tepelných zbytkových napětí v jednotlivých vrstvách uvažované konstrukce (řízeného použitými materiály a tloušťkami jednotlivých vrstev).

A radiação gama é uma das tecnologias aplicadas para a esterilização de sistemas de embalagens contendo produtos para a saúde. No processo de esterilização, é fundamental que as propriedades das embalagens sejam mantidas. Neste estudo, duas amostras de embalagens comerciais, no formato de envelope compostas por papel grau cirúrgico de um dos lados e filme plástico laminado do outro, foram irradiadas com raios gama com doses de 25 kGy (taxa de dose de 1,57 kGy/h) e 50 kGy (taxa de dose de 1,48 kGy/h). Uma das amostras de embalagem era constituída por papel de fibras de coníferas e filme plástico laminado de poli(tereftalato de etileno) (PET)/polietileno (PE) e a outra por papel de fibras de coníferas e de folhosas e filme plástico laminado de poli(tereftalato de etileno) (PET)/polipropileno (PP). Os efeitos da radiação nas propriedades físicas e químicas dos papéis e dos filmes plásticos, assim como nas propriedades da embalagem foram estudados. O papel foi o material mais sensível à radiação, sendo a alvura, o pH e as resistências ao rasgo, ao arrebentamento e à tração os parâmetros nos quais foram observadas maiores modificações, em ambas as amostras. Todavia, dos dois tipos de papel, o efeito foi mais pronunciado para a amostra com fibras de conífera e de folhosas. A porosidade dos papéis foi alterada com 50 kGy. No caso dos filmes plásticos, a propriedade com maior modificação foi a resistência à tração, em ambas as amostras. No caso das embalagens, a irradiação diminuiu a resistência da selagem. Os efeitos observados para a dose de 50 kGy foram em média mais pronunciados quando comparados com as modificações nos valores das amostras tratadas com 25 kGy, que é a dose usualmente empregada para esterilização de produtos para a saúde. A dosimetria deste estudo foi realizada nos materiais irradiados com 25 kGy, 40 kGy e 50 kGy, demonstrando sua importância à medida que a variação média para as três doses estudadas foi de 20 %. / Gamma radiation is one of the technologies applied for the sterilization of packaging systems containing products for health. During sterilization process it is critical that the properties of packages are maintained. In this study two samples of commercial pouch packaging comprised of surgical grade paper on one side and the other side multilayer plastic film were irradiated with gamma rays. The following doses were applied 25 kGy (1,57 kGy/h) and 50 kGy (1,48 kGy/h). One packaging sample was paper formed by softwood fibers and multilayer plastic film based on poly(ethylene terephthalate) (PET)/polyethylene (PE). The second type of paper sample was made by a mixture of softwood and hardwood fibers and multilayer plastic film based on polyethylene terephthalate (ethylene) (PET)/polypropylene (PP). The effects of radiation on the physical and chemical properties of papers and multilayer plastic films, as well as the properties of the package were studied. The paper was the more radiation sensitive among the studied materials and radiation effects were more pronounced at brightness, pH, tearing resistance, bursting strength and tensile strength. Nonetheless, worst comparatively effects were noted on the sample made by a mixture of softwood and hardwood fibers. The porosity of paper was enhanced by 50 kGy. In the case of plastic films, radiation effects on tensile strength was the most pronounced property for both samples. In the case of the packaging the sealing resistance decreased with radiation. The effects observed for the treatment at 50 kGy were more pronounced when compared to 25 kGy. This last is the dose which is usually applied to sterilize health products. A dosimetry study was performed during irradiation at 25 kGy, 40 kGy and 50 kGy and its importance may be reported by the average dose variation 20 %.

Este trabalho objetivou a manufatura de laminados híbridos metal-fibra (LMF) empregando-se chapas com 0,5 mm de espessura de liga-\'TI\'6\'AL\'4\'V\' com superfícies modificadas por laser de fibra de modo a otimizar a sua adesão com polímero termoplástico poli-sulfeto de fenileno (PPS). Observou-se que a microtextura superficial da liga metálica dependeu fortemente da potência do feixe laser, quando potências mais baixas levaram à verdadeira texturização da superfície metálica, enquanto que potências mais elevadas conduziram à ablação da mesma. A texturização superficial metálica sob laser de baixa potência aparentou ser a condição mais apropriada para a adesão metal-polímero por ancoragem mecânica de macromoléculas, o que foi contrabalanceado por elevados níveis de tensão residual das chapas metálicas, gerando grande distorção das mesmas e inviabilizando sua utilização. O emprego de uma potência intermediária (160 W) mostrou-se propício à otimização entre a adesão física entre metal-polímero e o nível de tensões residuais criado nas chapas metálicas. Concluiu-se que os espécimes extraídos do centro dos laminados metal-fibra exibem uma tensão limite média para falha por cisalhamento interlaminar consideravelmente superior à dos espécimes usinados a partir da borda dos LMF. O LMF manufaturado sob maiores pressão e temperatura exibiu uma maior compactação e melhor consolidação, culminando num máximo desempenho médio sob carga de cisalhamento interlaminar. Evidências de uma correlação entre o mecanismo de falha por cisalhamento interlaminar do corpo de prova e o seu nível de resistência a este tipo de carregamento mecânico foram documentadas e discutidas. / This work aimed at manufacturing hybrid fiber-metal laminates (FML) by employing 0,5 mm-thick \'TI\'6\'AL\'4\'V\'-alloy plaques with fiber laser modified surface in order to optimize metal adhesion with poli-phenylene sulfide (PPS) thermoplastic polymer. The surface microtexture of metallic alloy strongly depended upon the laser power, inasmuch as low-power laser led to true texturization of metal surface, whereas high-power laser light drove to its ablation. Surface metal texturization under low-power laser apparently was the most appropriate condition to metal-polymer adhesion via mechanical entanglement of macromolecules, which was offset by high levels of residual stresses on metallic plaques, bringing them quite warped and useless. The use of an intermediate laser power (160 W) has been shown benign to the optimization between metal-polymer physical adhesion and the residual stress level created in the metal plates. It has been concluded that testpieces machined from the FML central position exhibited average ultimate interlaminar shear strenght considerably higher than those extracted from the FML borders. The FML manufactured under higher pressure and temperature was more compacted and better consolidated, so that it displayed the greatest average performance under interlaminar shear loading. Evidences of a correlation between the failure mechanism by interlaminar shearing of test coupon and its allowance to this type of mechanical loading were documented and discussed.

Materiais compósitos laminados possuem uma alta eficiência estrutural, mas que é comprometida pela baixa resistência a cargas de impacto. O objetivo deste trabalho é o desenvolvimento de uma metodologia de simulação numérica para a estimativa de danos causados por cargas de impacto a baixas velocidades em placas de material compósito laminado. Ensaios experimentais foram realizados em placas reforçadas com tecidos de fibra de carbono e matriz de resina epóxi. Foram avaliadas três espessuras. Os carregamentos de impacto com uma massa em queda livre foram pontuais e transversais à placa, com intervalos de energia variando entre 5J e 94J, com velocidades inferiores a 6 m/s. As simulações numéricas utilizaram um programa comercial de elementos finitos com integração explícita. Foram avaliados dois critérios de falha da lâmina. O primeiro é o critério de máxima tensão. O segundo é uma proposta de modificação no critério de falha de Hashin, para sua aplicação em laminados reforçados com tecidos bidirecionais. Também foram avaliados quatro diferentes critérios de degradação da lâmina. As evoluções das forças de contato entre o impactador e a placa foram muito bem representadas numericamente. As áreas e os comprimentos dos danos numéricos foram similares ou maiores que os medidos nos resultados experimentais. / Laminate composite materials have high structural efficiency, however it is jeopardized due the low strength to impact loads. The objective of this work is to develop a numerical simulation methodology that estimates the damage in laminate plates caused by low velocity impact. Experimental tests were performed on laminate plates reinforced with weaven carbon fibers and epoxi resine. Three thickness plates were evaluated. The impact loads were transversal and punctual. They were done with drop-test, the impact energy range is between 5J and 94J, and the velocities were lower than 6m/s. The numerical simulations were done with FEM commercial code with explict integration. Two lamina failure criteria were evaluated. The first is the maximum stress. The second is a proposed modification of the Hashin failure criterion in order to be applied on the fabric laminates. Four lamina degradation criteria were evaluated too. The numerical contatct loads between the plate and impactor were well represented. The numerical damaged areas and lengths were similar or greater than the experimental results.

Acknowledging the goal of reduced aircraft weight, there is a need to improve on conservative design techniques used in industry. Minimisation of laminate in-plane elastic energy is used as an appropriate in-plane performance marker to assess the weight saving potential of new design techniques. MATLAB optimisations using a genetic algorithm were used to find the optimal laminate variables for minimum in-plane elastic energy and/or damage tolerance for all possible loadings. The use of non-standard angles was able to offer equivalent, if not better in-plane performance than standard angles, and are shown to be useful to improve the ease of manufacture. Any standard angle laminate stiffness was shown to be able to be matched by a range of two non-standard angle ply designs. This non-uniqueness of designs was explored. Balancing of plus and minus plies about the principal loading axes instead of themanufacturing axes was shown to offer considerable potential for weight saving as the stiffness is better aligned to the load. Designing directly for an uncertain design load showed little benefit over the 10% ply percentage rule in maintaining in-plane performance. This showed the current rule may do a sufficient job to allow robustness in laminate performance. This technique is seen useful for non-standard angle design that lacks an equivalent 10% rule. Current use of conservative damage tolerance strain limits for design has revealed the need for more accurate prediction of damage propagation. Damage tolerance modelling was carried out using fracture mechanics for a multi-axial loading considering the full 2D strain energy and improving on current uni-axial models. The non-conservativeness of the model was evidenced to be from assumptions of zero post-buckled stiffness. Preliminary work on conservative multi-axial damage tolerance design, independent of thickness, is yet to be confirmed by experiments.

O objetivo deste trabalho é analisar in vitro a dissipação de tensões em incisivos centrais superiores humanos restaurados com facetas de cerâmica feldspática, através da análise do método dos elementos finitos, considerando cargas funcionais de mastigação e corte dos alimentos, em função de três tipos de preparos utilizados: sem proteção incisal; com proteção incisal em ângulo e com proteção incisal em degrau palatino. Foram utilizadas modelagens bidimensionais de um incisivo central superior e suas estruturas de suporte, simulando três situações: (Primeira modelagem) incisivo central superior com desgaste vestibular (em forma de janela); (Segunda modelagem) incisivo central superior com desgaste vestibular e proteção incisal em plano inclinado; (Terceira modelagem) incisivo central superior com desgaste vestibular, e proteção incisal com degrau palatino. Foi considerada uma carga (P=100N) com uma inclinação de 45 concentrada, simulando a região de contato do incisivo central inferior com o superior durante a mastigação e uma na região de contato topo a topo dos incisivos superior e inferior, simulando o corte dos alimentos. Após a análise dos dados obtidos pela distribuição de tensões, pode-se concluir que quanto à dissipação das tensões em todo o sistema proposto, com a aplicação de carga em 45, não foram observadas mudanças no estado tensional nos três diferentes preparos. Quando foi aplicada carga vertical, simulando o contato de topo, houve variação no estado tensional no sistema do dente com preparo em janela. Nas facetas, com a aplicação de carga em 45, nos preparos em janela e com proteção incisal em plano inclinado o resultado foi semelhante nos valores tensionais enquanto, nas facetas em dentes preparados com proteção incisal com degrau palatino, a distribuição foi mais homogênea tendo valores superiores, mostrando que o abraçamento do dente diminuiu a flexão. / The aim of this study is to analyze in vitro stress dissipation on human maxillary central incisors restored with ceramic feldspathic veneers, through the finite element method. Functional chewing and food cutting loads were evaluated in three types of preparations of teeth: preparation without incisal protection, with incisal angle protection and with incisal protection with palatal step. Two-dimensional modeling of a maxillary central incisor and its supporting structures were used, simulating three conditions: 1) First modeling - maxillary central incisor with facial preparation (window shape); 2) Second modeling - maxillary central incisor with facial preparation and incisal protection on an inclined plane; 3) Third modeling - maxillary central incisor with facial preparation and incisal protection with palatal step. The chosen load (P = 100N) was applied to two different points: one of them to the palatal aspect with an inclination of 45 in order to simulate the contact area of the mandibular and the maxillary central incisors during chewing and the other one to the region of contact with edge-to-edge upper/lower central incisors, simulating food cutting. After analyzing the data obtained from the stress distribution it is possible to conclude that there are no alterations in tensional characteristics of the three different preparations concerning the stress dissipation on the whole proposed system, considering the application of load in 45. When the vertical load was applied, simulating an edge-to-edge contact, a variation in the stress state of tooth with window preparation was observed. For veneers with 45 load application, both the window preparation teeth and teeth with incisal protection on an inclined plane presented similar tensional values. For veneers of prepared teeth with incisal protection with palatal step, the stress distribution was more homogeneous with higher values, showing that tooth embracement reduced flexion.