Submitted by Automa??o e Estat?stica (sst@bczm.ufrn.br) on 2018-02-21T21:14:12Z No. of bitstreams: 1 AnaPaulaPereiraFulco_TESE.pdf: 5611369 bytes, checksum: 90dd17509ac9fc7af5b3bb30ec9b9fd9 (MD5) / Approved for entry into archive by Arlan Eloi Leite Silva (eloihistoriador@yahoo.com.br) on 2018-02-22T20:47:30Z (GMT) No. of bitstreams: 1 AnaPaulaPereiraFulco_TESE.pdf: 5611369 bytes, checksum: 90dd17509ac9fc7af5b3bb30ec9b9fd9 (MD5) / Made available in DSpace on 2018-02-22T20:47:30Z (GMT). No. of bitstreams: 1 AnaPaulaPereiraFulco_TESE.pdf: 5611369 bytes, checksum: 90dd17509ac9fc7af5b3bb30ec9b9fd9 (MD5) Previous issue date: 2017-11-30 / Conselho Nacional de Desenvolvimento Cient?fico e Tecnol?gico (CNPq) / Coordena??o de Aperfei?oamento de Pessoal de N?vel Superior (CAPES) / Materiais comp?sitos de matriz polim?rica refor?ados com fibras de carbono utilizados em estruturas aeron?uticas e aeroespaciais est?o frequentemente sujeitos ? carregamentos c?clicos e condi??es ambientais de temperatura e umidade, que podem provocar degrada??o e at? a falha do componente. O objetivo deste trabalho foi estudar os efeitos do envelhecimento sob exposi??o a temperatura at? 160?C e ? umidade nos mecanismos de dano de comp?sitos carbono/ep?xi submetidos a carregamento c?clico. Um estudo preliminar de envelhecimento acelerado foi inicialmente realizado em comp?sitos unidirecionais AS4/8552 com ciclo exposi??o de 8 h de radia??o UVA-340 a 80?C seguidas de 4 h de condensa??o a 50?C, at? atingir o tempo total de 2.160 h. Os efeitos do envelhecimento do material foram evidenciados pela perda de massa, exposi??o das fibras, altera??es qu?micas, aumento da densidade de trincas em testes de cisalhamento interlaminar e flambagem das fibras em amostras fraturadas em testes de compress?o, embora n?o tenham sido observadas altera??es significativas nas propriedades mec?nicas do material. Com base neste trabalho preliminar, um estudo foi realizado em laminados [02/902]s do mesmo material, utilizando ciclo de exposi??o de 8 h a 160 ?C seguidas de 4 h com umidade relativa de 80% a 70 ?C, at? atingir o tempo total de 2.880 h. Em seguida, as amostras foram submetidas a ensaios de fadiga com controle de carga, com raz?o de tens?es R = 0,1 e frequ?ncia de 5 Hz. Os comp?sitos foram caracterizados por espectroscopia de infravermelho com transformada de Fourier (FTIR), an?lise din?mico mec?nica (DMA), microscopia eletr?nica de varredura (MEV) e varia??o de massa, antes e ap?s a exposi??o higrot?rmica. Amostras de ep?xi puro 8552 foram tamb?m expostas as mesmas condi??es de envelhecimento e caracterizadas por microscopia ?tica (MO), espectroscopia FTIR e varia??o de massa. A partir dos diagramas de vida em fadiga, uma fun??o de deslocamento (shift) foi proposta para a previs?o de n?mero de ciclos para falha de comp?sitos envelhecidos com base em dados de testes de fadiga em comp?sitos n?o envelhecidos. O estudo tamb?m mostrou que a falha por fratura pode n?o ser o melhor par?metro para avalia??o do efeito do envelhecimento higrot?rmico na vida em fadiga de materiais comp?sitos de matriz polim?rica refor?ados com fibras de carbono. Outros par?metros como delamina??o e satura??o de trincas s?o tamb?m essenciais para avaliar a durabilidade desses materiais comp?sitos. / Carbon fiber reinforced polymer (CFRP) composites used in aeronautic and aerospace structures are often exposed to cyclic loading and environmental effects such as temperature and humidity, which can lead to degradation and failure of the component. The objective of this work was to study the effects of aging under exposure to temperature up to 160?C and humidity on the damage mechanisms of carbon/epoxy composites subjected to cyclic loading. Initially, a preliminary accelerated aging study was conducted with unidirectional AS4/8552 samples using an exposure cycle of 8 h of UVA-340 at 80 ?C followed by 4 h of condensation at 80 ?C, for a total exposure period of 2,160 h. The effects of aging were evidenced by weight loss, fiber exposure, chemical changes, increased crack density in interlaminar shear strength tests, and fiber buckling in fractured samples after compression tests, even though no significant changes mechanical properties were observed. Based on this preliminary work, a study was conducted on [02/902]s laminates of the same material, using an exposure cycle of 8 h at 160 ?C followed by 4 h of 80% relative humidity at 70 ?C, for a total exposure period of 2,880 h. Afterwards, stress-controlled tension-tension fatigue tests were conducted using a stress ratio R = 0.1 and frequency of 5 Hz. Composites were characterized using Fourier transform infrared spectroscopy (FTIR), Dynamic Mechanical Analysis (DMA), Scanning Electron Microscopy (SEM) and weight change, before and after hygrothermal exposure. Samples of plain epoxy 8552 were also exposed to the same aging conditions and characterized by optical microscopy (OM), FTIR spectroscopy and weight change. Based on the fatigue life diagrams, a shift function was proposed for the prediction of number of cycles to failure of aged composites based on data from unaged specimens. The study also showed that failure by fracture may not be the best parameter to evaluate the effect of hygrothermal aging on fatigue life of carbon fiber reinforced polymer composites. Other parameters such as delamination and crack saturation are also essential to assess durability of these composites.

Submitted by Automa??o e Estat?stica (sst@bczm.ufrn.br) on 2018-02-15T11:17:49Z No. of bitstreams: 1 AllanaAzevedoDoNascimento_DISSERT.pdf: 3970437 bytes, checksum: 117bfe2f45af82aa1ce79c2ec7c811e1 (MD5) / Approved for entry into archive by Arlan Eloi Leite Silva (eloihistoriador@yahoo.com.br) on 2018-02-16T11:03:56Z (GMT) No. of bitstreams: 1 AllanaAzevedoDoNascimento_DISSERT.pdf: 3970437 bytes, checksum: 117bfe2f45af82aa1ce79c2ec7c811e1 (MD5) / Made available in DSpace on 2018-02-16T11:03:56Z (GMT). No. of bitstreams: 1 AllanaAzevedoDoNascimento_DISSERT.pdf: 3970437 bytes, checksum: 117bfe2f45af82aa1ce79c2ec7c811e1 (MD5) Previous issue date: 2017-10-16 / As t?cnicas de auto-reparo em resinas ep?xi v?m sendo desenvolvidas buscando aumentar a vida ?til e reduzir os custos associados ? manuten??o desses materiais durante o servi?o. A adi??o de termopl?sticos ? matriz termofixa produzindo resinas repar?veis aparece como t?cnica de reparo promissora. Neste trabalho, o termopl?stico poli (etileno-co-?cido-metacr?lico) (EMAA) foi adicionado no plano m?dio de laminados comp?sitos carbono-ep?xi para fabrica??o de um sistema de reparo. Foram fabricadas placas com 5%, 10% e 15% de EMAA em massa de resina do prepreg. Ensaios de resist?ncia ao cisalhamento interlaminar (ILSS), an?lise din?mico mec?nica (DMA), espectroscopia de infravermelho por transformada de Fourier (FTIR), microscopia eletr?nica de varredura (MEV) e microscopia eletr?nica de varredura com fonte de emiss?o de campo (MEV-FEG) foram conduzidos para avaliar o efeito da adi??o desse termopl?stico ao comp?sito e seu comportamento antes e ap?s o reparo. As amostras reparadas n?o apresentaram aumento na resist?ncia ao cisalhamento interlaminar (ILSS) ap?s o reparo. Entretanto, para maiores porcentagens de EMAA, houve redu??o dessa propriedade, al?m de redu??o de m?dulo de elasticidade e da temperatura de transi??o v?trea (Tg), em rela??o aos valores apresentados pelo comp?sito puro. Imagens de MEV confirmaram a forte ades?o entre o EMAA e a resina ep?xi, formando uma camada adesiva que impediu a forma??o de delamina??es no plano m?dio do laminado. / Self-healing techniques in epoxy resins have been developed to improve the durability and reduce costs associated with repairs of these materials during service. The addition of thermoplastics into the thermoset matrix producing mendable resins appears as a promising self-healing technique. In this study, poly(ethylene-co-methacrylic acid) (EMAA) was added in the mid-plane of carbon fiber-epoxy composites laminates to produce a self-healing system. Plates were manufactured with addition of 5%, 10% and 15% of EMAA as related to the resin weight of prepreg. Interlaminar shear strength test (ILSS), dynamic mechanical analysis (DMA), Fourier-transform infrared (FTIR) spectroscopy, scanning electron microscopy (SEM) and field-emission gun scanning electron microcopy (FEG-SEM) were employed in order to evaluate the effect of the addition of the thermoplastic to the composite and its behavior before and after a healing cycle. The healed samples did not show an increase in interlaminar shear strength (ILSS) after healing. However, for higher percentages of EMAA there was a reduction of this property, besides a reduction of Young?s modulus and glass transition temperature (Tg), in relation to the values presented by the unmodified composite. SEM images confirmed the strong adhesion between EMAA and epoxy resin, which produced an adhesive layer that prevented delamination in the mid-plane of the laminate.

Made available in DSpace on 2014-12-17T14:07:19Z (GMT). No. of bitstreams: 1 PedroLSF_DISSERT.pdf: 5571248 bytes, checksum: d237019829d37099df0ac47168668556 (MD5) Previous issue date: 2014-07-21 / Conselho Nacional de Desenvolvimento Cient?fico e Tecnol?gico / Composite laminates with plies in different directions finely dispersed are classified as homogenized. The expected benefits of homogenization include increased mechanical strength, toughness and resistance to delamination. The objective of this study was to evaluate the effect of stacking sequence on the tensile strength of laminates. Composite plates were fabricated using unidirectional layers of carbon/epoxy prepreg with configurations [903/303/-303]S and [90/30/-30]3S. Specimens were subjected to tensile and open hole tension (OHT) tests. According to the experimental results, the mean values of strength for the homogenized laminates [90/30/-30]3S were 140% and 120% greater for tensile and OHT tests, respectively, as compared to laminates with configuration [903/303/-303]S. The increase in tensile strength for more homogenized laminates was associated with the increment in interlaminar interfaces, which requires more energy to produce delamination, and the more complicated crack propagation through plies with different orientations. OHT strength was not affected by the presence of the hole due to the predominance of the interlaminar shear stress in relation to the stress concentration produced by the hole / Laminados formados por l?minas com diferentes orienta??es, finamente dispersas, s?o classificados como homogeneizados. Os benef?cios esperados da homogeneiza??o incluem aumento de resist?ncia mec?nica, da tenacidade e da resist?ncia ? delamina??o. O objetivo deste trabalho foi avaliar o efeito da sequ?ncia de empilhamento na resist?ncia ? tra??o de laminados quase-isotr?picos. Placas de comp?sitos foram fabricadas com l?minas unidirecionais de ep?xi/carbono com configura??es [903/303/-303]S e [90/30/-30]3S. Corpos de prova foram submetidos a ensaios de tra??o e de open hole tension (OHT). De acordo com os resultados experimentais, os valores m?dios de resist?ncia para os laminados mais homogeneizados [90/30/-30]3S foram incrementados em 140% e 120% nos ensaios de resist?ncia ? tra??o e OHT, respectivamente, em rela??o aos laminados com configura??o [903/303/-303]S. O aumento de resist?ncia ? tra??o para laminados mais homogeneizados foi relacionado com o maior n?mero de interfaces interlaminares, que aumenta a quantidade de energia necess?ria para produzir delamina??o, e a maior dificuldade de propaga??o de trincas atrav?s de l?minas com orienta??es diferentes. A resist?ncia medida nos ensaios de OHT n?o foi afetada pela presen?a do furo devido ? predomin?ncia da influ?ncia da tens?o de cisalhamento interlaminar em rela??o ao efeito de concentra??o de tens?o provocado pelo furo