Compósitos processados via RTM em molde de aço carbono e de liga de alumínio: efeito da condutividade térmica nas propriedades mecânicas e térmicas
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Data
2017-02-06
Autores
Majewski, Marcelo [UNESP]
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Editor
Universidade Estadual Paulista (Unesp)
Resumo
O aumento do uso de compósitos estruturais tem levado a uma preocupação constante com a confiabilidade destes materiais. Em particular, o processo de cura das resinas na fabricação é citado como um dos problemas mais significativos no processamento de compósitos estruturais. Assim, para que essa classe de materiais possa ser economicamente viável e atender às exigências dos padrões de qualidade do setor aeronáutico, tecnologias de processamento automatizado e novas formas de matéria-prima estão sendo desenvolvidas e implantadas na fabricação. Desta forma, o objetivo da presente pesquisa foi estudar a influência das propriedades térmicas dos materiais de moldes, utilizados no processamento de compósitos via RTM, nas propriedades finais dos laminados. Foram processadas três placas de compósitos com reforço não dobrável (NCF-non-crimp fabric) biaxial [+45°/-45°] via RTM: em molde de aço 1020, laminado 1; e em liga de alumínio 5052-F, laminados 2 e 3. Para verificar a influência dos materiais dos moldes nas propriedades finais, foram analisadas a tenacidade à fratura interlaminar em modo I e investigação das superfícies de fratura pelo Microscópio Eletronico de Varredura (MEV). O comportamento térmico estudado via análise térmica dinâmico-mecânica (DMA), que avaliou as diferenças no grau de cura dos laminados 1, 2 e 3 com a análise da Tg. Nos processamentos, evidenciou-se que o molde de alumínio apresentou maior controle e estabilidade térmica, enquanto que o molde de aço apresentou maior estabilidade dimensional. Pelo modo I, observou-se maior energia de iniciação de trinca (GIc) para o laminado 1 em relação aos laminados 2 e 3. Nas imagens de fratura no MEV constatou-se a influência da fração volumétrica de fibras e a quantidade de fiber bridging. No laminado 1, observou-se mechas de fibra sobre a costura e fibras rompidas originadas do fiber bridging, que foram responsáveis pela energia adicional exigida na propagação da trinca (GI). No laminado 2 observou-se acúmulo de resina e menor quantidade de fiber bridging, consequentemente, valores intermediários de GI, já no laminado 3 notou-se a ausência de fiber bridging, o que proporcionou a propagação da trinca no domínio da matriz, apresentando o menor valor GI entre os laminados. Nos dois últimos laminados a diminuição de GIc foi atribuida ao grau de cura da resina. Na qual observou-se as transições vítreas (Tg) próximas entre os laminados 1 e 3, e para o laminado 2 a Tg foi inferior, o que demonstrou efetiva correlação entre as características térmicas dos moldes com as propriedades físicas e mecânicas finais dos laminados compósitos obtidos via RTM.
The increase use of structural composites has led to a constant concern on the reliability of these materials. In particular, curing process of resins during manufacturing are cited as one of the most significant problems in the structural composites. Therefore, in order to this class of materials can be economically viable and meet the requirements of quality in the aeronautic industry standards, automated processing technologies and new materials have been developed and implemented in manufacturing sector. Thus, this research aimed to investigate the influence of thermal properties of the mold, which was used in the processing of composites via RTM, on the final properties of the laminates. Three composite plates comprised with NCF (non-crimp fabric) reinforcement, which has biaxial [+45°/-45°] configuration, and epoxy matrix. Two molds were employed for this investigation: steel 1020, for laminate 1, and aluminum alloy 5052-F, for laminates 2 and 3, all laminates with the same fiber stacking sequence. The influence of the materials of the molds in the final properties were verified with interlaminar fracture toughness in mode I (GIc), and their images of the fractured surfaces investigated by Scanning Electron Microscope (SEM). The thermal analysis conducted with Dynamic Mechanical Thermal Analysis (DMA), which evaluated the differences in the degree of cure of laminate 1, 2 and 3 by vitreous temperature transitions (Tg). It was evidenced that the aluminium mold showed better thermal conductivity and temperature stability, while the steel mold showed higher dimensional stability. Mode I showed higher energy crack initiation (GIc) for laminate 1 than for laminates 2 and 3. In the SEM images, it was verified a change in fiber volume fraction and the amount of fiber bridging. Laminate 1 showed fiber tows on the stitch regions and ruptured fibers originated from the fiber bridging, which were responsible for the additional energy of propagation (GI). Laminate 2 showed resin accumulation and less loose fibers, and consequently, intermediate values of GI, Laminate 3 no fiber bridging occured, which showed the propagation of the crack in the matrix domain, presenting the lowest GI value between the laminates. In laminates 2 and 3, the decrease in GIc can be attributed to the degree of cure, in which correlated to the glass transitions (Tg) results. Overall, the tests demonstrated a good correlation between the thermal characteristics of the molds with the final physical and mechanical properties of the laminates obtained via RTM.
The increase use of structural composites has led to a constant concern on the reliability of these materials. In particular, curing process of resins during manufacturing are cited as one of the most significant problems in the structural composites. Therefore, in order to this class of materials can be economically viable and meet the requirements of quality in the aeronautic industry standards, automated processing technologies and new materials have been developed and implemented in manufacturing sector. Thus, this research aimed to investigate the influence of thermal properties of the mold, which was used in the processing of composites via RTM, on the final properties of the laminates. Three composite plates comprised with NCF (non-crimp fabric) reinforcement, which has biaxial [+45°/-45°] configuration, and epoxy matrix. Two molds were employed for this investigation: steel 1020, for laminate 1, and aluminum alloy 5052-F, for laminates 2 and 3, all laminates with the same fiber stacking sequence. The influence of the materials of the molds in the final properties were verified with interlaminar fracture toughness in mode I (GIc), and their images of the fractured surfaces investigated by Scanning Electron Microscope (SEM). The thermal analysis conducted with Dynamic Mechanical Thermal Analysis (DMA), which evaluated the differences in the degree of cure of laminate 1, 2 and 3 by vitreous temperature transitions (Tg). It was evidenced that the aluminium mold showed better thermal conductivity and temperature stability, while the steel mold showed higher dimensional stability. Mode I showed higher energy crack initiation (GIc) for laminate 1 than for laminates 2 and 3. In the SEM images, it was verified a change in fiber volume fraction and the amount of fiber bridging. Laminate 1 showed fiber tows on the stitch regions and ruptured fibers originated from the fiber bridging, which were responsible for the additional energy of propagation (GI). Laminate 2 showed resin accumulation and less loose fibers, and consequently, intermediate values of GI, Laminate 3 no fiber bridging occured, which showed the propagation of the crack in the matrix domain, presenting the lowest GI value between the laminates. In laminates 2 and 3, the decrease in GIc can be attributed to the degree of cure, in which correlated to the glass transitions (Tg) results. Overall, the tests demonstrated a good correlation between the thermal characteristics of the molds with the final physical and mechanical properties of the laminates obtained via RTM.
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Palavras-chave
Processamento RTM, Fibra de carbono, Tenacidade à fratura, DMA, RTM processing, Carbon fiber, Fracture toughness