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Advisor(s)
Abstract(s)
As estruturas das aeronaves chegam a incorporar mais de 50% de materiais compósitos e estão sujeitas
a impactos durante o voo, a descolagem, a aterragem e nas atividades de manutenção. Estes eventos,
para além de introduzirem danos internos, são responsáveis pela diminuição da resistência e rigidez
dessas estruturas. Deste modo torna-se inevitável a sua substituição ou reparação. Para os danos
menores e mais localizados, é vantajoso isolar e reparar apenas a área danificada de forma a corrigir a
integridade da estrutura danificada.
Assim, este trabalho pretende estudar o efeito da geometria de reparação na resistência ao impacto de
compósitos laminados. As geometrias de reparação estudadas são do tipo “patch repair” que podemos
traduzir como remendo compósito colado. Foram utilizadas geometrias de reparação por sobreposição
simples (SS) e de sobreposição dupla (SD).
Foi possível concluir que as reparações de SD são claramente preferíveis às de SS visto que, em termos
médios, a vida é 51,9 vezes superior às SS.
Aircraft structures come to incorporate more than 50% of composite materials and are subject to impacts during flight, takeoff, landing and in the maintenance activities. These events, in addition to introducing internal damage, are responsible for decreasing strength and stiffness of these structures. As such, substitution or repair becomes inevitable. For smaller, more localized damage, it’s advantageous to isolate and repair only the damaged area in order to correct the integrity of the damaged structure. This work aims to study the effect of the repair geometry on the impact resistance of composite laminates. "Patch repair” were the type of repairs studied. Repair geometries used were simple superposition (SS) and of double superposition (SD). It was concluded that the SD repairs are clearly preferable to the SS because, on average, their life is 51.9 times higher than that of the SS.
Aircraft structures come to incorporate more than 50% of composite materials and are subject to impacts during flight, takeoff, landing and in the maintenance activities. These events, in addition to introducing internal damage, are responsible for decreasing strength and stiffness of these structures. As such, substitution or repair becomes inevitable. For smaller, more localized damage, it’s advantageous to isolate and repair only the damaged area in order to correct the integrity of the damaged structure. This work aims to study the effect of the repair geometry on the impact resistance of composite laminates. "Patch repair” were the type of repairs studied. Repair geometries used were simple superposition (SS) and of double superposition (SD). It was concluded that the SD repairs are clearly preferable to the SS because, on average, their life is 51.9 times higher than that of the SS.
Description
Keywords
Adesivos Epóxidos Gfrp Mecanismos de Dano Multi-Impacto Reparação de Compósitos Reparações Adesivas