04.2 - Aerostructures Design, Structural Dynamics, Aeroelasticity
NUMERICAL ANALYSIS AND COMPARISON WITH RESULTS OF FRACTURE TESTS OF LUG MANUFACTURED IN COMPOSITE MATERIAL
G.C. Fonseca, Embraer Minas Gerais, Brazil; S.F.M. Almeida, Instituto Tecnológico de Aeronáutica, Brazil
The results obtained in this work will contribute to a better understanding of the behavior of thick laminated components in composite material subjected to tensile stresses. A failure analysis methodology will be presented for thick laminated type aeronautical components, based on the results of the numerical models studied and validated in comparison to the experimental results in the fracture region of the component.rnThis study may contribute to new developments in structures of high structural responsibility with a high level of reliability with respect to the working limits of the component, avoiding unplanned failures in service and catastrophic damages.