Experimental and Numerical Study of Damages Induced by Low-Velocity Impact on 4th Generation Composite Laminates
Résumé
The use of composite fiber reinforced polymer (CFRP) structures in the aircraft industry needs to demonstrate that they satisfy the same safety requirements as for metal structures. Among these requirements, impact damage tolerance is a major sizing criterion for those structures. Impact induce complex out-of-plane loadings that results on large damage extensions. Experimental campaigns are realized at the industrial level to design composite structures but, it induces long and costly development for innovative solutions. Finite Element Model (FEM) is a good tool for sizing efficiently composite components even those exposed to impact. Unfortunately, numerical models developed by academics are too complex to be used in the industry. Besides, due to the highly non-linear problem, explicit solvers are used to avoid convergence issues, which require an expertise in the results verification. In this way, we present a damage model developed at the ONERA [1,2] to predict the progressive rupture of last generation composite laminates subjected to low-velocity impact (LVI)/low-energy impact (LEI). This model has been developed with a fair level of complexity in order to be used in aeronautical industries. This material has thick resin layers at each interface between each plies, which increase the toughness of the laminate. In order to understand damage mechanisms of this specific material when subjected to LVI/LEI, an investigation of impact damages has been carried out in this study. Since LVI/LEI do not enter in the scope of fast transient dynamics, we use an implicit integration scheme and the first results using the damage model are compared with the experimental data given by experimental testing.
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