Delamination of multidirectional composite laminates at 0°/Theta° ply interfaces

The main objective of this study is to determine test and analysis methods suitable for establishing delamination propagation criteria of non-unidirectional laminates. The crack interface was chosen to be 0°/45° and the tests were focused on obtaining the mode I fracture toughness (GIC). The widely used DCB test was avoided due to anticipated problems with intralaminar damage developing at the ply interface of interest. The ADCB and AMMF methods were used to determine the mode I fracture toughness (GIC) with the amount of mode I close to 100%. The selected stacking sequence resulted in desirable crack propagation behavior; there was no change of delamination plane, an acceptable crack front profile, no initial specimen curvature, and no energy dissipation through global specimen damage. Finite element simulation was found to be the only tool capable of analyzing the experimental data

Modelling Strategies for Predicting the Residual Strength of Impacted Composite Aircraft Fuselages

Aeronautic Certification rules established for the metallic materials are not convenient for the composite structures concerning the resistance against impact. The computerbased design is a new methodology that is thought about to replace the experimental tests. It becomes necessary for numerical methods to be robust and predictive for impact. Three questions are addressed in this study: (i) can a numerical model be “mechanically intrinsic” to predict damage after impact, (ii) can this model be the same for a lab sample and a large structure, and (iii) can the numerical model be predictive enough to predict the Compression After Impact (CAI)? Three different computational strategies are used and compared: a Cohesive Model (CM), a Continuous Damage Model (CDM) coupling failure modes and damage, and a Mixed Methodology (MM) using the CDM for delamination initiation and the CM for cracks propagation. The first attempts to use the Smooth Particle Hydrodynamics method are presented. Finally, impact on a fuselage is modelled and a numerical two-stage strategy is developed to predict the CAI