Influence of interface ply orientation on delamination growth in composite laminates

The standard experimental procedures for determining the interlaminar fracture toughness are designed for delamination propagation in unidirectional specimens. However, in aerospace structural components, delamination usually occurs between plies at different orientations resulting in different damage mechanisms which can increase the value of the fracture toughness as the delamination propagates. Generally, numerical analyses employ the value measured at the delamination onset, leading to conservative results since the increase resistance of the delamination is neglected. In this paper, the fracture toughness and the R-curves of carbon/epoxy IM7/8552 are experimentally evaluated in coupons with delamination positioned at 0°/0° and 45°/−45° interfaces using Double Cantilever Beam (DCB) and Mixed-Mode Bending (MMB) tests. A simplified numerical approach based on the Virtual Crack Closure Technique (VCCT) is developed to simulate variable fracture toughness with the delamination length within a Finite Element code using a predefined field variable. The results of the numerical analyses compared with the experimental data in terms of load-displacement curves demonstrate the effectiveness of the proposed technique in simulating the increase resistance in delamination positioned between plies at 45°/−45° interface.

Experimental investigation of CFRP fracture toughness by delamination type

The results of analyzing fracture toughness in carbon fiber-reinforced plastics by the type of delamination are presented in the article. The goal of this paper is investigation of delamination propagation process and fracture mechanics parameters in modern CFRPs. This type of composite materials is extensively used in high load aerospace structures. Modern polymer composite materials are the subject of our research. A technique of manufacturing specimens for testing by the vacuum infusion process is presented in the paper. Experimental investigation of delamination propagation process by mode I and II was performed with the aid of up-to-date testing equipment using a special type of specimens such as a double cantilever beam. Researchers usually use this type of specimen for the validation of their numerical models. Critical values of energy release rate and load-displacement curves were obtained for two types of material unidirectional and woven. Examination of microscopic sections of the tested specimens using an optical microscope allowed us to identify the specific fracture mechanisms of material structure.

Analyses of criticality for multiple-site delaminations in the flap spar of Finnish F/A-18 aircraft

Metal-composite airframes will suffer various defects during their lifetime. One category of defects is composite laminate delamination. This study evaluates the criticality of delaminations existing around adjacent fastener holes in the carbon-fibre-reinforced plastic spar web of the F/A-18 aircraft’s trailing-edge flap. The evaluation is based on experiments and analyses. First, an intensive experimental program for determining necessary material values of F/A-18 is described. Multiple delaminations of the flap spar web are then modelled by varying the set of delaminated hole edges and the interface of delamination. The interaction of defects at the start of delamination propagation is studied via the developed interaction parameter. The results suggest that the interaction parameter can show significant differences in the interaction per delamination case and that the interface of delamination is an important variable. Finally, operator-dependent control parameters are studied, and it is found that the criticality of a delamination case is merely dependent on true material parameters.