Fibre-reinforced composites are widely used in aerospace and other high-tech industries. Understanding how their microstructure and the strength of the fibre-matrix interfaces affect their failure properties can lead to manufacturing stronger materials. A recent study at the University of Illinois at Urbana-Champaign developed a model to identify the sensitivities of transverse cracking, one of the key failure processes present in composite laminates, on details of the composite microstructure.
Composite laminates used in Aerospace applications are typically made of layers of carbon fibres with varying orientations embedded in epoxy. For example, the composite laminate can be composed of a carbon/epoxy layer with the fibres oriented in the 90-degree direction sandwiched between two 0-degree plies. The fibres are each about seven microns in diameter, or about one-seventh of the thickness of a human hair.
“We know from experiments that cracks propagate transversely across the 90-degree plane, then stop when they reach the interfaces with the 0-degree plies. So we developed a method that allows us to simulate hundreds of fibres in a realistic system and study how the failure response is affected if we change the location of a single fibre or of many fibres, or the strength of the interface,” said Philippe Geubelle, a professor in the Department of Aerospace Engineering.
In this new method, optical micrographs are taken of the 90-degree ply and the location of all of the fibers are extracted to construct a realistic computational model of the ply. Similar studies have been limited to tens of fibers.
“With the special finite element method we have developed to simulate the transverse cracking of the 90-degree ply, we can simulate hundreds of fibres,” Geubelle said. “The most we’ve done so far is close to 3,000 fibres.”
“Because the crack propagates primarily along the fibre-matrix interfaces, our model emphasizes the cohesive failure of these interfaces,” he said. “In addition, we have developed the ability to extract efficiently the sensitivity of the failure event with respect to the properties of the microstructure including the location and size of the fibres, and the failure properties of the fibre-matrix interfaces. We can also compute the sensitivity of the failure event with respect to the parameters (average, standard deviation, etc.) that define the distribution of these microstructural parameters.”
“Of course, you could get these sensitivities experimentally, with every conceivable variation, to see what the effect is on the failure event,” Geubelle said. “To do this numerically is much more efficient.”
Of course, you could get these sensitivities experimentally, with every conceivable variation, to see what the effect is on the failure event,” Geubelle said. “To do this numerically is much more efficient.
The study, “Transverse Failure of Unidirectional Composites: Sensitivity to Interfacial Properties,” written by S. Zacek, D. Brandyberry, A. Klepacki, C. Montgomery, M. Shakiba, M. Rossol, A. Naja, X. Zhang, N. Sottos, P. Geubelle, C. Przybyla, and G. Jefferson appears in Integrated Computational Materials Engineering.