Stress Intensity Factor and Strain Energy Release Rate in Carbon Epoxy Composite Specimen using ANSYS

In aeronautical industry carbon fiber reinforced polymeric composites are used to manufacture several components such as flaps, aileron, landing gears, doors, nose cone and others. The mechanical property of the composite becomes complex with the addition of fibers. When subjected to compression, tension and flexure tests polymeric composites are susceptible to mechanical damages that can lead to interlayer delamination. Catastrophic failure of the component can occur due to the increase in the external load. Transverse stitching or pinning the fabric across the laminate to hold the plies together to increase inter-laminar shear strength under physical approach. The experiments were conducted for carbon epoxy composite. Mechanical properties such as thickness and elastic ratios are varied to examine the stress intensity factor and strain energy release rate in carbon epoxy composite by using ANSYS FEA software. The objective of the present work is to prepare the three point bend test specimen to estimate the distribution, stress intensity factor and strain energy release rate in carbon epoxy composite using finite element technique. Finite element model is generated in ANSYS and numerical analysis is conducted as per ASTM standards.