FOUR-POINT BENDING NUMERICAL SIMULATION OF COMPOSITE PLATE WITH TRANSVERSE CRACK

• Main Author: Faridah Alfani, Fazat
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/36495
• Institution: Institut Teknologi Bandung

Today, the use of composite materials for human needs is increasingly high, especially in the aerospace industry. The applications of composite materials are increase every year. Therefore, the use of composite materials must be followed by the feasibility of supporting structures. Failure in composite structures must be avoided both in the production process and when the structure is used. Failures in aircraft structures can be mechanical, thermal or chemical and environmental failures that occur due to various flight conditions. Microscopic failures such as micro cracks occur due to impact loads and also internal stresses. Micro crack is the biggest cause of material failure because it is difficult to detect and inspected visually. In addition, induced structural fragments will cause a reduction in material properties such as the strength, stiffness and dimensional stability of the composite material. This research is a combination of two simple simulations, XFEM crack modeling and bending modeling with four loading points. The specimen used is unidirectional carbon-epoxy composite rectangular plate. This numerical simulation studies the crack propagation and delamination on the plate. Interface modeling between lamina using cohesive parts with cohesive elements. The results of the modeling will be compared with the experimental results from the reference paper. XFEM crack modeling and bending modeling using Abaqus/Standard has limitations. Limitations make modeling cannot be done perfectly, one of which is the emergence of shear-locking phenomena. The shear-locking phenomenon produces different modeling result compared to the experimental results.