Numerical Analysis on Delaminated Stiffened Panel with Three Point Bending Method through Impact Loading

• Main Author: Setyawan (NIM : 13113144), Arief
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/21220
• Institution: Institut Teknologi Bandung

Flight industry in Indonesia has gone through an increasing demand specifically on comercial transportation service time by time. For increasing the efficiency of flight operational, the utilization of lighter material yet fulfill the structural strength which is needed is conducted, which is the using of composite material. Composite material has higher specific strength than aluminium or steel that is usually used before. Some of aircraft components using a composite material are tail, panel on fuselage and wing, and stiffener. Panel that is strengthened by stiffener is called stiffened panel. One of its function is to strengthen the aircraft structure. <br /> <br /> <br /> Composite material could experience a failure. On composite, there are various failure modes which one of them is delamination. Delamination on composite panel could happened because of crash from airport ground vehicle, tools drop, operator’s weight during maintenance, etc. The effect of delamination size on absorbed energy by loading was studied on this final project. <br /> <br /> <br /> Stiffened panel is analyzed numerically through three point bending method by LS Dyna software. Simulation was conducted on a simple composite panel and stiffened panel. Energy that is absorbed by the loading was decreasing as the initial delamination got wider.