#TITLE_ALTERNATIVE#

• Main Author: I KADEK VERY ADE ANDREANA (NIM : 13613069)
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/22509
• Institution: Institut Teknologi Bandung

This research explains the behavior of composite material Carbon Epoxy. Currently, the largest composite material need is seen in the Aerospace Industry and followed by the Automotive Industry. Composite Carbon Epoxy is material composed from composite fibers that have strength properties greater than light and strong. This makes composite materials often used in aircraft and automotive structures. The Automotive or Aerospace industry begins to use composite materials, especially CFRP on the frame structure. For example, at present 50% to 70% of aircraft structures have been made from composite materials. The frame structure of the aircraft becomes very important because the frame of the wings, body and the tail is part of the Primary Structure. The regulation of the Airworthiness composite structure becomes a step that must be filled and approved before the material is used in frame structures. Proof of regulation composite structure can be done by studying behaviour experimentally and numerically of material composite. <br /> <br /> <br /> <br /> <br /> Numerical opproach using XFEM on the Epoxy IM7 / 8552 Carbon material is performed based on Overheight Compact Tension (OCT) test. Validation of results simulation data are shown by comparing experimental OCT results conducted by Xiangqian Li on Cross-ply dispersed IM7 / 8552 symmetric composition with thickness of 2 mm. Numerical simulation studies include the effect of angle orientation of Cross-ply Simulation, Isotropic Quasi, and also Symmetric Angle of ply on dispersed or blocked form. Characteristic differences will be seen in the results of numerical simulation studies which show that the strength of the material is greatly composed by the composition of composite forming fiber. The simulation results show the Cross-ply Symmetric on the dispersed composition can withstand higher than the angle and quasi isotropic ply. In the comparison of the dispersed and blocked arrangement we will see that the blocked result is capable of holding higher than the dispersed arrangement. The study of the effect of fiber and composition will be one of the considerations in choosing a composite composition on aircraft and automotive structures. The determination of composite compositions will be known by the needs and types of loading that occur.