Perpustakaan Digital ITB

Carbon Fiber Reinforced Composites (CFRP) is one type of composite material that is often used in the aviation industry. The strength of the composite structure can decrease if it is damaged. Delamination is one mode of damage that often occurs and is quite dangerous because it is difficult to detect visually. According to Meng-Low[3], the crack resistance of a composite structure will decrease with decreasing temperature. This is quite dangerous because composite structures at low temperatures are more prone to cracking or failure. In the journal, Meng-Low stated that material characteristics which associated with resistance to delamination is the fracture energy and nominal stress from the interlaminar zone. This research will focus on numerical simulations of low velocity impacts on composite laminate structures with various fracture energy and nominal stress. Analysis on composite laminates was carried out numerically using ABAQUS software. To observe delamination in each composite layer numerically, it will be modeled using the cohesive zone model. Material characteristics that change modeled based on the reference journals. In this study, an analysis of the different modeling methods will also be carried out, namely the comparison between clustering and non-clustering methods. An analysis of the differences between the two methods will be performed, and the results will be compared with an experimental reference journal to test the validity of the model with the experimental result. The expected results of this study are the suitability of the results of numerical analysis using non-clustering method and the application of the cohesive zone model with the experimental method of the reference journal. Then, a physical analysis of the phenomenon of delamination will be carried out due to the change of fracture energy, nominal stress, and the impact energy