#TITLE_ALTERNATIVE#

• Main Author: SIENA HARYADI MOEL (NIM : 13613018), STEFANUS
• Format: Final Project
• Language: Indonesia
• Online Access: https://digilib.itb.ac.id/gdl/view/24379
• Institution: Institut Teknologi Bandung

In the aircraft structure, cracked defect often occurs, especially on skin located at fuselage and skin located on the wing. For economic reason, aircraft structure done repair so that the lifetime of the structure increase and the aircraft can fly longer. Therefore high technology repair method is needed. Not only for patching up the hole or crack, but also increase the lifetime of the aircraft as long as possible. It becomes something that continues to be develoed. Furthermore, ease of manufacturing of repair method, cost and consequence to aircraft performance still calculated. So came some repair method that can be used. <br /> <br /> <br /> <br /> <br /> In this final project done simulation and modeling to study and analysis three different repair method with three different loading.Study of crack initiatin location, the direction of crack propagation and stress intensity factor that known from simulation, with the scope that used in this study, give the conclusion that repair method mechanically fastener dobler is the most efective For simulation and modeling of crack propagation doing it using ABAQUS perangkat lunak with Extended Finite Element Method (XFEM). While simulation and modeling to calculate stress intensity factor for three repair method is using ABAQUS perangkat lunak with finite element method.