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Research on multiple site damage in aging aircraft began popular after the accident of Aloha Airlines. The aircraft experienced an explosive decompression and structural failure because of the emergence of some cracked rivet hole that join into a single long crack. To ensure the safety of flight usi...
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| Format: | Final Project |
| Language: | Indonesia |
| Online Access: | https://digilib.itb.ac.id/gdl/view/17008 |
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| Institution: | Institut Teknologi Bandung |
| Language: | Indonesia |
| Summary: | Research on multiple site damage in aging aircraft began popular after the accident of Aloha Airlines. The aircraft experienced an explosive decompression and structural failure because of the emergence of some cracked rivet hole that join into a single long crack. To ensure the safety of flight using old aircraft, civil aviation authorities have now issued regulations about aging <br />
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aircraft. To comply the standard rules of the applicable aging aircraft, it is necessary to do damage tolerance analysis of CN-235 aircraft owned by PTDI when it enters the end of its age. As part of the development of aging aircraft program PTDI analysis, this research studies about <br />
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fracture mechanics analysis of multiple site damage cases (MSD) of aging aircraft by using boundary element method, simulating crack propagation, and determining the geometry factor from several scenarios cracked MSD cases in the fuselage lap joint . The calculation results in this research will be used as input to calculate the rate of probabilistic crack propagation. To get the geometry factors (β) on lap joint, two-stage modeling is performed. First, modeling lap joint with attachment point. Second, modeling plate with rivet hole, the bearing force earned <br />
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from the first modeling applied along the half circle on the rivet hole. Then stress intensity factor is calculated from the second model in the MSD configurations that have been determined. The crack path and the geometry factor in calculating stress intensity factor are strongly influenced by the crack geometry configuration. <br />
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In the case where crack grow from the edge of the hole, the geometry factor value will decrease proportionally as further the distance from the hole, and will increase when approaching other holes or meeting another cracks. In the fourth crack simulation scenario, the crack tip will begin to turn direction when approaching the frame and propagate perpendicular to the direction of maximum principal stress. <br />
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After conduction of this research, understanding about the habbit of lap joint structure experiencing multiple site damage cases can be more improved. |
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