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Fatigue Life Analysis of Holed Component in Aircraft Stuctures

Mohd Kasim, Muhammad Zulfaqqar (2015) Fatigue Life Analysis of Holed Component in Aircraft Stuctures. IRC, Universiti Teknologi PETRONAS. (Unpublished)

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Aircraft structure with holes was thought to have a significant impact towards fatigue life. Holes had been stress concentrators where high magnitude of stress will be focused around it and potentially be the fatigue crack imitation site. Stress and fatigue analysis were done through finite element simulation to see the effect of stress concentration upon the fatigue life of a plate-with-hole model. This model has been a simple representation of the complex holed aircraft structures. It was found out that the result obtained was consistent to the assumptions made where parts with stress concentration will have a shorter fatigue life due to the severity of damage it face as cyclic loading is being applied to it. The current practice of fatigue life prediction is usually through the process of full scale fatigue simulation which is a cost intensive and a very time consuming process and through lab experiment which considerably complicated and time consuming as well. This study had been focusing on creating a fatigue life estimation that is simple and reliable. In this study, a method that highly focuses on the usage of finite element software has been used and it was found out that the result is convincingly simple and reliable with only 0.5% error.

Item Type: Final Year Project
Academic Subject : Academic Department - Mechanical Engineering - Petroleum
Subject: T Technology > TJ Mechanical engineering and machinery
Divisions: Engineering > Mechanical
Depositing User: Ahmad Suhairi Mohamed Lazim
Date Deposited: 26 Jan 2016 15:26
Last Modified: 25 Jan 2017 09:35
URI: http://utpedia.utp.edu.my/id/eprint/16242

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