| Autor: |
Ibrahim, Fadzli, Mustafar, Masliza, Kalil, Shamsiah, Ahmad, Mohd Yazid, Abdullah Sani, Mohd Norhasani |
| Předmět: |
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| Zdroj: |
Defence S&T Technical Bulletin; 2014, Vol. 7 Issue 1, p40-48, 9p |
| Abstrakt: |
This paper presents a study on fatigue life prediction of an aluminium alloy (AA) 7075-T6 coupon using finite element analysis (FEA) simulation. The design part represented a wing lug component of a Royal Malaysian Air Force (RMAF) training aircraft. Linear static analysis indicated that the coupon material could withstand a maximum force of 70 kN with deformation of 1.22 mm before yielding. Then, by applying the most severe condition of real spectrum loading from the aircraft, fatigue analysis demonstrated that the coupon could survive until fatigue life of 3.0 x 107 cycles without considering any mean stress correction, and surface treatment or finishing. Finally, optimisation analysis proved that stress correction using the Gerber equation provided significantly better results than the Goodman equation. It was found that the material using polished surface finishing and nitrided surface treatment provided the best fatigue life result. [ABSTRACT FROM AUTHOR] |
| Databáze: |
Complementary Index |
| Externí odkaz: |
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