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| Fatigue Crack Extension Model of Aluminium Alloy with Prior Corrosion Damage Based on Localised Corrosion Damage |
| Received:July 19, 2014 Revised:December 15, 2014 |
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| DOI：10. 7643 / issn. 1672-9242. 2014. 06. 015 |
| KeyWord:pre-corrosion fatigue pitting rate fatigue crack growth aluminum alloy |
| Author | Institution |
| KONG Guang-ming |
Qingdao Campus of Naval Aeronautical Academy, Qingdao , China |
| LI Xu-dong |
Qingdao Campus of Naval Aeronautical Academy, Qingdao , China |
| MU Zhi-tao |
Qingdao Campus of Naval Aeronautical Academy, Qingdao , China |
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| Abstract: |
| Objective To establish a modified model for pre-corrosion fatigue crack growth rate of aluminum alloy. Methods Considering that the local damage around the crack tip was more reasonable for accelerating crack growth rate in corrosive environment, the pitting rate, which was a parameter characterizing the influence of corrosion in local environment, was used to correct the corrosion fatigue crack growth rate. Results The experimental results were in good agreement with predictions of the amended fatigue crack growth rate model for corroded aluminum alloy specimens. Conclusion The corrected aluminum alloy pre-corrosion fatigue crack growth rate model was reasonable and effective, and the test data and the prediction model could provide a reference for the damage tolerance design of navy aircraft structure. |
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