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| Crack Failure Analysis of Wing Rear Spar Fitting |
| Received:July 18, 2014 Revised:December 15, 2014 |
| View Full Text View/Add Comment Download reader |
| DOI：10. 7643 / issn. 1672-9242. 2014. 06. 022 |
| KeyWord:rear spar fitting assembly stress stress corrosion crack |
| Author | Institution |
| SHI Fei |
Aircraft Design and Research Institute, AVIC Hongdu, Nanchang , China |
| PENG Zhi-jun |
Aircraft Design and Research Institute, AVIC Hongdu, Nanchang , China |
| YE Bin |
Aircraft Design and Research Institute, AVIC Hongdu, Nanchang , China |
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| Abstract: |
| Objective In order to avoid the repeated occurrence of similar failures, the causes for the crack on the wing rear spar fitting of a certain type aircraft were analyzed. Methods Force analysis was conducted for the wing rear spar fitting, and based on the analysis of the structural assembly relationships of the wing rear spar fitting. FEM was used to calculate the stress on the fitting. Besides, macroscopic and microscopic analyses were performed for the crack fracture to determine the cause for the crack. Results The crack of aircraft wing rear spar fitting was caused by stress corrosion. Conclusion The material of the rear spar fitting LD5 was sensitive to stress corrosion. The fitting was subjected to relatively large assembly tension stress in the assembly process, and the corrosion preventive measure for the surface of the rear spar fitting was defective, therefore stress corrosion cracking occurred in the harsh servicing environment. |
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