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| Improvement and Validation about Anti-corrosion Sealing of Typical Assembly Structure of a Certain Aircraft |
| Received:October 21, 2015 Revised:February 15, 2016 |
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| DOI：10.7643/issn.1672-9242.2016.01.005 |
| KeyWord:assembly structure anti-corrosion sealing |
| Author | Institution |
| ZHANG Xing |
Structure Corrosion Protection and Control of Aviation Science and Technology Key Laboratory，China Special Vehicle Reach Institute，Jingmen ，ChinaVehicle Reach Institute，Jingmen ，China |
| HE Wei-ping |
Structure Corrosion Protection and Control of Aviation Science and Technology Key Laboratory，China Special Vehicle Reach Institute，Jingmen ，ChinaVehicle Reach Institute，Jingmen ，China |
| ZHANG Deng |
Structure Corrosion Protection and Control of Aviation Science and Technology Key Laboratory，China Special Vehicle Reach Institute，Jingmen ，ChinaVehicle Reach Institute，Jingmen ，China |
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| Abstract: |
| Objective To study method for improving anti-corrosion sealing of typical assembly structure of a certain aircraft. Methods Two schemes were put forward to improve the sealing process and the sealing structure form aiming at the sealant failure problem of typical assembly structure of the aircraft. The two schemes were then validated by carrying out accelerated corrosion test using the typical accelerated corrosion environment spectrum in the laboratory, in order to achieve to solution to the sealant failure problem. Results The crack initiation time of typical assembly structure was deferred from 1 cycle to 5 cycles of the accelerated test and the extent of coating cracking decreased when the curing time of sealant prolonged from 48 h to 168 h. The corrosion/failure initiation time of typical assembly structure using the local sealing design was deferred from 1 cycle to 10 cycles of the accelerated test, and red-brown rust appeared on the outer exterior of the sample. Conclusion Using the form of local sealing design and prolonging the curing time of sealant from 48 h to 168 h could effectively resolve the existing sealant failure problem of typical assembly structure of the aircraft. |
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