某型飞机典型连接结构防腐蚀密封改进及验证

目的研究某型飞机典型连接结构防腐蚀密封改进方法。方法针对飞机典型连接结构的密封剂失效问题提出改进密封工艺和密封结构形式两种方案,并采用实验室加速环境谱进行试验验证研究,以获得解决密封剂失效问题的途径。结果密封剂固化时间由48 h延长至168 h后,典型连接试验件的初始开裂时间由试验1循环延迟至5循环,降低了涂层开裂程度。采用局部密封设计后,试验件的初始腐蚀时间从试验1循环延迟至10循环,试验件外表面螺钉均产生红棕色锈蚀。结论采用局部密封设计形式和将密封剂固化时间由48 h延长至168 h可以有效解决某型飞机典型连接结构现有设计中的密封剂失效问题。

Improvement and Validation about Anti-corrosion Sealing of Typical Assembly Structure of a Certain Aircraft

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.