Accelerated corrosion test and corrosion failure distribution model of aircraft structural aluminum alloy

作     者：柳文林 穆志韬 金平 

作者机构：Airborne Vehicle EngineeringNaval Aeronautical Engineering AcademyYantai 264001China Qingdao BranchNaval Aeronautical Engineering AcademyQingdao 266041China School of Aeronautics Science and TechnologyBeijing University of Aeronautics and AstronauticsBeijing 100081China 

出 版 物：《中国有色金属学会会刊：英文版》 (Transactions of Nonferrous Metals Society of China)

年 卷 期：2006年第16卷第A03期

页      面：1485-1488页

核心收录：

学科分类：080503[工学-材料加工工程] 08[工学] 0805[工学-材料科学与工程（可授工学、理学学位）] 

基　　金：Project(513270301) supponed by the National Natural Science Foundation of China 

主　　题：金属腐蚀 微观结构 损伤机制 密度 失效模型 

摘      要：Based on corrosion damage data of 10 years for a type of aircraft aluminum alloy, the statistical analysis was conducted by Gumbel, Normal and two parameters Weibull distribution function. The results show that aluminum alloy structural member has the corrosion history of pitting corrosion—intergranular corrosion—exfoliation corrosion, and the maximum corrosion depth is in conformity to normal distribution. The accelerated corrosion test was carried out with the complied equivalent airport accelerated environment spectrum. The corrosion damage failure modes of aluminum alloy structural member indicate that the period of validity of the former protective coating is about 2.5 to 3 years, and that of the novel protective coating is about 4.0 to 4.5 years. The corrosion kinetics law of aluminum spar flange was established by fitting corrosion damage test data. The law indicates two apparent corrosion stages of high strength aluminum alloy section material: pitting corrosion and intergranular corrosion/exfoliation corrosion. The test results agree with the statistical fit result of corrosion data collected from corrosion member in service. The fractional error is 5.8% at the same calendar year. The accelerated corrosion test validates the corrosion kinetics law of aircraft aluminum alloy in service.