【作者】 孙祚东；

【导师】 常铁军；

【作者基本信息】 哈尔滨工程大学 ， 材料学， 2005， 硕士

【摘要】 随着腐蚀环境对飞机结构寿命的影响日益突出,日历寿命已成为当今乃至今后我军飞机面临的严峻问题。本论文较系统地阐述了军用飞机日历寿命研究的工程背景、关键技术、国内外同类研究概况以及存在的问题,着重围绕飞机典型铝合金结构腐蚀发展过程中的腐蚀特征、腐蚀机理、失效模式、腐蚀损伤的概率分布和变化规律、加速腐蚀环境谱的编制及腐蚀当量关系等关键技术问题进行了研究,并在如下几方面取得了较大进展: 1.针对我军飞机的典型服役环境,对铝合金结构防护涂层和金属基体的典型腐蚀失效特征和机理进行了研究,分析了典型铝合金结构的腐蚀发展历程,为制定加速腐蚀环境谱及试验方法提供了依据。 2.针对我军飞机的腐蚀现状,选取某型飞机腐蚀关键结构——机翼前梁腹板为研究对象,开展了加速腐蚀环境谱及加速腐蚀试验方法研究。试验结果表明,按照本文制定的加速腐蚀环境谱和试验方法进行试验,能够较好地加速再现某型飞机前梁腹板在服役期间的腐蚀失效过程。 3.在某型飞机机翼前梁腹板加速腐蚀试验的基础上,提出了采用腐蚀损伤等效建立腐蚀当量关系的方法,并依据服役环境和加速腐蚀环境下飞机结构的腐蚀损伤测量结果,确定了某型飞机前梁腹板加速腐蚀当量关系。 4.选取典型飞机铝合金结构材料LY12CZ为研究对象,采用EXCO溶液浸泡的加速腐蚀试验方法,对LY12CZ的腐蚀损伤的分布特性及其变化规律进行了研究。依据对试验数据的统计分析,建立了Gumbel、正态、双参数威布尔及对数正态四种类型最大腐蚀深度的概率密度函数,并确定了特征参数。在此基础上估算了某型飞机典型结构在给定服役时间所对应的最大腐蚀深度。 5.通过对LY12CZ铝合金在EXCO溶液中的腐蚀行为研究,建立了腐蚀发展过程中3个阶段腐蚀等级与最大腐蚀深度的对应关系,从而初步建立了评定飞机典型铝合金结构腐蚀等级的量化方法。更多还原

【Abstract】 With the increasing effects of corrosive environment on the aircraft structures, calendar life has become a severe trouble of the air force at present and in the future. In this paper, the engineer background, the core technology, the existing status quo and the problem of the military aircraft calendar life at home and abroad were expounded. Several key problems were studied emphatically, such as corrosion feature, corrosion mechanism, failure mode, probabilistic distribution and development of corrosion damage, the accelerated corrosion test environment spectrum and corrosion equivalent relationship. The main progresses of this paper are as following.1. In accordance with the typical service environment of the aircrafts of our air force, the typical corrosion feature and corrosion mechanism in the structures of aluminum alloy base and its anticorrosive coatings were studied, corrosion development of the typical aluminum alloy structures were analyzed. Then the foundation was offered for establishment of the accelerated corrosion test environment spectrum and experimenting method.2. In accordance with the status quo of the aircraft corrosion in our air force, one type of key structures due to corrosion in a certain type aircraft were chosen to investigate accelerated corrosion test environment spectrum and experimenting method. On the basis of experimenting results, above accelerated corrosion test environment spectrum and experimenting method can reproduce corrosion failure of above key structures during their service period.3. Based on above accelerated corrosion test, establishment of corrosion equivalent relationship is determined by contrasting the degree of corrosion.4. The distribution and development of corrosion damage of LY12CZ were studied by the accelerated corrosion experiments in accordance with EXCO immersion test method. Based on statistic of experimental data, the probability density function of maximum corrosion depth accord with Gumbel, Weibull, double parameter Weibull and logarithmic Weibull distribution were formed and their parameters were determined. Then the maximum corrosion depth of typicalstructures of a certain type aircraft was estimated.5. By the investigation of corrosion behavior of LY12CZ immersed EXCO solution, the relationship between the maximum corrosion depth and corrosion degree. Then the corrosion degree in typical aluminum alloy structures of aircraft can be quantified.更多还原