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  2019, Vol. 40 Issue (2): 137-146    DOI: 10.19636/j.cnki.cjsm42-1250/o3.2018.045
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航空铝合金力学与电化学耦合点蚀损伤模型研究
妙远洋1,2,吕胜利2
1. 西北工业大学航空学院
2. 西北工业大学无人机特种技术国家重点实验室
Micromechanics-based Modeling of Pitting Corrosion Damage in Aero Aluminum Alloy
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摘要 点蚀是航空铝合金材料在服役环境下常见的损伤形式,点蚀损伤会导致材料性能的下降, 严重地威胁着结构的承载能力。作为承力构件,航空铝合金不仅承受环境腐蚀的作用,还承受应力作用。论文根据点蚀基本原理,引入细观损伤变量孔隙率,考虑力学化学效应,建立了点蚀损伤弹性模量计算模型。使用2219铝合金,进行加速腐蚀试验和单向拉伸试验,利用显微扫描技术研究了点蚀坑深度随时间和载荷的变化,并对腐蚀后试验件的损伤宏观形貌进行观察分析。根据拉伸实验结果,对模型的正确性进行验证。模型计算与实验结果的对比证明了本文方法的可行性与正确性。
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妙远洋 吕胜利
关键词 航空铝合金点蚀损伤孔隙率力学化学效应弹性模量    
Abstract:Pitting corrosion is a common form of damage in aviation aluminum alloy materials in service. Pitting damage can lead to the deterioration of material properties, impair the bearing capacity of the structure, and seriously affect the flight safety and service life of the aircraft. Used for the bearing members, the aviation aluminum alloys are subjected to not only environmental corrosion, but also stress. Therefore, it is of great theoretical and practical significance to study the pitting corrosion damage of aluminum alloy under stress. According to the basic principle of pitting, this paper introduces the porosity of the damage variable which characterizes the hole damage of the material. Considering the mechanical chemistry effect, the calculation model of the elastic modulus of pitting damage material under stress is established, which provides a necessary foundation for the prediction of the deterioration of structural bearing capacity. Accelerated corrosion test and uniaxial tensile test were carried out using the 2219 aluminum alloy. The SZX12 research-grade microscope and laser range finder were used to study the change of pitting depth with time and load. The pitting porosity and stress tested at different times were in exponential relationship, verifying the effect of mechanical chemistry on the porosity of pitting damage. It is proved that a corrosion pit in the aluminum alloy can be simulated as a semi-ellipsoid; that is, the pit can be regarded as an ellipsoidal hole damage in the material caused by the corrosive action. The macroscopic morphology of the damaged specimens after corrosion was observed and analyzed, and the influences of corrosion time and applied load on pitting damage were further verified. The comparison between the calculated results and the experimental data shows the correctness of the method and the feasibility to apply the damage mechanics to the description of corrosion damage. This study also provides a new idea for the quantitative description of corrosion damage under stress.
收稿日期: 2018-08-17      出版日期: 2019-04-11
通讯作者: 吕胜利     E-mail: 1004078963@qq.com
引用本文:   
妙远洋 吕胜利. 航空铝合金力学与电化学耦合点蚀损伤模型研究[J]. , 2019, 40(2): 137-146.
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