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首页> 外文期刊>Fatigue of Aircraft Structures >Experimental and Theoretical Investigations of Fatigue Crack Growth in D16 Alloy
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Experimental and Theoretical Investigations of Fatigue Crack Growth in D16 Alloy

机译:D16合金疲劳裂纹扩展的实验与理论研究。

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摘要

In this work the arising and development of fatigue crack in aluminium alloy D16, taking into consideration the influence of notch in the form of hole with incisions which were done on its sides were tested. The process of working out of tests' programme was preceded by numeric analysis of stresses pattern and strains distribution in the zone of notch's influence which was focused on determination of stresses' face values. To examine stress and strain distributions, the specialised FEM software (MSC. Patran and MSC. Nastran) was applied. Findings have been presented in the form of a statement of ??max and ?μmax values, and functions of the following factors: a??, a?μ, and ak, computed on the grounds of these values for both different distances from the bottom of the notch and assumed levels of loading the specimens. Theoretical analysis has been supplemented with experimental investigation into the microstructure of fatigue-fracture surfaces in the area of crack initiation and that of fatigue of a propagating crack. The paper has been intended to present a model of the probabilistic estimation of fatigue life of structural members. The model has been based on the deterministic description of the cracking. Analyzed were components with notches in the form of centrally located holes with side cuts. In the method of probabilistically approaching the crack propagation, some dependences have been used that take account of the presence of areas showing plastic strains in front of crack tips. It has been assumed that the cracking can be modeled on the grounds of some general-purpose quantity used to describe the energy state in the area of the crack tip, i.e. the Rice's integral (J). The formulated computational model has been used to estimate fatigue life of model components made of D16 alloy. Experimental work was carried out using some flat specimens with centrally positioned holes. They were exposed to flat bending at R = 0. Analytical and experimental results have shown pretty good conformity.
机译:在这项工作中,考虑到侧面有切口的缺口形式的缺口的影响,测试了D16铝合金疲劳裂纹的产生和发展。在进行测试程序之前,先对缺口影响区域的应力模式和应变分布进行数值分析,然后重点确定应力的面值。为了检查应力和应变分布,使用了专用的FEM软件(MSC。Patran和MSC。Nastran)。结果以Δmax和Δμmax值以及以下因子的函数的形式表示:aΔ,aΔμ和ak,是根据这些值对距Δ的不同距离计算得出的。缺口的底部和假定的试样水平。对实验分析进行了理论分析,并补充了对裂纹萌生区域和扩展裂纹疲劳区域的疲劳断裂表面微观结构的实验研究。本文旨在提供一种模型估计结构构件疲劳寿命的模型。该模型基于裂纹的确定性描述。分析了带有缺口的组件,这些缺口的形式为位于中心的带有侧面切口的孔。在以概率方式接近裂纹扩展的方法中,已经使用了一些依赖关系,这些依赖关系考虑到在裂纹尖端前面存在显示塑性应变的区域。已经假设可以基于描述裂纹尖端区域中的能量状态的一些通用数量,即赖斯积分(J),来模拟裂纹。公式化的计算模型已用于估算由D16合金制成的模型部件的疲劳寿命。实验工作是使用一些带有居中位置孔的扁平标本进行的。它们在R = 0时受到平面弯曲的影响。分析和实验结果显示出很好的一致性。

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