摘要
TA17钛合金是航空航天等工程中重要的结构材料,其疲劳裂纹扩展性能直接影响整体结构的安全性和完整性。本文基于Cr2Ni2MoV钢材紧凑拉伸试样斜裂纹疲劳裂纹扩展的试验结果,验证了ABAQUS软件XFEM模块用于分析平面应力状态下疲劳裂纹扩展的有效性,然后采用XFEM模块分析了TA17钛合金及其连接件的疲劳裂纹扩展性能。结果表明降低最大荷载、减小加载比和采用长圆孔型均可有效提高TA17钛合金连接件的疲劳寿命。采用XFEM模块可以预测连接件疲劳寿命的S-N曲线,预测TA17钛合金结构载荷增大33.3%,疲劳寿命减小为原来的1/4,可为工程疲劳设计提供参考依据。
TA17 titanium alloy was an important structural material in aerospace engineering,and its fatigue crack propagation behavior directly impacted the safety and integrity of the entire structure.Based on the fatigue crack growth tests of compact tension specimens of Cr2Ni2MoV steel with oblique initial crack,the XFEM module in ABAQUS software was verified in analyzing fatigue crack propagation performance under plane stress conditions,and then the XFEM module was applied to analyze the fatigue crack propagation properties of TA17 titanium alloy and connection.The research results indicate that reducing the maximum load,decreasing the loading ratio,and utilizing obround holes can effectively enhance the fatigue life of TA17 titanium alloy connection.The S-N curve used to predict the fatigue life of the connection is obtained by adopted of XFEM module.When the load of TA17 titanium alloy is increased by 33.3%,the predicted fatigue life is reduced to 1/4,which provides reference for the engineering fatigue design of the TA17 titanium alloy structure.
作者
匡格平
王群
黄学伟
刘彬
徐文涛
KUANG Geping;WANG Qun;HUANG Xuewei;LIU Bin;XU Wentao(Beijing Institute of Astronautical Systems Engineering,Beijing 100076;School of Mechanics and Safety Engineering,Zhengzhou University,Zhengzhou 450001)
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2024年第2期75-81,共7页
Aerospace Materials & Technology
基金
国家自然科学基金(12202402)。
