| 李宏民,唐宇彬,赵朋飞,张翔羽,张生鹏.飞行器舱体轻质合金蠕变行为建模与寿命预测[J].装备环境工程,2025,22(5):7-12. LI Hongmin,TANG Yubin,ZHAO Pengfei,ZHANG Xiangyu,ZHANG Shengpeng.Modeling and Life Prediction of Creep Behavior of Lightweight Alloys for Aircraft Cabin Structures[J].Equipment Environmental Engineering,2025,22(5):7-12. |
| 飞行器舱体轻质合金蠕变行为建模与寿命预测 |
| Modeling and Life Prediction of Creep Behavior of Lightweight Alloys for Aircraft Cabin Structures |
| 投稿时间：2025-03-28 修订日期：2025-05-12 |
| DOI：10.7643/issn.1672-9242.2025.05.002 |
| 中文关键词: 蠕变 蠕变损伤 ZM6合金 本构模型 位错滑移 晶粒粗化 寿命预测中图分类号:V416 文献标志码:A 文章编号:1672-9242(2025)05-0007-06 |
| 英文关键词:creep creep damage ZM6 alloy constitutive model dislocation slip grain coarsening life prediction |
| 基金项目:技术基础科研项目(JSHS2022208B001) |
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| Author | Institution |
| LI Hongmin | School of Reliability and Systems Engineering, Beihang University, Beijing 100191, China |
| TANG Yubin | Aerospace Science and Industry Defense Technology Research and Test Center, Beijing 100854, China |
| ZHAO Pengfei | Aerospace Science and Industry Defense Technology Research and Test Center, Beijing 100854, China |
| ZHANG Xiangyu | Aerospace Science and Industry Defense Technology Research and Test Center, Beijing 100854, China |
| ZHANG Shengpeng | Aerospace Science and Industry Defense Technology Research and Test Center, Beijing 100854, China |
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| 中文摘要: |
| 目的 建立飞行器舱体轻质合金蠕变本构模型，预测其蠕变损伤行为规律及其寿命。方法 在蠕变损伤力学模型基础上，引入由材料蠕变机制确定的稳态蠕变速率模型，建立改进的蠕变损伤模型；开展单轴拉伸蠕变试验和材料微观分析，确定合金蠕变机理；考虑蠕变机理对合金蠕变速率的影响，建立相应的无量纲损伤因子，将其代入改进的蠕变损伤模型，得到合金的蠕变本构模型。结果 根据ZM6合金的蠕变试验和材料微观分析结果，确定ZM6合金的蠕变机理为位错滑移，蠕变损伤类型为晶粒粗化。通过数据拟合的方法确定了ZM6合金蠕变本构模型的模型参数，将ZM6合金蠕变本构模型的预测结果与试验结果进行对比，对稳态蠕变阶段的预测结果误差小于5%。结论 该模型可有效预测飞行器舱体轻质合金蠕变行为规律，为评估其贮存寿命提供了依据。 |
| 英文摘要: |
| The work aims to establish a creep constitutive model for the lightweight alloy of the aircraft cabin structures to predict the creep damage behavior and its life. Based on the creep damage mechanics model, a steady-state creep rate model determined by the material creep mechanism was introduced to establish an improved creep damage model. Uniaxial tensile creep tests and material microstructure analysis were conducted to determine the creep mechanism of the alloy. Considering the influence of the creep mechanism on the creep rate of the alloy, a dimensionless damage factor was established and substituted into the improved creep damage model to obtain the creep constitutive model of the alloy. According to the creep test and material microstructure analysis results of ZM6 alloy, it was determined that ZM6 alloy had the dislocation slip creep mechanism and grain coarsening creep damage. The model parameters of the ZM6 alloy creep constitutive model were determined by data fitting method. The prediction results of the ZM6 alloy creep constitutive model were compared with the test results, and the prediction error of the steady-state creep stage was less than 5%. In conclusion, this model can effectively predict the creep behavior of the lightweight alloy in the aircraft cabin structures, providing a basis for evaluating its storage life. |
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