7050航空铝合金“单因素”本构模型参数与温度相关性研究

从理论和实验两方面研究7050航空铝合金"单因素"本构模型中参数与温度的相关性.通过位错理论分析和进行材料基本关系式推导指出铝合金材料模型受温度的影响.设计准静态压缩实验和高速冲击压缩实验研究材料的静、动态力学性能.通过对试验数据的分析、拟合和比较,得出7050航空铝合金"单因素"本构模型中的参数与温度相关的结论.根据试验结果建立材料参数与温度之间的数学映射,并在此基础上构建7050航空铝合金单因素"本构模型,最后进行切削实验验证模型的正确性.7050航空铝合金"单因素"本构模型的建立为进一步开展切削加工有限元模拟和进行工艺优化奠定基础.

Study on Correlation between Parameters of "Single Factor" Constitutive Model and Temperature for 7050 Aviation Aluminum-Alloy

To investigate the correlation between parameters of "single factor" constitutive model and temperature for 7050 aviation aluminum-alloy,theoretic analyses and material experiments were employed.Based on dislocation theory and material functional relations,an analysis shows that material model is deeply affected by temperature.The quasi-static compression experiments and high-speed impact compression experiments were conducted in order to study the static and dynamic mechanics performance.By the least squares best fit to the available experimental data,material parameters were found.Analyses of experimental curves and comparison of material parameters show that parameters of the "single factor" constitutive model are temperature dependent.Using the mathematical mapping between material parameters and temperature,"single factor" constitutive model for 7050 aviation aluminum-alloy was established,which was proven to be correct by comparing with experimental measurements.The work of this paper provides a useful insight for understanding the material constitutive model and helps to develop further finite element simulation and technology optimization of cutting process for 7050 aviation aluminum-alloy.