TC4钛合金L型材热拉伸变形本构方程研究
发布时间：2018-12-17 10:11
【摘要】：钛合金型材作为力学性能良好的轻质材料,被广泛应用于飞行器框梁等骨架零件中,其成形质量直接关系到飞机的装配精度、整机气动外形和使用寿命。为探究TC4钛合金L型材的热拉伸变形行为及本构关系,在不同的温度(600~800℃)和初始应变速率(0.00033~0.0083 s~(-1))下进行了多组单轴热拉伸试验,根据应力-应变曲线特点分析了型材热拉伸变形行为,并通过采用回归处理和参数优化的方法建立其复合型唯象本构方程,该模型预测应力和实测应力的最小相关性系数R和最大平均相对误差绝对值AARE分别为0.9641和7.5%,即建立的本构模型能够高精度表征TC4钛合金L型材的热拉伸变形行为,可作为其热变形有限元模拟的准确材料模型。
[Abstract]:Titanium alloy profile, as a light material with good mechanical properties, is widely used in skeleton parts such as frame and beam of aircraft. Its forming quality is directly related to the assembly accuracy of aircraft, the aerodynamic shape and service life of the whole aircraft. In order to investigate the hot tensile deformation behavior and constitutive relationship of TC4 titanium alloy L profile, a series of uniaxial thermal tensile tests were carried out at different temperatures (600 鈩，
本文编号：2384062
[Abstract]:Titanium alloy profile, as a light material with good mechanical properties, is widely used in skeleton parts such as frame and beam of aircraft. Its forming quality is directly related to the assembly accuracy of aircraft, the aerodynamic shape and service life of the whole aircraft. In order to investigate the hot tensile deformation behavior and constitutive relationship of TC4 titanium alloy L profile, a series of uniaxial thermal tensile tests were carried out at different temperatures (600 鈩，
本文编号：2384062
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