| 摘要: |
| 对宇航紧固件典型规格Ф4.88 mm的TB3钛合金棒材开展了热压缩实验研究，对 TB3钛合金的热压缩流变曲线进行了摩擦和温度双修正，并利用修正后的数据计算出热激活能Q、应力指数n、应力水平参数α以及与温度无关的常数lnA等参数，构建了更准确的Arrhenius双曲正弦本构方程。研究获得的TB3钛合金本构方程，可以为宇航紧固件及精密结构件的冲压成型有限元模拟及工艺优化提供支撑。 |
| 关键词: 热压缩实验 摩擦温度双修正 本构方程 |
| DOI： |
|
| 基金项目:山东省泰山产业领军创新领军人才项目（tscx202312064）；山东省泰山学者青年专家项目（tsqn202211115）；国家自然科学基金（52274397） |
|
| Establishment of Constitutive Equations for TB3 Titanium Alloy Bars Used in Aerospace Fasteners |
| WANG Xiaoliang,ZHANG Hua,YUAN Tiebing |
| (Research and Development Department, Oriental Bluesky Titanium Technology Co., Ltd., Yantai 264003, China;Institute for Advanced Studies in Precision Materials, Yantai University, Yantai 264005, China) |
| Abstract: |
| In this paper, the hot compression tests were carried out on the TB3 titanium alloy bar with a typical specification of Ф4.88 mm for aerospace fasteners. The hot compression rheological curves of TB3 titanium alloy were modified by friction-temperature double correction, and the parameters such as thermal activation energy Q, stress index n, stress level parameter α and temperature-independent constant lnA were calculated by using the modified data. A more accurate Arrhenius hyperbolic sine constitutive equation is constructed. The constitutive equation of TB3 titanium alloy obtained by the study can provide support for the finite element simulation and process optimization of stamping and forming of aerospace fasteners and precision structural parts. |
| Key words: Hot compression test Friction-temperature double correction Constitutive equation |