Study on Electrically Assisted Stretch Bending of L-section Profile of Titanium Alloy
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摘要: 钛合金型材弯曲构件由于性能优异而逐渐成为先进民用复合材料机身的主要承力构件，其成形质量直接关系到飞机的装配精度。本文针对OT4M钛合金L型材的拉弯成形工艺进行了研究，建立了拉弯过程的解析模型，并在不同的试验条件下进行了多组热单轴拉伸试验来探究型材的热变形行为，利用绝缘模具开展了钛合金型材的电热拉弯成形试验，结果表明，材料的塑性变形能力受变形温度和速度影响显著，拉弯成形时绝缘模具的应用可使钛合金型材保持在相对较高的温度490℃下成形，进而降低了回弹。Abstract: The profile bending parts of Titanium alloy gradually become the main load-bearing components of advanced civil composite material fuselage due to their excellent properties. The forming quality is directly related to the assembly accuracy of aircraft. Here, a study on the stretch bending process of L-section profile of OT4M titanium alloy was conducted. Firstly, a model for stretch bending process was developed. Then, multiple groups of thermal uniaxial tension under different conditions were performed to determine the deformation behavior of profiles. Lastly, the electrically assisted stretch bending were carried out with insulation mold. The results indicate that the plastic deformation capacity of material is significant affected by the temperature and velocity, the application of insulation mold in the stretch bending process can reduce springback by keeping profiles forming at a temperature of 490℃.
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Key words:
- titanium alloy profile /
- stretch bending /
- analytical model /
- uniaxial tension /
- springback
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表 1 符号注释
符号 含义 σ 应力 E 弹性模量 σS 屈服应力 L0 坯料长度 M 弯矩 r1 回弹前半径 w(y) 型材宽度 Rn 中性轴半径 y Y坐标 ε 应变 D 应变硬化常数 εS 屈服应变 upre 预拉伸量 I 截面惯性矩 r2 回弹后半径 b 型材截面高度 yn 中性轴位置 yc 型材形心位置 
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