【摘要】：鈦合金型材作為力學(xué)性能良好的輕質(zhì)材料,被廣泛應(yīng)用于飛行器框梁等骨架零件中,其成形質(zhì)量直接關(guān)系到飛機(jī)的裝配精度、整機(jī)氣動(dòng)外形和使用壽命。為探究TC4鈦合金L型材的熱拉伸變形行為及本構(gòu)關(guān)系,在不同的溫度(600~800℃)和初始應(yīng)變速率(0.00033~0.0083 s~(-1))下進(jìn)行了多組單軸熱拉伸試驗(yàn),根據(jù)應(yīng)力-應(yīng)變曲線特點(diǎn)分析了型材熱拉伸變形行為,并通過采用回歸處理和參數(shù)優(yōu)化的方法建立其復(fù)合型唯象本構(gòu)方程,該模型預(yù)測應(yīng)力和實(shí)測應(yīng)力的最小相關(guān)性系數(shù)R和最大平均相對誤差絕對值A(chǔ)ARE分別為0.9641和7.5%,即建立的本構(gòu)模型能夠高精度表征TC4鈦合金L型材的熱拉伸變形行為,可作為其熱變形有限元模擬的準(zhǔn)確材料模型。
[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，

本文編號(hào)：2384062