發(fā)布時(shí)間：2018-12-29 19:46

【摘要】：采用有限元法對(duì)某型飛機(jī)鈦合金鈑金件熱沖壓成形過程進(jìn)行數(shù)值模擬,研究了成形溫度、變形速度以及摩擦系數(shù)對(duì)成形零件壁厚分布的影響。通過正交試驗(yàn)方法建立了有限元模擬的正交試驗(yàn)組,采用極差分析法確定各因素的影響程度的主次關(guān)系,并得到最優(yōu)的工藝參數(shù)水平組合。結(jié)果表明:成形溫度對(duì)壁厚分布影響最大,最優(yōu)工藝參數(shù)為成形溫度為675℃、變形速度為1 mm·min~(-1)、摩擦系數(shù)為0.3。根據(jù)優(yōu)化結(jié)果,對(duì)鈦合金進(jìn)行熱沖壓成形試驗(yàn),實(shí)際成形效果與模擬結(jié)果較為吻合。
[Abstract]:The influence of forming temperature, deformation speed and friction coefficient on the wall thickness distribution of a certain aircraft titanium alloy sheet metal was studied by means of finite element method (FEM). The orthogonal test group of finite element simulation was established by orthogonal test method. The primary and secondary relationship of the influence degree of each factor was determined by the range analysis method, and the optimal level combination of process parameters was obtained. The results show that the forming temperature has the greatest influence on the wall thickness distribution. The optimum process parameters are forming temperature of 675 鈩，

本文編號(hào)：2395304