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在航空用飞机蒙皮制造过程中,7075铝合金是十分理想的材料。为了更精确地研究并预测7075铝合金的疲劳寿命,对7075-T-651铝合金板材进行了疲劳试验,在应力比R=0.1条件下,测得120~320 MPa不同应力下7075-T-651铝合金板材的疲劳寿命。以试验数据为基础,将灰色系统理论运用到7075-T-651铝合金板材的疲劳寿命预测中,生成GM(1,1)模型,在与试验相同的条件下进行疲劳寿命预测,并将得到的疲劳寿命预测模型S-N曲线与试验数据S-N曲线进行对比。研究表明,所建立的灰色系统理论GM(1,1)模型S-N曲线与试验所得S-N曲线基本吻合,因此,可以通过GM(1,1)模型来预测7075铝合金板材的疲劳寿命。
7075 aluminum alloy is a very good material in the manufacture of aircraft aircraft skin. In order to more accurately study and predict the fatigue life of 7075 aluminum alloy, the fatigue test of 7075-T-651 aluminum alloy sheet was carried out. Under the stress ratio of R = 0.1, the tensile strength of 7075-T- 651 aluminum alloy sheet fatigue life. Based on the experimental data, the gray system theory is applied to the fatigue life prediction of 7075-T-651 aluminum alloy sheet to generate the GM (1,1) model. The fatigue life prediction is carried out under the same conditions as the experiment, The SN curve of fatigue life prediction model is compared with the SN curve of test data. The results show that the S-N curve of the GM (1,1) model is in good agreement with the S-N curve obtained from the test. Therefore, the fatigue life of 7075 aluminum alloy plate can be predicted by GM (1,1) model.