By setting surface- to- surface contact and applying bolt loads to simulate the bolt preload, a three-dimensional solid model is established to simulate the bolt connection. The stress maps of the lower wing surface of an aircraft is present after finite element calculation. The part with most serious force is obtained by analysis. Then calculate the fatigue life of the joints by the nominal stress method. fatigue life of. The S-N surface is generated by using MATLAB when the serious factor is equal to 3. 720 2, then the fatigue life and damage at loads of all levels are calculated. According to the miner linear cumulative damage rules, the fatigue life of the connector is calculated. It is found that the fatigue life calculation results of this paper agrees well with the traditional bar elements serious stress factor method results and experimental results.%建立三维实体模型,设置面面接触,并施加螺栓载荷来模拟预紧力来模拟螺栓连接.计算得到某型飞机机翼下壁板螺栓连接试验件的应力云图,分析得出受力最严重部位.通过名义应力法计算该连接件的疲劳寿命.运用MATLAB拟合生成理论应力集中系数为3.720 2下的S-N曲面,从而计算出各级载荷下的疲劳寿命和损伤.根据Miner线性累积损伤准则计算出了连接件的疲劳寿命,与传统的板杆单元应力严重系数法的计算结果以及实验结果进行了对比,发现疲劳寿命计算结果吻合较好.
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