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研究了飞机整体翼梁结构中止裂筋条对裂纹转折特性的影响。采用ABAQUS建立有限元模型,计算了应力强度因子和T应力,通过一阶最大切向应力理论和二阶最大切向应力理论预测裂纹转角,并与试验结果进行对比,发现二阶理论能够更准确地模拟裂尖靠近筋条时的急速转折现象;通过改变腹板厚度,讨论其对裂纹转折的影响。结果表明:筋条相对腹板刚度比越大,裂纹转角越大,对整体翼梁的止裂效果越好。
The effect of the breaking bars in the whole spar structure of aircraft on the crack transition characteristics was studied. The ABAQUS finite element model was used to calculate the stress intensity factor and the T stress. The first-order maximum tangential stress theory and the second-order maximum tangential stress theory were used to predict the crack angle. Compared with the experimental results, it was found that the second-order theory can be more accurate Simulate the rapid turning phenomenon when the crack tip is close to the tendons. By changing the web thickness, the influence on the crack transition is discussed. The results show that the greater the stiffness ratio of the web to the web, the larger the crack angle, the better the crack arrest effect on the whole spar.