摘要
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。
We establish the FE model of the crack-arresting stringer of the integrated wing beam structure with the finite element software ABAQUS and calculate its stress intensity factors and T-stress.We predict the crack turning angle of the crack-arresting stringer with the first-order maximum tangential stress theory and the second-order maximum tangential stress theory and then compare the prediction results with the experimental results.The comparison results show that the second-order maximum tangential stress theory can predict the sharp turning at the tip of the crack near the crack-arresting stringer more accurately than the first-order one.Then we discuss the effects of the various thicknesses of the wing beam structure on the crack turning.The discussion results show that the crack turning angle increases with increasing stiffness ratio of the crack-suppressing stringer,thus being more effective for arresting the cracks of the integrated wing beam structure.
出处
《机械科学与技术》
CSCD
北大核心
2012年第1期59-62,共4页
Mechanical Science and Technology for Aerospace Engineering
关键词
整体翼梁
T应力
损伤容限
应力强度因子
裂纹扩展轨迹
有限元
integrated wing beam structure
T-stress
crack-arresting stringer
stress intensity factor
crack turning angle
finite element method
