整体加筋壁板裂纹扩展轨迹模拟及控制分析

AN ANALYSIS OF CRACK GROWTH SIMULATION AND CRACK ARREST IN INTEGRALLY STIFFENED PANEL

应用有限元方法并结合裂纹扩展方向判据分析模拟了飞机整体加筋壁板裂纹的扩展轨迹,与实验结果对比证明此方法的有效性;并通过壳单元模型和粘聚区渐进损伤模型详细讨论了影响整体加筋壁板裂纹扩展的筋条参数,研究了壁板筋条对裂纹止裂的控制,并对不同参数下裂纹的应力强度因子和扩展情况作对比分析.文章所述方法和结论对于飞机整体加筋壁板的损伤容限设计具有指导意义.

With the finite element code ABAQUS and the crack propagation direction criterion,crack growth paths in integrally stiffened panels are simulated and the validity of this method is testified by contrast with experiment; Then some parameters that influence crack propagation in integrally stiffened panels are particularly discussed by shell model and cohesive zone model. The effect of stringer to crack arrest is analyzed in detail. The stress intensity factors and crack propagation distances under different stringer parameter are computed and contrasted with each other. The method and conclusion discussed in this paper can be used in damage tolerance design of integrally stiffened panels.