机身
材料科学
结构工程
断裂力学
强度因子
有限元法
内聚力模型
应变能释放率
裂缝闭合
断裂(地质)
非线性系统
复合材料
工程类
物理
量子力学
作者
V.N. Shlyannikov,A.V. Tumanov,А. В. Захаров
标识
DOI:10.1016/j.engfailanal.2019.06.061
摘要
This study focused on the numerical analysis of a cracked fuselage panel of an airplane on the basis of new nonlinear fracture mechanics parameters and concepts. Through finite element analysis (FEA) of the fragment of the fuselage panel with central crack, the governing parameters of the elastic–plastic crack-tip stress field (i.e., In-integral and the plastic stress intensity factor) were determined as a function of the crack length and biaxial loading conditions. Elastic–plastic FEAs of the cracked fuselage panel were performed by considering the accumulated damages in the fracture process zone at the crack tip via special cohesive elements. The curvilinear crack path in the fuselage panel under biaxial loading was predicted on the basis of strain energy density and cohesive zone concepts.
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