Computational assessment of nonlinear fracture resistance parameters for cracked fuselage panel under biaxial loading.

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., I n -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. • This study focused on the numerical analysis of a cracked fuselage panel of an airplane on the basis of new nonlinear fracture mechanic parameters and concepts. • The governing parameters of the elastic–plastic crack-tip stress field 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 damage 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. [ABSTRACT FROM AUTHOR]