The results of an analytical study of the nonlinear response of stiffened fuselage shells with long cracks are presented. The shells are modeled with a hierarchical modeling strategy and analyzed with a nonlinear shell analysis code. This modeling strategy and analysis method accurately accounts for global and local response phenomena. Results are presented for combinations of internal pressure and mechanical bending and vertical shear loads, and the effects of crack location and orientation on the shell response are described. These results indicate that the nonlinear interaction between the in-plane stress resultants and the out-of-plane displacements near a crack significantly affect the shell response and the strain energy release rate (or the stress intensity factors) associated with the crack. The results also show that a combination of internal pressure and an axial compression load applied to a panel with a longitudinal crack causes larger values of the strain energy release rate associated with the crack than a combination of internal pressure and an axial tension load or internal pressure acting alone. The results also indicate that a vertical shear load has a significant effect on the local stress intensity factors of a fuselage side panel with a longitudinal crack. In addition, the results indicate that the shell curvature may affect the response of a shell with a cercumferential crack differently than it affects the response of a shell with a longitudinal crack.
Nonlinear response of damaged stiffened shells subjected to combined internal pressure and mechanical loads
Nichtlineares Verhalten beschädigter, ausgesteifter Rümpfe bei kombinierter Belastung durch Innendruck und mechanische Lasten
1995
13 Seiten, 18 Bilder, 1 Quelle
Aufsatz (Konferenz)
Englisch
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