The effect of geometrically nonlinear behaviour on the calculation of energy release rates in a centrally cracked tensile test plate and a damaged pressurized fuselage panel is evaluated. Tensile plate test specimens are used to generate allowables for the failure prediction of damaged fuselage panels under pressure load. Both the tensile plate and the damaged fuselage panel deform nonlinearly under loading. However, the nonlinear behaviour of each is different. The tensile plate behaves nonlinearly after it buckels transversely in the cracked region well before failure, while the damaged pressure loaded fuselage behaves nonlinearly due to a membrane stress stiffening effect. Deformations predicted by nonlinear analyses for the test plate and the fuselage panel are significantly different from those predicted by linear analyses. Therefore, energy release rate allowables derived from cracked flat plate tests based on linear deformation theory need to be adjusted before being applied to damaged pressurized fuselage panels. Two methods are presented to evaluate the effect of nonlinear deformations on energy release rate calculations. One is the virtual crack closure technique (VCCT) and the other is the gradient method.
Computation of energy release rates for cracked composite panels with nonlinear deformation
Berechnung der Energiefreisetzung für Verbundwerkstoffplatten mit Rissen bei nichtlinearer Verformung
1995
15 Seiten, 15 Bilder, 26 Quellen
Conference paper
English
Computation of Energy Release Rates for Cracked Composite Panels with nonlinear Deformation
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