Abstract
This paper aims to analyze the multi-effects of the glass fiber reinforced polymer (GFRP) composite patch to repair the inclined cracked 2420-T3 aluminum plate. Three-dimensional finite element method (FEM) was used to study the effect of GFRP composite patch with different stacking composite laminate sequence, [0°]4, [90o]4, [45o]4, [0o/45o]2s and [0°/90°]4s on the crack driving force, J-integral, of inclined cracked 2420-T3 aluminum plate. Furthermore, the effects of patch geometry, number of layers, single or double side patch and crack incline angle are described. The present results show that the patch has a high effect in case of a crack in pure mode I. Furthermore, the effectiveness of the composite patch is increasing with the crack length increases. Moreover, the efficiency of the composite patch has a high effect by changing the fiber orientation, the number of layers, and the single or double side patch.
Highlights
I n aircraft applications, service life is very important
Bouiadjra et al [6] compared the performances of using composite and metallic patches for repairing cracked aircraft structures. They found that the composite patch is more efficient than a metallic patch for reducing the stress intensity factor of cracked aircraft structures
Huang and Feng [9] used the finite element method to study the effect of carbon fiber reinforced polymer (CFRP) repaired for edge crack under different failure modes
Summary
I n aircraft applications, service life is very important. It is affected by structural and aerodynamic loads as landing, take off, fatigue, ground handling, and bird strikes. Kaddouri et al [15] used the numerical finite element method to study the effect of geometrical and mechanical of boron/epoxy composite patch to reduce the driving force stress intensity factor of the central cracked plate. They found that the stress intensity factor at the repaired crack with the composite patch is highly influenced by changing the geometrical and mechanical of boron/epoxy composite patch. Ounias et al [16] used a bonded boron/epoxy composite patch to repair a cracked aluminum plate with imperfection in the bond between the patch and the plate They showed that the stress intensity factor is affected by these debonds. The stacking composite laminate sequence and geometry of the patch are changed
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