Finite Element analysis of the behavior of bonded composite patches repair in aircraft structures

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�]2s, 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 inclination angle are described. The present results show that the patch has a high effect in case of a crack in pure mode I. The effectiveness of the composite patch increases with increasing the crack length. 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.

Keywords

• mode of mixity
• j-integral
• aluminum alloy
• 3-d fem
• composite repair patch