Abstract
The Bonded repair is broadly used in aging aircrafts to improve the structural integrity of damaged aircraft panels. The aim of this paper is to study the behaviour of multiple cracks on the flat panels using FEA. In this paper two twin collinear cracks are modeled and analyzed in terms of stress intensity factor(SIF). To improve the strength of the panel with multiple cracks it is repaired by adhesively bonded composite patch. It is shown that bonded repair reduces SIF near the crack tips of multiple cracks. Further, the adhesive is the weakest link which undergo failure under the applied load. Hence in this work debonding analysis of patch from the panel is carried out by appling load in increments. From the debonding analysis it is observed that the debonding of patch reduces the strength of repaired panel and leads to rise in SIF at the crack tips.The Bonded repair is broadly used in aging aircrafts to improve the structural integrity of damaged aircraft panels. The aim of this paper is to study the behaviour of multiple cracks on the flat panels using FEA. In this paper two twin collinear cracks are modeled and analyzed in terms of stress intensity factor(SIF). To improve the strength of the panel with multiple cracks it is repaired by adhesively bonded composite patch. It is shown that bonded repair reduces SIF near the crack tips of multiple cracks. Further, the adhesive is the weakest link which undergo failure under the applied load. Hence in this work debonding analysis of patch from the panel is carried out by appling load in increments. From the debonding analysis it is observed that the debonding of patch reduces the strength of repaired panel and leads to rise in SIF at the crack tips.
Published Version
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