Repaired crack in AA7075-T6 structures subjected to biaxial tensile stresses

Abstract eng:
Many materials contain geometrical discontinuities usually grouped under the generic term of notch. When a notched material is charged, local concentrations of stress and strain are produced in the indented area and micro-cracks may appear that develop and coalesce with one another until they form a macroscopic crack which propagates until the total breakdown of the material. Patches composite materials are conventionally used in aeronautics for the repair of metal structures with cracks type of damage. The estimate of the repair performance of aeronautical structures requires notched identify failure criteria for different load. The study by finite element method using ABAQUS Software 6.14 focuses on repairing structures AA7075-T6 containing a circular notch damaged by cracking and repaired by patch Boron/epoxy bonded with a structural epoxy adhesive film FM73. It was found that it was necessary to study the effect of biaxial tension loading on the behavior of cracks. Such cracks located in the crown of the fuselage, are subject to this type of loading due to internal pressurization. The results clearly show the beneficial effect of the patch composite on the stress absorption at the crack tip and the relationship between the orientations of the fibers with the latter also can be noted that the best results are given by the orientation of 0°. The integral J is affected by the effect of loading. The increase of the latter led to the increase of the J integral.

• Export as: BibTeX | MARC | MARCXML | DC | EndNote | NLM | RefWorks
• Add to your basket