ANALYTICAL MODEL OF DAMAGED AIRCRAFT SKIN BONDED REPAIRS ASSUMING THE MATERIAL PROPERTIES DEGRADATION

ANALYTICAL MODEL OF DAMAGED AIRCRAFT SKIN BONDED REPAIRS ASSUMING THE MATERIAL PROPERTIES DEGRADATION

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The search of optimal variants for composite repair patches allows to increase the service life of a damaged air- plane structure.To sensibly choose the way of repair, it is necessary to have a computational complex to predict the stress- strain condition of "structure-adhesive-patch" system and bostik mvp to take into account the damage growth considering the material properties change.The variant of the computational complex based on inclusion method is proposed.

For calculation purposes the repair bonded joint is divided into two areas: a metal plate with patch-shaped hole and a "patch-adhesive layer-skin" composite plate (inclusion).Calculation stages:Evaluation of the patch influence to the skin stress-strain condition, stress distribution between skin and patch in the case of no damage.Calculation of the stress-strain condition is performed separately for the skin with hole and for the inclusion; solutions are coupled based on strain compatibility.

Definition of the damage growth parameters at new stress-strain condition due to bonded patch existence.Skincrack stress intensity factors are found to identify the crack growth velocity.Patch is modelled as a set of "springs" bridging the crack.

Degradation analysis of bovi-shield gold fp 5 l5 elasticity properties for the patch material.Repair effectiveness is evaluated with respect to crack growth velocity reduction in the initial material in compari- son with the case of the patch absence.Calculation example for the crack repair effectiveness depending on number of loading cycles for the 7075-T6 aluminum skin is given.

Repair patches are carbon-epoxy, glass-epoxy and boron-epoxy material systems with quasi- isotropic layup and GLARE hybrid metal-polymeric material.The analysis shows the high effectiveness of the carbon-epoxy patch.Due to low stiffness, the glass-epoxy patchdemonstrates the least effectiveness.

GLARE patch containing the fiberglass plies oriented across the crack has the same effectiveness as the carbon and boron patches.Proposed bonded repair calculation method and corresponding computational model allow to analyze effectively the possible structural damage cases and to select optimal variant of patch installation subject to material durability undercyclic loads.Lack of this information may lead to establishing the inadequate inspection intervals of the damage locationand may reflect on economic factors of the airplane maintenance and flight safety.