Failure prediction of repaired composite structures in aviation

There is no standardized methodology, applicable to primary composite structure repair. In order to define reliable repair methodology applicable to damaged composite structure complete initial stress-strain state, stress-strain state of the damaged structure and stress-strain state of the repaired structure has to be known. Stress distribution in the repaired composite structure depends on the repair elements used. In the present study the effects of the repair element type, element size, element geometry, damage size, damage location, repair element material type and thickness of the adhesive, on the stress distribution in the repaired composite structure were investigated.