Reparation of Composites used in Naval Industry

ESTEBAN SOROCINSCHI; EXEQUIEL RODRIGUEZ; VERA ALVAREZ; ANALÍA VÁZQUEZ

Journal of Reinforced Plastics and Composites

Sage

Año: 2007 vol. 26 p. 1821 - 1829

In this work the repairing process of a completely cured epoxy-glass laminate was simulated. Repairing plaques were joined to the original material at different curing temperatures. After reparation, delamination, lap-shear and impact tests were carried out. Fiber bridging was observed. The optimum temperature for delamination was 708C. Strength and modulus increased with the curing temperature. In the case of impact test, higher temperature favored the patch failure against the failure of the base material.8C. Strength and modulus increased with the curing temperature. In the case of impact test, higher temperature favored the patch failure against the failure of the base material.