TY - GEN
T1 - Residual strength and fracture path for drilled epoxy-glass composites
AU - Torres, Mauricio
AU - Gonzalez, Jorge Luis
AU - Hernandez, Hilario
PY - 2009
Y1 - 2009
N2 - Aircraft composite structures are mostly joined by mechanical fasteners like bolts, pins or screws. However, the effect of the presence of holes in the remaining strength of the composite structures is still being studied extensively. In this work, epoxy/glass laminates with drilled holes of different sizes were tensile tested and from these results, the residual strength was plotted. Strength vs. hole's diameter at different fiber orientation was obtained. The fracture path and failure mechanism were identified by fractographic examination. The Point Stress Criterion (PSC) was used, in order to establish the stress intensification due to the presence of a drilled hole. A numerical model by Finite Element Method was carried out to verify the experimental results and the analytic failure predictions. A reduction of 50% in laminate strength was observed when diameter-width ratio was 0.12. The principal fracture mechanism observed in composite laminates was interface breakup. FEM results and analytic results by PSC show accuracy of 90% for predicting the damage in drilled composites.
AB - Aircraft composite structures are mostly joined by mechanical fasteners like bolts, pins or screws. However, the effect of the presence of holes in the remaining strength of the composite structures is still being studied extensively. In this work, epoxy/glass laminates with drilled holes of different sizes were tensile tested and from these results, the residual strength was plotted. Strength vs. hole's diameter at different fiber orientation was obtained. The fracture path and failure mechanism were identified by fractographic examination. The Point Stress Criterion (PSC) was used, in order to establish the stress intensification due to the presence of a drilled hole. A numerical model by Finite Element Method was carried out to verify the experimental results and the analytic failure predictions. A reduction of 50% in laminate strength was observed when diameter-width ratio was 0.12. The principal fracture mechanism observed in composite laminates was interface breakup. FEM results and analytic results by PSC show accuracy of 90% for predicting the damage in drilled composites.
KW - Fiber orientation
KW - Finite element
KW - Fracture
KW - Residual strength
UR - http://www.scopus.com/inward/record.url?scp=70349290659&partnerID=8YFLogxK
U2 - 10.4028/www.scientific.net/amr.65.89
DO - 10.4028/www.scientific.net/amr.65.89
M3 - Contribución a la conferencia
SN - 9780878493302
T3 - Advanced Materials Research
SP - 89
EP - 96
BT - 17th International Materials Research Congress; from the 17th International Materials Research Congress, Symposium 11, Fracture Mechanics
PB - Trans Tech Publications
T2 - 9th Edition of the Symposium Fracture Mechanics; Held within the Activities of the 17th International Materials Research Congress, IMRC
Y2 - 18 August 2008 through 21 August 2008
ER -