Author/Authors :
yalçin, bekir isparta uygulamalı bilimler üniversitesi - teknoloji fakültesi - makine ve imalat mühendisliği bölümü, Isparta, Turkey , ergene, berkay isparta uygulamalı bilimler üniversitesi - teknoloji fakültesi - makine ve imalat mühendisliği bölümü, Isparta, turkey
Abstract :
The using areas of composite materials in mainly aerospace sector and other industry have been increased due to their more light, high fatigue strength, impact strength and specific strength properties than metals. The critical factor in fiber reinforced laminate composites from composite materials is to crack formation on interface matrix structure and fibers carrying loads and distributing forces to matrix structure. Also, the cracks on interface matrix structure and fibers cause decreasing the composite structure strength with crack propagations under loads. In this study, the effect of location and angle of the crack in the laminate hybrid composite material reinforced with glass-epoxy, boron-epoxy, carbon-epoxy, glass-boron-carbon-epoxy fibers at different angles on mechanical behaviors is determined with finite element analyses. In analyses, the different located crack and crack angles (0° and 30°) inside the laminate composite structure with different fiber materials reinforced at different angles (0°, 15°, 30°, 45°, 60°, 75° and 90°) with 1.5 mm of total composite thickness were formed and applied tensile forces. Afterwards, stress and displacement values were obtained in the cracked fiber reinforced structures. According to results, Decrease in stress at top and bottom aluminium plate was observed in case of parallel fiber orientation to the applied forces. Beside, shear stresses increase with increasing the crack angle.
