Buckling in rectangular hybrid composite plates with angled groove-shaped cut-outs

Abstract

Abstract In this paper, eight-layer composite laminates were produced using twill and plain woven glass and carbon laminate fibers as a reinforcement element and as a matrix with epoxy resin. All laminates having the layup of [(0°/90°)2]s but the hybrid laminate arrangement varies between the number of woven glass and carbon laminates. The buckling behaviour of woven composite laminates used for typical of the aerospace industry is investigated. Un-grooved and grooved with centered elliptical groove angles with 0°, 15°, 30°, 45°, 60°, 75° and 90° specimens were subjected to buckling tests. It was investigated how the woven type, laminate designation, and groove angles affect the buckling behaviour. Cut-out causes to decrease of buckling load of composite plates. It is understood that the buckling load increased with regard to the increase groove angle (from 0° to 90°) of the composite plates. As the laminate designation changed, the buckling load also changed significantly. The buckling load of composite plates is highly influenced by its weave type. As a fiber, it has been determined that the buckling behaviour of carbon fiber is better than glass fiber. In addition, it was concluded that the twill weave type is generally better than the plain weave type.