Failure Analysis of Pin Joints in Carbon-Epoxy Nanoclay Composite Laminates

Abstract

Fiber reinforced composite materials have been gaining wide application in aircraft submarine and spacecraft constructions. These applications require joining composites either to composites or to metals. Most commonly, joints are formed using mechanical fasteners. Therefore, suitable revealing methods for the failure strength would help in selecting the appropriate joint size in a given application. The objective of the present study is to investigate the effect of joint geometry on strength of pin-loaded carbon-epoxy nanoclay nanocomposite laminates experimentally and numerically. Composite laminates were prepared using press moulding technique at 150C. Specimens were made according to ASTM standards. Geometric parameters that were investigated during analyses; the distance from the free edge of plate to the diameter of the first hole (E/D) ratio, width of the specimen to the diameter of the holes (W/D) ratio. Both the experimental and analytical results were compared. The results showed that the pin hole farthest from the free edge is subjected to the highest stress. It can also be seen that geometric parameters such as E/D and W/D ratios are crucial for pinned laminated composite joints.