Experimental Investigation of Single Lap Joint on Composite Materials

Abstract

To improve the efficiency and performance can be achieved by decreasing the aircraft weight through considerable usage of composite material in primary aircraft structures. In fuselage construction it consist of various structural members such as skin, stringers, frames, bulkheads etc., all fastened together by rivets and bolts. The failure of riveted joint take place when tearing of the plate, shearing of rivets and plate under the action of over load. This project deals with the tensile strength analysis of riveted lap joints of three different composite materials such as Glass fiber, Basalt fiber and Carbon fiber are reinforced with epoxy resins. By using universal testing machine the tensile strength of the riveted single lap joint of three different composite materials are tested experimentally.