Abstract
Composite materials are widely used in diverse applications, and extensive research have been performed to enhancethe understanding of the mechanical behavior of joined composite materials. It is mainly to develop design procedures for taking maximum advantage of their properties. Here in these joints the load is transferred between the disjointed components across the bonding surfaces of the joint. Composite joints have special characteristics which complicates its failure investigation. Through systematic scientific investigation, it is possible to recognize that the strength of the adhesively bonded joint is higher than that of the mechanically fastened joint. This paper presents investigations on joints and bonded materials in failure modes of joining of aircraft composite structures.
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