Abstract
Composite materials technology in aircrafts needs improved damage growth predictions and effective repair techniques for damaged structures. Improper joint design may lead to overweight or defective structures. The joining of composite materials has traditionally been achieved by mechanical fastening or adhesive bonding. Hybrid joints are a combination of adhesive bonding and mechanical fastening; these joint systems have attracted the attention in aerospace and general mechanical industries due to its higher strength and stiffness and higher energy absorption prior to failure. In this work a parametric study was performed using a finite element software to determine the mechanical resistance of hybrid and simple lap joints. The parametric study consists in the numerical modeling of different conditions that permit estimates the main characteristics of lap joining. The study performed in this investigation seeks for a better understanding of joining of composite materials.
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