Influence of matrix properties on the interlaminar fracture toughness on carbon fiber/epoxy composites

Abstract

The use of metallic materials in aeronautic industry is consolidated, however some disadvantages on structural application due to its high density and high maintenance cost, have increased interest in alternative materials research, for example, carbon fiber/epoxy composites. The carbon fiber/epoxy advanced composites lead to structural weight relief high stiffness with high mechanical performance and fatigue resistance. Resin Transfer Moulding (RTM) process is a manufacturing procedure which allows the operator to obtain plates of very complex geometry, reproducibility with a low curing time. RTM process brings also the advantage of not exposing the operator to toxic volatile products. [11]Plates processed by RTM can acquire internal voids and other common defects. Defect verification can be done by using non-destructive techniques. In this project, RTM6-2 will be injected in the mould which contains preformed fibrous fabric 5HS. Samples removed from plates will be analyzed in an optical microscope to evaluate void presence in composite structure. Mechanical tests on fracture toughness by mode I (Tension) will be conducted, in order to observe material resistance to delamination. The main objective is to evaluate interlaminar fracture toughness of RTM6-2/5HS composites.