Abstract

Nowadays, polymeric matrix composite materials are used in multiple applications. One of the important areas of application is in the aeronautical sector, due to the relatively low density of the combined materials; these compounds have good mechanical properties, comparable to metallic materials, but providing additional benefits. The objective of this work is to carry out the experimental tests and the numerical analysis of the structure of the alternative composite material to be used to repair of the flight surfaces of CIDFAE aircraft. A widely extended vacuum bagging process was used to obtain a more homogeneous compound, thus reducing defects in processing, better controlling the fiber fraction and the overall thickness of the compound. Specimens of epoxy resin reinforced with layers of flat fabric of three different fibers of: carbon, glass and aramid, in different orientations, were made, which were tested for traction, bending and impact to determine their mechanical properties. It has been shown that the results obtained by analytical methodology and the finite element method are approximate to the results obtained with destructive tests. The experimental results show that the tensile strength values are higher in epoxy resin materials reinforced with 4 layers of carbon fiber in orientation 0 ° -90 °.