Investigation on the debonding between different layers in a hybrid aluminum/glass-epoxy/rubber laminate under high velocity impact

The purpose of this study is to examine the interfacial adhesion properties of a novel rubber layered fiber metal laminate against various high strain rate perforations. The structure consists of four layers of different materials including two layers of Aluminum 6061-T6 as facing layers, 6 layers of glass/epoxy composite and a 2 mm thickness natural rubber. The purpose of fabricating such a structure was to maintain the stiffness as well as high capacity of energy absorption but the debonding between different layers can be hazardous in real functionalities. To overcome this problem three types of adhesives including Bylamet S2, Chemosil 222 and Cyanoacrylate were used in fabrication process. High velocity impact tests were carried out using a 10 millimeter spherical projectile in a gas gun apparatus. A comprehensive discussion about the failure mechanisms in the tested specimens is presented to show which type of adhesive is the proper choice.

Keywords:

laminate , debonding , rubber , high velocity impact