Impact Properties of Parts Manufactured from Fiberglass and Kevlar Composite Panels

Abstract

This paper presents a method of finite element modelling used to study the effect of laminates orientation and thickness on impact properties of a composite sandwich panel made of glass and kevlar fibers in an epoxy resin matrix. In this research, the composite sandwich panel consists of a fuselage skin panel from an aircraft having two configurations: (0/90/0/90/core/90/0/90/0) and (0/90/45/-45/core/-45/45/90/0). This panel is loaded with one uniform distributed abuse loading case and the stress variation within the composite panel for each configuration is determined.