What is it about?
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 fibres 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.
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Why is it important?
The paper presents a research for the impact properties of two selected configurations of composite sandwich panels of a fuselage skin panel.
Perspectives
The mathematical models developed in this paper having as input data the deformations and tensions obtained from finite element analysis of panels can be useful for further enhancing different material databases.
Mr. Croitoru E. Ionut
Universitatea Transilvania Brasov
Read the Original
This page is a summary of: Impact Properties of Parts Manufactured from Fiberglass and Kevlar Composite Panels, Applied Mechanics and Materials, November 2015, Trans Tech Publications,
DOI: 10.4028/www.scientific.net/amm.809-810.938.
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