Structural Analysis of Sandwich panels Used in Aerospace Applications

Abstract

Sandwich concept describes the behavior of a beam, plate, or shell which consists of three layers - two face sheets and one core. Probably the most ordinarily used sandwich conception is linear and is an extension of first order beam concept. Linear sandwich concept is of importance for the design and evaluation of sandwich panels, that are of use in building construction, vehicle building, aircraft building and refrigeration engineering. Sandwich cross sections are composite. They probably consist of a low to average stiffness core which is hooked up with two stiff exterior face-sheets. The composite has substantially larger shear stiffness to weight ratio than an identical beam made of only the core material or the face-sheet material. The composite additionally has a high tensile strength to weight ratio. Sandwich panels are usually used in aerospace purposes, similar to wing flaps, plane flooring and overhead storage bins. We construct experiment and analyze the strength and stiffness of composite sandwich panels from without problems available materials. Thus our intension is to do the evaluation on a well-designed sandwich panel arrangements used for plane Wing & fuselage structures & different safety applications via utilising ANSYS.