Modeling And Fe Analysis Of Semimonocoque At Different Load Conditions

Abstract

A sandwich-structured composite is a special class of composite materials that is fabricated by attaching two thin but stiff skins to a lightweight but thick core. The core material is normally low strength material, but its higher thickness provides the sandwich composite with high bending stiffness with overall low density. Sandwich structures, widely used in aerospace and naval applications, tend to be limited to a small range of material combinations. In this present work, a sandwich composite for Semi-monocoque construction in aircraft fuselage is analyzed for its strength under different loading conditions using different materials for Stringers balsa wood, synthetic foams, and honeycombs and Carbon Fiber reinforced thermoplastics is used as skin material. 3D modeling is done in CATIA V5 R20. Static and Modal analysis is done on the beam using finite element analysis software ANSYS 14.5