Finite element analysis of aircraft wing using carbon fiber reinforced polymer and glass fiber reinforced polymer.

Abstract

A wing is a structural component of aircraft which is used to produce lift during the flight. Wing is initially inclined at certain angle of attack. When the flow passes over it, due to the pressure difference at top and bottom surface of the wing lift force is generated. The aim of this present study is to analyze the wing of an aircraft using Carbon fiber reinforced polymer (CRFP), Glass fiber reinforced polymer (GRFP) and compare with Al alloy to find suitable material for wing. The wing is designed in solid modeling software CATIA V5 R20 and analysis is done using finite element method by using ANSYS. Static structural analysis of the wing is done to find deformation, stress, and strain induced in the wing structure. Modal analysis is done to find the natural frequency of the wing to reduce the noise and avoid vibration. Finally fatigue life analysis is carried out to find out the damage, life and factor of safety of the wing due to applied pressure loads. In this study, the trainer aircraft wing structure with skin, 2 spars and 15 ribs is considered for the analysis. The ribs are running from leading edge to trailing edge and 2 spars running longitudinally along the length of wing. Front spar is made “I” section and rear spar having “C” section according to design.