Static structural analysis and testing of aircraft wing spar using composite material

Abstract

A complicated mechanical device with the ability to fly is referred to as a “aircraft”. In the realm of structural engineering, the aircraft structure is the best example of least weight design. To achieve this cost-effective airframe design, the concept of material strength is used. The two major components of the wing are the fuselage and the wing. When considering the wing, the spar is the primary load bearing capability in the structure. In this paper, the spar is modelled as a beam with distributed load at different stations, with each station’s bending moment being calculated.The Finite element analysis (FEA) method is used to calculate the stress developed at each station for a given bending moment. The design limit load of the spar beam is taken into account. The paper's findings are compared to the conventional design approach and the optimized design. GFRP (Glass Fiber Reinforced Polymer) composites are used to make the spar beam. The structural testing of the spar beam is done by applying an equivalent load to the free end of the spar. Strain gauges and dial gauges are used to measure strain and deflection at different locations, respectively.