DESIGN AND ANALYSIS OF AIRCRAFT WING SPAR WITH DIFFERENT MATERIALS USING ANSYS

Aircraft is considered as the complex mechanical invention possessing flying capability. In the structural engineering field, the finest example for the minimum weight design is the structure of the airframe. This efficient design of airframe is achieved by the concept of strength of material approach. The two major parts of the wing is the fuselage and the wing. While considering the wing, the primary load carrying ability is required when the wing is subjected to bending. A typical wing spar is chosen for our study. The study was further enhanced by changing the materials used for wing spar construction. Four different materials were chosen for our study which includes Aluminum, Cobalt, Structural steel and HA. The model was designed using CATIA V5 software and the structural analyses were performed using the ANSYS software packages. The behavior of the spar with different with respect to the applied load at its free end is our observations and the comparative analyses were done among these four different configurations.