DESIGN AND STRUCTURAL ANALYSIS OF AIRCRAFT LANDING GEAR USING DIFFERENT ALLOYS

Abstract

Landing gear is most significant part in an aircraft system during ground and take off operations. Now-a-days we can see that majority of failures of aircraft structure takes place because of malfunction of landing gear system solely. Generally a landing gear should bear serious compressive load, drag load and side load. Drag load and side load values are terribly tiny in comparison to compressive load. So, it’s treated as united dimensional structure. During landing it’s designed to take in the landing impact energy so that the load transmitted to the aircraft frame is minimized. Aside from static strength, energy absorption is a very important design criteria. For tiny aircrafts, a lip spring sort of landing gear is generally sufficient for absorbing the impact energy. But for heavy aircrafts, oleo pneumatic landing gear strut is the general choice. So we have taken the standard landing gear of an aircraft and it is designed by using CATIA V5R20 and analyzed for the structural safety using ANSYS 19.2 software. The maximum possible load is given as design load. Landing gear assembly is analysed for the traditional metallic materials like Aluminium Alloy 7075, Alloys Steel 4340, Titanium 6AL-4V, Titanium 6AL-6V-2Sn, and Titanium 10V-2Fe-3Al using ANSYS software. Stress analysis, deflection analysis is carried out by importing the modelled landing gear into the ANSYS19.2 software .So by the comparing the results of mentioned materials the Titanium alloy 10V-2Fe-3Al have the highest factor of safety and minimum value of maximum stress developed. At last titanium alloys are suggested to avoid structural failures of modelled landing gear system.