Design and Structural Analysis of an Aircraft Landing Gear strut under Static Loading Condition

Abstract

Aircraft Landing gear strut is major structural components which takes various types of loads. Main landing gear bears with impact load while the nose landing gear bears side, break and impact loads. In aerospace industry, weight reduction is an important aspect and use of composite plays a major role by providing better strength to weight ratio. In this work, weight of landing gear strut. A light weight aircraft is selected for the analysis. The design of landing gear strut is carried out as per the CS-23 Certification specification. Computational analysis is carried out on the existing design with appropriate loading and boundary conditions to arrive at optimized landing gear strut cross section. Fatigue life for the composite landing gear strut is also estimated using SN curve approach. With the optimization of existing titanium alloy landing gear strut, mass of the strut is reduced by only 4.5%. Stresses and deflections under all loading conditions are within the acceptable limit. The static structural analysis was carried out to compare with different materials and as per dimensions of the strut. Maximum Stresses of strut performances for aircraft landing gear is very significant role for determination of safety and stability of structural assemblies The design of Boeing 747 nose landing gear structure and using FEA package of ANSYS workbench is carried the static structural analysis is done and determined the deformation and stresses for various material with comparison of selected material such as Titanium alloy, Aluminum alloy and Steel alloy and studied their material characteristic to design a landing gear structure to improve the strength and stiffness.