Design and Analysis of Medium Utility Aircraft Landing Gear

Abstract

Stress analysis is one of the important works in finding the structural safety and integrity of a structure. In this work, initially, the main landing gear strength calculation based on the ultimate load is carried out analytically. The stress failure exists in the intermediate zone between the support bearing of the wheels and the clamping of the axle to the nose of the aircraft. To determine the causes of the failure, a material analysis was performed. The margin of safety for major components, such as axle, piston, cylinder, and yoke, as well as minor components, such as toggle link, toggle fork, stub fork, and bolts, is determined. Both analytical and FEA results for stresses are compared. It is found out that the factor by which the FEA and analytical results are varying. The margin of safety calculated by analytical work based on ultimate loads gives positive values as expected. The landing gear strength calculations by both analytical and FEA show the maximum stress for different load conditions based on ultimate loads are well within the ultimate strength of that material.