The Key Strength Of Aircraft Landing Gear Components Analysis And Structural Optimization

Aircraft landing gear is the key mechanical parts, it is not only bear the load of aircrafttaking off and landing, but also the completion of the aircraft taxiing and steering, so thelanding gear of the aircraft, it is essential to protect the aircraft taking off and landing safetygear is necessary to protect the force performance and service life. With the improvement ofthe performance of the aircraft on landing gear design also put forward higher requirements,require not only strength enough with reasonable force, but also to try to make it lightweight.In this paper, eight transport aircraft main landing gear strut and key parts on the brakelever extended study, after conducting strength analysis, the safety margin is relatively large,so in order to develop their potential and achieve the purpose of lightweight materialsdesigned for both structures were optimized so that parts meet the requirements under thecircumstances, the weight has been reduced, the mechanical properties improved.In this paper, the landing gear struts, respectively, and the brake lever carried by twomethods of strength analysis and structural optimization, landing gear struts used for Matlabsoftware, designed by pole-sectional dimensions function constraints, while optimizing thestrength to meet the cross-sectional dimensions of the pole, and then using ANSYS finiteelement software structure optimized for strength check carried out, and ultimately determinethe size of the strut optimization section, the original cross-sectional area of1800mm2into1085mm2, reduced quality than the original39.7%.Strength analysis and structural optimization of the landing gear brake lever is the use ofCATIAsoftware, ANSYS Workbench software modeling and topology optimization feature tocreate a three-dimensional model of the brake levers in the CATIAsoftware, by importing theANSYS Workbench software to be applied load and strength analysis, in the case of larger rod safety factor topology optimization was carried out to remove the material, the first50%of the rod material removal conducted the trial, the results of strength seriously weakened,does not meet the requirements, then reduce material removal the relationship between theproportion of re-optimize the removal of material drawn trolley intensity ratio between thecurves, curve finalized by analyzing the material removal ratio of20%; topologyoptimization, the use of CATIA software for accurate modeling, import ANSYS Workbenchagain software strength check, and ultimately determine the size of the optimizedcross-section, the cross-sectional area from the rod1785mm2into1455mm2, quality than theoriginal18.6%decrease in the use of conditions are met, to achieve the purpose lightweightdesign.