| The lug connecting piece is a commonly used connecting structure on airplanes,and the lug connecting structure is used with a pin or bolt.However,in the long-term service of the aircraft,fretting wear and stress concentration will occur around the lug holes,leading to failure and fracture.Because of the complex working load characteristics of the lugs and their important position in the connection structure of the aircraft,it is of great engineering significance to carry out the research on the structural strength and fatigue performance of the typical aircraft lugs.This article takes the typical aircraft lugs as the research object,and carries out static tensile and fatigue experiments on lugs of different materials and different structural parameters.First,the structure of the lugs of different sizes was parameterized,the static tensile and fatigue test methods and special fixtures of the lugs were designed,the static tensile and fatigue test results were counted.The static tensile failure and fracture forms were discussed,and the macro and micro fatigue fractures of the lugs were observed,the influence of different structural parameters on the structural strength and fatigue performance of the lugs was analyzed.The Abaqus finite element model of the lugs was established,the static tension process of the lugs with different structural parameters was simulated,the tensile failure load and failure form were calculated,and the test results were compared to verify the accuracy of the finite element model.On the basis of the Abaqus fracture failure model,it was improved to retain only the elastic phase of the material.The static analysis of the lugs under the fatigue peak load was carried out,the static calculation results were imported into the Fe-safe software,and the load conditions and other parameters were created.Fe-safe software was used to predict the fatigue life of the lugs with different structural parameters.The predicted fatigue life results were consistent with the results obtained from the fatigue test,and the error was within the allowable range.On the basis of the axial tension finite element model,the load direction was changed,and the lug hole peak stress and stress concentration coefficient of each structural parameter lug under different loading angle loads were calculated,the location law of the peak stress near the lug hole was discussed,and the bearing capacity of the lug with different structural parameters to the inclined load was compared,it provided a certain basis for the structure design and optimization of the lugs. |
