Structural Analysis of Wing-Fuselage Lug Attachment

The objective of this paper is to perform the stress analysis of lug joints of wing-fuselage attachment numerically and to compare the results with theoretical values. The wing and fuselage connecting points or joints are the critical in an aircraft structure. In the present work, numerical stress analysis has been carried out with bending load transfer to lug joint of a two-seated trainer aircraft and then validated with theoretical values at static conditions. The numerical analysis was done with finite element analysis and theoretical study considering stress value and margin of safety obtained. The results revealed that the maximum load to be applied for tongue attachment is 1684 kg and for fork bracket attachment is 851 kg. Finite element analysis showed maximum stress values for tongue and fork bracket, respectively, 23.150 kg/mm(2) and 11.07 kg/mm(2). It could be concluded that this method enhanced the strength and lifetime of attachment of fuselage and wing configuration.