Aircraft Research & Design Centre, HAL is involved in design activities for the development of newgeneration aircraft. This requires substantial research on product improvement, acquisition of newtechnologies and application of state-of-the art software. The present paper deals with certain aspects of 3Dstress and fatigue analysis of a wing - fuselage attachment lug of fighter aircraft using contemporary finiteelement software. Bottom lug of the attachment frame experiences tensile loads and the objective is to designit against static and fatigue failures. MSC/NASTRAN and MSC/FATIGUE software are used to estimatestresses, displacements in the bottom lug and predicting its crack initiation and crack propagation life. Thistype of 3D finite element analysis increases the confidence level of designer in optimizing a structuralcomponent rapidly as well as helps avoiding some of the costly structural tests. This paper also explains theanalysis procedures for the aircraft structural component to meet the concerned specifications. In totality, theobjective of this work is to increase the productivity, reduce the effort and cost by avoiding some of thestructural tests and augmenting design quality.
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