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THREE-DIMENSIONAL FINITE ELEMENT ANALYSIS OF SINGLE BOLTED ALUMINIUM LAP JOINT AND VALIDATION BY XRD TECHNIQUE

Amal Hisham E. Shereef, A. Dinesh, V Dhanush, Piyush Raj

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Abstract

In structural applications such as aircraft, spacecraft and civil engineering structures, composite components are often fastened to other structural members by bolted joints. Bolted joints being very often the critical part of the structure, it is therefore important to design them safely. In this study, Three-dimensional finite element model have been developed. Investigations on the effect of failure criteria including the behavior of bolted joints in aircraft using aluminium laminates are examined. The joint type studied is single - bolt, single - lap joint. Load bolt displacement curves and stress around the hole is analyzed. The model is generated in Finite Element Software, FEAST SMT and attempts are made to validate it by X-ray

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What this paper is about

In structural applications such as aircraft, spacecraft and civil engineering structures, composite components are often fastened to other structural members by bolted joints. Bolted joints being very often the critical part of the structure, it is therefore important to design them safely. In this study, Three-dimensional finite element model have been developed. Investigations on the effect of failure criteria including the behavior of bolted joints in aircraft using aluminium laminates are examined. The joint type studied is single - bolt, single - lap joint. Load bolt displacement curves and stress around the hole is analyzed. The model is generated in Finite Element Software, FEAST SMT and attempts are made to validate it by X-ray

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Available abstract

In structural applications such as aircraft, spacecraft and civil engineering structures, composite components are often fastened to other structural members by bolted joints. Bolted joints being very often the critical part of the structure, it is therefore important to design them safely. In this study, Three-dimensional finite element model have been developed. Investigations on the effect of failure criteria including the behavior of bolted joints in aircraft using aluminium laminates are examined. The joint type studied is single - bolt, single - lap joint. Load bolt displacement curves and stress around the hole is analyzed. The model is generated in Finite Element Software, FEAST SMT and attempts are made to validate it by X-ray

Key concepts: Bolted joint, Finite element method, Structural engineering, Joint (building), Displacement (psychology), Engineering, Mechanical joint, Lap joint

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