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Abstract

The present paper is concerned with numerical studies of composite T-joints which are made of carbon fibre composite (CFC) materials. CFC materials are used due to their high load carrying capacity and lightweight. The composite T-section is formed at the spar-lower skin joint section in aircraft wings. The behaviour of such joints is very complex. In this study, a brief account of the problem is first presented and areas of principal interest which most influence joint behaviour are identified. A thick composite shell finite element is specially developed and it is then used for a detailed finite element analysis of composite T-joints. Though several types of forces act on the spar, in the present case, a pull-out force is applied on the top of the web to determine strength and to study the behaviour of T-joints. Parametric variations account for two different stacking sequences and variations in filler area and radius of curvature at the web/skin interface. Accuracy of the present finite element analysis is established by comparing present results with the published ones. Numerical results obtained through parametric variations are presented and discussed to understand the joint behaviour.

Keywords

finite element composite joint composite shell element deflection stresses bending

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Finite Element Analysis of Composite Wing T-Joints

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