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1 Journal of KONES

1 2008

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Numerical analysis of the metal-composite joints

Derewońko A., Cielęta R.

Journal of KONES

2008

Vol. 15, No. 1

39-50

The development and implementation of the new technologies and materials are one of the conditions allowing improving the aircraft structures. The composite materials enable to reduce the aircraft weight and keep appropriate strength and fatigue properties. Application of the composite materials in the wing elements, and metal alloys in assemblies of the aircraft fuselage requires elaboration of the appropriate method for technology joining metal and composite. Bonding eliminates breakages in the composite plies which are initiated during assembly process of the structure with mechanically fastened joints e.g. bolts [1]. The strength and stiffness of the composite depend on shape and direction of the fibre which carry the tensile and compression stresses. Shear stress and strength of the composite depend on the resin system. Therefore, the use of composites brings more complicated design approach compare to metal. The aim of the study is tofind appropriate method to determine the failure loading of the metal-composite aircraft wing pivot fitting. Numerical and laboratory investigations for metal-composite joints are presented. Interaction between the composite plies is modelled as the contact problem. It allows determining the strain and stress at the contact surfaces and stress concentration fields. Contact modelling technique is also applied to model interface between metal and composite. Engineering approach to the model full-scale co-curing triple stepped lap joint is presented. The professional engineering software tools are used to create accurate models. Tensile tests of the metal-composite joint were carried out to verify the numerical analysis methods.