Numerical analysis of the metal-composite joints

• Autorzy: Derewońko A. , Cielęta R.
• Języki publikacji: EN

Abstrakty

EN

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.

Słowa kluczowe

EN

metal-composite joint; FEM; contact problem; nonlinearity; aircraft structure

• Wydawca: Łukasiewicz Research Network - Institute of Aviation ; European Science Society of Powertrain and Transport KONES Poland ; Wydawnictwo Instytutu Technicznego Wojsk Lotniczych
• Czasopismo: Journal of KONES
• Rocznik: 2008
• Tom: Vol. 15, No. 1
• Strony: 39--50
• Opis fizyczny: Bibliogr. 6 poz., rys.

Twórcy

autor

Derewońko A.

autor

Cielęta R.

• Military University of Technology, Department of Mechanics and Applied Computer Science Kaliskiego Street 2, 00-908 Warsaw, Poland tel: [phone], fax: [phone],

Bibliografia

• [1] Broughton, W. R., Crocker, L. E., Gower, M. R. L., Design Requirements for Bonded and Bolted Composite Structures, NPL Report MATC(A)65, United Kingdom 2002.
• [2] Derewonko, A., Niezgoda, T., Godzimirski, J., 3D Numerical Investigation of Tensile Loaded Lap Bonded Joint of Aircraft Structure, Journal of KONES, Vol. 13, 2006.
• [3] German, J., Podstawy mechaniki kompozytów włóknistych, Cracow University of Technology, Cracow 1996.
• [4] Jaeger, J., New Solutions in Contact Mechanics, WIT Press, 2005.
• [5] MSC.Marc ver. 2005, Vol. A, Theory and User Information, The MacNeal-Schwendler Corporation.
• [6] Muc, A., Mechanika kompozytów włóknistych, Księgarnia Akademicka, Cracow 2003.