Numerical modelling of a selected part of the airplane fuselage

• Autorzy: Szymczyk E. , Orzyłowski M.
• Języki publikacji: EN

Abstrakty

EN

Analysis of a riveted lap joint, the part of M-28 Skytruck fuselage, is presented. The aim of the paper is a proper choice of finite element mesh parameters (shape and density) around the rivet hole as well as a study of the influence of different sheets thickness on secondary bending. Riveting still remains the most popular method of joining metal and composite parts of the aircraft structure. During the operation (service) the severe stress concentrations and the effects such as fretting and secondary bending occur, thus reducing fatigue life. The specimen consists of two thin sheets (0.6 and 1.2 mm thick) stiffened with a 3 mm thick frame. The parts are connected by 14 rivets (3.5 mm diameter) and 8 rivets (3 mm diameter). Overall specimen dimensions are following: length 682 mm, width 136 mm, rivets pitch 17 mm. The riveted joint is subjected to a tensile load. The analysis of large parts of structures like fuselages, wings or multi-row riveted specimens can be performed using global shell models. The correct stress state in global modelling can be obtained by taking into consideration the hole in the sheet, the rivet axis (as a rigid or beam element) and contact elements between the rivet and the hole as well as between the sheets. Deformation of the joint and stress state are calculated. Large difference between sheets thickness causes non-physical deformation of the rivet cross sections. Proper deformations of the joint are obtained by increasing stiffness of those sections in a thinner sheet. Results are compared with an experimental investigation and applied to estimations of specimen fatigue life.

Słowa kluczowe

EN

riveted joint; FEM model parameters

• 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: 2010
• Tom: Vol. 17, No. 2
• Strony: 459--465
• Opis fizyczny: Bibliogr. 4 poz., rys.

Twórcy

autor

Szymczyk E.

autor

Orzyłowski M.

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

Bibliografia

• [1] Muller, R., An experimental and numerical investigation on the fatigue behaviour of fuselage riveted lap joints, Doctoral Dissertation, Delft University of Technology, 1995.
• [2] Szymczyk, E., Jachimowicz, J., Sławiński, G., Global approach In model ling of riveted joints, SSTA 2009.
• [3] MSC.Marc user manual, The MacNeal – Schwendler Corp, 2004
• [4] de Rijck J., Stress Analysis of Fatigue Cracks in Mechanically Fastened Joints, Doctoral Dissertation, Delft University of Technology, 2005