Experimental Method of Analysis of Metal-Composite Joints for Aeronautical Structures
DOI:
https://doi.org/10.22480/revunifa.2011.24.720Keywords:
Metal-composite joints, Fastened joints, Composite aeronautical structures, Experimental methodAbstract
The metal-composite structural joints remain a challenge for the design and analysis of aeronautical structures. This paper consists on a new methodology for analysis of metal-composite joints joined by fasteners. Thus, joints made of titanium joined to composite (carbon fiber with epoxy resin) by monel fasteners were investigated. It is important to mention that only single lap joints were analyzed. However, before manufacturing specimens of joints, composite specimens were tested following the ASTM D3039 and ASTM D3518. The tensile and shear tests provided the mechanical properties and strength values of the composite part. Finite element analyses of the joints were carried out, using average mechanical properties and strength values. These simulations followed the specifications of ASTM D5961 in order to predict the mechanical behavior of the joints during the experimental tests, as well as, to provide good strategy for the test setup. The experimental tests were carried out using geometry specifications of ASTM D5961 (composite-composite joints), and procedure established by the Secondary Module Method of MIL-HDBK-5J (metal-metal joints). Therefore, a new methodology was proposed for testing metal-composite joints. Joints with the composite layers oriented by 0°/90° failed by net-tension, while the joints with composite layers oriented ±45° failed by tear-out. Thus, the experimental method proposal not only provides an effective approach to obtain the mechanical properties of metal-composite joints, but also shows the failure mode of the joint.
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Copyright (c) 2011 Ricardo de Medeiros Volnei Tita, Silvio Venturini Neto
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