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M. Calomfirescu, R. Zwinderman
The use of composite materials, such as carbon-fiber reinforced plastic (CFRP) composites, in aerostructures has led to an increased need of advanced assembly joining and repair technologies. Adhesively bonded joints provide an alternative to mechanically fastened composite structures, which often introduce undesirable stress concentrations. The objective of this paper is to evaluate the P-FEM method implemented in the commercial software tool StressCheck for failure prediction of adhesively bonded composite joints. The validation of the (geometrical and material) non-linear Finite Element Analysis was performed on bonded scarf joints. Bonded scarf joints are relevant for repairs of composite structures. A main focus within the analysis was to consider all relevant failure modes such as cohesive failure in the bondline and failures in the composite adherends (delamination, matrix and fiber failure). The validation has been performed on coupon level in tensile tests conducted at room temperature as well as at hot wet condition. The failure modes as well as the failure loads could be predicted within a satisfactory degree of agreement between analysis and testing.
Deutscher Luft- und Raumfahrtkongress 2013, Stuttgart
Deutsche Gesellschaft für Luft- und Raumfahrt - Lilienthal-Oberth e.V., Bonn, 2013
21,0 x 29,7 cm, 5 Seiten
Stichworte zum Inhalt:
composites, Strukturelles Kleben