عنوان مقاله [English]
نویسندگان [English]چکیده [English]
Sandwich panels with honeycomb core are widely used as satellite primary structure due to high specific strength (strength to weight ratio) and high specific stiffness (stiffness to weight ratio). Therefore, Due to the application of sandwich panels and the need for implementation of these joints in space structures, modeling and analysis of these joints seems to be necessary. In this study, a finite element model is provided to predict the behavior of this type of joints under pull-out loading. This model considers the whole joint components including core, skin (face), cohesive element, bolt and insert. Abaqus 6.14 software was used for simulation. The results indicated that under tensile load, in the adhesive layer between the lower fin insert and composite face the highest stress occurs. Comparison of finite element results of this study with available experimental data confirmed the fracture mode of the joint. Finally, the effect of core and composite face characteristics on joint failure load was investigated. The core density had the greatest influence on failure Load.
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