Investigation of Joining Methods of Honeycomb Composite Panels Used in Structural Elements of Aircraft Cabin Units
Design, material selection, production and assembly of structural elements used in aircraft are critical problems of the aeronautical industry. The usability of these elements is determined by considering parameters such as strength, cost, and weight. Accordingly, this study aims to optimize the joining methods of different thickness honeycomb composite panels used in the aviation industry, considering these parameters. Panel type, panel thickness and joining methods were determined as input parameters, and fracture force, displacement, cost, and weight as output parameters. Tenon-mortise, double-sided bracket, single-sided bracket, and extrusion methods were investigated for L and T-type panels. Panel thicknesses were determined as 10 mm and 22 mm according to standards, tensile test and finite element analysis were performed. The weight and cost of the panels were determined by the process analysis. The obtained findings were optimized according to multi-criteria decision making, and response surface analysis methods. In the analysis, tensile strength maximization, displacement, cost, and weight minimization were determined as target functions. At the end of the study, the optimum thickness value for both types of panels was determined as 22 mm, and the optimum joining method was tenon-mortise.
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