Abstract
A sandwich construction is applied to wing skins and fuselages, along with many other structures in aeronautical applications, due to its increased stiffness and reduced weight. In this paper, a face-sheet composed of plain-woven composite laminate that uses prepregs (HPW193/RS3232) and a core material of aluminum honeycomb (Al5052/F40-0.0025) is used. Launch vehicle structures have cut-out areas to check the status of the payload and electric equipment. Cut-out areas reduce the structural stiffness of the launch vehicle structure. Changes in the shape of cut-outs can cause a difference in load support ability of the structure. Compression tests and FEM analysis were performed on composite sandwich panels with various types of cut-out, but with the same overall area.
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