FIELD: aviation; machine building.
SUBSTANCE: invention relates to aircraft engineering. Panel of wing or fin of aircraft from laminar composite materials comprises a load-bearing frame in the form of rib-cellular structure 2 with outer smooth lining 3, formed by layers of systems of overlapping high-strength and/or high-modulus, bonded by cured polymer binder yarns and butt end of metal plate 4, with system of intersecting slots 5 on its outer surface with ribs of carcass 6 and recesses 7 located in them, in all or in some of which there are cylindrical holes 8 for, for example, bolts or threaded pins with arrangement of axes of latter perpendicular to inner surface of plate.
EFFECT: invention is aimed at increasing strength and reliability of connection of panel with aircraft power elements.
7 cl, 4 dwg
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