Methods of manufacturing a stiffening element for an aircraft skin panel and a skin panel provided with the stiffening element

摘要

A method of manufacturing a stringer (1) for a fuselage skin panel comprises the steps of: preparing a pile (32) of sheet-metal strips (3) bent so as to have a cross-section of given shape, alternating with at least one layer of resin-impregnated fibre (4), and applying heat and pressure (70) to the pile (32) in a manner such as to cure the resin and set the shape. A composite laminated stringer is thus obtained. In order to manufacture a fuselage panel of composite laminated material, provided with composite laminated stringers, the resin in the stringers is cured simultaneously with the resin which is present between the metal layers of a laminate suitable for forming the outer skin.