Methods of manufacturing a stiffening element for an aircraft skin panel and a skin panel provided with the stiffening element
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United States of America Patent
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app pub date -
Jan 22, 2003
filing date -
Feb 19, 2002
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Abandoned
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Abstract
A method of manufacturing a stringer for a fuselage skin panel comprises the steps of: preparing a pile of sheet-metal strips bent so as to have a cross-section of given shape, alternating with at least one layer of resin-impregnated fibre, and applying heat and pressure to the pile 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.
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