Spliced laminate for aircraft fuselage

Details Spliced laminate for aircraft fuselage Spliced laminate for aircraft fuselage

B - Operations, Transporting

32

B

B32B 15/08 (2006.01) B32B 3/10 (2006.01) B64C 1/00 (2006.01) B64C 1/12 (2006.01)

Patent

CA 2139856

A laminated body panel for aircraft applications comprises first and second metal layers and an adhesive layer. First and second sections in each metal layer are generally coplanar and separated by a splice line. A first splice line in a first metal layer is generally parallel to a second splice line in a second metal layer, and spaced laterally from the second splice line. An adhesive layer between the metal layers preferably contains reinforcing fibers bridging across the splice lines. An aircraft fuselage or wing or empennage made with spliced body panels of the invention has fewer joints and weights less than one made with narrower body panels containing unspliced metal layers.

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