B - Operations – Transporting – 32 – B
Patent
B - Operations, Transporting
32
B
B32B 15/14 (2006.01) B29D 99/00 (2010.01) B29C 70/44 (2006.01) B29C 70/46 (2006.01) B29C 70/88 (2006.01) B32B 7/12 (2006.01) B32B 15/08 (2006.01) B64C 1/12 (2006.01)
Patent
CA 2417072
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.
Livi Francesco
Puccini Geremia
Alenia Aeronautica S.p.a.
Macrae & Co.
LandOfFree
Methods of manufacturing a stiffening element for an... does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Methods of manufacturing a stiffening element for an..., we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Methods of manufacturing a stiffening element for an... will most certainly appreciate the feedback.
Profile ID: LFCA-PAI-O-1516074