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

• US 20030168555A1
• Filed: 01/22/2003
• Published: 09/11/2003
• Est. Priority Date: 02/19/2002
• Status: Abandoned Application

• Current Assignee: Alenia Aeronautica SPA (Leonardo S.p.A.)
• Original Assignee: Alenia Aeronautica SPA (Leonardo S.p.A.)
• Inventors: Puccini, Geremia, Livi, Francesco
• Application Number:
  US10/348,815
• Publication Number:
  US 20030168555A1
• Time in Patent Office: Days
• US Class Current: 244/132
• CPC Class Codes: B29C 70/44 using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
• CPC Class Codes: B29C 70/46 using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
• CPC Class Codes: B29C 70/885 with incorporated metallic wires, nets, films or plates as lost heating elements B29C35/0272, B29C61/0625
• CPC Class Codes: B29D 99/0014 provided with ridges or ribs, e.g. joined ribs
• CPC Class Codes: B29L 2031/3082 Fuselages
• CPC Class Codes: B32B 15/08 of synthetic resin
• CPC Class Codes: Y02T 50/40 Weight reduction

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.

Claims

1. A method of manufacturing an elongate stiffening element for an aircraft skin panel, comprising the following steps:

a) preparing a pile of sheet-metal strips bent so as to have a cross-section of given shape, with at least one layer of resin-impregnated fibre interposed between two consecutive sheet-metal strips, and

b) applying heat and pressure to the pile thus produced in a manner such as to cure the resin and set the shape.

2. The method of claim 1, wherein step a) includes the steps of:

a1) piling up the sheet-metal strips substantially flat,

a2) applying the at least one layer of resin-impregnated fibre, and

a3) bending the sheet-metal strips to the said shape.

3. The method of claim 2, wherein the bending step (a3) is performed by placing the pile of sheet-metal strips alternating with the fibre layers in a forming die, and wherein the curing step (b) is performed with the use of the same die to keep the pile in the desired shape.

4. The method of claim 2, wherein step (a3) is preceded by the step of:

fitting a vacuum bag on the pile and depressurizing the vacuum bag in order to compact and temporarily hold the strips which are piled up in an orderly manner.

5. The method of claim 1, wherein at least one of said steps (a, b) is performed with the use of pairs of pressing means in continuous rotary motion, acting on opposed faces of a pile of sheet-metal strips in which at least one layer of resin-impregnated fibre is interposed between two consecutive sheet-metal strips.

6. The method of claim 5, wherein the pressing means comprise belt means.

7. The method of claim 5, which includes the step of applying heat and pressure to the pile so as to fluidize the adhesive in the fibre layers without curing it.

8. A method of manufacturing an aircraft skin panel with elongate stiffening elements, comprising the steps of:

a′

) preparing at least one pile of sheet-metal strips bent so as to have a cross-section of given shape, with at least one layer of resin-impregnated fibre interposed between two consecutive sheet-metal strips,

b′

) preparing a laminate suitable for forming the outer skin, the laminate comprising at least two sheet-metal layers with at least one layer of resin-impregnated fibre interposed between two consecutive sheet-metal layers,

c′

) arranging the at least one pile on the skin laminate with a layer of adhesive interposed between the pile and the skin laminate, and

d′

) applying heat and pressure in a manner such as to cure simultaneously the resin contained in the fibre layers of the pile and of the laminate, and the adhesive interposed between the pile and the laminate.

9. The method of claim 8, wherein the polymerization step (d′

) includes the step of positioning rigid locating elements associated with the piles in order to keep the piles in the desired shape and position during the curing cycle.

10. The method of claim 8, wherein step (a′

) is followed by the step of applying heat and pressure to the pile so as to fluidize the resin in the fibre layers without curing it.

11. A method of manufacturing an aircraft skin panel with elongate stiffening elements, comprising the steps of:

a″

) preparing at least one pile of sheet-metal strips bent so as to have a cross-section of given shape, with at least one layer of resin-impregnated fibre interposed between two consecutive sheet-metal strips,

b″

) applying heat and pressure to the pile thus produced in a manner such as to cure the resin and set the shape so as to produce at least one elongate, composite, rigid element,

c″

) preparing a laminate suitable for forming the outer skin, the laminate comprising at least two sheet-metal layers with at least one layer of resin-impregnated fibre interposed between two consecutive sheet-metal layers,

d″

) arranging the elongate rigid element on the laminate, with a layer of adhesive interposed between the elongate element and the laminate, and

e″

) applying heat and pressure in a manner such as simultaneously to cure the resin contained in the fibre layers of the laminate and the adhesive interposed between the elongate element and the laminate.

12. An elongate stiffening element for an aircraft skin panel, wherein the element comprises a pile of sheet-metal strips bent so as to have a cross-section of given shape, with at least one layer of resin-impregnated fibre interposed between two consecutive sheet-metal strips.

13. An aircraft skin panel comprising at least one elongate stiffening element according to claim 12.