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1. WO2007003372 - PROCESS FOR PRODUCING A SUBSTANTIALLY SHELL-SHAPED COMPONENT

Note: Text based on automatic Optical Character Recognition processes. Please use the PDF version for legal matters

Airbus Deutschland GmbH June 30, 2006
05HB84

Patent Claims

1. Process for producing a substantially shell-shaped component, in particular a fuselage shell, a wing shell, a vertical or horizontal stabilizer shell of an aircraft or the like, from substantially carbon-fiber-reinforced synthetic material having at least one local reinforcing zone and at least one stiffening element, comprising the steps of:
arranging at least one doubler (1) which has already been cured, on an at most partially cured shell skin (2) to form a local reinforcing zone (3),
applying at least one stiffening element which has already been cured, and
placing at least one at most partially cured connecting angle bracket (6) against the at least one stiffening element at least in the region of the at least one doubler (1) ,
introducing the structure constituted by the shell skin (2), the at least one doubler (1), the at least one stiffening element and the at least one
connecting angle bracket (6) into a vacuum bag, which is moved into an autoclave for curing, and
curing the shell skin (2) and the connecting angle bracket (6) at a temperature of between 12O0C and 1800C and a pressure of up to 10 bar in an autoclave to produce a finished shell-shaped component.

2. Process according to Claim 1,
characterized in that
the at least one stiffening element, in the region of the at least one doubler (1), is matched to the contour of - li ¬

the at least one doubler (1) before being applied to the shell skin (2) .

3. Process according to Claim 1 or 2,
characterized in that
the stiffening elements are formed using reinforcing profiled sections, in particular T-profiled sections.

4. Process according to one of Claims 1 to 3,
characterized in that
the shell skin (2), the at least one stiffening element, the at least one doubler (1) and/or the at least one connecting angle bracket (6) are substantially formed using a fiber-reinforced synthetic material, in
particular a material that has a carbon fiber
reinforcement preimpregnated with a curable epoxy resin.

5. Shell-shaped component having at least one local reinforcing zone and at least one stiffening element, in particular a fuselage shell, a wing shell, a vertical or horizontal stabilizer shell of an aircraft, produced in accordance with one of Claims 1 to 4.