Patent ID: 9079366
Filing Date: 2015-07-14
Classification: B29C,B29D,B29L,Y02T

Abstract:
1. A method for producing a fuselage section for an aircraft, having a composite fibre material, comprising the following steps: a) application of a first vacuum film to a stable winding core and evacuation of the first vacuum film, b) depositing of the fuselage section in layers on the stable winding core by wrapping the stable winding core with the layers, c) application of an outer mould that is unstable compared to the stable winding core, to the fuselage section, wherein the stable winding core stabilizes the outer mould, d) application of a second vacuum film to the outer mould, e) aeration of the first vacuum film and evacuation of the second vacuum film in order to draw the fuselage section closer to the outer mould and detach the fuselage section from the stable winding core at least in one region, wherein the steps a)-e) form an entire arrangement, and f) curing of the entire arrangement in an autoclave to produce the fuselage section, wherein the entire arrangement cured in the autoclave comprises the stable winding core, the first vacuum film, the layers, the outer mould and the second vacuum film, wherein the stable winding core stabilizes the outer mould during the curing.