| 摘要 |
Simplification of the manufacture of composite material fuselages for aircraft, as well as mass reduction of fuselage sections and space optimization inside such fuselage sections. To accomplish this, it is proposed to use stringers of a new type which have a closed transverse section, and which are thus able to be self-positioned relative to one another by being positioned edge-to-edge on a stringer supporting structure, such as the outer surface of a mandrel. The installation of the stringers in grooves of conjugate shape is by this means made unnecessary. The stringers have cut-outs located between circumferential frames, and are able to house utility systems. |
| 主权项 |
1. A method for manufacturing a fuselage section for an aircraft, including:
manufacturing at least one fuselage structure by means of the following steps: preparing a supporting structure, preparing pre-cured composite material stringers, each of which having a transverse section which is closed such that it has a first base plate and a second base plate which are separate from one another, and also two cores respectively connecting pairs of lateral ends of said base plates, followed by installing the pre-cured stringers on said supporting structure, such that said first base plate of each stringer is resting on at least one outer surface of said supporting structure, and so as to constitute at least one assembly of stringers in which every pair of consecutive stringers in a transverse direction is such that one of said cores of each of the stringers of said pair of stringers is applied against one of said cores of the other stringer of said pair of stringers, followed by forming a skin made of a composite material, hereinafter called an outer skin, covering said second respective base plates of the stringers of each previously constituted assembly of stringers, followed by strengthening said outer skin and said stringers, so as to make said respective second base plates of said stringers adhere to said outer skin, followed by, obtaining by this means a unitary fuselage structure formed from said outer skin and from said stringers, and in which said first respective base plates of said stringers jointly form a wall, hereinafter called an inner wall, followed by separating said fuselage structure from said supporting structure; forming a fuselage skin having a closed transverse section, by means of said at least one fuselage structure; installing circumferential frames within a space delimited by said fuselage skin, and attaching said circumferential frames to said inner wall of said at least one fuselage structure forming said fuselage skin; making at least one cut-out in said inner wall, located between said two cores of at least one of said stringers and between two of said circumferential frames arranged consecutively. |
