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The present invention relates to a tubular-shaped component (19) for an aeronautical fuselage made of composite materials comprising an outer skin (1) without joints having a cylindrical or cylindrical-conical shape, a plurality of stiffeners or stringers (2) longitudinally arranged in said outer sk

The present invention relates to a tubular-shaped component (19) for an aeronautical fuselage made of composite materials comprising an outer skin (1) without joints having a cylindrical or cylindrical-conical shape, a plurality of stiffeners or stringers (2) longitudinally arranged in said outer skin (1) and a plurality of anchoring elements (3) for anchoring other elements to subsequently be incorporated transversally arranged between said stiffeners or stringers (2). The invention also comprises a jig (18) comprising a support body (12) and a plurality of panels (9) that can shift between an extended position (10) and a retracted position (10') in both directions and a process for manufacturing said component (19) in the last step of which once the tubular component (19) is formed and cured, it is separated from the jig (18) by means of a longitudinal movement after the shifting of those elements of the jig (18) preventing it, and particularly the panels (9) that can be shifted.

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The invention claimed is: 1. A process for manufacturing a tubular-shaped component (19) for aeronautical fuselages made of composite materials comprising an outer skin (1) without joints having a cylindrical or cylindrical-conical shape, a plurality of stiffeners or stringers (2) longitudinally ar

The invention claimed is: 1. A process for manufacturing a tubular-shaped component (19) for aeronautical fuselages made of composite materials comprising an outer skin (1) without joints having a cylindrical or cylindrical-conical shape, a plurality of stiffeners or stringers (2) longitudinally arranged in said outer skin (1) and a plurality of anchoring elements (3) for anchoring other elements to subsequently be incorporated to the tubular component (19), transversally arranged between said stiffeners or stringers (2), comprising the following steps: a) Providing a jig (18) with an outer surface having a shape similar to the inner surface of the tubular component (19) including slots (7, 8) for housing the stiffeners or stringers (2) and the anchoring elements (3), respectively; b) Providing the stiffeners or stringers (2) and anchoring elements (3) and arranging them in said slots (7, 8); c) Laminating the outer skin (1) on the jig (18); d) Applying an autoclave curing cycle to the assembly of the jig (18) and the tubular component (19) provided with a curing membrane (20); e) Extracting the tubular component (19) by means of a longitudinal movement after the shifting of those elements of the jig (18) which prevent it. 2. A process for manufacturing a tubular-shaped component (19) for aeronautical fuselages made of composite materials according to claim 1, wherein step c) is carried out with a fiber placement machine by rotating the jig (18) and using means to hold the stiffeners or stringers (2) and the anchoring elements (3) in their position. 3. A process for manufacturing a tubular-shaped component (19) for aeronautical fuselages made of composite materials according to claim 1, wherein the shifting of said elements of the jig (18) in step e) is carried out by retracting them in the radial direction (11) without removing them from the jig (18). 4. A process for manufacturing a tubular-shaped component (19) for aeronautical fuselages made of composite materials according to claim 1, wherein the shifting of part of said elements of the jig (18) in step e) is carried out by retracting them in the radial direction (11) without removing them from the jig (18), and the shifting of another part of said elements of the jig (18) is carried out in the longitudinal direction (17) after their removal from the jig (18).