Patent ID: 7597772

Claim:
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.