Patent ID: 7597772
Filing Date: 2009-10-06
Classification: B29C,B29D,B29L,B64C,Y02T,Y10T

Abstract:
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 ( b) Providing the stiffeners or stringers ( c) Laminating the outer skin ( d) Applying an autoclave curing cycle to the assembly of the jig ( e) Extracting the tubular component (