Abstract: A manufacturing method of structures formed co-bonding second structural components to a first structural component. The method comprises the following steps: a) preparing for each second structural component an ensemble wherein a preform of the second structural component, surrounded by a band of a suitable material to form a vacuum bag, is disposed between curing tools which are thus in contact with the bag and not with the preform; b) positioning the ensembles on the first structural component and forming the vacuum bag for the complete structure joining the bands and complementary pieces; c) applying to the resulting assembly an autoclave cycle.

Abstract: Inspection methods and systems for detecting leaks in a vacuum bag assembly used in the manufacture of a composite part based on spraying helium over the vacuum bag and detecting the helium drawn by the vacuum inside the vacuum bag through a leak. The inspection methods comprise creating a local helium atmosphere in a chamber over the vacuum bag assembly by zones, following a programmed zonal sequence, for a first leak detection test of each zone and a subsequent second leak detection test if the first test gives a positive result. The inspection systems comprise a helium spraying system and helium detecting equipment arranged to implement the inspection methods.

Abstract: Inspection methods and systems for detecting leaks in a vacuum bag assembly used in the manufacture of a composite part based on spraying helium over the vacuum bag and detecting the helium drawn by the vacuum inside the vacuum bag through a leak. The inspection methods comprise creating a local helium atmosphere in a chamber over the vacuum bag assembly by zones, following a programmed zonal sequence, for a first leak detection test of each zone and a subsequent second leak detection test if the first test gives a positive result. The inspection systems comprise a helium spraying system and helium detecting equipment arranged to implement the inspection methods.

Abstract: A manufacturing method of structures formed co-bonding second structural components to a first structural component. The method comprises the following steps: a) preparing for each second structural component an ensemble wherein a preform of the second structural component, surrounded by a band of a suitable material to form a vacuum bag, is disposed between curing tools which are thus in contact with the bag and not with the preform; b) positioning the ensembles on the first structural component and forming the vacuum bag for the complete structure joining the bands and complementary pieces; c) applying to the resulting assembly an autoclave cycle.

Abstract: 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.

Abstract: 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.