Abstract: The present disclosure refers to a method for manufacturing carbon fiber panels stiffened with omega stringers for the construction of aircraft structures, such as fuselage sections, wing panels, etc. One tubular pressure member is provided for each omega stringer of the structure to be manufactured, wherein the tubular pressure member is configured with the shape of the omega stringer. Each tubular pressure member is enclosed between the omega stringer and part of the laminate, and autoclave pressure is applied to the interior of the tubular pressure member, so that the tubular pressure member is used to consolidate the omega stringers and/or part of the laminate from the interior of these two elements, while these two elements are being co-cured or co-bonded in an autoclave. Imperfections on those internal surfaces such as resin wrinkles of the structure are reduced.

Abstract: The disclosure refers to a method for manufacturing rod-shaped components of composite material, for example rowings or fillers, wherein a laminate is layered by automatically laying up a plurality of plies of composite material, which is then cut in an automated machine to obtain a plurality of rods having substantially the same cross-sectional shape. The obtained rods are then simultaneously conformed by applying heat and pressure to obtain rods with the desired cross-sectional shape. With the method of the disclosure, a large number of these types of components are produced with improved quality and in a very simple manner, using the machinery and equipment already commonly existing in a factory of aeronautic components.

Abstract: An apparatus for manufacturing composite stringers from a composite laminate comprising a male mold, a main caul plate, two fixed female mold halves, two secondary movable caul plates and a retention device. The main caul plate is located below the male mold, the female mold halves are located at both sides of the main caul plate and the secondary movable caul plates, each of them located respectively over each one of the two female mold halves. The male mold, the main caul plate, the two female mold halves and the two secondary caul plates are non-developable surfaces. The retention device keeps each secondary movable caul plate at a predetermined distance of its respective female mold half.

Abstract: The disclosure refers to a method for manufacturing rod-shaped components of composite material, for example rowings or fillers, wherein a laminate is layered by automatically laying up a plurality of plies of composite material, which is then cut in an automated machine to obtain a plurality of rods having substantially the same cross-sectional shape. The obtained rods are then simultaneously conformed by applying heat and pressure to obtain rods with the desired cross-sectional shape. With the method of the disclosure, a large number of these types of components are produced with improved quality and in a very simple manner, using the machinery and equipment already commonly existing in a factory of aeronautic components.

Abstract: The present disclosure refers to a method for manufacturing carbon fiber panels stiffened with omega stringers for the construction of aircraft structures, such as fuselage sections, wing panels, etc. One tubular pressure member is provided for each omega stringer of the structure to be manufactured, wherein the tubular pressure member is configured with the shape of the omega stringer. Each tubular pressure member is enclosed between the omega stringer and part of the laminate, and autoclave pressure is applied to the interior of the tubular pressure member, so that the tubular pressure member is used to consolidate the omega stringers and/or part of the laminate from the interior of these two elements, while these two elements are being co-cured or co-bonded in an autoclave. Imperfections on those internal surfaces such as resin wrinkles of the structure are reduced.

Abstract: An apparatus for manufacturing composite stringers from a composite laminate comprising a male mould, a main caul plate, two fixed female mould halves, two secondary movable caul plates and a retention device. The main caul plate is located below the male mould, the female mould halves are located at both sides of the main caul plate and the secondary movable caul plates, each of them located respectively over each one of the two female mould halves. The male mould, the main caul plate, the two female mould halves and the two secondary caul plates are non-developable surfaces. The retention device keeps each secondary movable caul plate at a predetermined distance of its respective female mould half.

Abstract: The present invention relates to a process for manufacturing panels (9) for aeronautical structures with U-shaped stiffening members (13) and I-shaped stiffening members (17) between their webs comprising the following steps: providing laminates for shaping the skin (11) on the curing tool (31); providing planar laminates (23) for shaping the stiffening members (13, 17); shaping the U-shaped stiffening members (13) on individual shaping tools (33) and placing the I-shaped stiffening elements (17) in said tools; grouping said individual shaping tools (33) together on an assembly tool (41); placing the group of stiffening members (13, 17) on the skin (11); placing a vacuum bag (55) on the assembly with the aid of profiles (59); consolidating said assembly by means of a curing process under suitable pressure and temperature conditions using external tools (60) to assure verticality of the webs of the stiffening members (13, 17).