Abstract: Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.—providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6), b.—positioning the fresh skin (3), the at least one fresh stringer, the fresh spars (5, 6) in a curing tool in a configuration corresponding to that of a base structure (8), c.—subjecting the structure (8) to a single curing cycle, obtaining a cured base structure (8).

Abstract: A method for manufacturing a composite material part comprising a web and at least one flange. In a laying up stage, a plurality of plies of different orientations, including 0° oriented plies, are laid up to obtain a flat laminate with edges comprising an outer contour and an inner contour, the flat laminate also comprising at least one section with a radius of curvature of less than 10 m. A forming stage comprises forming a fold along a folding line on the flat laminate to create a flange forming an angle with the web, and applying a stress tension to the 0° oriented plies located at least partially between the folding line and the outer contour of the flat laminate, in the at least one section, to avoid the appearance of wrinkles.

Abstract: An integrated composite trailing edge and its method of manufacturing. The trailing edge comprises an integrated main structure having an upper cover, lower flanges, and a set of ribs extending between the upper cover and the lower flanges, with a set of sandwich type lower panels attachable to the lower flanges of the integrated main structure. The method comprises the steps of providing a set of prepreg laminated preforms over a set of tool modules having a hollow so that each laminated configures a double C-shaped laminated preform having an upper section with a recess, two primary and secondary flanges, the upper section partly forming the upper cover, the two primary flanges partly forming the ribs and the two secondary flanges forming the lower flanges.

Abstract: A method for manufacturing a composite material part comprising a web and at least one flange. In a laying up stage, a plurality of plies of different orientations, including 0° oriented plies, are laid up to obtain a flat laminate with edges comprising an outer contour and an inner contour, the flat laminate also comprising at least one section with a radius of curvature of less than 10 m. A forming stage comprises forming a fold along a folding line on the flat laminate to create a flange forming an angle with the web, and applying a stress tension to the 0° oriented plies located at least partially between the folding line and the outer contour of the flat laminate, in the at least one section, to avoid the appearance of wrinkles.

Abstract: Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.—providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6), b.—positioning the fresh skin (3), the at least one fresh stringer, the fresh spars (5, 6) in a curing tool in a configuration corresponding to that of a base structure (8), c.—subjecting the structure (8) to a single curing cycle, obtaining a cured base structure (8).

Abstract: An integrated composite trailing edge and its method of manufacturing. The trailing edge comprises an integrated main structure having an upper cover, lower flanges, and a set of ribs extending between the upper cover and the lower flanges, with a set of sandwich type lower panels attachable to the lower flanges of the integrated main structure. The method comprises the steps of providing a set of prepreg laminated preforms over a set of tool modules having a hollow so that each laminated configures a double C-shaped laminated preform having an upper section with a recess, two primary and secondary flanges, the upper section partly forming the upper cover, the two primary flanges partly forming the ribs and the two secondary flanges forming the lower flanges.

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).