Abstract: The manufacturing method object of the invention comprises the following stages: A) stacking strips of prepreg material on a laminating tool (14), so that an angled laminated part (2) is obtained comprising a central section (2a) contained in a first plane (12), at least one side section (2b) contained in a second plane (13), and at least one bending axis (5) between the central section (2a) and the at least one side section (2b), so that, the first plane and the second plane form an angle ?; B) forming of the angled laminated part (2) comprising bending along the bending axis (5) the, at least, one side section with respect to the central section (2a), obtaining a formed part (6); C) curing, of the formed part (6).

Abstract: A method of manufacturing composite material parts is provided. The method includes tape laying by means of fiber placement on the outer surface of a tape laying tool, such that at least one laminate with a geometry different from the end geometry of the part is obtained and forming the at least one laminate obtained in tape laying by means of a forming tool, such that the laminate acquires the end geometry of the part. The method also includes curing the at least one part.

Abstract: The manufacturing method object of the invention comprises the following stages: A) stacking strips of prepreg material on a laminating tool (14), so that an angled laminated part (2) is obtained comprising a central section (2a) contained in a first plane (12), at least one side section (2b) contained in a second plane (13), and at least one bending axis (5) between the central section (2a) and the at least one side section (2b), so that, the first plane and the second plane form an angle ?; B) forming of the angled laminated part (2) comprising bending along the bending axis (5) the, at least, one side section with respect to the central section (2a), obtaining a formed part (6); C) curing, of the formed part (6).

Abstract: A method of manufacturing composite material parts is provided. The method includes tape laying by means of fiber placement on the outer surface of a tape laying tool , such that at least one laminate with a geometry different from the end geometry of the part is obtained and forming the at least one laminate obtained in tape laying by means of a forming tool, such that the laminate acquires the end geometry of the part. The method also includes curing the at least one part.

Abstract: A mechanically fastened permanent or detachable joint between two or more parts (21, 23, 25, 41), at least one of them made of a composite material, preferably carbon fibres impregnated with thermoset resin, with continuous plies from the full-composite area along the joint area (15) and including a metal reinforcement, preferably made of titanium, in the joint area (15), the joint area (15) thickness being increased in the thickness of said reinforcement plus the eventual additional composite plies laid only on the reinforced area. The metal reinforcement may consist of one or more metal foils or sheets (31) interleaved between the composite plies or one or more metal plates (33) embedded between two of the composite plies.

Abstract: A composite beam that comprises a web (21) having a corrugated-shaped profile, with aligned parts (23, 22) in two parallel planes (27, 25) in the longitudinal direction and tilted parts (29) between them; two flanges (17, 19); a first element (33) of C-shape and a second element (43, 53, 63) of beam-shape, such as C or Z, each of them having webs (35; 45, 55, 65) bonded to the parallel parts (23, 22) of the corrugated web in one plane (27, 25) enclosing the web (21) between them, and having the caps (37, 39; 47, 49; 57, 59; 67, 69) of said first and second elements bonded to one or two additional single flanges (7, 9) or bonded between them to form the beam flanges (17, 19).

Abstract: The invention relates to a stringer (11, 21, 31) made of a composite material for stiffening panels made of a composite material, particularly those used in the aeronautics industry, formed by a foot (15) for joining with the panel and a structural member (13, 23, 33) with a structural reinforcement (17, 27, 37) embedded at the end opposite to the foot (15) formed by high-modulus unidirectional fibers of the same material as the stringer or another material compatible with it. The invention also relates to a process of manufacturing the stringer.