Abstract: A composite skin (11) with swept angle and dihedral for an aircraft mid-box lifting surface having a left side (5), a right side (7) and a central transition area (9) where both sides meet, that is designed and manufactured as a single part from left tip to right tip following a common ply structure for the whole part defined in relation to a single orientation rosette (25). The invention also refers to a composite aircraft mid-box lifting surface including an upper and lower panel with said composite skin (11).

Abstract: A composite skin (11) with swept angle and dihedral for an aircraft mid-box lifting surface having a left side (5), a right side (7) and a central transition area (9) where both sides meet, that is designed and manufactured as a single part from left tip to right tip following a common ply structure for the whole part defined in relation to a single orientation rosette (25). The invention also refers to a composite aircraft mid-box lifting surface including an upper and lower panel with said composite skin (11).

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 fibers 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 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).