Abstract: A lifting structure for aircraft is essentially applicable to a horizontal stabilizer that includes two side symmetrical boxes that converge at one end (its root) thereof in a shared center area in order to connect integrally in the central area. Both boxes connect by a single part that constitutes a center rib with a double T-shaped profile. The root of the side boxes overlap converging on the inside surfaces of the wings of the center rib. The connection is ensured with rivets (lap joint). The proposed connection simplifies the assembly process (single part) and lead to a weight reduction since a carbon fiber connecting rib can be used.

Abstract: The invention relates to a cover for the access opening in a composite material aircraft structure, characterized in that it comprises the following elements: an outer cover (18) arranged on the outer part of the aircraft skin (28), the carbon fiber layers (14) forming the skin (28) being deformed towards the inner part of the aircraft structure, leaving enough space between the aircraft structure and the outer part of the skin (28) for the seating of the outer cover (18). a composite material plate (15) arranged in the outer part of the skin (28) and surrounding the area for installing the outer cover (18); an inner cover (27) arranged on the inner part of the aircraft skin (28).

Abstract: The invention concerns an antirotation system for metal bushings that are installed on carbon fiber fittings used in the design and construction of aeronautical structures, particularly those that include carbon fiber components. The system is essentially characterized in that it comprises a main piece (1) linked to the respective metal bushing, linkage that comprises means for avoiding relative rotation between the metal bushing (2) and the main piece (1), at the same time that the main piece comprises at least one bracket (5) embracing at least one side portion (6) of the fitting for its immobilization.

Abstract: Aircraft aerofoil structure, in particular rear spar structure (1) for the joining of lateral box beams (2) of a horizontal stabilizer of an aircraft, said rear spar (1) comprising a right rear spar (5) and a left rear spar (6), moreover said structure of said rear spar (1) includes a central section formed by an integrated component (10), and said integrated component (10) includes fittings (11) that serve for joining said rear spar structure (1) to the aircraft fuselage and projections (12) that serve for joining the central section formed by the integrated component (10) to the right rear spar (5) and left rear spar (6).

Abstract: The invention relates to a cover for the access opening in a composite material aircraft structure, characterized in that it comprises the following elements: an outer cover (18) arranged on the outer part of the aircraft skin (28), the carbon fiber layers (14) forming the skin (28) being deformed towards the inner part of the aircraft structure, leaving enough space between the aircraft structure and the outer part of the skin (28) for the seating of the outer cover (18). a composite material plate (15) arranged in the outer part of the skin (28) and surrounding the area for installing the outer cover (18); an inner cover (27) arranged on the inner part of the aircraft skin (28).

Abstract: It is essentially applicable to a horizontal stabilizer that includes two side symmetrical boxes that converge at one end (its root) thereof in a shared center area in order to connect integrally in said central area. It is characterized in that both boxes connect by means of a single part that constitutes a center rib with a double T-shaped profile. The root of the side boxes overlap converging on the inside surfaces of the wings of the center rib. The connection is ensured with rivets (lap joint). The proposed connecting means simplifies the assembly process (single part) and lead to a weight reduction since that a carbon fiber connecting rib can be used.