Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

Abstract: The invention provides an aircraft with a trimmable horizontal stabilizer (13) that not requires a cut-out in resistant areas of the rear fuselage and that occupies less space that in conventional horizontal stabilizers. The rear fuselage (5) comprises at least a first section (9) having a resistant fuselage and a second section (11), aft of the first section, having a non-resistant fuselage (i.e. a fairing). The load-bearing structure (30) of the horizontal stabilizer and the trimming actuator (50) are disposed inside said second section (11). The pivot element (41) is mounted on its forward side and coupled to the first section (9) of the rear fuselage. The connection fitting (21) is mounted on its rearward side and the trimming actuator (50) is disposed so that it exerts a force in the direction of the Z-axis of the aircraft on the connection fitting (21) during a trimming operation.

Abstract: Aircraft horizontal stabilizer surface (8) in which the sweep angle (40) of this surface (8), where this angle (40) is the one formed by the projection of the reference line of points located at 25% of the local chord (19) of the horizontal stabilizer surface (8) on a plane perpendicular to the aircraft plane of symmetry (21), and which also contains this plane to the flight direction of the aircraft with respect to the aircraft plane of symmetry (21), is less than 90 degrees, with this angle (40) being measured in the flight direction of the aircraft. In addition, the structural connection of this horizontal stabilizer surface (8) to the aircraft fuselage (1) is located at a closing frame (13) of this fuselage (1).

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: Aircraft horizontal stabilizer surface (8) in which the sweep angle (40) of this surface (8), where this angle (40) is the one formed by the projection of the reference line of points located at 25% of the local chord (19) of the horizontal stabilizer surface (8) on a plane perpendicular to the aircraft plane of symmetry (21), and which also contains this plane to the flight direction of the aircraft with respect to the aircraft plane of symmetry (21), is less than 90 degrees, with this angle (40) being measured in the flight direction of the aircraft. In addition, the structural connection of this horizontal stabilizer surface (8) to the aircraft fuselage (1) is located at a closing frame (13) of this fuselage (1).

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: 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.