Abstract: An aircraft includes a structure exhibiting a median plane XZ and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane XZ, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane XZ independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced.

Abstract: An aircraft includes a structure exhibiting a median plane XZ and including a fuselage, a fixed vertical stabilizer at the rear of the fuselage, an adjustable horizontal stabilizer rotatably mounted about a horizontal axis on a first section of the structure, and extending on either side of the median plane XZ, and at the rear, two elevators mounted rotatably about a horizontal axis on a second section of the structure on either side of the median plane XZ independently of the adjustable horizontal stabilizer. In an aircraft of this kind, the elevators no longer have any impact on the adjustable horizontal stabilizer, which allows, among other things, the dimensions of the adjustable horizontal stabilizer, and also of the actuator operating them, to be reduced.

Abstract: The seal comprises a casing made of two portions (1, 2) crimped into one another with an accurate hermetic position adjustment at interfaces (15, 6b) and a composite structure comprising inside the casing an advantageously flexible and resilient core (24) and a winding (20) of brush bristles. This structure directly extends facing internal faces (9, 10) facing each other in the casing, which compresses the same and has an arcuate shape having a slightly higher radius of curvature. The composite structure is held at an accurate position, firmly but free of constraint.

Abstract: The seal comprises a casing made of two portions (1, 2) crimped into one another with an accurate hermetic position adjustment at interfaces (15, 6b) and a composite structure comprising inside the casing an advantageously flexible and resilient core (24) and a winding (20) of brush bristles. This structure directly extends facing internal faces (9, 10) facing each other in the casing, which compresses the same and has an arcuate shape having a slightly higher radius of curvature. The composite structure is held at an accurate position, firmly but free of constraint.

Abstract: A process and a device for automatically optimizing on the ground the aerodynamic configuration of an aircraft. The device (1) includes means (7, 8, 10) for determining and applying to the spoilers (6) a command providing the aircraft with an optimum aerodynamic configuration.

Abstract: The method of the invention comprises imparting to the flaps (6G, 6D) of said aircraft either a nose-up deflection (?F) corresponding to the maximum sharpness if the nose-up order is higher than a predetermined threshold, or a deflection (?0) corresponding to the minimum drag if the nose-up order is lower than said threshold.

Abstract: A process and device for the automatic flight optimization of the aerodynamic configuration of an aircraft. The device (1) includes means (7, 8, 10) for determining and applying to the spoilers (6) of the aircraft commands for providing the aircraft with an optimum aerodynamic configuration.

Abstract: According to the invention, during take-off, the aircraft (AC) is given an attitude (?c) close to the tail-touching attitude and the ailerons (6G, 6D) are fully deflected downwards.

Abstract: According to the invention, during take-off, the aircraft (AC) is given the tail strike attitude (?ts) and the ailerons (6G, 6D) are deflected fully downwards.

Abstract: In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b0) or corresponds either to the maximum sharpness of the aircraft (b1), or the optimal lift of the latter (b2).

Abstract: According to the invention, during take-off, the aircraft (AC) is given an attitude (?c) close to the tail-touching attitude and the ailerons (6G, 6D) are fully deflected downwards.

Abstract: A roll steering method subdivides the direction of an aircraft control surface into two elements and, during a roll control operation using ailerons, steers an upper element of the control surface in the roll direction and a lower element in the opposite direction.

Abstract: The method of the invention comprises imparting to the flaps (6G, 6D) of said aircraft either a nose-up deflection (?F) corresponding to the maximum sharpness if the nose-up order is higher than a predetermined threshold, or a deflection (?0) corresponding to the minimum drag if the nose-up order is lower than said threshold.

Abstract: According to the invention, during take-off, the aircraft (AC) is given the tail strike attitude (?ts) and the ailerons (6G, 6D) arc deflected fully downwards.

Abstract: A process and device for the automatic flight optimisation of the aerodynamic configuration of an aircraft. The device (1) includes means (7, 8, 10) for determining and applying to the spoilers (6) of the aircraft commands for providing the aircraft with an optimum aerodynamic configuration.

Abstract: A process and a device for automatically optimising on the ground the aerodynamic configuration of an aircraft. The device (1) includes means (7, 8, 10) for determining and applying to the spoilers (6) a command providing the aircraft with an optimum aerodynamic configuration.

Abstract: The invention concerns a method which consists in subdividing the direction of the control surface into at least two elements (6I, 6S) and, during a roll control using the ailerons (5G, 5D), steering the upper element (6S) in the roll direction and the lower element (6I) in the opposite direction.

Abstract: In conformance with the invention, based on the incident conditions and velocity, the steering of the ailerons is weakly negative (b0) or corresponds either to the maximum sharpness of the aircraft (b1), or the optimal lift of the latter (b2).

Abstract: Process for reducing the aerodynamic loads applied to the elevators of an aircraft during takeoff wherein, prior to the rotation, the adjustable horizontal tailplane (2) is nose-up overdeflected and the elevators (4) are nose-down deflected.

Abstract: Process for improving the maneuverability of an aircraft during a resource. According to the invention, prior to the resource, the adjustable horizontal tailplane (2) is nose-up deflected and the elevators (4) are nose-down deflected.