Abstract: An aircraft provided with a wall having an exterior surface in contact with air flows external to the aircraft, an internal cavity in the aircraft, recessed relative to the exterior surface of the wall, at least one mobile trapdoor, which in closed position prolongs the exterior surface in such a way as to shut off the cavity from the exterior, and which in open position projects relative to the exterior surface in such a way as to open the cavity to the exterior, and provided with at least one mobile aerodynamic deflector, whose movement is slaved to that of the at least one trapdoor, the at least one aerodynamic deflector projecting relative to the exterior surface in a zone thereof situated outside the zone covered by the at least one trapdoor when the at least one trapdoor is open.

Abstract: The invention relates to an aircraft (10) provided with: a wall (14) having an exterior surface in contact with air flows external to the aircraft, an internal cavity (16) in the aircraft, recessed relative to the exterior surface of the wall, at least one mobile trapdoor (18, 20), which in closed position prolongs the exterior surface in such a way as to shut off the cavity from the exterior, and which in open position projects relative to the exterior surface in such a way as to open the cavity to the exterior, characterized in that it is provided with at least one mobile aerodynamic deflector (30, 32), whose movement is slaved to that of the said at least one trapdoor, the said at least one aerodynamic deflector projecting relative to the exterior surface in a zone thereof situated outside the zone covered by the said at least one trapdoor when the said at least one trapdoor is open.

Abstract: A method for preventing vibration of a rudder of an aircraft may have, on a lateral aerodynamic surface of the aircraft's rudder, a protruding aerodynamic element capable of generating an aerodynamic effect tending to rotate the rudder about its articulation axis. An actuator of the rudder is controlled such that it counters the action of the protruding aerodynamic element and such that it imposes on the rudder a position of equilibrium in aerodynamic extension of the fixed vertical stabilizer.

Abstract: Method making it possible to prevent vibration of a rudder of an aircraft and aircraft using this method. According to the invention: on one (6G) of the said lateral aerodynamic surfaces of the rudder (4), there is fixed a protruding aerodynamic element (14) capable of generating an aerodynamic effect tending to rotate the said rudder (4) about the said articulation axis (8); and the actuating means of the said rudder (4) are controlled such that they counter the action of the said protruding aerodynamic element (14) and such that they impose on the said rudder (4) a position of equilibrium in aerodynamic extension of the fixed vertical stabilizer (3).

Abstract: An aircraft includes a fuselage and a fixed flying surface having two wings, and a cradle-shaped ventral fairing at the crossover of the latter with the flying surface and provided with two longitudinal flanges climbing laterally along the fuselage and being provided with an opening for the passage with play of the corresponding wing to form a first peripheral slot around the ventral fairing and a second peripheral slot around each wing. An elongate seal is fixed to the periphery of the ventral fairing and to the periphery of each opening, so at to shut off the first and second slots, respectively. The seal includes a longitudinal elastic end lip applied, via the inner face of its free end, respectively against the fuselage or the flying surface and a longitudinal leaktightness member, carried by the inner face of the seal set back with respect to the end lip and also able to be applied against the fuselage or flying surface, respectively.

Abstract: According to the invention, fitted into the slot (20) between the suction face side (32) of a wing (6) and said ventral fairing (10) is a seal (22), the internal face (26) of the free end (28) of the lip (24) of which comprises at least one boss (30) able to keep said lip locally away from said suction face side (32) to form a controlled leakage of air passing through said slot (20).

Abstract: Aircraft with ventral fairing and seal for such an aircraft.

Abstract: Aircraft with ventral fairing and seal for such an aircraft.

Abstract: Aircraft wing equipped with high-lift flaps and with at least one pylon for suspending an engine. According to the invention, the upper part of the pylon is bent to avoid discontinuity of the wing leading edge between said pylon and the high-lift flaps regardless of whether or not said flaps are in out-spread position. The invention improves aerodynamic performances both in smooth configuration and in high-lift configuration.

Abstract: The invention relates to aircraft wings, wherein the fairing element between the leading edge of a wing and the fuselage comprises a streamlining flap movable between a folded position in which it is housed in a recess in the fairing element and forms a part of the leading edge and the part adjacent the lower surface of said fairing element, and an extended position in which it ensures continuity of the leading edge between the fuselage and the high-lift spoiler likewise in extended position. Moreover, there is a communication between the housing of the streamlining flap and the housing of the high-lift spoiler so that, when these two flap elements are in their extended positions, the air penetrating in the housing of the streamlining flap disposed on the lower surface side emerges through the housing of the high-lift spoiler disposed on the upper surface side, with the result that there is an increased upper surface blowing.