Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

Abstract: An acoustic structure for an aircraft nacelle which comprises an acoustically resistive substructure, at least one layer of cells and a reflective layer. The acoustic structure comprises at least one single-piece substructure which divides up the layer of cells and which incorporates elongated elements of a de-icing system.

Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closed and open positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective open positions. From the open positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward the closed position. In some embodiments, the nacelle further includes an additional, or second, flap.

Abstract: A nacelle has a fixed cowl and a mobile cowl, which is movable along a translation path between closing and opening positions, a window delimited by the fixed cowl and the mobile cowl and open between an airflow and exterior of the nacelle, a reverser flap rotatably mounted to move between closed and open positions, and a drive mechanism configured to control passage of the reverser flap between the closed and open positions as the mobile cowl moves between the closed and open positions. From the closing/closed positions, the drive mechanism assures a translation of the mobile cowl and a rotation of the reverser flap toward their respective opening/open positions. From the open/opening positions, the drive mechanism assures a rotation of the reverser flap and a translation of the mobile cowl toward their respective closed/closing position. In some embodiments, the nacelle further includes an additional, or second, flap.

Abstract: A nacelle for a ducted fan turbojet engine comprising an engine. The nacelle comprises a fixed cowl, an upstream wall bounding off, with the engine, a working section for a secondary flow, a movable cowl with an interior wall and an exterior wall, and movable in translation between a closing position where the exterior wall adjoins the fixed cowl and the interior wall prolongs the upstream wall, and an opening position where the exterior wall is distant from the fixed cowl so as to open a window and the interior wall is distant from the upstream wall, an inverter flap between the interior wall and the exterior wall mounted to be free in rotation about an axis of rotation situated on the interior wall and a drive mechanism for moving the movable cowl.

Abstract: The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear.

Abstract: An acoustic structure for an aircraft nacelle which comprises an acoustically resistive substructure, at least one layer of cells and a reflective layer. The acoustic structure comprises at least one single-piece substructure which divides up the layer of cells and which incorporates elongated elements of a de-icing system.

Abstract: This relates to a process for manufacturing a microstructured coating on a substrate, which comprises a step of spraying molten particles having a diameter comprised between 0.05 ?m and 5 ?m onto the substrate, the spraying being carried out by at least one plasma torch, which is moved relative to the substrate, the movement parameters and/or the flowrate of particles sprayed by the plasma torches being variable as a function of the position of the plasma torches, ensuring a variable thickness for the coating formed by the particles, at various points of the substrate. The embodiment also relates to a wall having a coating obtained by this process.

Abstract: An aircraft nacelle includes a wall that delimits an inside pipe (42) that channels a stream of air to a power plant, at the front a lip (44) and on the outside an outside wall (46) that delimits a cavity (54), whereby the outside wall includes—at its inside surface—at least one stiffener (58) that is arranged in a transverse plane, characterized in that the at least one stiffener (58) includes at least one drainage opening that allows the flow of liquids through the stiffener (58) in the direction of a discharge opening (56) that is located away from the lip in such a way as to limit the risks of air being sucked inside the cavity (54).

Abstract: An acoustic treatment panel that is connected to an air intake of an aircraft nacelle, includes at least one acoustically resistive structure (30) and a reflective layer (32), between which are located—in a direction that is essentially perpendicular to the longitudinal direction of the nacelle—bands (34) of alveolar cells spaced in such a way as to allow the passage of hot air provided for a frost treatment, characterized in that it includes pipes (36) for hot air that are each delimited by at least one partition that extends from the acoustically resistive layer (30) up to the reflective layer (32) in such a way as to insulate the bands (34) of cells in the longitudinal direction.

Abstract: An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation.

Abstract: An air discharging device (20) for an aircraft turbine engine, comprising at least one door (24) displaceable between an open and a closed position of a corresponding orifice (30) and comprising two valves (26, 28), which delimit between them a conduit (68) for guiding a portion (74) of the secondary flow (76) outwards in the downstream direction, and which are integral with each other and are hinged around a pivot axis (58), so that in said open position, the upstream end of said internal valve (26) protrudes from the inner side relative to the internal surface (12), the downstream end of said external valve (28) protrudes from the external side relative to the external surface (14), and said internal valve (26) is spaced away from the fixed structure (22) so that an air passage exists downstream of said internal valve (26), between the latter and said fixed structure (22).

Abstract: An aircraft nacelle that makes it possible to channel a stream of air in a longitudinal direction and that includes at least two panels (50, 50?) placed end to end in the longitudinal direction, each including a so-called aerodynamic surface (52, 52?) that is in contact with the air stream and an edge (54, 54?) that is in contact with the edge of the other panel, characterized in that at least one of the panels includes—at its edge (54, 54?)—at least one partition (58) that projects relative to the edge that extends in the direction of the edge of the other panel, in a manner that is secant to the aerodynamic surface and in a plane that contains the longitudinal direction, so as to limit the circulation of air between the edges of the panels.

Abstract: The invention proposes to protect a rear part of a floor of an aft fairing of a pylon of an aircraft bypass turbojet engine using a film of cool air formed of part of a bypass flow of the jet engine which is guided under the floor by two lateral wall portions of this fairing which have been profiled for this purpose. To do that, these two lateral wall portions delimit respective air passage spaces formed between a forward part of the floor and a jetpipe of the turbojet engine and which open laterally and towards the rear.

Abstract: An aircraft turbojet nacelle comprising blowing means intended to inject a tangential airflow (Ft) into the internal volume (V) of the nacelle, said blowing means being provided in a wall of the air intake of the nacelle in the supersonic area of said air intake. The invention also concerns a method for controlling separation in an aircraft nacelle, wherein a tangential airflow is injected (Ft) into the internal volume (V) of the nacelle in the locally supersonic area of the air intake so as to pull the main airflow (F) into the extension of the inner wall of the nacelle.

Abstract: A process for producing a panel for acoustic treatment including a resistive porous layer, an alveolar structure, a reflective layer with openings, and a drainage plate having a furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film a core whose cross-section is adapted to that of the evacuation pipe so that the core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the core, demolding the drainage plate and removing the core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer.

Abstract: A nacelle, for an aircraft jet engine having a high bypass ratio, in which a jet engine having a longitudinal axis is mounted. The nacelle includes a wall that concentrically, and at least partially, surrounds the jet engine and together defines an annular duct. The nacelle further includes a displacement device that controllably displaces a portion of the nacelle wall in order to modify the section of the flow outlet passage and form at least one longitudinally extending opening. A device for forming a fluid barrier along the at least one longitudinally extending opening is provided to counteract the natural exhaust.

Abstract: An aircraft leading edge is extended by an aerodynamic surface providing an aerodynamic flow and where air discharges are arranged preventing separation of the aerodynamic flow. The air discharges are arranged in at least two rows essentially parallel to the leading edge and in an offset manner for at least two consecutive rows. At least one block is inserted between two walls that form the aerodynamic surface. The block includes, on the one hand, an outside surface extending the aerodynamic surface, a first inclined surface contacting the first wall forming the aerodynamic surface, and a second inclined surface contacting the second wall that forms the aerodynamic surface, and, on the other hand, projecting and/or hollow shapes that are made at the inclined surfaces and that are arranged in an alternating fashion from one surface to the next, allowing air to pass on both sides of the aerodynamic surface.

Abstract: A process for producing a panel for acoustic treatment including an acoustically resistive porous layer, at least one alveolar structure, a reflective layer with openings, and a drainage plate having at least one furrow for delimiting at least one evacuation pipe when the drainage plate is flattened against the free surface of the reflective layer, includes: shaping, if necessary, the reflective layer according to its final geometry, affixing a demolding film on at least one portion of the free surface of the reflective layer, positioning on the demolding film at least one core whose cross-section is adapted to that of the evacuation pipe so that the at least one core covers the openings of the reflective layer, molding the drainage plate on the demolding film and the at least one core, demolding the drainage plate and removing the at least one core and the demolding film, and making the drainage plate integral with the free surface of the reflective layer.

Abstract: An aircraft nacelle includes at its outside wall a cowl moveable relative to the nacelle so as to block or unblock an opening. The cowl includes an articulation and locking/unlocking elements distant from the upstream edge of the cowl that include elements for limiting the appearance of scooping phenomena. The limiting elements include at least one lock integral with the rest of the nacelle or respectively the cowl that can occupy a locked state in which part of the lock interferes with the cowl or respectively the rest of the nacelle and prevents a deformation that includes a radial component of the cowl, and another free state in which the part no longer interferes with the cowl or respectively the rest of the nacelle and allows the opening movement of the cowl, with the switch from one state to the next being generated by a gas pressure variation.