Abstract: An aircraft assembly with a hot air exhaust outlet. The aircraft assembly has an assembly surface over which a hot-air exhaust flow from the hot-air exhaust outlet is exhausted. The aircraft assembly also has a vortex generator with a flow surface. The flow surface lies in an air flow over the vortex generator. The flow surface is arranged to interrupt the hot-air exhaust flow and generates a flow vortex to cool the air flow over the assembly surface.

Abstract: To facilitate the assembly of the wing unit of an aircraft, this wing unit includes two wings each having a lateral wing box extended toward the interior by a center wing box half having an interior end, the two wings being attached to one another using attachment bolts linking the two interior ends of the two center wing box halves, and passing through an intermediate wall connecting two fuselage frame walls.

Abstract: A device for a lacquer transfer includes a frame, transfer roller with a circumferential lateral wall, drive unit for rotating the transfer roller, and slit nozzle with a muzzle end for dispensing lacquer. The slit nozzle includes a first nozzle-part, second nozzle-part and deformation unit. The deformation unit is attached to the first nozzle-part, the lateral wall passing in a rotation direction subsequently the deformation unit and the muzzle end during transfer unit rotation. The lateral wall of the transfer roller is deformed by the deformation unit in the radial direction resulting in a deformation section of the lateral wall in the rotation direction behind the deformation unit, the muzzle end of the slit nozzle arranged for dispensing lacquer into depressions of the lateral wall. The transfer roller can roll with the outside contact surface on a work surface of a work piece for transferring lacquer from the depressions to the work surface of the work piece.

Abstract: A leading edge (3) of a control surface (1) for an aircraft includes a balance weight (6) attached to the forward-most region of the leading edge (3). The control surface (1) rotates with respect to the stabilizer (2) around a hinge line (5). The balance weight (6) is ahead of and adjacent to the most frontal portion (7) of the leading edge (3) of the control surface (1) are is inside the trailing edge of the stabilizer (2). This arrangement allows to have an anti-flutter balance weight without any impact in aerodynamic drag.

Abstract: To improve reliability and safety of an actuator assembly for a high-lift device, a torque sensing device is provided on a static structural part, which is used to mount the actuator of the actuator assembly to an aircraft interface, such as a rib or an interconnection strut. A controller determines a reaction torque value based on the output signal of the torque sensing device and monitors and controls the actuator based on the reaction torque value and predetermined load thresholds.

Abstract: A roller gear for use in a roller gear and sprocket configuration of a drive system is disclosed, particularly for use in a landing gear drive system of an aircraft. Alternative embodiments and, in particular, means for permitting removal and replacement of rollers and roller mounting pins in the roller gear are disclosed.

Abstract: A windshield for an aircraft cockpit is provided which includes a glazed windshield part which has a single curvature corresponding to a portion of the envelope of a cone extending between a lower plane and an upper plane which intersect an axis of the cone. The single curvature of the glazed part of the windshield enables the glazed part to be produced more easily, for example by rolling or by hydroforming. It also makes it possible to create configurations for a cockpit for two pilots, a single pilot or even no pilot, on the basis of a single aerodynamic shape of the fuselage of the aircraft by only adapting the structure of the windshield. Also provided are a windshield frame for such a windshield, a windshield assembly including such a windshield frame and such a windshield, and an aircraft equipped with such a windshield.

Abstract: A duct stringer is disclosed and forms at least part of a duct with a closed cross-section along which a fluid flows. An aperture is formed through a duct wall of the duct stringer and communicates with the duct. An insert is adhered in the duct stringer and is configured to engage with a fastening member to mount a fluid transporting conduit, such as a pipe, over the aperture.

Abstract: A method of monitoring the pressure of a tire of an aircraft, the method including: taking two or more pressure readings from the tire at different times; calculating an estimated deflation rate based on the pressure readings; and calculating a time for the tire to deflate to a reference pressure level based on the estimated deflation rate. Two or more temperature readings are each associated with one of the pressure readings, and the estimated deflation rate is calculated by normalising each pressure reading based on its associated temperature reading and a common reference temperature to obtain a temperature-normalised pressure reading, and calculating the estimated deflation rate based on the temperature-normalised pressure readings. The estimated deflation rate is compared with a threshold, and a warning provided if the estimated deflation rate exceeds the threshold.

Abstract: A disruption device for fixing to an aerial vehicle. The disruption device is adapted to disrupt at least one radio path between at least one receiving unit of an unmanned flying body and at least one transmitting unit provided for controlling the flight path of the unmanned flying body. An aerial vehicle having the disruption device is further provided.

Abstract: An aircraft seat arrangement having identical groupings, each separately including at least one aircraft seat, each including a voltage supply port associated only with the aircraft seat for the connection of external devices of a passenger seated on the aircraft seat, a voltage supply unit, with a voltage input, at least one voltage output, each connected to the voltage supply port of another of the aircraft seat, and a switching circuit, such that each of the voltage output can be activated and deactivated. At least one control unit is connected to the switching circuit, and a near-field communication reading device is connected to the control unit for wireless reception of near-field communication signals from an external near-field communication sending device. The communication reading device can receive signals from a predetermined group of predetermined near-field communication signals.

Abstract: A clamp to retain a block of material on a machining table including a body having a first face, a first front face oriented toward the machining table and the block of material when in use, a nose projecting relative to the first front face having a second front face parallel to the first front face, first and second edges connecting the first and second front faces, and at least one internally threaded hole opening at least partly at the level of the second front face with an axis forming a non-zero angle with the first face and the second front face, at least one grub screw screwed into the internally threaded hole having a pointed free end configured to penetrate into the block of material when in use when screwing in the grub screw, and a connecting system to demountably connect the clamp to the machining table.

Abstract: A rear engine attachment having a beam fixed to a pylon, a spreader pivotally mounted on the beam, the spreader comprising two ends situated on either side of a median plane, two rods located one on either side of the median plane, each rod having a first end fixed to one end of the spreader by a ball joint and a second end fixed to the engine, each ball joint comprising a clevis with two arms at the first end of the rod, a swivel bearing arranged on the end of the spreader, and a hinge pin passing through the two arms, the swivel bearing arranged between the two arms and fitted on the hinge pin. For each ball joint, an interface part is removably interposed between the end of the spreader and the first end of the rod and forms a contact surface between the spreader and the rod.

Abstract: A rear engine attachment having first and second parts, wherein the first part has two first clevises fixed to a lower face of a pylon, two second clevises fixed to a structural casing, two connecting rods mounted to be articulated between first and second clevises, and two shafts realizing the connections between the connecting rods and the clevises. The second part has a shoe fixed to the lower face and having a bore, a main rod which bears a vertical peg engaging in the bore and which is fixed to the structural casing by a first pivot connection, and a secondary rod fixed to the main rod by a second pivot connection and to the structural casing by a third pivot connection. Such a rear engine attachment is more compact, taking up space in the longitudinal direction and thus minimizing the space taken up in the transverse direction.

Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

Abstract: An air inlet for an aircraft nacelle, including a lip and a front frame, which together form a duct with D-shaped section receiving hot air. The front frame is arranged in an advanced position inside the lip. The lip has de-icing grooves, which communicate with the duct and extend essentially downstream of the front frame. Downstream of the front frame, outside of the de-icing grooves, the lip has perforated zones provided with sound absorption holes. The air inlet includes a foil, which hermetically seals the de-icing grooves and is provided with sound absorption holes facing the perforated zones. The air inlet comprises acoustic panels inside the lip downstream of the front frame. The advanced position of the front frame, due to the de-icing grooves which ensure the de-icing of the lip downstream of the front frame, allows the acoustic treatment surface of the air inlet to be increased.

Abstract: An aircraft pylon including a heat exchange device having a heat exchanger which includes a first circuit portion ducting a flow of hot air tapped off an engine of the aircraft and a second circuit portion ducting a flow of cold air, the first and second circuit portions of the heat exchanger being coaxial, separated by at least one partition forming an exchange surface, and positioned, at least partially, in the primary structure of the pylon.

Abstract: A portable tool comprising a hollow body delimiting two chambers and comprising a shoulder and a barrel extending from the shoulder. A piston slides in the chambers and a stem is secured to the piston and is accommodated in the barrel. A C-shaped head with a first end forms a shoe which presses against the shoulder and in which is created a bore into which the barrel fits, and with a second end facing the free end of the stem. A fastening system comprises a channel on the barrel perimeter. Two sliders are slidably mounted on the shoe parallel to a plane of movement which is perpendicular to the axis of the barrel. Each slider has an arc shaped face and movable between a retracted position in which the face is accommodated in the channel and an extended position in which the face is outside the channel.

Abstract: To facilitate assembly of an aircraft cockpit, a cockpit module includes an instrument panel to support at least one screen and an air conditioning distribution block bordering the instrument panel and integral with a rear face of it. The air conditioning distribution block includes an air distributor, an excess air collector, and air distribution channels each including a first end communicating with the air distributor and a second end communicating with the excess air collector, each distribution channel being equipped with an air outlet arranged between its first and second ends.

Abstract: An aircraft structural component is described, including an aircraft skeleton component which divides a space along a longitudinal axis of the aircraft skeleton component into two spatial portions arranged on opposite sides of the aircraft skeleton component, and including a fluid conduit component which runs on an outer side of the aircraft skeleton component and fluidically connects the two spatial portions. Also described is an aircraft wing with an aircraft structural component, as well as an aircraft with an aircraft structural component or with an aircraft wing.