Abstract: A seat for an aircraft includes at least one seat-portion structure; and an understructure. The understructure includes at least one guide element comprising a guide groove. The guide groove includes a first portion and a second portion, called the inclined portion. The seat further includes at least one seatbelt attachment and at least one attachment support. The seatbelt attachment is mounted rotatably with respect to the attachment support via an attachment shaft. The attachment support is mounted rotatably with respect to the seat-portion structure via a support shaft. The head of the attachment shaft is arranged inside the inclined portion of the guide groove when the seat is in an upright position.

Abstract: An aircraft interior unit with a detachable panel. The aircraft interior unit comprises a wall comprising a hollow panel, and a door mounted to the wall. The door is slidable between a closed position in which it covers an entrance to the aircraft interior unit, and an open position in which the entrance to the aircraft interior unit is uncovered. In the open position, the door is at least partially disposed within the hollow panel of the wall. The hollow panel can be detached from the rest of the aircraft interior unit, and the door, when moved from the open position, can be detached from the wall.

Abstract: An acoustic panel has two substantially parallel skins between which cavities forming Helmholtz resonators are arranged. One of the skins is bored with orifices, each of which opens into one of said cavities and forms a neck of the resonators. One or more of said cavities includes of a hollow structure having the shape of a triangular-based prism.

Abstract: A seat unit, in particular for an aircraft cabin, includes a seat provided with seat cushion and backrest kinematics, and a seat-base structure on which the seat is mounted. The seat-base structure includes a frame with a tubular structure including a first lower tube and a second lower tube, the first lower tube and the second lower tube each carrying at least one bolt intended to be fastened to rails, and two fastening feet for fastening the seat cushion and backrest kinematics. A fastening foot is formed by a tube connected by one of its ends to the first lower tube of the frame and by its other end to the second lower tube of the frame.

Abstract: A group of stator vanes for a row of stator vanes of a stage of a turbomachine compressor, the vanes of the group of stator vanes being close together and affording easy assembly. The group of stator vanes include a platform of a first vane having an aperture for accommodating the head of a second vane, the outer surface of the platform of the first vane being in contact with the inner surface of the platform of the second vane.

Abstract: A handling assembly of a propulsion assembly includes a nacelle and an aircraft turbojet engine. The handling assembly also includes a handling envelope covering at least half of the circumference of an outer wall of an air inlet of the nacelle, when the propulsion assembly is mounted on said handling assembly, and at least two interfaces for attaching slings, the slings being connected to a hoisting system which is external to said handling assembly. A method for handling a propulsion assembly is also disclosed.

Abstract: An acquisition and analysis device to be integrated in a pre-existing aircraft that includes original systems comprising pilot controls and also an autopilot system includes acquisition means arranged to acquire parameters produced by the original systems, and analysis means arranged on the basis of the parameters, to evaluate whether the pre-existing aircraft is normal or abnormal, and to evaluate the current stage of flight of the pre-existing aircraft, on the basis of the state of the pre-existing aircraft and of the current stage of flight of the pre-existing aircraft, to define a piloting setpoint selected from piloting setpoints comprising at least a manual piloting setpoint produced by a pilot actuating pilot controls, an autopilot setpoint produced by the autopilot system, and an alternative piloting setpoint, and to cause the selected piloting setpoint to be transmitted to the original systems of the pre-existing aircraft.

Abstract: A turbomachine of the type with an unducted fan, comprising: a separation nozzle splitting an air flow into a primary flow and a secondary flow; a compressor compressing the primary flow; and an air/oil heat exchanger; wherein the exchanger is positioned in a channel through which a tertiary flow passes, the tertiary flow being drawn from the secondary flow upstream of the exchanger and meeting at least one annular row of rotor blades of the compressor downstream of the exchanger.

Abstract: A process for three-dimensional printing of a workpiece (10), comprising a succession of steps for producing a layer (18) of the workpiece (10) by means of a nozzle (28) which has an output cross-section along a path (32) of the nozzle (28), wherein, during at least one step for producing a layer (18), use is made of at least one nozzle (28), an output portion (42) of which has an output cross-section which is variable between a first maximum cross-section and a second minimum cross-section, and wherein the cross-section of at least one part of an output portion (42) of the nozzle is varied along at least one portion (32a, 32b) of the path (32).

Abstract: A propulsion unit having a propeller for an aircraft including a nacelle; a propeller mounted in the nacelle so as to be capable of rotating about a longitudinal axis of rotation, the propeller having blades mounted by a root so as to be capable of pivoting between a deployed position, in which they extend radially relative to the axis of rotation, and a folded position, in which they are longitudinally received against the nacelle; drive means that rotate the propeller; indexing means for stopping the propeller in at least one indexed angular position (? i) relative to the nacelle; the propulsion unit wherein the indexing means consist of a stepping electric motor including a rotor that is coupled to the propeller.

Abstract: An actuating device of a pump of a fuel pumping system of an engine, including a motor, a generator, an inverter, a switching member and a control member, the motor including a first rotor coupled to the pump and a first stator including at least one input stator winding, the generator including a second rotor coupled to a drive shaft of the engine, and a second stator including at least one output stator winding, the control member being configured to control the switching member in order to selectively connect each input stator winding: to a corresponding output stator winding if a speed of the engine is higher than or equal to a predetermined speed; to a corresponding output of the inverter, otherwise.

Abstract: Propulsion system for a helicopter comprising a main engine, a main rotor, a main gearbox including an output mechanically connected to the main rotor, a reduction gearbox mechanically coupled between the main engine and a first input of the main gearbox, and an assistance device. The assistance device comprises a first electric machine mechanically coupled to the reduction gearbox and configured to operate as an electric generator to take off energy produced by the main engine, and a second electric machine mechanically coupled to a second input of the main gearbox, the second electric machine being supplied with electrical power by the first electric machine and configured to operate as an electric motor to deliver additional mechanical power to the main gearbox.

Abstract: Aircraft having at least one propulsion unit supplied with hydrogen by at least one hydrogen tank, and having at least one thrust reversal system including at least one actuator. The aircraft can include at least one means for storing or transporting the residual hydrogen of the propulsion unit, a fuel cell disposed in the hydrogen power source and supplied with hydrogen by the at least one means for storing the residual hydrogen, and a hydrogen thrust reverser actuation system. The thrust reverser actuation system can include a hydrogen thrust reverser actuation controller and a hydrogen primary power unit with a fuel cell supplied with hydrogen and powering the at least one thrust reverser actuator.

Abstract: A mechanical part for an aircraft turbomachine, the mechanical part being made of metal and comprising at least one profiled surface configured to ensure an oil flow during operation.

Abstract: An encapsulated shock absorber of an aircraft undercarriage includes a sliding rod slidably mounted in a leg strut of the undercarriage and an inner cylinder extending inside the strut. The inner cylinder is fastened to the strut via a top end, and the rod slides around the inner cylinder. The inner cylinder is terminated inside the sliding rod by a diaphragm that defines an oil chamber in the shock absorber and inside the sliding rod. A mixed oil/gas chamber is located in the inner cylinder, and an expansion chamber extends between the sliding rod and the inner cylinder. A hole being made in the inner cylinder in register with the expansion chamber is connected by a pipe to a pressure sensor situated outside the strut. The pipe extends inside the inner cylinder from the hole to the top end of the inner cylinder.

Abstract: A turbine ring assembly having ring segments made of ceramic matrix composite material and each having first and second attachment tabs and a cavity for the circulation of air flow, a metal support having a first bracket and a second bracket bearing axially upstream against the second tab, a first metal flange arranged upstream of the first bracket and having an inner periphery bearing axially downstream against the first tab and an outer periphery fastened to the first bracket, and air passage orifices formed in the inner periphery of the first flange and/or in the second bracket, the orifices configured to ensure that the air flow passes from the cavity to the outside of the assembly.

Abstract: A landing gear of an aircraft includes a pair of wheels between which an electric actuator at least partially covered with a lightning arrester cowl is placed. The lightning arrester cowl has an insulating matrix onto which at least an electrical conductor is attached. The electrical conductor includes electrical connection means for connecting the electrical conductor to a ground conductor of the aircraft.

Abstract: A method for filling a hydraulic circuit of an electro-hydrostatic system includes connecting first and third shut-off valves to a discharge valve, and connecting a second shut-off valve to a filling valve, while the second and third shut-off valves are closed, opening the filling valve, the discharge valve and the first shut-off valve and operating a vacuum generator, once a vacuum has been established in the hydraulic circuit, opening the second shut-off valve in order to fill the hydraulic circuit with pressurized hydraulic fluid while the vacuum generator is still in operation, once the hydraulic circuit has been filled with fluid, closing the first shut-off valve and then opening the third shut-off valve in order to bypass the vacuum generator and circulate the fluid through the electro-hydrostatic system until the fluid contained in the hydraulic circuit reaches a predetermined pressure, and closing the discharge valve and the filling valve.

Abstract: A thrust reverser includes a fixed structure and a movable structure defining an air stream, a flap including a single wall perforated on the surface thereof, and a structure strengthening the flap and having an acoustic function. The flap being articulated between the fixed structure and the movable structure to allow in a direct jet position, disposing the wall along an acoustic section of the movable structure and allowing the circulation of an air flow through the air stream, the acoustic section forming with the structure of the wall an acoustic resonator, and in a reverse jet position, disposing the wall to deflect an air flow passing through the air stream and allow the passage through the wall and through the air stream of a portion of the air flow deflected by the flap.

Abstract: A thrust reverser for an aircraft propulsion unit. The thrust reverser includes three gates that can be deployed downstream of an outlet section of the propulsion unit. The device increases the possibilities for installation of the reverser, in particular when a tail assembly extends in line with the propulsion unit.