Abstract: An actuator for aviation applications, in particular for adjusting rotor blades in a helicopter, may include an electromechanical drive assembly connected to an output drive via a downstream transmission, where the drive assembly is divided into sub-drives that can be operated independently, and where at least two sub-drives are spatially separated from one another in that the transmission is placed between these sub-drives. The transmission may include at least two harmonic gearings coupled to one another by at least one first coupling element, where a first harmonic gearing is located inside a non-rotating first housing, where a second harmonic gearing is located inside a rotating second housing, and where the second housing is connected to the output drive.

Abstract: An anticorrosion coating and an article coated with an anticorrosion coating, especially for use in an aircraft, and a method of producing a coated article and a vehicle, especially an aircraft, including an anticorrosion coating or at least one such coated article. An anticorrosion coating includes an aluminum alloy having 0.03-0.5% by weight of tin. A coated article produced at least partly from a material and having at least partly been coated with the anticorrosion coating including an aluminum alloy having 0.03-0.5% by weight of tin. A method of producing the anticorrosion coating is also disclosed.

Abstract: An assembly for supplying power to an aircraft is disclosed having at least one battery housed in a respective housing, each housing comprising a wall in which a through-opening is arranged, and an exhaust device including a discharge duct connecting each housing opening to a common discharge port, a valve mounted on each opening. Each valve includes a membrane arranged so as to seal the opening closed and having a surface of pressure application towards the inside of the housing and a surface of pressure application towards the outside of the housing. The surface of pressure application towards the outside of the housing is larger than the surface of pressure application towards the inside of the housing, so that the membrane bursts at a bursting pressure inside the housing that is lower than a bursting pressure reached outside the housing.

Abstract: The integration of a hinged door with a door leaf in a non-pressurized aircraft. The non-pressurized aircraft includes a canopy frame with a canopy frame cross-section profile. The canopy frame cross section profile has first and second canopy frame faces that are arranged at a predetermined angle relative to each other, and a third canopy frame face that is arranged between the first and second canopy frame faces. The non-pressurized aircraft further includes a hinge that is entirely arranged within the outline of the non-pressurized aircraft and pivotally mounts the door leaf to the third canopy frame face.

Abstract: A wing for an aircraft is disclosed including a main wing, a leading edge high lift assembly having a leading edge high lift body, and a connection assembly movably connecting the leading edge high lift body to the main wing, wherein the connection assembly includes a drive system that is mounted to the main wing and connected to the leading edge high lift body for driving the leading edge high lift body between the retracted position and the extended position. The drive system includes a first drive unit and a second drive unit, the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section coupled to a first connection element and including a first output wheel. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section coupled to a second connection element and including a second output wheel.

Abstract: A cyclic pitch angle adjustment apparatus for a rotor or propeller and to a rotorcraft with such a rotor. The cyclic pitch angle adjustment apparatus may include levers that rotate rotor blades around associated pitch axes rods that mechanically link the levers with a bearing such that the rods are movable relative to the central point, the bearing being attached to a central rod that is movable and adapted for adjusting the cyclic pitch angle of the rotor blades from one pitch angle in one position to another pitch angle in another position.

Abstract: An aircraft sound diagnostic method includes a step of measurement of acoustic signals by a plurality of microphones mounted at different positions inside the aircraft, a step of recording of the measured acoustic signals, a computation step which generates a sound mapping on the basis of the measured acoustic signals, a step of comparison of the sound mapping and a reference mapping and a step of transmission of the comparison to a user device. The method makes it possible to track the trending of an abnormal noise or of an abnormal noise level and assist in determining the context thereof. An aircraft sound diagnostic device for implementing the method is also described.

Abstract: A method for monitoring a gearbox in an aircraft. The gearbox comprises at least one gearbox section with at least one measuring area. A first and a second electrical contact are arranged in the measuring area at a spacing from one another. A magnetic field is generated in the gearbox section. The magnetic field is adapted to move at least one ferromagnetic particle arranged in the gearbox section towards the measuring area, so that a bridge produced from one or more of the ferromagnetic particles is formed between the two electrical contacts. A measured value is generated based on an electrical parameter between the two electrical contacts. A measure of the criticality of a flight operation is determined on the basis of the measured value.

Abstract: A system for protection of at least one aircraft door sill, including a rigid panel having shape and dimensions configured to cover and to protect the sill at least partially having an attachment face oriented toward the sill of the aircraft and configured to come to rest on the latter and a step face oriented in the direction away from the attachment face. The panel includes, on one transverse side, at least one cavity forming a housing and, on the other side, an arrangement for removably fixing to the sill. The protection system equally includes at least one bar having a shape at least partially complementary to the cavity to assure the nesting thereof. In this way the panel protects the sill and can easily be replaced: the sill is provided with a rapidly interchangeable protection system.

Abstract: A wing for an aircraft is disclosed having a main wing, a high lift body, and a connection assembly movably connecting the high lift body to the main wing, such that the high lift body can be moved between a retracted position and at least one extended position. The connection assembly includes a drive system having a first drive unit and a second drive unit, wherein the first drive unit has a first input section coupled to a drive shaft, a first gear unit and a first output section drivingly coupled to the high lift body. The second drive unit has a second input section coupled to the drive shaft, a second gear unit, and a second output section drivingly coupled to the high lift body.

Abstract: An aircraft cabin section includes a door frame, which forms a door opening, a passenger door, which is arranged on the door frame and is configured to close the door opening, and a door insulation arrangement, which is larger in at least one direction than the door opening. The door insulation arrangement is produced from a textile which is heat-insulating and/or airflow-inhibiting. Furthermore, a corresponding door insulation arrangement and an aircraft having such an aircraft cabin section or such a door insulation arrangement are disclosed.

Abstract: A propulsion assembly with an outer compartment, an inner compartment, a supply pipe and a transfer pipe between the two compartments, a suction system between the two pipes, a regulating element that regulates the flow rate of air in the suction system and a fire-fighting system having a reservoir of extinguishing fluid, a discharge pipe connected to the reservoir, and a control system between the reservoir and the discharge pipe. The discharge pipe is configured and arranged to supply the transfer pipe when the control system is in the open position. The outside air is then driven by the suction system and passes through the two compartments in a forced manner and the extinguishing fluid reaches the transfer pipe to flow into the inner compartment.

Abstract: A transmitter device of a bi-static or multi-static radar system is disclosed and implemented for aerial surveillance. The transmitter device is intended to be on board a satellite orbiting the Earth. Once in orbit, the transmitter device is configured to obtain information relating to a region of interest monitored by at least one receiver device of the radar system, and to transmit a signal in a radio beam illuminating at least one portion of the region of interest.

Abstract: To reduce the bulk of the acquisition systems embedded onboard an aircraft and dedicated to predicting failures, an acquisition system is provided comprising an avionics rack and at least one recording device, in which the avionics rack comprises a front panel provided with at least one test connector configured to be connected to all or some of the data buses of the aircraft, each recording device comprises a housing and an acquisition port, the acquisition port being provided on an outer face of the housing, the acquisition port of each recording device is engaged with a corresponding test connector of the avionics rack, each recording device is configured to acquire at least some signals applied to the acquisition port by the corresponding test connector, and to store the acquired signals.

Abstract: A system for an aircraft comprising a controller configured to obtain a first piece of information regarding whether the aircraft has achieved lift-off; to obtain a second piece of information regarding whether the aircraft is in a flight phase in an initial part of lift-off; to determine, on the basis of at least the first piece of information whether the gear is retractable, and, if the gear is retractable in an initial part of the lift-off, to trigger a landing-gear-retraction alarm taking an audio form and/or a visual form, and, if the gear is retractable after the initial part of the lift-off to optionally trigger a second landing-gear-retraction alarm taking an audio form and/or a visual form. A method implemented by the system is provided. Advantageously, an omission of the retraction of the landing gear of an aircraft is notified to its flight crew.

Abstract: To improve measurement or assessment of fatigue damage to parts, a computer-implemented method for measuring striation properties of fatigue striations on a sample surface of a part is disclosed. A sample surface is imaged using a scanning electron microscope to obtain a sample image potentially containing the fatigue striations. A sample image patch potentially containing fatigue striations is selected from the sample image. After normalizing the sample image patch and enhancing line-like regular structures contained in the sample image patch, the normalized image patch is autocorrelated, Radon transformed and spectrally analyzed. The resulting power spectrum of the transformed image patch contains information about striation properties of the fatigue striations contained in the sample image, if any fatigue striations are present. Furthermore, a system for performing the method is disclosed.

Abstract: A table device for a vehicle cabin, in particular for a passenger cabin of an aircraft. The table device includes an active surface which is coated with at least one active material that is photoactive and antimicrobial. The table device furthermore includes an irradiation device, which is configured to irradiate the active surface with light. A passenger seat or a vehicle cabin may incorporate such a table device.

Abstract: An electric propulsion unit of an aircraft including a nacelle housing an electric power system, an electric motor and a cooling system for the electric power system; the nacelle including a central fairing, a front fairing which extends from the central fairing to a front end and a rear fairing which extends from the central fairing to a rear end. The front fairing includes a protrude positioned in a lower part of the front fairing, the protrude having a front face in a transverse plane, a main air inlet of the cooling system being positioned on the front face.

Abstract: An acoustic panel comprising a cellular structure, such as a honeycomb structure, having cells that open at least onto a first frontal face of the structure. The panel comprises a capsular skin which is fastened to the first frontal face of the cellular structure next to a plurality of cells. The capsular skin including a continuous layer of material, in one piece, forming capsules that extend into the cellular structure. At least one channel is provided at the apex of each capsule for the passage of acoustic waves. Such a panel effectively attenuates the noise of aircraft engines, in particular, the low frequencies. It is extremely easy to manufacture industrially, the capsular skin being able to be obtained by molding with polymerization in situ, the polymerizable material then adhering to the cellular structure while it polymerizes.

Abstract: A structural component for an aircraft including at least one heatable component section having a layer structure including an inner base structure, at least one heating layer having carbon allotropes embedded in a matrix material, at least one first group of consecutive layers including at least one anode layer, at least one first insulating layer, and at least one cathode layer having an electroactive coating. The first group of layers are arranged between the inner base structure and the at least one heating layer, and at least one protective layer is arranged outside the heating layer. The first group of layers constitute a structural battery. The at least one anode layer and the at least one cathode layer are electrically connectable with the heating layer.