Abstract: A discharge valve for an aircraft includes a cylindrical body having an inlet and an outlet, a first valve, and a second valve arranged inside the body. The first and the second valves are rotatable around a first axle and a second axle, respectively, between a closed position and an open position. A mechanism for locking the second valve in the closed position includes a control lever arranged around a third axle, an interface arranged on the second valve, and a device for rotating the third axle. The control lever is rotatably movable around the third axle between an unlocking position, in which the interface is in abutment against the drive device, and a locking position, in which the interface is engaged in the drive device.

Abstract: A cell storage box for storing a battery cell includes a first end provided with a safety valve and a second end. The cell storage box includes a metal case having a bottom wall and side walls, and a thermally insulating support arranged in the metal case. The thermally insulating support includes a shoulder raised relative to the bottom wall of the metal case, a side bearing wall configured such that the cell rests against the at least one side bearing wall so as to keep the cell at a first distance from the at least one side wall of the metal case, and an opening arranged below the shoulder in order to allow smoke and gas to escape during a runaway of the cell.

Abstract: A device for detecting a frosting intensity for an aircraft in flight includes a surface for collecting the frost and measuring means capable of measuring the thickness of the frost deposited on the frost collection surface. The device further includes calculation means configured to determine, at predetermined time intervals (Tsamp), the change in the thickness of the frost, and control means configured to generate an alarm signal when the difference in the thickness of the frost measured between two time intervals (Tsamp) is greater than a threshold value.

Abstract: A magnetic head for a magnetic detector for detecting metal particles in a hydraulic circuit includes an axial body internally including at least one magnet, at least a first electrode defining an air gap zone located in the magnetic field created by the magnet, such that the circuit creates a particle alignment zone in the air gap, and an electrical connector for electrically connecting the electrodes. The magnet can be a diametrically magnetized magnet.

Abstract: An aircraft includes an engine, a fuel tank, a chamber, a system, and an introduction line. The chamber is located in the tank, occupies only a part of the tank, and includes a sensor for measuring a property of the fuel. The system injects fuel into the line. The introduction line introduces fuel from the injection system into the chamber. The introduction line includes a valve capable of preventing an introduction of fuel from the injection system into the chamber via the line.

Abstract: On board an aircraft, a method is perform in which the following steps are implemented in the following order: measuring a first density value, a first dielectric constant value and a first temperature value of the fuel at a first time, measuring a second density value, a second dielectric constant value and a second temperature value of the fuel, determining parameters of a function for calculating a density from a temperature or a dielectric constant, measuring a volume flow rate value and at least one of a third temperature value and a third dielectric constant value of the fuel in a fuel injection duct in the engine, and determining a density value of the fuel and a mass flow rate of the fuel in the injection line.

Abstract: A servovalve having a pilot stage includes two hydraulic elements that are movable relative to each other so as to move a power-directing member, the pilot stage including a linear actuator having a main pusher arranged to modify the relative position of the hydraulic elements. The pilot stage has a position feedback lever.

Abstract: A device for unlocking a system for closing a container by means of a tie, such as a rope or strap, in particular a tie tensioned between closing eyelets, includes a cutting tool (O) capable of cutting the tie in order to unlock the closing system. It also includes an actuation member linked to the cutting tool, the actuation member being capable of being manipulated manually by a user in order to cause the cutting tool (O) to move into a position for severing the tie.

Abstract: A method for the surface treatment of a part made of aluminum or aluminum alloy, comprising an anodization step and a step of sealing with a silicate salt. Additionally, a surface treatment method according to the invention for manufacturing an aluminium or aluminium alloy part intended, in particular for use in the aviation sector.

Abstract: Embodiments of the present invention provide a fuel tank communication system. The communication system includes a main body (30) used to connect two fuel bladder flanges (12, 20) to one another. The communication system provides two separate, independent locking features (42, 60) that can secure fuel bladders to one another.

Abstract: Described is a heated gaseous welder system and associated methods of welding plastic with the heated gaseous welder system. The heated gaseous welder system includes a welding tool and a welder control unit. The welder control unit includes a gaseous control system and a heater control system. The gaseous control system is configured to selectively supply a gas to the welding tool and control at least one characteristic of the gas supplied to the welding tool. The heater control system is configured to selectively control power supplied to the welding tool.

Abstract: Quick coupling device 1 for transferring liquid for an aircraft, comprising a female member 7 configured to be connected to a first reservoir, said female member 7 forming a passage and comprising a cylindrical portion 13 and a radial portion 14, a male member 2 configured to be connected to a second reservoir, said male member 2 forming a passage, slidably mounted in a liquid-tight manner in the female member 7 and comprising a cylindrical portion 3 and a radial portion 4, and a member 40 for locking the male member 2 in the female member 7, the locking member 40 being disposed between the radial portion 14 of the female member 7 and the radial portion 4 of the male member 2, the locking member 40 surrounding the male member 2 and leaving a limited sliding extent for the male member 2 with respect to the female member 7, engaging with the female member 7 in the locked position and releasing the female member 7 in the unlocked position, the locking member 40 comprising an axial blocking lock that can be actua

Abstract: A cell storage box for storing a battery cell includes a first end provided with a safety valve and a second end. The cell storage box includes a metal case having a bottom wall and side walls, and a thermally insulating support arranged in the metal case. The thermally insulating support includes a shoulder raised relative to the bottom wall of the metal case, a side bearing wall configured such that the cell rests against the at least one side bearing wall so as to keep the cell at a first distance from the at least one side wall of the metal case, and an opening arranged below the shoulder in order to allow smoke and gas to escape during a runaway of the cell.

Abstract: A device for disconnection by a mechanical action includes at least one mechanical connection part, in particular a buckle held closed by spring action, linked to at least one triggering means via at least one connecting member, and a release lever configured to be triggered by application of a force according to a predefined opening direction. The disconnect device also includes at least one guide for the connecting member configured to redirect an effort applied on the triggering means, when opening is required, towards the mechanical connection part linked to the connecting member, according to the predefined opening direction.

Abstract: The invention relates to a protective sheath designed, in particular but not exclusively, for an aircraft. The conduit is flexible and can have a small radius of curvature able to be obtained without torsion and allowing access, over the majority or entirety of its length, to the electrical wire or cable inside. The protective sheath (1) comprises a flexible body generally having a cylindrical shape, the flexible body being slit along at least a certain length and along a longitudinal axis, characterised in that the body has an open-work wall and in that the sheath is capable of being deformed along its length in order to be compressed/compacted on itself.

Abstract: An inflatable device for aircraft buoyancy, configured to be inflated in case of emergency landing on water, the device comprising a first inflatable chamber configured to be inflated from a source of gas, to change from a folded state to an inflated stated, a plurality of second inflatable chambers, each configured to be supplied from gas flowing in the first chamber, via at least one supply passage, each second inflatable chamber configured to be inflated to change from a folded state to an inflated stated, wherein each supply passage comprises a check valve.

Abstract: A device for unlocking a system for closing a container by means of a tie, such as a rope or strap, in particular a tie tensioned between closing eyelets, includes a cutting tool (O) capable of cutting the tie in order to unlock the closing system. It also includes an actuation member linked to the cutting tool, the actuation member being capable of being manipulated manually by a user in order to cause the cutting tool (O) to move into a position for severing the tie.

Abstract: A device for absorbing kinetic energy of a vehicle or any other moving body includes at least one bundle of straps formed by at least one strap having at least one first strand and at least one second strand secured by a connection means capable of being progressively destroyed by a tensile force intended to be applied on the first strand of the strap. The device also includes at least one anchoring means suitable for connecting the kinetic energy absorption device to a structure on which is intended to be installed. The anchoring means is arranged downstream of the bundle of straps with respect to a deployment direction of the strap under the tensile force intended to be applied on the first strand of the strap.

Abstract: Quick coupling device 1 for transferring liquid for an aircraft, comprising a female member 7 configured to be connected to a first reservoir, said female member 7 forming a passage and comprising a cylindrical portion 13 and a radial portion 14, a male member 2 configured to be connected to a second reservoir, said male member 2 forming a passage, slidably mounted in a liquid-tight manner in the female member 7 and comprising a cylindrical portion 3 and a radial portion 4, and a member 40 for locking the male member 2 in the female member 7, the locking member 40 being disposed between the radial portion 14 of the female member 7 and the radial portion 4 of the male member 2, the locking member 40 surrounding the male member 2 and leaving a limited sliding extent for the male member 2 with respect to the female member 7, engaging with the female member 7 in the locked position and releasing the female member 7 in the unlocked position, the locking member 40 comprising an axial blocking lock that can be actua

Abstract: An inflatable device for aircraft buoyancy, configured to be inflated in case of emergency landing on water, the device comprising a first inflatable chamber configured to be inflated from a source of gas, to change from a folded state to an inflated stated, a plurality of second inflatable chambers, each configured to be supplied from gas flowing in the first chamber, via at least one supply passage, each second inflatable chamber configured to be inflated to change from a folded state to an inflated stated, wherein each supply passage comprises a check valve.