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: Systems and methods for de-icing an aircraft surface. The systems create a shock pulse to create a shock activation. The shock pressure is designed to deform the surface of an erosion shield on the surface in order to expulse ice from the wing. The deformation may be between a negative to a positive shape. In one example, the de-icing occurs from a pulse delivered by pressurized fluid injected into and quickly removed from a recess between the aircraft surface and an erosion shield. A pulse of pressurized air or fluid may be injected into one or more cells formed in the recess, together or alternatively, according to the designed effect on the erosion shield surface.

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.