Abstract: A nasal dilator comprises magnets. The nasal dilator is a set comprising two bodies. Each of the two bodies has a first leg having at a distal portion thereof a magnet; and a second leg connected to the first leg via a bridge comprising flexible material. Each of the two bodies are designed so as to allow said body to be clamped to an ala nasi of a human nose between the distal portions of said first leg and said second leg. The magnets of the bodies are aligned such that with a body clamped to the ala nasi of a nose, the magnet is oriented at an angle to a plane defined by the ala nasi area clamped between said two distal portions of said first leg and second leg. Thanks to the repelling action of the magnets, the alae nasi are pushed apart, resulting in improved ease of breathing.

Abstract: A nasal dilator comprises magnets. The nasal dilator is a set comprising two bodies. Each of the two bodies has a first leg having at a distal portion thereof a magnet; and a second leg connected to the first leg via a bridge comprising flexible material. Each of the two bodies are designed so as to allow said body to be clamped to an ala nasi of a human nose between the distal portions of said first leg and said second leg. The magnets of the bodies are aligned such that with a body clamped to the ala nasi of a nose, the magnet is oriented at an angle to a plane defined by the ala nasi area clamped between said two distal portions of said first leg and second leg. Thanks to the repelling action of the magnets, the alae nasi are pushed apart, resulting in improved ease of breathing.

Abstract: An aircraft nacelle includes an air intake (12) followed at the upper part by a part (14) integral with the mast, called a cap, and at least one door (16) with a curved profile, and a device for encircling it in the form of at least one flexible element (38), guide elements (40) for allowing the at least one flexible element (38) to follow the curved profile of the at least one door, a first anchoring point (42) of the at least one flexible element (38) integral with a first edge (78) of the cap and another anchoring point of the at least one flexible element (38) integral with a second edge (80) of the cap, whereby the anchoring points (42) allow a relative translational movement, in a direction that is parallel to the longitudinal axis of the nacelle, between the cap (14) and the at least one door (16).

Abstract: A closing system for a fan cowling on a jet engine of an aircraft that has at least one assembly including a male contrivance integral with the cowling, and a female contrivance integral with the jet engine that has a lower element forming at least one first guide ramp and an upper element forming at least one second guide ramp, with the aforementioned female contrivance being suitable on the one hand for guiding the male contrivance during the opening and/or the closing of the fan cowling, and on the other hand providing a limitation of the radial and circumferential displacements of the male contrivance.

Abstract: An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes: a flexible element that follows the curved profile of the door between two remote anchoring points, at least one safety index including a latch pivotable around an axis of rotation, and connected to the door so as to occupy a locked position in which the end of the latch rests against the inside surface of an edge upstream from the door, and an unlocked position in which the end of the latch is offset relative to the edge, whereby in the locked position, the latch prevents the scooping phenomena by limiting movements of the door in the radial direction toward the outside of the nacelle, and elements for stretching the flexible element between the two anchoring points and for controlling the pivoting in the locked position of the latch.

Abstract: Aircraft nacelle including a cowling and an engine, the cowling including a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system including a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling including an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion.

Abstract: An aircraft nacelle includes an air intake (12) followed at the upper part by a part (14) integral with the mast, called a cap, and at least one door (16) with a curved profile, and a device for encircling it in the form of at least one flexible element (38), guide elements (40) for allowing the at least one flexible element (38) to follow the curved profile of the at least one door, a first anchoring point (42) of the at least one flexible element (38) integral with a first edge (78) of the cap and another anchoring point of the at least one flexible element (38) integral with a second edge (80) of the cap, whereby the anchoring points (42) allow a relative translational movement, in a direction that is parallel to the longitudinal axis of the nacelle, between the cap (14) and the at least one door (16).

Abstract: An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes: a flexible element that follows the curved profile of the door between two remote anchoring points, at least one safety index including a latch pivotable around an axis of rotation, and connected to the door so as to occupy a locked position in which the end of the latch rests against the inside surface of an edge upstream from the door, and an unlocked position in which the end of the latch is offset relative to the edge, whereby in the locked position, the latch prevents the scooping phenomena by limiting movements of the door in the radial direction toward the outside of the nacelle, and elements for stretching the flexible element between the two anchoring points and for controlling the pivoting in the locked position of the latch.

Abstract: A closing system for a fan cowling on a jet engine of an aircraft that has at least one assembly including a male contrivance integral with the cowling, and a female contrivance integral with the jet engine that has a lower element forming at least one first guide ramp and an upper element forming at least one second guide ramp, with the aforementioned female contrivance being suitable on the one hand for guiding the male contrivance during the opening and/or the closing of the fan cowling, and on the other hand providing a limitation of the radial and circumferential displacements of the male contrivance.

Abstract: Aircraft nacelle comprising a cowling and an engine, the cowling comprising a fixed portion and a mobile portion able to slide in order to define a radial opening with the mobile portion, a thrust reverser system comprising a plurality of flaps intended to be deployed in order to seal at least partially an annular channel surrounding the engine, the mobile portion of the cowling comprising an annular housing extending longitudinally in order to receive the flaps in rest position. Each flap is linked to the fixed portion by a pivot joint and is linked to the mobile portion by a sliding-pivot joint, in such a way that a sliding of the mobile portion in separating from the fixed portion provokes a rotation of each flap around the axis of rotation of the joint with the fixed portion.

Abstract: Stiffening means are added into an air intake structure of an aircraft engine nacelle, to stiffen this structure, in order to prevent any modification to the shape of the structure, for example following suction of the intake lip inwards the fan duct. The stiffening means pass through the structure diagonally, in other words one of their ends is fixed, for example, in the forward direction and externally, and the other end is fixed in the aft direction and internally. These stiffening means may be added to the existing forward and aft stiffening frames.

Abstract: Stiffening means are added into an air intake structure of an aircraft engine nacelle, to stiffen this structure, in order to prevent any modification to the shape of the structure, for example following suction of the intake lip inwards the fan duct. The stiffening means pass through the structure diagonally, in other words one of their ends is fixed, for example, in the forward direction and externally, and the other end is fixed in the aft direction and internally. These stiffening means may be added to the existing forward and aft stiffening frames.

Abstract: A multi-component acoustically resistive layer, for acoustical attenuating panels having a cellular core (1) flanked, on the sound wave arrival side, with an acoustically damping layer (2) and, on the opposite side, with a rear reflector (3), comprises a first structural component (4) in contact with the aerodynamic flow and formed by at least one layer of fibers connected by a suitable resin and oriented in the direction of aerodynamic flow the component (4) comprising a suitable quantity of open surface; a dissipating component (6) disposed against the surface of the first component (4) opposite the flow, formed by a metallic cloth; and a second structural component (7) formed by at least one layer of fibers connected by a suitable resin, oriented orthogonally to the direction of aerodynamic flow. The second structural component (7) is connected to the cellular core (1) and comprises a suitable open surface quantity.

Abstract: A multi-component acoustically resistive layer, for acoustical attenuating panels having a cellular core (1) flanked, on the sound wave arrival side, with an acoustically damping layer (2) and, on the opposite side, with a rear reflector (3), comprises a first structural component (4) in contact with the aerodynamic flow and formed by at least one layer of fibers connected by a suitable resin and oriented in the direction of aerodynamic flow the component (4) comprising a suitable quantity of open surface; a dissipating component (6) disposed against the surface of the first component (4) opposite the flow, formed by a metallic cloth; and a second structural component (7) formed by at least one layer of fibers connected by a suitable resin, oriented orthogonally to the direction of aerodynamic flow. The second structural component (7) is connected to the cellular core (1) and comprises a suitable open surface quantity.

Abstract: A process for producing an acoustically resistive layer, particularly for the nacelles of aircraft jet engines. The process includes producing a structural component by using thermoplastic resins, this component having a given quantity of open surface relative to the acoustic waves to be treated. The structural component is connected to an acoustic metallic fabric having a mesh adapted to the open surface quantity of the structural component. Then, the thermoplastic resin is heated under pressure at high temperature.

Abstract: An air inlet cowl for a jet engine, particularly an aeroengine, includes a leading edge deicer, a hollow leading edge defining an internal peripheral chamber, closed by a first internal partition, and an exhaust orifice, in the leading edge, connecting the internal chamber with the outside. The cowl further includes a pressurized hot air feedpipe for being connected, at its rear end away from the leading edge and passing through a second internal partition, to a pressurized hot air circuit and, at its front end toward the leading edge, to an injector of pressurized hot air into the internal chamber, a protective internal casing functioning with the first and second internal partitions to define an isolation volume enclosing the feedpipe, and an air extraction opening, in the first partition, to place the isolation volume in communication with the internal peripheral chamber.

Abstract: A panel of composite material, in particular with a thermosetting or thermoplastic matrix, with edges and/or external surface protected from shocks and erosion, for any streamlining element for housings or nacelles of aeronautical motors, comprises, over all or a portion of its edges, a cladding which forms a border overlapping the two opposite surfaces of the panel. The border comprises a metallic cloth connected to the structure of the panel by an adhesive agent, diffused through the cloth. The panel is particularly applicable to aircraft.

Abstract: A process for the production of an acoustical attenuating panel comprises emplacing on a mold a layer (1′a) with structural properties constituted by filaments (7, 8) pre-impregnated with a thermoplastic or thermosetting resin, by draping, winding or wrapping, such that the layer has an open surface quantity of about 30% of the total surface of the exposed layer, emplacing from above the layer with structural properties a layer (1′b) with acoustical properties constituted by a microporous cloth of a thickness of about one tenth of that of the layer with structural properties, then emplacing a cellular structure (2) and a reflector (3) with if desired the addition of an adhesive (5, 6) between the components, at least one step of baking in an autoclave being practiced at the end of at least one of the above-mentioned emplacing steps.

Abstract: Air inlet cowl for a jet engine, provided with deicing means.