Abstract: A device for repairing a damaged zone in a first cavity, with a first diameter, of an intermediate layer interposed between two layers that have a second cavity with a second diameter smaller than the first diameter. The device includes a stop that forms an abutment at the interface between the first cavity and one of the second cavities, a ring having a deformable corrugated shape, an initial inside diameter, an initial outside diameter smaller than the second diameter, and being positioned in the first cavity, a deformation element having an elastically variable outside diameter initially smaller than the initial inside diameter of the ring, and a tool being able to increase the outside diameter of the deformation element so that it deforms the ring in the first cavity in order to reduce the difference between the first and second diameters.

Abstract: A connecting rod including two non-connected rod elements coaxial with a longitudinal axis which are offset along the longitudinal axis, and an energy-absorption device that absorbs energy by plastic deformation. The energy-absorption device includes a coaxial hollow tube with a wall which deforms plastically when subjected to an axial compressive force exceeding a certain threshold, a coaxial pin having ends immobilized with respect to the rod elements in the event of tensile forces, and a sleeve fitting over the two facing ends of the rod elements which are positioned one on each side of the energy-absorption device, the sleeve being slidable with respect to one rod element in order to allow the hollow tube and/or the pin to deform and absorb energy. The sleeve limits a range of deformation so that a breaking point of the energy-absorption device is not reached.

Abstract: An air inlet for nacelle of an aircraft propulsion unit comprising an inner envelope provided with a plurality of orifices for passage of fluid passing through the envelope, and a lip connected to the upstream edge of the inner envelope, and having a portion devoid of orifices for passage of fluid with an axial span of between 20% and 90% of the span of the inner envelope, and a circumferential span a of between 60° and 150° about a longitudinal axis of the air inlet. A process for repairing an air inlet comprising cutting out a recess in an upstream edge of an inner envelope of the air inlet, then arranging and fixing an impermeable panel in the recess so as to create an air inlet of the type described above.

Abstract: A repair part enables rapid and efficient repair of damaged metal structures, in particular airframe fuselage skins having internal and external faces, without necessitating any additional thickness compromising the transmission of waves. To this end, the repair part includes a double internal/external plate adapted to be fastened to the internal face and the external face of the metal structure, respectively. The repair part also includes a central hub connecting the internal plate and the external plate and forming a groove between the plates. The part is constituted of a single composite material block, and a glass ply, lining the groove, may be positioned between the plates and the structure. The hub may have passing through it at least one orifice adapted to allow connections to pass through the structure.

Abstract: A device for repairing a damaged zone in a first cavity, with a first diameter, of an intermediate layer interposed between two layers that have a second cavity with a second diameter smaller than the first diameter. The device includes a stop that forms an abutment at the interface between the first cavity and one of the second cavities, a ring having a deformable corrugated shape, an initial inside diameter, an initial outside diameter smaller than the second diameter, and being positioned in the first cavity, a deformation element having an elastically variable outside diameter initially smaller than the initial inside diameter of the ring, and a tool being able to increase the outside diameter of the deformation element so that it deforms the ring in the first cavity in order to reduce the difference between the first and second diameters.

Abstract: In the method of fastening aircraft parts together, the following steps are performed: crimping an element onto at least two parts so as to fasten them together; and screwing a screw into the element through at least one other part so as to fasten all the parts together and so as to place a head of the screw in a flush position relative to the other part.

Abstract: A device for repairing defects in an internal layer of a structure, for example, an aircraft. The device includes a cylindrical body which rotates around its axial direction, a movement conversion device housed in the cylindrical body and assembled such that it is able to move in the axial direction, a configuration device able to cause the displacement of the conversion device by an axial traveling motion, and a cutting element coupled to the cylindrical body and to the conversion device such that the cutting element is able to be made to rotate by the cylindrical body and to be made to move with a radial displacement by the conversion device between a folded position and a deployed position through an opening defined in the cylindrical body in order to machine the internal layer with a cut which depends on the axial displacement of the conversion device.

Abstract: A connecting rod including two non-connected rod elements coaxial with a longitudinal axis which are offset along the longitudinal axis, and an energy-absorption device that absorbs energy by plastic deformation. The energy-absorption device includes a coaxial hollow tube with a wall which deforms plastically when subjected to an axial compressive force exceeding a certain threshold, a coaxial pin having ends immobilized with respect to the rod elements in the event of tensile forces, and a sleeve fitting over the two facing ends of the rod elements which are positioned one on each side of the energy-absorption device, the sleeve being slidable with respect to one rod element in order to allow the hollow tube and/or the pin to deform and absorb energy. The sleeve limits a range of deformation so that a breaking point of the energy-absorption device is not reached.

Abstract: A device for repairing defects in an internal layer of a structure, for example, an aircraft. The device includes a cylindrical body which rotates around its axial direction, a movement conversion device housed in the cylindrical body and assembled such that it is able to move in the axial direction, a configuration device able to cause the displacement of the conversion device by an axial traveling motion, and a cutting element coupled to the cylindrical body and to the conversion device such that the cutting element is able to be made to rotate by the cylindrical body and to be made to move with a radial displacement by the conversion device between a folded position and a deployed position through an opening defined in the cylindrical body in order to machine the internal layer with a cut which depends on the axial displacement of the conversion device.

Abstract: The invention aims to enable rapid and efficient repair of damaged metal structures, in particular airframe fuselage skins, without necessitating any additional thickness compromising the transmission of waves. To this end it proposes a double internal/external plate constituted by a particular material. In one embodiment, the damaged structure having an external face and an internal face, the part features a substantially plane double internal/external plate adapted to be fastened to the internal face and the external face of the metal structure, respectively, and a central hub connecting the internal plate and the external plate. A groove is thus formed between these plates. The part is constituted of a single composite material block, and a glass ply, lining the groove, may be positioned between the plates and the structure. The hub may have passing through it at least one orifice adapted to allow connections to pass through the structure.

Abstract: An air inlet for nacelle of an aircraft propulsion unit comprising an inner envelope provided with a plurality of orifices for passage of fluid passing through said envelope, and a lip connected to the upstream edge of said inner envelope, and having a portion devoid of orifices for passage of fluid with an axial span of between 20% and 90% of the span of said inner envelope, and a circumferential span ? of between 60° and 150° about a longitudinal axis of said air inlet. A process for repairing an air inlet comprising cutting out a recess in an upstream edge of an inner envelope of the air inlet, then arranging and fixing an impermeable panel in said recess so as to create an air inlet of the type described above.

Abstract: In the method of fastening aircraft parts together, the following steps are performed: crimping an element onto at least two parts so as to fasten them together; and screwing a screw into the element through at least one other part so as to fasten all the parts together and so as to place a head of the screw in a flush position relative to the other part.