A non-destructive inspection system is presented. The non-destructive inspection system comprises a robotic end effector having an extendable actuator and a flange-mounted roller containing an ultrasonic sensor, the flange-mounted roller connected to the extendable actuator by a pivot connection, the extendable actuator configured to extend the flange-mounted roller until the flange-mounted roller contacts an inspection surface.

A process for producing a polymeric stiffened sheet-like component, for example a panel, for aircraft construction. Production includes integration of hollow stiffening profiles, for example closed omega stringers, onto a sheet-like component, for example an external skin, where the stringers and external skin are produced from thermoplastic composite material. The stringers are integrated onto the external skin by establishing contact between the stringers and the external skin and melting thermoplastic composite material with exposure to heat and pressure at the areas of contact between external skin and stringers. Melting of the other sections of the stringers is avoided with a pressurized cooling fluid with a temperature significantly below the melting point of thermoplastic composite material, the fluid flowing through the airtight enclosed space in the stringers. Use of closed airtight thermoplastic omega stringers allows integration of the stringers onto the external skin in absence of any flexible tube within the stringers.

A process for producing a polymeric stiffened sheet-like component, for example a panel, for aircraft construction. Production includes integration of hollow stiffening profiles, for example closed omega stringers, onto a sheet-like component, for example an external skin, where the stringers and external skin are produced from thermoplastic composite material. The stringers are integrated onto the external skin by establishing contact between the stringers and the external skin and melting thermoplastic composite material with exposure to heat and pressure at the areas of contact between external skin and stringers. Melting of the other sections of the stringers is avoided with a pressurized cooling fluid with a temperature significantly below the melting point of thermoplastic composite material, the fluid flowing through the airtight enclosed space in the stringers. Use of closed airtight thermoplastic omega stringers allows integration of the stringers onto the external skin in absence of any flexible tube within the stringers.

A composite panel assembly including a first panel with a first skin, a second skin, a core, and an assembly flange. A second panel includes a first skin, a second skin, a core, and an assembly flange. A fastening device is adapted to fasten the assembly flange of the first panel to the assembly flange of the second panel, wherein the core of one of the first panel or the second panel includes reinforcing pins and a high-density portion placed along the assembly flange.

A composite panel assembly including a first panel with a first skin, a second skin, a core, and an assembly flange. A second panel includes a first skin, a second skin, a core, and an assembly flange. A fastening device is adapted to fasten the assembly flange of the first panel to the assembly flange of the second panel, wherein the core of one of the first panel or the second panel includes reinforcing pins and a high-density portion placed along the assembly flange.

This composite material structure is provided with: a first composite material that is obtained by stacking a plurality of first composite material sheets, each of which is obtained by impregnating electroconductive first reinforcing fibers with a first resin; a second composite material which is obtained by impregnating electroconductive second reinforcing fibers with a second resin; an insulating bonding layer that is arranged between the first composite material and the second composite material, thereby bonding the first composite material and the second composite material to each other; and an electroconductive member that connects the plurality of first composite material sheets.

A resistive skin element for an acoustic panel intended for an aircraft includes a first ply, a second ply with openings and a wire mesh which is sandwiched between the two plies. First ply includes at least one layer made of C/PEAK and a film made of PEI. Second ply includes at least one layer made of PEI First ply is crossed by perforations. Second ply has openings configured so that second ply does not obstruct the perforations of first ply. The wire mesh allows perforations with large sizes to be made while keeping good acoustic properties.

A resistive skin element for an acoustic panel intended for an aircraft includes a first ply, a second ply with openings and a wire mesh which is sandwiched between the two plies. First ply includes at least one layer made of C/PEAK and a film made of PEI. Second ply includes at least one layer made of PEI First ply is crossed by perforations. Second ply has openings configured so that second ply does not obstruct the perforations of first ply. The wire mesh allows perforations with large sizes to be made while keeping good acoustic properties.

A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a décor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the décor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.

A wall covering panel for a nose of an aircraft. The panel comprises a rigid carrying framework preferably having an alveolar structure obtained by 3-D printing, a décor carried by the carrying framework and an acoustically and thermally insulating padding fixed to the carrying framework, and also attachments for fixing the carrying framework to the primary structure of the aircraft. Preferably, the panel also integrates systems, such as electrical route portions or ventilation route portions that traverse the panel from one side to the other or lead to an outlet equipment item also integrated in the panel. Only the carrying structure of the panel, which carries the décor, the insulating padding and any route portions and equipment items, is fixed to the primary structure of the aircraft. The number of attachments is low; the kitting-out and the finishing of the nose of the aircraft are greatly simplified.