Abstract: A device for detecting an impact on a composite material structure. This detection device comprises at least two acoustic modules intended to be secured to the composite material structure and a processing unit able to communicate remotely with each of the acoustic modules. Each acoustic module is electrically autonomous and comprises its own means for recording the sound waves sensed by its acoustic sensor. An aircraft structure is also provided comprising a composite material structural element equipped with the impact detection device. A method is also provided for detecting an impact on a composite material aircraft structural element equipped with an impact detection device.

Abstract: A process for the production of a stiffened panel made of composite material, includes the stages of depositing the fibers that constitute the panel on a rigid device (50), depositing the at least one stiffener (14), covering the unit with a sealed wall connected to the rigid device (50) on the periphery of the panel, and then polymerizing, and providing—for each stiffener (14)—a rigid counter-mold in contact with the convex surface of the stiffener (14), using—for each stiffener (14)—a core (66) in the form of a flexible and sealed bladder, and subjecting the interior of the bladder to pressure during polymerization for compacting the stiffener (14) and the panel.

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 detecting an impact on a composite material structure. This detection device comprises at least two acoustic modules intended to be secured to the composite material structure and a processing unit able to communicate remotely with each of the acoustic modules. Each acoustic module is electrically autonomous and comprises its own means for recording the sound waves sensed by its acoustic sensor. An aircraft structure is also provided comprising a composite material structural element equipped with the impact detection device. A method is also provided for detecting an impact on a composite material aircraft structural element equipped with an impact detection device.

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: 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: 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 process for the production of a stiffened panel made of composite material, includes the stages of depositing the fibers that constitute the panel on a rigid device (50), depositing the at least one stiffener (14), covering the unit with a sealed wall connected to the rigid device (50) on the periphery of the panel, and then polymerizing, and providing—for each stiffener (14)—a rigid counter-mold in contact with the convex surface of the stiffener (14), using—for each stiffener (14)—a core (66) in the form of a flexible and sealed bladder, and subjecting the interior of the bladder to pressure during polymerization for compacting the stiffener (14) and the panel.