Abstract: A conductive device to form electrical connections on the surface of a structure made of composite material. The device includes a thin interface layer having a face via which the device is fixed to the surface of the structure made of composite material. A conductive metal element is placed on the face of the interface layer opposite the face making contact with the surface of the structure. The conductive element is configured to be able to undergo tensile and compressive stresses without damage. A protective layer is configured to protect the conductive element from attack from the environment surrounding the structure. These various elements are arranged relative to one another such that the length of the conductive element can vary as a function of temperature variations independently of the amplitude of the variations undergone by the structure on which the device is mounted.

Abstract: A device to absorb kinetic energy caused by an exceptional load includes an outer casing configured to maintain integrity after the exceptional load. A core of the device is made of a compactable material at least partially filling the outer casing. The core material is compacted under an exceptional load and absorbs some of the kinetic energy caused by the load. At least one stiffness element is incorporated into the core. A distribution element includes each stiffness element. An aircraft, a vehicle, an item of equipment and an installation includes such a device.

Abstract: A conductive device to form electrical connections on the surface of a structure made of composite material. The device includes a thin interface layer having a face via which the device is fixed to the surface of the structure made of composite material. A conductive metal element is placed on the face of the interface layer opposite the face making contact with the surface of the structure. The conductive element is configured to be able to undergo tensile and compressive stresses without damage. A protective layer is configured to protect the conductive element from attack from the environment surrounding the structure. These various elements are arranged relative to one another such that the length of the conductive element can vary as a function of temperature variations independently of the amplitude of the variations undergone by the structure on which the device is mounted.

Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, and a foam core contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements include at least one dry composite fiber preform integrated into the foam core to dissipate, in combination with the foam core, the kinetic energy generated by the impact. A method for integrating the device for absorbing kinetic energy.

Abstract: A multilayer sealed skin, in particular for an inflatable structure and that includes a first polymer film, a reinforcing fabric disposed on the first polymer film and a second polymer film disposed on the reinforcing fabric and adhered by means of an adhesive to the first polymer film through cavities in the reinforcing fabric. The skin can be applied to the production of an inflatable structural element such as an inflatable beam for which the skin forms an outer wall of the structural element and for which the first film of the skin forms an inner face of the outer wall of the structural element, and the second film forms an outer face of the wall.

Abstract: A device to absorb kinetic energy caused by an exceptional load includes an outer casing configured to maintain integrity after the exceptional load. A core of the device is made of a compactable material at least partially filling the outer casing. The core material is compacted under an exceptional load and absorbs some of the kinetic energy caused by the load. At least one stiffness element is incorporated into the core. A distribution element includes each stiffness element. An aircraft, a vehicle, an item of equipment and an installation includes such a device.

Abstract: A method of manufacturing a stiffened panel having a skin and at least one substantially elongate stiffener having a longitudinal groove forming a cavity. At least one storage device for storing and releasing electrical energy. The longitudinal groove is filled with at least one storage device for storing and releasing electrical energy. The storage device is covered with a skin which forms the cavity together with the longitudinal groove of the stiffener. A stiffened ring can be derived from the method.

Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, a foam core, contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core is configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements are integrated at least partially into the foam core to dissipate, combined with the form core, the kinetic energy generated by the impact. The reinforcing elements includes discontinuous threads inserted into the foam core by stitching, and each discontinuous thread includes an L- or T-shaped head, folded down outside the outer enclosure.

Abstract: An aircraft fuselage structure, includes a circumferential reinforcing frame (2) and a plurality of stringers (3) substantially perpendicular to the frame. The frame includes a mechanically weakened area able to cause its localized buckling under the effect of a compressive force exerted circumferentially thereon. The structure includes an energy absorbing device (5) having two effector members (52) secured to the frame respectively on either side of the weakened area, and a central core (51) maintained between the effector members such that a reduction in the distance between the effector members produces a deformation of the central core, which is able to absorb energy under the effect of the deformation.

Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, and a foam core contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements include at least one dry composite fiber preform integrated into the foam core to dissipate, in combination with the foam core, the kinetic energy generated by the impact. A method for integrating the device for absorbing kinetic energy.

Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, a foam core, contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core is configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements are integrated at least partially into the foam core to dissipate, combined with the form core, the kinetic energy generated by the impact. The reinforcing elements includes discontinuous threads inserted into the foam core by stitching, and each discontinuous thread includes an L- or T-shaped head, folded down outside the outer enclosure.

Abstract: A method of manufacturing a stiffened panel having a skin and at least one substantially elongate stiffener having a longitudinal groove forming a cavity. At least one storage device for storing and releasing electrical energy. The longitudinal groove is filled with at least one storage device for storing and releasing electrical energy. The storage device is covered with a skin which forms the cavity together with the longitudinal groove of the stiffener. A stiffened ring can be derived from the method.

Abstract: An aircraft fuselage structure, includes a circumferential reinforcing frame (2) and a plurality of stringers (3) substantially perpendicular to the frame. The frame includes a mechanically weakened area able to cause its localized buckling under the effect of a compressive force exerted circumferentially thereon. The structure includes an energy absorbing device (5) having two effector members (52) secured to the frame respectively on either side of the weakened area, and a central core (51) maintained between the effector members such that a reduction in the distance between the effector members produces a deformation of the central core, which is able to absorb energy under the effect of the deformation.