Abstract: A bipolar plate for use in a fuel cell device, the bipolar plate including an integrated ply, the ply including one or more electrically conductive fibers and being configured and electrically connectable to a power supply such that the one or more fibers are heated when power is supplied to the ply.

Abstract: A sound wave absorbing laminate composite material structure for an aircraft including stacked plies of a hybrid composite material, wherein each of the hybrid composite material plies includes first polymer material tows parallel to a warp direction, second polymer material tows parallel to a weft direction, and sound absorbent material tows parallel to the warp direction, wherein the first and second polymer material tows carbon or glass fiber reinforcing polymer.

Abstract: A bipolar plate for a proton exchange membrane fuel cell includes a laminate of carbon fiber reinforced plastic (CFRP) with a first outer ply. The CFRP includes a resin and carbon fibers. The first outer ply is arranged at a first lateral surface of the laminate, wherein the laminate includes a first plurality of carbon nanotubes (CNTs). The first outer ply includes a first groove, wherein the first groove is configured to define a first gas diffusion channel. At least some of the first plurality of CNTs extend through the first outer ply in a direction transversely to the first lateral surface of the laminate.

Abstract: A panel (1000) for a cabin of an aircraft, the panel (1000) including a laminate (150) with a first layer formed of lithiated carbon fibers (100), a second layer form of carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and a pressure sensor (50a, 50b) on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150) based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

Abstract: A multifunctional diffusion barrier comprising at least one organic polymer and a 2D graphene or 2D graphene derivative material and a method for preparing the multifunctional barrier. The multifunctional diffusion barrier can be used as a liquid and/or gas barrier, or as structural material, or as sealing material, or as a self-cleaning material or as protective material against UV radiation in aeronautical, automotive, marine or building field. The multifunctional diffusion barrier is suitable in producing parts of aircraft such as a fuel tank, a fuel tank conduit and a gasket.

Abstract: Methods for recycling plastic Nylon 6,6 from vacuum bags to obtain filaments or powder for 3D printing processes. The method to obtain filaments includes a step of providing used Nylon 6,6 vacuum bags, a quality control step to check the status of the used vacuum bags, a step to form smaller parts, such as smaller pieces or pellets, from the used vacuum bags, quality control step to check the status of the smaller pieces or the pellets, an extrusion step wherein the smaller pieces or the pellets are introduced into an extruder, where they are melted, and the molten mixture is cooled and expelled through the die of the extruder to produce the recycled filaments, and a winding step wherein the recycled filaments that go out of the extruder are rolled up in coils.

Abstract: A sound wave absorbing laminate composite material structure for an aircraft including stacked plies of a hybrid composite material, wherein each of the hybrid composite material plies includes first polymer material tows parallel to a warp direction, second polymer material tows parallel to a weft direction, and sound absorbent material tows parallel to the warp direction, wherein the first and second polymer material tows carbon or glass fiber reinforcing polymer.

Abstract: A resistive heated aircraft component, comprising a fiber reinforced polymer surface and further comprising a graphene paper having first and second opposite faces, a pair of electrodes connected to the graphene paper, the graphene paper and the pair of electrodes being configured to conduct an electrical current such that the graphene paper produces heat, the second face of the graphene paper being located towards the fiber reinforced polymer surface of the aircraft, and a protective layer located on the first face of the graphene paper.

Abstract: A panel (1000) for a cabin of an aircraft, the panel (1000) including a laminate (150) with a first layer formed of lithiated carbon fibers (100), a second layer form of carbon fibers with a cathode lithium coating (200), and an electrolyte-containing separator (300) interposed between the first and the second layers and a pressure sensor (50a, 50b) on an outer surface of the laminate (150), and a switch (40) to regulate a voltage to the laminate (150) based on an output of the pressure sensor (50a, 50b) so that the panel (1000) expands.

Abstract: A structural composite component, in particular for an aircraft or spacecraft, includes: a lightning strike protection layer; and a composite battery including a cathode layer and a separation layer, wherein the lightning strike protection layer is formed integrated with the cathode layer, and wherein the separation layer is configured for providing acoustic damping, and/or fire barrier, and/or impact resistance to the structural composite component. A method for configuring such a structural composite component; and an aircraft or spacecraft including such a structural composite component are also described.

Abstract: A fireproof and thermal insulator product, which comprises a material combination of an Earth Silicate material, and alumina, such that the alumina is bonded onto the Earth Silicate material or is diffused inside the Earth Silicate material.

Abstract: A multifunctional diffusion barrier comprising at least one organic polymer and a 2D graphene or 2D graphene derivative material and a method for preparing the multifunctional barrier. The multifunctional diffusion barrier can be used as a liquid and/or gas barrier, or as structural material, or as sealing material, or as a self-cleaning material or as protective material against UV radiation in aeronautical, automotive, marine or building field. The multifunctional diffusion barrier is suitable in producing parts of aircraft such as a fuel tank, a fuel tank conduit and a gasket.

Abstract: A method for printed cable installation in a harness system of an aircraft. The method includes: printing at least a first conductive trace comprising conductive particles to a surface of an aircraft with a printing technology; printing at least second conductive trace comprising conductive particles to the surface of an aircraft with the printing technology; sintering the first and the second conductive traces by a laser, and interposing an insulating film between the first and the second conductive traces. For a trace length less than 5 meters, the first and second conductive traces provide the electromagnetic compatibility of a twisted pair of wires when printed with a guard trace.

Abstract: A structural composite component, in particular for an aircraft or spacecraft, includes: a lightning strike protection layer; and a composite battery including a cathode layer and a separation layer, wherein the lightning strike protection layer is formed integrated with the cathode layer, and wherein the separation layer is configured for providing acoustic damping, and/or fire barrier, and/or impact resistance to the structural composite component. A method for configuring such a structural composite component; and an aircraft or spacecraft including such a structural composite component are also described.

Abstract: Provided is a structure of composite material, comprising a continuous first layer of composite material, a second layer of viscoelastic material, and a continuous impact-protection third layer. The first layer is formed by structural components in the form of a matrix and fibers. The second layer of viscoelastic material is added on top of the first layer and said second layer can be continuous or non-continuous. If a non-continuous second layer is used, elongate, circular or square cavities are arranged inside the layer. Optionally, reinforcements comprising carbon nanofibers or nanotubes are provided in either of the first and second layers. The third layer of impact-protection material is added in a continuous manner on top of the second layer, the third layer forming the outermost layer of the composite material. In addition, this third layer is electrically conductive. The composite material has noise attenuation, impact resistance and electric conductivity properties.

Abstract: Provided is a structure of composite material, comprising a continuous first layer of composite material, a second layer of viscoelastic material, and a continuous impact-protection third layer. The first layer is formed by structural components in the form of a matrix and fibers. The second layer of viscoelastic material is added on top of the first layer and said second layer can be continuous or non-continuous. If a non-continuous second layer is used, elongate, circular or square cavities are arranged inside the layer. Optionally, reinforcements comprising carbon nanofibers or nanotubes are provided in either of the first and second layers. The third layer of impact-protection material is added in a continuous manner on top of the second layer, the third layer forming the outermost layer of the composite material. In addition, this third layer is electrically conductive.

Abstract: Protective shield against ice impacts on aircraft, wherein the shield comprises plies of composite material (1) having microcapsules (2), each microcapsule containing a healing agent (5). When a crack (4) produced on the shield reaches at least a microcapsule (2), the healing agent is spilled in the delaminated area. Some catalyst particles (3) can be included in the material and in that case, the healing agent (5) is polymerized reacting with the catalyst particles (3). If no catalyst particles (3) are included in the material, the healing agent (5) may also actuate when manually heated. Such kinds of materials allow recovering at least partially the impact strength of the shields after impact, which is particularly important in case of ice impacts that can be repetitive during operations in icing conditions.