Abstract: A fireproof and thermal insulator product (1) including an Alkaline Earth Silicate (AES) material (2), and at least one of the following: a liquid barrier film (5), an FRP (Fiber Reinforcement Plastic) layer (4), cork (3), wherein the liquid barrier film (5) and the FRP layer (4) are staked onto the AES material (2), and wherein the cork (3) material is also staked onto the AES material (2) or embedded into said AES material (2) in where said cork (3) is configured as a plurality of strips performing a grid structure infilled with the AES material (2).

Abstract: A method for manufacturing a vessel configured for housing a fluid within, the method comprising: providing two Fiber Reinforced Polymer (FRP) structures shaped with complementary coupling interfaces configured to match with each other, such that an interior volume is defined when the FRP structures are coupled to each other; coupling the FRP structures to each other such that the interior volume is defined; and fastening the FRP structures after they have been coupled to each other.

Abstract: A method for manufacturing a vessel configured for housing a fluid within, the method including: providing at least two at least partially cured fiber reinforced polymer (FRP) structures with complementary shapes configured for matching with each other such that an interior volume is defined when the at least partially cured FRP structures are coupled to each other; coupling the at least partially cured FRP structures to each other such that the interior volume is defined; winding at least one layer of FRP material onto at least a portion of the at least partially cured FRP structures once coupled to each other; and applying a curing cycle to cure the resulting assembly.

Abstract: A method for manufacturing an aeronautical sandwich panel with a honeycomb core and results in a core sealed to prevent infused resin from entering into the honeycomb core open cells while improving its mechanical properties, especially for curved or highly curved panels. In further embodiments, the invention proposes the automation of this process.

Abstract: A method for manufacturing an aeronautical panel with improved impact and damping behaviors. The method is applicable not only to flat panels but also to curved or highly curved panels, whatever their size and the shape of their core. The manufactured sandwich panels comprise dry fiber mats made from fabric material and/or non-crimp fabric material. In a particular embodiment, the fabric material and/or the non-crimp fabric material comprise dry fibers which are recycled and/or reused fibers.

Abstract: A method for manufacturing an aeronautical sandwich panel with a honeycomb core and results in a core sealed to prevent infused resin from entering into the honeycomb core open cells while improving its mechanical properties, especially for curved or highly curved panels. In further embodiments, the invention proposes the automation of this process.

Abstract: A method for manufacturing a part layer-upon-layer using Additive Manufacturing technology suitable for structural applications. The method includes selectively depositing at least a first type filament and a second type filament, wherein the second type filament differs from the first type filament at least in the cross-sectional dimension.

Abstract: A fireproof and thermal insulator product which includes a honey-comb core infilled with Alkaline Earth Silicate material. The material of the honey-comb core can be metallic or polymeric. The product may further include a FRP layer, and/or a liquid barrier film, preferably being of thermoplastic material. An adhesive layer may be further deposited between the layer of honey-comb core infilled with AES and the layer of FRP.

Abstract: A fireproof and thermal insulator product (1) including an Alkaline Earth Silicate (AES) material (2), and at least one of the following: a liquid barrier film (5), an FRP (Fiber Reinforcement Plastic) layer (4), cork (3), wherein the liquid barrier film (5) and the FRP layer (4) are staked onto the AES material (2), and wherein the cork (3) material is also staked onto the AES material (2) or embedded into said AES material (2) in where said cork (3) is configured as a plurality of strips performing a grid structure infilled with the AES material (2).

Abstract: A three-dimensional printing system including: a printing bed (3) where a printed material is deposited to form an object (1), a bobbin (4) configured to hold a filament (2) of thermoplastic material reinforced with a continuous electrically conductive element, a printing head (5) fed by the bobbin (4) and configured to deposit, e.g., print, the filament on the printing bed (3) to form an object and first and second electrodes (7, 8) connected to a power supply (6), wherein the first electrode (7) is connected to the printing bed (3), and the second electrode (8) is connected to the filament, wherein an electric circuit is created through the continuous conductive element in the filament to heat the printed material.

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 joining method for thermoplastic elements that comprises the steps of providing two thermoplastic parts having two surfaces to be joined, locating a graphene layer between the two thermoplastic parts adjacent to the surfaces to be joined, and heating the graphene layer such that the graphene layer melts the thermoplastic resin of the adjacent surfaces of the two thermoplastic parts that are to be joined.

Abstract: The invention relates to a jig (9) for manufacturing composite material parts out-of-autoclave, comprising a base (11) the upper surface of which includes a stacking table (13) having a rotating movement and a shifting movement in the laminating direction, and a head (15) supported on a portal frame (17) through means allowing the shift perpendicular to the laminating direction on the mentioned table (13), the head (15) in turn comprising: automatic means (21) for placing tapes or roves of composite material in the form of prepreg; compacting means (23) for compacting the composite material and curing means (25) for polymerizing the composite material. The invention also relates to an out-of-autoclave process for manufacturing composite material structures.

Abstract: This invention relates to a tool (9) for manufacturing pieces of composite material outside an autoclave comprising a stacking table (11); a movable head (15) on said stacking table (11) provided with: automatic means for placing tapes (19) of composite material; compacting means for compacting the composite material and microwave emission means (25) to cure the composite material. The invention also relates to a process for manufacturing pieces of composite material outside an autoclave, comprising the following steps: a) Placing composite material in the form of tapes on a tool with the shape of the piece to be manufactured, compacting it and partially curing it after its placement until completing a layer of the piece; b) Repeating step a) until completing the stacking of the piece and c) Curing the last layer of the piece until the required degree of curing.