Abstract: A double-wall tank comprising at least one piping connecting system and to a method for assembling a double-wall tank provided with at least one piping connecting system. An inner connecting part is coupled to an comprises an inner part hole. The inner part hole and an inner wall hole of the inner wall are coincident. An outer connecting part is coupled to an outer wall and comprises an outer part hole. The outer part hole and an outer wall hole of the outer wall are coincident. One or more pipes pass through the outer part hole, the outer wall hole, the inner part hole, the inner wall hole. The pipe is coupled, in a fluid-tight fit, to the inner part hole and the outer part hole.

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 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 hydrogen tank for aircraft, including an inner vessel configured to contain hydrogen, first and second outer jacket domes having a semi-spherical shape and first L-shaped ends, a first cylindrical outer jacket established on top of the first and second outer jacket domes, a second cylindrical outer jacket established in the bottom of the first and second outer jacket domes. The first and second cylindrical outer jackets include second L-shaped ends. The first and second L-shaped ends form L-shaped junctions to attach the first and second outer jacket domes to the first and second cylindrical outer jackets.

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 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: Fixing system for a modular leading edge (2) to the structure of an aircraft lift plane (1), in which the leading edge (2) has a covering (4) formed from a first lamina (5) and a second lamina (6) between which there is an interior airtight chamber, and the fixing system comprises a main attachment element (3) whose cross-section has a central element (13), a first arm (14) which is fixed to the first lamina (5) of the covering (4) of the leading edge (2), and a second arm (15) which is fixed to the second lamina (6) of the covering (4), and the central element (13) is in turn fixed to a covering (10) of the torsion box (8) of the structure of the lift plane (1).

Abstract: Fixing system for a modular leading edge (2) to the structure of an aircraft lift plane (1), in which the leading edge (2) has a covering (4) formed from a first lamina (5) and a second lamina (6) between which there is an interior airtight chamber, and the fixing system comprises a main attachment element (3) whose cross-section has a central element (13), a first arm (14) which is fixed to the first lamina (5) of the covering (4) of the leading edge (2), and a second arm (15) which is fixed to the second lamina (6) of the covering (4), and the central element (13) is in turn fixed to a covering (10) of the torsion box (8) of the structure of the lift plane (1).