A tank, in particular for a liquid hydrogen reservoir, provided with internal rails for putting an equipment module in place, includes a central portion provided with a wall, and at least one rail and preferably a plurality of rails, each of the rails being integrated in the wall of the central portion of the tank so as to be accessible from inside the tank, such rails allowing easier integration and fastening of a module comprising equipment inside the tank, so as to simplify the manufacture and assembly of the tank.

A storage system for storing a cryogenic medium, in particular, for storing hydrogen. The storage system includes storage container for receiving the cryogenic medium, at least one pipe projecting from outside the storage container into the storage container, and a shut-off valve in fluidic communication with the at least one pipe. The at least one pipe is closed at an end thereof facing away from the storage container and is open at another end thereof located in the storage container. The shut-off valve is moveable between an open operating state in which an inner space of the at least one pipe is in fluidic communication with an inner space of the storage container, and a closed operating state in which the inner space of the at least pipe is not in fluidic communication with the inner space of the storage container.

A cryogenic fluid pressure vessel for an aircraft, having: a first wall layer, which contains carbon fiber-reinforced plastic, having an inner contact surface for the contact with a pressurized cryogenic fluid to be accommodated inside the cryogenic fluid pressure vessel; a second wall layer, which is arranged on an outer surface of the first wall layer and has a thermal barrier; a closable inlet/outlet opening for cryogenic fluid, which extends through the first and the second wall layer; and a structural insert integrated in the first and the second wall layer, which has a fastening connecting piece located on the outside of the cryogenic fluid pressure vessel for mechanically coupling the cryogenic fluid pressure vessel with external structures; wherein the cryogenic fluid pressure vessel forms an essentially cylindrical main body. Furthermore, the present invention provides an aircraft having such a cryogenic fluid pressure vessel.

Aircraft fuel system including a fuel vessel containing a non-mixture fuel. A protective vessel is arranged about the fuel vessel such that the fuel vessel is contained within the protective vessel and a protective space is defined between an outer surface of a vessel wall of the fuel vessel and an inner surface of a vessel wall of the protective vessel. At least one mounting structure fixedly positions the fuel vessel within the protective vessel. A fuel consumption device configured to consume the non-mixture fuel. A fuel output fluidly connects an interior of the fuel vessel to the fuel consumption device, the fuel output being fluidly isolated from the protective space. A relief output fluidly connects the protective space to a relief flow path, the relief output and relief flow path configured to vent gas from the protective space and remove any non-mixture fuel from the protective space.

A valve assembly, comprising: a valve housing body extending along a longitudinal axis X between a first end and a second end and defining a cylindrical passage therethough from the first to the second end; a fluid inlet at the first end for receiving a pressurized fluid; and a fluid outlet provided in between the first and second end of the housing body; and a piston provided in said cylindrical passage, said piston being axially movable between a first position wherein said fluid outlet is blocked by said piston such that the piston blocks the flow of fluid from the inlet to the outlet, and a second position wherein said outlet is not blocked by said piston and a fluid flow path is formed from the inlet to the outlet.

A composite structure is disclosed forming part of a wall of a liquid hydrogen tank, and including at least one thermal protection device having one or more of hollow fibers, such as to create thermal protection, for example a thermal barrier or a heat exchanger, which makes it possible to protect the composite structure in case of a high temperature gradient between the two faces thereof, while benefiting from the advantages of a composite material in terms of mass.

A liquefied fuel cryogenic tank has an inner jacket delimiting a fluid storage volume and an outer jacket disposed around the inner jacket with a vacuum thermal insulation gap therebetween. A withdrawal circuit has an assembly of one or more valves and a withdrawal line that has a first heating heat exchanger located outside the inner jacket and a second heating heat exchanger located inside the inner jacket. Fluid flows through the withdrawal line via the first heat exchanger and then the second heat exchanger or via the first heat exchanger without entering the second heat exchanger.

A storage tank for a cryogenic fluid including an inner tank that is configured to store the fluid and that is seated in an outer envelope, the inner tank and the outer envelope having a shared longitudinal axis, such that a thermal insulation volume surrounds the inner tank, and wherein the outer envelope surrounds the volume about the inner tank. The tank has at least one damping element made of a deformable material positioned between one end of the inner tank and the outer envelope to wedge the inner tank against the outer envelope. This enables a reliable sliding mechanical link to be formed between at least one end of the inner tank and the outer envelope of the tank, thereby increasing resistance to wear and facilitating assembly of the tank.

A hydrogen tank, preferably a tank for storing liquid hydrogen at low pressure in cryogenic condition, includes at least one gaseous hydrogen capture system. The system is provided with absorbent fillers configured to capture the gaseous hydrogen, the absorbent fillers being linked to at least a part of a wall of the tank, and/or to a skin arranged on an outer face of the tank, and/or to an outer jacket intended to implement an auxiliary function. The system has a reduced weight and is able to retain and store gaseous hydrogen which could escape from the tank so as to prevent it from being given off into the environment of the tank. The captured gaseous hydrogen is able to be restored later by the system.

A multi-walled storage tanks use pressure differences between walls/shells to maximize fluid mass storage for tank size by reducing or minimizing the distance between the outer most layers of a multi-layer storage device, and keeping the middle one(s), particularly the innermost space, as large as possible, while having shell walls of substantially the same material and thickness, with no wall being thicker than the inner shell wall.