The invention relates to a method of manufacturing a pressure vessel and to a corresponding pressure vessel. The invention proposes a manufacturing method for a pressure vessel where first a pressure vessel blank having at least one liner type 4 and a cylindrical pipe operatively connected to it is manufactured and subsequently, for instance, a fibre composite material is wrapped onto the pressure vessel blank.

A pressure vessel includes a vessel main body, a first protective member, and a second protective member. The vessel main body is configured to contain gas inside. The second protective member is configured to exhibit performance that is different from that of the first protective member. One of the first protective member and the second protective member has recesses that the other one of the first protective member and the second protective member does not have at an end on a peak of a domical panel side provided with the one of the first protective member and the second protective member.

An integrated fill system is provided for a vehicle. The integrated fill system can include a container configured to house a compressed gas having a first end and a second end. A first neck mount is configured to receive the first end of the container and configured to restrict movement, and a second neck mount is configured to receive the second end of the container and configured to enable movement. A housing is configured to encase the container and the first and second neck mounts. A fill line has a first end coupled to the first end of the container, and a draw line has a first end coupled to the second end of the container. A filter is arranged proximate to the fill line to prevent contaminants from entering the container.

The invention relates to a tank device (1) for storing a gaseous medium, in particular hydrogen, comprising at least one tank reservoir (3), wherein said at least one tank reservoir (3) comprises a tank housing (30) having a tank neck (2). Furthermore, a tank pressure bottom (8) is arranged in the tank neck (2), which tank pressure bottom (8) separates a tank neck space (7) and a tank interior (6) from one another, and wherein said tank neck (2) has an outer thread (10) as an abutment on an outer side (20).

The invention relates to a tank device (1) for storing a gaseous medium, in particular hydrogen, comprising at least one tank container (2), wherein said at least one tank container (2) has a tank housing (20) with a tank neck (3). In addition, a connection screw element (5) is arranged in the tank neck (3), wherein said connection screw element (5) is in contact with a conical sealing seat (10) formed on an inner face (8) of the tank housing (20), thereby sealing a tank neck interior (30) of the tank neck (3), and the connection screw element (5) can be pretensioned by means of a union nut element (6) attached to an outer face (9) of the tank housing (20).

A gas supply marine vessel and a refueling facility are described. The gas supply marine vessel includes a hull with an upper deck having an elongated cargo cavity formed therein. Gas interface modules are disposed in the cavity and extend between hull sides, each module having a plurality of fuel vessel docking stations. A plurality of stacked fuel container assemblies are fluidically coupled to the docking stations. A gantry, is movable along the length of the cavity, straddles the cargo cavity between hull sides. An articulating crane is mounted on the gantry and it utilized to move fuel container assemblies to a fuel container depression formed in the deck of a floating refueling facility. The floating refueling facility includes a concave side to facilitate mooring adjacent a shoreline, the concave side forming angled extensions at corners of the deck with a linkspan extending from each of the angled extensions.

An aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system. The aircraft further comprises a fuselage having a cargo bay (502) including one or more (510A-G) of the plurality of hydrogen storage tanks, the longitudinal axes (511A-G) of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis (501) of the fuselage and lying in one or more planes (595, 597) extending across the width dimension of the cargo bay. The hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 4.2≤R≤25.7, allowing the volume of space with the cargo bay occupied by stored hydrogen to be maximised or approximately maximised.

A tank for pressurized gas, such as hydrogen, comprises a structure, a base, a sealing jacket and a ring. The structure has a substantially cylindrical shape along an axis and includes at least one axial opening along the axis. The base is able to be positioned in said opening and comprises, on the inner side, a housing of revolution about the axis and a first fastener, and is pierced with at least one through pipe that is axial along the axis. The sealing jacket is flexible and tight, and is to cover the inner wall of the structure and comprises a neck able to be received in the housing. The ring is substantially of revolution about the axis, and comprises a second fastener able to cooperate with the first fastener in order to assemble the ring with the base, on the inner side, by bringing the ring closer to the base along the axis, so as to progressively press the neck between the ring and the base. The ring comes closer to the base following a movement parallel to the axis from the inside of the tank toward the outside. and A face of the housing opposite the neck and a face of the ring opposite the neck have a small taper.

A fuel distribution station includes a first fuel tank for releasably holding a first fuel, and a second fuel tank for releasably holding a second fuel. A connection member extends between the first fuel tank and the second fuel tank, and provides a rigid connection between the first fuel tank and the second fuel tank. A support structure supports the first fuel tank and the second fuel tank in an elevated position a predetermined distance above ground, sufficient to allow for passage of land vehicles beneath the support structure during a fueling operation. A control system is utilized for selectively permitting and monitoring a discharge of fuel from the first fuel tank and the second fuel tank to the land vehicles during the fueling operation.

A system for storing fuel includes a support structure supporting at least one fuel tank a predetermined distance above ground. The fuel tank includes an inner tank configured to contain a gaseous fuel, an intermediate tank encompassing the inner tank and defining a first annular space therebetween, and an outer tank encompassing the intermediate tank an defining a second annular space therebetween. The first annular space is filled with a shock-absorbing resin for absorbing structural stresses, while the second annular space is filled with an insulating material providing for fire and ballistic resistance. The intermediate tank is connected to the support structure and to at least one adjacent fuel tank, and prevents the transfer of load to the inner tank.