A composite storage tank may include a wall structure including at least three regions including an inner region, an outer region, and at least one permeation barrier. Another region may be optionally incorporated for venting potential permeation of fluids. The at least one permeation barrier and/or the venting layer may be strategically positioned between the inner region and the outer region to reduce or at least partially prevent fluid permeation of the inner region or the outer region. A vehicle may include such a composite storage tank. Methods of forming a composite fluid storage tank may include forming an inner composite region, applying a permeation barrier to an outer surface of the inner composite region, forming an outer composite region, and curing the inner composite region and the outer composite region with the permeation barrier to form the composite fluid storage tank.

A pressure recipient or vessel (1) has a polymeric impermeable liner (2) and a reinforcing layer (4) of a composite material externally formed around the impermeable liner (2), as well as at least one boss (5) coupled to the impermeable liner (2) and to the reinforcing layer (4) to provide an opening (6) of the pressure vessel (1). The impermeable liner (2) is joined to the boss (5) by a co-molded polymer-metal annular connection zone (7).

A hydrogen storage tank for a hydrogen fueled aircraft. The tank has a wall made of layers of aerogel sections around a hard shell layer, sealed within a flexible outer layer, and having the air removed to form a vacuum. The periphery of each layer section abuts other sections of that layer, but only overlies the periphery of the sections of other layers at individual points. The wall is characterized by a thermal conductivity that is lower near its gravitational top than its gravitational bottom. The tank has two exit passageways, one being direct, and the other passing through a vapor shield that extends through the wall between two layers of aerogel. A control system controls the relative flow through the two passages to regulate the boil-off rate of the tank.

The present invention is directed to a reinforcement method for a cylindrical high-pressure tank reinforced by FRP prepreg bandage, totally. For that purpose, this invention developed the manufacturing process for the internal metallic tank assembly where its diameter is comparatively large. It is effective for lightening weight of a high-pressure tank.

Disclosed herein is a structure that comprises a tank including an outer cylindrical surface and a domed end. The structure also comprises a tank skirt positioned circumferentially around the tank. A wall of the tank and a wall of the tank skirt form two sides of a y-joint between the tank and the tank skirt. The y-joint includes a wedge structure positioned between the tank and the tank skirt. Additionally, a thickness of at least one of the wall of the tank or the wall of the tank skirt forming the y-joint tapers such that the thickness of the at least one of the wall of the tank or the wall of the tank skirt that tapers has a greater thickness at the y-joint than away from the y-joint.

The present invention provides a lightweight high pressure vessels that are made from a liner or a liner housing that is overwrapped with a composite material. Unlike conventional high pressure vessels, the lightweight high pressure vessel of the invention includes a liner that comprises a plurality of liner sections without using welding or crimping. In particular, the lightweight high pressure vessels of the invention include a plurality of elements that are combined to form a liner housing and a composite overwrap that provides structural and mechanical strength to maintain integrity of the high pressure vessel. In one particular embodiment, the high pressure vessel of the invention is a diaphragm accumulator.

A hydrogen storage tank for a hydrogen fueled aircraft. The tank has a wall made of layers of aerogel sections around a hard shell layer, sealed within a flexible outer layer, and having the air removed to form a vacuum. The periphery of each layer section abuts other sections of that layer, but only overlies the periphery of the sections of other layers at individual points. The wall is characterized by a thermal conductivity that is lower near its gravitational top than its gravitational bottom. The tank has two exit passageways, one being direct, and the other passing through a vapor shield that extends through the wall between two layers of aerogel. A control system controls the relative flow through the two passages to regulate the boil-off rate of the tank.

A container that provides for control of fluid flow in the event of a failure of the container is disclosed. In accordance with embodiments of the present invention, a container is presented that includes a container wall; and one or more flow impeding structures coupled to the container wall, wherein at least one of the one or more flow impeding structures is a multi-sheet layer that deforms to impede flow in a failure of the container wall. In some embodiments, the multi-sheet layer includes cavities formed between individual sheets.

A high-pressure tank includes: a cylindrical hollow container; an outer shell that is formed of a fiber-reinforced plastic band which is wound on an outer circumference of the hollow container to cover the outer circumference; and a cap that is attached to an inner side of at least one of one axial end and the other axial end of the outer shell. The hollow container is formed of a material which has airtightness and which is able to expand and contract in an axial direction and a radial direction inside the outer shell, and a frictional portion that is used to set a frictional resistance to an inner circumferential surface of the outer shell to be greater than that in the other area is provided in an axial intermediate portion on an outer circumferential surface of the hollow container.

A liner includes dome sections having outer surfaces along an uniform stress surface at both ends in an axial direction, and nozzles are mounted on the dome section by introducing nozzle flanges into pedestal sections of apexes of the dome sections. Then, ring-shaped caps having the same linear expansion coefficient as the liner and inner surfaces in a curved surface shape of outer surfaces of the dome sections and the nozzle flanges are mounted on boundary portions between the nozzle flanges and the pedestal sections. In forming a fiber layer after that, a helical winding layer is formed first by winding a fiber bundle disposed at the dome sections to cover the dome sections while including the nozzle flanges.