A gas storage structure includes: a container and a continuous coiled pipe supported by the container, the continuous coiled pipe including a major portion formed of thin walled pipe and a thick walled pipe defining an end of the continuous coiled pipe, the thick walled pipe having a wall thickness thicker than the thin walled pipe, the thick walled pipe being welded at a welded joint to the major portion to place an inner diameter of the thick walled pipe into communication with an inner diameter of the major portion and the thick walled pipe being connected to the container, while the major portion is free of any rigid, such as welded, connections to the container.

Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) connected to the primary volume (V1) via a valve (20) configured to selectively allow a passage of fluid from the primary volume (V1) to the secondary volume (V2), or to isolate the secondary volume (V2) from the primary volume (V1), the primary volume (V1) having a primary orifice (11) adapted to be connected to a first pressurization source (41), the secondary volume (V2) having a supply orifice (4) adapted to be connected to a supply line of a spacecraft engine (30), and a secondary orifice (12) adapted to be connected to a second pressurization source (42).

A high-pressure hydrogen tank includes a metal circular cylinder configured to store high-pressure hydrogen therein, a cap part configured to cover each of opposite end portions of the metal circular cylinder, an outer cylinder surrounding an outer periphery of a circular-cylindrical portion of the metal circular cylinder, and a fastening part configured to fix the cap part to the outer cylinder.

A high-pressure tank comprises a liner, a strengthening layer including a first helical layer and a first hoop layer each including a carbon fiber, and a protective layer including a second helical layer and a second hoop layer each including a glass fiber, in this order. The high-pressure tank is provided with a stress-generating portion, a reinforcement layer includes a first area α overlapping the stress-generating portion in a stacking direction and a second area β that is an area except for the first area, and a one-round portion including a final crossing portion at an end of winding of the glass fiber constituting the second hoop layer overlaps the second area in the stacking direction.

A composite pressure vessel that includes a monolayer liner and a reinforcing structure arranged on top of the liner. The liner is made by injection moulding and includes at least two shells weldable together. Each shell is made of a polymer composition including at least 45% by weight of an aromatic polyamide relative to the total weight of the polymer composition, and at least 10% by weight of an aliphatic polyamide relative to the total weight of the polymer composition.

The present disclosure relates to a vacuum heat-insulation device for a large low-temperature tank, the vacuum heat-insulation device having excellent heat insulation properties and vacuum stability by using a low-temperature heat-insulating material maintained in a vacuum at all times so as to store an ultra-low-temperature liquefied gas such as liquid nitrogen (LN.sub.2) or liquid hydrogen (LH.sub.2), and to a vacuum heat-insulation device for a low-temperature tank, the vacuum heat-insulation device having a flexible structure in which a vacuum jacket is partially contractible according to contraction of a low-temperature tank or a low-temperature heat-insulating layer.

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 double-walled tank including at least one link system linking the outer and inner chambers of the tank and including a central part linked to the inner chamber and at least three blades distributed around the central part, each blade extending between a first end linked to the central part and a second end which has a head linked to the outer chamber, each blade being sufficiently flexible to be deformed elastically between its first and second ends in a direction of displacement.

Disclosed is a pressure vessel including an upper liner portion including a top insertion-injection molded and coupled to a peripheral part of a boss portion in which a through hole extends in a vertical direction, extending downward cylindrically from the top to form a first accommodation space accommodating a fluid and having an open lower center, and including a first shape-matching portion in which a first overlapped-coupled surface is formed on a bottom end edge to be perpendicular to a laser emission direction and extends in a vertical direction along a circumferential direction and a lower liner portion having a top end edge coupled to the bottom end edge of the upper liner portion.

The invention discloses a bimetallic cryogenic membrane storage compartment for liquefied natural gas (LNG) storage. The invention is based on the design of bimetallic membrane panels and two insulating panels to achieve two completely independent insulation spaces, fully meeting the relevant requirements of the amendments to the International Code for the Construction and Equipment of Ships Carrying Liquefied Natural Gas in Bulk (“IGC CODE”) adopted on May 22, 2014. The invention improves the safety of the cryogenic membrane storage compartment, reduces the limitation of free liquid level loading of liquid cargo in the cargo compartment, reduces the application and time consuming of low-temperature resistant glue in the construction process, and adopts the more mature and safe design method of welding bimetallic membrane panels and the environmental protection method of prefabricated foam insulation panels, thus reducing the construction workload, shortening the construction cycle and improving the safety of the equipment.