[Problem] When configuring a device for storing and supplying fluid, each components such as vessels, valves/pipes and the like, are placed independently outside a vessel that stores the fluid, and even if these components are small, the volume of the area between the components cannot be effectively used because each of them occupies the surrounding area, and when the total size of the device is limited, it is difficult to ensure a sufficient volume of the vessel that stores the fluid. The present invention provides a design for a configuration of a mechanism consisting of components such as valves/pipes and the like, that functions for storing and exhausting the fluid inside the storage vessel to innovatively improve the volume usage efficiency of the device.

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 tank suitable for storing a product at a cryogenic temperature, including a fluid tight interior barrier, a fluid tight exterior barrier, surrounding the first interior barrier, an intermediary volume interposed between the interior and exterior barriers and at least one insulating layer positioned in the intermediary volume and including at least one thermal insulation mat, with very low thermal conductivity. The intermediary volume contains microspheres outside of the thermal insulation mats and has an enhanced level of vacuum. This solution makes it possible to maintain satisfactory performance in terms of thermal insulation even in the event of a loss of vacuum in the intermediary volume.

Provided is a flight vehicle which makes it possible to more reliably retain the sealability of a sealing member of a valve provided on a hydrogen tank even in continuous supply of hydrogen or a low-temperature environment. The flight vehicle having a fuel cell, and a hydrogen tank in which hydrogen for generation of electricity by the fuel cell is stored includes: a valve including a sealing member, the valve being disposed on the hydrogen tank, via the valve hydrogen being taken out from a body of the tank; and a warming unit in which fluid conducts part of waste heat from any portion of the flight vehicle to the sealing member.

The invention relates to a hybrid pressure vessel with a fiber-composite component and a metallic component. Furthermore, the invention relates to a manufacturing method for such a hybrid pressure vessel. The hybrid pressure vessel according to the invention has a liner having an inner face and an outer face, with an outer diameter DL, and a metallic boss with an outer diameter DB, the metallic boss being adapted to accommodate a valve, the hybrid pressure vessel having a storage volume on the inside, the liner being pipe-shaped and the outer diameter DB of the boss being at least as large as the outer diameter DL of the liner.

A multiple storage tank system includes: storage tanks in which cryogenic fluid is stored; discharge lines connected to the storage tanks to discharge the stored cryogenic fluid or introduce cryogenic fluid; a supply line connected to the discharge lines and a supply target to supply the discharged cryogenic fluid to the supply target; a build-up line branching off the supply line to control internal pressure of a first storage tank of the storage tanks; and a gas transfer line connected to the storage tanks to transfer gas inside the storage tanks, wherein when the internal pressure of the first storage tank is controlled while the cryogenic fluid passes through the build-up line, gas inside the first storage tank is transferred to at least one other storage tank through the gas transfer line so that internal pressure of the at least one other storage tank is controlled.

A cryogenic tank for storing cryogenic fluids is disclosed. The cryogenic tank is typically configured to be mounted on a vehicle for supplying cryogenic fuel to a propulsion system of the vehicle. The cryogenic tank comprises an inner vessel for containing cryogenic fluids and an outer vessel surrounding the inner vessel to define a vacuum insulating volume therebetween. The outer vessel is configured to transmit static and/or dynamic loads, while the inner vessel is partially or completely isolated from such loads.

A tank includes a liner including an inner shell; and a reinforcing layer covering an outer surface of the liner; wherein the reinforcing layer is formed by continuously winding resin-impregnated fiber bundles around the liner, the reinforcing layer includes a hoop layer placed in a side of the liner, and a helical layer, gaps are formed between adjacent bundles of the resin-impregnated fiber bundles wound in the hoop layer, there is at least one site where the resin-impregnated fiber bundles are wound without forming a gap between adjacent bundles in the helical layer, and resin in the resin-impregnated fiber bundles has a resin toughness value of not less than 1.0 MPa.Math.m.sup.0.5.

A high altitude atmospheric energy storing apparatus having a new structure, which is conceived to store the energy of low-temperature air located at high altitude in the sky and utilize it as needed, is provided. The high altitude atmospheric energy storing apparatus includes an air tank adapted to store air, an air supply pipe provided such that it extends in a vertical direction and its lower end is connected to the air tank, and a compression device provided in the sky, connected to the upper end of the air supply pipe, and configured to compress air using the wind and supply the compressed air to the air tank through the air supply pipe, thereby enabling air to be compressed by the wind blowing at high altitude and to be then stored in the air tank.

An Automatic Service Station Facility (ASSF) for replenishing various motivational energy sources onboard different types of AUV, Drones, and Remotely Controlled (RC) or robotic vehicles is disclosed herein. In one embodiment, the automatic service station facility includes a rack, replaceable fuel tanks, a service module, and an electronic computer control system. The replaceable fuel tanks are stocked on the rack and substantially filled with various fluids which are utile as motivational energy sources within fuel-operated vehicles. The service module is mounted on the rack, and the electronic computer control system is connected in electrical communication with the service module. In this configuration, the service module is controllably operable to receive a depleted replaceable fuel tank from a fuel-operated vehicle and also selectively deliver one of the filled replaceable fuel tanks onboard the vehicle. In another embodiment, the service station facility may also stock replaceable batteries for selective delivery onboard battery-operated vehicles. In another embodiment, the ASSF is self-propelled, remotely controlled, and solar powered, being able to move long distances to remote locations which may be hazardous to humans, such as disaster zones or battle fields, where the ASSF can service AUV, Drones, and Remotely Controlled (RC) or robotic vehicles needed for the particular applications. Alternatively, the solar powered ASSF can be made to move continuously and service vehicles continuously for long duration operations like herding cattle for example.