A method for generating liquefied gas is provided. The method includes receiving air, refining the air to create refined air, performing liquefaction on refined air to form liquefied gas, and transferring at least one constituent liquefied gas of the liquefied gas to a storage tank in a lighter than air aircraft. The constituent liquefied gas(es) is configured to serve as an energy source for the lighter than air aircraft. The method may include distilling the liquefied gas to obtain liquid nitrogen and one or more other constituent gases. The liquid nitrogen may be configured to store at least 250 kilojoule per liter of energy. Additionally, the air may be refined to create refined air by compressing the air, separating water from the air, scrubbing carbon dioxide from the air, and/or filtering dust from the air. The method may be carbon-neutral or carbon-negative.

In one embodiment, systems and methods include using a pressure relief shipping adapter to reduce the internal pressure of a container. A pressure relief shipping adapter comprises a body comprising a first portion and a second portion. The first portion comprises a first bore and a set of protrusions. The second portion comprises a second bore, wherein the second bore comprises a radial gap, wherein the radial gap comprises a uniform arc length along the length of the radial gap. A first end and a second end of the radial gap comprise a greater arc length than the radial gap. A pressure relief shipping adapter further comprises a pressure relief valve disposed at a first end of the first bore and an interlocking component comprising a first tab and a second tab, wherein the interlocking component is at least partially contained within the second bore.

A pressure vessel includes: a barrel part disposed in a predefined square area and having a diameter corresponding to a length of one side of the square area; a first nozzle member disposed at one end of the barrel part; a second nozzle member disposed at an opposite end of the barrel part; and clamp rings disposed in the square area, positioned outside the barrel part, and configured to lock the first and second nozzle members to the barrel part, thereby improving spatial utilization and a degree of design freedom.

A storage tank for liquid hydrogen comprises first and second shells each constructed of laminate material, the second shell being disposed outwardly of the first shell with respect to the centre of the storage tank. The first and second shells are mechanically connected by a first plurality of pins each of which passes through at least some layers of the second shell and at least some layers of the first shell. The storage tank may be constructed using a simpler manufacturing process involving less tooling and fewer process steps than is the case for known tanks for storing liquid hydrogen. The storage tank has also has a lower mass and reduced thermal losses compared to tanks of the prior art. The plurality of pins allows for the shells to be thinner, and hence lighter, than similar shells in tanks of the prior art.

A fluid tank for integration into a structure of an unmanned aircraft includes a shell having a first axial wall, an oppositely arranged second axial wall, an upper side, a lower side, and an enclosed interior, at least one receiving chamber in the interior for storing fluid, and a collection chamber, which is arranged on the lower side and which is fluidically connected to the at least one receiving chamber. The collection chamber includes a bottom surface, through which there extends a drain, wherein a covering surface is arranged above the bottom surface and covers at least a portion of the collection chamber. At least one flow opening could be arranged on an upper side of the collection chamber, which flow opening allows gas bubbles to escape in the direction of the upper side of the fluid 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.

A container includes one or more hollow shell assemblies, each assembly having a first hollow shell including a first inner surface to cover a portion of a pressure vessel (PV) and a second hollow shell including a second inner surface attachable to the first hollow shell. The first and/or second hollow shells may include a fiber layer that may be at least partially impregnated with resin, and an energy dissipating material that is substantially concentric with the inner surfaces of the respective shells. The first and second hollow shells are attachable to one another to define a volume for at least partially enclosing the PV, and may be overwrapped via filament winding.

One or more indicators provide an indication of fueling status of a hydrogen powered vehicle. One or more sensors detect temperature and/or other characteristics of the fuel provided to the vehicle and provide an electrical signal to one or more of the indicators to permit an indication of fueling status. The indicators, which may be visual and/or audible, may be positioned on the fueling apparatus and on the vehicle in the vicinity of a fueling receptacle. The indicators may also be positioned elsewhere on the vehicle and may be separate from the vehicle such as on or around a fueling station and/or on separate computerized devices.

A hydrogen tank for aircraft, including an inner vessel configured to contain hydrogen, first and second outer jacket domes having a semi-spherical shape and first L-shaped ends, a first cylindrical outer jacket established on top of the first and second outer jacket domes, a second cylindrical outer jacket established in the bottom of the first and second outer jacket domes. The first and second cylindrical outer jackets include second L-shaped ends. The first and second L-shaped ends form L-shaped junctions to attach the first and second outer jacket domes to the first and second cylindrical outer jackets.

A tank, in particular for a liquid hydrogen reservoir, provided with at least one dome fixed by way of an outer welded joint and having a central portion provided with at least one free end including a first connecting element and at least one dome provided with an open end including a second connecting element, the dome and the central portion being able to be joined together, the first connecting element and the second connecting element being configured to form, when the central portion and the dome are joined together, a protruding tab extending toward the outside of the tank and able to be welded to a protruding end, such a protruding tab making it possible in particular to join together the tank, this being done entirely from the outside of said tank, and to easily mount and dismount the dome, in particular without accessibility issues.