An aircraft with a multi-walled fuel tank and method of manufacturing is presented. The aircraft includes a blended wing body and a fuel tank attached to the blended wing body configured to store liquified gas fuel. The fuel tank includes an inner wall, outer wall, and interstitial volume in between that is filled with insulation. The interstitial volume includes a reflective film layer and a structural insulation layer.

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 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 heat exchanger comprises an inlet, an outlet, a heat exchanging channel, and an opening. The heat exchanging channel surrounds a cavity. The opening provides access to the cavity. The inlet is coupled to one end of the heat exchanging channel and the outlet is coupled to another end of the heat exchanging channel. The heat exchanging channel is isolated from the cavity. No access or passage is present between the heat exchanging channel and the cavity. During operation, heat exchanging fluid flows through the heat exchanging channel thereby cooling fluid within the cavity. The heat exchanging fluid never contacts the fluid within the cavity. In various embodiments, the heat exchanging channel has a single or stacked layer when viewed along a cross section. The heat exchanging channel has a spherical, cylindrical, or rectangular shape. In one embodiment, an insulative layer is disposed between layers of the heat exchanging channel.

A dry vapor cryogenic storage container includes an absorbent core made from a porous material that absorbs a liquid cryogen and releases the cryogen in vapor form as the absorbed liquid evaporates. Fluid channels are formed in the absorbent core to increase the available surface area through which the liquid cryogen can be absorbed. The core can absorb the cryogenic liquid much faster with inclusion of the fluid channels. The absorbent core can be made by cutting a cavity and drilling holes in a stack of calcium silicate panels. The cavity holds a contents container or an inner core. The inner core can be part of an extractor and made from porous material including fluid channels for absorbing liquid cryogen. Contents containers can be housed in the inner core.

A liquid nitrogen tank includes a tank, a storage rack and a drive component. The tank includes a tank cover, a tank body, a vacuum cavity layer and a heat-insulating cavity layer. The tank cover is disposed to cover on the tank body. An access door is provided on the tank body. A storage cavity is provided in the tank body. The heat-insulating cavity layer is provided on a periphery of the storage cavity. The vacuum cavity layer is provided on a periphery of the heat-insulating cavity layer. The storage rack is provided in the storage cavity. A plurality of cryopreservation tube racks are stored in the storage rack. The drive component can drive the storage rack to rotate and move up and down in the storage cavity, and can drive the plurality of cryopreservation tube racks to move to a position corresponding to the access door.

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.

For improving storage of hydrogen in a vehicle, a hydrogen tank assembly is provided for a vehicle. The hydrogen tank assembly includes an inner tank wall defining a hydrogen tank volume configured for storing liquid hydrogen; and an outer hydrogen collector defining, together with the inner tank wall, at least one cavity outside of the hydrogen tank volume and including at least one hydrogen outlet for leading gaseous hydrogen which leaks from the hydrogen tank through the inner tank wall into the at least one cavity to a hydrogen storage or a hydrogen consumer.

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 production method for an aerogel laminate includes a step of preparing a sol of producing a sol for forming an aerogel, an applying step of applying the sol obtained in the step of preparing a sol to a support having a heat ray reflective function or a heat ray absorbing function, and drying the sol to form an aerogel layer, an aging step of aging the aerogel layer obtained in the applying step, a washing step of washing the aged aerogel layer and performing solvent exchange, and a drying step of drying the aerogel layer washed in the washing step.