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 fuel cylinder, such as a high-pressure fluid storage tank, is provided with dual-inlet refilling capabilities. The storage tank may include a main body section with a first domed end portion and a second domed end portion disposed at opposite portions of the main body section. A first inlet assembly and a second inlet assembly are provided at the respective first domed end portion and the second domed end portion. Each inlet assembly is configured to provide fluid communication between a supply of a high-pressure fluid and an interior of the storage tank. Each inlet assembly may include a boss and a tank valve, with each tank valve being in fluid communication with the compressed fluid receptacle. During filling of the storage tank, the high-pressure fluid travels through a compressed fluid receptacle and enters the interior of the storage tank simultaneously through each of the first and second inlet assemblies.

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 fuel gauging sensing device for a fuel tank for aircrafts includes an optical fiber harness along the internal surface of the tank, a master optical controller connected to a first terminal of the optical fiber harness, a slave optical controller connected to a second terminal of the optical fiber harness, wherein the optical fiber harness includes Fiber Bragg Grating (FBG) sensors spaced in the optical fiber harness between 1 mm and 25 mm to provide temperature gradients inside the tank and wherein the master and slave optical controllers are configured to obtain the fuel gauging of the tank based on the output from the FBG sensors.

A reinforcement element, suitable for composite pressure vessel, may be configured to be inserted and to fill in a hollow shaft of a plastic liner of the composite pressure vessel, the hollow shaft connecting opposite walls of the liner. The reinforcement element may include a central part and two external parts constituted by a plurality of continuous fibres impregnated with a first resin. The central part of the reinforcement element may have a dimension substantially equal to the dimension of the hollow shaft and being a full part. The two external parts may be able to be unfolded and fixed on the external surface of opposite walls of the liner. A composite pressure vessel may include such a reinforcement element.

The disclosure relates to an electrically powered mobile fluid supply system (MFSS) for supplying fluid to a host unit. The MFSS comprises at least one pressurized fluid volume, a fluid dispenser fluidly connectable to the host unit and configured to supply fluid from the at least one pressurized fluid volume to the host unit in a fluid supply operation, and at least one compressor configured to build sufficient pressure for the fluid supply operation in the MFSS. The MFSS is configured to be electrically connected to the host unit and the at least one compressor is configured to be electrically connected to the MFSS and electrically powered by the host unit during the fluid supply operation.

The disclosure further relates to a method for supplying fluid to a host unit, to a control unit configured to control the fluid supply operation, and to the MFSS.

An integrated pressure regulator is provided with three stages configured to reduce an extreme tank pressure down to a typical working pressure. The regulator is configured to supply a steady working pressure until the tank pressure is reduced to little more than the working pressure itself. Stages of the pressure regulator are integrated into a body and arranged to minimize regulator mass and volume. A thermally-triggered pressure relief device may be included with a triggering time adapted to enhance the safety of smaller cylinders that may be used, e.g., in aerial applications.

In order to enlarge a tank volume of a hydrogen powered aircraft, an aircraft tank for storing cryogenic H.sub.2 is configured as a non-circular dorsal tank. The aircraft tank may be configured as a conformal fuel tank fitted to an outer contour of an aircraft fuselage. Further, an aircraft is provided with such an aircraft tank.

A system and method for the transfer of cryogenic fluid fuel includes a nozzle positionable with respect to fuel tank inlet, e.g., of an unmanned aerial vehicle (UAV), a seal to seal the area where the nozzle and inlet are connected, a collapsible and expandable bellows providing an isolation volume where the fluid is transferred from the nozzle into the inlet; a vacuum is provided in the volume to avoid accumulation of fuel or other species in the volume.

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.