The invention relates to a method for refuelling a vehicle (60) or an autonomous vehicle (60). At least one hydrogen tank (10) accommodating gaseous hydrogen is fitted in the vehicle (60). The method comprises the following method steps: The vehicle (60) drives into a refuelling area (24). A refuelling operation (28; 78, 80, 82) is performed on the vehicle (60). Then, the temperature of the contents of the at least hydrogen tank (10) is checked (30). If a temperature (74) of the tank contents of the at least one hydrogen tank (10) exceeds a temperature limit value (32), the vehicle (60) is transferred to a cooling down area (36). There, the tank temperature (44) is checked a second time following a cooling down phase. The tank pressure is checked (48) if the tank temperature (74) lies below a temperature limit value. If the tank pressure (76) in the at least one hydrogen tank (10) is below a tank pressure limit value, the vehicle (60) is transferred to the refuelling area (24) to continue refuelling; if the tank pressure (76) is in the tank pressure limit range, refuelling is halted (52).

A hydraulic compressed air energy storage system includes air and liquid tanks, each of which includes interdependent volumes of liquid and air. Each tank includes dedicated passages through which incoming air may be fed, forcing outflow of liquid, or incoming liquid may be fed, forcing outflow of air. Compressed air tanks are connected to a first group of the air and liquid tanks. The system further includes a pump and a liquid turbine, the liquid turbine being electrically connected to a generator for generating electric power. During charging of the system, liquid is pumped through the first group of air and liquid tanks, and air is expelled from the first group of air and liquid tanks and compressed in the compressed air tanks. During discharging of the system, compressed air is released from the compressed air tanks, and said compressed air pumps liquid through the liquid turbine, thereby generating electricity.

A device for carrying fuel in aircraft and spacecraft includes a carrier element having a longitudinal axis, and a fuel tank with a side wall and a chamber at least partially delimited by the side wall. The tank is arranged in the carrier element. The chamber and the side wall extend in a direction along the longitudinal axis. The side wall has a pressure-receiving component that converts a pressure from the chamber on the side wall into a contraction force acting on the side wall along the longitudinal axis. The contraction force compensates for an expansion force, resulting from the pressure from the chamber and acting on the side wall along the longitudinal axis. This provides an improved device for carrying fuel in aircraft and spacecraft, wherein the aircraft and spacecraft has constant flight mechanical properties because of the device.

Methods of, and control systems for, operating modular, liquid natural gas (LNG) manifold apparatuses, crossover systems for such modular manifold apparatuses, and systems including one or more of the modular manifold apparatuses and a plurality of ISO tank containers. The modular manifold apparatus includes an ISO container (e.g., an open-frame ISO container) with a plurality of container connection sections or bays, a liquid system, and a vent system, where each of the liquid and vent systems includes a header and a plurality of connection lines configured to be coupled to the respective liquid and vent connections of LNG containers adjacent the modular manifold apparatus.

A cryogenic fluid transfer device comprising a first tank, a second tank, and a fluid transfer circuit, wherein the first tank comprises a cryogenic fluid distribution tank configured to store a cryogenic fluid in a liquid phase in a lower part thereof and in a gaseous phase in an upper part thereof, wherein the second tank comprises a cryogenic receiving tank configured to house the cryogenic fluid in liquid phase in a lower part thereof and in gaseous phase in an upper part thereof, wherein the fluid transfer circuit is configured to connect the first and second tanks, the fluid transfer circuit comprising a first pipe connecting the upper parts of the first and second tanks and comprising at least one valve, and a second pipe connecting the lower part of the first tank to the second tank that comprises a pump that has an inlet connected to the first tank and an outlet connected to the second tank, wherein: the pump and the at least one valve of the first line are configured so as to ensure a fluidic connection of the upper parts of the first and second tanks by opening the at least one valve during a transfer of the cryogenic fluid in liquid phase from the first tank to the second tank with the pump.

An apparatus and a method are provided for an alternative fuel system, comprising a plurality of fuel tank assemblies interconnected with fuel lines; the plurality of fuel tank assemblies comprising a CNG fuel tank and a fuel tank shield; wherein a first and second fuel tank assembly is disposed immediately in front of a rear wheel assembly, and a third fuel tank assembly is disposed immediately behind the rear wheel assembly.

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.

Device for storing and transferring cryogenic fluid, comprising at least one elementary container comprising a liquefied gas tank, the tank being provided with a first pipe for transferring fluid, which pipe has a first end connected to an upper end of the tank, the tank being provided with a second pipe for transferring fluid, which pipe has a first end connected to a lower end of the tank, the first and the second transfer pipes each comprising an assembly of respective valves, characterized in that the first transfer pipe comprises two arms forming two second ends connected in parallel to the first end of the first transfer pipe, the two second ends of the first transfer pipe each being provided with a respective fluidic connection coupling, and in that the second transfer pipe comprises two arms forming two second ends connected in parallel to the first end of the second transfer pipe, the two second ends of the second transfer pipe each being provided with a respective fluidic connection coupling.

An array of pressure vessels for storage of a compressed gas includes at least one Type 4 pressure vessel and at least one Type 1 pressure vessel. The Type 1 pressure vessel is in fluid communication with the at least one Type 4 pressure vessel. A metal wall of the at least one Type 1 pressure vessel has a Type 1 thermal conductance that is greater than a Type 4 thermal conductance of the at least one Type 4 pressure vessel.

Provided is a high-pressure tank that includes a tank main body including a mouthpiece, a valve fitted to the mouthpiece, and a pipe extending from the valve in an axially inward direction of the tank main body and for ejecting a gas into the tank main body. The pipe includes an ejection nozzle provided at an end of the pipe and for ejecting the gas, a first bent portion located between the ejection nozzle and the valve and extending in a direction inclined relative to an axial direction of the tank main body, and a second bent portion having the ejection nozzle and extending in a direction inclined relative to the axial direction. One of an inclination angle of the first bent portion relative to the axial direction and an inclination angle of the second bent portion relative to the axial direction is larger than 0° and not larger than 90°, and the other is not smaller than −0° and smaller than 0°, when the pipe is viewed in a direction perpendicular to the axial direction.