Cryogenic propellant tank (1) for a spacecraft engine, comprising an external enclosure (10) defining an internal volume, characterized in that the internal volume of the tank comprises a primary volume (V1) and a secondary volume (V2) connected to the primary volume (V1) via a valve (20) configured to selectively allow a passage of fluid from the primary volume (V1) to the secondary volume (V2), or to isolate the secondary volume (V2) from the primary volume (V1), the primary volume (V1) having a primary orifice (11) adapted to be connected to a first pressurization source (41), the secondary volume (V2) having a supply orifice (4) adapted to be connected to a supply line of a spacecraft engine (30), and a secondary orifice (12) adapted to be connected to a second pressurization source (42).

A hydrogen filling apparatus that can quickly fill vehicles equipped with multiple large-capacity fuel tanks with hydrogen gas while complying with filling protocol. The hydrogen filling apparatus (100) of the present invention includes: a plurality of filling systems; a filling control device (10, 20) for each of the filling systems; a filling pipe communicating with a rear facility in each of the filling systems; a set of filling members (for example, flow control valves, flow meters) interposed in each of the filling pipes and connected to each of the filling control devices; and a filling hose connected to each of the filling pipes, each filling hose having a filling nozzle at a tip; wherein one of the plurality of filling control devices has a function of selectively exerting a first control mode that controls only the filling system including the filling control device and a second control mode shared as a control device for the plurality of filling systems, and a switching means for switching between the first control mode and the second control mode in the one of the filling control devices is provided.

A direct fueling station and a method of refueling are provided. The station includes an insulated tank for storing a liquefied fuel, a pump, at least a heat exchanger, a control unit, a dispenser including a flow meter, a flow control device, and at least one sensor for testing pressure and/or temperature. The heat exchanger converts liquefied fuel from pump into a gaseous fuel, which is added into an onboard fuel tank in a vehicle. The control unit includes one or more programs used to coordinate with the pump, the flow meter, the flow control device, and/or the sensor(s) so as to control a refueling method. A peak electrical power requirement is less than that determined by the product of a rated volumetric flow rate of the pump and a rated pumping pressure adequate for a fill pressure of the vehicle. A computer implemented system having the program(s) is also provided.

A hydrogen gas supply apparatus according to one aspect of the present invention includes a compressor configured to compress hydrogen gas and supply the hydrogen gas compressed to a pressure accumulator which accumulates the hydrogen gas, an adsorption column disposed between the discharge port of the compressor and the pressure accumulator, and configured to include an adsorbent for adsorbing impurities in the hydrogen gas discharged from the compressor, and a plurality of valves disposed at the gas inlet/outlet port side of the adsorption column, being at a discharge port side of the compressor, and configured to be able to seal the adsorption column, wherein the space in the adsorption column is sealed using the plurality of valves such that the inside of the adsorption column is maintained to have a high pressure by the hydrogen gas compressed in the case where the compressor is stopped.

A cryogenic fluid containment system is disclosed. The system can store a fluid such as hydrogen at a cryogenic temperature and pressure. As the fluid naturally warms, the fluid can be directed to a portion of a liquefaction system that is configured to perform a cooling technique on the fluid. The cooling techniques may be Joule-Thomson cooling techniques. The liquefaction system may be equipped to perform both non-Joule-Thomson cooling techniques and Joule-Thomson cooling techniques. The system is configured to direct fluid to an appropriate portion of the liquefaction system, which may be based at least in part upon a Joule-Thomson coefficient of the fluid.

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 system for dispensing cryogenic liquid includes a container defining an interior with a partition dividing the interior into primary and reserve chambers. Cryogenic liquid within the primary chamber is separated from cryogenic liquid in the reserve chamber. The partition provides a headspace cornrnurrrcation passage. A primary pressure building circuit has an inlet selectively in liquid communication with the primary chamber and an outlet in fluid communication with the headspaces of the primary and reserve chambers. A reserve pressure building circuit has an inlet selectively in liquid communication with the reserve chamber and an outlet in fluid communication with the headspaces of the primary and reserve chambers. An equalizing circuit is selectively in liquid communication with the primary and reserve chambers. A dispensing line is selectively in liquid communication with the primary chamber.

Measures for monitoring and manufacturing tanks for cryogenic liquids. The tank is manufactured in a way that signal and power lines from a control unit to sensors of the cryogenic tank are integrated with the tank walls. The conductive track structure so formed has a layer structure that uses the naturally occurring or artificially generated insulating layer on the tank wall material as a substrate on top of which conductive paths are formed that connect the sensors to the control unit.

Filling methods and systems are provided for a conformable fuel tank. In one example, a system comprises an active thermal management arrangement for the conformable fuel tank. The active thermal management arrangement comprises one or more recirculation passage for mixing hot fuel distal to an inlet port of the conformable fuel tank with cool incoming fuel flowing to the inlet port.

A body structure has an inlet port that receives fluid, a first outlet port that connects to a top-fill line of a cryogenic tank, a second outlet port that connects to a bottom-fill line of a cryogenic tank and a slider tube cylinder. A cylinder housing connects to the body structure and has a pressure comparison cylinder with upper and lower volumes, with the latter in fluid communication with a cryogenic tank. A piston having a piston shaft slides within the pressure comparison cylinder. A pressure regulator is in fluid communication with the upper volume and the slider tube cylinder. A slider tube is connected to the piston shaft and slides within the slider tube cylinder. The slider tube cylinder selectively directs fluid to a top-fill line through the first outlet port or to a bottom-fill line through the second outlet port.