A pressure vessel fluid manifold assembly includes a pressure vessel having a plurality of lobes joined to each other, each of the plurality of lobes having a wall disposed in contact with an adjacent wall of an adjacent lobe, and wherein the manifold can be external or internal to the lobes.

The invention relates to a container for holding and storing liquids and viscous materials, in particular cryogenic fluids, comprising a jacket (12), which defines the interior (14) of the container (10) having a chamber (16), said container (10) being constituted of at least two container structures (20, 20′, 20″) and each of said at least two container structures (20, 20′, 20″) being formed as one piece from a blank (32) and having a dome portion (22), a branching portion (24), which is contiguous to the dome portion (22), and two cylinder portions (26, 28; 26′, 28′), which are contiguous to the branching portion (24), and the mutually facing container structures (20, 20; 20′, 20″) which are adjacent to each other being joined together.

Liquid storage systems for space vehicles include at least one storage tank including a tank inlet, a tank outlet, and a plurality of liquid storage compartments coupled to each other in series between the tank inlet and the tank outlet. Each liquid storage compartment includes an end plate including a porous outlet at an end of the liquid storage compartment adjacent to another liquid storage compartment. Propulsion systems for space vehicles include at least one such liquid storage tank. Methods of providing a liquid propellant to a thruster of a space vehicle include withdrawing a liquid propellant from a first compartment within a tank and flowing the liquid propellant from a second compartment into the first compartment through a porous element associated with an end plate separating the first compartment from the second compartment.

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).

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 fuel delivery and storage system is provided. A further aspect employs a remote central controller and/or software instructions which receive sensor data from stationary and bulk fuel storage tanks, portable distribution tanks, and end use tanks. Another aspect of the present system senses and transmits tank or hydrogen fuel characteristics including temperature, pressure, filled volume, contaminants, refilling cycle life and environmental hazards. Still another aspect includes a group of hydrogen fuel tanks which is pre-assembled with sensor, valve, microprocessor and transmitter components, at least some of which are within an insulator.

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.

A pressure vessel and a system of a vehicle with such a pressure vessel, wherein the pressure vessel is suitable for storage of pressurized fluids, comprising a housing which extends along a longitudinal axis. The housing defines an inner volume. The shape of the housing, in longitudinal cross-section, is defined by the circumference of a set of circles. The set of circles comprises a central circle, with a center point which is defined by the longitudinal axis, and four primary peripheral circles each of which intersects with the central circle at two points. The primary peripheral circles are axially distributed on the central circle in opposing pairs.

The present invention relates to a storage tank for liquid hydrogen, comprising a wall, a base, which closes the wall at the end face on one side, a top, which closes the wall at the end face on the side facing away from the base, and an intermediate wall, which is arranged inside of the wall and at a distance therefrom, wherein a gap is provided between a lower edge of the intermediate wall and the base, so that an interior enclosed by the intermediate wall is fluidically connected to an interior enclosed by the wall.

A large volume natural gas storage tank comprises rigid tubular walls having closed tubular cross-sections that are interconnected at opposing ends with two other rigid tubular walls such that interiors of the rigid tubular walls define an interior fluid storage chamber. The storage tank also includes bulkheads positioned in the interior fluid storage chamber across intermediate segments of the rigid tubular walls and closure plates connected between exterior surfaces of successive interconnected rigid tubular walls to define sides of the storage tank. Interior surfaces of the closure plates and exterior surfaces of the rigid tubular walls define an auxiliary fluid storage chamber. The storage tank also includes exterior support structures extending through the closure plates and between the exterior surfaces of the rigid tubular walls on some of the sides of the storage tank to reinforce the storage tank against dynamic loading from fluid in the interior fluid storage chamber.