An intelligent fuel storage system can consist of a storage pod connected to a storage module with the storage pod having a plurality of separate storage vessels each residing below a ground level. The storage pod may concurrently store a first volume of a first fuel and a second volume of a second fuel prior to altering the first and second volumes in accordance with a performance strategy generated by the storage module to provide a predetermined blend of the first fuel and second fuel with at least a threshold volume and at least a threshold pressure.

A cryogenic dewar may include an inner tank and an outer tank. The cryogenic dewar may further include a plurality of trunnion mounts. A first four of the trunnion mounts may be coupled between a front half of the inner tank and a front half of the outer tank. A second four of the trunnion mounts may be coupled between a rear half of the inner tank and a rear half of the outer tank. The trunnion mount may be further strengthen with a plurality of pie-shaped reinforcing pads welded to each other and to an outer surface of the inner tank.

Disclosed herein is a structure that comprises a tank including an outer cylindrical surface and a domed end. The structure also comprises a tank skirt positioned circumferentially around the tank. A wall of the tank and a wall of the tank skirt form two sides of a y-joint between the tank and the tank skirt. The y-joint includes a wedge structure positioned between the tank and the tank skirt. Additionally, a thickness of at least one of the wall of the tank or the wall of the tank skirt forming the y-joint tapers such that the thickness of the at least one of the wall of the tank or the wall of the tank skirt that tapers has a greater thickness at the y-joint than away from the y-joint.

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 liquid cryogen stored in a liquid cryogen space of a closed insulated cryogenic storage vessel is subcooled by allowing it to enter into a conduit disposed in the liquid cryogen space where it is expanded by a pressure reducer in the conduit, thereby producing a cooled biphasic mixture of the cryogen in liquid and vaporized forms. The cooled biphasic mixture has a temperature lower than that of the liquid cryogen in the liquid cryogen space. Heat is transferred across the conduit from the liquid cryogen in the liquid cryogen space to the cooled biphasic mixture.

A cryogenic energy storage system comprises at least one cryogenic fluid storage tank having an output; a primary conduit through which a stream of cryogenic fluid may flow from the output of the fluid storage tank to an exhaust; a pump within the primary conduit downstream of the output of the tank for pressurising the cryogenic fluid stream; evaporative means within the primary conduit downstream of the pump for vaporising the pressurised cryogenic fluid stream; at least one expansion stage within the primary conduit downstream of the evaporative means for expanding the vaporised cryogenic fluid stream and for extracting work therefrom; a secondary conduit configured to divert at least a portion of the cryogenic fluid stream from the primary conduit and reintroduce it to the fluid storage tank; and pressure control means within the secondary conduit for controlling the flow of the diverted cryogenic fluid stream and thereby controlling the pressure within the tank. The secondary conduit is coupled to the primary conduit downstream of one or more of the at least one expansion stages.

A gas valve is adapted for controlling the flow of a medical gas for oxygen therapy in case of spontaneous breathing. The gas valve comprises a connection component for connecting the gas valve to an external supply; and a regulating system configured for selecting and supplying a pulsating flow of medical gas or a continuous flow of medical gas, in which the regulating system comprises a first sub-regulating system for supplying a pulsating flow and a second sub-regulating system for supplying a continuous flow.

The invention relates to a container (1) for pressurized fluid, in particular a gas cylinder, having a given internal volume (2), having a fluid distribution valve (3) having a member for selecting the flow rate (12) able to adopt a plurality of distinct positions each corresponding to a given fluid flow rate, and an electronic device (7) having means for measuring pressure, microprocessor (15)-based data processing means (5) for processing the pressure measurements, and display means (6) for displaying the remaining fluid calculated by the data processing means (5).

A multi-walled storage tanks use pressure differences between walls/shells to maximize fluid mass storage for tank size by reducing or minimizing the distance between the outer most layers of a multi-layer storage device, and keeping the middle one(s), particularly the innermost space, as large as possible, while having shell walls of substantially the same material and thickness, with no wall being thicker than the inner shell wall.

Various embodiments of space launch vehicle systems and associated methods of manufacture and use are disclosed herein. In some embodiments, the systems include a reusable, horizontal takeoff/horizontal landing (HTHL), ground-assisted single-stage-to-orbit (SSTO) spaceplane that is capable of providing frequent deliveries of people and/or cargo to Low Earth Orbit (LEO). In some embodiments, the spaceplane can takeoff with the aid of a rocket-powered sled that, in addition to providing additional thrust for takeoff, can also provide propellant for the spaceplane engines during the takeoff run so that the spaceplane launches with full propellant tanks.