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.

Collapsible containers are an attractive alternative to surface-tension propellant management devices (PMDs) for handling cryogenic liquids, as the collapsible container comparatively may 1) allow higher expulsion flow rates than vanes and sponges, 2) significantly reduce operational complexity, and 3) thermally insulate the propellant from environmental heat leaks. Furthermore, while historical cryogenic collapsible containers suffered from the low ductility of polymer films at cryogenic temperatures, the technology disclosed herein shows that the incorporation of folded patterns into the collapsible container substantially increases the reusability of the cryogenic PMD.

A rocket propellant tank arrangement (40) for storing fuel and oxidizer for launching a rocket includes an oxygen tank (42) for storing liquid oxygen and a fuel tank (52) for storing liquid fuel, wherein the fuel tank is at least partially arranged within the oxygen tank.

A tank support assembly for a vehicle includes a vehicle structure and a storage tank assembly. The storage tank assembly is held in place relative to the vehicle structure via a magnetic support system. The magnetic support system includes tank magnets affixed to the storage tank assembly and structure magnets affixed to the vehicle structure. The tank magnets interact with the structure magnets to passively provide repulsive magnetic forces that constrain movement of the storage tank assembly relative to the vehicle structure without the tank magnets mechanically engaging the structure magnets.

In accordance with at least one aspect of this disclosure, a life support system (LSS) for a spacecraft includes a gas accumulator configured to store a gas, the gas accumulator including a non-metallic inner lining. A fluid processor is fluidly connected to the gas accumulator configured to produce one or more life sustaining fluids from at least the gas. A supply conduit can be fluidly connected to the fluid processor configured to supply the one or more life sustaining fluids to one or more portions of the spacecraft.

The present invention is directed toward a new and improved solenoid-controlled, liquid cryogenic-hydraulically actuated valve assembly wherein, in addition to the valve assembly controlling the flow of liquid cryogenic fluid therethrough, a portion of the liquid cryogenic fluid is effectively utilized to hydraulically actuate and control OPEN and CLOSED valves to predetermined positions such that the flow of cryogenic fluid, through the valve assembly from an inlet flange to an outlet flange of the valve assembly, is permitted or prevented.

A novel tank cryogenic-compatible composite pressure vessel that beneficially utilizes Vapor Cooled Shielding (VCS) is introduced to minimize thermal gradients along support structures and reduces heat loads on cryogenic systems. In particular, the configurations and mechanisms to be utilized herein include: providing for a desired number of passageways and a given thickness of the VCS, reducing the thermal conductivity of the VCS material, and increasing the cooling capacitance of the hydrogen vapors.

A gas injection device for injecting an expulsion gas into a tank for a liquid. The gas injection device comprises an inlet pipe for receiving the gas and a distributor portion for releasing the gas through a plurality of capillary passages. The inlet pipe has a first end configured to be connected to a gas supply line and a second end located within a chamber in the distributor portion. The capillary passages respectively extend in a direction adapted to a periphery of the chamber. A tank for a liquid is provided, the tank comprising a gas injection device. A spacecraft is provided comprising such a tank.

A rocket propellant tank arrangement (40) for storing fuel and oxidizer for launching a rocket includes an oxygen tank (42) for storing liquid oxygen and a fuel tank (52) for storing liquid fuel, wherein the fuel tank is at least partially arranged within the oxygen tank.

A hybrid softening strip for controlling stresses in a joint at low temperatures includes a layer of sacrificial material that can be tailored to fit the softening strip in the joint after the softening strip has been bonded to a structure.