A heat exchanger generally employs a method for supplying liquid having critical pressure or higher or high pressure in order to suppress boiling. However, gas obtained by a evaporator behind the heat exchanger has relatively low pressure, and therefore supplying the liquid to the heat exchanger requires a system for converting an energy form of the obtained gas into kinetic energy or electrical energy, and increasing the pressure by a mechanical pump. Thus, the complicated system involving an efficiency loss is only solution, and it is difficult to achieve simplification of a system or reduction in the weight of a propellant supply device in a moving body, specifically, a flying object.

Example implementations relate to Additive Manufacturing (AM) pressurization diffusers. An example diffuser includes an integral component configurable for receiving and diffusing pressurant. Particularly, the integral component includes multiple elements manufactured as a single-piece structure, including an inner filter, outer shell, and flange. The inner filter includes micro-diamond holes that enable pressurant received at an opening of the inner filter to diffuse out of the inner filter and subsequently through holes positioned in a shell surface of the outer shell. The flange can position the diffuser such that the opening of the inner filter is in pressurant communication with a pressurant source (e.g., opening of a tank) enabling the diffuser to receive and diffuse pressurant in a predefined pattern. For example, when the diffuser is positioned inside a tank, the diffuser can have a frustum configuration that helps diffuse pressurant upwards towards inner sidewalls of a pressure vessel, tube or channel.

A container that provides for control of fluid flow in the event of a failure of the container is disclosed. In accordance with embodiments of the present invention, a container is presented that includes a container wall; and one or more flow impeding structures coupled to the container wall, wherein at least one of the one or more flow impeding structures is a multi-sheet layer that deforms to impede flow in a failure of the container wall. In some embodiments, the multi-sheet layer includes cavities formed between individual sheets.

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.

Provided is a liquid tank, including: a cylindrical seamless tank body having both end portions being reduced in diameter toward respective end sides; and a plurality of annular baffles provided inside the tank body and arranged at intervals in an axial direction of the tank body, in which at least one of the plurality of baffles is held on an inner peripheral surface of the tank body.

A fire retardant material comprising a carbon fiber which tensile elasticity is 700 GPa or more, and a fire retardant resin such as polycarbonate.

A rocket propulsion system comprising a first cryogenic tank and a second cryogenic tank, wherein the first cryogenic tank is filled with a first propellant, and the second cryogenic tank is filled with a second propellant, for purposes of feeding at least one repeatedly ignitable main propulsion unit in a propulsion phase of the rocket propulsion system. For purposes of tank pressurization via at least a low level of acceleration in a ballistic phase, a first auxiliary propulsion unit can be operated by means of a first gas pressure accumulator, and at least one further auxiliary propulsion unit can be operated by means of a further gas pressure accumulator, and the rocket propulsion system is assigned an energy conversion unit, which is designed at least to charge the first and the second gas pressure accumulator, preferably in the ballistic phase.

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 system for increasing the efficiency of heating cryogenic fluid flowing in a downstream direction through a fluid conduit includes a heating mechanism, an upstream valve, a downstream valve, and a controller. The heating mechanism heats the cryogenic fluid, resulting in conversion of a portion of the cryogenic fluid into a buoyant flow moving in an upstream direction. The upstream valve is located upstream of the heating mechanism and controls an upstream-valve mass flow rate of the cryogenic fluid. The downstream valve is located downstream of the heating mechanism and controls a downstream-valve mass flow rate of the cryogenic fluid. The controller adjusts the upstream valve to a choked position at which: an upstream-valve non-buoyant mass flow rate substantially matches the downstream-valve mass flow rate, and the upstream valve at least partially blocks the buoyant flow from flowing in the upstream direction past the upstream valve.

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.