A tank device for a tank liquid comprises a pressure vessel with a first chamber for the tank liquid and second chamber arranged in an interior of the tank. The first and second chamber are closed off with respect to each other and are in operative connection via at least one membrane which separates the first and second chambers and is capable of vibration. The tank device further comprises a controllable element for effecting a pressure surge in the pressure vessel, a pressure sensor for detecting a pressure vibration resulting from the pressure surge and a temperature sensor for measuring a temperature prevailing in the pressure vessel. An evaluation device of the tank device is configured to determine a current gas volume in the pressure vessel from a respectively detected pressure vibration and a measured temperature to thereby calculate the mass of the tank liquid.

A composite storage tank may include a wall structure including at least three regions including an inner region, an outer region, and at least one permeation barrier. Another region may be optionally incorporated for venting potential permeation of fluids. The at least one permeation barrier and/or the venting layer may be strategically positioned between the inner region and the outer region to reduce or at least partially prevent fluid permeation of the inner region or the outer region. A vehicle may include such a composite storage tank. Methods of forming a composite fluid storage tank may include forming an inner composite region, applying a permeation barrier to an outer surface of the inner composite region, forming an outer composite region, and curing the inner composite region and the outer composite region with the permeation barrier to form the composite fluid storage tank.

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 pressure vessel containing a main body with at least one opening. The pressure vessel is made from a BMG material. The pressure vessel may contain an additional part such as a neck, a liner, a rib, a lattice, a fin, and a diaphragm. The pressure vessel may be free of a welded joint in entirety. The pressure vessel may contain multiple parts in the main body, each of which is free of a welded joint. The pressure vessel may be made through thermoplastic forming.

To manage propellant in a spacecraft, the method of this disclosure includes storing propellant in a tank as a mixture of liquid and gas; transferring the propellant out of the tank; converting the mixture of liquid and gas propellant into a single phase, where the single phase is either liquid or gaseous; and supplying the single phase of the propellant to a thruster.

The invention provides improvements on thermal performance of multilayer insulation for hot and cold feedlines. Insulation on feedlines has always been problematic, and can perform ten times worse than tank insulation contributing as much as 80% of total system heat leak. The poor performance of traditional MLI wrapped on feed lines is due to compression of the layers, causing increased interlayer contact and heat conduction. The MLI performance is not only much worse than expected, but also difficult to predict. Spacer structures are presented which provide a well-defined, accurately characterized support between the thermal radiant barriers in a multilayer insulation. The invention provides a robust, structural insulation that is much less sensitive to wrap compression and installation workmanship allowing for more predictable, higher performance insulation structure.

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.

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 fiber reinforced energetic composite is provided. The fiber reinforced energetic composite includes reinforcing fiber embedded in a cured polymer matrix and energetic polymer nanocomposite disposed in the reinforcing fiber. The energetic polymer nanocomposite including core-shell nanoparticles entrained in a polymer matrix. The core-shell nanoparticles include a core made of a metal and at least one shell layer made of a metal oxide disposed on the core or a core made a metal oxide and at least one shell layer made of a metal disposed on the core. The method of making a fiber reinforced energetic composite is also provided. Further, a composite container made of fiber reinforced energetic composite is further provided.

To provide a propellant tank such as a fuel tank and an oxidant tank for a spacecraft, the propellant tank discharging propellant such as liquid hydrogen and liquid oxygen accumulated therein toward a rocket engine by pressurizing an inside thereof by operating gas. The propellant tank includes a tank body that accumulates therein the propellant in a liquid state, and a holding container that is provided inside the tank body and disposed with a predetermined gap from an inner wall of the tank body, so that the propellant in a liquid state can be held therein, when the inside of the tank body is in a microgravity state or a zero-gravity state.