An aircraft with a multi-walled fuel tank and method of manufacturing is presented. The aircraft includes a blended wing body and a fuel tank attached to the blended wing body configured to store liquified gas fuel. The fuel tank includes an inner wall, outer wall, and interstitial volume in between that is filled with insulation. The interstitial volume includes a reflective film layer and a structural insulation layer.

A multi-layered vessel may include a first vessel layer and a retaining vessel layer. The retaining vessel layer may be configured to strengthen the first vessel layer, and the retaining vessel layer may be secured to outer walls and/or inner walls of the first vessel layer. The first vessel layer alone (or with the retaining vessel layer and/or one or more additional retaining vessel layers) may form a sealed vessel.

A method of manufacturing a vessel for housing a fluid, wherein the vessel comprises at least one strut extending through an inner space of the vessel. The method comprises the steps of manufacturing a core structure as a shaping element of the vessel, during and/or after manufacturing the core structure, providing the at least one strut such that at least one end portion of the at least one strut extends from an outer surface of the core structure, bending the at least one end portion of the at least one strut, and arranging at least one outer vessel layer to cover the at least one bent end portion of the at least one strut. The invention further concerns a vessel for housing a fluid.

Methods and manufactures disclosed herein generally relate to a cannular composite (ITC) structure composed of multiple layers of sealing, reinforcement, sensing, protection, and interspatial injected materials.

The invention concerns a spacecraft propellant tank designed for storing and supplying fuel to the propulsion system, as well as its application method, which is related to space technology and particularly to the design of tanks for storing liquid propellants within rocket engines. The tank in question comprises a body featuring at least one convex edge that creates a corner capillary and an intake port positioned on one of these convex edges. Additionally, the tank's interior surface is treated to be hydrophilic. The objective of this invention is to develop a spacecraft propellant tank characterized by its lightweight and straightforward design. It facilitates the creation of various propellant tank shapes while minimizing the quantity of internal components that reduce useful volume. It also ensures consistent and reliable functionality of the propellant system with continuous supply of propellant to the intake port, even in the absence of gravity and during multiple activations of the propulsion system. The claimed invention achieves its objective by implementing technical results that include enhancing the efficiency of propellant supply within the tank to the intake port, improving reliability, augmenting the useful internal volume, and offering a variety of tank shapes. The stated objectives are met in particular through the hydrophilic properties of the propellant tank's inner surface, the design of the propellant tank shape featuring at least one convex edge that forms a corner capillary, and positioning of the intake port on one of the convex edges that forms the corner capillary. The application method for the spacecraft propellant tank involves initially filling the tank with liquid propellant and pressurizing gas through the intake port prior to spacecraft launch. Subsequently, once the spacecraft is in orbit, propellant is conveyed from the tank to the propulsion system through the intake port. The movement of liquid propellant towards the intake port is facilitated by the pressure of the pressurizing gas and a localized pressure reduction generated during propellant discharge. This reduction occurs in the corner capillary near the intake port relative to the pressure of the propellant in other sections of at least one corner capillary, thus establishing a flow of propellant through the corner capillaries towards the intake port area.

A pressure vessel includes a body defined by a cross-sectional shape along a plane transverse to a centerline. The cross-sectional shape includes an inner surface defining an interior void and a wall extending from the inner surface to an outer surface defining an exterior of the body. The inner surface includes an arcuate region and a gabled region. The gabled region forms a curved interior peak opposite a center of the arcuate region. The arcuate region and the gabled region together define a teardrop shape. The wall includes a curved segment along the arcuate region having a curved segment minimum thickness at a location opposite the interior peak, an apex aligned with the interior peak and having an apex thickness, and thickened regions adjacent intersections between gabled region and the arcuate region and having greater radial thickness than the curved segment minimum thickness.

A pressure vessel that is able to store fluid includes a plurality of main body portions provided with a space inside, and one or more connection portions that communicate the main body portions to each other. The main body portion and the connection portion are alternately connected in series, and the connection portions are bent. A cross section perpendicular to a longitudinal direction of the main body portion has an outer shape including a linear portion and an arc portion. Each of the main body portions is disposed such that an outer peripheral surface located on the linear portion is in contact with an outer peripheral surface located on the linear portion of an adjacent main body portion.

A pressure vessel in which fluid is storable includes a plurality of main body portions that each forms a space on the inside, and one or more connecting portions that each provide communication between the main body portions. The main body portion and the connecting portion are alternately connected in series and the connecting portion is bent, and a section of the main body portion perpendicular to the longitudinal direction has a substantially quadrilateral shape. The main body portion has a reinforcing member that connects a pair of surfaces facing each other in the space.

A pressure vessel for fluid includes a plurality of main body portions, each having a tubular shape extending along a first direction and disposed along a second direction orthogonal to the first direction, and one or more bent portions, each having a tubular shape, extending between two adjacent end portions of the main body portions, and connecting the main body portions in series, and a reinforcing layer covering outer peripheral walls of the main body portions and outer peripheral walls of the one or more bent portions, and including carbon fiber. A content of the carbon fiber per unit length in an extension direction of the reinforcing layer in the bent portion is less than a content of the carbon fiber per unit length in an extension direction of the reinforcing layer in the main body portion.

An organic composite gas storage tank 100 comprises a hollow central portion 106 which is substantially cylindrical and formed integrally with first and second end portions 102, 104, and which defines a longitudinal tank axis 101. The first end portion 102 comprises a hollow truncated conical region 102A which meets the hollow central portion at a first end thereof, and a cylindrical region 102B which meets an end of the hollow truncated conical portion remote from the hollow central portion. An organic fibre winding 107 extends at least between axial positions which coincide with the hollow truncated conical region of the first end portion and the hollow central portion respectively. A hollow metal end-fitting 120 has a hollow truncated conical portion 124 embedded within the wall of the hollow truncated conical region of the first end portion, providing a long leakage path around the metal end-fitting.