A method for manufacturing a high pressure tank includes a step of forming a reinforcing pipe portion including a straight pipe portion and reduced-diameter portions, a step of forming reinforcing dome portions, a step of forming a joined body by joining the reinforcing pipe portion and the reinforcing dome portions, and a step of forming an outer helical layer on an outer face of the joined body. The reinforcing dome portions are disposed with opening ends of the reinforcing dome portions positioned on outer faces of the reduced-diameter portions of the reinforcing pipe portion.

A method for manufacturing a high pressure tank includes a step of forming a reinforcing pipe portion including a straight pipe portion and reduced-diameter portions, a step of forming reinforcing dome portions, a step of forming a joined body by joining the reinforcing pipe portion and the reinforcing dome portions, and a step of forming an outer helical layer on an outer face of the joined body. The reinforcing dome portions are disposed with opening ends of the reinforcing dome portions positioned on outer faces of the reduced-diameter portions of the reinforcing pipe portion.

Provided are a method for manufacturing a structural body and a structural body, the structural body formed of FRP and having a high degree of freedom in cross-sectional shape even at a low cost. The method for manufacturing a structural body includes a winding step of forming a cylindrical laminate body LM by winding a plurality of composite materials including reinforcing fibers and an uncured thermosetting resin around a hollow cylindrical core member CY; a compressing step of winding a tape or film around an outer circumference of the laminate body LM and compressing the same; a preheating step of heating the laminate body LM until a state prior to complete curing of the thermosetting resin; and a main heating step of arranging the laminate body LM around which the tape or film is wound and the cylindrical core member in a molding die and pressing the same to thereby heat the laminate body LM until the thermosetting resin is completely cured while deforming the cylindrical core member CY to a non-circular cross-sectional shape. Thereby, a structural body in which the cylindrical core member CY and the laminate body LM are integrated can be formed.

A system and method for forming a strut. A strut comprises a laminated composite tube having a substantially hollow interior and a pair of longitudinal stiffeners attached to opposite sides of the laminated composite tube.

A manufacturing method for a tank is a method of manufacturing the tank by winding fibers impregnated with an epoxy resin in a plurality of layers around an outer circumference of a liner having a body part and dome parts provided at both ends of the body part. The manufacturing method includes sequentially laminating a plurality of hoop layers by hoop-winding the fibers from a side closer to an outer circumference of the body part toward a side farther from the outer circumference of the body part. When laminating the hoop layers, a temperature of end portions of the body part adjacent to the dome parts is set lower than a temperature of a remaining portion of the body part, the remaining portion being a portion of the body part other than the end portions.

A method for manufacturing a fiber reinforced structure includes the following. A mandrel of a first material comprises a hollow interior and an aperture that allows a fluid to enter the interior. A layer of a second material provided on the mandrel includes an uncured resin and fibers. The mandrel and the layer are placed in a mold cavity formed by a mold. A pressurized fluid is introduced into the interior of the mandrel via the aperture to generate a force acting to expand the mandrel outward. The mandrel is heated so that it becomes deformable and expand outward to press the layer against the mold. The layer is heated so that it cures. The mandrel is then heated to a temperature above its melting point of the first material so that it melts, after which it is removed.

A mandrel structure for use in manufacturing a fiber reinforced resin vessel by a filament winding process, includes: a shaft having a pair of axial ends configured to be supported by a drive unit; a mandrel having the shaft passed therethrough; and a pair of fittings having the shaft passed therethrough and projecting axially from respective axial ends of the mandrel. The mandrel is formed as a hollow shell made of a water-soluble material, and includes a pair of shaft holes receiving the shaft therein, and a receiving recess formed in a part of the mandrel surrounding each shaft hole and configured to engage the corresponding fitting in a rotationally fast manner.

A manufacturing method for a high-pressure tank is a manufacturing method for a high-pressure tank including a reinforced layer formed such that an electrically conductive fiber bundle impregnated with thermosetting resin is wound around a liner. The manufacturing method includes: a step of preparing the tank in which the uncured reinforced layer is formed on the liner; a first heating step of heating the uncured reinforced layer by low-frequency induction heating so the thermosetting resin is softened; and a second heating step of, after the first heating step, heating the softened reinforced layer by high-frequency induction heating so that the softened reinforced layer is hardened.

Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.

A tank including a liner; a reinforcing layer formed of fiber reinforced resin that is arranged on the liner; a label arranged on the reinforcing layer; and a surface layer formed of glass fiber reinforced resin that is arranged to cover the label. The reinforcing layer includes an inner layer, and an outer layer having a cover rate smaller than the inner layer and smaller than 100%, the cover rate being a percentage of a volume occupied by the fiber reinforced resin in space of the reinforcing layer, and the outer layer being arranged on the inner layer, and at least a part of the label is embedded in the reinforcing layer.