A method for manufacturing an overhead storage compartment for an aircraft cabin, including providing a shell part extending between a first end and a second end, wherein the shell part has a first edge at the first end and a second edge at the second end. A first end wall and a second end wall are provided. The shell part and the first and second end walls are assembled, wherein the first edge is attached to the first end wall and the second edge is attached to the second end wall, such that the shell part, the first end wall and the second end wall together surround an interior space. An object, to provide a simple and fast method for manufacturing an overhead storage compartment, wherein possibly little handwork is required, is achieved in that the first end wall and/or the second end wall include an undirected long fiber reinforced plastic material.

A press for pressing a component, such as a thermoplastic consolidation and/or forming press, has a first fixed part as a first pressing tool, a movable part as a second pressing tool for pressing a component together with the first pressing tool, and a second fixed part for applying a pressing force to the movable part, wherein the second fixed part and the movable part apply the pressing force generated via interaction between a magnetic field of a pressing magnet and a superconductor cooled below its step temperature.

A press for pressing a component, such as a thermoplastic consolidation and/or forming press, has a first fixed part as a first pressing tool, a movable part as a second pressing tool for pressing a component together with the first pressing tool, and a second fixed part for applying a pressing force to the movable part, wherein the second fixed part and the movable part apply the pressing force generated via interaction between a magnetic field of a pressing magnet and a superconductor cooled below its step temperature.

A composite material structure forming method capable of improving the shape and dimensional accuracy inside a composite material structure. The method includes: winding a prepreg (2) around an inner jig (6); stacking a ply (8) on the prepreg (2) wound around the inner jig (6); and forming a composite material structure by providing composite outer plates (4a, 4b) on an outer periphery of the inner jig (6) on which the ply (8) is stacked and mounting divided outer jigs (9) thereon.

A composite material containing reinforcing fibers A and a matrix resin, the reinforcing fibers A being discontinuous fibers having a fiber length of at least 5 mm and containing reinforcing fibers A1 having a bundle width of less than 0.3 mm and a reinforcing fiber bundle A2 having a fiber width of 0.3-3.0 mm, inclusive, wherein the coefficient of variation CVi.sub.A2 of Vfi.sub.A2 is 35% or less in at least a minimum bundle width zone (i=1) and a maximum bundle width zone (i=n) when the reinforcing fiber bundle A2 is divided into a pre-set plurality of bundle width zones (total number of bundle width zones n≥3) and the volume ratio of the reinforcing fiber bundle A2 in each bundle width zone is Vfi.sub.A2. Also, a method for producing a molded article which uses the composite material.

A composite sandwich panel comprises a first composite skin, a second composite skin, a hollow cell core between the first composite skin and the second composite skin, and a first over-crush edge region with a first edge. The first edge has a first thickness at least 40% less than a nominal thickness of the composite sandwich panel. The first over-crush edge region has a length of at least 0.25 inches over which a thickness of the composite sandwich panel decreases.

A composite sandwich panel comprises a first composite skin, a second composite skin, a hollow cell core between the first composite skin and the second composite skin, and a first over-crush edge region with a first edge. The first edge has a first thickness at least 40% less than a nominal thickness of the composite sandwich panel. The first over-crush edge region has a length of at least 0.25 inches over which a thickness of the composite sandwich panel decreases.

A method for manufacturing a fiber-reinforced resin tube body includes: a preparing step of preparing a cylindrical expandable body having fiber wound therearound; an installing step of installing the expandable body in a mold after the preparing step; a flowing step of flowing resin into the mold, in which the expandable body is placed, after the installing step; and an expanding step of expanding the expandable body toward an inner wall of the mold after the flowing step.

A device for manufacturing a stiffened panel with reinforcements which each have a final thickness and a final height. The manufacturing device includes tools configured to each support a preform of fibers having a U-shaped or C-shaped cross section with a base and two wings. Each tool comprises, at at least one of its first and second lateral faces, a set-back portion which, when two tools are juxtaposed, delimits a recess configured to form a reinforcement during a consolidation or polymerization step. The tools are dimensioned such that each recess has a width, at the consolidation or polymerization temperature, that is substantially equal to the thickness of the reinforcements. This solution makes it possible to more effectively control the geometry of the stiffened panel by avoiding the formation of beads. A method for manufacturing a stiffened panel using the device is also disclosed.

A device for manufacturing a stiffened panel with reinforcements which each have a final thickness and a final height. The manufacturing device includes tools configured to each support a preform of fibers having a U-shaped or C-shaped cross section with a base and two wings. Each tool comprises, at at least one of its first and second lateral faces, a set-back portion which, when two tools are juxtaposed, delimits a recess configured to form a reinforcement during a consolidation or polymerization step. The tools are dimensioned such that each recess has a width, at the consolidation or polymerization temperature, that is substantially equal to the thickness of the reinforcements. This solution makes it possible to more effectively control the geometry of the stiffened panel by avoiding the formation of beads. A method for manufacturing a stiffened panel using the device is also disclosed.