A method manufactures a thermoplastic fiber-reinforced resin molded article by pressing one thermoplastic fiber-reinforced resin prepreg, a plurality of laminated prepregs, or a plurality of prepregs. The method includes: a step in which the temperatures of an upper die and a lower die are set to 170-270° C.; a step in which the prepreg is placed between the upper die and the lower die; a step in which a load is applied to the prepreg so as to deform the prepreg; a step in which the temperatures of the upper die and the lower die are lowered at a speed of 5 to 50° C. per minute; and a step in which, after the upper die and the lower die are sufficiently cooled, the upper die is raised and a thermoplastic fiber-reinforced resin molded article is extracted.

A system includes a mandrel contoured to define a tapering tubular shape of a workpiece cured on the mandrel and a demolding tool. The demolding tool is configured to remove the workpiece from the mandrel after the workpiece is cured on the mandrel and cut longitudinally. The demolding tool is configured to remove the workpiece from the mandrel by deforming a first end of the workpiece to at least partially disengage the first end of the workpiece from a first end of the mandrel, and subsequently, deforming a second end of the workpiece to at least partially disengage the second end of the workpiece from a second end of the mandrel. The first end of the workpiece may have a first cross-sectional area that is smaller than a second cross-sectional area of the second end of the workpiece.

There is disclosed a tool for manufacturing a composite component, the tool comprising: a skin composed of fibre reinforced plastic and defining a layup surface for the composite component, the skin having a plurality of passageways extending from the layup surface to an opposing surface of the skin; a backing secured to the skin, the backing and the skin defining a cavity therebetween; a support core disposed within the cavity and comprising a gas-permeable material in fluid communication with the passageways; and a conduit extending through the backing such that the conduit is in fluid communication with the gas-permeable material.

There is disclosed a tool for manufacturing a composite component, the tool comprising: a skin composed of fibre reinforced plastic and defining a layup surface for the composite component, the skin having a plurality of passageways extending from the layup surface to an opposing surface of the skin; a backing secured to the skin, the backing and the skin defining a cavity therebetween; a support core disposed within the cavity and comprising a gas-permeable material in fluid communication with the passageways; and a conduit extending through the backing such that the conduit is in fluid communication with the gas-permeable material.

A method of manufacturing a composite structure, e.g. wind turbine blade, using reusable and removable perimeter plates to establish air flow channels in conjunction with a vacuum bag and mold. An exemplary setting is the perimeter of large wind blade shells where a perimeter vacuum is used to retain the part in the mold for the bonding process. The reusable plates disclosed herein create air channels whether the vacuum is introduced to the perimeter of the mold: i) through the flange in different locations; or ii) with the use of vacuum lines into the perimeter bag; or iii) built in vacuum channels in the flange of the mold.

A method of manufacturing a composite structure, e.g. wind turbine blade, using reusable and removable perimeter plates to establish air flow channels in conjunction with a vacuum bag and mold. An exemplary setting is the perimeter of large wind blade shells where a perimeter vacuum is used to retain the part in the mold for the bonding process. The reusable plates disclosed herein create air channels whether the vacuum is introduced to the perimeter of the mold: i) through the flange in different locations; or ii) with the use of vacuum lines into the perimeter bag; or iii) built in vacuum channels in the flange of the mold.

Methods, systems, and apparatuses are disclosed for the manufacture of composite components having incorporated reinforcing structures machined into composite material substrates, and composite components manufactured according to disclosed methods, and assemblies and larger structures comprising the composite material components.

An automated fiber bundle placement apparatus is configured to lay a strip-like fiber bundle impregnated with a thermoplastic resin on a stacking surface on an upper side of a placement die by moving a placement head and by emitting a laser from an emitting device to deposit the fiber bundle on the stacking surface incompletely. The emitting device is configured to emit the laser toward the fiber bundle laid on the stacking surface to its surface that is a reverse side of its surface facing the stacking surface.

A method apparatus, and system method for manufacturing a composite part. A set of composite preforms is placed on a set of slip sheets. The set of slip sheets with the set of composite preforms is attached to a cure mandrel to form a composite preform assembly.

A method, apparatus, system, and computer program product for fabricating a composite part. Composite materials are laid up on a mandrel. A caul is placed over the composite materials laid up on the mandrel. An inner mold line of the caul is sized to an outer surface of the composite materials in a cured state. The composite materials laid up on the mandrel with the caul over the composite materials is cured to form the composite part. The composite materials expand to the inner mold line of the caul during curing of the composite materials to form the composite part.