A wrinkle mitigation system may include at least one tooling rod disposed against a tool surface at a location on the tool where a composite ply is configured to overlap the tooling rod. The tooling rod may have an elongated shape and may be generally oriented along a direction of wrinkle formation in the composite ply. The tooling rod may have a rod width that results in the composite ply assuming a corrugated shape when compaction pressure is applied to the composite ply.

A wrinkle mitigation system may include at least one tooling rod disposed against a tool surface at a location on the tool where a composite ply is configured to overlap the tooling rod. The tooling rod may have an elongated shape and may be generally oriented along a direction of wrinkle formation in the composite ply. The tooling rod may have a rod width that results in the composite ply assuming a corrugated shape when compaction pressure is applied to the composite ply.

A first laminated body is worked to form a second laminated body, the first laminated body being formed by laminating prepregs including reinforcing fibers and resin, the second laminated body including a flat portion and a wavy portion, the flat portion being located at at least one of side edge portions of the second laminated body, the wavy portion being located at a portion adjacent to the side edge portion and extending along a longitudinal direction. An intermediate product is formed from the second laminated body by a forming die such that the flat portion becomes a bent portion that is an inside portion whose circumferential length is shorter in a curved portion, and the wavy portion becomes a bent portion that is an outside portion whose circumferential length is longer in the curved portion.

A method for manufacturing a fiber layer or a component perform includes yieldably tensioning a plurality of yarns in a tensioning plane such that each yarn is separately and individually held in a yieldable manner. Then, a workpiece carrier is moved through the tensioning plane in a perpendicular direction thereto such that the yarns contact the workpiece carrier and respectively bend according to the contour of the workpiece carrier. If a predetermined tensile force on one or more of the plurality of yarns is exceeded, then an additional length of such yarn(s) is supplied from a reserve and/or a coil to cover the workpiece carrier. Then, the ends of the yarns are fixed along an edge of the workpiece carrier.

A method for manufacturing a fiber layer or a component perform includes yieldably tensioning a plurality of yarns in a tensioning plane such that each yarn is separately and individually held in a yieldable manner. Then, a workpiece carrier is moved through the tensioning plane in a perpendicular direction thereto such that the yarns contact the workpiece carrier and respectively bend according to the contour of the workpiece carrier. If a predetermined tensile force on one or more of the plurality of yarns is exceeded, then an additional length of such yarn(s) is supplied from a reserve and/or a coil to cover the workpiece carrier. Then, the ends of the yarns are fixed along an edge of the workpiece carrier.

Forming systems and methods for forming an elongate charge of composite material are disclosed herein. The forming systems include an elongate forming tool having an elongate forming surface with a forming surface shape that corresponds to a predetermined material shape for the elongate charge of composite material. The forming systems also include an elongate end effector, which is configured to tension the elongate charge of composite material across the forming surface. The elongate end effector includes an elongate vacuum distribution manifold, a porous elongate vacuum region, and an elongate friction surface. The methods include methods of tensioning an elongate charge of composite material across an elongate forming surface of an elongate forming tool utilizing an elongate end effector.

A device for producing a curved fiber preform from a bi- or multidirectional fiber semi-finished product, in particular for an aircraft or spacecraft fuselage component has first lamellae and second lamellae formed to be couplable to one another criss-cross such that they are positioned on a shared plane and thus form a grid. The lamellae at least in part are formed resiliently bendable about an axis intersecting the shared plane such that a local orientation of the lamellae in the grid changes. An adhesion device or structure is formed for temporarily adhering the fiber semi-finished product and is configured such that the local fiber orientation of the fiber semi-finished product also changes accordingly when the lamellae bend.

A device for producing a curved fiber preform from a bi- or multidirectional fiber semi-finished product, in particular for an aircraft or spacecraft fuselage component has first lamellae and second lamellae formed to be couplable to one another criss-cross such that they are positioned on a shared plane and thus form a grid. The lamellae at least in part are formed resiliently bendable about an axis intersecting the shared plane such that a local orientation of the lamellae in the grid changes. An adhesion device or structure is formed for temporarily adhering the fiber semi-finished product and is configured such that the local fiber orientation of the fiber semi-finished product also changes accordingly when the lamellae bend.

The present invention relates to production method of a composite material wherein the composite material is tensioned and cured to produce a composite material with a single cord or cord fabric reinforced with another component, comprising the steps of adhering at least two layers of compound material, attaching the adhered compound materials inside a hollow frame, placing said frame into a pre-tensioning device, wrapping the cords around the frame with the desired pre-tension, removing the frame together with the compound material and the cords from the pre-tensioning device, placing at least one layer of compound material on the curing tray, placing the coated frame removed from the pre-tensioning device onto the compound material layers, placing at least one more layer of compound material on the coated frame, closing the lid over the curing tray, curing the material and cutting the composite material into strips.

The present invention relates to production method of a composite material wherein the composite material is tensioned and cured to produce a composite material with a single cord or cord fabric reinforced with another component, comprising the steps of adhering at least two layers of compound material, attaching the adhered compound materials inside a hollow frame, placing said frame into a pre-tensioning device, wrapping the cords around the frame with the desired pre-tension, removing the frame together with the compound material and the cords from the pre-tensioning device, placing at least one layer of compound material on the curing tray, placing the coated frame removed from the pre-tensioning device onto the compound material layers, placing at least one more layer of compound material on the coated frame, closing the lid over the curing tray, curing the material and cutting the composite material into strips.