In the manufacturing method of the present invention, as preparation for providing a mold 30 with protrusions 31 and 32 to be printed on an FRP material of a skin 1 in co-bold molding, which requires resetting of the skin 1 to the mold 30, a long protrusion 32A and a short protrusion 32B are interchangeable as one protrusion 32. The long protrusion 32A is printed to form a second recessed part 12 in the skin 1, and before the skin 1 is reset, the long protrusion 32A is replaced with the short protrusion 32B. In this way, as the short protrusion 32B is housed in the second recessed part 12 formed during elongation of the mold 30, the skin 1 can be reset in the state of being positioned relative to the mold 30 by the first protrusion 31 and the short protrusion 32B.

Systems and methods are provided for placing preforms onto a mandrel. One illustrative method includes moving a mandrel in a process direction relative to a station(s) that comprises multiple pick-and-place machine(s), identifying a tray that stores a preform comprising an unhardened fiber-reinforced material, placing the strong back at the preform via at least one of the pick-and-place machine(s), applying a vacuum to hold the preform in contact with the strong back, transporting the preform to a mandrel via the pick-and-place machine(s), and placing the preform onto the mandrel.

An efficient method for manufacturing a partially cured composite component intended to be joined with other component or components to form a composite structure and a manufacturing method of the composite structure. The partial curing of a composite layup is achieved using a mold comprising heat conductive elements and insulating elements and applying heat and pressure over the mold. The heat conductive elements are used to transmit or dissipate heat to/from the composite layup. The insulating elements are used to prevent the transmission or dissipation of heat to/from the composite layup.

A method for assembling a stiffened composite structure includes a step of positioning a plurality of dry fibers along a first side of a pre-preg composite laminate skin element wherein the pre-preg composite laminate skin element is dimensionally changeable. The method further includes a step of positioning an interlayer between the plurality of dry fibers and the first side of the pre-preg composite laminate skin element and a step of infusing the plurality of dry fibers with a resin forming a plurality of infused fibers. The method also includes a step of co-curing the pre-preg composite laminate skin element and the plurality of infused fibers.

A composite stiffener for a stiffener reinforced panel is disclosed. The stiffener has a longitudinal direction and a run-out region which terminates at an end of the stiffener. The stiffener also has a constant section region inboard of the run-out region in the longitudinal direction and having a constant cross section transverse to the longitudinal direction with a crown between adjacent foot portions. The run-out region has a changing cross section transverse to the longitudinal direction with a crown between adjacent foot portions and the crown reduces in height towards the end of the stiffener forming a ramp. The composite stiffener includes a number of blankets of non-crimp fabric layers.

A composite skin and composite stiffeners are co-cured in an autoclave. Uncured stiffeners are placed in channels of a tool, and an uncured skin is placed on the tool contacting the stiffeners. The vacuum bag is sealed over the tool. Bladders placed in the stiffeners are exposed to autoclave pressure through a manifold system employing vent tubes that pass through the vacuum bag along a side of the tool.

Embodiments of the present disclosure provide systems and methods for producing a moulded component, for example a component for an automobile, having at least two unidirectional fibre portions. The unidirectional fibre portions are joined together at nodal points in a first step to produce a network of unidirectional fibres with over-moulded nodal points. The network of unidirectional fibres with over-moulded nodal points is then placed in a large mould tool along with a second moulding material. The large mould tool is then closed to produce a part that comprises the network of unidirectional fibres embedded within the second moulding material.

A jig includes mold parts that have a contact surface of a cylindrical part of a material to be molded having a shape complying with the inner peripheral surface of the cylindrical par and are arranged in a direction crossing one direction; a bladder having on a side opposite to the contact surfaces of plurality of mold parts relative to the mold parts, capable of accommodating a fluid therein, and expandable/retractable according to a pressure of the accommodated fluid; a joining part that joins the plurality of mold parts and the bladder; and a connection part that connects a one-side mold part and an another side mold part adjacent to the one-side mold part among a plurality of mold parts to each other and restricts an interval between the one-side mold part and the other-side mold part in a direction crossing the one direction with a prescribed range.

A trailing edge for a composite multispar integrated lifting surface includes a first C-shape composite form that includes a web and two flanges. The web forming a portion of the rear spar of a torsion box. The two flanges extending along a skin chordwise direction. A second C-shape composite form includes a web and two flanges. The web forms an auxiliary spar. The flanges extend along the skin chordwise direction. The first C-shape composite form and the second C-shape composite form forming a first auxiliary cell and a second cell. The first auxiliary cell is delimited by the first C-shape composite form and the second C-shape composite form. The second cell is an open cell delimited by the second C-shape composite form.

A method for manufacturing a stiffened panel made from composite material comprising a skin and elongated reinforcing elements wherein some of the elongated reinforcing elements cross each other. The method comprises the steps of (a) laying up a flat laminate comprising stacked plies of composite layers for forming a structure comprising the elongated reinforcing elements of the panel, (b) cutting the flat laminate along intersection lines of planes defining the webs of two crossing reinforcing elements, (c) cutting in the flat laminate the outline of the elongated reinforcing elements, (d) forming the structure comprising the elongated reinforcing elements of the panel, (e) laying up plies of composite layers for forming the skin, and (f) curing the laid-up plies of the skin and the formed structure comprising the elongated reinforcing elements.