A composite charge is formed between two compression dies into a composite laminate stiffener. The stiffener is contoured along its length by contouring the dies. Wrinkle diffusers attached to, or embedded or incorporated into the tool surfaces of the dies, diffuse wrinkles formed on the inside radius of the stiffener during the contouring.

A method, apparatus, and system for applying a vacuum-based pressure on an uncured composite structure. Membranes are bonded to a boundary of a caul. The membranes include positive features that define vacuum channels. The membranes are spliced to each other. The positive features that define the vacuum channels in the membranes are aligned to each other during splicing of the membranes. The membranes spliced to each other and bonded to the caul to form an integrated caul. The integrated caul applies a pressure on the uncured composite structure during operation of the integrated caul.

There is provided a laminated composite structure having improved impact damage resistance and improved strength. The laminated composite structure has a plurality of stacked layers of a composite material. The plurality of stacked layers have one or more interlaminar corrugations formed within the plurality of stacked layers. Each interlaminar corrugation has a substantially sinusoidal shaped profile, and has a depth and a length dependent on a size of the laminated composite structure formed. The laminated composite structure with the one or more interlaminar corrugations has improved strength and improved impact damage resistance at an exposed edge of the laminated composite structure, when the exposed edge is subjected to an impact force.

Systems and methods for assembling elongate composite structures are disclosed. The systems include a first rigid elongate cure tool defining a first elongate support surface for supporting a first elongate charge of composite material (FEC), a second rigid elongate cure tool defining a second elongate support surface for supporting a second elongate charge of composite material (SEC), and a flexible elongate caul plate. The systems further include a vacuum compaction film, a translation structure, and a vacuum source. Methods according to the present disclosure include positioning a vacuum compaction film, positioning a flexible elongate caul plate, and positioning an FEC. The methods further include positioning an SEC, contacting a region of the FEC with a region of the SEC, sealing the vacuum compaction film, evacuating the enclosed volume to generate an elongate composite assembly, and heating the elongate composite assembly to define the elongate composite structure.

A method of manufacturing a cured composite structure includes placing a radius filler element into a radius cavity extending along a length of a composite base member formed of dry fiber material comprised of reinforcing fibers. The radius filler element is formed of a radius filler material. The method also includes infusing resin into the dry fiber material, and chemically reacting the resin with the radius filler material to create a mixture of resin and radius filler material along side surface interfaces between the radius filler element and the composite base member. The method additionally includes curing or solidifying the resin, and allowing solvent in the resin to evaporate causing hardening of the mixture and bonding of the radius filler element to the composite base member, and resulting in a cured composite structure.

The present invention provides a tool 1 for curing a composite component, the tool comprising a lay-up surface 8 for laying-up layers of an uncured composite component, a cover assembly 9 for moving in relation to the lay-up surface to cover a layed-up uncured composite component on the lay-up surface, the cover assembly comprising a sealable cover for sealing around the uncured composite component on the lay-up surface to form a sealed zone, and a vacuum port 25 for providing a vacuum to the sealed zone, wherein the tool further comprises at least one heating element 15, 53 within the sealed zone for heating the uncured composite component. The invention also provides a method of manufacturing a composite component and a composite component. The composite component may form at least part of a piece of aircraft furniture, such as an aircraft seat shell.

A method and apparatus for forming a composite structure. A stackup comprising a plurality of overbraided thermoplastic members and an overbraided thermoplastic skin is built. The stackup is placed between an inner tooling and an outer tooling. The inner tooling, the stackup, and the outer tooling are held in place together using a load constraint. The inner tooling, the stackup, the outer tooling, and the load constraint form a consolidation setup. The consolidation setup is heated to form the composite structure.

An intensifier mechanism for forming stacked material includes a support, a first body coupled to the support, and a second body having a main portion, a pivoting portion, and a joint. The main portion is coupled to the support and the joint movably couples the main portion to the pivoting portion. The joint allows the pivoting portion to pivot in relation to the main portion when the membrane moves towards the bottom wall.

A method for fusing thermoplastic composite structures includes placing a thermoplastic substructure on an inner surface of a skin that is laid up on a shaping surface of a tool configured to maintain the shape of an outer mold line. The method further includes applying at least one metal layer over the substructure and applying an insulation layer over edge portions of the substructure and over exposed portions of the inner surface of the skin not in contact with the substructure and applying a vacuum bag that at least partly encloses the skin, the substructure, and the metal layer. The method yet still further includes applying heat to the shaping surface to fuse the substructure to the skin such that the skin exceeds its melting point and at least a portion of a raised segment of the substructure does not exceed its melting point.

A device for manufacturing a composite component including a tool with a first and second sections forming first and second confinement surfaces, the sections movable relative to each other into and out of a fastening configuration. The device includes a closing mechanism with a closing section. In the fastening configuration, the first confinement surface and the second confinement surface face one another, and the sections and the closing mechanism are arranged such that a cavity is formed between the sections and the closing mechanism. The closing section is transferable from an open configuration into a closed configuration. In the closed configuration, the third confinement surface extends along a plane perpendicular to the first and second confinement surfaces, wherein, when the closing mechanism is heated from a first temperature to a second temperature, the closing section transfers from the open configuration into the closed configuration at a predefined temperature.