Methods and apparatus for securing an autoclave bag to a composite fixture are disclosed. An example apparatus includes a flange sealing device including a forward flange at a first end and an aft flange at a second end, and a composite fixture including a forward groove to locate and seal with the forward flange of the flange sealing device to affix an autoclave bag, an aft groove to locate and seal with the aft flange of the flange sealing device to affix the autoclave bag, and an aft locating ring to position the autoclave bag.

A rotating manifold includes an axle, a hub rotatable relative to the axle about an axis of rotation, and a compressed air line in fluid communication housed in the axle. The rotating manifold further includes a vacuum line in fluid communication with the hub. The rotating manifold further includes a plurality of conduits connected to the hub. Each conduit of the plurality of conduits is in fluid communication with the vacuum line and houses a compressed air line arm in fluid communication with the compressed air line.

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.

A two-part bag seal and a method for sealing a vacuum bag to a mold for a molding process. The two-part bag seal includes an elongate first seal part having a cross-sectional portion enclosing an open channel therein, and an angled cross-sectional portion having an open receptacle channel therein, and an elongate second seal part having a flexible wing portion and a flexible prong distal from the flexible wing portion, wherein the flexible prong is engageable with the open receptacle channel of the elongate first seal part.

A method of moulding includes positioning a fibre between a hard mould face and flexible contra mould face, sealing the space between the two mould faces, deforming the flexible contra mould face to produce a channel, introducing a thermosetting resin into the space between the two mould faces, and returning the flexible contra mould face to its undeformed condition before the onset of resin gel.

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.

The present invention relates to a method for manufacturing a solar cell panel by means of an autoclave, the method comprising the steps of: (a) positioning at least one solar cell module on a mold having a release material layer; (b) laminating a prepreg on the mold by a predetermined thickness so as to cover the solar cell module; (c) covering a laminated structure of the solar cell module and prepreg with a bagging film and encapsulating the inner space of the bagging film from the outside; and (d) making the inner space of the bagging film into a vacuum state, and then inputting the mold into a chamber of an autoclave and pressing and hardening the prepreg by applying heat and pressure, wherein, in step (b), a mounting space for forming a solar cell panel is provided on the mold, and the prepreg is laminated while the solar cell module is insertedly positioned in a fixing groove formed on a mounting surface of the mounting space.

A drape forming apparatus includes a forming tool having a first forming surface and a second forming surface nonplanar with the first forming surface. A tray is spaced apart from the forming tool and is configured to pivot about a hinged end from a first position to a second position under an applied force such that a distal end moves away from the forming tool. A first side of the tray faces a first heat source when the tray is in the first position, and a second heat source is disposed at a second side of the tray. A device for use in forming the composite structure includes a standoff and the tray, and a heat source is secured to the second side of the tray. A method of forming a composite structure includes heating both sides of the composite material with the first and second heat sources.

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 co-consolidation tool, including a heating assembly to receive one or more thermoplastic parts and to apply a consolidation temperature to the one or more thermoplastic parts, a pressure bladder to apply a consolidation pressure to the one or more thermoplastic parts, and a support insert shaped and configured to support and at least partially surround at least one of the one or more thermoplastic parts, wherein at least one of heating assembly and the pressure bladder is shaped to receive and support the support insert.