A system and method for fabricating large composite fuselages or other vehicle structures, in which the composite structure is fabricated and cured as on a tool, segmented and removed from the tool without disassembling the tool, and then reassembled off the tool to reform the large structure. The tool includes mandrel segments attached to a substructure. The attachments may be moveable to accommodate differential expansion and contraction during curing, and the tool may be rotatable to facilitate access. A composite material of resin and synthetic fibers is applied over the mandrel segments to fabricate the structure on the tool. Caul plates are secured over the composite material, and the composite material is cured on the tool. The resulting structure is cut into part segments which are then removed from the tool, and the part segments are joined to reassemble the large composite structure off the tool.

A precast concrete panel and method for forming the panel are disclosed. A method of forming the panel to be used as a floor, wall, or roof structure includes positioning one or more forming members within a casting bed having a plurality of upright surfaces defining a generally rectangular interior area, the one or more forming members comprising an insulating material extending along a length dimension of the one or more forming members to define a plurality of rectangular-shaped channels in a parallel and spaced-apart relationship, placing uncured concrete within the casting bed and allowing the concrete to cover the one or more forming members and substantially fill the channels, and allowing the concrete to cure.

A method for forming a fiber-reinforced thermoplastic control surface may comprise: stacking plies of thermoplastic composite sheets to a first desired thickness to form a first skin; stacking plies of thermoplastic composite sheets to a second desired thickness to form a second skin; forming the first skin in a first contour; forming the second skin in a second contour; forming a stiffening member including a thermoplastic resin, the stiffening member including a shape having a plurality of peaks and troughs; assembling the stiffening member between the first skin and the second skin; and joining the stiffening member to the first skin and the second skin.

A prefabricated wall panel has a precast body including at least one decorative design element. In addition, the wall panel includes a mounting element having a first end embedded in the precast body and a second end projecting from the precast body. A groove is formed between the precast body and the second end of the mounting element along a first edge of the precast body. A tongue is formed along a second edge of the precast body opposite the first edge. The tongue and groove cooperate to allow prefabricated wall panels to be more easily installed on a support substrate.

A fan track liner for a fan containment arrangement for a gas turbine engine comprises a cellular impact structure and a supporting sub-laminate integrally formed with each other from a fibre-reinforced polymer material.

A reinforcing structure for a wind turbine blade A reinforcing structure for a wind turbine blade (12) is described. The reinforcing structure comprises one or more pultruded strips (42C) having spanwise grooves (54). The grooves (54) impart transverse flexibility to the strips (42C), allowing the strips (42C) to conform to the curvature of a wind turbine blade mould (44). An associated method of making a reinforcing structure for a wind turbine blade (12) is described. The method comprises providing an elongate mould (44) extending in a longitudinal direction and defining a mould surface at least part of which is concave-curved in transverse cross section. One or more pultruded strips (42C) with spanwise grooves (54) are arranged in the mould (44) to form the reinforcing structure. The pultruded strip(s) are bent along the grooves (54) so that they substantially conform to the transverse curvature of the mould surface. In preferred embodiments the reinforcing structure is a spar cap (36).

Disclosed are a vacuum insulation panel application device and method. The device comprises a conveying platform for conveying a refrigerator housing, a foaming material spray gun head, a vacuum insulation panel taking and placing mechanism and a press-fitting mechanism for pasting a vacuum insulation panel onto the refrigerator housing, wherein the foaming material spray gun head, the vacuum insulation panel taking and placing mechanism and the press-fitting mechanism are sequentially arranged in the moving direction of the conveying platform; the spray gun head is fixedly arranged beside the conveying platform; and the press-fitting mechanism is provided with rollers for rolling the vacuum insulation panel.

A fluid ejection device may include a fluid ejection die including nozzles and fluid feed holes. Each nozzle may have a nozzle orifice formed in a top surface of the fluid ejection die. The fluid feed holes may be formed in a bottom surface of the fluid ejection die and fluidly connected to the nozzles. The fluid ejection device may include a molded panel into which the fluid ejection die is at least partially embedded, the molded panel having a fluid slot formed therethrough such that the fluid slot is fluidly connected to the fluid feed holes of the fluid ejection die, the molded panel formed with a mold chase and a release liner coupled to and at least partially covering an interior surface of the mold chase, the mold chase having a fluid slot feature corresponding to the fluid slot.

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. The radius filler element is formed of a permeable material. The method also includes absorbing resin from the composite base member into the permeable material of the radius filler element. The method additionally includes curing or solidifying the resin in the radius filler element and in the composite base member to form a cured composite structure in which the resin bonds the radius filler element to the composite base member.

A system and method for thermoplastic composite processing including compressing and heating a thermoplastic composite panel having a plurality of terminal edges. The method further includes heating the thermoplastic composite panel to a melting temperature to create a melt front of the thermoplastic composite panel at a first location and heating the thermoplastic composite panel to the melting temperature in a pre-determined pattern from the first location toward the terminal edges of the thermoplastic composite panel. Extending the melt front toward the terminal edges in this way causes air constrained within the thermoplastic composite panel to escape the thermoplastic composite panel through unmelted portions of the thermoplastic composite panel located between the melt front and the terminal edges. Cooling of the panel may be similarly conducted, cooling a first region and then gradually continuing to cool the panel in a direction toward one or more of the terminal edges.