A thermoplastic surfacer for providing lightning strike protection to a composite component of an aircraft, methods of manufacturing the surfacer, and methods of applying the surfacer to a composite part. The thermoplastic surfacer includes a broadgood having an amorphous thermoplastic resin, one or more fillers embedded into the broadgood, and a lightning strike protection mesh or foil embedded into the broadgood. When applying the surfacer to a composite part of an aircraft, the method includes draping the surfacer on an at least partially unconsolidated composite part, consolidating the at least partially unconsolidated composite part by heating the part to a temperature at or above a melt temperature of a resins used in the part and in the surfacer, and filling at least one surface defect in the consolidated part using the amorphous thermoplastic polymer resin and milled fibers provided in the thermoplastic surfacer.

A heating element for resistance welding of thermoplastic components includes an electrically conductive sheet with cut-outs, wherein a ratio of cut-outs to electrically conductive sheet changes at least along a transverse direction of the sheet, so that an electrical resistance of the sheet has a maximum at a center of the sheet. A welding kit includes the heating element and an electrical insulation layer. A method of manufacturing the heating element, and a method of employing the heating element for welding two thermoplastic components to one another are disclosed.

An object of the disclosure is to improve the quality of a molded component after processed. A processing apparatus 10 is the processing apparatus 10 for a composite material 1 in which fibers and a thermoplastic resin are compounded. The processing apparatus 10 includes: a pair of pallets 20 configured to clamp the composite material 1; a heating die 30 configured to press and heat the composite material 1 via the pair of pallets 20; a cooling die 40 configured to press and cool the composite material 1 via the pair of pallets 20; a temperature adjustment unit configured to adjust a temperature of the cooling die 40; and a conveyance device 50 configured to convey the pair of pallets 20 clamping the composite material 1 from the heating die 30 to the cooling die 40.

A thermoplastic welding assembly includes a structural cage that supports a press and one or more hydraulic and pneumatic actuators. The press includes first and second plates that movable toward and away from each other to load and remove thermoplastic components to be held together for thermoplastic welding. Specifically, the first plate of the press includes non-conductive tooling inserts that are positioned to form a slot for a welding prove, and the second plates includes non-conductive tooling inserts that form cavities for plungers to move through. Plungers that are movable using the actuators are positioned in the cavities of the second plate, and compressible pressurizers are attached to the ends of the plungers. An operator uses electrical controls to move the plungers in the plunger cavities toward the thermoplastic components in the press to drive the pressurizers into the thermoplastic components and provide stabilizing pressure on the components during welding.

The invention relates to a method for manufacturing a composite aircraft window frame; the method comprises the steps of: a) positioning in a mold a preform made of pre-impregnated material including dispersed fibers, with a predefined orientation, in a thermosetting resin matrix; b) closing the mold so as to define a gap between at least one surface of said preform and a portion of said mold; c) injecting thermosetting resin into the closed mold through an inlet opening of the mold itself, so as to fill the gap and completely lap said surface of the preform; and d) applying a uniform hydrostatic pressure on the surface by the injection of the resin.

Grommet assembly and method for installing a grommet assembly in a penetration hole of a panel. In one embodiment, a grommet assembly is comprised of multiple parts, including end members having a diameter greater than the penetration hole, and a middle member having a diameter sized to fit within the penetration hole. Each of the members includes one or more conduit holes for a conduit that is routed through the penetration hole, and an installation slit disposed between an outer peripheral surface and a conduit hole.

Forming systems and methods for drape forming a composite charge are disclosed herein. The forming systems include a forming die having a forming surface configured to receive the composite charge and a collapsible support having a support surface. The forming surface has a forming surface edge that extends along a length of the forming surface, and the support surface has a die-proximate support surface edge that extends along the length of the support surface. The forming surface edge and the die-proximate support surface edge define a gap therebetween. A shape of the die-proximate support surface edge corresponds to a shape of the forming surface edge such that a gap width of the gap is at least substantially constant along a length of the gap. The collapsible support is configured to transition from an extended conformation to a collapsed conformation. The methods include methods of utilizing the systems.

A system includes a U-shaped chute, one or more feeder mechanisms, a sock application assembly, and a film application assembly. The chute has a chute inlet and a chute outlet and is configured to receive a mandrel having a mandrel length. The one or more feeder mechanisms are configured to move the mandrel into the chute inlet and through the chute. The sock application assembly has a sock material spool containing a breather sock in tubular form. The sock application assembly is configured to progressively apply the breather sock over the mandrel length as the mandrel exits the chute outlet. The film application assembly has a film material spool containing a film in tubular form. The film application assembly is configured to progressively apply the film over the breather sock covering the mandrel exiting the sock application assembly to thereby form a film-sock-mandrel assembly.

A joined article includes a first component having a laser-treated surface portion and a second component having a laser-treated surface portion. An adhesive joins the first component to the second component at the treated surface portion. A method of making a joined article form components and a system for making joined articles are also disclosed.

A method of fabricating a gas turbine casing out of composite material of varying thickness, the method including making a strip-shaped fiber texture by three-dimensional weaving; winding the fiber texture as a plurality of superposed layers onto a mandrel of profile corresponding to the profile of the casing that is to be fabricated, so as to obtain a fiber preform of shape corresponding to the shape of the casing that is to be fabricated; and densifying the fiber preform with a matrix; wherein, before beginning to wind the fiber texture onto the mandrel, a reinforcing band of width smaller than the width of the fiber texture is placed on the mandrel in a zone that is to form a retention zone of the casing.