A method of fabricating a composite structure includes laying at least one composite ply about a bladder, the bladder comprising a phase change material in a first phase having a first volume, positioning an outer mold about the bladder and the at least one composite ply, and curing the at least one composite ply to form the composite structure. Curing causes the phase change material contained within the bladder to change to a second phase to expand from the first volume to a second volume and apply a pressure to an interior surface of the composite ply and press an outer surface of the composite ply against the outer mold to form an interior cavity. The bladder is not removable from the formed interior cavity.

An example method of forming a composite structure is described that includes applying a laminated charge onto an expandable pallet, moving the expandable pallet at a translation rate and relative to a die conveyor that comprises a plurality of die sections, and driving the plurality of die sections on the die conveyor at an angle relative to the expandable pallet so as to drive the plurality of die sections progressively deeper into a recess defined by the expandable pallet and shape the laminated charge into at least part of a shape of the composite structure.

To improve a method for ultrasonic welding of parts for vehicles and/or aircraft, a method in which an energy director made of non-woven fiber material is arranged between a first fiber composite part and a second fiber composite part to be joined together. A sonotrode is used to join/weld the parts together by pressing on the parts. The energy director is compliant such that a uniform even contact is generated between the first and second fiber composite parts during the welding process.

Provided are systems and apparatuses for manufacturing aircraft support structures. An example robotic end effector comprises a rotatable reel with a flat strip of material wound around the reel. The end effector further includes a forming shoe including a forming surface contacting the strip of material. A first end of the forming surface corresponds to a start shape and a second end of the forming surface corresponds to an end shape. As the strip of material passes from the first end of the forming surface to the second end of the forming surface, the strip of material transitions from the first shape to the end shape and is deposited as a formed stringer ply onto an application surface. The forming shoe may further include a vacuum system to suction air through a plurality of ports along the forming surface to urge the strip of material against the forming surface.

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 a 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 thermoplastic polymer resin and milled fibers provided in the thermoplastic surfacer.

The invention provides a sonotrode (100) for welding a material, the sonotrode (100) comprising a welding section (110) configured for contacting the material, wherein the welding section (110) defines a rounded shape (111) in a cross-section parallel to a longitudinal axis (A) of the sonotrode (100), wherein the rounded shape (111) approximates a circular sector (20), wherein the circular sector (20) has a central angle α.sub.c selected from the range of 25°-300°, and wherein the circular sector (20) has a central radius r.sub.c selected from the range of 5-30 mm, and wherein the sonotrode (100) has a width W perpendicular to the longitudinal axis (A) [and to the cross-section], wherein W is selected from the range of 10-100 mm.

An anti-icing honeycomb core composite manufactured by forming an electromagnetic wave absorption layer by using dielectric fiber, molding the electromagnetic wave absorption layer into a honeycomb core structure by using a molded part including a first base, a second base, and an inner block, hardening the honeycomb core structure, and removing the molded part. The molding step includes first stacking, on the first base including a plurality of grooves in which the inner blocks each having a hexagonal column shape are able to be seated, a plurality of the inner blocks and a plurality of the electromagnetic wave absorption layers as the honeycomb core structure so that the electromagnetic wave absorption layer is disposed between the plurality of inner blocks, and second stacking covering the inner blocks and the electromagnetic wave absorption layers stacked on the first base with the second base having the same shape as the first base.

A method for making a composite part using a reformable mandrel, including contouring a reformable mandrel; placing an uncured composite part on the reformable mandrel; curing the uncured composite part; and removing the reformable mandrel, wherein the reformable mandrel includes a core including a transitional state material having a transition temperature, and a sleeve at least partially surrounding the core and including a heat-resistant flexible material having an operational temperature.

The present disclosure is directed to a method for reactivating a co-cured film layer disposed on a composite structure, the method comprising applying a reactivation treatment composition comprising at least two solvents and a surface exchange agent comprising a metal alkoxide or chelate thereof to the co-cured film layer, and allowing the reactivation treatment composition to create a reactivated co-cured film layer, wherein the co-cured film layer was previously cured at a curing temperature greater than about 50° C. A reactivated co-cured film layer and an aircraft part having a reactivated co-cured film layer are also provided.

An apparatus for consolidating fiber-reinforced resin material comprises a housing, comprising a barrel and a receptacle. The receptacle comprises a base, a lid, positionable relative to the base and relative to the barrel such that the housing is in an open state or a closed state, and a de-gassing port. The apparatus comprises a gasket that is in contact with the lid, the base, and the barrel when the housing is in the closed state. The apparatus comprises a piston, movable between a retracted position, in which the piston, in its entirety, is in the barrel, and an extended position, in which a portion of the piston is in the receptacle and another portion of the piston is in the barrel. The apparatus comprises a seal, which is in contact with the piston and the barrel, and a drive system, configured to control movement of the piston.