The present disclosure relates to a system for manufacturing a hybrid component including a first thermal supplier configured to heat a steel plate, a rolling roll for undercut configured to pressurize the steel plate heated by the first thermal supplier, and to form an undercut on one surface of the steel plate, a first molding roll configured to pressurize the steel plate formed with the undercut to mold the steel plate in a shape of a component to be manufactured, a composite material feeder configured to supply a composite material tape to be seated on one surface of the steel plate formed with the undercut through the first molding roll, and a composite material pressurization roll configured to pressurize the steel plate on which the composite material tape is seated.

A fuselage structure of an aircraft includes a fuselage skin, and a plurality of frame elements spaced apart from one another in a direction parallel to the aircraft longitudinal axis for supporting the fuselage skin. The fuselage skin includes a plurality of interconnected fiber-reinforced composite skin panels that extend between each pair of frame elements and are connected thereto. The composite skin panels further comprise a stiffener integrally formed in each composite skin panel. A method for manufacturing the fuselage skin. The composite skin panels may be interconnected and/or connected to a frame element through an induction welded connection.

In a metal-fiber reinforced plastic (FRP) composite, the FRP and the metal member are bonded together, so internal stress (thermal stress) is generated due to the misfit of coefficients of thermal expansion of the metal member and the FRP. Not only does the binder layer peel off and the mechanical properties of the FRP cannot be obtained, but also defects in appearance (surface strain) occur. Therefore, the technical problem is to secure the mechanical properties as a composite while easing the internal stress and keeping surface strain from being generated. The metal-fiber reinforced plastic (FRP) composite according to the present invention solves the technical problem by sandwiching an FRP between two metal members and not having at least one of the metal members joined (bonded) with the FRP. Further, it is possible to arrange an intermediate member between the other metal member and the FRP and sandwich the FRP between the two metal members through the intermediate member.

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.

A heated composite structure and a method for forming a heated composite structure. The structure includes carbon fibers embedded within a thermoplastic matrix. The carbon fibers are connected with first and second electrodes that are configured to be connected with an electric source such that applying current to the electrodes causes current to flow through the embedded carbon fibers to provide resistive heating sufficient to heat the composite structure to impede formation of ice on the composite structure.

An acoustic panel comprising a cellular structure, such as a honeycomb structure, having cells that open at least onto a first frontal face of the structure. The panel comprises a capsular skin which is fastened to the first frontal face of the cellular structure next to a plurality of cells. The capsular skin including a continuous layer of material, in one piece, forming capsules that extend into the cellular structure. At least one channel is provided at the apex of each capsule for the passage of acoustic waves. Such a panel effectively attenuates the noise of aircraft engines, in particular, the low frequencies. It is extremely easy to manufacture industrially, the capsular skin being able to be obtained by molding with polymerization in situ, the polymerizable material then adhering to the cellular structure while it polymerizes.

A method and apparatus for forming a composite structure. An inner tooling, a stackup, and an outer tooling are held in place together using a load constraint. A bladder and a plurality of stringer bladders in the stackup are pressurized to cause expansion of the bladder and the plurality of stringer bladders, thereby pushing together an overbraided thermoplastic skin and a plurality of overbraided thermoplastic members in the stackup. The overbraided thermoplastic skin and the plurality of overbraided thermoplastic members are co-consolidated while the bladder and the plurality of stringer bladders are pressurized to form the composite structure.

In an example, a method is described. The method comprises forming a single hole into a bond gap repair area. The method also comprises evacuating, via an adhesive injection apparatus attached to the single hole, the bond gap repair area and an injection channel of the adhesive injection apparatus. The method also comprises forcing adhesive through the evacuated injection channel and into the evacuated bond gap repair area.

A method of forming a reinforced panel may include engaging a reinforcement component having a faying surface with a first portion of a heated press, engaging an uncured panel component with an opposing second portion of the press, the panel component having a faying surface complementarily-configured with respect to the faying surface of the reinforcement component, treating the faying surface of the reinforcement component such that the faying surface is active for co-bonding with respect to the panel component, actuating the press to direct the first and second portions of the press toward each other, such that the faying surfaces are complementarily engaged under pressure; and heating the first and second portions of the press to a curing temperature associated with the panel component to substantially simultaneously co-bond the faying surfaces of the reinforcement component and the panel component together, cure the panel component, and form the reinforced panel.

A joining system includes a holding fixture assembly configured to hold a fuselage skin. The stringers are temporarily attached to the fuselage skin. The joining system includes an upper beam assembly including an upper beam and a lower beam assembly. The lower beam assembly includes a lower beam and at least one lower heating element. The holding fixture assembly is coupled to the upper beam assembly. The holding fixture assembly is coupled to the lower beam assembly. The upper beam is movable relative to the lower beam to clamp the at least one of the plurality of stringers and the fuselage skin together prior to and during welding.