A metallic structure defines ribs and a skin supported by the ribs. The ribs may be defined by metal strips and the skin may be attached to the ribs. Alternatively, the skin may be defined by a plurality of tiles and the ribs may be defined by flanges of each of the plurality of tiles that cooperate to define the ribs. Tiles may be attached to separate rib lattice. Structurally weak locations at nodes where ribs intersect may be reinforced. The components may be brazed together and the stiffness of adjacent locations in the structure adjusted in the brazing operation to reduce the difference in stiffness and to reduce resulting stress risers. The metallic structure may be armored using metal foam to absorb the energy of a projectile.

Systems and methods are provided for enforcing contours onto parts of an aircraft. One embodiment is a method for enforcing a contour onto aircraft parts. The method includes removably attaching segmented ring details to aircraft skin details, attaching stringers to skin details to create skin assemblies, positioning skin assemblies at a support structure defining a contour, and fastening frames to the skin assemblies to create a panel. The method also includes removably installing a spreader section onto the panel to complete assembly of a brace prior to removal of the panel, transporting the panel while the brace enforces the contour, attaching the brace to braces for other panels to form a barrel section of a fuselage for an aircraft while the brace enforces the contour, and removing the brace from the barrel section after the barrel section has been formed.

A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing having a bore, a conical sleeve configured to be disposed about the frustoconical internal bearing, a composite structure configured to couple between the frustoconical internal bearing and the conical sleeve, a metallic end fitting configured to be disposed within the bore and couple to the frustoconical internal bearing, and an external nut configured to couple to the metallic end fitting and the conical sleeve, wherein at least one of the frustoconical internal bearing or the conical sleeve comprises a flanged portion mutually configured to couple the conical sleeve to the frustoconical internal bearing via a locking ring.

There is provided a laminated hybrid metallized polymer film for erosion protection of a composite structure. The laminated hybrid metallized polymer film includes a metal foil layer, a laminating adhesive layer underlying the metal foil layer, and a polymer film layer underlying the laminating adhesive layer. The polymer film layer is laminated to the metal foil layer with the laminating adhesive layer coupled between the metal foil layer and the polymer film layer. The laminated hybrid metallized polymer film further includes an adhesive layer underlying the polymer film layer. The adhesive layer adheres the polymer film layer to a substrate surface of the composite structure. The metal foil layer, the laminating adhesive layer, the polymer film layer, and the adhesive layer form the laminated hybrid metallized polymer film for application over and to the substrate surface of the composite structure.

An auxiliary power unit enclosure of an aircraft includes a space frame configured to carry a load and defining an auxiliary power unit compartment. The space frame includes a plurality of frame elements coupled together at a plurality of nodes. The auxiliary power unit enclosure also includes a fairing coupled to and surrounding the space frame.

An integrated panel made of interconnected laminates includes stacked first and second metal layers (5, 5, 5) and fibre-reinforced adhesive layers (19) between adjacent metal layers. At the location of the transition from the outer surface (7) of the first outer metal layer (5) to the outer surface (7) of the second outer metal layer (4) is located a filler (11). The panel further includes a cladding layer (14), which includes at least one fibre material layer (15, 24) that extends over the filler (11) and the adjacent outer surface regions (12, 13) of the outer metal layers (5, 4) located on opposite sides and which are adhered to the outer surface regions.

A method for assembling two components and method for assembling two portions of an aircraft. A method for assembling first and second components includes, prior to the setting in place of temporary linking elements in the first and second starter holes, producing the first starter holes in the first component, depositing a sealing mastic on at least one of the first and second contact faces of the first and second components, placing the first and second components against one another, and producing second starter holes in the second component using a drilling tool connected to a suction system and equipped with a drill bush including a first part that has an outside diameter less than or equal to that of the first starter holes and a first end bearing against the second contact face of the second component upon production of the second starter holes.

A method for manufacturing a brushed rolled product made from AlCuLi alloy with a thickness of less than 12 mm, including the steps of producing a rolled product, solution heat treatment and quenching, stress relieving, optionally tempering, and brushing, wherein the brushing tool applies a force to the rolled product generating residual compressive stresses at the surface of the brushed product; eliminates a thickness of at least 9 m from the surface of the non-brushed rolled product; wherein the brushing step comprises at least one circular brushing motion. The rolled product obtained by the method according to the invention is advantageous. The use of such a product in an aircraft fuselage panel is advantageous.

Applicant discloses a two part polymer mix for use in the aircraft industry that is applied with pneumatic mix and spray gun. The two part cartridge is used in the mix and spray gun so the mix is applied immediately upon mixing, but the two components are kept separated unless the gun is applying the mix. The mix cures to form a clear sealant that allows for inspection of cracks and corrosion beneath the sealant. It cures quickly so that the coated part may be further processed, for example in the assembly line during aircraft build.

A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing, an internal bolt coupled within a bore of the frustoconical internal bearing, a metallic end fitting coupled to the internal bolt, wherein the metallic end fitting comprises a bearing portion disposed within the bore, a conical sleeve disposed about the frustoconical internal bearing, and an external nut coupled to the metallic end fitting and the conical sleeve.