Abstract: The invention relates to airplane floor assemblies and to methods for their assembly. In one embodiment, an airplane comprises at least one fuselage section and at least one floor section. At least one system component is installed to the floor section prior to installation of the floor section in the fuselage of the airplane. In another embodiment, a floor section adapted to be installed in an airplane includes at least one system component installed to the floor section while it is outside of the airplane. In yet another embodiment, a method is disclosed for assembling an airplane. The method comprises installing at least one system component to a floor section, and installing the floor section into a fuselage section of the airplane.

Abstract: Laminate structures and methods for forming same are disclosed. In one embodiment, a laminate structure includes a metal-polymer composite lamina. The metal-polymer composite lamina has a first face and a second face spaced apart, and extends to a terminal edge. The lamina includes a ply of fiber-reinforced polymer that extends between the first face and the second face and has an interior edge. The interior edge defines at least one cutout. A ply of metal foil extends between the first face and the second face substantially from the interior edge filling the at least one cutout.

Abstract: A selectively reinforced hybrid metal-composite structural element can include a metal element and a composite material. The composite material can be bonded to the metal element by an adhesive layer including a polymer matrix using a radiation curing process, resulting in insubstantial or negligible residual stresses at the bond line between the metal element and the composite element. The structural element also can include a metal closeout cap to provide a barrier from a corrosive atmosphere, and the adhesive layer can encapsulate the composite element to provide a corrosion-resistant barrier between the composite element and the surrounding metal.

Abstract: Laminate structures and methods for forming same are disclosed. In one embodiment, a laminate structure includes a metal-polymer composite lamina. The metal-polymer composite lamina has a first face and a second face spaced apart, and extends to a terminal edge. The lamina includes a ply of fiber-reinforced polymer that extends between the first face and the second face and has an interior edge. The interior edge defines at least one cutout. A ply of metal foil extends between the first face and the second face substantially from the interior edge filling the at least one cutout.

Abstract: A number of integrated floor structures made of lightweight composite materials for use in an aircraft are disclosed. Generally, each of such floors includes a top-layer skin, a bottom-layer skin disposed below the top-layer skin and a first structural core disposed between the top-layer skin and the bottom-layer skin, the first structural core being composed of a honeycomb composite material. One or more denser structural cores can also be incorporated at strategic locations.

Abstract: An exemplary fiber metal laminate includes at least two metallic layers and at least one fiber layer bonded between the two metallic layers. The fiber layer includes a resin matrix and organic polymeric fibers with a modulus of elasticity greater than 270 GPa. The polymeric fibers may include poly diimidazo pyridinylene fibers. The metallic layers may include pre-treated aluminum alloy layers.