An energy absorbing rub strip having a core material and a fairing positioned over the core material. The core material may be configured to buckle under the application of a predetermined amount of force and the fairing may be configured to be attached to a fuselage of an aircraft. The fairing may be made out of an abrasive-resistant material such as titanium or a nickel-based metal. The core material may be comprised of an aluminum honeycomb. The core material may be comprised of a dual density material. The length of the rub strip may extend beyond potential contact points on the fuselage during landing and takeoff. Upon a ground contact event, the thickness of deformed/buckled core material may be measured to determine if the ground contact event may have caused structural damage to the aircraft.

A perforated composite panel comprises a substrate and an applied layer, the substrate having a first surface and an opposite second surface. A method of forming the perforated composite panel comprises the steps of: i. cutting a plurality of first holes in the substrate; ii. positioning the applied layer against the substrate such that a surface of the applied layer overlays the first surface of the substrate to thereby form the composite panel; iii. locating the composite panel in a fixture, the fixture having one or more datum features; iv. determining the location and axis direction for each of the first holes in the substrate, relative to the or each datum feature; and v. cutting a plurality of second holes in the applied layer, each of the plurality of second holes being coincident and coaxial with a corresponding one of the plurality of first holes.

A product includes a three-dimensional structure comprising a continuous metallic material. The continuous metallic material includes at least two layers. A first layer of the at least two layers includes a metal and a second layer of the at least two layers includes a transition metal having a body-centered-cubic crystal structure. A method of forming a three-dimensional structure having a continuous metallic material includes forming a polymer template, depositing a seed layer on the polymer template, and depositing a metallic layer on the seed layer. The metallic layer includes a transition metal that is nucleated by the seed layer thereby forming the continuous metallic material having a body-centered-cubic crystal structure.

A combined material honeycomb core and methods of manufacture are presented. The combined material honeycomb core comprises a plurality of cells arranged in columns and rows formed of multiple materials, the multiple materials comprising a metallic material and either a second metallic material or a non-metallic material.

A pulse current-assisted roll bonding method for a magnesium/titanium composite plate with a large thickness ratio is provided. The specific steps are as follows: 1, pre-treating a slab; 2, applying a pulse current; 3, rolling and bonding; and 4, post-treating the slab. The magnesium/titanium composite plate with the large thickness ratio is obtained.

A method including arranging a plurality of flat sheets into a part assembly, consisting of a first outer sheet and a second outer sheet. A friction-modifying layer is applied to the first outer sheet, where the first outer sheet has a first portion and a second portion. The friction-modifying layer is applied at a first thickness in the first portion and a second thickness in the second portion. The first thickness and the second thickness are different thicknesses. The method also includes placing the part assembly on a lower die of a die system with the first outer sheet facing the lower die. The method further includes moving an upper die of the die system in a forming direction toward the lower die to stretch and compress the part assembly between the upper die and the lower die and to super-plastically form the part assembly into the formed part.

The present specification relates to a decorative member comprising a base and inorganic layers comprising a first light absorption layer, a light reflection layer, and a second light absorption layer sequentially provided on the base, in which E.sub.12 indicated in Equation 1 is 1 or more, and a method of manufacturing the decorative member.

A rail for the fastening of equipment elements, such as, in particular, seats, in aircraft, includes a holding region for connection to an equipment element of an aircraft, and a support region to fasten the rail to a carrier element of the aircraft. The rail has a metallic shell which is, for example, made of titanium and which is filled with a fiber-reinforced thermoplastic filler material which is reinforced by short fibers. To produce the rail, a metallic molded part is used as a casting mold and is filled, for example by injection, with the filler material and, after the rail has been produced, forms the metallic shell for the filler material.

A manufacturing method for manufacturing a welded thermoplastic composite and honeycomb core structure is provided. A thermoplastic composite and honeycomb structure is generated by positioning a first thermoplastic composite skin on a support structure, positioning a first thermoplastic film over the first thermoplastic composite skin, positioning a honeycomb core over the first thermoplastic film, positioning a second thermoplastic film is positioned over the honeycomb core, and positioning a second thermoplastic composite skin over the second thermoplastic film. The second thermoplastic composite skin is ultrasonically welded to the honeycomb core. The thermoplastic composite and honeycomb structure is then flipped over, and the first thermoplastic composite skin is then ultrasonically welded to the honeycomb core.

A pulse current-assisted roll bonding method for a magnesium/titanium composite plate with a large thickness ratio is provided. The specific steps are as follows: 1, pre-treating a slab; 2, applying a pulse current; 3, rolling and bonding; and 4, post-treating the slab. The magnesium/titanium composite plate with the large thickness ratio is obtained.