Abstract: The invention pertains to a method for making a laminate comprising at least the following steps: placing a metal sheet on a form tool or a substrate, placing an adhesive layer on top of the first metal sheet, placing a second metal sheet on top of the adhesive layer such that at least one of the metal sheets overlaps at least one edge of the other metal sheet, applying heat and pressure to the thus obtained stack, where during the application of pressure at least one of the metal sheets is bent towards the plane of the other metal sheet. Thus, complicated structures can be optimized for a certain application and, besides, manufactured in one go using comparatively inexpensive tools.

Abstract: A metal-polymer laminate has a bidirectional reinforcing layer containing about 45-70 vol. % high strength glass fibers. The bidirectional reinforcing layer includes a center layer containing glass fibers oriented generally parallel to a first direction; and first and second outer layers each reinforced with glass fibers oriented in a second direction extending generally transverse to the first direction. The bidirectional laminate is suitable for use in aircraft flooring and other applications requiring improved impact strength.

Abstract: A laminated body panel for aircraft applications comprises first and second metal layers and an adhesive layer. First and second sections in each metal layer are generally coplanar and separated by a splice line. A first splice line in a first metal layer is generally parallel to a second splice line in a second metal layer, and spaced laterally from the second splice line. An adhesive layer between the metal layers preferably contains reinforcing fibers bridging across the splice lines. An aircraft fuselage or wing or empennage made with spliced body panels of the invention has fewer joints and weighs less than one made with narrower body panels containing unspliced metal layers.

Abstract: A metal-polymer-metal laminate is made by joining adjacent laminate sections in a staggered relationship. Terminal portions of metal layers in a first laminate section are opposed to ends of fiber-reinforced polymer layers in a second laminate section. End portions of fiber-reinforced polymer layers in the first laminate section are opposed to ends of metal layers in a second laminate section. The two laminate sections are then joined by an adhesive layer.