The present invention provides a laminate material having a polyester film and a web of polyester fibers cohesively bonded directly thereto, such that portions of the fibers are bonded to the polyester film and portions of the fibers are free from the polyester film. The invention may also include a glass reinforced polymer layer formed on the laminated facer where the polymer of the glass reinforced polymer layer is commingled with the nonwoven of the laminated facer. The laminate may further include a second polymer layer having a thickness joined to the fiber layer and/or a layer of hot melt adhesive applied to the polyester fibers. Also presented is a composite material having a polyester film, a layer of polyester fibers bonded to the second polymer layer; a second polymer layer joined to the polyester film; and a glass reinforced polymer layer formed on the laminated facer, where the polymer of the class reinforced polymer layer is commingled with the nonwoven of the laminated facer.

Composite articles comprising a porous prepreg or core layer and a powder coated layer thereon are described. In some instances, a thermoplastic composite article comprises a porous core layer comprising a web of reinforcing fibers held together by a thermoplastic material, and a powder coated layer disposed on the porous core layer, in which a particle size of the powder coated layer is selected to provide an interface between the powder coated layer and the porous core layer, wherein at least 50% by weight of the disposed powder coated layer is present above the interface.

A method for producing an aircraft structural component includes the steps of introducing a plurality of semi-finished product layers for producing a component from a fibre-reinforced, thermoplastic plastic material into a compression mould, applying pressure to the stacked semi-finished product layers, the stacked semi-finished product layers being fixed, before pressure is applied, at particular points in their position in the compression mould and/or relative to one another in such a way that, while pressure is being applied to the semi-finished product layers stacked in the compression mould, a sliding movement of the semi-finished product layers relative to one another and/or relative to the compression mould, preventing wrinkling in the semi-finished product layers, takes place, and removing the aircraft structural component from the compression mould.

A ceiling material body (1a) includes a substrate layer (2) formed from rigid urethane foam; a first fiber-reinforced layer (3) provided on an in-cabin side of the substrate layer (2); a second fiber-reinforced layer (4) provided on an out-cabin side of the substrate layer (2); a surface layer (5) provided on an in-cabin side of the first fiber-reinforced layer (3); and a back layer (6) provided on an out-cabin side of the second fiber-reinforced layer (4). The second fiber-reinforced layer (4) includes a glass paper (7) overlaying the substrate layer (2) and a glass mat (8) overlaying an opposite side of the glass paper (7) from the substrate layer (2).

The present invention relates to a sandwich panel and a method of manufacturing the same. The sandwich panel according to the present invention has high density and improved physical properties such as flexural strength, flexural modulus, bending strength and lightening weighting ratio and is suitable for use in various consumer products or industrial materials.

An impact resistant exterior sheathing gypsum building panel with an integrated impact resistant woven mesh which protects against impact from projectiles such as those conveyed by hurricane force winds is provided. Methods for manufacturing these exterior sheathing gypsum building panels with an integrated impact resistant woven mesh are also provided. An exterior sheathing system employing the exterior sheathing cementitious building panel is provided.

The present invention relates to a sandwich panel and a method of manufacturing the same. The sandwich panel according to the present invention has high density and improved physical properties such as flexural strength, flexural modulus, bending strength and lightening weighting ratio and is suitable for use in various consumer products or industrial materials.

A honeycomb structure has a core made up of a plurality of corrugated sheets which are superposed and fixed together. The corrugated sheets are made from a thermally insulating material. The corrugated sheets are impregnated with a resin filled with thermally conductive powder along their entire length. The honeycomb structure can be used when the ambient temperature exceeds, for example, 120° C.

One aspect of the present disclosure provides a composite sheet including a porous sintered ceramic component having a thickness of less than 2 mm and a resin filled into pores of the sintered ceramic component, wherein the curing rate of the resin is 10 to 70%.

A laminated adhesive tape includes a substrate comprising two or more plies of thin, flexible material, the substrate having a first major surface and a second major surface opposite the first major surface. A polymeric laminating composition comprising a polymer and an alkyl ketene dimer binds the two or more plies and a pressure sensitive adhesive carried on the first major surface. In a further aspect, a method of making a laminated adhesive tape is provided.