A method of producing a laminated article comprising placing a first metal skin, a core, and a second metal skin freely onto each other as discreet layers to provide a layered component; and forming the layered component into a shaped article via a die prior to producing a laminated article by applying pressure and heat to the shaped article, wherein at least the first skin moves relative to the core and/or second skin during the forming.

A resin-coated metal sheet for a container, the metal sheet including: a first resin coat layer provided on a first surface of the metal sheet; a second resin coat layer provided on a second surface of the metal sheet, wherein each of the first and the second resin coat layers is composed mainly of a polyester resin having a melting point of 230 C. to 254 C., and the first resin coat layer, in a state that the resin coat layers coat the metal sheet, is formed of a resin material having: an arithmetic average roughness (Ra) of 0.10 m to 1.0 m; a crystallization temperature of 110 C. to 160 C.; and a water contact angle of 55 degrees to 80 degrees in a state that the resin coat layers have been heated at 240 C. for 90 seconds after the resin coat layers coat the metal sheet.

A curable matrix resin composition containing a thermoset resin component and metastable thermoplastic particles, wherein the metastable thermoplastic particles are particles of semi-crystalline thermoplastic material with an amorphous polymer fraction that will undergo crystallization upon heating to a crystallization temperature T.sub.c. A fiber-reinforced polymeric composite material containing metastable thermoplastic particles is also disclosed.

A method of producing a laminated article comprising placing a first metal skin, a core, and a second metal skin freely onto each other as discrete layers to provide a layered component; and forming the layered component into a shaped article via a die prior to producing a laminated article by applying pressure and heat to the shaped article, wherein at least the first skin moves relative to the core and/or second skin during the forming.

Method and apparatus for fabricating an anti-fatigue mat are disclosed. In one embodiment an anti-fatigue mat includes a foam member and a gel member, wherein each member exhibits a different durometer. The foam member includes a gel receiver that is configured with a geometry shaped to receive the gel member. A top fabric is situated on the top of the mat above the gel member and the foam member. A non-slip surface is provided on the bottom of the anti-fatigue mat. The gel member may be sealed within the mat by the foam member and the top fabric.

The invention relates to a timepiece component made of composite material including at least one reinforcement and one matrix, the reinforcement having a three-dimensional honeycomb structure with a plurality of cells into which the matrix is injected.

The invention also concerns a method for manufacturing such a timepiece component.

A curable matrix resin composition containing a thermoset resin component and metastable thermoplastic particles, wherein the metastable thermoplastic particles are particles of semi-crystalline thermoplastic material with an amorphous polymer fraction that will undergo crystallization upon heating to a crystallization temperature Tc. A fiber-reinforced polymeric composite material containing metastable thermoplastic particles is also disclosed.

Described is laminate of a stack of mutually bonded adhesive layers and metal layers. An outer metal layer has spliced metal sheets having overlapping end parts and/or abutting metal sheet edges extending in a first and a different second planar direction of the laminate to define first and second splice lines. Connected to an outer surface are first and second splice straps covering the first and second splice lines. A lateral edge part of each splice strap has a lower bending stiffness than the bending stiffness of the outer metal layer sheets, the edge part being defined as extending from an outer lateral edge of a splice strap over a lateral distance of at least 5 times the edge part average thickness. The laminate may be used for making large structural components, such as a wing or fuselage of an aircraft.

An object of the present invention is to provide a laminate of an olefin-type rubber, which is non-polar or has a small polarity and which is difficult to bond with a different material, and a rubber including Group 16 elements and/or Group 17 elements, which is a different kind of rubber. The laminate according to the present invention includes a structure including, in order, an olefin-type rubber layer (A) ; an adhesive resin layer (B) containing at least one selected from the group consisting of an ethylene/vinyl acetate copolymer, a silane-modified ethylene/vinyl acetate copolymer, an ethylene/acrylic acid copolymer and an ionomer thereof, and an ethylene/methacrylic acid copolymer and an ionomer thereof; and a rubber layer (C) containing Group 16 elements and/or Group 17 elements.

A method of and system for adhesive bonding by a) providing a polymerizable adhesive composition on a surface of an element to be bonded to form an assembly; b) irradiating the assembly with radiation at a first wavelength capable of vulcanization of bonds in the polymerizable adhesive composition by activation of sulfur-containing compound with at least one selected from x-ray, e-beam, visible, or infrared light to thereby generate ultraviolet light in the polymerizable adhesive composition; and c) adhesively joining two or more components together by way of the polymerizable adhesive composition.