Disclosed are a vehicle seat cover made of an artificial suede. The vehicle seat cover includes a top layer provided in the top portion, a bottom layer provided in the bottom portion, and a intermediate layer positioned between the top layer and the bottom layer. Each of the layers has a tricot texture, and the top layer includes the first yarn having a configuration in which the dope dyed microfiber yarn and the first high shrinkage yarn are interlaced. Thus, the suede material may have superior friction fastness and the light fastness and the vehicle seat cover is manufactured at less cost than a vehicle seat cover made of a conventional artificial suede.

A composite sandwich panel assembly including an open area core, a high gloss surface sheet, and a structural skin. The open are core defines a plurality of pores and has a first face and an opposing second face. The high gloss surface sheet is adhered to the first face of the open area core by a first adhesive layer. The high gloss surface sheet has a high gloss surface. The structural skin is adhered to the second face of the open area core by a second adhesive layer. A process for forming the composite sandwich panel assembly includes positioning the high gloss surface sheet, joining the first face of the open area core to the high gloss surface sheet with a first adhesive layer intermediate therebetween, and joining the structural skin to the second face of the open area core with a second adhesive layer intermediate therebetween.

A sliding seismic isolation device includes a structure fixation plate having a first sliding surface and a metallic slider having a second sliding surface contacting the first sliding surface. A friction member composed of a single-layer fabric is attached to the first sliding surface, the second sliding surface, or both of the first sliding surface and the second sliding surface. One of a warp and a weft is formed of multiple plied yarns into which high-strength fibers and PTFE fibers are twisted together and the other of the warp and the weft is formed of multiple high-strength fibers in the single-layer fabric. The single-layer fabric has a twill weave and is woven such that the plied yarns of the one forming the single-layer fabric are exposed at a surface opposite from the attachment side of the friction member more than the high-strength fibers of the other forming the single-layer fabric.

The method for producing a laminate having a patterned metal foil includes masking the whole surface of a first metal foil in a laminate having the first metal foil, a first insulating resin layer having a thickness of 1 to 200 μm and a second metal foil laminated in this order, and patterning the second metal foil.

The present disclosure provides a composite lift gate for a vehicle. The composite lift gate includes a polymer matrix and a fiber assembly. The fiber assembly is embedded in the polymer matrix. The fiber assembly includes a fiber mat and a plurality of substantially-aligned continuous fibers. The plurality of substantially-aligned continuous fibers is directly connected to a portion of the fiber mat. In one aspect, the composite lift gate further includes an electronic component connected to the fiber assembly. In various aspects, the present disclosure provides a method of manufacturing a composite lift gate for a vehicle.

A traction mat wherein the foam is reinforced with a layer of fabric or fiber between the CLCC foam layer and the substrate or underlying surface. The layering is preferably a first foam layer and a fabric layer impregnated with a pressure sensitive adhesive. This prevents the CLCC foam from being bonded directly to the substrate and allows the fabric/fiber to support the CLCC foam such that the entire assembly can be removed in one piece without the CLCC foam disintegrating. The introduction of the reinforcing fabric and/or fiber layer eliminates any residual CLCC foam from being bonded to the substrate. Consequently, the traction mat can be easily lifted away and removed.

A structural reinforcement for an article including a carrier that includes: (i) a mass of polymeric material having an outer surface; and (is) at least one consolidated fibrous insert having an outer surface and including at least one elongated fiber arrangement having a plurality of ordered fibers arranged in a predetermined manner. The fibrous insert is envisioned to adjoin the mass of the polymeric material in a predetermined location for carrying a predetermined load that is subjected upon the predetermined location (thereby effectively providing localized reinforcement to that predetermined location). The fibrous insert and the mass of polymeric material are of compatible materials, structures or both, for allowing the fibrous insert to be at least partially joined to the mass of the polymeric material. Disposed upon at least a portion of the carrier will be a mass of activatable material.

Provided is a jig which assists in the adhesion of a thin-film sheet to an adhesion target surface (skin etc.), and which can easily adhere the thin-film sheet to the adhesion target surface. The jig includes: a base part having a first surface; and a porous hydrophilic film that is adhered to the first surface and has fine pores with a predetermined porosity, wherein the porosity is 35% to 55% inclusive. The hardness of the base part is preferably 4-20 inclusive. In addition, it is preferable that the base part and the hydrophilic film have transparency.

Hybrid fibrous composite materials incorporating at least two different fabric components and a multicomponent adhesive system for adhering the fabric components together. The adhesive system enhances the bond strength between the fabric components, which would otherwise easily delaminate from each other and peel apart. The components of the adhesive system bond strongly to each other as well as to the fabric elements.

An aerospace component, for example, used in a gas turbine engine, includes the following structurally-integrated layers: a metallic layer and a composite layer having reinforcing fibers embedded in a matrix material. The aerospace component can also include an insulating layer disposed between the metallic layer and the composite layer where the insulating layer has a thermal conductivity that is lower than a thermal conductivity of the composite layer.