An aramid paper suitable for use as electrical insulation comprising a first outer layer and a second outer layer, each of which comprising 70 to 30 weight percent aramid floc and 30 to 70 weight percent aramid fibrids, and each of which being free of mica and having a first face and a second face; an inner layer comprising 50 to 70 weight percent aramid material and 30 to 50 weight percent mica and having a first face and a second face; wherein the first face of the first outer layer is a first outer face of the aramid paper, and the second face of the first outer layer is coextensive with and bound face-to-face with the first face of the inner layer solely by fibrids in the first outer layer and the inner layer; and wherein the first face of the second outer layer is coextensive with and bound face-to-face with the second face of the inner layer solely by fibrids in the second outer layer and the inner layer, and the second face of the second outer layer is a second outer face of the aramid paper; the aramid paper having a total of 25 to 40 weight percent mica.

Processes for forming fiber reinforced composite aircraft components, i.e., aircraft components formed of a cured fiber-reinforced resin, are provided. According to specific embodiments, a finished surface of the composite aircraft component can be achieved by providing in-mold coating of the cured fiber-reinforced resin by a dried and cured film layer of a water-based primer paint material to thereby achieve a composite aircraft component having an exterior surface that does not necessarily require further finishing.

The invention relates to a pre-impregnated fibre-reinforced composite material in laminar form, obtained impregnating a fibrous mass with a polymeric binder composition and intended to be subjected to successive forming and complete curing operations to produce a fibre-reinforced composite material. The polymeric binder composition comprises one or more resins chosen in the group consisting of siloxane resins and silsesquioxane resins, and can optionally comprise one or more organic resins. The polymeric binder composition appears as a liquid with viscosity between 55000 and 10000 mPas at temperatures between 50° C. and 70° C. The polymeric binder composition forms a polymeric binder matrix, not cross-linked or only partially cross-linked, that fills the interstices of the fibrous mass. The invention also relates to a method for making said pre-impregnated fibre-reinforced composite material in laminar form. The invention also relates to a manufactured article obtained by hot forming and complete curing of the aforesaid pre-impregnated fibre-reinforced composite material, as well as a method for making said manufactured article.

An enclosure member for a building structure comprising a planar laminate having a first facing layer; a layer of foam having a first face and a second opposing face; and a second facing layer; where the first facing layer is fastened to the first face of the layer of foam, and the second facing layer is fastened to the second opposing face of the layer of foam. An edge of the enclosure is provided with a perimeter structure that can perform one or more of a sealing function, an edge reinforcement function and a pivotable joining function with another enclosure, in accordance with the particular embodiment.

The invention relates to a method for producing an absorbing sound insulation motor vehicle trim element having a four-layered structure made from a first foam layer, a second foam layer, a non-woven foam layer and a non-woven fabric layer. The invention further relates to an absorbing sound insulation motor vehicle trim element.

A synthetic resin skin material composite, including: a urethane resin skin material including a urethane resin skin layer provided at one surface of a substrate; and a cushion layer that is placed at a surface on an opposite side of the substrate from the surface of the urethane resin skin material at which the urethane resin skin layer is provided; in which the urethane resin skin material has recesses at a side of the urethane resin skin layer, and each of the recesses has a depth in a thickness direction of the synthetic resin skin material composite, such that the recesses extend from the urethane resin skin layer into the cushion layer beyond an interface between the urethane resin skin material and the cushion layer that is present in a region without a recess, as well as a method of producing a synthetic resin skin material composite.

A method comprising providing a polymeric substrate having a melting point of from about 130° C. to about 190° C., and locating a material layer onto the substrate, wherein the material layer comprises one or more polymeric materials that liquefy upon exposure to temperatures of at least about 100° C., to blend with a softened portion of the polymeric substrate. Upon exposure of one or more of the substrate and the material layer to a stimulus, the temperature is increased in a predetermined temperature zone of one or more of the substrate and material layer to cause blending of the one or more polymeric materials of the material layer with the softened portion of the polymeric substrate.

A disposable surgical gown is provided. The gown includes a front panel and sleeves formed from a first spunbond layer, a nonwoven (e.g., SMS) laminate, and a liquid impervious, moisture vapor breathable elastic film disposed therebetween. The gown also includes a first and second rear panels formed from a nonwoven laminate that is air breathable and allows for an air volumetric flow rate ranging from about 20 standard cubic feet per minute (scfm) to about 80 scfm. The gown further includes a collar formed from an air breathable knit material positioned adjacent a proximal end of the gown. The collar defines a neck opening having a v-neck shape adjacent the front panel. The v-neck shape forms an angle of greater than 90° at the neck opening. The combination of features results in a reduced-glare gown that is stretchable and impervious to liquids, yet can still dissipate heat and humidity.

Forming systems and assemblies as disclosed herein comprise a composite material comprising a structural component and a resin component combined with the reinforcing component. A forming element is disposed within the composite material and has a coefficient of thermal expansion that is greater than that of the composite material. The forming element is positioned to provide a desired integral structural reinforcement and/or surface feature to the composite. The composite material may comprise one or more passages extending from a surface thereof to the forming element. The composite material may be cured by heat to take a set configuration and then allowed to cool. The cooling of the composite material and the forming element enables the forming element to contract relative to the composite material and become delaminated therefrom to facilitate easy removal, and thereby provide an improved method and assembly for making structural reinforcing features in composite structures.

This invention relates to a wind turbine blade component, a method of manufacturing such a wind turbine blade component and a wind turbine blade comprising the wind turbine blade component. The wind turbine blade component comprising a stack of layers arranged in a first group and in a second group, wherein the layers of each group has the same width. The layers of each group is continuously offset in an edgewise direction to form a tapered edge profile. The first group of layers may be arranged relative to the second group, or in an alternating order. The layers of the first group may further have a first length which is greater than a second length of the layers of the second group.