This specification discloses an article of manufacture. The article of manufacture has at least one structural blank and at least one guide. The structural blank has a plurality of oriented fiber plies in a thermoplastic matrix. The guide has a plurality of random dispersed fibers in a thermoplastic matrix. The guide is affixed to the structural blank by injection molding and over molding the guide onto the structural blank. The article of manufacture can take a number of forms for use in industries such as aircraft, automobiles, motorcycles, bicycles, trains or watercraft.

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.

A method of forming a gas diffusion layer includes causing, at least in part, a stack of layers to be arranged between compressing surfaces of a press, the stack of layers including a plurality of gas diffusion layers. The method also includes causing, at least in part, the press to apply one or more compression cycles to the stack of layers to reduce a combined, uncompressed thickness of the plurality of gas diffusion layers between about 2% and about 30%.

The invention relates to a multilayer prepreg comprising a first and a second fiber prepreg, one or two micaceous prepregs and B staged thermosetting resin, which may be different for each layer or identical. The micaceous prepregs are positioned on the top (outside) of the fiber prepregs. There may be plurality of further fiber prepregs. The micaceous prepregs preferably comprise mica flakes in the form of a mica paper. The use of such prepreg as surfacing layer at the top of a composite material or near the top of a composite material can determine an improvement in burn-through and fire retardancy performance of composite materials. It is also disclosed a cured composite panel, such as an aircraft part, obtainable by curing the multilayer prepreg to a C stage.

A ready to use surface veil and surface film integrated prepreg layer which is suitable to use in the production of lightweight structural parts/panels with class A surfaces includes a curable bottom base resin formulation including a curable bottom base resin, at least one first toughening agent, at least one accelerator, at least one curing agent and at least one hardener. The prepreg layer further includes a release paper that is coated with the curable bottom base resin formulation to obtained curable bottom base resin formulation coated release paper as a first resin film; a reinforcement fabric; an outer resin formulation including the outer resin which is the curable bottom base resin being 10% more viscous than the resin, at least one thermoplastic toughening agent, at least one accelerator, at least one curing agent and at least one hardener agent.

A method for manufacturing a turbine nozzle vane made of ceramic matrix composite material, wherein the vane is manufactured using a first fibrous preform including a hollow central section intended to form a fibrous reinforcement of an airfoil of the vane to be obtained, and a pair of second fibrous preforms each having an opening with a shape of the airfoil of the vane to be obtained.

A composite structural panel for use in bridge structures, and method of manufacturing same, comprises a top panel and a bottom panel separated by and attached to at least one, but preferably a plurality, of structural composite preforms which may be fabricated by a continuous manufacturing process and may be saturated by resin using a continuous wetting process. The composite preforms may take any cross-sectional shape but are preferably trapezoidal. The top and bottom panels may be fabricated from a plurality of layers of woven fabric layers and non-woven fabric layers which are saturated with a resin that is subsequently cured using cure processes known in the art. The composite structural panel of the invention is usable as a flat structural member for use as bridge decking, ramps, trestles, and any application requiring a structural panel.

An embodiment relates to a multilayer graphite sheet with excellent electromagnetic shielding capability and thermal conductivity, and a manufacturing method therefor, wherein the multilayer graphite sheet has a multilayer structure of five or more layers in total and can be manufactured to have a thick thickness of 70 μm or more such that the electromagnetic shielding capability can be significantly improved. In addition, the multilayer graphite sheet is manufactured by graphitizing a hybrid laminate in which heterogeneous materials are mixed such that thermal conductivity and electromagnetic shielding capability can be simultaneously realized at a lower cost, thereby being useful as a thick film sheet which used in various applications such as home appliances and electric vehicles.

One or more aspects of the present disclosure are directed to components having an optical element that imparts structural color to the component or article. The present disclosure is also directed to articles of manufacture including the component having an optical element, and methods for making components and articles having an optical element that imparts structural color.