There is provided a curable resin composition capable of obtaining a resin molded body that is excellent in wear resistance and has a high flexural modulus. The curable resin composition according to the present invention contains a polyol compound, an isocyanate compound, a long reinforcing fiber, and a filler, in which the specific gravity of the filler is less than 4 and the average circularity of the filler is 0.65 or more.

A method for making a conductive pre-impregnated composite sheet includes the steps of joining a nanomaterial composite sheet, a fiber-reinforcing sheet and a resin system to form a combined sheet, heating the combined sheet, compacting the combined sheet, and cooling the combined sheet to form conductive pre-impregnated composite sheet including the fiber-reinforcing sheet, and the nanomaterial composite sheet coupled to the fiber-reinforcing sheet, wherein the fiber-reinforcing sheet and the nanomaterial composite sheet are embedded in the resin system.

A manufacturing process, which includes: (i) preparing a preform; (ii) laying the preform within a mold; (iii) heating the mold to a predetermined temperature; and (iv) injecting a modified resin system, wherein the modified resin system is formulated to have a viscosity below a threshold viscosity at a specific temperature and a high level of toughness. In one embodiment, the modified resin system contains a combination of epoxies, a curing agent, core-shell rubber particles, a thermoplastic material in an amount of less than 7% by weight, wherein in a cured condition, the thermoplastic material is separated into aggregate domains from the base resin, each aggregate domain having an island-like morphology.

A lightweight composite material includes a substrate and a carbon fiber layer. The substrate has a first surface and a second surface opposite to each other, and is prepared by impregnating glass fibers with a resinous matrix which is formed by mixing hollow glass microspheres with a thermosettable resin material. The carbon fiber layer is bonded to one of the first and second surfaces of the substrate by thermosetting the thermosettable resin material.

A method of making a fiber reinforced energetic composite is provided. The method includes providing a mold or mandrel defining a shape for the fiber reinforced energetic composite, providing an impregnated fiber layup over the mold or mandrel, and curing the impregnated fiber layup. The impregnated fiber layup includes a fiber layup and polymer resin, the fiber layup formed from a plurality of reinforcing fiber layers and an energetic polymer nanocomposite disposed adjacent one or more of the reinforcing fiber layers with the polymer resin impregnated within the reinforcing fiber layers. The energetic polymer nanocomposite includes core-shell nanoparticles entrained in a thermoplastic polymer matrix where the core-shell nanoparticles include a core made of metal and at least one shell layer made of metal oxide disposed on the core or a core made of metal oxide and at least one shell layer made of metal disposed on the core.

The present invention pertains to a method for producing a long-fiber composite in which a fiber bundle is impregnated with a non-Newtonian resin. More specifically, the present invention pertains to a method for producing a thermoplastic long-fiber composite, wherein the efficiency of a non-Newtonian resin impregnation process is improved using Equation 1 representing the correlation between the penetration pressure, effective viscosity, transverse permeability, and average penetration velocity of the non-Newtonian resin, and the thickness of the fiber bundle.

A method of manufacturing a flywheel comprising: forming a first hollow cylinder from glass fibre composite with magnetic particles dispersed through at least part of the cylinder; curing said first cylinder in a first curing step; forming a second hollow cylinder from carbon fibre composite; and curing said second hollow cylinder in a second curing step.

A thermoplastic surfacer for providing lightning strike protection to a composite component of an aircraft, methods of manufacturing the surfacer, and methods of applying the surfacer to a composite part. The thermoplastic surfacer includes a broadgood having an amorphous thermoplastic resin, one or more fillers embedded into the broadgood, and a lightning strike protection mesh or foil embedded into the broadgood. When applying the surfacer to a composite part of an aircraft, the method includes draping the surfacer on an at least partially unconsolidated composite part, consolidating the at least partially unconsolidated composite part by heating the part to a temperature at or above a melt temperature of a resins used in the part and in the surfacer, and filling at least one surface defect in the consolidated part using the amorphous thermoplastic polymer resin and milled fibers provided in the thermoplastic surfacer.

A fiber reinforced composite component may include interleaved textile layers and ceramic particle layers coated with matrix material. The fiber reinforced composite component may be fabricated by forming a fibrous preform and densifying the fibrous preform. The fibrous preform may be fabricated by forming a first ceramic particle layer over a first textile layer, disposing a second textile layer over the first ceramic particle layer, forming a second ceramic particle layer over the second textile layer, and disposing a third textile layer over the second ceramic particle layer.

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.