A UAV surface coating includes at least a bonding layer, an antioxidant layer, an oxygen-blocking propagation layer and a heat-insulation cooling layer. The coating is fabricated on a surface of a UAV machine body or covers on the surface of the UAV machine body through a composite material matrix. The UAV machine body is made of lightweight material, and the composite material matrix includes a resin-based composite matrix and a ceramic-based composite matrix. Wherein, a thickness of the bonding layer is from 20 ?m to 200 ?m, a thickness of the oxygen-blocking propagation layer is from 20 ?m to 200 ?m, and a thickness of the heat-insulation cooling layer is from 80 ?m to 1000 ?m.

Dry prepregs for ceramic matrix composites are described. The dry prepregs comprise a tow or fabric of ceramic fibers infiltrated with preceramic matrix comprising low levels of an aqueous solvent. The preceramic matrix contains an inorganic portion and a binder system. Binder systems comprising a binder and a plasticizer for the binder are described.

Latent epoxy resin formulations are suitable for liquid impregnation processes for production of fibre composite materials.

A resin-impregnated boron nitride body includes a polymer-derived boron nitride and a resin. A process for manufacturing such a resin-impregnated boron nitride body includes: polymerizing a boron nitride molecular precursor into a preceramic polymer shaping the preceramic polymer to form an infusible polymer body; submitting the polymer body to a thermal treatment to obtain a boron nitride body; impregnating the boron nitride body with a resin; and curing the resin.

A pre-preg composite includes a thermoplastic-thermosetting resin composition and fibers, re-moldability of a molded part prior to final cure, and is capable of being final cured in a free-standing state. The thermoplastic-thermosetting resin includes a crosslinkable thermoplastic resin and a thermosetting resin. A method of making the pre-preg is provided. A method of forming a thermoset article from the pre-preg composite is also provided. The method includes providing a pre-preg composite, pre-curing the pre-preg composite such that the pre-preg composite is cured to an extent of from 2% to 80%, and curing the pre-cured pre-preg composite to form the thermoset article.

An impregnating resin for an electrical insulation body includes a base resin, a filler having nanoscale particles, and a radically polymerizing reactive diluent. The impregnating resin includes a crosslinker for crosslinking the base resin and the reactive diluents. The base resin is an epoxy resin. An electrical insulation body includes the impregnating resin and a method produces the electrical insulation body by production of an impregnating resin having a base resin, a filler having nanosize particles and a free-radically polymerizing reactive diluent.

Dry prepregs for ceramic matrix composites are described. The dry prepregs comprise a tow or fabric of ceramic fibers infiltrated with preceramic matrix comprising low levels of an aqueous solvent. The preceramic matrix contains an inorganic portion and a binder system. Binder systems comprising a binder and a plasticizer for the binder are described.

Provided is an epoxy resin composition containing an epoxy resin (A), an epoxy resin curing agent (B) containing a phenolic curing agent, and a curing accelerator (C),

wherein the epoxy resin (A) contains from 10 to 85 mass % of an epoxy resin (A1) and from 15 to 90 mass % of an epoxy resin (A2), the epoxy resin (A1) having a glycidyloxy group derived from resorcinol, and the epoxy resin (A2) being other than the epoxy resin (A1) and containing an aromatic ring,

the epoxy resin (A2) contains at least one type selected from the group consisting of an epoxy resin (a2-1) having a glycidyloxy group derived from bisphenol F. and an epoxy resin (a2-2) having a glycidyloxy group derived from a polyol having a naphthalene backbone, and

a total content of the epoxy resin (a2-1) and the epoxy resin (a2-2) in the epoxy resin (A2) is 50 mass % or more. Also provided are a cured product of the epoxy resin composition, a prepreg using the epoxy resin composition, a fiber-reinforced composite material and a high-pressure gas container.

Systems and methods relating to a composite flat panel, curved panel, hand-layup panel, prepreg, skin, or composite core matrix panel are provided. In some aspects, it includes a core sandwiched between a first layer and a second layer. At least one of the first layer or the second layer includes a hardening material. At least one of the first layer or the second layer includes a basalt fiber. In other aspects, it includes a hand-layup panel, prepreg, or skin. The hand-layup panel, prepreg or skin includes a layer that includes a hardening material. The layer includes a basalt fiber. In other aspects, it includes a hand-layup panel, prepreg, or skin. It includes a first layer and a second layer, each of the first and second layer includes a hardening material. Each of the first and second layer includes a basalt fiber.

A process for a composite material, including an assembly of one or more reinforcing fibers, impregnated with at least one thermoplastic polymer with a glass transition temperature Tg of less than or equal to 75 C. and a melting point of from 150 C. to less than 250 C. or a Tg of greater than 75 C., the process including: i) a step of impregnating said assembly in bulk melt form with at least one thermoplastic polymer, which is the product of polymerization by polyaddition reaction of a reactive precursor composition including: a) at least one prepolymer P(X)n of said thermoplastic polymer, and b) at least one chain extender, represented by Y-A-Y, ii) a step of cooling and obtaining a fibrous preimpregnate, and iii) a step of processing and final forming of said composite material.