The present invention provides a prepreg that has high impact resistance despite being an all-carbon-fiber FRP (CFRP), the prepreg moreover enabling a molding time to be set to five minutes or less and making it possible to reduce molding costs. This prepreg is obtained by impregnating carbon fiber with a matrix resin comprising a mixture of a thermoplastic resin, a thermosetting resin, and a curing agent, wherein: the thermoplastic resin is a phenoxy resin; the thermosetting resin is a urethane acrylate resin; the thermoplastic resin and the thermosetting resin are compounded in a mass ratio of 15:85-35:65 (thermoplastic resin/thermosetting resin); and the curing agent causes cross-linking to occur due to a radical polymerization reaction, and is formed so as to include first and second peroxides having mutually different initiation temperatures, initiation of the second peroxide starting at a temperature at which termination of the first peroxide occurs.

Methods of manufacturing of aerospace structures are disclosed. More specifically, methods of manufacturing relatively lightweight yet strong aerospace structures. In one embodiment, the method includes the addition of a volume of a rigid and flexible polyurethane mixture into a mold to create a composite structure. In one aspect, the method includes the integration of special structures within a larger structure to remove traditionally structurally weak or vulnerable areas.

To provide a method for manufacturing a novel molded article using a commingled yarn and a composite material using a commingled yarn. The method for manufacturing a molded article, includes disposing a commingled yarn containing a continuous reinforcing fiber and a continuous thermoplastic resin fiber on a part of a surface of a prepreg, the prepreg containing continuous reinforcing fibers paralleling at least unidirectionally, and a thermosetting resin impregnated between the continuous reinforcing fibers, and heat-processing the prepreg with the commingled yarn.

The disclosure discloses a preparation method and product of carbon fiber reinforced polymer composites with a designable characteristic structure. The method includes: (a) choosing carbon fabrics as raw material, where a predetermined number of the fabrics are selected to deposit the reinforcement phase; (b) coating all carbon fabrics with resin matrix, placing the fabrics layer by layer, where the carbon fabrics with the reinforcement phases are placed in a predetermined layer, meanwhile a micro power supply is placed in a setting layer during the stacking process, then a prefabricated product is obtained; (c) placing the prefabricated product in a vacuum bag then evacuating and sealing, hot pressing the sealed prefabricated product, finally the carbon fiber reinforced polymer composite product in the vacuum bag after hot pressing is successfully manufactured.

A molded article of a carbon fiber composite material includes at least carbon fibers and a resin composition. The molded article of a carbon fiber composite material is characterized in that the surface roughness Ra thereof is 0.01-2 ?m and in that the tensile shear adhesive strength (F0) thereof when a metal has been adhered to the surface thereof via an adhesive layer that contains an epoxy compound and is 0.1-3 mm thick is 10-40 MPa.

The present invention provides a fast-curing molding process for epoxy resin. The method includes the following steps: S1, mixing epoxy resin A glue and a protein-grafted manganese-zinc-iron oxide nanomaterial well into a colloidal state, and grounding the mixture for 10 to 30 min; S2, adding epoxy resin B glue to the mixed colloid in S1, and performing ultrasonic dispersion at 20 to 30? C. for 10 to 30 min; and S3, placing the mixture obtained after ultrasonic dispersion in S2 in a vacuum environment for 20 to 40 min, then taking the mixture out and injecting the mixture into a mold, placing the mold and the mixed colloid into an electromagnetic induction heater, placing the electromagnetic induction heater in a magnetic field environment with a magnetic field intensity of 1 to 1.5 mT for 2 to 3 h, cooling and then taking them out to obtain the cured epoxy resin.

A three-dimensional (3D) printing methodology is disclosed for freeform fabrication of hydrophobic structures without the use of printed support structures. The build material is directly printed in and supported by a fumed silica-containing yield-stress support bath to form an intermediate article in the support bath material. The intermediate article may be liquid or only partially solidified after being printed into the support bath material. The intermediate article is then heated or irradiated with ultraviolet radiation to initiate cross-linking to solidify the printed intermediate article, forming a finished article.

The present invention provides a fast-curing molding process for epoxy resin. The method includes the following steps: S1, mixing epoxy resin A glue and a protein-grafted manganese-zinc-iron oxide nanomaterial well into a colloidal state, and grounding the mixture for 10 to 30 min; S2, adding epoxy resin B glue to the mixed colloid in S1, and performing ultrasonic dispersion at 20 to 30? C. for 10 to 30 min; and S3, placing the mixture obtained after ultrasonic dispersion in S2 in a vacuum environment for 20 to 40 min, then taking the mixture out and injecting the mixture into a mold, placing the mold and the mixed colloid into an electromagnetic induction heater, placing the electromagnetic induction heater in a magnetic field environment with a magnetic field intensity of 1 to 1.5 mT for 2 to 3 h, cooling and then taking them out to obtain the cured epoxy resin.

A fiber-reinforced resin composite material includes first and second members. The first member includes a first fiber and a first matrix resin. The first fiber includes a reinforcing fiber and is impregnated with the first matrix resin. The reinforcing fiber has a melting point and a tensile strength higher than those of an aliphatic polyamide fiber. The second member includes a stack and a second matrix resin. The stack includes a second fiber and a third fiber filled with the second matrix resin. The second fiber includes the reinforcing fiber. The second matrix resin includes a component common to that of the first matrix resin, and includes a first polyamide resin that includes an aliphatic polyamide resin. The third fiber includes a second polyamide resin that includes an aliphatic polyamide resin and has a melting point higher than that of the first polyamide resin by 7 to 50 degrees centigrade.

A preform for forming a composite structure, such as, but not limited to a panel for a building, house or the like includes a body substantially formed of a reinforcing material. The reinforcing material defines one or more compartments or sections. The compartments are fillable with a granular filler material through which settable liquid matrix material is impregnatable to form the composite structure. There is also disclosed a composite structure, a panel and related methods of forming the preform, the composite structure and the panel.