A method for fabricating a laminated composite work piece includes providing a first layer of carbon fiber. The first layer extends continuously across the entire area of the work piece. A second layer is placed adjacent to the first layer. The second layer includes a first fiber material extending across a first portion of the work piece, and a second fiber material extending across a second portion of the work piece. The work piece is cured and provides a case component of an information handling system.

A composite sheet material and method for forming the same is provided that includes a substrate, a matrix, and a cover sheet. The substrate has a first face surface, a second face surface, and a plurality of edges, and includes a thermoplastic material. The matrix is attached to the substrate. The matrix includes a support component having a first melting point, and a thermoplastic component having a second melting point. The second melting point is less than the first melting point. The cover sheet imparts one or more surface characteristics to the composite sheet material during thermo-pressure formation of the composite sheet material.

Problems of high impact resistance and warpage of a molded body are solved by a method for producing a molded body, including: using a mold MA and a mold MB, which are a pair of male and female molds, to compression-mold a material A and a material B in contact with the mold MA and the mold MB, respectively, in which the material A contains a carbon fiber and a thermoplastic resin M1, and the material B contains a glass fiber and a thermoplastic resin M2, the molded body includes a pair of side walls and a connecting wall that is connected to the side walls, the molded body has a wave shape in cross section, and a relationship between a flatness Fa of the molded body and a height h of the side wall satisfies 0Fa/h<1.3.

Disclosed are a multilayer prepreg structure and a method of manufacturing the same. The multilayer prepreg structure includes a prepreg layer formed by impregnating a carbon fiber fabric with a first resin, and a fixed layer formed of a second resin having a higher curing rate than the first resin and provided on one surface of the prepreg layer.

A composite sheet material and method for forming the same is provided that includes a substrate, a matrix, and a cover sheet. The substrate has a first face surface, a second face surface, and a plurality of edges, and includes a thermoplastic material. The matrix is attached to the substrate. The matrix includes a support component having a first melting point, and a thermoplastic component having a second melting point. The second melting point is less than the first melting point. The cover sheet imparts one or more surface characteristics to the composite sheet material during thermo-pressure formation of the composite sheet material.

A process for preparing a composite part, the process comprising: recovering unsaturated resin prepreg scrap; combining the recovered unsaturated resin prepreg scrap with a second resinous thermosetting component; and co-molding the prepreg scrap and resinous thermosetting component together under a pressure of 25 to 4000 psi and at a temperature of 100-400 F.

A method is described for producing a fiber-reinforced plastic substrate that simultaneously satisfies three points of joinability, mechanical characteristics, and productivity, the method including the following components [A], [B], and [C], wherein at least the following drawing step, first impregnating step, second impregnating step, and take-up step are continuously and sequentially performed while the component [A] is caused to run: [A] a reinforcing fiber [B] a thermoplastic resin [C] a thermosetting resin <drawing step> step of drawing a continuous reinforcing fiber sheet containing the component [A]; <first impregnating step> step of impregnating either the component [B] or the component [C] from one surface of the continuous reinforcing fiber sheet to obtain a fiber-reinforced plastic intermediate in which either the component [B] or the component [C] is disposed on a first surface; <second impregnating step> step of impregnating the other of the component [B] or the component [C] from a second surface opposite to the first surface to obtain a fiber-reinforced plastic substrate; and <take-up step> step of taking up the fiber-reinforced plastic substrate.

A method is described for producing a fiber-reinforced plastic substrate that simultaneously satisfies three points of joinability, mechanical characteristics, and productivity, the method including the following components [A], [B], and [C], wherein at least the following drawing step, first impregnating step, second impregnating step, and take-up step are continuously and sequentially performed while the component [A] is caused to run: [A] a reinforcing fiber [B] a thermoplastic resin [C] a thermosetting resin 2<drawing step> step of drawing a continuous reinforcing fiber sheet containing the component [A]; <first impregnating step> step of impregnating either the component [B] or the component [C] from one surface of the continuous reinforcing fiber sheet to obtain a fiber-reinforced plastic intermediate in which either the component [B] or the component [C] is disposed on a first surface; <second impregnating step> step of impregnating the other of the component [B] or the component [C] from a second surface opposite to the first surface to obtain a fiber-reinforced plastic substrate; and <take-up step> step of taking up the fiber-reinforced plastic substrate.

A blade including a structure with aerodynamic profile including two opposite skins obtained by three-dimensional weaving of a fibrous reinforcement densified by a matrix, and a longeron including a fibrous reinforcement obtained by three-dimensional weaving and densified by a matrix, the longeron including a first part extending outside the structure with aerodynamic profile and designed to be connected to a drive hub in rotation of the blade and a second part arranged inside the structure with aerodynamic profile between the two skins. The second part of the longeron has a thickness substantially similar to that of the skins of the structure with aerodynamic profile. In addition, the fibrous reinforcement of the second part of the longeron has the same weaving armor as that of the reinforcement of the skins of the structure with aerodynamic profile.

A method for bonding composite structures which includes providing a first and second composite substrate and coupling a co-cure prepreg tape having chemically protected polymerizable functional groups onto a surface of both the first and second composite substrates. The first and second composite substrates are then cured to the co-cure prepreg tape at a first temperature to form a co-cure prepreg tape portion where the first and second composite substrates are fully cured and the co-cure prepreg tape is partially cured. The co-cure prepreg tape portion of the first composite substrate is then coupled to the co-cure prepreg tape portion of the second composite substrate and a deprotection initiator is applied to facilitate deprotection of the chemically protected polymerizable functional groups and cure the co-cure prepreg tape portion of the first and second composite substrates to form a single covalently bonded composite structure.