A fiber composite material and a manufacturing method thereof are provided. The fiber composite material includes: a fiber prepreg layer including a first resin and fibers impregnated with the first resin; and a plurality of strip-shaped composite resin layers including multi-layered carbon nanotubes and a second resin disposed on the fiber prepreg layer, wherein the plurality of the strip-shaped composite resin layers and the fiber prepreg layer together form a hollow tubular body, and a length direction of the plurality of strip-shaped composite resin layer is at an angle of from 0 degree and less than 90 degrees with respect to an extending direction of the fiber prepreg layer.

A method for manufacturing a composite part includes preparing a stack of plies made of a starting material, applying a vacuum bag to the stack of plies, and subjecting the stack of plies to a temperature and pressure cycle in an autoclave. The starting material is a laminate material of resin matrix reinforced with a fiber material. The matrix has a core layer of semi-crystalline thermoplastic resin and a pair of outer layers of amorphous thermoplastic resin arranged on opposite sides of the core layer. The glass transition temperature of the amorphous thermoplastic resin is below the melting point of the semi-crystalline thermoplastic resin. The autoclave temperature cycle heating rapidly the stack of plies to a working temperature above the transition temperature, but below the melting point, keeping the stack of plies at the working temperature during a time period for compaction alone; and cooling the stack of plies.

An erosion resistant aerodynamic fairing for a rotor blade. A fairing body is formed from at least one reinforcing fiber layer set in a cured resin. An erosion resistant pre-form is fixed to an outer surface of the fairing body. The erosion resistant pre-form comprises a thermoplastic film outer layer fused to a fiber substrate. The fiber substrate of the erosion resistant pre-form is impregnated with the cured resin of the fairing body which fixes at the preform to the fairing body.

A horological component is disclosed, which comprises at least one portion made of colored forged carbon comprising cut carbon fibers, secured to one another by a matrix comprising at least one resin as component, and at least one pigment, the pigment taking the form of solid particles that cannot be mixed with, or are not soluble in, the resin or resins of which the matrix is composed, and the particles of pigment being situated on the surface of at least some of the carbon fibers and located in one or more predefined regions of the portion of horological component. A manufacturing method allowing such a horological component to be produced is also disclosed.

An interlayer sheet for a spar cap is provided. The interlayer sheet includes a first fibre layer having a first plurality of fibres with a first upper fibre surface and a first lower fibre surface, and a second fibre layer having comprising a second plurality of fibres with a second upper fibre surface and a second lower fibre surface. The first fibre layer is arranged on top of the second fibre layer, such that the first lower fibre surface is in contact with the second upper fibre surface. The first fibre layer is of a different characteristic than the second fibre layer. A number of the interlayer sheets may be arranged between a plurality of pre-cured fibre-reinforced elements to make a spar cap for a wind turbine blade.

An object of the present invention is to obtain a fiber-reinforced composite material achieving both lightweight properties and mechanical properties at a high level. The present invention provides a fiber-reinforced composite material including a resin (A) and a reinforcing fiber (B), and having: a porous structure portion having micropores with an average pore diameter of 500 ?m or less as measured by a mercury intrusion method; and a coarse cavity portion defined by the porous structure portion and having a maximum length of more than 500 ?m as a cross-sectional opening portion.

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.

An object of the present invention is to provide a prepreg and a laminate for producing a laminate suitable as a structural material, which have excellent joining strength and can be firmly integrated with another structural member by welding. The present invention provides a prepreg including the following structural components: [A] reinforcing fibers, [B] a thermosetting resin, and [C] a thermoplastic resin, wherein [A] has a surface free energy, measured by a Wilhelmy method, of 10 to 50 mJ/m.sup.2, [C] is present on a surface of the prepreg, and the reinforcing fibers [A] are present, which are included in a resin area including [B] and a resin area including [C] across an interface between the two resin areas.

A method for producing a fiber composite laminate, including the steps of applying pressure and/or heat to a first preform, which has one or more dry fiber layers and a thermoplastic elastomer, such that the thermoplastic portion of the thermoplastic elastomer completely impregnates the dry fiber layers of the first preform in at least one first region and only partially impregnates the dry fiber layers in at least one second region and, in a thermosetting polymer matrix, impregnating and curing the fiber layers of the second region of the first preform that are still dry and have not been impregnated with the thermoplastic portion of the thermoplastic elastomer.

Disclosed herein is a method of forming a composite part. The method includes heating an unconsolidated mat including a first thermoplastic, a second thermoplastic, and reinforcing fibers to a first temperature. The first thermoplastic includes a first melting temperature and the second thermoplastic includes a second melting temperature greater than the first melting temperature. The first temperature is greater than the second melting temperature. The method includes compressing the unconsolidated mat, while heated, into a composite fiber-reinforced consolidated sheet. The method includes reheating the composite fiber-reinforced consolidated sheet to a second temperature, wherein the second temperature is above the first melting temperature and below the second melting temperature and, while reheated, forming the composite fiber-reinforced consolidated sheet into a desired shape.