A combustion engine is provided that includes an engine block with a fiber material in a resin. The engine block defines a piston bore and a bore liner positioned within the piston bore and includes a substrate and a coating positioned on an interior surface of the substrate. An exterior surface of the substrate defines a retention feature.

A protective case for electronic device includes an inner shell, an outer shell, and a magnetic interlayer that fits and in contact with the inner shell and the outer shell, wherein: the magnetic interlayer includes an interlayer base material and a magnetic part, the magnetic interlayer is provided with a through installation hole, and the magnetic part is fixedly embedded in the installation hole, the thickness of the magnetic part matches with the depth of the installation hole, the interlayer base material includes a hot-melt base material and reinforcing fiber yarn contained in the hot-melt base material, and the hot-melt base material is filled between the magnetic part and the inner side wall of the installation hole.

The present invention provides a fiber-reinforced composite film with omnidirectional stretchability on which an auxetic structure 100 is formed integrally with the film on a film, wherein the auxetic structure 100 comprises a plurality of space regions 130 in the form of single closed curves regularly arranged on the film; an island 120 formed surrounded by the space region 130; and a connection portion 110 formed at regular intervals by the space region 130 to connect adjacent islands 120; wherein the film, island 120 and connection portion 110 are plastic materials reinforced with fibers wherein the space region 130 is filled with the elastic auxiliary member 20 and a manufacturing method thereof.

The present application relates to a fiber reinforced composite. More particularly, the present application relates to a fiber reinforced composite comprising a polyamide-based resin and an aramid staple fiber, and articles comprising the same.

The present invention is an optical fiber unit (cable) made from a coated optical fiber with UV-curable resin that is integrated into a cross-section of Fiber-reinforced polymer (FRP) composite to provide more mechanical protection for the optical fiber. In the first stage, the optical fiber is covered with a coating of acrylic or silicon UV-curable resin, and then all or a part of the cross-section of the optical fiber is placed in a fiber-reinforced polymer (FRP) that is cured by UV in Pultrusion process. Then, the composition is covered by thermoplastic polymers. At least one optical fiber is regularly located on the cross-section or outer surface of an FRP in such a way that all or part of the cross-section of the optical fiber is placed in the cross-section of FRP cross-section.

A warp-directional stretch fabric that defines two right faces and is formed from warp yarns defined by a nylon and fill yarns defined by an aramid. The fabric can be incorporated into a toothed belt, for example a transmission belt, to produce a belt that has enhanced structural and resistance capabilities while capable of being produced at a lower cost than prior art belts. A method of producing an improved toothed belt including the fabric is also provided.

A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

A joint member (100) includes a metal component (12) and a composite component (14) which are joined by a joint (10) formed at a non-planar joint interface (18) defined by a textured surface portion (28) of the metal component (12) and a solidified melted area (24) of the composite component (14). The solidified melted area (24) adjacent to the joint interface (18) is characterized by a plurality of non-contiguous solidification boundaries (22) and a non-contiguous dispersion of porosity (16). A method includes forming a textured surface portion (28) on the metal component (12), pressing the textured surface portion (28) into the surface of the composite component (14) to form depressions (32) in the composite component (14), such that a joint interface (18) is defined by the surfaces of the textured surface portion (28) and the composite depressions (32), heating the joint interface (18) to melt an area of the composite component (14) adjacent to the joint interface (18), and solidifying the melted area (24) to the form a joint (10) at the joint interface (18).

A joint member (100) includes a metal component (12) and a composite component (14) which are joined by a joint (10) formed at a non-planar joint interface (18) defined by a textured surface portion (28) of the metal component (12) and a solidified melted area (24) of the composite component (14). The solidified melted area (24) adjacent to the joint interface (18) is characterized by a plurality of non-contiguous solidification boundaries (22) and a non-contiguous dispersion of porosity (16). A method includes forming a textured surface portion (28) on the metal component (12), pressing the textured surface portion (28) into the surface of the composite component (14) to form depressions (32) in the composite component (14), such that a joint interface (18) is defined by the surfaces of the textured surface portion (28) and the composite depressions (32), heating the joint interface (18) to melt an area of the composite component (14) adjacent to the joint interface (18), and solidifying the melted area (24) to the form a joint (10) at the joint interface (18).