Methods to increase structural performance, strength, and durability of textile-reinforced composite materials are provided. The textile reinforcement may be knitted, for example, in a flat bed weft knitting machine. The method may include pre-stressing a textile reinforcement preform by applying tension. A polymeric precursor may be introduced to the pre-stressed textile reinforcement preform. The polymeric precursor may then be cured or consolidated, followed by releasing of the applied tension to form the composite article comprising polymer and the pre-stressed textile reinforcement. In other aspects, a composite article is provided that has a pre-stressed textile reinforcement structure and a cured polymer. The textile reinforcement may be a knitted, lightweight, seamless, unitary structure. The knitted reinforcement structure may have distinct first and second knitted regions with different levels of pre-stress, thus providing enhanced control over strength, rigidity, and flexibility of the composite article.

The purpose is to shape a laminate with high accuracy by properly causing the slipping between fiber sheets in the laminate during a bending processing of the laminate. A laminate shaping apparatus is equipped with: a holding section (2) for holding a sheet-like laminate (50) composed of a plurality of fiber sheets laminated on each other; and a slipping promotion section (3) which is arranged along a surface of a region other than a region held by the holding section (2) in the laminate (50) and is so configured as to promote the slipping between the fiber sheets in the laminate (50) during the bending processing of the laminate (50).

The purpose is to shape a laminate with high accuracy by properly causing the slipping between fiber sheets in the laminate during a bending processing of the laminate. A laminate shaping apparatus is equipped with: a holding section (2) for holding a sheet-like laminate (50) composed of a plurality of fiber sheets laminated on each other; and a slipping promotion section (3) which is arranged along a surface of a region other than a region held by the holding section (2) in the laminate (50) and is so configured as to promote the slipping between the fiber sheets in the laminate (50) during the bending processing of the laminate (50).

A stiffening element comprises a tension and compression member, a shear member, an attachment member, and a plurality of beads. The tension and compression member is positioned spaced apart from the skin and configured to bear tension or compression forces that stiffen the skin and prevent the skin from buckling or bending. The shear member is connected to the tension and compression member and configured to bear shear forces between the skin and the tension and compression member. The attachment member is connected to the shear member and is configured to connect to the skin. The beads each create out-of-plane feature that is positioned in at least one of the shear member and the attachment member. The beads permit the stiffening element be reshaped to adjust a longitudinal curvature of the stiffening element.

A fiber reinforced resin composite for ballistic protection comprising a plurality of first and second plies wherein the first and second plies further comprise a woven fabric and a polymeric resin. The fabric has a Russell tightness factor of from 0.2 to 0.7 and a cover factor of at least 0.45, The fabric is impregnated with the resin, the resin comprising from 5 to 30 weight percent of the total weight of fabric plus resin. The fabric of each first and second ply comprises regions wherein the fabric is distorted from an orthogonal woven state by a distortion angle of least 30 degrees. The composite may further comprising a third ply having a surface area no greater than 50% of the surface area of a first and second ply. The ratio of the number of first plus second plies to the number of third plies is from 2:1 to 12:1.

A fiber reinforced resin composite for ballistic protection comprising a plurality of first and second plies wherein the first and second plies further comprise a woven fabric and a polymeric resin. The fabric has a Russell tightness factor of from 0.2 to 0.7 and a cover factor of at least 0.45, The fabric is impregnated with the resin, the resin comprising from 5 to 30 weight percent of the total weight of fabric plus resin. The fabric of each first and second ply comprises regions wherein the fabric is distorted from an orthogonal woven state by a distortion angle of least 30 degrees. The composite may further comprising a third ply having a surface area no greater than 50% of the surface area of a first and second ply. The ratio of the number of first plus second plies to the number of third plies is from 2:1 to 12:1.

Provided is a bushing for manufacturing a three-dimensional composite preform using a tow made of a fiber reinforced polymer. The bushing includes a base plate in which one or more through-holes are formed, and a plurality of spools spaced apart from each other on the base plate. A flat top is formed at an end portion of the spools, and grooves are formed on outer surfaces of the plurality of spools in a circumferential direction thereof.

Provided is a bushing for manufacturing a three-dimensional composite preform using a tow made of a fiber reinforced polymer. The bushing includes a base plate in which one or more through-holes are formed, and a plurality of spools spaced apart from each other on the base plate. A flat top is formed at an end portion of the spools, and grooves are formed on outer surfaces of the plurality of spools in a circumferential direction thereof.

A method of manufacturing a wind turbine blade shell part is described. Fibre mats and a root end insert are laid up in a mould part in a layup procedure by use of an automated layup system. The fibre mats are laid up by use of a buffer so that the fibre mats may continuously be laid up on the mould surface, also during a cutting procedure. The root end insert is prepared in advance and mounted on a mounting plate. The root end insert is lowered onto the mould by use of the mounting plate and a lowering mechanism. After the wind turbine blade shell has been moulded, the mounting plate is removed.

An armor plate and method of making an armor plate is provided having the steps of: suspending a carbon fiber weave within a mold; heating aluminum 6061 or 7075 alloy to a molten state; pouring the molten aluminum into the mold having ceramic particulates in the range of 1 to 60 percent by volume of the molten aluminum and in the range of 3-44 microns in diameter; cooling the resultant matrixed aluminum to ambient temperature; and laminating at least two layers of ballistic fiber to the matrixed aluminum.