A fabric and a method for making the same. The fabric includes a layer of unidirectionally oriented carbon fibre filaments sandwiched between a first layer of glass fibre rovings and a second layer of glass fibre rovings. The first layer of glass fibre rovings and the second layer of glass fibre rovings are linked by a connecting material.

A fabric and a method for making the same. The fabric includes a layer of unidirectionally oriented carbon fibre filaments sandwiched between a first layer of glass fibre rovings and a second layer of glass fibre rovings. The first layer of glass fibre rovings and the second layer of glass fibre rovings are linked by a connecting material.

A honeycomb-like core member that can be easily manufactured is disclosed, and a structure using such core member is disclosed. The core member has a plurality of flat plate members (a plurality of first flat plates and a plurality of second flat plates), each of which includes a comb teeth portion that has a plurality of notches, which are open in the long side of a rectangular shape of the flat plate member and extend parallel to the short side of the rectangular shape of the flat plate member. The notches are engaged with each other so that the plate members cross each other, and thus, a plurality of hexagonal-cylinder-shaped first cylinder portions and a plurality of triangular-cylinder-shaped second cylinder portions are formed by the plate members.

A composite assembly with a laminate of fibre plies impregnated with a laminate matrix material is disclosed having pad of fibre plies impregnated with a pad matrix material, and a part with a body with protrusions which extend from the body and penetrate at least some of the fibre plies of the pad. The pad is bonded to the laminate by a stepped lap joint or a scarf joint. The assembly is manufactured by pressing the protrusions into the pad, and after the protrusions have been pressed into the pad, curing a pad matrix material impregnating the pad, and bonding the pad to the laminate.

A composite assembly with a laminate of fibre plies impregnated with a laminate matrix material is disclosed having pad of fibre plies impregnated with a pad matrix material, and a part with a body with protrusions which extend from the body and penetrate at least some of the fibre plies of the pad. The pad is bonded to the laminate by a stepped lap joint or a scarf joint. The assembly is manufactured by pressing the protrusions into the pad, and after the protrusions have been pressed into the pad, curing a pad matrix material impregnating the pad, and bonding the pad to the laminate.

A resin-integrated fiber sheet 1 for vacuum forming for producing a fiber reinforced resin molded body through vacuum forming includes: unidirectional continuous fibers 2 that are spread fibers of a continuous fiber group and arrayed in parallel in one direction; bridging fibers 3 lying in directions crossing the unidirectional continuous fibers 2; and thermoplastic resin 4 present on part of the surface of the unidirectional continuous fibers 2 to unify the unidirectional continuous fibers 2 and the bridging fibers 3. A fiber reinforced resin molded body of the present invention is a vacuum formed body in which two or more of the resin-integrated fiber sheets 1 are stacked. A method for producing the molded body of the present invention includes subjecting the resin-integrated fiber sheets 1 to vacuum forming from a lower mold with a vacuum line and pressurizing the sheets with compressed air from an upper mold. Thus, the present invention provides a resin-integrated fiber sheet for vacuum forming having excellent shapeability and avoiding voids, a molded body including the same, and a method for producing the molded body including the same.

The present invention provides stretchable laminates with a flat appearance on the visible surface. The laminates comprise a textile layer, a functional layer, and a plurality of elastic fibers. The plurality of elastic fibers are in a substantially parallel arrangement and the internal distance between adjacent fibers does not exceed the maximum fiber spacing, which depends on laminate thickness in a stretched state. Also provided are garments and footwear comprising the stretchable laminates and methods of producing the stretchable laminates.

The present invention provides stretchable laminates with a flat appearance on the visible surface. The laminates comprise a textile layer, a functional layer, and a plurality of elastic fibers. The plurality of elastic fibers are in a substantially parallel arrangement and the internal distance between adjacent fibers does not exceed the maximum fiber spacing, which depends on laminate thickness in a stretched state. Also provided are garments and footwear comprising the stretchable laminates and methods of producing the stretchable laminates.

A composite structural member including at least one first flange element made from a first composite material, and at least one first web element made from a second composite material. The at least one first web element is connected to at least one first flange element in a non-coplanar manner along a corresponding mutual first edge via a first corner element made from a third composite material, the mutual first edge extending along a first direction. The third composite material includes a corresponding first plurality of third composite material first fibers and a corresponding second plurality of third composite material second fibers embedded in a corresponding third composite material matrix in a non-parallel orientation with respect to the third composite material first fibers, wherein the third composite material first fibers are nominally orthogonal to the mutual first edge or to the first direction.

A reinforcing element for a structural profile, in particular for a round, oval or elliptical structural tube. The reinforcing element comprises: a fiber structure which has a hollow-cylindrical, helically wound mesh of fiber strands and forms an inner shell surface formed to receive the structural profile; and a matrix material into which the fiber strands are respectively embedded and which is formed to be shrinkable by heating so that the fiber structure can be fastened to the structural profile with the inner shell surface by heating the matrix material. Also provided are a structural arrangement with such a reinforcing element, an aircraft or spacecraft with such a structural arrangement, as well as a method for producing such a structural arrangement.