The present invention relates to a method of molding a shell part of a wind turbine blade comprising the steps of providing a mold (64) comprising a mold cavity (66) with a root end (68) and an opposing tip end (70), arranging one or more preformed sheets (72a, 72b, 72c) in the mold cavity (66), wherein each preformed sheet comprises a mixture of fibre rovings (82) and a binding agent, wherein the fibre rovings are at least partially joined together by means of the binding agent, and injecting the one or more preformed sheets (72a, 72b, 72c) with a resin to mold the shell part. The present invention also relates to a shell part of a wind turbine blade obtainable by said method, to a preformed sheet for use in said method and to a method of manufacturing said preformed sheet.

The disclosure provides an interior trim part for a motor vehicle having a sliding or panoramic roof comprising a headliner and a stiffening frame attached to the headliner and enclosing and stabilizing an opening in the headliner enclosing the sliding or panoramic window, the stiffening frame being made of a fiber-reinforced composite material comprising a fiber mat and a textile lattice material, the textile lattice material being applied over a surface of the fiber mat and impregnated together therewith.

An iso-grid composite component according to an exemplary aspect of the present disclosure includes a spacer transverse to a uni-tape ply bundle, the spacer interrupted by the uni-tape ply bundle.

A plurality of structural fibers are laid onto a substrate. The plurality of structural fibers are stitched together with a thread in a specified stitching pattern to form a composite preform. The thread in the specified stitching pattern secures the structural fibers to each other such that the structural fibers provide a tailored load path within the composite preform and presents a visible image on an outer surface of the composite preform.

A plurality of structural fibers are laid onto a substrate. The plurality of structural fibers are stitched together with a thread in a specified stitching pattern to form a composite preform. The thread in the specified stitching pattern secures the structural fibers to each other such that the structural fibers provide a tailored load path within the composite preform and presents a visible image on an outer surface of the composite preform.

A method for manufacturing an aeronautical panel with improved impact and damping behaviors. The method is applicable not only to flat panels but also to curved or highly curved panels, whatever their size and the shape of their core. The manufactured sandwich panels comprise dry fiber mats made from fabric material and/or non-crimp fabric material. In a particular embodiment, the fabric material and/or the non-crimp fabric material comprise dry fibers which are recycled and/or reused fibers.

A method for producing a composite material in which a first fabric and a second fabric made from a fiber material are impregnated with a thermosetting resin and integrally molded, wherein a resin flow path through which thermosetting resin flows is provided between the first fabric and the second fabric, and the first fabric and the second fabric are impregnated with thermosetting resin from the resin flow path as well as being impregnated with thermosetting resin from the surface.

A method for producing a composite material in which a first fabric and a second fabric made from a fiber material are impregnated with a thermosetting resin and integrally molded, wherein a resin flow path through which thermosetting resin flows is provided between the first fabric and the second fabric, and the first fabric and the second fabric are impregnated with thermosetting resin from the resin flow path as well as being impregnated with thermosetting resin from the surface.

A composite yoke includes a plurality of packs of unidirectional plies and at least one pack of chopped fibers disposed between two adjacent packs of unidirectional plies. A method of manufacturing a composite yoke includes arranging a plurality of plies of unidirectional fibers to form a first pack of unidirectional plies, arranging a layer of chopped fibers on the first pack of unidirectional plies, arranging a plurality of plies of unidirectional fibers on to form a second pack of unidirectional plies on the layer of chopped fibers, curing the composite yoke to form a cured composite yoke, and cutting excess material from the first pack of unidirectional plies, the layer of chopped fibers, and the second pack of unidirectional plies to form a plurality of arms.

An airfoil including a plurality of composite plies extending from a leading edge to a trailing edge and between a tip and a root. The airfoil further includes a frangible airfoil portion at the tip extending between the leading edge and the trailing edge and extending between the tip and a frangible line along a span including a first plurality of composite plies. The frangible airfoil portion includes a first plurality of composite plies including fibers having a first fiber modulus. The airfoil further includes a residual airfoil portion extending from the frangible line to the root along the span including a second plurality of composite plies. The second plurality of composite plies including one or more plies having a second fiber modulus. The second fiber modulus is greater than the first fiber modulus. Further, the residual airfoil portion meets the frangible airfoil portion at the frangible line.