A fiber-reinforced resin molded article is produced by pressing a plurality of thermoplastic base material sheets, each of which contains a plurality of reinforcing fibers, in a stacked state where the base material sheets are stacked so that the fiber directions (orientation direction of the reinforcing fibers) are alternated. Each base material sheet is provided with a cut including: a plurality of lengthwise cut lines extending parallel to the fiber direction; and a plurality of crosswise cut lines extending parallel to a direction that is perpendicular to the fiber direction. A plurality of cut interruption parts for interrupting the lengthwise cut lines in the fiber direction are formed. The cut interruption parts are arranged in a staggered manner so as to be displaced from each other in the fiber direction.

The invention relates to a method for producing a hollow electrical insulator having the following steps:—providing a core,—winding first wound layers (2) of a first fiber element onto the core,—winding second wound layers (7) of a second fiber element (8) onto an end region (10) of the core, wherein—the first wound layers (2) comprise turns of the first fiber element which include a first winding angle with a main direction of extension (R) of the core,—the second wound layers (7) comprise turns (18) of the second fiber element (8) which include a second winding angle (α2) with the main direction of extension (R) of the core, which second winding angle is larger than the first winding angle, and—an inner region (11) of the core remains free of second wound layers (7). The invention also relates to a hollow electrical insulator and the use thereof.

A wheel suspension unit of a motor vehicle, for example a trailing arm, the trailing arm produced, at least in part, from a fiber-reinforced plastic. The trailing arm including a molded member or tube formed of braided and/or wound continuous fibers. The continuous fibers of the molded member or tube interlinked with a plastic matrix. The shape of the molded member or tube predefines the basic shape of the trailing arm with the trailing arm being of a curved and/or angled design

Disclosed are embodiments of a three-dimensional (3D) printer for building 3D objects with layer based, additive manufacturing techniques. The hot end can be moved in a horizontal plane parallel a planar printing surface of the printing bed while the printing bed can be moved perpendicular to the planar printing surface to print a 3D object. The hot end can be part of an extrusion guide assembly. The 3D printer can auto-level the printing bed.

This relates to a composite structural element, in particular a rib or a spar, specifically for use in a torsion box of an aircraft structure such as a vertical tailplane, wherein the structural element defines a coordinate system with a first axis “a” wherein the structural element comprises a substantially planar main section defining a coordinate system with a first axis “a” extending along the longitudinal axis “L” of the structural element and a second axis “b” extending perpendicular to said longitudinal axis “L” within the planar main section and defining an angle of +90° with the first axis “a”, wherein the structural element contains a lay-up of single plies consisting of a fiber-reinforced composite material with a substantially unidirectional fiber orientation.

A fiber reinforced composite, a component for a wind turbine and a method for manufacturing a component for a wind turbine are provided. The fiber reinforced composite includes a plurality of first fibers, the first fibers being arranged in a unidirectional or biax-configuration, a plurality of second fibers, the second fibers being arranged perpendicularly with respect to a lengthwise direction of the first fibers, and a resin impregnating the first and second fibers, wherein a E-modulus of the resin equals an E-modulus of the second fibers. Since the E-modulus of the resin and the E-modulus of the second fibers are equal, an early initiation of fatigue cracks is avoided.

In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.

Provided is a method for fabrication of a profile for a spar cap for a wind turbine blade, wherein the profile is fabricated in a pultruding process using one or more strands and/or layers of unidirectional fibres or rovings of unidirectional fibres arranged along a longitudinal direction of the profile and a tool for moulding of the fibres, wherein one or more additional fibres or rovings of additional fibres are introduced in the pultruding process prior to the moulding, wherein the additional fibres are arranged under an angle to the unidirectional fibres, and/or wherein one or more surficial fibres or rovings of surficial fibres are introduced in the pultruding process after the moulding, wherein the surficial fibres are arranged on the outer surface of the moulded profile.

The present invention relates to manufactured articles consisting of the coupling of at least two polyamide-based parts, one of which consists of a polyamide matrix, preferably loaded with a dispersed filler, and the other consists of a polyamide matrix reinforced with fibres in their turn made of polyamide. The invention also relates to a process for the production of these manufactured articles. The manufactured articles of the invention have high mechanical strength but, unlike similar manufactured articles, they are made of a single polymer.

A composite structural element comprising a substantially planar main section defining a coordinate system with a first axis extending along a longitudinal axis of the structural element and a second axis extending perpendicular to the longitudinal axis within the planar main section. The structural element contains a basic lay-up of single plies, each comprising a fiber-reinforced composite material with a substantially unidirectional fiber orientation. The lay-up comprises N plies arranged from top to bottom in the following form: [[α, β]M; [γ]K; [β, α]M], wherein α, β and γ represent one ply having an angle enclosed between the first axis and the unidirectional fiber orientation of the one ply, respectively, [x]y means y plies each having angle x; [x, y]z means z pairs of plies, K and M are both positive integers equal to or greater than 1: N=4.Math.M+K.