A carrier plate for a preform manufacturing arrangement for producing a preform element for a wind turbine blade is provided, adapted to receive either a mold element with preform building material on a receiving surface or to directly receive the preform building material on the receiving surface, with the carrier plate having a rectangular shape with a longer longitudinal axis and a shorter transverse axis, wherein the carrier plate is flexible around the longitudinal axis but stiffened against bending around the transverse axis, and stretchable along the transverse axis but stiff along the longitudinal axis.

A press tool for a press assembly includes an additive manufactured body including a plurality of stacked layers of additive manufacturable material extending between an interior side and an exterior side. The interior side has a part forming surface including a surface profile for forming a part. The exterior side has a plurality of hollow cores defined by longitudinal walls and lateral walls meeting at joints. Press inserts are coupled to the longitudinal walls and the lateral walls at the exterior side. The press inserts are configured to be pressed inward by a pressing load during a pressing operation for forming the part. The press inserts distribute the pressing load along the longitudinal and lateral walls.

A setup device for manufacturing a fuselage barrel, made of a fiber composite material, for an aircraft is provided. The setup device for the purpose of reinforcement includes several stringers arranged so as to be spaced apart from each other. The stringers include a base structure to form a load-bearing rigid substructure that is connected to an outwardly curved supporting surface that can be adjusted by means of actuators for the positive setup of the fuselage barrel to be manufactured with the help of form channels for accommodating the stringers. The actuators, designed as pressure-means cylinders, move one or several form channels in radial direction. The form channels are interconnected longitudinally by means of a flexible intermediate element for forming a ring-shaped supporting surface that is closed in a vacuum-tight manner and that overall is able to adjust itself in radial direction.

A method and system for composite molding, and the method includes additively manufacturing a mold shell that includes a part forming cavity. The method includes filling at least a portion of the mold shell with a strengthening agent. The method includes hardening the strengthening agent to form a mold, and laying-up a composite material on the part forming cavity. The method includes curing the mold to form a composite part.

A method of forming a metal mold for casting a micro-scale dry adhesive structure includes securing a master patch of material including a micro-scale dry adhesive structure on a plating fixture, electroforming the metal mold on the patch of material, and removing the metal mold from the plating fixture and patch of material.

A mold for coating a pipeline section with molten coating material from an injection molding machine, wherein the mold Includes a shell of impervious material reinforced by an exoskeleton of non-distensible material. An assembly for supporting a mold including a plurality of mutually separable shell bodies for coating a pipeline section, wherein the assembly includes motorized opening and closing of the shell bodies in a straight line. An assembly for supporting a bent pipeline section wherein the assembly includes a base and a pair of arms extending from the base, wherein each arm includes a respective clamping collar for clamping a bent pipe section between the arms. A vehicle for induction heating a bent pipeline section, wherein the vehicle includes a helical induction coil; and wheels arranged to guide movement of both ends of the induction coil through a tubular inside face of a bent pipeline section.

A display system includes: an imaging unit that images a mold from below; and a display unit that displays an image taken by the imaging unit together with a carry-in range of the mold in order to transport the mold in place between the stationary platen and the moving platen.

A collapsible, coiled mandrel, for use in co-curing of a hollow carbon-epoxy structure such as a stringer in aircraft construction, is made of a coil having an outer coil shape resistant to external compression forces when used as a mandrel during lay-up and curing, and is collapsible when an end of the coil is pulled along its longitudinal axis so that it can be easily removed after curing and discarded.

The subject matter disclosed herein relates to a method for assembling at least one panel and frames for producing part of an aircraft fuselage, the method including shaping the panel on support surfaces of a tool, wherein it includes holding each frame clamped against at least one sliding support surface arranged in a transverse plane, the sliding support surfaces of the various frames and the support surfaces being secured to the same tool and positioned relative to one another, and in putting in place permanent attachment elements for connecting the panel and the frames. The subject matter disclosed herein also proposes a tool for implementing the assembly method.

A stiffened composite panel is fabricated using modular tooling. Composite pre-preg is laid up and formed over forming block modules each of which is assembled by co-linearly arranging a plurality of forming block segments. The formed stiffeners are respectively transferred to individual cure tool modules that are assembled by co-linearly arranging a plurality of cure tool module segments. The stiffeners are assembled by arranging the cure tool modules side-by-side, and a composite skin is placed on the assembled stiffeners. The panel is vacuum bagged using a segmented vacuum bag.