A system for manufacturing a part that includes a mold, a first fixation component, fixed to the mold, second fixation components, each configured to be fixed to a consolidated laminate sheet, third fixation components, each fixed to the mold. The system also includes tension straps. The first fixation component is configured to attach the consolidated laminate sheet to the mold so that the consolidated laminate sheet does not translationally move relative to the forming surface of the mold. Each one of the second fixation components is configured to attach the tension straps to the consolidated laminate sheet. Each one of the third fixation components is configured to attach the tension straps to the mold so that the tension straps are movable relative to the mold. The system also includes a heating assembly and a strap retraction mechanism, configured to retract the tension strap.

A method of manufacturing a composite component according to various aspects of the present disclosure includes disposing a fiber preform in a mold. The fiber preform includes a first portion having a first edge and a second portion having a second edge. The first edge and the second edge cooperate to at least partially define a gap. One of the first portion or the second portion includes a first ferromagnetic material and the other of the first portion or the second portion includes a first magnetic or magnetizable component. The method further includes closing the gap by generating a magnetic field from the first magnetic or magnetizable component. The method further includes injecting a polymer precursor into the mold. The method further includes forming the composite component by solidifying the polymer precursor to form a polymer. The composite component includes the fiber preform and the polymer.

A system for fabrication of a wind turbine blade including a laser projection which identifies the dimensions for a plurality of layup segments; determines the sequence of layup segments within first and second sections of the mold, wherein the sequence of layup segments within the second section of the mold are synchronized with the layup segments within a first section of the mold. The system also includes a projection device visually depicting the boundaries of a plurality of layup segments onto the mold. This system automates fabrication of composite structures by setting a pace for each task and ensuring operators complete each task within the allotted period. The projection system and layup delivery mechanism can advance with respect the mold to ensure the pace is maintained and an overall product cycle time is adhered to.

An end of arm tool (EOAT) for use during manufacture of parts using one or more pre-impregnated composite plies is disclosed. In an embodiment, the EOAT includes a mechanical gripper arrangement with first and second fingers configured to supply a compressive force to grip a pre-impregnated composite ply therebetween. At least one of the first and second fingers include a roller member to engage opposite surfaces of the pre-preg ply and supply a compressive gripping force. The roller member on either or both the first and second fingers preferably include a torque regulator to selectively adjust an associated roller member's resistance to rotation via supply of a rotational torque resistance.

Described herein are methods and systems for forming composite stringer assemblies or, more specifically, for shaping composite charges while forming these stringer assemblies. A system comprises a bladder, having a bladder core, and a bladder skin. The bladder core is formed from foam. The bladder skin is formed from an elastic material and encloses the bladder core. When a composite stringer assembly is formed, the bladder is positioned over a charge base. The charge base later becomes a stringer base, such as a fuselage section or a wing skin. A charge hat is then positioned over the bladder and is conformed to the bladder. A combination of the bladder skin and the bladder core provides support during this forming operation and later while the stringer assembly is cured. In some examples, the bladder core is collapsible for the removal of the bladder from the cavity of the stringer assembly.

A system for fabricating a composite structure includes a ply carrier including a ply support surface configured to support at least one composite ply. The system includes a carrier transfer device configured to convey the ply carrier. The system includes a lamination system configured to selectively apply the at least one composite ply to the ply support surface of the ply carrier. The system includes a transfer system configured to remove the ply carrier from the carrier transfer device and to apply the at least one composite ply to at least a portion of a forming surface of a forming tool. The system includes a forming system configured to form the at least one composite ply over the at least a portion of the forming surface of the forming tool.

A composite material blade molding method is for molding a composite material blade by curing a prepreg. The composite material blade has a back-side blade member and a belly-side blade member which are superposed and joined. The composite material blade molding method includes: a lamination step for forming a back-side laminate in a back-side molding die and forming a belly-side laminate in a belly-side molding die; an inner surface cowl plate disposition step for disposing an inner surface cowl plate for maintaining an inner space formed by the back-side laminate and the belly-side laminate; a die mating step for die-mating the back-side molding die and the belly-side molding die and disposing a foaming agent in the inner space maintained by the inner surface cowl plate; and a curing step for heating and expanding the foaming agent and heat-curing the back-side laminate and the belly-side laminate.

A method for manufacturing an aeronautical sandwich panel with a honeycomb core and results in a core sealed to prevent infused resin from entering into the honeycomb core open cells while improving its mechanical properties, especially for curved or highly curved panels. In further embodiments, the invention proposes the automation of this process.

A tool for creating a self-stiffened panel, which comprises a support, a set of punches and a channel delimited between two punches, for each punch, a first securing arrangement including a slider that is able to move in translation on the support and at least one hook secured to the slider, and a second securing arrangement including at least one nose integral with the punch, and an actuating arrangement that moves the slider from a securing position in which each nose is located between the support and a hook, to a release position in which the hooks are offset with respect to the noses. With such a tool, each punch is held in position over its length, which ensures correct positioning during lay-up, even in the event of the tool being rotated.

A method for making a first ply for laying up a fibrous preform on a tool. An attachment zone is made on the laying up surface of the tool. The zone is integral with the laying up surface of the tool. A polymer is deposited by additive manufacturing on the surface of the tool. The polymer deposit passes on the attachment zone. The first ply is laid up by activating the tackiness of the polymer deposited using additive manufacturing, so as to make the deposited fibers adhere to the material deposited by additive manufacturing.