Systems and methods are provided for processing composite parts. One embodiment is a method for preparing a composite part for assembly. The method includes receiving a mandrel to which a composite part has been molded, and operating a work station to install an indexing feature into a manufacturing excess of the composite part.

This invention relates to a root end structure, a wind turbine blade comprising such a root end structure and a method of manufacturing such a wind turbine blade. The root end structure comprises a plurality of fastening members distributed along a root end of a blade part, wherein a first plurality of pultruded elements are arranged in between the fastening members and a second pultruded element is further arranged at the blade joint ends adjacent to an outermost fastening member. Each first pultruded element has opposite facing second sides each facing a first side of an adjacent fastening member. The second pultruded element has one second side facing the outermost fastening member and another second side facing the blade joint interface. The second pultruded element comprises a transition portion forming a smooth transition for the inner layers extending further along the mould edge surface.

Systems are provided for fabricating a preform for a fuselage section of an aircraft. The system includes advancing a series of arcuate mandrel sections in a process direction through an assembly line, laying up fiber reinforced material onto the arcuate mandrel sections via layup stations, uniting the series of arcuate mandrel sections into a combined mandrel; and splicing the fiber reinforced material laid-up onto the arcuate mandrel sections.

Methods, systems, and apparatuses are disclosed for the manufacture of composite components having incorporated reinforcing structures machined into composite material substrates, and composite components manufactured according to disclosed methods, and assemblies and larger structures comprising the composite material components.

A scrap collection assembly for a tape lamination head that applies a plurality of composite tape segments includes a crack-off assembly with a scrap crack-off redirect roller configured to engage one or more composite tape segments and one or more scrap portions; and a secondary crack-off roller configured to engage one or more composite tape segments and one or more scrap portions; a pivot that connects the crack-off assembly to the tape lamination head, wherein the secondary crack-off roller selectively moves about the pivot to change a direction of composite tape movement.

Described herein are stringer assemblies, such as blade stringers, and methods of forming thereof. A stringer assembly comprises a first fabric composite stiffener, a second fabric composite stiffener, and an intermediate tape composite stiffener, disposed between and connected to each of the first and second stiffeners. Using three separate components allows forming sharp bends, eliminating voids and gap fillers, and adding new features, such as edge reinforcements. Each of the first and second fabric composite stiffeners comprises a web portion, a flange portion, and a curved portion, positioned between the web and flange portions. The web portions surround and are attached to the intermediate tape composite stiffener and, in some examples, include tapered-out edges for additional rigidity. The flange portions are attached to the composite base. The curved portions conform to the flared-out edges of the intermediate tape composite stiffener, which extends and connects to the composite base.

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.

Systems, methods, and devices are provided for the creation of predictable and accurate defects in a fiber tow of an Automated Fiber Placement (AFP) process, with such artificial defects being useful to support calibration of an in situ inspection system used in the AFP process. Various embodiments include methods for creating such artificial defects that support calibration of an in situ inspection system of an AFP system or process. Various embodiments may also include a defect stencils for an AFP system or process.

A tacking device may comprise: a handle; a main body extending from a first end of the handle to a second end of the handle; and a plurality of soldering irons, each soldering iron in the plurality of soldering irons extending from a first side of the main body through the main body to a second side of the main body, each soldering iron in the plurality of soldering irons including a piercing end disposed on the second side of the main body.

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.