The Boeing Company

Spirit Aerosystems, Inc.

Christopher John Morrow

Dwight L Engwall

Blaise Francis Bergmann

Allison Lynne Horner

Christopher James Padovano

Benjamin Wayne Ferrell

William Joseph Bryant

Kenneth I Fried

An apparatus for picking, placing, and forming a composite charge over a complex geometry tool comprises a first frame, a second frame, and a plurality of dynamic mechanisms. The first frame is formed from rigid material and includes a first frame member that forms at least a rectangular perimeter. The second frame is formed from flexible material and includes a second frame member that forms at least a rectangular perimeter. Each dynamic mechanism is connected to the first frame and the second frame and located along the perimeters of the first frame and the second frame. Each dynamic mechanism includes a length-variable component positioned between the first frame and the second frame, with at least a portion of the dynamic mechanisms configured to vary a length of the length-variable component for the second frame member to conform to the shape of the complex geometry tool.

Integrated pick, place and forming apparatus and method for composite charges over complex geometries

Integrated pick, place, and forming apparatus and method for composite charges over complex geometries

A method of forming a composite material part using an integrated shape memory polymer (SMP) and caul tool comprises the steps of: placing a caul on a positive feature of a mold, deforming the SMP from a relaxed state such that the SMP integrates with the caul to form an integrated SMP and caul tool, placing composite material on the integrated SMP and caul tool, heating the composite material to cure the composite material to form a composite material part while the SMP remains deformed, and stimulating the SMP to return to the relaxed state such that the SMP separates from the caul and the composite material part.

Integrated shape memory polymer and caul tool

A system for processing a composite material may comprise a chamber, a mandrel, an upper ramp, and an upper diaphragm. The chamber generally provides structural support while a vacuum is applied to the system and may have a six-sided generally rectangular box shape. The mandrel generally provides support for the composite material, and may be located within the chamber. The upper ramp generally provides a path for the upper diaphragm to follow under vacuum, and may be located adjacent to the mandrel and tilted at approximately 45 degrees downward thereto. The upper diaphragm may be placed over an opening along one side of the chamber. During processing, a vacuum may be applied to chamber and the upper diaphragm may be pulled inward through the opening to press the composite material against the mandrel.

System for processing composite materials

A method for fabricating stringers is provided. The co-cured composite stringer includes a stringer and a mandrel positioned within a channel defined in the stringer. A plurality of strips are positioned within an opening of the mandrel, and a substrate layer, such as aircraft skin, is positioned adjacent to the stringer. During application of the substrate layer to the stringer, the mandrel and plurality of strips support the stringer.

Method for fabricating stringers

Embodiments of an assembly for securing a stringer to a substrate are provided. The stringer assembly includes a stringer and a mandrel positioned within a channel defined in the stringer. A plurality of strips are positioned within an opening of the mandrel, and a substrate layer, such as aircraft skin, is positioned adjacent to the stringer. During application of the substrate layer to the stringer, the mandrel and plurality of strips support the stringer.

Assembly for securing a stringer to a substrate

A co-cured composite stringer and associated apparatus and method are provided. The co-cured composite stringer includes a stringer and a mandrel positioned within a channel defined in the stringer. A plurality of strips are positioned within an opening of the mandrel, and a substrate layer, such as aircraft skin, is positioned adjacent to the stringer. During application of the substrate layer to the stringer, the mandrel and plurality of strips support the stringer.

Co-cured stringers and associated mandrel and fabrication method

A bonding tool assembly (10) for supporting a composite part structure (11) during fabrication and curing processes, includes a bonding tool (12) and a plurality of fairing bars (14). The bonding tool (12) contains a support surface (16) upon which a composite part structure (11) is placed. The plurality of fairing bars (14) are placed completely around the periphery of the composite part structure (11) providing lateral support. The fairing bars (14) each contain a mating surface (18) which is placed directly upon the support surface (16) of the bonding tool (12). Each mating surface (18) contains a plurality of extended indexing protrusions (20) which form a distinct pattern and are secured by threaded fasteners (21). The support surface (16) contains a plurality of indexing recesses (22) that are configured to form the same pattern as the indexing protrusions (20) such that the fairing bars (14) and the bonding tool (12) are matable. Each fairing bar (14) also contains a plurality of magnets (24) that are located in pockets (26) slightly above the mating surface (18) of the fairing bars (14). The magnets (24) are secured in the pockets (26) by a heat-resistant adhesive (28). The fairing bars (14) magnetically adhere to the support surface (16) of the bonding tool (12) which is either adapted of a magnetically conductive material or contain magnetically conductive inserts (30).

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Wichita, KS, United States of America

Christopher John Morrow