Spirit Aerosystems, Inc.

Sprint Aerosystems, Inc.

Rahbar Nasserrafi

Gerald E Hicks

Kerrick Robert Dando

Darrell A Wade

Mark Anthony Wadsworth

Craig M Clasper

Thanh A Le

Michael A Walker

Dennis Lebeda

David E Jakstis

Kevin Lyle Obrachta

Amitabh Vyas

Roger Edmund Kornfeld

Aaron Rae Heitmann

LaVerne L Waalkes

Derek D Donaldson

Gary W Sundquist

Bryan David Woods

Michael Basala

Helen Ehlers

Gerald Eugene Hicks, Jr

Theodore Joseph Eilert

Scott E Graves

Micheal A Walker

Shawn Douglas Vierthaler

Linda Cadwell Stancin

Steven Paul Meyer

A method of forming a metal matrix composite component includes positioning a preform including an electrically non-conductive fibrous material in a shaping tool. The fibrous material is pre-coated. The method includes flowing a molten metal comprising zinc into the shaping tool so that at least a portion of the preform is enveloped by the molten metal to form the metal matrix composite component; and cooling the metal matrix composite component.

Method to produce low-cost metal matrix composites for industrial, sports, and commercial applications

A method of manufacturing a complex-shaped composite part, including the steps of applying a metallic sheath around a composite laminate workpiece and applying an electric current through the metallic sheath to heat the workpiece. The metallic sheath may be sealed around the composite laminate workpiece, with air or atmosphere evacuated therefrom. The method also includes shaping the workpiece in the metallic sheath into a complex-shaped composite part while it is being heated. The shaping can be performed between two ceramic dies or using other techniques for forming complex shapes and curvatures into the workpiece. The method then may include cooling the complex-shaped composite part and removing the metallic sheath from the complex-shaped composite part. This method minimizes cycle times and reduces breakage of fiber reinforcement of the composite laminate. The method also helps avoid tearing, buckling, or wrinkling of the workpiece during formation via the structural support provided.

Method of forming composites by joule heating of enveloping metallic sheets

A system and method for welding thermoplastic components by positioning and moving a heated plate between the components to melt their respective faying surfaces, and as the plate moves, pressing the components together so that the melted faying surfaces bond together as they cool and re-solidify, thereby creating a composite structure. The plate has a heated portion which is positioned between and heated to melt a portion of the first and second faying surfaces. A manipulator mechanism moves the plate along an interface from between the portion to between a series of subsequent portions of the first and second faying surfaces, thereby welding the thermoplastic components along the entire interface to create the composite structure. An injection device may also move behind the plate and reciprocally inject a polymer between the first and second faying surfaces to provide toughness and crack arresting properties.

System and method for welding thermoplastic components to create composite structure

A method of manufacturing metal matrix composite (MMC) parts, including the steps of applying a metallic sheath around a bundle of MMC laminates, heating the bundle of MMC laminates in the metallic sheath at a curing or fusing temperature to consolidate the bundle of MMC laminates into a single cured or fused part, and then cooling the cured or fused part. The bundle of MMC laminates may be formed by removing surface contamination from the dry reinforcement fibers, creating a plurality of individual MMC laminates by plating dry reinforcement fibers with electroless nickel, and/or electrodeposited nickel or cobalt, and stacking each of the plurality of individual MMC laminates into a bundle. Autocatalytic and/or electroplating may be used as the primary means to incorporate fiber reinforcement into the metal matrix composite by covering and bonding fiber reinforcement into MMC laminates/plies and/or 3-D woven parts.

Method for manufacturing metal matrix composite parts

An aircraft nacelle and method of fabricating a monolithic lipskin of the nacelle. The nacelle may include a fan cowl, a bulkhead, and the monolithic lipskin. The lipskin may be formed by spin-forming or explosive forming an annularly-shaped plate onto a mandrel, and machining or chemically-milling integrated stiffeners or other protrusions and attachment tabs into an inner mold line (IML) of the lipskin. The machining or chemical milling may occur before or after the spin-forming or explosive forming. The stiffeners may have a spiral or circumferential configuration. An attachment tab extending from the IML may attach to the bulkhead, such that an outer mold like (OML) of the lip-skin is not disrupted by mechanical fasteners attaching the lipskin to the bulkhead.

Monolithic lipskin and method of fabrication

A method for heat-treating a titanium alloy, such as Ti-6Al-4V. The method may occur after or include a step of forging the titanium alloy such that localized, highly deformed grains are formed in the titanium alloy. Then the method may include steps of recrystallization annealing the titanium alloy by heating the titanium alloy to a temperature in a range between 30&#xb0; F. to 200&#xb0; F. below beta transus of the titanium alloy for 1 hour to 6 hours and then furnace cooling of the titanium alloy to 1200&#xb0; F. to 1500&#xb0; F. at a rate of 50&#xb0; F. to 500&#xb0; F. per hour. Following the recrystallization annealing, the method may include beta annealing the titanium alloy. These steps may be performed in a single heat treating cycle.

Method to prevent abnormal grain growth for beta annealed Ti&#x2014;6AL&#x2014;4V forgings

A joule-heating press and method for manufacturing a metallic honeycomb core via diffusion bonding. The method may include printing a pattern of strips of a stop-off material to surfaces of a plurality of sheets of metal at locations where diffusion bonding is not desired and stacking the sheets of metal together in a sequence for forming the honeycomb core. Then the method may include steps of pressing the sheets of metal together between two press plates made of conductive material and applying electric current to the conductive material of the press plates. This allows current to flow through a thickness of the sheets of metal and the sheets of metal are thereby diffusion bonded to each other via joule heating at locations absent the stop-off material. Finally, the method may include a step of expanding the sheets of metal into the honeycomb core.

Method for joule heating diffusion bonded honeycomb core

Aluminum alloys are provided that can comprise boron and vanadium and high amounts of titanium and zirconium. The aluminum alloys described herein can exhibit superior tensile properties at both room temperature and elevated temperatures and still maintain desirable ductility. The aluminum alloys can be used in applications where resistance to fatigue and breakdown at elevated temperatures is desirable, which includes applications in the aerospace and aeronautical fields.

Aluminum-copper alloys with improved strength

Method to prevent abnormal grain growth for beta annealed TI-6AL-4V forgings

An aircraft thrust reverser inner wall and method of manufacturing the same. The aircraft thrust reverser inner wall may include a face sheet, a perforated back sheet, and a core sandwiched between the face sheet and the perforated back sheet. The face sheet may have an inner face sheet surface and an outer face sheet surface, and the core may have an inner core surface, an outer core surface, and a plurality of cell walls extending therebetween. An electro-depositable material may be applied, via electrodeposition, in a substantially continuous layer over the outer core surface, the cell walls, and the outer face sheet surface, thus bonding the face sheet and core together. The perforated back sheet may be attached to the core at the outer core surface, and a conductive coating may be applied to the inner face sheet surface.

Hybrid thrust reverser inner wall for aircraft engines

A system and method for heat-treating a titanium part. The system may include foil, adhesive tape, and a localized heat source. The foil may include two sheets of foil made of a material more reactive (more prone to oxidize) than the titanium part, and the localized heat source may include a heating element mostly surrounded by insulation. The method may include taping the foil to opposing sides of the titanium part, thus sealing a portion of the titanium part to be heat treated from external atmosphere. The method may also include heating and placing the localized heat source near or against the foil until heat treating is complete. A small amount of air remaining between the heated foil and the titanium part has a preferential reaction with the foil, since it is more reactive than the titanium part. This prevents oxidation of the titanium part during localized heat treating.

Localized heat treating of net shape titanium parts

A method of shaping a metallic honeycomb panel using a continuous drive sheet. The metallic honeycomb panel may have a perforated upper sheet, a non-perforated lower sheet, and a metal honeycomb core fixed between the upper and lower sheets. The method may include the steps of designing and manufacturing the drive sheet using finite element analysis (FEA) and criteria regarding shaping of the metallic honeycomb panel, then welding the drive sheet to the lower face of the lower sheet. The drive sheet may cover all of the lower face of the lower sheet and may have varying thicknesses determined based on the criteria and the FEA. The method may also include the steps of heating the drive sheet and metallic honeycomb panel to a creep forming or hot-stretch forming temperature and urging the metallic honeycomb panel and drive sheet into a male or female die mold to be shaped.

Bifurcation honeycomb sandwich structure with optimized doubler

Aluminum-based alloys for casting or wrought processing having improved combinations of properties, including improved high temperature strength, are provided. The alloys generally comprise copper, magnesium, silver, and titanium, along with scandium and/or cobalt. Zirconium, zinc, and/or vanadium may also optionally be present in the alloy. When cobalt is present in the alloy, nickel may also optionally be present. Cast and wrought products, as well as methods of making the same using the alloys, are also disclosed.

Wrought and cast aluminum alloy with improved resistance to mechanical property degradation

A system and method for shaping a net or near-net titanium part, the method comprising machining a piece of titanium into a titanium part having non-uniform thickness, heating the titanium part to a target temperature within a target temperature range between an auto-relief temperature of the titanium part and a minimum temperature required for super plastic forming of the titanium part, and lowering a die into the titanium part with sufficient force to shape the titanium part. The system for shaping the titanium part may comprise a multiple-axis machine, a die, electrical clamps, sensors, and a control system for adjusting heating temperatures based on information received from the sensors regarding the titanium part.

System and method for forming contoured new and near-net shape titanium parts

A system and method for direct manufacturing and stress relieving a metal part without removing the metal part from a vacuumed chamber. The system may comprise the chamber, a wire feeder for depositing a metal wire onto a metal plate, an electron beam (EB) source for providing an electron beam to melt the metal wire during deposition, and a current-providing apparatus for joule heating the metal plate to provide heat treatment to the metal part. The method may comprise depositing the metal wire onto the metal plate within the vacuumed chamber, then providing intermediate stress relief after a portion of the metal wire is deposited onto the metal plate by applying an electrical current to the metal part. The electron beam may also be set at a temperature below a melting point of a particular metal of the metal part for relieving stress in the metal part.

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Andover, KS, United States of America

Rahbar Nasserrafi