The Boeing Company

Paul Gabriel Werntges

Gregory J Hickman

Byron James Autry

David Raines

Samuel James Knutson

Santiago M Mejia

Patrick James Macko

Sara Murphy

Larry Scott Smotherman

Randall Dow Wilkerson

Dennis Ray Mathis

Aaron Ross Cowin

Charlie E Branyon, Iii

Eileen E Miller

Daniel B Freeman

Scott L Smotherman

Alice R Arnold

Joshua Paul Koehn

David Howard Curry, Iii

A system for joining a first thermoplastic component of a workpiece with a second thermoplastic component of the workpiece includes a first joining plate assembly comprising a housing, a heat plate, and a thermal insulator disposed between the housing and the heat plate, wherein the heat plate defines a heating surface; a second joining plate assembly opposed from the first joining plate assembly; and a clamping assembly engaged with both the first joining plate assembly and the second joining plate assembly.

Systems and methods for joining thermoplastic components

A device to assemble a skin and a frame of an aircraft fuselage. The device includes first and second brace members that extend along opposing sides of a gap. Arches are spaced apart and fixedly connected to the first and second brace members and that extend across the gap. A strongback is attached to and movable along the first and second brace members with the strongback having a curved shape that matches the plurality of arches. The strongback includes clamps configured to engage with the frame. First and second tension devices apply tension to the skin at the strongback.

Method and apparatus for the application of frame to fuselage pull-up force via fuselage skin waterline tensioning

A system for manufacturing a part includes a mold having a contoured forming surface. The system also includes at least one tension strap, configured to attach to a consolidated laminate sheet, and a heating assembly, positioned relative to the mold and configured to supply heat to the consolidated laminate sheet, when attached to the at least one tension strap, to form a heated consolidated laminate sheet. The system additionally includes a strap retraction mechanism, configured to retract the at least one tension strap, when attached to the consolidated laminate sheet, to force the heated consolidated laminate sheet against the contoured forming surface of the mold. The heating assembly includes a flexible heating element configured to flex to conform to a shape of the heated consolidated laminate sheet as the heated consolidated laminate sheet is forced against the contoured forming surface of the mold.

Systems and methods for manufacturing large contoured parts from thermoplastic laminate sheets

A joining system includes a holding fixture assembly configured to hold a fuselage skin. The stringers are temporarily attached to the fuselage skin. The joining system includes an upper beam assembly including an upper beam and a lower beam assembly. The lower beam assembly includes a lower beam and at least one lower heating element. The holding fixture assembly is coupled to the upper beam assembly. The holding fixture assembly is coupled to the lower beam assembly. The upper beam is movable relative to the lower beam to clamp the at least one of the plurality of stringers and the fuselage skin together prior to and during welding.

Method and apparatus for bonding stringers to a fuselage skin

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 and structure for processing a plurality of prepreg sheets includes a conveyor assembly having a first conveyor, a second conveyor, and a processing zone positioned between the first and second conveyors. In an implementation, a plurality of prepreg sheets are advanced from a plurality of material supply creels into the processing zone by a first conveyor and a second conveyor turning in opposite directions. Within the processing zone, a compressive pressure is applied to the prepreg sheets by first pressure plates attached to first conveyor and second pressure plates attached to the second conveyor. A thermoplastic within the prepreg sheets is melted within the processing zone by a heater to consolidate the prepreg sheets into a consolidated laminate.

Method and apparatus for rapid continuous consolidation of thermoplastic components

An apparatus for mounting a splice component for joining two or more workpieces includes a base plate and one or more bias assemblies. The base plate includes one or more passageways extending through the base plate and one or more barrier elements mounted proximate to the passageway(s). Each barrier element and associated passageway are configured to freely receive a protrusion of a splice component. The bias assembly includes a bias element that extends proximate to the passageway and is configured to move resiliently to urge the protrusion against the barrier element. The passageway, the barrier element, and the bias assembly are configured to allow movement of the splice component relative to the base plate transverse to a direction of force applied by the bias element on the protrusion.

Growing community of inventors

Charleston, SC, United States of America

Paul Gabriel Werntges