The Boeing Company

Byron James Autry

James R Kendall

Santiago M Mejia

David Raines

Samuel James Knutson

Brian Timothy Peters

Raviendra Sidath Suriyaarachchi

Paul Gabriel Werntges

Patrick James Macko

Sara Murphy

Darrell Darwin Jones

Daniel R Smith

Larry Scott Smotherman

Samantha Eberhardt

Brian S Carpenter

Andrew Elmer Modin

Karl Marius Nelson

Richard Alexander Prause

Patrick B Stone

Paul D Shaw

Matthew S Stauffer

Richard E Heath

Gregory J Hickman

Matthew Benjamin Moore

William H Ingram

Steven P Wanthal

Ivan Gilberto Ramirez

Brian D Smith

David Howard Curry, Iii

Alice R Arnold

Scott L Smotherman

Michael J Bailey

David M Petka

David H Curry, Iii

Kyle Michael Ithal

Brian Bentley Reid

David M Raines

David H Curry Iii

A method of processing a composite structure includes a step of positioning a first processing tool of a tooling assembly and a second processing-tool of the tooling assembly from an open position, in which the first processing-tool and the second processing-tool are spaced apart, to a closed position, in which the first processing-tool and the second processing-tool are sealed to each other and are sealed to a mandrel-tool, supporting the composite structure, to form a vessel that surrounds the composite structure. The method also includes a step of processing the composite structure.

Apparatus and method for processing a composite structure

Systems () for assembling stiffened composite structures comprise a layup mandrel () and a network () of fluid lines () configured to be selectively and fluidically coupled to string bladders () positioned relative to the layup mandrel ().

Systems and methods for assembling stiffened composite structures

An apparatus, system, and methods for providing flowable material to a part-forming fixture. The apparatus comprising a tool manifold and a fixture manifold. The tool manifold comprises a tool-manifold base and a plurality of tool fittings extending through the tool-manifold base. The fixture manifold comprises a fixture-manifold base and a plurality of fixture fittings extending through the fixture-manifold base. An interface end of each one of the plurality of tool fittings is removably attachable to an interface end of a corresponding one of the plurality of fixture fittings such that, when attached, a seal is created between the tool fittings and the corresponding fixture fitting and flowable material is flowable from each one of the tool fittings into the corresponding one of the fixture fittings.

Quick connect manifold for flowable material delivery to a part-forming fixture and associated systems and methods

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 part transfer system includes a movable support, a plurality of arms coupled to the movable support, and an end effector coupled to each of the plurality of arms. The end effector includes a body and a plurality of dividers each coupled to the body. The plurality of dividers divides the body into a plurality of partitions. The end effector includes a plurality of vacuum ports each in fluid communication with one of the plurality of partitions. The part transfer system further includes a vacuum source in fluid communication with at least one of the plurality of vacuum ports. Each of the plurality of vacuum ports is configured to draw a fluid from the plurality of partitions to establish a vacuum between the end effector and a part that is engaged with the end effector, thereby securing the part to the end effector.

Part transfer system

Disclosed herein is a bladder assembly for forming a part made of a fiber-reinforced polymeric material. The bladder assembly comprises a bladder comprising an interior having a hollow interior channel within the interior of the bladder. The bladder assembly also comprises an intake port fluidically coupled with the interior of the bladder and an exhaust port fluidically coupled with the interior of the bladder. The bladder assembly further comprises a pressure control device fluidically coupled with the exhaust port and configured to control a pressure drop across the interior of the bladder from the intake port to the exhaust port.

Autoclave system, bladder assembly, and associated method for forming a part

An apparatus for processing a composite structure includes a mandrel that includes a tooling surface and vacuum bagging that includes an elastomeric membrane and a bagging surface. The apparatus also includes a surface interface formed between the mandrel and the elastomeric membrane. The surface interface includes a suction channel formed in at least one of the tooling surface of the mandrel and the bagging surface of the elastomeric membrane. The elastomeric membrane is configured to be sealed to the mandrel along the suction channel in response to a vacuum applied to the suction channel.

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

An apparatus for processing a composite structure includes a first processing-tool and a second processing-tool that are movable between an open position, in which the first processing-tool and the second processing-tool are separated from each other, and a closed position, in which the first processing-tool and the second processing-tool are configured to be sealed to each other. In the closed position, the first processing-tool and the second processing-tool are configured to be sealed to a mandrel-tool, located between the first processing-tool and the second processing-tool and supporting the composite structure. In the closed position, the first processing-tool, the second processing-tool, and the mandrel-tool form a vessel, configured to apply at least one of pressure and heat to the composite structure.

In an example, a system is disclosed. The system comprises a one-piece mandrel, a fuselage coupled to the one-piece mandrel, and a strongback apparatus positioned on the fuselage. The strongback apparatus comprises an arcuate central body comprising a front end, a rear end, and a plurality of elongated members that connect the front end to the rear end, and actuators mounted to the plurality of elongated members. The actuators are configured to move in a radially outward direction from extended positions to retracted positions and comprise (i) proximal ends mounted to the plurality of elongated members and (ii) distal ends having vacuum suction cups. In the extended positions, the vacuum suction cups engage the fuselage on which the strongback apparatus is positioned. As the actuators moves from the extended positions to the retracted positions, the vacuum suction cups pull the fuselage away from the one-piece mandrel.

Methods and apparatuses for decoupling a fuselage from a mandrel

Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.

Circumferential lap splices for sections of fuselage

Methods and apparatus involved in the process of hardening a composite part are disclosed herein. The methods include applying a preform to a mandrel, covering the preform with a caul plate, sealing the caul plate to the mandrel, pushing the caul plate toward the preform and the mandrel and hardening the preform into a composite part while the caul plate is held against the preform. The apparatus include a mandrel, a caul plate which defines a surface of a preform and where the caul plate may include a rigid material and seals disposed between the mandrel and the caul plate. In an additional aspect, the apparatus may include a sealed chamber with a mandrel and a caul plate and a circumferential seal between the mandrel and the caul plate.

Caul plate system for aircraft fabrication

Systems and methods are provided for demolding a composite part from a mandrel. The method includes mechanically coupling a first arm of an extraction tool to a first arcuate portion of a composite part that has been hardened onto a mandrel, mechanically coupling a second arm of an extraction tool to a second arcuate portion of the composite part, and separating the composite part from the mandrel by iteratively performing the following operations until the composite part no longer contacts the mandrel: elastically straining the first arcuate portion of the composite part via the first arm, and elastically straining the second arcuate portion of the composite part via the second arm.

Demolding of large composite parts for aircraft

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.

Growing community of inventors

Charleston, SC, United States of America

Byron James Autry