The Boeing Company

Matthew Benjamin Moore

Patrick B Stone

Joseph D Anderson

Don J Russell

Jason Warner

Jeffrey A Zornes

David Jon Herman

Michael David Collier, Sr

Darrell Darwin Jones

Daniel R Smith

Byron James Autry

David Raines

Lile P Squires

A system includes a support beam elongated along a longitudinal axis. The support beam includes a first end portion longitudinally opposed from a second end portion, a first beam-side indexing feature proximate the first end portion, and a second beam-side indexing feature proximate the second end portion. The system further includes a first frame assembly having a first base portion, a first riser portion defining a first vertical axis, and a first carriage connected to the first riser portion and moveable relative to the first riser portion along the first vertical axis. The system further includes a second frame assembly having a second base portion, a second riser portion defining a second vertical axis, and a second carriage to the second riser portion and moveable relative to the second riser portion along the second vertical axis.

Systems and methods for supporting a workpiece in a manufacturing environment

A system for handling a composite workpiece includes a work cell and a plurality of workpiece holders to hold a composite workpiece in the work cell. Each one of the plurality of workpiece holders is selectively controlled to index the composite workpiece in the work cell and to conform the composite workpiece to an as-built shape of the composite workpiece.

System and method for handling a composite workpiece in a work cell

A system for damping machine-induced vibration in a workpiece includes a plurality of workpiece holders to hold the workpiece in a work cell. The system also includes a machine tool located in the work cell. The machine tool performs a machining operation on the workpiece while the workpiece is held by the plurality of workpiece holders. The system further includes a damping apparatus coupled to the workpiece. The damping apparatus controls machine-induced vibrations in the workpiece during the machining operation.

System and method for damping machine-induced vibrations in a workpiece

A method for manufacturing a structure includes sensing activity in a workstation with at least one sensor. The method further includes transporting the structure to the workstation, engaging a telescoping platform with the structure, and releasing an access barrier after the engaging.

Methods and systems for manufacturing a structure

A method for manufacturing a composite barrel structure includes fabricating a first plurality of composite panels that are assemblable into a first partial composite barrel section. The fabricating includes assembling a first layup of composite material and, concurrently, assembling at least one additional layup. The fabricating further includes heating the first layup with the at least one additional layup. A system for fabricating a plurality of panels that are assemblable into partial barrel sections includes a first workstation for fabricating a first plurality of composite panels that are assemblable into a first partial composite barrel section. The first workstation includes a first assembly station configured to concurrently assemble a first layup of composite material and at least one additional layup and a first heating station configured to heat the first layup concurrently with the at least one additional layup to yield the first plurality of composite panels.

Methods and associated systems for manufacturing composite barrel structures

Methods and systems for assembling containerized aircraft as complete aircraft. The methods comprise removing aircraft components from shipping container(s), unloading the aircraft components from shipping fixture(s), removing tooling comprising aircraft component positioning structure(s) from the shipping container(s), loading aircraft component(s) onto aircraft component positioning structure(s), positioning the aircraft components in aircraft component installation positions, positioning the aircraft component(s) using the aircraft component positioning structure(s), and attaching the aircraft components to assemble the complete aircraft. The systems comprise aircraft components configured to be loaded into shipping container(s) in a shipping arrangement, unloaded from the shipping arrangement and attached to at least one other aircraft component to assemble the complete aircraft; shipping fixture(s) configured to support the aircraft components in the shipping arrangement, and tooling configured to facilitate assembly of the aircraft components and comprising aircraft component positioning structure(s) configured to position aircraft component(s) in aircraft component installation position(s).

Systems and methods for assembling containerized aircraft

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

An airframe handling apparatus is operable to support and move a partially assembled aircraft fuselage. The aircraft fuselage is incomplete, lacking a wing and landing gear. The apparatus is attachable to the aircraft fuselage in place of the wing and landing gear, utilizing wing attachment structures on the aircraft fuselage that are designed for flight loads. With the aircraft fuselage attached to the apparatus, the entire fuselage is supported on the apparatus that can be operated to move and manipulate the aircraft fuselage as if the wing and landing gear were present. With the apparatus attached to the aircraft fuselage, movement of the fuselage by the apparatus imparts no handling-induced internal loads on the aircraft fuselage, and maximizes unobstructed access to the exterior surface of the fuselage for painting and other surface preparations.

Apparatus that supports an aircraft fuselage without exterior surface contact

A flay assembly for separating a workpiece from a manufacturing fixture has a horizontal beam assembly and a pair of vertical beam assemblies. The horizontal beam assembly includes a horizontal beam having a horizontal drive motor. Each vertical beam assembly includes a vertical beam operably engaged to the horizontal drive motor and has a workpiece attachment assembly operably engaged to a vertical drive motor. The workpiece attachment assembly has an attachment mechanism attachable to the workpiece. The horizontal drive motor and the vertical drive motors are operable in a manner to move the vertical beams away from each other along a horizontal drive axis while simultaneously moving each workpiece attachment assembly along a vertical drive axis to cause the attachment mechanisms to pull the workpiece side portions away from the manufacturing fixture while a center support of the horizontal beam maintains a workpiece crown in contact with the manufacturing fixture.

Growing community of inventors

Edmonds, WA, United States of America

Matthew Benjamin Moore