The Boeing Company

The Boeiog Company

Dan Dresskell Day

Eric M Reid

Darrell Darwin Jones

James N Buttrick, Jr

Clayton Lynn Munk

Matthew Ray DesJardien

Stephen G Moore

Charles Michael Richards

Noel A Spishak

James Niemann Buttrick

Paul Reed Stone

James M Cobb

Steven Best

Luis A Perla

Raymond C Eng

Matthew R Desjardien

Steven Douglas Bye

Kim Marie Larson

Jeff Hansen

Jeffrey Scott Stephens

Steven John Schmitt

David Paul Banks

Kwok Tung Chan

Joseph Warren

Paul C Chang

Steven A Best

Jeffrey M Hansen

William Thomas Kline

Geoffrey Allen Butler

Mark A Woods

Erik Lund

Charles Yuanxin Hu

Ian E Schroeder

Harry E Townsend

Kenneth Paul Zaballos

Thomas Joseph Kennedy

Brett D Whitmer

Christopher Wheaton

Robert G Meyer

John A Davies, Jr

Gordon Dale Davis

Brian R Conlan

Tyler W Downey

Paul Gregory Kostenick, Jr

Kristopher William Talcott

Jason H Inouye

William H Graham

Peter J VanVoast

Gregory John Shish

Kerri L Olson

Charles J Nelson

Thang D Phung

Curtis M Groth

Richard A Ransom

Justin L Holland

Eric M Avakian

Omar J Pacheo Agosto

Jean R Paillant

Thanh Quach

Gavin Lloyd Smith

Raymond Cho Eng

Kenneth P Zaballos

David P Banks

Christopher J Wheaton

Paul G Kostenick

Matthew Ray Desjardien

Luis A Peria

Joseph F Warren

Safety architecture for an automated work cell provides a barrier separating a work cell area from an operator or personnel area. The safety architecture enables personnel to conduct routine interactions with nonfunctioning motion platforms or positioning machines located in the work cell area through openings in the barrier separating the personnel area from the work cell area while other motion platforms or positioning machines in the work cell area continues to function.

Safety architecture for an automated work cell

A method and apparatus for manufacturing an aircraft structure. A drivable support may be driven from a first location to a second location to bring the drivable support together with at least one other drivable support to form a drivable support system. A structure may be held in a desired position using the drivable support system.

Flexible manufacturing system for aircraft structures

Examples include an apparatus configured for attaching a rib of an aircraft wing to a panel of the aircraft wing, the apparatus including: an insert that is configured to be attached, via an interference fit, to a hole in the rib; a shear tie including a socket at a first end of the shear tie, where the shear tie is configured to be attached to the panel at a second end of the shear tie; a ball stud including a shaft and a ball that is opposite the shaft, where the shaft is configured to be attached to the insert and the ball is configured to be positioned within the socket; and a fastener that is configured to secure the ball within the socket, thereby attaching the ball stud to the shear tie.

Apparatus for attaching aircraft wing structural components

An apparatus and method for supporting an object. In one illustrative embodiment, an apparatus may comprise a support structure, a positioning system, and a retention system. The positioning system may be associated with the support structure and configured to position the support structure with respect to a number of linear axes. The retention system may be associated with the support structure. The retention system may be configured to retain a portion of an object and move the portion of the object towards a platform such that the portion of the object substantially conforms to a shape of the platform.

Modular and reconfigurable support system

A method and apparatus for maintaining a selected configuration for a structure. Metrology data for a support system is received while the support system holds the structure. A determination is made as to whether a current configuration of the structure is within selected tolerances of the selected configuration for the structure based on the metrology data. The support system is moved to move the structure held by the support system into the selected configuration in response to a determination that the current configuration of the structure is not within the selected tolerances of the selected configuration for the structure.

Metrology system for positioning assemblies

Flexible manufacturing for aircraft structures

A magnet sensing portable autonomous device includes a platform. A plurality of wheel sets is coupled to the platform. A drive system is used for driving the plurality of wheels. An attachment mechanism is positioned on an underside of the platform for securing the device to a surface. A control board is used for controlling the operation of the device. In some embodiments, a drill spindle assembly is coupled to the platform. A drill feed assembly is coupled to the drill spindle assembly for raising and lowering the drill spindle assembly. A plurality of sensors are operable to sense one or more magnets disposed below the surface. A drive table is used for positioning the drill spindle assembly in an XY plane based on an output of said plurality of sensors.

Magnet sensing portable autonomous device and method of operation

A method and apparatus for maintaining a selected configuration for a structure during a manufacturing process for forming a product using the structure. Metrology data for a support system is received. The support system holds the structure during the manufacturing process. A determination is made as to whether a current configuration of the structure is within selected tolerances of the selected configuration for the structure based on the metrology data. The support system is reconfigured to move the structure into the selected configuration in response to a determination that the current configuration of the structure is not within the selected tolerances of the selected configuration for the structure.

A portable device to drill holes has a platform. A plurality of wheel sets is coupled to the platform. A drive system is used for driving the plurality of wheels. An attachment mechanism is positioned on an underside of the platform for securing the device to a surface. A control board is used for controlling the operation of the device. A drill spindle assembly is coupled to the platform. A drill feed assembly is coupled to the drill spindle assembly for raising and lowering the drill spindle assembly. A plurality of sensors are operable to sense one or more magnets disposed below the surface. A drive table is used for positioning the drill spindle assembly in an XY plane based on an output of said plurality of sensors.

Magnet sensing hole driller and method therefor

A method and apparatus for installing a fastener in a surface of a structure. A crawler robot may comprise a first movement system and a second movement system. The first movement system may be configured to move the crawler robot and a track system along the surface. The second movement system may be configured to move the crawler robot along the track system on the surface.

Crawler robot and supporting platform

A composite skin and composite stiffeners are co-cured in an autoclave. Uncured stiffeners are placed in channels of a tool, and an uncured skin is placed on the tool contacting the stiffeners. The vacuum bag is sealed over the tool. Bladders placed in the stiffeners are exposed to autoclave pressure through a manifold system employing vent tubes that pass through the vacuum bag along a side of the tool.

Apparatus for co-curing composite skins and stiffeners in an autoclave

A method for forming a structural member and a structural member produced thereby includes positioning a first composite section and a second composite section within a tool. The tool has an inner surface and a wall intersection and is supported by a tool platform. The tool platform and a pressure platform are relatively movable between an open position and a closed position. The tool has a non-planar outer surface against which the member may be pressed. A composite splice member is positioned at least partially overlapping both the first composite section and the second composite section to form a joint in the composite structural member. The composite structural member is pressed against the non-planar outer surface of the tool by applying pressure to the joint from a pressure bladder. Heat is applied to the composite structural member at the joint to cure the composite splice member to the first composite section and the second composite section.

Aircraft skin attachment system

A joint fastening system employs a lock bolt having a pull stem and locking threads inserted through a bore in a joint having fay sealant between layers. A collar is received over the pull stem to engage the threads, the collar producing tension on the threads to generate clamp force sufficient for fay sealant squeeze out.

Temporary clamp up system for sealant squeeze out in lock bolt installations

Growing community of inventors

Seattle, WA, United States of America

Dan Dresskell Day