BRICE AARON JOHNSON
Engineers in Auburn, WA

7479201, Jan 20, 2009

Sep 27, 2005

11/239453

Peter M. Wegner - Tijeras NM, US
Jeffrey M. Ganley - Albuquerque NM, US
Brice A. Johnson - Federal Way WA, US
Barry P. Van West - Bellevue WA, US

The United States of America as represented by the Secretary of the Air Force - Washington DC

B29D 31/00, B29D 22/00, B32B 27/00, B65C 3/26, B29C 53/80, B29C 53/58, B29C 70/86, B29C 69/00, B29C 45/14, B65H 81/00, B28B 7/22, B27N 3/10

156242, 156156, 156169, 156170, 156171, 156172, 156173, 156174, 156175, 264255, 264257

A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. Ribs are formed on a smooth hard base tool. Expansion blocks are placed in the shallow cavities formed by the ribs and the base tool, and held in place by a synthetic elastomer-based adhesive while a skin is placed over the ribs, expansion blocks, and base tool. The assembly is then placed in a vacuum bag and autoclave cured. After cooling, the expansion blocks are removed and the formed structure is removed from the hard base tool. This abstract is provided to comply with the rules requiring an abstract, and is intended to allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.

7282107, Oct 16, 2007

Aug 22, 2003

10/646509

Brice A. Johnson - Federal Way WA, US
Stephen S. Spoon - Buckley WA, US
Randal S. Darras - Auburn WA, US

The Boeing Company - Chicago IL

B65H 81/00

156169, 156173, 156175, 156425, 156433, 156441

An aircraft part manufacturing device for automated composite lamination on a mandrel surface of a tool having a rotational axis includes a mechanical supporting structure that supports multiple material delivery heads. The tool is moveable and rotatable relative to the mechanical supporting structure. The mechanical supporting structure provides for axial translation of the material delivery heads relative to the mandrel surface while the mandrel surface is rotated for laying down courses of composite material over the entire mandrel surface of the tool. The position and movement of each of the plurality of material delivery heads is individually adjustable. Arm mechanisms provide motion of each material delivery head in a direction normal to the mandrel surface; rotation about an axis normal to the mandrel surface; circumferential position adjustment in a hoop direction relative to the mandrel surface; and axial position adjustment relative to the other material delivery heads.

7228611, Jun 12, 2007

Nov 18, 2003

10/717030

Donald A. Anderson - Bellevue WA, US
Brice A. Johnson - Federal Way WA, US
Stephen S. Spoon - Buckley WA, US

The Boeing Company - Chicago IL

B23P 11/02, B29C 65/00, B64C 1/00

29448, 29464, 29559, 156285, 156286, 156382, 156425, 264102, 264571, 244119, 244120

A method of transferring an uncured composite laminate skin from a lay-up surface of a male mandrel tool to a female cure tool includes defining multiple vacuum zones on the lay-up surface, each zone corresponding to one of a multiple of portions into which the skin is to be separated. For example, to separate the skin into two portions, a low profile seal of a first membrane to the lay-up surface is formed at a first vacuum zone and a second low profile seal for a second membrane is formed at a second vacuum zone. The method further includes laying up a composite laminate skin over all the vacuum zones; separating the composite laminate skin into portions, for example, a first portion over the first vacuum zone and a second portion over the second vacuum zone; and releasing the portions individually into cure tools having an outside mold line surface.

7039485, May 2, 2006

Mar 12, 2004

10/799306

Roger W. Engelbart - St. Louis MO, US
Michael R. Chapman - Federal Way WA, US
Brice A. Johnson - Federal Way WA, US
Kathryn A. Soucy - Seattle WA, US
Reed Hannebaum - Mount Vernon IL, US
Steve Schrader - Bridgeton MO, US

The Boeing Company - Chicago IL

G06F 19/00, B32B 31/00

700110, 700117, 156379

A method generally includes electronically accessing positional data defining a defect location on a composite structure, and automatically causing a material placement machine to return to the defect location as defined by the positional data. The method can also include automatically causing the material placement machine to place or lay down material sufficient for repairing a defect at the defect location. Alternatively, the material placement machine may automatically return to a defect location, and then an operator may manually repair the defect at the defect location.

7935289, May 3, 2011

Apr 2, 2007

11/695561

Donald A. Anderson - Bellevue WA, US
Brice A. Johnson - Federal Way WA, US
Stephen S. Spoon - Buckley WA, US

The Boeing Company - Chicago IL

B32B 37/00

264257, 264500, 264510, 264511, 264258

A method is provided for making a composite laminate aircraft skin for a fuselage in multiple composite panels. A resin-impregnated composite tape is placed on a lay-up surface of a mandrel tool to form the composite laminate aircraft skin as a barrel that is substantially the shape of a fuselage section. The barrel is cut into a plurality of panels on the mandrel tool, and at least one panel of the plurality of panels is transferred, individually and independently of all other of the plurality of panels, from the lay-up surface of the mandrel tool to a first cure tool of a plurality of cure tools having an aero surface tooled to an outer mold line. The at least one of the panels is cured on the first cure tool to form a cured composite panel. The first cure tool defines and controls the outer mold line of the at least one panel. The cured composite panel is removed from the first cure tool.

2014006, Mar 6, 2014

Aug 31, 2012

13/600686

SAMUEL F. PEDIGO - Lake Forest Park WA, US
Julie A. Shah - Boston MA, US
Brice A. Johnson - Federal Way WA, US

The Boeing Company - Seal Beach CA

G06F 19/00

700108

Systems and methods for the dynamic control of task assignments in a fabrication process that employs a plurality of machines to fabricate a manufactured component. These systems and methods may include executing a plurality of task assignments with an available portion of the plurality of machines, monitoring a process variable that defines the available portion of the plurality of machines, and adjusting the plurality of task assignments to create a plurality of adjusted task assignments based upon the monitoring. The plurality of task assignments may include a plurality of tasks that are to be completed during fabrication of the manufactured component, and the executing may include initiating a respective task assignment of the plurality of task assignments with each machine in the available portion of the plurality of machines, thereby fabricating at least a portion of the manufactured component.

2011007, Mar 31, 2011

Dec 6, 2010

12/961066

Brice A. Johnson - Federal Way WA, US
David J. Carbery - Vashon WA, US

The Boeing Company - Chicago IL

B32B 37/02

156 60, 156538

To apply a course on a layup mold, a ply boundary that defines a ply area on the layup mold is determined and a tape of composite material is applied on the ply area at an oblique angle relative to the ply boundary. In addition, a leading edge of the tape is butt cut and the leading edge, and the ply boundary essentially converge. Furthermore, a trailing edge is generated. The trailing edge is a butt cut and the trailing edge and the ply boundary essentially converge.

2012015, Jun 21, 2012

Dec 15, 2010

12/969106

Samuel Francis Pedigo - Lake Forest Park WA, US
Brice A. Johnson - Federal Way WA, US

B32B 37/00, G05G 15/00, B29C 53/82

156 64, 156391, 156350, 156169, 901 27, 901 28

A fiber placement system is described. The system includes a motion system having a robotic arm, a fiber-placement layup mandrel mounted on the robotic arm, and a fiber-placement delivery system having a delivery head. The robotic arm is operable for movement of the mandrel with respect to and proximate the delivery head for fabrication of a composite fiber part.

2012032, Dec 27, 2012

Jun 26, 2011

13/168990

Michael D. Silcock - Southbank, AU
Christopher A. Howe - Glen Waverley, AU
Brice A. Johnson - Federal Way WA, US

B32B 38/04, B32B 38/18

156176, 156166, 156199, 156358, 156437, 156530, 156538

A composite structure is fabricated by laying up at least one ply of fiber reinforcement and at least one layer of resin on a tool. The resin film layer is formed by laying strips of resin film. The fiber reinforcement is infused with resin from the resin layer.

2013005, Feb 28, 2013

Aug 23, 2011

13/215913

Samuel Francis Pedigo - Lake Forest Park WA, US
Brice A. Johnson - Federal Way WA, US
Craig Farris Battles - Seattle WA, US
Donald L. Kaiser - Kent WA, US
Kimberly Jyl Kaiser - Kent WA, US
Richard Neil Blair - Kent WA, US
James M. Cobb - Burien WA, US
Matthew W. Smith - Puyallup WA, US

G06F 19/00

702108

An anomaly detection and cataloging system is described that includes a handheld probe having a probe tip, a user interface, and a communications interface. The system further includes a system controller and a probe locating device. The probe is operable, via the user interface, for transmitting, via the communications interface, a user selected anomaly type to the system controller, the anomaly type being associated with a manufactured part or airplane on the ground (AOG). The probe locating device is operable to provide to the system controller a location associated with the probe tip, and the system is programmed to associate the user selected anomaly type with the location associated with the probe tip.