Brian W Robins

US Patent:

7861969, Jan 4, 2011

Filed:

May 24, 2007

Appl. No.:

11/753482

Inventors:

Juan C. Guzman - Seattle WA, US
Douglas A. McCarville - Orting WA, US
Daniel M. Rotter - LFP WA, US
Brian G. Robins - Renton WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 1/00

US Classification:

244120, 244119, 2441231

Abstract:

A stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel. The stringer has a pair of stringer sides, each extending from a stringer top to a stringer leg. The stringer sides may each extend through a wide radius, smooth continuous curve to a stringer leg. The wide radius, smooth continuous curve may be proximate the base of the stringer side in a region where the stringer side transitions to the stringer leg.

US Patent:

8216499, Jul 10, 2012

Filed:

Dec 9, 2008

Appl. No.:

12/331389

Inventors:

Travis J. Sherwood - Seattle WA, US
Brian G. Robins - Renton WA, US
Darrell D. Jones - Mill Creek WA, US
Joseph D. Brennan - Poway CA, US
Michael R. Anderson - Renton WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

D01D 5/16
B29C 47/88
B29C 45/14

US Classification:

2642102, 2641771, 26417712, 2641772, 26421112, 264259, 264261

Abstract:

A structural filler is installed in a gap between at least first and second composite members by extruding a flowable filler material, placing the extruded filler on one of the composite structural members, and assembling the composite members.

US Patent:

8257536, Sep 4, 2012

Filed:

Dec 18, 2008

Appl. No.:

12/337931

Inventors:

Brian G. Robins - Renton WA, US
Darrell D. Jones - Mill Creek WA, US
Kurtis S. Willden - Kent WA, US
Daniel M. Rotter - Lake Forest Park WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B32B 37/00

US Classification:

156227, 156 52, 156 53, 156 54, 156 56, 156200, 156201, 156202, 156213, 156226, 156463, 156464, 156467, 1564771, 156475

Abstract:

A method and apparatus for a tray, a folding section connected to the tray, and a tape application system. The tray has a channel for receiving an elongate insert for a composite material with a number of layers for a release system. The folding section is capable of folding a number of layers around the elongate insert to cover the elongate insert as the elongate insert is moved through the folding unit. The tape application system is capable of applying a tape to the number of layers for covering the elongate insert to form the release system.

US Patent:

8377247, Feb 19, 2013

Filed:

Dec 22, 2010

Appl. No.:

12/976070

Inventors:

Juan C. Guzman - Seattle WA, US
Douglas A. McCarville - Orting WA, US
Daniel M. Rotter - Lake Forest Park WA, US
Brian G. Robins - Renton WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B32B 37/10

US Classification:

156285, 156212, 156286, 264510, 264511

Abstract:

A stiffened skin panel of an aircraft that includes an aircraft skin panel of composite material and a composite stringer consolidated with the aircraft skin panel. The stringer has a pair of stringer sides, each extending from a stringer top to a stringer leg. The stringer sides may each extend through a wide radius, smooth continuous curve to a stringer leg. The wide radius, smooth continuous curve may be proximate the base of the stringer side in a region where the stringer side transitions to the stringer leg.

US Patent:

8454870, Jun 4, 2013

Filed:

Dec 19, 2008

Appl. No.:

12/339488

Inventors:

William S. Hollensteiner - Kent WA, US
Joseph D. Brennan - Poway CA, US
Jennifer Sue Noel - Kent WA, US
Kurtis Shuldberg Willden - Kent WA, US
Daniel M. Rotter - Lake Forest Park WA, US
Shane Edward Arthur - Belgrade MT, US
Brian G. Robins - Renton WA, US
Darrell D. Jones - Millcreek WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B29C 70/44

US Classification:

264101, 264257, 264258, 264313, 264319

Abstract:

A method for manufacturing composite parts. A temporary removal layer may be placed on an inner mold line tool. A composite material may be laid up on the inner mold line tool for a composite part. The inner mold line tool may be positioned with the composite part inside an outer mold line tool. The composite part and the temporary removal layer may be transferred from the inner mold line tool to the outer mold line tool. The inner mold line tool and the temporary removal layer may be removed from inside of the outer mold line tool after transferring the composite part and the temporary removal layer to the outer mold line tool.

US Patent:

8529721, Sep 10, 2013

Filed:

Jul 12, 2012

Appl. No.:

13/548057

Inventors:

Brian G. Robins - Renton WA, US
Darrell D. Jones - Mill Creek WA, US
Kurtis S. Willden - Kent WA, US
Daniel M. Rotter - Lake Forest Park WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B32B 37/00

US Classification:

156227, 156 52, 156 53, 156 54, 156 56, 156200, 156201, 156202, 156213, 156226, 156463, 156464, 156467, 1564771, 156475

Abstract:

A method and apparatus for a tray, a folding section connected to the tray, and a tape application system. The tray has a channel for receiving an elongate insert for a composite material with a number of layers for a release system. The folding section is capable of folding a number of layers around the elongate insert to cover the elongate insert as the elongate insert is moved through the folding unit. The tape application system is capable of applying a tape to the number of layers for covering the elongate insert to form the release system.

US Patent:

8601694, Dec 10, 2013

Filed:

Jun 13, 2008

Appl. No.:

12/138975

Inventors:

Joseph D. Brennan - Shoreline WA, US
Darrell D. Jones - Mill Creek WA, US
Brian G. Robins - Renton WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B21D 53/88

US Classification:

298972

Abstract:

A hands-free method and related apparatus are used to shape, place and compact a composite stringer on a composite skin of an aircraft. A composite charge is placed on a tool assembly that used to shape the charge into a preformed stringer. With the stringer held on the tool assembly, the tool assembly is used to move the preformed stringer into proximity with the skin and both place and compact the stringer against the skin. Following compaction of the stringer, the tool assembly is removed and the skin and the stringer are co-cured.

US Patent:

20040124954, Jul 1, 2004

Filed:

Dec 30, 2002

Appl. No.:

10/331869

Inventors:

Michael Strohecker - Palo Alto CA, US
Brian Robins - Tracy CA, US
Steve Holme - San Ramon CA, US

International Classification:

H01P001/208

US Classification:

333/208000, 333/126000

Abstract:

A multiplexer is constructed, which has a stable volume over its thermal operating range. A composite material is used that utilizes a fabric having fibers of opposing coefficients of thermal expansion. Such fibers are assembled at an angle to each other so that resulting expansion and contractions counter act and cancel. One of the fibers is selected for its high thermal conductivity and extends over the length of the multiplexer to form a heat dissipating path.