Wallace Chi Hua Chan

Address:

17314 16 Dr SE, Bothell, WA 98012

VIN:

5TDDK3EH3CS170950

Make:

TOYOTA

Model:

HIGHLANDER

Year:

2012

US Patent:

8061035, Nov 22, 2011

Filed:

Jan 18, 2008

Appl. No.:

12/016258

Inventors:

Jeffrey F. Stulc - Marysville WA, US
Wallace C. Chan - Mill Creek WA, US
Brian C. Clapp - Wichita KS, US
Neal G. Rolfes - Wichita WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B21D 53/88

US Classification:

298972, 29897, 5278712, 244119, 244120, 244132

Abstract:

Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

US Patent:

20060060705, Mar 23, 2006

Filed:

Sep 23, 2004

Appl. No.:

10/949848

Inventors:

Jeffrey Stulc - Seattle WA, US
Wallace Chan - Seattle WA, US
Brian Clapp - Seattle WA, US
Neal Rolfes - Seattle WA, US

International Classification:

B64C 1/00

US Classification:

244119000

Abstract:

Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

US Patent:

20120061512, Mar 15, 2012

Filed:

Nov 18, 2011

Appl. No.:

13/300487

Inventors:

Jeffrey F. Stulc - Seattle WA, US
Wallace C. Chan - Seattle WA, US
Brian C. Clapp - Seattle WA, US
Neal G. Rolfes - Seattle WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64C 1/06
B64D 11/00
B64C 1/14
B32B 3/24
B32B 3/28
B32B 3/00
B32B 3/12
B21D 53/88
B32B 3/30

US Classification:

2441185, 298972, 244119, 428172, 428174, 428 57, 428178, 428138

Abstract:

Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

US Patent:

20140001311, Jan 2, 2014

Filed:

Jul 2, 2012

Appl. No.:

13/540005

Inventors:

Bernhard Dopker - Bellevue WA, US
Wallace Chi-Hua Chan - Bothell WA, US
Henri Michael Ostroff - Seattle WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64C 1/00
B23P 11/00
B32B 37/12
B32B 38/04
B32B 38/00

US Classification:

244120, 156182, 29428

Abstract:

A fuselage having a longitudinal window belt has a composite outer skin including upper and lower composite skin sections. The skin includes at least one window opening located at the window belt. The upper and lower skin sections are joined together by a longitudinal splice joint located at the window belt.

US Patent:

20170183075, Jun 29, 2017

Filed:

Mar 15, 2017

Appl. No.:

15/459810

Inventors:

- Chicago IL, US
Wallace C. Chan - Seattle WA, US
Brian C. Clapp - Seattle WA, US
Neal G. Rolfes - Seattle WA, US

International Classification:

B64C 1/06
B64C 1/14
B64C 1/12

Abstract:

Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

US Patent:

20160339611, Nov 24, 2016

Filed:

May 22, 2015

Appl. No.:

14/720645

Inventors:

- Chicago IL, US
Wallace Chan - Bothell WA, US
Paul B. Diep - Bothell WA, US
Bernhard Dopker - Bellevue WA, US
David Gideon - Edmonds WA, US

International Classification:

B29C 43/18

Abstract:

An assembly of thermoplastic parts for forming a final composite part is presented where the assembly includes at least two prefabricated shells fabricated of thermoplastic. Each prefabricated shell has substantially the same shape as the final composite part and where the shapes of the prefabricated shells have dimensions that allow the prefabricated shells to be assembled into a nest for placement into a mold.

US Patent:

20160318596, Nov 3, 2016

Filed:

Jul 13, 2016

Appl. No.:

15/209129

Inventors:

- Chicago IL, US
Bernhard Dopker - Bellevue WA, US
Wallace Chi-Hua Chan - Bothell WA, US

International Classification:

B64C 1/12
B29C 65/56
B29C 65/00
B64C 1/10

Abstract:

A method of forming a direct bearing joint includes coupling a first load-bearing structure to a second load-bearing structure. The second load-bearing structure includes a first structural feature comprising a first arcuate shape. The method also includes coupling a composite skin including a second structural feature comprising a second arcuate shape to the second load-bearing structure. The composite skin is coupled to the second load-bearing structure such that the first and second structural features are mated against each other to facilitate distributing compressive loads from the second load-bearing structure into the composite skin.

US Patent:

20160251071, Sep 1, 2016

Filed:

Oct 28, 2014

Appl. No.:

14/525218

Inventors:

- Chicago IL, US
Wallace C. Chan - Seattle WA, US
Brian C. Clapp - Seattle WA, US
Neal G. Rolfes - Seattle WA, US

International Classification:

B64C 1/06
B64C 1/14
B64C 1/12

Abstract:

Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.