Brian C Clapp from 3600 School Rd, Kintnersville, PA 18930, age 50, Phone: 2679991417

Us Patents

Splice Joints For Composite Aircraft Fuselages And Other Structures
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US Patent:

7325771, Feb 5, 2008
Filed:

Sep 23, 2004
Appl. No.:

10/949848
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 1/12
US Classification:

244119, 244120, 244132, 5278712
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.

Splice Joints For Composite Aircraft Fuselages And Other Structures
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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.

Splice Joints For Composite Aircraft Fuselages And Other Structures
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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.

Splice Joints For Composite Aircraft Fuselages And Other Structures
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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.

Splice Joints For Composite Aircraft Fuselages And Other Structures
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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.

Splice Joints For Composite Aircraft Fuselages And Other Structures
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US Patent:

20140165361, Jun 19, 2014
Filed:

Sep 2, 2011
Appl. No.:

13/225057
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
US Classification:

29428
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 disclosure 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 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.

Real Estate Brokers

Brian Clapp, Bellevue WA Real estate agent

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Specialties:

Buyer's Agent
Listing Agent

Work:

Prudential Northwest Realty
200 112Th Ave Ne Suite 200, Bellevue, WA 98004
2068985631 (Office)

Experience:

11 years

Description:

Why Sell your home with me? *I use advanced technology to expose your home professionally to the entire marketplace. * I also use tried and true "grassroots" marketing to give a blend of old and new. * I hire a professional photographer to take great pictures and develop a personal website for your home. * I purchase a home warranty policy to cover your home while it's on the market, and it transfers to the eventual buyer. * My 25 step marketing plan is proven to work, call or email me today and we can discuss in further detail! Why use me as your buyers agent? * Because I care, but don't just take my word for it, viewtheclient testimonials on my website, www.clapprealestate.com * I work at your pace, I don't believe in high pressure so I'll always follow your lead. * I purchase a 1-year home warranty to give you peace of mind from issues that can come up in your first year of ownership. * I'm a skilled negotiator, and I'll always fight to get you the best deal. Who am I? I was born and raised just outside of Boston, Massachusetts in a small apple town named Bolton. I graduated from the University of Delaware in 1992 and got hired by CNN/Sports Illustrated in Atlanta. In 2001 I moved to Seattle to work at Fox Sports Northwest, but after three years at Fox,I decided it was time for a change. For years I had consideredgetting into real estate and in 2004 I made the move. I love working inthis businessand I haven't looked back... even though it's tough to give up your press pass :)

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