Doan D Pham

Address:

6386 Hidden Lk Cir, Richland, MI 49083

VIN:

3VWRZ7AJ9AM120999

Make:

VOLKSWAGEN

Model:

JETTA

Year:

2010

US Patent:

7014143, Mar 21, 2006

Filed:

Oct 11, 2002

Appl. No.:

10/269194

Inventors:

Doan D. Pham - Renton WA, US
Mark W. Tollan - Puyallup WA, US
Gregory R. Gleason - Seattle WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H05A 3/00

US Classification:

244 10, 244119, 244123

Abstract:

An aircraft panel assembly is provided, including a panel core a plurality of pre-preg layers surrounding the panel core forming an internal layer of plies at least one metal foil layer positioned on an outer layer of the internal layer of plies The at least one metal foil layer providing an electrical conduit between the outer surface of the aircraft panel assembly and a sub-structure for grounding.

US Patent:

7052573, May 30, 2006

Filed:

Nov 21, 2003

Appl. No.:

10/719219

Inventors:

Doan D. Pham - Renton WA, US
Michael A. Lee - Kent WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B29C 65/00

US Classification:

156286, 1563077, 244131, 264102

Abstract:

A method and article of manufacture of joining a stringer to a wing or tail panel and curing a wing or tail panel is disclosed. A sheet of titanium is placed between a cured stringer and an uncured wing or tail panel. The stringer, wing or tail panel and sheet are then placed within a vacuum bag, and gas is pumped out of the bag. The bag is then placed in an auto-clave to cure the wing or tail panel.

US Patent:

7357166, Apr 15, 2008

Filed:

Nov 24, 2004

Appl. No.:

10/904717

Inventors:

Doan D. Pham - Tacoma WA, US
Mark Tollan - Puyallup WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B29C 65/70
B32B 37/10
B28B 7/30

US Classification:

156382, 156500, 156581, 1565833, 425403, 264313

Abstract:

An aircraft stringer lay-up assembly is provided comprising a contoured curing block and a first mandrel element positioned thereon. The first mandrel assembly includes a first bar assembly having a plurality of rigidity reducing first slots formed along a first mandrel length. The plurality of rigidity reducing first slots protruding partially through a first mandrel depth of the first mandrel element to allow the first bar assembly to conform to the contoured curing block. A composite ply assembly is laid up onto the first mandrel element and cured while conformed to said contoured curing block such that a contoured composite stringer element is generated.

US Patent:

7459048, Dec 2, 2008

Filed:

Jan 31, 2006

Appl. No.:

11/343701

Inventors:

Doan D. Pham - Tacoma WA, US
Mark W. Tollan - Puyallup WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B65H 81/00

US Classification:

156173, 156169, 156175

Abstract:

A method of manufacturing a unitary seamless section of an aircraft fuselage comprises disposing a thin lay-up mandrel element onto the outer shell surface of a cylindrical inner mandrel shell, thereby forming a mandrel with a lay-up surface. A plurality of resin impregnated stiffener fibers may be layed-up within a plurality of stiffener channels in the lay-up surface to form a plurality of stiffeners or stringers. The method further includes laying up a plurality of resin impregnated skin fibers onto the lay-up surface while the mandrel rotates to form a unitary pre-cured section of an aircraft fuselage.

US Patent:

7588655, Sep 15, 2009

Filed:

Nov 24, 2004

Appl. No.:

10/904709

Inventors:

Doan D. Pham - Renton WA, US
Mark W. Tollan - Puyallup WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B32B 37/10
B29C 70/34
B29C 70/56
B29C 33/76

US Classification:

156227, 156245, 156267, 156285, 264231, 264313

Abstract:

An aircraft stringer lay-up assembly is provided comprising a first mandrel element having a first mandrel material with a first mandrel coefficient of thermal expansion. A composite ply assembly is laid up onto the first mandrel element to generate a primary lay-up surface. The composite ply assembly comprises a first primary fold-over portion folded onto to the first mandrel right end surface. A second primary fold over portion folds over to the first mandrel left end surface. The first mandrel coefficient of thermal expansion is adapted such that the first mandrel is movable between a first mandrel normal condition and a first mandrel heated condition where the first mandrel right end surface and the first mandrel left end surface move away from each other. The first primary fold-over portion and the secondary primary fold over portion are thereby moved such that wrinkles are pulled out of said primary lay-up surface.

US Patent:

7635106, Dec 22, 2009

Filed:

Nov 30, 2006

Appl. No.:

11/564964

Inventors:

Doan D. Pham - Tacoma WA, US
Mark W. Tollan - Puyallup WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 3/26
B64C 1/12

US Classification:

244131, 244132, 2441231

Abstract:

A composite shear tie for connecting a rib in a wing of an aircraft to a skin panel. The shear tie includes a web section having a first edge, a second edge, and a third edge. The web section is formed from a composite material. The first edge is parallel to the second edge, and the web section is configured to be connected to the rib in the wing of the aircraft. The shear tie also has a first free flange extending from the first edge, wherein the first free flange is around perpendicular to the web section and wherein the first free flange is formed from the composite material. A second free flange is present in the shear tie in which the second free flange extends from the second edge, wherein the second free flange is around perpendicular to the web section and wherein the second free flange is formed from the composite material. The shear tie has a base flange section extending from the third edge, wherein the first base flange is configured for attachment to the skin panel and wherein the first base flange is formed from the composite material.

US Patent:

7874518, Jan 25, 2011

Filed:

Mar 16, 2006

Appl. No.:

11/378791

Inventors:

Doan D. Pham - Renton WA, US
Michael A. Lee - Kent WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 1/12

US Classification:

244132

Abstract:

A method and article of manufacture of joining a stringer to a wing or tail panel and curing a wing or tail panel is disclosed. A sheet of titanium is placed between a cured stringer and an uncured wing or tail panel. The stringer, wing or tail panel and sheet are then placed within a vacuum bag, and gas is pumped out of the bag. The bag is then placed in an auto-clave to cure the wing or tail panel.

US Patent:

7901531, Mar 8, 2011

Filed:

Dec 26, 2007

Appl. No.:

11/964133

Inventors:

Doan D. Pham - Tacoma WA, US
Mark Tollan - Puyallup WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B32B 37/10
B29C 65/70
B29C 70/54
B29C 33/76

US Classification:

156245, 156285

Abstract:

An aircraft stringer lay-up assembly is provided comprising a contoured curing block and a first mandrel element positioned thereon. The first mandrel assembly includes a first bar assembly having a plurality of rigidity reducing first slots formed along a first mandrel length. The plurality of rigidity reducing first slots protruding partially through a first mandrel depth of the first mandrel element to allow the first bar assembly to conform to the contoured curing block. A composite ply assembly is laid up onto the first mandrel element and cured while conformed to said contoured curing block such that a contoured composite stringer element is generated.