Kenneth H Griess

US Patent:

7333898, Feb 19, 2008

Filed:

Jun 5, 2006

Appl. No.:

11/422223

Inventors:

Kenneth H. Griess - Kent WA, US
Gary E. Georgeson - Federal Way WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G06F 19/00

US Classification:

702 35, 714 25

Abstract:

A system and method for assessing and monitoring a structure are provided. The system includes at least one non-destructive inspection sensor carried by the structure and configured for acquiring data in response to ambient events associated with the structure. The system also includes a data acquisition system configured to communicate with the non-destructive inspection sensor and provide information indicative of a defect in the structure based on the data acquired by the non-destructive inspection sensor in response to the ambient events.

US Patent:

7367236, May 6, 2008

Filed:

Jul 21, 2005

Appl. No.:

11/186021

Inventors:

Gary E. Georgeson - Federal Way WA, US
Kenneth H. Griess - Kent WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G01N 29/04

US Classification:

73801, 73 1209, 73802

Abstract:

An assembly, system, and method for identifying defects in a structure are provided. The assembly includes a structure of a metallic or composite material, and a flexible sheet of material positioned adjacent to the structure. The assembly also includes a plurality of non-destructive sensors secured to the flexible sheet, and a mechanism operable to impact the flexible sheet or proximate to the flexible sheet to generate stress waves within and along a surface of the structure. The system further provides a data acquisition system capable of communicating with the sensors such that the data acquisition system generates feedback indicative of at least a portion of the structure based on data from the stress waves acquired by the sensors.

US Patent:

7398698, Jul 15, 2008

Filed:

Nov 3, 2005

Appl. No.:

11/266499

Inventors:

Kenneth H. Griess - Kent WA, US
Gary E. Georgeson - Federal Way WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G01N 29/04
G01N 3/00

US Classification:

73801, 73 1208, 73802, 702 36

Abstract:

A system and method for identifying defects in a repair patch applied to a structure are provided. The system includes a sheet of material configured to be attached to the structure, and a mechanism operable to generate stress waves within and along the sheet of material. The system also includes a plurality of non-destructive sensors carried by the sheet of material. Each sensor is capable of detecting the stress waves. The system further includes a data acquisition system capable of communicating with the sensors such that the data acquisition system is also capable of generating information indicative of at least a portion of the sheet of material based on the data detected by the sensors.

US Patent:

7414189, Aug 19, 2008

Filed:

Sep 30, 2005

Appl. No.:

11/163001

Inventors:

Kenneth H. Griess - Kent WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H01B 7/00
H01B 7/34

US Classification:

174 36, 174110 R, 174113 R, 174119 R

Abstract:

A wire for integration with an airplane composite structure material includes a conductive core surrounded by an isolation layer for substantially isolating the conductive core from the composite structure material. The isolation layer includes braided fibers, and the braided fibers include a material having at least substantially similar properties as the composite structure material.

US Patent:

7735779, Jun 15, 2010

Filed:

Nov 2, 2006

Appl. No.:

11/555829

Inventors:

Kenneth H. Griess - Kent WA, US
Gary E Georgeson - Federal Way WA, US

Assignee:

The Boeing Company - Irvine CA

International Classification:

B64C 1/00

US Classification:

244119, 244120

Abstract:

A fuselage structure including an upper fuselage portion defined by a first cross-section including at least three different radii of curvature. The fuselage structure may also include a lower fuselage portion defined by a second cross-section including at least three different radii of curvature, wherein the first cross-section is different from the second cross-section.

US Patent:

7861970, Jan 4, 2011

Filed:

Aug 21, 2007

Appl. No.:

11/842414

Inventors:

Kenneth H. Griess - Kent WA, US
Gary E. Georgeson - Federal Way WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 1/00

US Classification:

244120, 244119

Abstract:

A fuselage structure for an aircraft or similar vehicle may include an upper fuselage portion and a lower fuselage portion. A floor may be disposed between the upper fuselage portion and the lower fuselage portion. At least one unitized stanchion may be disposed between the floor and the lower fuselage portion. The at least one unitized stanchion may form the only structural support between the floor and the lower fuselage portion without any vertical beams.

US Patent:

7948443, May 24, 2011

Filed:

Jan 23, 2008

Appl. No.:

12/018642

Inventors:

Steven J. Bullock - Riverside CA, US
Kenneth H. Griess - Kent WA, US
Otis F. Layton - Bonney Lake WA, US
Julio A. Navarro - Kent WA, US
Manny S. Urcia - Bellevue WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

H01Q 1/42

US Classification:

343789, 343700 MS, 343853

Abstract:

A structural phased array antenna and method for manufacturing are disclosed. An integrated structural antenna aperture can be used to reduce net weight, cost, and volume where an array of antenna elements are incorporated into a structural member, e. g. in a spacecraft. A structural material layer, such as a structural foam, may be used with the array of individual antenna element cavities machined into the layer. The antenna element cavities are lined with a conductive material, such as plated aluminum. Facesheets may be bonded to the front and/or backside of the structural material layer in order to increase strength and/or stiffness using an RF transparent material. The array of antenna elements may be coupled to filters at the back side of structural material layer.

US Patent:

7954760, Jun 7, 2011

Filed:

Jun 11, 2007

Appl. No.:

11/761193

Inventors:

Kenneth H. Griess - Kent WA, US
Gary E. Georgeson - Federal Way WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 1/20

US Classification:

2441181

Abstract:

Embodiments provide a cargo floor, a system, and a method adapted to be made integral with or complementary of the aircraft fuselage. Cargo floor members may be adapted to be coupled with a flat fuselage bottom inner skin of an aircraft fuselage to serve as the main orthotropic stiffeners to the flat fuselage bottom inner skin such that a portion of the in service loading experienced by the aircraft are shared by a combination of the fuselage and the cargo floor.