Eric E Adamson

US Patent:

6857598, Feb 22, 2005

Filed:

Oct 9, 2003

Appl. No.:

10/683671

Inventors:

Eric E. Adamson - Newcastle WA, US
Paul W. Dees - Woodinville WA, US
Edward W. Gronenthal - Renton WA, US
Chester P. Nelson - Kirkland WA, US
Mithra M. Sankrithi - Lake Forest Park WA, US
Gerhard E. Seidel - Renton WA, US
V. Kenneth Stuhr - Seattle WA, US

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64D027/16

US Classification:

244 15, 244119, 244130, 244 55

Abstract:

Integrated high-speed aircraft, such as high-speed transport aircraft, and associated methods of manufacture. In one embodiment, a high-speed transport aircraft includes a fuselage having a first fuselage portion and a second fuselage portion positioned aft of the first fuselage portion. The first fuselage portion can have a first cross-sectional area and the second fuselage portion can have a second cross-sectional area that is less than the first cross-sectional area. The high-speed transport aircraft can further include a wing and a propulsion system. The wing can extend outwardly from the fuselage at least proximate to the second fuselage portion and can include a leading edge region and a trailing edge region. The propulsion system can include an engine nacelle fixedly attached to the wing and laterally aligned with the second fuselage portion. In one aspect of this embodiment, the engine nacelle can include an air inlet positioned aft of the leading edge region of the wing and an exhaust gas outlet positioned aft of the trailing edge region of the wing.

US Patent:

20060157613, Jul 20, 2006

Filed:

Jan 19, 2005

Appl. No.:

11/039651

Inventors:

Eric Adamson - Seattle WA, US
Chester Nelson - Seattle WA, US

International Classification:

B64C 1/40

US Classification:

24400100N

Abstract:

Methods and systems for actively reducing sonic boom in commercial supersonic aircraft and other supersonic aircraft are described herein. A method for operating an aircraft in accordance with one aspect of the invention includes configuring at least one lift control device to produce a first streamwise lift distribution, and flying the aircraft at a subsonic speed while the lift control device is configured to produce the first streamwise lift distribution. The method can further include configuring the lift control device to produce a second streamwise lift distribution, and flying the aircraft at a supersonic speed while the lift control device is configured to produce the second streamwise lift distribution. The first streamwise lift distribution produces an N-shaped ground pressure signature and a corresponding first sonic boom at the supersonic speed. The second streamwise lift distribution, however, produces a “shaped” ground pressure signature and a corresponding second sonic boom that is less than the first sonic boom at the supersonic speed.

US Patent:

20140076041, Mar 20, 2014

Filed:

Sep 20, 2012

Appl. No.:

13/623346

Inventors:

Eric E. Adamson - Newcastle WA, US
Alicia L. Bidwell - Seattle WA, US

Assignee:

THE BOEING COMPANY - Seal Beach CA

International Classification:

G01M 9/02
B23P 11/00

US Classification:

73147, 295921

Abstract:

A method for removing interference-induced distortion effects from an environment used to experimentally measure aerodynamic signatures. A space marching algorithm is used to extract the effects of environment including rail and wall reflections and rail edge effects to create an interference-free pressure signature.

US Patent:

20190367152, Dec 5, 2019

Filed:

Jun 4, 2018

Appl. No.:

15/997343

Inventors:

- Chicago IL, US
Adam P. Malachowski - Lynnwood WA, US
Bonnie R. Smith - Everett WA, US
Eric E. Adamson - Newcastle WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 3/14
B64C 9/24

Abstract:

A wing includes: an inner end configured to be coupled to a fuselage of an aircraft; an inboard section extending from the inner end; a fixed leading edge of the inboard section having a drooped contour positioned along at least a portion thereof; and an outboard section extending from the inboard section.