David P Manley

US Patent:

7635107, Dec 22, 2009

Filed:

Aug 9, 2005

Appl. No.:

11/200515

Inventors:

Arvin Shmilovich - Huntington Beach CA, US
Yoram Yadlin - Irvine CA, US
Roger W. Clark - Huntington Beach CA, US
David J. Manley - Huntington Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 21/04

US Classification:

244207, 244208

Abstract:

A system and method for controlling boundary layer flow over an aircraft wing are provided. The system includes at least one wing element, and a plurality of ports defined in the wing element and in fluid communication with one another. The system also includes at least one fluidic device operable to continuously ingest the fluid through at least one of the ports and eject the fluid out of at least one other port to control boundary layer flow of the fluid over the wing element.

US Patent:

D616804, Jun 1, 2010

Filed:

Oct 3, 2008

Appl. No.:

29/325636

Inventors:

David J. Manley - Huntington Beach CA, US
Aaron J. Kutzmann - Long Beach CA, US
John C. Vassberg - Long Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

1207

US Classification:

D12319

US Patent:

8061655, Nov 22, 2011

Filed:

Mar 25, 2009

Appl. No.:

12/410813

Inventors:

David J. Manley - Huntington Beach CA, US
Aaron J. Kutzmann - Long Beach CA, US
Robb Gregg, III - Fullerton CA, US
John C. Vassberg - Long Beach CA, US
Antonio B. Gonzales - Cypress CA, US
Steve Hollowell - Huntington Beach CA, US
Neal Harrison - San Clemente CA, US
Edward Lawson - Long Beach CA, US
Max Kismarton - Renton WA, US
Kevin Lutke - Huntington Beach CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 1/00

US Classification:

244120, 244119, 244207

Abstract:

Apparatus and methods provide for an aircraft configuration that utilize structural and engine exhaust flow control devices to enhance performance. Aspects of the disclosure provide a fuselage with a pressure vessel nested within a non-cylindrical outer mold line fairing. A twin-boom empennage may be connected to the fuselage. A wing may attach in a blended wing configuration with a sweep angle that positions the aircraft center of lift to minimize any pitching moment induced by the activation or deactivation of an upper surface blown (USB) system. The USB system may include a conformal USB flap positioned downstream of an engine exhaust plume, as well as a controllable USB nozzle aperture to promote exhaust flow attachment to the conformal USB flap. A universal convergent nozzle may be utilized to connect each controllable USB nozzle aperture to a corresponding internally mounted aircraft engine.

US Patent:

8382045, Feb 26, 2013

Filed:

Jul 21, 2009

Appl. No.:

12/506462

Inventors:

David J. Manley - Huntington Beach CA, US
Robert E. Grip - Rancho Palos Verdes CA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 3/44

US Classification:

244219, 244218, 244213

Abstract:

A method and apparatus for controlling the shape of a control surface. A structure is rotated about an axis. The structure is located between a flexible skin and a skin located substantially opposite of the flexible skin. An assembly is moved to change the shape of the control surface in response to a rotation of the structure. The assembly is movably connected to the structure and is configured to move such that the flexible skin forms a plurality of curvatures.

US Patent:

20060102801, May 18, 2006

Filed:

Nov 1, 2004

Appl. No.:

10/980147

Inventors:

David Manley - Huntington Beach CA, US

International Classification:

B64C 21/06

US Classification:

244208000

Abstract:

The present invention is directed to a distributed active flow control (“DAFC”) system that maintains attached airflow over a highly cambered airfoil employed by an aircraft or other similar applications. The DAFC system includes a primary power source comprised of one or more aircraft engines, one or more power conversion units, and optionally, one or more auxiliary power units. The power conversion units are coupled to one or more aircraft engines for supplying power to a distribution network. The distribution network disperses power from the one or more power conversion units to active flow control units disposed within one or more aircraft flight control surfaces (e.g., the aircraft wing, the tail, the flaps, the slats, the ailerons, and the like). In one embodiment, an auxiliary power unit is included for providing a redundant and auxiliary power supply to the distribution network. In another embodiment, a back-up power source is provided in communication with the distribution network for providing an additional redundant power supply.

US Patent:

20080173766, Jul 24, 2008

Filed:

Jul 26, 2007

Appl. No.:

11/828437

Inventors:

David J. Manley - Huntington Beach CA, US

International Classification:

B64C 21/00
B64C 21/06
B64C 21/04

US Classification:

244208, 244204

Abstract:

The present invention is directed to a distributed active flow control (“DAFC”) system that maintains attached airflow over a highly cambered airfoil employed by an aircraft or other similar applications. The DAFC system includes a primary power source comprised of one or more aircraft engines, one or more power conversion units, and optionally, one or more auxiliary power units. The power conversion units are coupled to one or more aircraft engines for supplying power to a distribution network. The distribution network disperses power from the one or more power conversion units to active flow control units disposed within one or more aircraft flight control surfaces (e.g., the aircraft wing, the tail, the flaps, the slats, the ailerons, and the like). In one embodiment, an auxiliary power unit is included for providing a redundant and auxiliary power supply to the distribution network. In another embodiment, a back-up power source is provided in communication with the distribution network for providing an additional redundant power supply.