Douglas J Wilson

8052095, Nov 8, 2011

Jun 15, 2007

11/763754

Douglas L. Wilson - Mercer Island WA, US
Julie R. Brightwell - Everett WA, US
Christopher P. Beamis - Edmonds WA, US

The Boeing Company - Chicago IL

B64C 19/00

244188, 244183, 244 9912

Systems and methods for providing supplemental drag to an aircraft are disclosed. In one embodiment, a method includes detecting changes in at least one throttle resolver angle (TRA). Deflections are determined for one or more flight control surfaces based on the changes in TRA, and accordingly, the one or more flight control surfaces are deflected automatically to generate supplemental drag. The one or more flight control surfaces include at least one at least one of an aileron, a spoiler, and an elevator. Additionally, in one instance, the deflections of the one or more flight control surfaces is implemented as a rated limited time lag function of the changes in TRA.

20100100260, Apr 22, 2010

Oct 21, 2008

12/255233

Melville Duncan Walter McIntyre - Bellevue WA, US
Andrew William Houck - Woodinville WA, US
Russell Tanner Bridgewater - Monroe WA, US
Robert E. Freeman - Seattle WA, US
Paul Salo - Lynnwood WA, US
Douglas L. Wilson - Mercer Island WA, US
Jonathan K. Moore - Kirkland WA, US

G06F 19/00
G01S 19/14

701 6, 34235709

A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack.

20180356439, Dec 13, 2018

Jun 12, 2017

15/620224

- Chicago IL, US
Douglas Lee Wilson - Mercer Island WA, US

G01P 5/175
B64D 45/00
G01P 21/02

A system and method for estimating a plurality of airspeed parameters of an aircraft is disclosed. The system comprises one or more processors and a memory coupled to the processor. The memory storing data comprises a database and program code that, when executed by the one or more processors, causes the system to receive a plurality of operating parameters that each represent an operating condition of the aircraft. The system is further caused to determine a stability-axis drag coefficient based on the plurality of operating parameters. The stability-axis drag coefficient quantifies a stability-axis drag of the aircraft created during high speed conditions. The system is caused to determine a body-axis lift coefficient based on the plurality of operating parameters, which corresponds to a lift of the aircraft created along a vertical body-axis. The system is also caused to determine a dynamic pressure, which is used to estimate the airspeed parameters.

20170060141, Mar 2, 2017

Aug 31, 2015

14/840483

- Chicago IL, US
Douglas Lee Wilson - Mercer Island WA, US
Nikos Damian Mills - Seattle WA, US

G05D 1/08
B64D 43/02
B64D 31/06
G05D 1/06
B64C 13/16

An aircraft stall protection system and method include calculating a first angle of attack and a second angle of attack based on aircraft configuration and environmental conditions, the first angle of attack being greater than the second angle of attack. The system and method limit the actual aircraft angle of attack to the first angle of attack for a predetermined period of time and thereafter the system and method limit the actual aircraft angle of attack to the second angle of attack. The system and method allow the aircraft operator or pilot to extract maximum performance from the aircraft for any given set of flight conditions, without the risk of stalling or remaining in a high drag state for a prolonged period of time. This system and method are suitable for use in conjunction with a stall warning system.

20140330455, Nov 6, 2014

May 20, 2014

14/282875

- Chicago IL, US
Andrew W. HOUCK - Woodinville WA, US
Russell T. BRIDGEWATER - Monroe WA, US
Robert Erik FREEMAN - Seattle WA, US
Paul SALO - Lynnwood WA, US
Douglas L. WILSON - Mercer Island WA, US
Jonathan K. MOORE - Kirkland WA, US

The Boeing Company - Chicago IL

B64C 19/00
B64D 43/00

701 3

A method, apparatus, and computer program product for identifying air data for an aircraft. The lift for the aircraft is identified. The number of surface positions for the aircraft is identified. The angle of attack during flight of the aircraft is identified. A synthetic dynamic pressure is computed from the lift, the number of surface positions, and the angle of attack.