Edward H Coleman

US Patent:

7474944, Jan 6, 2009

Filed:

Apr 4, 2005

Appl. No.:

11/099684

Inventors:

Daniel H. Cartmell - Bellevue WA, US
Edward E. Coleman - Lake Forest Park WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 13/00
B64C 19/00

US Classification:

701 3, 701 4, 701 5, 701 8, 244 751, 244221, 244234

Abstract:

Methods and systems for linking input control signals, such as control signals used to control aspects of aircraft operation. In one embodiment, the method includes receiving first and second force signals corresponding to first and second forces applied to first and second controllers. The method can further include directing first and second position signals to the first and second controllers to move the first and second controllers to approximately the same positions. Each force signal is transmitted along a signal path, and the signal paths can be linked at a point where the signals on each path correspond to a quantity other that a position of a controller. The signal paths can be linked such that only one of the forces must exceed a threshold value for both controllers to be moved, and if one of the forces is outside a selected limit range, that force can be at least partially discounted.

US Patent:

8024079, Sep 20, 2011

Filed:

May 20, 2008

Appl. No.:

12/123942

Inventors:

Kioumars Najmabadi - Clyde Hill WA, US
William F. Shivitz - Renton WA, US
Edward Ernest Coleman - Forest Park WA, US
John Koon-hung Ho - Shoreline WA, US
Richard D. Johnson - Edmonds WA, US
William F. Carver - Shoreline WA, US
David W. Grubb - Monroe WA, US
Robert James McIntosh - Bothell WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G01C 23/00
G06F 17/10
B64C 3/58

US Classification:

701 3, 701124, 244 49, 244213

Abstract:

A computer implemented method, apparatus, and computer usable program product for symmetric and anti-symmetric control of aircraft flight control surfaces to reduce wing-body loads. Commands are sent to symmetrically deploy outboard control surfaces to shift wing air-loads inboard based on airplane state and speed brake deployment. Surface rate retraction on a wing with peak loads is limited to reduce maximum loads due to wheel checkback accompanied by utilization of opposite wing control surfaces to retain roll characteristics. Airloads are shifted inboard on a swept wing to move the center of pressure forward, thereby reducing the tail load required to perform a positive gravity maneuver. In a negative gravity maneuver, speed brakes are retracted, thereby reducing the positive tail load and reducing the aft body design loads. High gain feedback commands are filtered from wing structural modes above one hertz by a set of linear and non-linear filters.

US Patent:

8342445, Jan 1, 2013

Filed:

Sep 26, 2008

Appl. No.:

12/239278

Inventors:

Chuong B. Tran - Mukilteo WA, US
Kioumars Najmabadi - Bellevue WA, US
Edward E. Coleman - Lake Forest Park WA, US
David W. Grubb - Monroe WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

B64C 9/00

US Classification:

244 87, 244 89, 244 90 R, 244 321

Abstract:

A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit.

US Patent:

20040078121, Apr 22, 2004

Filed:

Oct 22, 2002

Appl. No.:

10/279092

Inventors:

Daniel Cartmell - Bellevue WA, US
Edward Coleman - Lake Forest Park WA, US

International Classification:

G06F017/00

US Classification:

701/003000, 244/175000

Abstract:

Methods and systems for linking input control signals, such as control signals used to control aspects of aircraft operation. In one embodiment, the method includes receiving first and second force signals corresponding to first and second forces applied to first and second controllers. The method can further include directing first and second position signals to the first and second controllers to move the first and second controllers to approximately the same positions. Each force signal is transmitted along a signal path, and the signal paths can be linked at a point where the signals on each path correspond to a quantity other that a position of a controller. The signal paths can be linked such that only one of the forces must exceed a threshold value for both controllers to be moved, and if one of the forces is outside a selected limit range, that force can be at least partially discounted.

US Patent:

20090157239, Jun 18, 2009

Filed:

Dec 17, 2007

Appl. No.:

11/958248

Inventors:

Vincent M. Walton - Federal Way WA, US
Christopher J. Borland - Bellevue WA, US
Tze L. Siu - Seattle WA, US
Kioumars Najmabadi - Clyde Hill WA, US
Edward E. Coleman - Seattle WA, US
David P. Marquis - Mukilteo WA, US
Dianne L. McMullin - Bothell WA, US

Assignee:

The Boeing Company - Chicago IL

International Classification:

G05D 1/00
G05D 1/08
G05D 1/04

US Classification:

701 6, 701 4

Abstract:

A method for vertical gust suppression due to turbulence for an aircraft having at least one of direct lift control surfaces or pitch control surfaces. The method includes sensing atmospheric turbulence, measuring the sensed atmospheric turbulence to generate turbulence data, generating a command based on the turbulence data, and applying the command to aircraft controls to actuate the direct lift control surfaces or the pitch control surfaces based on the turbulence data. Therefore, an aircraft response to the actuation of the direct lift control surfaces or the pitch control surfaces reduces a vertical acceleration, a pitch acceleration, a pitch rate, a pitch attitude or a structural load of the aircraft due to the turbulence. Thus, the method reduces the effects of vertical gusts of wind on the aircraft, improves the comfort level for aircraft passengers and crew, and reduces diversions the aircraft may take to avoid the turbulence.

US Patent:

20140067168, Mar 6, 2014

Filed:

Dec 16, 2012

Appl. No.:

13/716163

Inventors:

The Boeing Company - , US
Kioumars Najmabadi - Bellevue WA, US
Edward E. Coleman - Lake Forest Park WA, US
David W. Grubb - Monroe WA, US

Assignee:

THE BOEING COMPANY - Chicago IL

International Classification:

B64C 13/26

US Classification:

701 3, 701 21, 701 36

Abstract:

A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit.

US Patent:

61586951, Dec 12, 2000

Filed:

Sep 7, 1999

Appl. No.:

9/390183

Inventors:

Kioumars Najmabadi - Bellevue WA
Monte R. Evans - Federal Way WA
Edward E. Coleman - Lake Forest Park WA
Robert J. Bleeg - Mercer Island WA
Richard S. Breuhaus - Issaquah WA
Dorr M. Anderson - Seattle WA
Timothy A. Nelson - Kirkland WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 1316

US Classification:

244183

Abstract:

A method of providing speed protection to a neutrally-stable aircraft including the calculation of at least one of a stall protection signal and an overspeed protection signal. The aircraft includes a pitch control system having a command pitch signal received from pilot input to a control column. The protection signal is provided to the pitch control system to limit the commanded pitch signal during flight. The calculation of a stall protection signal includes differencing the aircraft's current airspeed with a reference speed and multiplying the difference by a scaling factor that corresponds to the force required by the pilot to move the control column. The calculation of an overspeed protection signal includes calculating a first signal based on airspeed, calculating a second signal based on Mach, selecting the large of the two signal and passing it through a limiter. The limiter is a function of roll attitude and corresponds to the force required by the pilot to move the control column. Also provided is a method of calculating a flare compensation signal to emulate ground effects encountered by an aircraft while executing a landing.

US Patent:

57226202, Mar 3, 1998

Filed:

May 15, 1995

Appl. No.:

8/441281

Inventors:

Kioumars Najmabadi - Bellevue WA
Monte R. Evans - Federal Way WA
Edward E. Coleman - Lake Forest Park WA
Robert J. Bleeg - Mercer Island WA
Richard S. Breuhaus - Issaquah WA
Dorr Marshall Anderson - Seattle WA
Timothy A. Nelson - Kirkland WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B64C 1318

US Classification:

244181

Abstract:

Disclosed is a pitch-axis stability and command augmentation system (19) in which a pilot column input (. delta. sub. C) is provided to a pitch command processor (26), the output of which is a C*U feedforward command (C*U. sub. FFC) that is supplied as an additive input to a combining unit (20). The combining unit (20) receives a second additive input of an augmented feedback command signal (AFB. sub. COM). The resulting output is filtered and generates an elevator command signal (. delta. sub. e,FILT). The command processor (26) additionally supplies a corrected column position signal (. delta. sub. C,COR) to a pitch command C*U processor (26) that converts the corrected column position signal (. delta. sub. C,COR) into a C*U pitch command (C*U. sub. PilotCmd), representative of the pilot's requested elevator pitch which is generated by movement of the control cola.