James N Quitmeyer, 593871 Barberry Pl, Chandler, AZ 85248

7093696, Aug 22, 2006

Oct 25, 2004

10/973572

James N. Quitmeyer - Chandler AZ, US
Donald J. Christensen - Phoenix AZ, US
Kellan P. Geck - Chandler AZ, US

Honeywell International, Inc. - Morristown NJ

F16D 55/00

188 711, 188206 R

An aircraft brake actuation system includes an actuator for selectively moving to a position that corresponds to a commanded brake force. A cap assembly is coupled to the end of the actuator and is configured to engage an aircraft brake element and supply the commanded brake force to one or more aircraft wheels. The cap assembly is constructed of a low thermal conductivity material and has thermal resistance grooves formed therein. The cap assembly is also configured to compensate for certain undesired tangential movements that may occur during an aircraft brake cycle.

7096657, Aug 29, 2006

Dec 30, 2003

10/749852

Timothy D. Mahoney - Chandler AZ, US
James N. Quitmeyer - Chandler AZ, US
Darrell Horner - Oro Valley AZ, US
Jeff Miller - Tucson AZ, US

Honeywell International, Inc. - Morristown NJ

F02C 9/00

60 3925, 60794, 415 42, 415150

An electromechanical inlet guide vane actuation system includes one or more electric motor driven actuators that are used to appropriately position the inlet guide vanes in a gas turbine engine. The actuation system includes a control circuit that supplies guide vane actuation control signals in response to guide vane position command signals it receives. The guide vane actuation control signals are supplied to one or more electric motors, which position actuators, and thus the inlet guide vanes, to the commanded position.

7273067, Sep 25, 2007

Apr 14, 2005

11/107568

James N. Quitmeyer - Chandler AZ, US
Kellan P. Geck - Chandler AZ, US
Louie T. Gaines - Phoenix AZ, US
Jeff S. Rayner - Gilbert AZ, US
Charles M. Royalty - Tempe AZ, US

Honeywell International, Inc. - Morristown NJ

F16K 37/00

137553, 137559, 25112911

A relatively small, lightweight valve actuator assembly that can withstand relatively high levels of vibration and shock includes a motor, a position sensor, and a drive belt mounted on an actuator housing assembly. The position sensor is preferably disposed within a sensor housing that is mounted on a side of the actuator housing assembly. As a result, the overall center-of-gravity (CG) and weight of the actuator assembly is significantly reduced, as is the overall size envelope.

7317981, Jan 8, 2008

Nov 19, 2004

10/993608

Paul S. Evans - Gilbert AZ, US
James N. Quitmeyer - Chandler AZ, US

Honeywell International, Inc. - Morristown NJ

G06F 17/00
B60T 8/86

701 70, 701 3

An aircraft brake actuation system implements an anti-hysteresis feature that compensates for various hysteresis effects exhibited in an aircraft brake actuation system due to one or more sources of mechanical inefficiency within the system. The anti-hysteresis feature adjusts the command signal up or down, depending on the direction of the command, a predetermined amount based on the amount of hysteresis in the system. By doing so, the actual brake force supplied to the aircraft brake elements more accurately represents the brake force being commanded.

7560888, Jul 14, 2009

Sep 8, 2005

11/223325

James N. Quitmeyer - Chandler AZ, US
Kellan P. Geck - Chandler AZ, US
Paul S. Evans - Gilbert AZ, US

Honeywell International Inc. - Morristown NJ

G05B 11/18

318590, 318594, 318616

A relatively small, lightweight actuator includes a plurality of motors, an actuation element, a translation member, and a plurality of position sensors. The motors each supply a drive force to the actuation member, causing it to rotate. The translation member is configured, upon rotation of the actuator, to translate to a position. The position sensors sense the translational position of the translation member and the rotational position of each motor. The actuator is relatively small, lightweight, and can withstand the relatively severe environmental conditions and relatively significant levels of vibration and shock associated with many aerospace applications.

7629763, Dec 8, 2009

Jan 31, 2007

11/700271

James N. Quitmeyer - Chandler AZ, US
Dwayne M. Benson - Chandler AZ, US
Kellan P. Geck - Chandler AZ, US

Honeywell International Inc. - Morristown NJ

G05B 19/19

31856811, 318432, 3185682

An actuator assembly including an actuator housing assembly and a single axis of rotation locking member fixedly attached to a portion of the actuator housing assembly and an external mounting structure. The single axis of rotation locking member restricting rotational movement of the actuator housing assembly about at least one axis. The single axis of rotation locking member is coupled at a first end to the actuator housing assembly about a Y axis and at a 90 angle to an X and Z axis providing rotation of the actuator housing assembly about the Y axis. The single axis of rotation locking member is coupled at a second end to a mounting structure, and more particularly a mounting pin, about an X axis and at a 90 angle to a Y and Z axis providing rotation of the actuator housing assembly about the X axis. The actuator assembly is thereby restricted from rotation about the Z axis.

7775120, Aug 17, 2010

Sep 23, 2008

12/236345

Kevin Eugene Owens - Glendale AZ, US
Robert Jay Blome - Chandler AZ, US
Dwayne M. Benson - Chandler AZ, US
Steven Talbert Forrest - Phoenix AZ, US
James Neil Quitmeyer - Chandler AZ, US
Hugh Scott McDowell - Tempe AZ, US

Honeywell International Inc. - Morristown NJ

G01M 19/00

73777, 7311801, 73780

An electromechanical actuator test system includes an inertia simulator, a first load actuator, a second load actuator, and a test system control. The inertia simulator simulates the inertia of at least a portion of a system that is moved by a test actuator. The first load actuator supplies a first load to the inertia simulator to simulate at least one or more dynamic system loads, and the second load actuator supplies a second load to the inertia simulator to simulate at least one or more steady-state system loads. The test system control supplies the first actuator commands and the second actuator commands.

7960934, Jun 14, 2011

Sep 23, 2008

12/236326

Dwayne M. Benson - Chandler AZ, US
James Neil Quitmeyer - Chandler AZ, US
William Daugherty - Tucson AZ, US

Honeywell International Inc. - Morristown NJ

G05B 9/03

318564, 31840004, 318603, 318605, 318618

A fault-tolerant position feedback filter may be used in an actuation control system to limit the authority of a first position signal, should the first position signal become erroneous, and thereby prevent a postulated runaway condition of an acuator. The filter includes a difference function, a limited integrator, and a summer. The difference function supplies a first position error signal representative of a mathematical difference between a first position signal and a combined position signal. The limited integrator supplies an integrated position error signal that is limited in magnitude to a predetermined limit. The summer supplies the combined position error signal that is representative of a mathematical sum of the integrated position error signal and the second position signal.