Robert D Winkel, 79Peoria, AZ

7000308, Feb 21, 2006

Jan 31, 2002

10/062182

Stephen E. Fiske - Phoenix AZ, US
Robert E. Winkel - Phoenix AZ, US

Honeywell International Inc. - Morristown NJ

H02K 15/02

29598, 295275, 29732, 29596, 74 5 R

A method of constructing a rotor for a gyroscopic device is provided comprising fabricating a unitary assembly comprising a rim, a hollow shaft, a hub at each end of the shaft, a web that extends radially inward from the rim to one of the hubs at an angle to a spin axis of the rotor and machining the assembly. A second web may be welded between the rim and the second hub.

7299817, Nov 27, 2007

Sep 1, 2004

10/933093

Gary L. Gisler - Glendale AZ, US
James T. Hanks - Peoria AZ, US
Carlos J. Stevens - Peoria AZ, US
Robert E. Winkel - Phoenix AZ, US

Honeywell International, Inc. - Morristown NJ

F16K 17/36
G05D 16/06

137 811, 137 785

A valve is provided for use on a control moment gyroscope (CMG) having a housing separating an internal environment from an external environment. The valve includes a valve housing, a valve element, and bellows. The valve housing is configured to couple to the CMG housing and includes an inner surface defining a cavity, an outer surface, and an opening extending therebetween. The valve element is disposed within the valve housing cavity and is movable between a closed position, in which fluid is prevented from flowing through the valve housing opening, and an open position, in which fluid may flow through the valve housing opening. The bellows is disposed within the valve housing and coupled to the valve element and has an internal chamber. The bellows selectively moves the valve element closed and open in response to a differential pressure between the bellows internal chamber and the valve housing cavity.

7325769, Feb 5, 2008

Feb 25, 2005

11/067038

Paul E. Harnisch - Phoenix AZ, US
Robert E. Winkel - Phoenix AZ, US

Honeywell International, Inc. - Morristown NJ

F42B 10/64

244 328, 244 327

Methods and apparatus are provided for a missile that includes a housing, a fin, and a first actuator. The housing has a slot formed therethrough. The fin is disposed within the housing proximate the slot. The first actuator is coupled to the fin and configured to selectively move the fin at least partially in and out of the housing through the slot.

7690602, Apr 6, 2010

Mar 29, 2006

11/394037

Louis R. Jackson - Peoria AZ, US
Bruce W. Rogers - Glendale AZ, US
Robert E. Winkel - Phoenix AZ, US

Honeywell International Inc. - Morristown NJ

B64G 1/28

244165, 244170, 2441586

Methods and apparatus are provided for active motion damping of a spacecraft whose attitude control system (SACS) has experienced a partial failure. In a preferred embodiment, the apparatus comprises, an attitude control processor (ACP), a motion damping controller (MDC) coupled to the ACP, a control moment gyro (CMG) comprising a gimbal loop controller (GLC) coupled to the MDC and a gimbal motor with input coupled to the GLC and gyroscopic torque output coupled to the satellite. Normally, a gimbal rate command (GRC) from the ACP passes to the GLC for execution to rotate the CMG gimbal and the coupled satellite. If the ACP output becomes invalid, the MDC assumes control and can modify CMG operation in several ways to safely decelerate a moving satellite without hazardous mechanical stress. Following such active motion damping, the CMG remains quiescent until a RESET is received whereby further valid GRCs are then executable.

7721998, May 25, 2010

Mar 14, 2007

11/685931

Louis R. Jackson - Peoria AZ, US
Bruce W. Rogers - Glendale AZ, US
Robert E. Winkel - Phoenix AZ, US

Honeywell International Inc. - Morristown NJ

B64G 1/28

244165, 244164, 701 13

A system and method are provided for operating a control moment gyro (CMG) in a spacecraft. The CMG includes a spin motor, and a CMG rotor that is coupled to the spin motor and is configured to rotate about a spin axis. Electrical power from a power source is supplied to the spin motor to rotate the CMG rotor about the spin axis. A determination is made as to whether the power source can supply sufficient electrical power to the spin motor. If the power source cannot supply sufficient electrical power to the spin motor, the spin motor is rotated by the CMG rotor to generate and supply electrical power to the power source.

8002251, Aug 23, 2011

Nov 14, 2007

11/940032

Timothy A. Hindle - Peoria AZ, US
Toren S. Davis - Peoria AZ, US
Brian J. Hamilton - Glendale AZ, US
Robert E. Winkel - Phoenix AZ, US

Honeywell International Inc. - Morristown NJ

F16F 15/00
G01C 19/04

26714015, 26714011, 74 55, 74 5 F

A vibration reduction system is provided for use in conjunction with a rotational device including a stationary body, a rotating body, and a first bearing assembly disposed between the stationary body and the rotating body. The vibration reduction system includes a first plurality of bearing mount actuators residing between the stationary body and the first bearing assembly. The first plurality of bearing mount actuators is configured to adjust the radial position of the first bearing assembly. The vibration reduction system further includes a vibration sensor, which is coupled to the stationary body, and a controller, which is coupled to the vibration sensor and to the first plurality of bearing mount actuators. The controller is configured to reduce vibrations sensed by the vibration sensor by selectively adjusting the radial position of the first bearing assembly utilizing the first plurality of bearing mount actuators.

2004008, May 13, 2004

Nov 8, 2002

10/290653

Carlos Stevens - Peoria AZ, US
Robert Winkel - Phoenix AZ, US

F16H055/18

074/440000

In a gear train having a first gear, a second gear in mesh with the first gear, and a third gear in mesh with the second gear, an anti-backlash mechanism having a first anti-backlash gear positioned in operative relationship with the first gear and the second gear, a second anti-backlash gear positioned in operative relationship with the second gear and the third gear, whereby the first anti-backlash gear controls backlash between the first gear and the second gear, and the second anti-backlash gear controls backlash between the second gear and the third gear. Additionally, in a gear train having a first gear, a second gear in mesh with the first gear, and a third gear in mesh with the second gear, a method for reducing backlash comprising providing a first anti-backlash gear positioned in operative relationship with the first gear and the second gear, and providing a second anti-backlash gear positioned in operative relationship with the second gear and the third gear, whereby the first anti-backlash gear controls backlash between the first gear and the second gear, and the second anti-backlash gear controls backlash between the second gear and the third gear.

2009010, Apr 23, 2009

Oct 23, 2007

11/877409

Robert E. Winkel - Phoenix AZ, US
James T. Hanks - Peoria AZ, US
Gary L. Gisler - Glendale AZ, US
Dennis W. Smith - Phoenix AZ, US

HONEYWELL INTERNATIONAL, INC. - Morristown NJ

G01C 19/06

74 5 R

A rotor assembly includes a rotor assembly housing, a shaft, a bearing assembly coupling the shaft to the rotor assembly housing, and a mass structure coupled to and rotatable with the shaft. The bearing assembly includes a bearing housing, a first raceway defined in the bearing housing, a second raceway defined in the shaft, and a plurality of ball bearings positioned within the first and second raceways to enable the shaft to rotate relative to the rotor assembly housing.