Kevin K Chakkera from 2222 Iowa St, Chandler, AZ 85224, age 68, Phone: (480)9610539

Us Patents

Thrust Reverser Actuator Including An Integrated Locking Mechanism
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US Patent:

6487846, Dec 3, 2002
Filed:

Sep 7, 2001
Appl. No.:

09/949431
Inventors:

Kevin K. Chakkera - Tempe AZ
Andrew T. Johnson - Scottsdale AZ
Kyle D. Eilers - Everett WA
Assignee:

Honeywell International, Inc. - Morristown NJ
International Classification:

F02K 154
US Classification:

602262, 244110 B, 23926527
Abstract:

A thrust reverser system includes one or more actuators each having an integrated locking mechanism that prevents unintended actuator movement, and thus unintended thrust reverser movement. Each of the actuators with the integrated locking mechanism includes a housing, a drive shaft, and a lock. The drive shaft includes an outer surface, is rotationally mounted within the housing, and is operable, in response to the operation of the one or more motors, to rotate in a first rotational direction, to thereby move the thrust reverser to the deploy position, and a second rotational direction, to thereby move the thrust reverser to the stow position. The lock is movably mounted within the housing and is operable to move between at least a first position and a second position, and includes at least a side surface and a bottom surface. One or more gears are provided on the outer surface of the drive shaft, each of which is adapted to mesh with gears that are operably coupled to the thrust reverser. In addition, one or more protrusions extend from the outer surface of the drive shaft.

Jet Engine Thrust Reverser System Having Torque Limited Synchronization
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US Patent:

6598386, Jul 29, 2003
Filed:

Oct 16, 2001
Appl. No.:

09/981011
Inventors:

Andrew T. Johnson - Scottsdale AZ
Kevin K. Chakkera - Chandler AZ
Assignee:

Honeywell International, Inc. - Morristown NJ
International Classification:

F02K 176
US Classification:

602262, 244110 B, 23926529
Abstract:

A thrust reverser system that has one or more moveable thrust reverser components for redirecting the thrust of a jet engine. The thrust reverser system has a torque limiter coupled between synchronization mechanisms that mechanically couple actuators used to drive the thrust reverser. The torque limiter reduces the potential for the transmission of excessive torque between thevdifferent moveable thrust reverser components, and reduces the likelihood of secondary system damage due to a jam in the system. Thus, the cost and/or weight associated with each of the components comprising the system may be reduced.

System And Method For Controlling The Movement Of An Aircraft Engine Cowl Door
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US Patent:

6622963, Sep 23, 2003
Filed:

Apr 16, 2002
Appl. No.:

10/123785
Inventors:

Terry J. Ahrendt - Mesa AZ
Andrew T. Johnson - Scottsdale AZ
Kevin K. Chakkera - Chandler AZ
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

B64D 2700
US Classification:

244 54, 244 53 B, 602262, 248554
Abstract:

An electric control system and method for operating the cowl doors of an aircraft engine that includes one embodiment with one or more electric motors that are energized to move the cowl doors to the open position. The motor is de-energized and the cowl doors are allowed to close under their own weight, driving the motor and causing it to operate as a generator. An electrical load absorbs the energy generated by the motor while the cowl doors close, thereby limiting the speed at which the doors close.

System Architecture For Electromechanical Thrust Reverser Actuation Systems
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US Patent:

6655125, Dec 2, 2003
Filed:

Dec 5, 2001
Appl. No.:

10/006640
Inventors:

Andrew T. Johnson - Scottsdale AZ
Terry J. Ahrendt - Mesa AZ
Richard J. Foley - Tempe AZ
Michael R. Madsen - Rocky Mount NC
Kevin K. Chakkera - Chandler AZ
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F02K 176
US Classification:

602262, 244110 B, 23926519
Abstract:

An electromechanical thrust reverser actuation system that is designed with non-symmetric redundant channels is interfaced with an aircraft engine control system that is also redundantly designed. In one embodiment, the engine control system is also designed with non-symmetric redundant channels, and in another embodiment it is designed with symmetric redundant channels.

Thrust Reverser Actuator With An Automatic Relock And Lock Drop Prevention Mechanism
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US Patent:

6786039, Sep 7, 2004
Filed:

Sep 3, 2002
Appl. No.:

10/233752
Inventors:

Kevin K. Chakkera - Chandler AZ
Donald J. Christensen - Phoenix AZ
Andrew T. Johnson - Scottsdale AZ
Assignee:

Honeywell International, Inc. - Morristown NJ
International Classification:

F02K 170
US Classification:

602262, 244110 B, 23926529, 23926531
Abstract:

A thrust reverser system includes one or more actuators each having a locking mechanism that prevents unintended actuator movement, and thus unintended thrust reverser movement. Each of the actuators additionally includes a lock inhibitor assembly that engages the lock and prevents it from moving to its locked position until the actuator is moved into a stow position. Upon movement to the stow position, the lock inhibitor assembly disengages the lock, and the lock automatically moves into its locked position.

Thrust Reverser System Electro-Mechanical Brake Manual Release Mechanism
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US Patent:

7093424, Aug 22, 2006
Filed:

Aug 24, 2004
Appl. No.:

10/925700
Inventors:

Casey Hanlon - Queen Creek AZ, US
Donald J. Christensen - Phoenix AZ, US
Kevin K. Chakkera - Chandler AZ, US
Assignee:

Honeywell International, Inc. - Morristown NJ
International Classification:

F02K 1/70
F02K 1/76
US Classification:

602262, 244110 B, 23926523
Abstract:

A manual release mechanism for a thrust reverser actuation system electromechanical brake includes a first release plate, a second release plate, at least two balls, and a handle. The first and second release plates each have grooves formed therein that have a cam surface located at a predetermined angle. The release plates face one another such that the grooves in each plate are substantially aligned, and the balls are each positioned in the aligned grooves. The first release plate is configured to rotate, and the second release plate is configured to translate. The handle is coupled to the first release plate to allow manual rotation thereof. In response to rotation of the first release plate, the second release plate will translate and disengage the electromechanical brake.

Spline With Lubricant Retention Feature For Use In Torque Limiter
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US Patent:

7491127, Feb 17, 2009
Filed:

Apr 27, 2006
Appl. No.:

11/414645
Inventors:

Brent L. Bristol - Phoenix AZ, US
Remo N. Neri - Cave Creek AZ, US
Kevin K. Chakkera - Chandler AZ, US
David M. Mathis - Phoenix AZ, US
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F16D 3/06
US Classification:

464 16, 4033596
Abstract:

A torque limiter for use on an aircraft comprises a drive shaft having a toothed outer portion, an output shaft, and a spline having an aperture therethrough for receiving the toothed portion. The spline is configured to rotationally couple the drive shaft to the output shaft and to rotationally disengage from the output shaft when the torque at the drive shaft exceeds a predetermined torque threshold. The spline comprises an outer annular portion and an inner annular portion configured to receive a lubricant. The inner annular portion comprises a plurality of circumferentially-spaced tooth structures and root structures. At least one of the root structures has at least one slot therein for receiving and retaining the lubricant.

Bi-Directional Locking Ring Assembly For Aircraft Thrust Reverser Manual Drive Unit
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US Patent:

7946105, May 24, 2011
Filed:

Nov 2, 2006
Appl. No.:

11/592468
Inventors:

Brent L. Bristol - Phoenix AZ, US
Kevin K. Chakkera - Chandler AZ, US
Peter J. Auer - Chandler AZ, US
Remo N. Neri - Cave Creek AZ, US
Assignee:

Honeywell International Inc. - Morristown NJ
International Classification:

F02K 3/02
F02K 1/00
F02K 1/54
US Classification:

602262, 60230, 244110 B
Abstract:

A bi-directional locking ring assembly is provided comprising a housing and a gear having a plurality of teeth. The gear is coupled to the housing to rotate in opposite directions about a rotational axis. A pin is also coupled to the housing and has an apex configured to travel along a line that does not pass through the rotational axis of the gear. The pin is configured to translate between (1) a disengaged position wherein the gear is free to rotate, and (2) an engaged position wherein the apex resides between two of the plurality of teeth to prevent rotation of the gear in both rotational directions. A pin actuator is coupled to the housing and configured to engage the pin to selectively lock the pin in the engaged position.