Tim H Barber Deceased301 N Colorado Ave, Mangum, OK 73554

2013005, Feb 28, 2013

Aug 29, 2011

13/220081

Timothy Hindle - Peoria AZ, US
Tim D. Barber - Litchfield Park AZ, US
Paul Buchele - Glendale AZ, US

HONEYWELL INTERNATIONAL INC. - Morristown NJ

F01D 25/04

415119

Embodiments of a gas turbine engine are provided, as are embodiments of an annular bearing support damper and embodiments of a method for manufacturing an annular bearing support damper. In one embodiment, the gas turbine engine includes engine housing and a rotor assembly disposed within the engine housing. A rotor bearing supports the rotor assembly within the engine housing, and an annular bearing support damper is positioned between the rotor bearing and the engine housing. The support damper includes an annular housing assembly having a damping fluid annulus. An array of circumferentially-spaced damper pistons is movably coupled to the annular housing assembly and fluidly communicates with the damping fluid annulus. The damper pistons are fixedly coupled to the rotor bearing and moves in conjunction therewith to force the flow of damping fluid around the annulus during engine operation to reduce the transmissions of vibrations to the engine housing.

2013011, May 9, 2013

Nov 4, 2011

13/289815

Ken Young - Peoria AZ, US
Timothy Hindle - Peoria AZ, US
Tim Daniel Barber - Litchfield Park AZ, US

HONEYWELL INTERNATIONAL INC. - Morristown NJ

F16F 15/00
F16C 11/06
F16M 13/00

248636, 248201, 403118

Mounting systems for structural members, fastening assemblies thereof, and vibration isolation systems including the same are provided. Mounting systems comprise a pair of mounting brackets, each clamped against a fastening assembly forming a mounting assembly. Fastening assemblies comprise a spherical rod end comprising a spherical member having a through opening and an integrally threaded shaft, first and second seating members on opposite sides of the spherical member and each having a through opening that is substantially coaxial with the spherical member through opening, and a partially threaded fastener that threadably engages each mounting bracket forming the mounting assembly. Structural members have axial end portions, each releasably coupled to a mounting bracket by the integrally threaded shaft. Axial end portions are threaded in opposite directions for permitting structural member rotation to adjust a length thereof to a substantially zero strain position. Structural members may be vibration isolator struts in vibration isolation systems.

2013013, May 30, 2013

Nov 30, 2011

13/308178

Tim Daniel Barber - Litchfield Park AZ, US
Timothy Hindle - Peoria AZ, US
Steven Hadden - Peoria AZ, US

HONEYWELL INTERNATIONAL INC. - Morristown NJ

B64D 27/26

244 54

Resilient aircraft engine mounts and mounting systems including the same are provided. A resilient aircraft engine mount comprises a base and a pair of opposed spiral springs in parallel forming a clevis with the base. A first spiral spring of the pair of opposed spiral springs has a first center opening extending therethrough. A second spiral spring of the pair of opposed spiral springs has a second center opening extending therethrough that is concentric with the first center opening for accepting a clevis pin. First and second spiral springs are each comprised of a rectangular cross section beam. The resilient aircraft engine mount is tunable in three translational axes to support three degrees of freedom vibration isolation. Two or more resilient aircraft engine mounts provide six degrees of freedom vibration isolation. Resilient aircraft engine mounts attach the aircraft engine to a pylon structure and help isolate vibratory forces.

2013022, Aug 29, 2013

Feb 28, 2012

13/406647

Tim Daniel Barber - Litchfield Park AZ, US
Timothy Hindle - Peoria AZ, US
Ken Young - Peoria AZ, US
Torey Davis - Peoria AZ, US

HONEYWELL INTERNATIONAL INC. - Morristown NJ

B64G 1/64

2441731

Embodiments of a launch lock assembly are provided, as are embodiments of a spacecraft isolation system including one or more launch lock assemblies. In one embodiment, the launch lock assembly includes first and second mount pieces, a releasable clamp device, and an axial gap amplification device. The releasable clamp device normally maintains the first and second mount pieces in clamped engagement; and, when actuated, releases the first and second mount pieces from clamped engagement to allow relative axial motion therebetween. The axial gap amplification device normally residing in a blocking position wherein the gap amplification device obstructs relative axial motion between the first and second mount pieces. The axial gap amplification device moves into a non-blocking position when the first and second mount pieces are released from clamped engagement to increase the range of axial motion between the first and second mount pieces.

2015022, Aug 13, 2015

Feb 11, 2014

14/177916

- Morristown NJ, US
Tim Daniel Barber - Litchfield Park AZ, US
Ken Young - Peoria AZ, US

HONEYWELL INTERNATIONAL INC. - Morristown NJ

F16F 9/36
F16F 9/19

Embodiments of an isolator are provided. In one embodiment, the isolator includes a damper housing having a radially-extending partition wall through which a central opening is formed. First and second hydraulic chambers are located on opposing sides of the radially-extending partition wall and may be filled with a damping fluid. At least one restricted orifice is formed through the damper housing and fluidly couples the first and second hydraulic chambers. The isolator further includes a damper piston, which extends through the central opening, which is exposed to the damping fluid when the first and second hydraulic chambers are filled therewith, and which is configured to translate along the working axis with respect to the damper housing during operation of the isolator.

2015019, Jul 9, 2015

Jan 9, 2014

14/151415

- Morristown NJ, US
Tim Daniel Barber - Litchfield Park AZ, US
Stella Silvana Dearing - Buckeye AZ, US
Ken Young - Peoria AZ, US

HONEYWELL INTERNATIONAL INC. - Morristown NJ

F16F 13/06
F16F 15/02

An apparatus is provided for vibration damping and isolation. The apparatus includes an annular spring portion including a resilient member that is substantially equally resilient in two dimensions, an annular bellows portion including at least two pairs of diametrically opposed bellows providing damping in the two dimensions, and a rigid connection member coupling the annular spring portion and the annular bellow portion in parallel to one another.