John M Mccullough

US Patent:

20120284970, Nov 15, 2012

Filed:

Feb 2, 2011

Appl. No.:

13/521397

Inventors:

Carl A. May - Mansfield TX, US
John R. McCullough - Weatherford TX, US
Ronald K. Cox - North Richland Hills TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - FORT WORTH TX

International Classification:

E04B 1/38
E04D 1/36

US Classification:

24304

Abstract:

An apparatus for attaching a member to a honeycomb core-stiffened structure includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of a honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus. A honeycomb core-stiffened structure includes a honeycomb core and an apparatus for attaching a member to the honeycomb core. The apparatus includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of the honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus.

US Patent:

20120308768, Dec 6, 2012

Filed:

Jul 15, 2011

Appl. No.:

13/578059

Inventors:

Suvankar Mishra - Carrollton TX, US
John R. McCullough - Weatherford TX, US
Mark Chris - Dallas TX, US
Stanley B. Woychesin - McKinney TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - Fort Worth TX

International Classification:

B32B 3/26
B29C 70/30
B32B 3/12
B29C 44/02

US Classification:

428116, 264 455, 156245, 4283044

Abstract:

A composite structure includes a first face sheet, a second face sheet, and a foam member located between the first face sheet and the second face sheet. The foam member has a molded contour, the mold contour being configured to provide tooling surface for at least one of the first face sheet and the second face sheet prior to curing of the composite structure. A method of making the foam member includes creating a mold tool having an interior surface which resembles the desired outer contour of the foam member. A mixture is poured into a pour opening in the mold tool. The mixture is allowed to polymerize into a foam as the foam expands and distributes within the mold tool. Vent openings in the mold tool are selectively tailored to control the density of the foam member. The foam member is cured in the mold tool.

US Patent:

57283109, Mar 17, 1998

Filed:

Aug 2, 1995

Appl. No.:

8/510287

Inventors:

Charles L. Ice - Grapevine TX
John V. McCullough - Santa Cruz CA

Assignee:

Forward Systems Automation - Grand Prairie TX

International Classification:

H05B 672

US Classification:

219679

Abstract:

There is provided a microwave waste sterilizer comprising an upper outer shell, a lower outer shell, an upper means for guiding microwave energy, a lower means for guiding microwave energy, an upper means for dispersing microwave energy, and a lower means for dispersing microwave energy. There is also provided a method for sterilizing waste materials with dual sources of microwave energy. Further there is provided a method for dispersing microwave energy into a chamber such that the dispersed microwave energy creates a flux field of substantially uniform flux.

US Patent:

20200115052, Apr 16, 2020

Filed:

Oct 16, 2018

Appl. No.:

16/161279

Inventors:

- Fort Worth TX, US
Joseph Scott DRENNAN - Dallas TX, US
Michael John RYAN - Colleyville TX, US
John Richard MCCULLOUGH - Weatherford TX, US
Brett Rodney ZIMMERMAN - Hurst TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64D 1/22
B64D 5/00
B64C 39/02
B64C 27/06

Abstract:

A system for deploying and retrieving a parasite aircraft includes a parasite aircraft with a dock and a carrier aircraft that includes a maneuverable capture device tethered to the carrier aircraft via a cable. The maneuverable capture device includes a plurality of rotors and is configured to dock in the dock of the parasite aircraft. A method of deploying a parasite aircraft includes positioning a parasite aircraft on a loading surface; positioning a carrier aircraft above the parasite aircraft; releasing, from the carrier aircraft, a maneuverable capture device comprising a plurality of rotors; securing the maneuverable capture device to a dock positioned on the parasite aircraft; lifting, via a cable secured at a first end to the carrier aircraft and at a second end to the maneuverable capture device, the parasite aircraft with the carrier aircraft; and releasing the parasite aircraft from the maneuverable capture device.

US Patent:

20190077502, Mar 14, 2019

Filed:

Sep 8, 2017

Appl. No.:

15/699677

Inventors:

- Fort Worth TX, US
Frank B. Stamps - Colleyville TX, US
Andrew Paul Haldeman - Fort Worth TX, US
Robert P. Wardlaw - Keller TX, US
John R. McCullough - Weatherford TX, US
Gary Miller - North Richland Hills TX, US
Andrew Ryan Maresh - Hurst TX, US
Drew A. Sutton - Georgetown KY, US

International Classification:

B64C 27/35
B64C 27/51
B64C 27/48
F16C 27/00

Abstract:

In one embodiment, a rotor hub comprises a hub plate, a yoke for attaching a plurality of rotor blades, a plurality of yoke support bearings, and a plurality of cushioned damper bearings for attaching a plurality of dampers.

US Patent:

20190039726, Feb 7, 2019

Filed:

Aug 2, 2017

Appl. No.:

15/666654

Inventors:

- Fort Worth TX, US
Nathan P. Green - Mansfield TX, US
John R. McCullough - Weatherford TX, US
Russell Cole - Euless TX, US
Paul Sherrill - Grapevine TX, US
Robert Wardlaw - Keller TX, US

International Classification:

B64C 27/00
F03D 3/06

Abstract:

The present invention includes a rotor-blade span-balancing system, including a span-balance pocket in a surface of a rotor blade; a cover operably configured to cover the span-balance pocket, wherein the cover is operably configured to be substantially flush with the surface of the rotor blade surface when covering the span-balance pocket, and wherein the cover includes a cover boss for reacting centrifugal force of the cover into the rotor blade; and one or more span-balance weights attached to the cover to span-balance the rotor blade.

US Patent:

20190039727, Feb 7, 2019

Filed:

Aug 1, 2017

Appl. No.:

15/666449

Inventors:

- Fort Worth TX, US
Nathan Patrick Green - Mansfield TX, US
John R. McCullough - Weatherford TX, US

International Classification:

B64C 27/35
B64C 27/48

Abstract:

A centrifugal force (CF) bearing for a rotorcraft rotor assembly includes an inner-member, an outer-member, and an elastic member interposed between the inner- and outer-members. The outer-member includes an upper flange extension and a lower flange extension for location to and engagement with a grip. The upper flange extension is disposed over an upper surface portion of the elastic member, and the lower flange extension is disposed under a lower surface portion of the elastic member. The CF bearing is configured for attachment to a grip of the rotor assembly. The outer-member is configured to communicate mechanical loads (e.g., centrifugal force, lateral shear, vertical shear) from the grip to the yoke during operation of the rotor assembly.

US Patent:

20170291701, Oct 12, 2017

Filed:

Jun 16, 2017

Appl. No.:

15/625598

Inventors:

- Forth Worth TX, US
Werner Idler - Arlington TX, US
John R. McCullough - Weatherford TX, US
Patrick Ryan Tisdale - Keller TX, US
Frank Bradley Stamps - Colleyville TX, US
Ronald J. Measom - Hurst TX, US
Paul K. Oldroyd - Azle TX, US

International Classification:

B64C 27/32
B29C 70/38

Abstract:

An apparatus comprising a soft in plane rotor yoke comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material having a plurality of first fibers oriented in a first direction, and a plurality of second layers formed of a second composite fabric material having a plurality of second fibers oriented in a second direction. Included is an apparatus comprising a soft in plane rotor comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material, and a plurality of second layers formed of a second composite fabric material, wherein the soft in plane rotor yoke does not comprise any narrow steered slit tape or filament windings.