John Alan Mccullough

Address:

1825 Christy Ct, Fort Worth, TX 76112

VIN:

YV4CY982971341236

Make:

VOLVO

Model:

XC90

Year:

2007

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:

20130026297, Jan 31, 2013

Filed:

Dec 28, 2010

Appl. No.:

13/641369

Inventors:

John R. McCullough - Weatherford TX, US
David Gordon Carlson - North Richland Hills TX, US
James Donn Hethcock - Colleyville TX, US
Paul K. Oldroyd - Azle TX, US
Carl A. May - Mansfield TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64C 3/18
B23P 11/00

US Classification:

244131, 298972

Abstract:

A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.

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:

60970154, Aug 1, 2000

Filed:

Oct 14, 1998

Appl. No.:

9/172028

Inventors:

John V. McCullough - Fort Worth TX
Charles L. Ice - Fort Worth TX
Jeremy W. Leonard - Dallas TX
Stephen Sherard - Richardson TX

Assignee:

Healthbridge, Inc. - Vancouver

International Classification:

G05B 1100

US Classification:

219686

Abstract:

A novel method and apparatus for sterilizing, disinfecting or otherwise heating materials, objects, liquids and the like under pressure is disclosed. The invention utilizes the generation and transmission of single-mode, non-interfering coaxial microwaves from multiple sources into the material to be treated. As a result, a more efficient transfer of microwave energy into the material to be treated is obtained.

US Patent:

20210403152, Dec 30, 2021

Filed:

Sep 10, 2021

Appl. No.:

17/472001

Inventors:

- Providence RI, US
John McCullough - Weatherford TX, US
Russell Steven Cole - Euless TX, US
Zachary Edwin Dailey - Grapevine TX, US

International Classification:

B64C 27/48
B29C 70/54

Abstract:

A rotorcraft main rotor system, including a yoke, a rotor blade, and a grip assembly attaching the rotor blade to the yoke. The grip assembly includes a grip body formed from a contiguous laminated composite and has a substantially constant thickness, where the grip body has an upper extension, a lower extension and a connecting portion connected between an inboard end of the upper extension and an inboard end of the lower extension. An inside surface of the upper extension faces, and is substantially parallel to, an inside surface of the lower extension, and the upper extension has first features and the lower extension has second features that are aligned with the first features, where the first features and second features each include at least one of an edge contour, attachment holes, or first protective elements.

US Patent:

20210300580, Sep 30, 2021

Filed:

Apr 8, 2021

Appl. No.:

17/225778

Inventors:

- Providence RI, US
John Richard McCullough - Weatherford TX, US

Assignee:

Textron Innovations Inc. - Providence RI

International Classification:

B64D 31/06
B64C 29/02
B64D 27/24
B64C 27/52
B64C 39/02
G05D 1/08

Abstract:

An aircraft has multiple independent yaw authority mechanisms. The aircraft includes an airframe having first and second wings with at least first and second pylons extending therebetween and with a plurality of tail members extending therefrom each having an active control surface. A two-dimensional distributed thrust array is coupled to the airframe that includes a plurality of propulsion assemblies each having a rotor assembly and each operable for thrust vectoring. A flight control system is operable to independently control each of the propulsion assemblies. A first yaw authority mechanism includes differential speed control of rotor assemblies rotating clockwise compared to rotor assemblies rotating counterclockwise. A second yaw authority mechanism includes differential longitudinal control surface maneuvers of control surfaces of two symmetrically disposed tail members. A third yaw authority mechanism includes differential thrust vectoring of propulsion assemblies.

US Patent:

20210237876, Aug 5, 2021

Filed:

Apr 6, 2021

Appl. No.:

17/223274

Inventors:

- Fort Worth TX, US
Carlos Alexander FENNY - Fort Worth TX, US
Michael John RYAN - Colleyville TX, US
John Richard MCCULLOUGH - Weatherford TX, US
Brett Rodney ZIMMERMAN - Hurst TX, US

Assignee:

Bell Textron Inc. - Fort Worth TX

International Classification:

B64D 5/00
B64C 1/06
B64C 3/56
B64C 3/54
B64D 3/00

Abstract:

A parasite aircraft for airborne deployment and retrieve includes a wing; a fuselage rotatably mounted to the wing; a dock disposed on top of the fuselage and configured to receive a maneuverable capture device of a carrier aircraft; a pair of tail members extending from the fuselage; and a plurality of landing gear mounted to the wing. A method of preparing a parasite aircraft for flight includes unfolding an end portion of a wing; unfolding an end portion of a tail member of the parasite aircraft; and rotating a fuselage of the parasite aircraft so that the fuselage is perpendicular to the wing. A method of preparing a parasite aircraft for storage includes rotating a fuselage of the parasite aircraft to be parallel with a wing of the parasite aircraft; folding an end portion of the wing; and folding an end portion of a tail member of the parasite aircraft.

US Patent:

20210114719, Apr 22, 2021

Filed:

Dec 26, 2020

Appl. No.:

17/134378

Inventors:

- Providence RI, US
Michael K. McNair - Weatherford TX, US
John Richard McCullough - Weatherford TX, US

Assignee:

Textron Innovations Inc. - Providence RI

International Classification:

B64C 27/00
B64D 27/10
B64C 27/08
B64D 27/24

Abstract:

A propulsion assembly for a rotorcraft includes a blade assembly, a drive shaft coupled to the blade assembly and an electric motor coupled to the drive shaft and operable to provide rotational energy to the drive shaft to rotate the blade assembly. The propulsion assembly includes a landing assistance turbine coupled to the drive shaft and operable to selectively provide rotational energy to the drive shaft during an underpowered descent to rotate the blade assembly and provide upward thrust, thereby reducing a descent rate of the rotorcraft prior to landing.