DUDLEY EDINGTON SMITH
Pilots at Danbury Dr, Arlington, TX
License number
Texas A1767587
Issued Date
Nov 2016
Expiration Date
Nov 2018
Category
Airmen
Type
Authorized Aircraft Instructor
Address
Address
3722 Danbury Dr, Arlington, TX 76016
Professional information
Method And Apparatus For In-Flight Blade Folding
US Patent:
2012029, Nov 22, 2012
Filed:
Jun 15, 2010
Appl. No.:
13/576612
Inventors:
Charles Hollimon - Fort Worth TX, US
Dudley E. Smith - Arlington TX, US
David Ludolph - Arlington TX, US
Dudley E. Smith - Arlington TX, US
David Ludolph - Arlington TX, US
Assignee:
BELL HELICOPTER TEXTRON INC - FORT WORTH TX
International Classification:
B64C 27/30, B64C 11/28, B64C 27/26, F01D 7/00
US Classification:
244 7 A, 416142
Abstract:
A foldable rotor system for a rotorcraft, the foldable rotor system comprising a rotor assembly operably associated with a driveshaft, the driveshaft being operable associated with an engine, the rotor assembly comprising a rotor blade connected to a grip pin. A swashplate is operable associated with the grip pin in order selectively change a pitch of the rotor blade. A blade fold actuator is operably associated with the grip pin such that the blade fold actuator is configured to fold and unfold the rotor blade about a blade fold axis. During an airplane mode, the rotorcraft can stop and fold the rotor blades so that the rotorcraft relies upon thrust from the engine for propulsion. The rotor blades are folded in a spiral fold path so that the rotor blades remain substantially edgewise, or feathered, during the folding process. The spiral fold path minimizes the aerodynamic drag experienced by the rotor blades while being folded during flight of the rotorcraft.
Propulsive Anti-Torque Nozzle System With External Rotating Sleeve For A Rotorcraft
US Patent:
8636242, Jan 28, 2014
Filed:
Nov 12, 2010
Appl. No.:
13/579002
Inventors:
Dudley E. Smith - Arlington TX, US
Assignee:
Textron Innovations Inc. - Providence RI
International Classification:
B64C 15/00, B64C 27/82
US Classification:
244 1719, 244 52
Abstract:
The system of the present application includes a system duct in fluid communication with a tailboom duct, the system duct having a downstream portion with an anti-torque cutout and a pro-torque cutout. The system further includes an anti-torque nozzle exteriorly proximate to the anti-torque cutout and a pro-torque nozzle exteriorly proximate to the pro-torque cutout. A rotating sleeve is configured to selectively allow airflow into at least one of the anti-torque nozzle and the pro-torque nozzle. A thrust nozzle is in fluid communication with the system duct. An upper clamshell and a lower clamshell are each configured to selectively control airflow in the thrust nozzle.
Counter-Torque Device For A Helicopter
US Patent:
8640984, Feb 4, 2014
Filed:
Aug 7, 2012
Appl. No.:
13/568262
Inventors:
John M. Kebrle - Dallas TX, US
James R. Andrews - Mansfield TX, US
Justin Daw - Fort Worth TX, US
Jim Hurdle - Fort Worth TX, US
Paul Sherrill - Grapevine TX, US
Jimmy C. Narramore - Bedford TX, US
Sidney Xue - Colleyville TX, US
Charles Hollimon - Forth Worth TX, US
Dudley Smith - Arlington TX, US
Bryce Docker - Arlington TX, US
John T. Brieger - Colleyville TX, US
James R. Andrews - Mansfield TX, US
Justin Daw - Fort Worth TX, US
Jim Hurdle - Fort Worth TX, US
Paul Sherrill - Grapevine TX, US
Jimmy C. Narramore - Bedford TX, US
Sidney Xue - Colleyville TX, US
Charles Hollimon - Forth Worth TX, US
Dudley Smith - Arlington TX, US
Bryce Docker - Arlington TX, US
John T. Brieger - Colleyville TX, US
Assignee:
Bell Helicopter Textron Inc. - Hurst TX
International Classification:
B64C 27/82
US Classification:
244 1719, 416203
Abstract:
A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub.
Proprotor Blade With Leading Edge Slot
US Patent:
7594625, Sep 29, 2009
Filed:
Jan 23, 2003
Appl. No.:
10/543222
Inventors:
Daniel B. Robertson - Southlake TX, US
Dudley E. Smith - Arlington TX, US
Charles L. Hollimon - North Richland Hills TX, US
Jimmy C. Narramore - Bedford TX, US
Robert B. Mullins - Mansfield TX, US
Dudley E. Smith - Arlington TX, US
Charles L. Hollimon - North Richland Hills TX, US
Jimmy C. Narramore - Bedford TX, US
Robert B. Mullins - Mansfield TX, US
Assignee:
Bell Helicopter Textron Inc. - Fort Worth TX
International Classification:
B64C 39/00
US Classification:
244 70, 416148, 416231 B
Abstract:
A proprotor blade () having a fixed, spanwise, leading edge slot () located in at least the inboard portion of the proprotor is disclosed. The slot () is formed by a selectively shaped slat () disposed in a selectively shaped recessed area () located at the leading edge () of the main portion of the proprotor blade. The slot () is selectively shaped so the a portion of the airflow over the lower airfoil surface of the proprotor blade is diverted between the main portion of the proprotor blade and the slat () and exits at the upper airfoil surface of the proprotor blade. The present invention may be used on both military-type tiltrotor aircraft () and civilian-type tiltrotor aircraft () with only minor variations to accommodate the different shapes of the proprotor blades.
Propulsive Anti-Torque System For Rotorcraft
US Patent:
7731121, Jun 8, 2010
Filed:
Sep 28, 2004
Appl. No.:
11/662559
Inventors:
Dudley E. Smith - Arlington TX, US
Walter C. Joiner - Arlington TX, US
Paul J. Madej - Grand Prairie TX, US
Charles L. Hollimon - North Richland Hills TX, US
Daniel B. Robertson - Southlake TX, US
Walter C. Joiner - Arlington TX, US
Paul J. Madej - Grand Prairie TX, US
Charles L. Hollimon - North Richland Hills TX, US
Daniel B. Robertson - Southlake TX, US
Assignee:
Bell Helicopter Textron Inc. - Fort Worth TX
International Classification:
B64C 27/82
US Classification:
244 1719, 244 23 D
Abstract:
A rotorcraft having an enhanced configuration in which a simple wing and a propulsive anti-torque system are combined is disclosed. The propulsive anti-torque system includes an anti-torque thruster system in which a variable pitch fan is installed internal to the tail boom of the rotorcraft and an anti-torque thruster nozzle is mounted at the extremity of the tail boom. The fan is driven directly from the main rotor drive. The configuration and location of the fan allows the primary exhaust from the engine to be mixed with the compressed air flow from the fan. The mixed air flow from the fan and the engine passes through the tail boom and out the thruster nozzle.
Multiple Drive-Path Transmission With Torque-Splitting Differential Mechanism
US Patent:
8141812, Mar 27, 2012
Filed:
Nov 14, 2006
Appl. No.:
12/446396
Inventors:
Frank B. Stamps - Colleyville TX, US
Dudley Smith - Arlington TX, US
Charles J. Kilmain - Fort Worth TX, US
Ryan Ehinger - Euless TX, US
Bob Collins - Bedford TX, US
Dudley Smith - Arlington TX, US
Charles J. Kilmain - Fort Worth TX, US
Ryan Ehinger - Euless TX, US
Bob Collins - Bedford TX, US
Assignee:
Textron Innovations Inc. - Providence RI
International Classification:
B64C 27/08
US Classification:
244 1723
Abstract:
A transmission for a rotary-wing aircraft has a differential torque-splitting mechanism associated with an input shaft. The differential has a drive disk coaxial with the shaft and integral in rotation with the shaft, a first driven member coaxial with the shaft and generally adjacent the drive disk, and a second driven member coaxial with the shaft and generally adjacent the drive disk. At least one pin engages each of the drive disk, the first driven member, and the second driven member. The first driven member is configured to drive a first transfer gear, and the second driven member is configured to drive a second transfer gear for supplying torque to a bull gear associated with a rotor mast.
Rotorcraft With Variable Incident Wing
US Patent:
8251305, Aug 28, 2012
Filed:
Feb 11, 2009
Appl. No.:
12/866904
Inventors:
Dudley E. Smith - Arlington TX, US
Walter C. Joiner - Arlington TX, US
Daniel B. Robertson - Southlake TX, US
David J. Ludolph - Arlington TX, US
Jennifer D. Langston - Coppell TX, US
Walter C. Joiner - Arlington TX, US
Daniel B. Robertson - Southlake TX, US
David J. Ludolph - Arlington TX, US
Jennifer D. Langston - Coppell TX, US
Assignee:
Textron Innovations Inc. - Providence RI
International Classification:
B64C 27/28
US Classification:
244 7C
Abstract:
A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position.
Multiple Drive-Path Transmission With Torque-Splitting Differential Mechanism
US Patent:
8356768, Jan 22, 2013
Filed:
Mar 26, 2012
Appl. No.:
13/429880
Inventors:
Frank B. Stamps - Colleyville TX, US
Dudley Smith - Arlington TX, US
Charles J. Kilmain - Fort Worth TX, US
Ryan Ehinger - Irving TX, US
Bob Collins - Bedford TX, US
Dudley Smith - Arlington TX, US
Charles J. Kilmain - Fort Worth TX, US
Ryan Ehinger - Irving TX, US
Bob Collins - Bedford TX, US
Assignee:
Textron Innovations Inc. - Providence RI
International Classification:
B64C 27/08
US Classification:
244 1723
Abstract:
A transmission for a rotary-wing aircraft has a differential torque-splitting mechanism associated with an input shaft. The differential has a drive disk coaxial with the shaft and integral in rotation with the shaft, a first driven member coaxial with the shaft and generally adjacent the drive disk, and a second driven member coaxial with the shaft and generally adjacent the drive disk. At least one pin engages each of the drive disk, the first driven member, and the second driven member. The first driven member is configured to drive a first transfer gear, and the second driven member is configured to drive a second transfer gear for supplying torque to a bull gear associated with a rotor mast.
Counter-Torque Device For A Helicopter
US Patent:
8286908, Oct 16, 2012
Filed:
Jul 15, 2005
Appl. No.:
11/632421
Inventors:
John M. Kebrle - Dallas TX, US
Justin Daw - Fort Worth TX, US
Jim Hurdle - Fort Worth TX, US
Paul Sherrill - Grapevine TX, US
Jimmy C. Narramore - Bedford TX, US
Sidney Xue - Colleyville TX, US
Charles Hollimon - Fort Worth TX, US
Dudley Smith - Arlington TX, US
Bryce Docker - Arlington TX, US
John T. Brieger - Colleyville TX, US
Justin Daw - Fort Worth TX, US
Jim Hurdle - Fort Worth TX, US
Paul Sherrill - Grapevine TX, US
Jimmy C. Narramore - Bedford TX, US
Sidney Xue - Colleyville TX, US
Charles Hollimon - Fort Worth TX, US
Dudley Smith - Arlington TX, US
Bryce Docker - Arlington TX, US
John T. Brieger - Colleyville TX, US
Assignee:
Bell Helicopter Textron Inc. - Hurst TX
International Classification:
B64C 27/82
US Classification:
244 1719, 416203
Abstract:
A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub.
Rotorcraft With Variable Incident Wing
US Patent:
8567709, Oct 29, 2013
Filed:
Aug 15, 2012
Appl. No.:
13/586020
Inventors:
Dudley E. Smith - Arlington TX, US
Walter C. Joiner - Arlington TX, US
Daniel B. Robertson - Southlake TX, US
David J. Ludolph - Arlington TX, US
Jennifer D. Langston - Coppell TX, US
Walter C. Joiner - Arlington TX, US
Daniel B. Robertson - Southlake TX, US
David J. Ludolph - Arlington TX, US
Jennifer D. Langston - Coppell TX, US
Assignee:
Textron Innovations Inc. - Providence RI
International Classification:
B64C 27/28
US Classification:
244 7C
Abstract:
A twin-rotor side-by-side compound rotorcraft has a fuselage and variable incident wing assembly that pivots relative to fuselage. The aircraft also has landing gear assembly and a tail fin assembly. The variable incident wing assembly is pivotally attached to the fuselage, and includes wing members, engines fixedly mounted to the wing members or another area of the rotorcraft, and a mast attached at a fixed angle relative to the wing members. Then engines may also be located near the fuselage or another area of the rotorcraft. The variable incident wing assembly is capable of pivoting about a pivot axis, thereby allowing mast orientation in at least a hover mast position and a forward flight mast position. The rotors provide additional forward thrust and the wings provide additional lift, when the mast is in the forward flight mast position.