Daniel Q Robertson

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

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.

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

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.

US Patent:

7828525, Nov 9, 2010

Filed:

Aug 27, 2004

Appl. No.:

10/567886

Inventors:

Frank B. Stamps - Colleyville TX, US
Michael R. Smith - Colleyville TX, US
Christopher M. Bothwell - Grapevine TX, US
Lawrence M. Corso - Keller TX, US
David A. Popelka - Colleyville TX, US
Ernst C. Schellhase - Benbrook TX, US
Charles L. Hollimon - North Richland Hills TX, US
Thomas J. Newman - Midlothian TX, US
Bryan Baskin - Arlington TX, US
Thomas C. Campbell - Keller TX, US
Daniel B. Robertson - Southlake TX, US

Assignee:

Bell Helicopter Textron Inc. - Fort Worth TX

International Classification:

B64C 27/51

US Classification:

416134A, 416107, 416140, 416141, 416148, 1882821, 188283, 1882663, 1882991, 1883192, 18832215

Abstract:

A rotor hub assembly for a rotary-wing aircraft has a central member and a plurality of blade grips adapted for attaching rotor blades to the central member. The blade grips are pivotally attached to the central member and are capable of pivoting about a pivot axis generally normal to a plane of rotation of the blades. The pivoting allows for in-plane motion of the blades relative to the central member. A damper is operably connected to each blade grip for damping the in-plane motion of the associated blade, each damper being selectively switchable between at least two spring rates.

US Patent:

8181755, May 22, 2012

Filed:

Aug 27, 2004

Appl. No.:

10/568170

Inventors:

Frank B. Stamps - Colleyville TX, US
David A. Popelka - Colleyville TX, US
Michael R. Smith - Colleyville TX, US
Christopher M. Bothwell - Grapevine TX, US
Lawrence M. Corso - Keller TX, US
Ernst C. Schellhase - Benbrook TX, US
Charles L. Hollimon - North Richland Hills TX, US
Thomas J. Newman - Maypearl TX, US
Bryan Baskin - Arlington TX, US
Thomas C. Campbell - Keller TX, US
Daniel B. Robertson - Southlake TX, US

Assignee:

Textron Innovations Inc. - Providence RI

International Classification:

F16F 57/00
F16M 13/00

US Classification:

188290, 188317, 267136, 416134 A

Abstract:

A damper has a piston having an axis, an outer surface, and opposing ends. Elastomeric seals are in sealing contact with the outer surface of the piston, the seals being coaxial with the piston and limiting movement of the piston to a path along the axis of the piston. The seals also define fluid chambers adjacent the ends of the piston. A primary passage communicates the fluid chambers, and a selectively switchable valve for controls a flow of fluid from one of the chambers to another of the chambers through the primary passage. When the flow of fluid through the primary passage is permitted, movement of the piston is resisted by a first spring rate due to a shear force required to cause shear deflection of the seals. When the flow of fluid through the primary passage is restricted, movement of the piston is resisted by a second spring rate due to a fluid force required to cause bulging deflection of the seals.

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

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.

US Patent:

8469308, Jun 25, 2013

Filed:

Sep 2, 2011

Appl. No.:

13/224902

Inventors:

Daniel B. Robertson - Southlake TX, US
Kirk L. Groninga - Keller TX, US

Assignee:

Textron Innovations Inc. - Providence RI

International Classification:

B64C 15/00
B64C 27/22
B64C 27/82
B64C 3/48
B64C 29/00

US Classification:

244 52, 244 123, 244 1719, 244218

Abstract:

A system and method to control flight of an aircraft. The aircraft having an engine with a rotatably nozzle assembly configured to create forward propulsion and yaw control of the aircraft. The engine exhaust passing through the nozzle is redirected with a valve disposed within the nozzle. Lift is created with a lift system carried by the wing of the aircraft. Additional lift is created during flight with a retractable wing extension disposed within the wing of the aircraft.

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

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.

US Patent:

8636243, Jan 28, 2014

Filed:

Nov 12, 2010

Appl. No.:

13/580532

Inventors:

Daniel B. Robertson - Southlake 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 duct for receiving airflow from within a duct portion of a tailboom. The airflow is a mixture of fan driven air and engine exhaust. The system includes a fixed nozzle assembly with an anti-torque nozzle, a pro-torque nozzle and a thrust nozzle. A rotating sleeve valve is located within the fixed nozzle assembly. The rotating sleeve valve located within the fixed nozzle assembly and is configured to selectively redirect airflow into one or more of the anti-torque nozzle, the pro-torque nozzle and the thrust nozzle.