Thomas A Newman

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:

20120230823, Sep 13, 2012

Filed:

May 1, 2012

Appl. No.:

13/461414

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 Richmond 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:

BELL HELICOPTER TEXTRON INC. - Fort Worth TX

International Classification:

B64C 11/12

US Classification:

416135

Abstract:

A rotor hub and method to dampen a force exerted on a rotor hub by a rotor blade during flight. The rotor hub including a central member rotatably coupled to a rotor mast, a blade grip rigidly attached to a blade and movably coupled to the central member, and an adjustable damper operably associated with the blade grip. The method includes damping the force exerted on the rotor hub with the adjustable damper and selectively adjusting the adjustable damper between a first spring rate and a second spring rate.

US Patent:

20170253327, Sep 7, 2017

Filed:

May 23, 2017

Appl. No.:

15/603119

Inventors:

- Fort Worth TX, US
Mithat Yuce - Lantana TX, US
Thomas J. Newman - Midlothian TX, US
Mark A. Wiinikka - Hurst TX, US

International Classification:

B64C 27/54
B64C 27/59

Abstract:

An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.

US Patent:

20150336664, Nov 26, 2015

Filed:

May 21, 2014

Appl. No.:

14/283515

Inventors:

- Fort Worth TX, US
Mithat Yuce - Lantana TX, US
Thomas J. Newman - Midlothian TX, US
Mark A. Wiinikka - Hurst TX, US

Assignee:

BELL HELICOPTER TEXTRON INC. - Fort Worth TX

International Classification:

B64C 27/54
B64C 27/51

Abstract:

An aircraft includes a rotor blade and a rotor hub system. The rotor hub system includes a lead-lag damper having a rod end and being operably associated with the rotor blade; a blade adapter having a first arm and an opposing second arm; a pin carried by the blade adapter and configured to secure in position via the first arm and the second arm; and an actuator secured to the pin and configured to adjust the position of the lead-lag rod end relative to the first arm and the second arm.