Douglas Haywood Swanson

US Patent:

6695294, Feb 24, 2004

Filed:

Jul 20, 2001

Appl. No.:

09/910386

Inventors:

Lane R. Miller - Fuquay-Varina NC
Douglas A. Swanson - Apex NC
Russell E. Alteri - Cary NC
Douglas E. Ivers - Cary NC
Stephen F. Hildebrand - Apex NC
William S. Jensen - Apex NC
Scott K. Miller - Raleigh NC
Michael D. Janowski - Clayton NC
Michael F. Walch - Cary NC

Assignee:

Lord Corporation - Cary NC

International Classification:

F16F 500

US Classification:

267 6416, 18832218

Abstract:

A controlled equilibrium device comprising a housing; at least one spring, each at least one spring having a spring stiffness; and a load leveling device movable through the housing between a first maximum displacement position and a second maximum displacement position, the load leveling device comprising a deadband displacement zone defined between a first deadband displacement threshold and a second deadband displacement threshold, the displacement required to reach the first and second deadband displacement thresholds being less than the displacement distances required to reach the first and second maximum displacement positions, the at least one spring stiffness being substantially constant when the displacement of the load leveling device is within the deadband zone, the stiffness of the at least one spring being modified to a second stiffness when the load leveling device is equal to or beyond either the first deadband displacement threshold or the second deadband displacement threshold.

US Patent:

7571876, Aug 11, 2009

Filed:

Mar 15, 2006

Appl. No.:

11/375945

Inventors:

Paul Joseph Bachmeyer - Cary NC, US
Douglas A. Swanson - Cary NC, US
Bryan J. Pittman - Fuquay-Varina NC, US
Scott K. Thompson - Erie PA, US
Doug A. Hodgson - Fuquay-Varina NC, US

Assignee:

Lord Corporation - Cary NC

International Classification:

B64C 25/00
F16F 1/00

US Classification:

244100R, 244102 R, 188381, 267134, 267136, 26714011

Abstract:

An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. The assembly includes a grease disposed between the outer elastomer surface and the nonelastomeric outer member frictional interface inner surface segment with the greased grooved outer elastomer surface engaging the nonelastomeric outer member frictional interface inner surface segment and inhibiting an oscillating rotation.

US Patent:

7686246, Mar 30, 2010

Filed:

Nov 19, 2007

Appl. No.:

11/942381

Inventors:

Askari Badre-Alam - Apex NC, US
Douglas Swanson - Cary NC, US
Jeffrey Cranmer - Holly Springs NC, US

Assignee:

Lord Corporation - Cary NC

International Classification:

B64C 11/00

US Classification:

244 1713, 244 1727

Abstract:

A method/system for controlling helicopter vibrations is provided that includes a vibration canceling force generator for actively generating a vibration canceling force. The system includes a resonant actuator having a natural resonant frequency and a resonant actuator electronic control system. The resonant actuator electronic control system provides an electrical drive current to the resonant actuator to drive the resonant actuator about the resonant frequency when commanded by a received command signal. The resonant actuator has a feedback output with the feedback output fed back into the resonant actuator electronic control system wherein the resonant actuator electronic control system adjusts the electrical drive current based on the resonant actuator feedback output to generate the vibration canceling force.

US Patent:

8162606, Apr 24, 2012

Filed:

Apr 7, 2009

Appl. No.:

12/419775

Inventors:

Mark R. Jolly - Raleigh NC, US
Andrew D. Meyers - Apex NC, US
Daniel Mellinger - Philadelphia PA, US
Douglas E. Ivers - Cary NC, US
Askari Badre-Alam - Apex NC, US
Douglas A. Swanson - Apex NC, US
Russell E. Altieri - Cary NC, US

Assignee:

Lord Corporation - Cary NC

International Classification:

F04D 29/26
F01D 5/26
B64C 11/00

US Classification:

416 1, 416 61, 416500, 415 1, 415119

Abstract:

A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, and a distributed force generation data communications network link.

US Patent:

8272592, Sep 25, 2012

Filed:

Dec 17, 2009

Appl. No.:

12/640149

Inventors:

Askari Badre-Alam - Apex NC, US
Douglas Swanson - Cary NC, US
Jeffrey Cranmer - Holly Springs NC, US

Assignee:

Lord Corporation - Cary NC

International Classification:

B64C 11/00

US Classification:

244 1713, 244 1727

Abstract:

A method/system for controlling helicopter vibrations is provided that includes a vibration canceling force generator for actively generating a vibration canceling force. The system includes a resonant actuator having a natural resonant frequency and a resonant actuator electronic control system. The resonant actuator electronic control system provides an electrical drive current to the resonant actuator to drive the resonant actuator about the resonant frequency when commanded by a received command signal. The resonant actuator has a feedback output with the feedback output fed back into the resonant actuator electronic control system wherein the resonant actuator electronic control system adjusts the electrical drive current based on the resonant actuator feedback output to generate the vibration canceling force.

US Patent:

8534600, Sep 17, 2013

Filed:

Aug 10, 2009

Appl. No.:

12/538241

Inventors:

Paul J. Bachmeyer - Verona, IT
Douglas A. Swanson - Cary NC, US
Bryan J. Pittman - Fuquay-Varina NC, US
Scott K. Thompson - Erie PA, US
Doug A. Hodgson - Fuquay-Varina NC, US

Assignee:

Lord Corporation - Cary NC

International Classification:

B64C 25/00
F16F 1/00

US Classification:

244100R, 244102 R, 188381, 267134, 267136, 26714011

Abstract:

An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. The assembly includes an elastomer encompassing the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment. The assembly includes a grease disposed between the outer elastomer surface and the nonelastomeric outer member frictional interface inner surface segment with the greased grooved outer elastomer surface engaging the nonelastomeric outer member frictional interface inner surface segment and inhibiting an oscillating rotation.

US Patent:

20090152396, Jun 18, 2009

Filed:

Dec 13, 2007

Appl. No.:

11/956118

Inventors:

Paul Joseph BACHMEYER - Verona, IT
Douglas A. SWANSON - Cary NC, US
Bryan J. PITTMAN - Fuquay-Varina NC, US
Scott K. THOMPSON - Erie PA, US
Doug HODGSON - Fuquay-Varina NC, US
Darrin M. JONES - Derby KS, US
Nicholas V. ANDERSON - Haysville KS, US

International Classification:

B64C 25/50

US Classification:

244104 R

Abstract:

An aircraft vehicular assembly is provided that includes a nonelastomeric outer tubular member having an inner axial center bore with a tubular cylindrical frictional interface contiguous smooth inner surface segment, and a nonelastomeric inner member having an outer bonding surface segment. The nonelastomeric inner member is rotationally received in the outer member inner axial center bore with the nonelastomeric inner strut member rotatable within said outer member. An elastomer encompasses the nonelastomeric inner strut member outer bonding surface segment. The elastomer has an inner bonding surface segment and an outer grooved elastomer surface, the inner bonding surface segment is bonded to the nonelastomeric inner member outer bonding surface segment.

US Patent:

20110208361, Aug 25, 2011

Filed:

Sep 4, 2009

Appl. No.:

13/062526

Inventors:

Stephen F. Hildebrand - Apex NC, US
Douglas Swanson - Apex NC, US
Matthew Ferguson - Erie PA, US
Matthew A. Smith - Erie PA, US

International Classification:

G05D 19/02
G06F 1/26

US Classification:

700280

Abstract:

A digital processing link for a vibration control system collects sensor signals at a transfer station and combines the sensor signals into a collective signal that is transmitted under a digital communications protocol to a base station. The sensor signals are separated at the base station and individually processed to produce one or more output control signals to actuators for counteracting the measured vibration.