Douglas E Ivers

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:

6983833, Jan 10, 2006

Filed:

May 16, 2003

Appl. No.:

10/439572

Inventors:

Douglas E. Ivers - Cary NC, US

Assignee:

LORD Corporation - Cary NC

International Classification:

F16F 7/10

US Classification:

188379

Abstract:

A system and method for absorbing vehicle body vibrations is described. The mechanical self-tuning vibration absorber system is utilized to absorb a body vibration with a varying frequency. In a particular application the absorber system provides for absorbing varying frequency vibrations of a helicopter aircraft body. The vibration absorber system utilizes asymmetrical damping to tune the resonant frequency of the system.

US Patent:

7448854, Nov 11, 2008

Filed:

Aug 30, 2005

Appl. No.:

11/215388

Inventors:

Mark Jolly - Raleigh NC, US
Stephen Hildebrand - Apex NC, US
Russell Altieri - Cary NC, US
Matthew Ferguson - Erie PA, US
Douglas Ivers - Cary NC, US

Assignee:

Lord Corporation - Cary NC

International Classification:

F04D 29/26

US Classification:

416 1, 415119, 416 24, 416 98

Abstract:

Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass. The electronics housing cavity contains an electronics control system which receives sensor outputs and electrically controls and drives the first motor and the second motor such that the first imbalance mass and the second imbalance mass are driven at a vibration canceling rotation frequency greater than the operational rotation frequency wherein the helicopter rotary wing hub periodic vibrations are reduced.

US Patent:

7942248, May 17, 2011

Filed:

Dec 31, 2002

Appl. No.:

10/334200

Inventors:

Kenneth A. St. Clair - Cary NC, US
Kenneth R. Boone - Cary NC, US
Douglas E. Ivers - Cary NC, US

Assignee:

LORD Corporation - Cary NC

International Classification:

F16F 9/53

US Classification:

1882671, 1882672

Abstract:

A damper device comprising a first mode having a first level of damping, a second mode having a second level of damping corresponding to a predetermined function, a sensor system having a first output corresponding to a normal position and a second output corresponding to an end stop approaching position, and a control system operable for receiving the first output and the second output and executing the first mode and the second mode. The damper device is operable in the first mode when the control system receives the first output and is operable in the second mode when the control system receives the second output. A controllable suspension system comprising a damper device, a magnetic probe, a sensor system comprising at least one position sensor operable for sensing the position of the magnetic probe, and a control system electronically connected to the sensor system and the damper device, wherein the control system is operable for receiving an output from the sensor system and executing a predetermined function to control the damper device. Electric signals are supplied to the damper device from the control system during system operation to provide damping sufficient to prevent end stop collisions.

US Patent:

7942633, May 17, 2011

Filed:

Sep 30, 2008

Appl. No.:

12/286461

Inventors:

Mark Jolly - Raleigh NC, US
Stephen Hildebrand - Apex NC, US
Russell Altieri - Cary NC, US
Matthew Ferguson - Erie PA, US
Douglas Ivers - Cary NC, US

Assignee:

LORD Corporation - Cary NC

International Classification:

F01D 5/26

US Classification:

416 1, 416 24, 416 98, 415 1, 415116

Abstract:

Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass. The electronics housing cavity contains an electronics control system which receives sensor outputs and electrically controls and drives the first motor and the second motor such that the first imbalance mass and the second imbalance mass are driven at a vibration canceling rotation frequency greater than the operational rotation frequency wherein the helicopter rotary wing hub periodic vibrations are reduced.

US Patent:

8033358, Oct 11, 2011

Filed:

Apr 25, 2008

Appl. No.:

12/109675

Inventors:

Douglas E. Ivers - Cary NC, US

Assignee:

Lord Corporation - Cary NC

International Classification:

B64D 33/02
F01N 1/06
B64D 33/00
F01N 1/00
F04D 29/66

US Classification:

181214, 181250, 181254, 181278, 244 1 N, 244 53 B, 415119

Abstract:

An aircraft turbine engine with a takeoff fan speed and a landing fan speed, the aircraft engine includes a fan duct with a HQ (Herschel-Quincke) acoustic control noise reduction tube. The acoustic control noise reduction tube contains a movable frequency tuner obstruction. The movable frequency tuner obstruction is movable within the acoustic control noise reduction tube, with the movable frequency tuner obstruction movable along a fixed tube path length between a first takeoff frequency obstruction tube path location, and a second landing frequency obstruction tube path location, with the frequency tuner obstruction positioned at the first takeoff frequency location with the takeoff speed, and the frequency tuner obstruction positioned at the second landing frequency location with the landing speed to reduce noise.

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:

8313296, Nov 20, 2012

Filed:

May 16, 2011

Appl. No.:

13/108080

Inventors:

Mark Jolly - Raleigh NC, US
Stephen Hildebrand - Apex NC, US
Russell Altieri - Cary NC, US
Matthew Ferguson - Erie PA, US
Douglas Ivers - Cary NC, US

Assignee:

Lord Corporation - Cary NC

International Classification:

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

US Classification:

416 55, 416 60, 416 61, 416500, 415119

Abstract:

Helicopter rotating hub mounted vibration control system for a rotary wing hub having periodic vibrations while rotating at an operational rotation frequency. The vibration control system includes a housing attachable to the rotary wing hub and rotating with the hub at the operational frequency. The housing is centered about the rotary wing hub axis of rotation and has an electronics housing cavity subsystem and an adjacent rotor housing cavity subsystem. The rotor housing cavity contains a first coaxial ring motor with a first rotor and imbalance mass and a second coaxial ring motor with a second rotor and imbalance mass. The electronics housing cavity contains an electronics control system which receives sensor outputs and electrically controls and drives the first motor and the second motor such that the first imbalance mass and the second imbalance mass are driven at a vibration canceling rotation frequency greater than the operational rotation frequency wherein the helicopter rotary wing hub periodic vibrations are reduced.