Lord Corporation

Lord Corporaiton

Askari Badre-Alam

Mark R Jolly

Russell E Altieri

Douglas A Swanson

Andrew D Meyers

Douglas Edward Ivers

Daniel Mellinger

Steve C Southward

Jeffrey Cranmer

Jonathan M Owens

James F Kuhn

Leslie P Fowler

Eric Cady

Bradley N Jones

Doug Swanson

Michael W Trull

Douglas Pedersen

Brian S Carr

Jihan Ryu

Paul Black

Wayne Lee Winzenz

Michael Jarzomski

David Edeal

David Boswell

Donald Morris

Lane R Miller

Dennis P McGuire

Benjamin L Holton

Donald L Margolis

Mark A Norris

Matthew K Ferguson

Richard Wilder

Stefan Barbulescu

Luca Di Deco

Russell E Alteri

Anthony Gray Hunter

Bradley Jones

Michael D Janowski

Douglas Swansor

Ben Holton

Joshua Fishman

Doug A Swanson

Anthony Hunter

Benjamin Lanning Holton

Brian Carr

Russel E Altieri

R Jolly Mark

Dennis Mcguire

A magnetically-responsive device () having a magnetic seal () to retain magnetically responsive material within a defined space () is provided. The magnetically-responsive device () has a shaft (), a rotor (), a magnetic field generator (), a magnetically-responsive medium and a magnetic seal (). The seal () is preferably a non-contact seal () that does not deteriorate over time and generates little to no resistance.

Magnetic seal for magnetically-responsive devices, systems, and methods

Electromagnetic locking devices, systems, and methods are provided. The electromagnetic locking devices, systems, and methods are configured to lock an actuating arm of an actuator in any desired position between and including a fully extended position and a fully retracted position with respect to an outer cover of the electromagnetic locking device and/or system. The electromagnetic locking devices, systems, and methods described herein may include an unpowered deformable member that imparts fail-safe functionality thereto.

Electromagnetic locking devices, systems, and methods

The invention provides a system for creating a prescribed vibration profile on a mechanical device comprising a sensor for measuring an operating condition of the mechanical device, a circular force generator for creating a controllable rotating force vector comprising a controllable force magnitude, a controllable force phase and a controllable force frequency, a controller in electronic communication with said sensor and said circular force generator, the controller operably controlling the controllable rotating force vector, wherein the difference between the measured operating condition and a desired operating condition is minimized.

Mechanical devices and method of creating prescribed vibration

A control system for resonant inertial actuators estimates operating parameters of the resonant inertial actuators based on voltage and current feedback and dynamically limits selected parameters to maintain the safe, efficient, and cost effective operation of the resonant inertial actuators. Resistance within the electrical drives for the resonant inertial actuators is estimated from the voltage and current feedback and in conjunction with the modeling of the resonant inertial actuators other operating parameters are calculated or otherwise estimated. Having regard for the responsiveness of the resonant inertial actuators to changes in command signals, the command signals are adjusted to dynamically limit the estimated parameters.

Rotary wing aircraft vibration control system with resonant inertial actuators

A pumping system is provided. The pumping system includes an output conduit, a first sensor, a second second sensor, a feedforward active controller, and a fluid flow normalizer (FFN). The output conduit is associated with an output of a positive displacement pump. The first sensor is configured to measure a fluid flow characteristic (FFC) within the output conduit. The second sensor is configured to measure a phase of the positive displacement pump. The feedforward active controller is configured to receive information related to the FFC, receive information related to the phase of the positive displacement pump, and determine an FFC variability value. The first fluid flow normalizer (FFN) is configured to at least one of add fluid to the output of the positive displacement pump and remove fluid from the output of the positive displacement pump in response to a signal from the feedforward active controller.

Fluid flow normalizer

A rotary wing aircraft including a vehicle vibration control system. 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, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.

Helicopter vibration control system and circular force generation systems for canceling vibrations

A rotary wing aircraft including a vehicle vibration control system. 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 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, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hub rotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced.

A method of controlling the vibration of a vibratory separator, the method including providing a vibratory separator having a frame and a plurality of force generators coupled to the frame and a control unit operatively connected to each of the plurality of force generators, and independently controlling each of the plurality of force generators. Independently controlling each of the plurality of force generators controls a motion profile of the vibratory separator.

Shaker with automatic motion

An electromagnetic inertial actuator includes a support base and a parallel arrangement of a first flexure part, a voice coil motor part, and a second flexure part. The parallel arrangement is cantilevered from the support base.

Electromagnetic inertial actuator

An aircraft system/method for propeller balancing. The system includes an inboard driver with a first and second inboard electromagnetic coil, the inboard driver and the first counterweight balancing rotor and the second counterweight balancing rotor centered around the aircraft propeller shaft rotating machine member with the first inboard electromagnetic coil proximate the first inboard magnets of the first counterweight balancing rotor, with the inboard electromagnetic coil driver proximate the rotation axis of the aircraft propeller shaft rotating machine member and the first counterweight balancing rotor outboard of the inboard electromagnetic coil driver with the first inboard electromagnetic coil generating a electromagnetic field to electromagnetically step the first inboard magnets of the at least first counterweight balancing rotor to electromagnetically actuate rotational movement of the first counterweight balancing rotor around the rotating machine member and relative to the inboard electromagnetic coil driver to a first rotor held balancing position.

Aircraft propeller balancing system

An aircraft system and method with a first counterweight rotating balancing rotor mass concentration, and a second counterweight rotating balancing rotor mass concentration to balance a first aircraft propeller. The system includes an inboard electromagnetic coil driver with a first inboard electromagnetic coil, and a second inboard electromagnetic coil, the inboard electromagnetic coil driver and the first counterweight balancing rotor and the second counterweight balancing rotor centered around the aircraft propeller shaft rotating machine member. The system/method utilizes a first control system controller to control the coils and position the mass concentrations to balance the first aircraft propeller. The system/method includes a third counterweight rotating balancing rotor mass concentration, and a fourth counterweight rotating balancing rotor mass concentration to balance a second aircraft propeller which positioned and controlled by a second control system controller.

A method and system is disclosed for controlling problematic vibrations in an aircraft having. The method and system have the ability to cancel problematic rotary wing helicopter vibrations using independent active force generator power and with distributed communications therebetween.

Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations

Growing community of inventors

Apex, NC, United States of America

Askari Badre-Alam