Lord Corporation

Douglas A Swanson

Mark R Jolly

Russell E Altieri

Askari Badre-Alam

Paul Black

Douglas Edward Ivers

Paul Joseph Bachmeyer

Andrew D Meyers

Daniel Kakaley

Daniel Mellinger

Lane R Miller

Steve C Southward

Mark A Norris

Scott K Thompson

Dino J Rossetti

Doug Hodgson

Douglas Pedersen

Jeffrey Cranmer

Victor Zaccardo

Bryan J Pittman

Russell E Alteri

Christopher P Townsend

Peter J Jones

Stephen F Hildebrand

Douglas A Hodgson

Scott Kennedy

William S Jensen

David Edeal

Scott K Miller

Kevin C Cooney

Charles A Clifton

Michael D Janowski

Michael F Walch

William Arlendo Smith

David Newton

Ian Cassidy

Gary Martin

Russel E Altieri

Systems and methods for measuring a clearance between a rotating machine component and a sensor unit are disclosed. In some aspects, a system includes a sensor unit oriented to detect the rotating machine component as the rotating machine component rotates past the sensor unit, the sensor unit including at least a first sensing element and a second sensing element spaced apart from the first sensing element. The system includes a sensor processing unit in electrical communication with the sensor unit. The sensor processing unit is configured for receiving a first waveform from the first sensing element; receiving a second waveform from the second sensing element; and determining, based on a comparison between the first waveform and the second waveform, a distance between the blade tip and the sensor unit.

Rotating machine component clearance sensing systems and methods

Torque sensing devices, systems, and methods are capable of measuring and/or determining a torque being transmitted through a shaft by measuring the torsional deformation of the shaft over a short length thereof. Such devices, systems, and devices have a sensor positioned adjacent to the outer surface of the shaft as it rotates, the sensor being positioned to maintain a substantially constant distance between the sensor and the outer surface of the shaft. The sensors may be variable reluctance (VR) sensors rigidly attached to a frame mounted on a bearing (e.g., a hanger bearing), which is mounted on the shaft, such that relative radial motion between the shaft and the VR sensor is minimized (e.g., so that they move in unison). Reducing this amount of motion results in a more accurate torque measurement.

Hanger bearing mounted torque sensor

An active vibration control system (AVCS) and method for reducing motion and/or vibration of a seat frame within an aircraft includes vibration sensors, a controller, and force generators. In some embodiments, the vibration sensors and/or the force generators are attached to the seat frames. In other embodiments, the vibration sensors and/or the force generators are attached to aircraft structures, proximate to the seat frame. By monitoring the motion and/or vibration of the seat frame, the controller calculates a cancelling force to be generated by the force generators to reduce the vibration experienced by the seat frame and its occupant. Such seat frame vibration control can be implemented as a separate AVCS in an aircraft, or can be integrated in an existing AVCS that is also configured to provide vibration control in other parts thereof.

Active vibration control of floor and seat frame vibration

Systems and method for active vibration control on an aircraft. An active vibration control system (AVCS) is configured for an aircraft having an aircraft structure and a gun. The AVCS includes at least one control sensor on the aircraft, at least one force generator on the aircraft, and at least one controller in electronic communication with the sensor and the force generator. The controller is configured for determining, using the at least one control sensor, force generating commands for controlling vibrations acting on the aircraft structure, sending the force generating commands to the at least one force generator, causing the at least one force generator to produce a vibration canceling force, determining that the gun is firing, and in response to determining that the gun is firing, determining different force generating commands and sending the different force generating commands to the at least one force generator.

Active vibration control system in a gunfire vibration environment

Actuators are components of machines, which move and/or control a mechanism or system. During operation, actuators can experience regeneration events, with the actuator actually generating excess energy (e.g., regenerative energy) which must be stored or dissipated to avoid damaging the power supply. An actuator motor controller is configured to implement field oriented voltage control and flux weakening voltage control without current sensors. Dissipating regenerative energy includes providing a motor controller to command a motor drive to modify an input voltage, or to dissipate regenerative energy in a dump circuit. This command can cause motor windings to dissipate regenerative energy. Systems having a plurality of actuators distribute regenerative energy from one actuator to another. A central controller provides centralized regeneration dissipation control for the plurality of actuators. A power distribution unit includes a dump resistor to dissipate regenerative energy in addition to or instead of in the actuators.

Actuator motion controller with regeneration compensation

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

Structural health monitoring and protection systems and methods are provided. System and methods utilize structural information and/or enhanced built in testing capabilities for detecting failure modes that may cause damage to a structure. Systems and methods herein may protect a structure by mitigating one or more incorrect forces. The structure may be an aircraft, a rotary wing aircraft, or any other physical structure subject to vibrations and receptive to canceling of those vibrations.

Systems and methods for structural health monitoring and protection

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

Redundant active vibration and noise control systems and methods are provided, which include safety-critical systems and methods. In one embodiment, a safety-critical active vibration control system (SCAVCS) is provided, which includes a plurality of digital buses, a force generator, at least one sensor and at least one system parameter. The at least one force generator is in electronic communication with at least two digital buses. The force generator includes a pair of unbalanced masses, at least one motor, at least one microprocessor, at least one speed sensor, at least one accelerometer, and at least one power input. The at least one sensor is in electronic communication with each of the digital buses and with each of the microprocessors. The at least one system parameter is in electronic communication with each of the digital buses and each of the microprocessors.

Redundant active vibration and noise control systems and methods

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.

Aircraft landing gear assembly shimmy damper

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.

Method and system for controlling helicopter vibrations

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.

Helicopter hub mounted vibration control and circular force generation systems for canceling vibrations

Growing community of inventors

Apex, NC, United States of America

Douglas A Swanson