Abstract: A combined brake and motor providing tactile feedback control to a human-machine interface steering input device as part of a steer-by-wire system is provided. The brake is a tactile feedback device (TFD) brake and the motor is an electric motor coupled to the brake. The brake provides end stop control and resistive torque to the steer-by-wire system. The motor provides motion control to the steer-by-wire system, where motion control includes a return-to-center, a command following, an on-center control, an active force-feel, and/or a warning mode (e.g., similar to an aircraft stick shaker or a lane departure). The steer-by-wire system is an active system.

Abstract: The present subject matter relates to devices, systems, and methods for identifying the position of a movable component. A position sensor system is provided in which a Hall effect sensor is coupled to a fixed housing, and a plurality of magnets is coupled to a movable component that is movable to a sensing position at which the plurality of magnets is proximal to the Hall effect sensor. In this configuration, the plurality of magnets is arranged to produce an aggregate magnetic field having a flux concentration directed toward the Hall effect sensor when the plurality of magnets is in the sensing position.

Abstract: A magnetically-responsive device (100) having a magnetic seal (160,170) to retain magnetically responsive material within a defined space (150) is provided. The magnetically-responsive device (100) has a shaft (110), a rotor (130), a magnetic field generator (145), a magnetically-responsive medium and a magnetic seal (160,170). The seal (160,170) is preferably a non-contact seal (160,170) that does not deteriorate over time and generates little to no resistance.

Abstract: A magnetically-responsive device (100) having a magnetic seal (160,170) to retain magnetically responsive material within a defined space (150) is provided. The magnetically-responsive device (100) has a shaft (110), a rotor (130), a magnetic field generator (145), a magnetically-responsive medium and a magnetic seal (160,170). The seal (160,170) is preferably a non-contact seal (160,170) that does not deteriorate over time and generates little to no resistance.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: 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.

Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: A rotary wing aircraft including a vehicle vibration control system.

Abstract: 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.

Abstract: An aircraft system/method for propeller balancing.

Abstract: 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.

Abstract: 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.

Abstract: 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.