Eaton Intelligent Power Limited

Eaton Corporation

John David Neely

John Mendenhall White

Stanley Lawrence Seely

Sayeed Ahmad Mir

Stan Lawrence Seely

Sayeed Ahmed Mir

A method of controlling an electric motor includes determining a PWM control signal, analyzing the PWM control signal to determine if components of the PWM signal are within a threshold amount of each other, applying duty-cycle blanking to the PWM control signal, if the components of the PWM control signal are within the threshold amount of each other, to generate an adjusted PWM control signal, and controlling the electric motor with the adjusted the PWM signal to limit parasitic effects.

Motor control system, controller, and method

A system includes a three phase AC or brushless DC motor, an inverter and a controller. The inverter is electrically coupled to the motor. The controller is -electrically coupled to the inverter. The controller is configured to control the inverter to deliver a three phase pulse width modulated voltage to the AC motor, wherein the three phase pulse width modulation comprises a repeating two-cycle pattern.

Three-phase variable reference pulse width modulation

A system comprises an aircraft hydraulic system motor, a position sensor, and a programmable controller. The aircraft hydraulic system motor includes a rotor whose position is detected by the position sensor. The position sensor produces an output representative of that position. The programmable controller is configured to receive the output of the position sensor and calculate an estimated velocity of the aircraft hydraulic system motor based on the output of the position sensor. The calculation of the estimated velocity comprises determining both a high bandwidth velocity estimation and a low bandwidth velocity estimation. The programmable controller is additionally configured to compare the estimated velocity to a desired velocity and direct the aircraft hydraulic system motor to increase or decrease velocity based on the comparison.

Motor velocity control within an aircraft hydraulic system

An electronic control architecture for an aircraft actuation system may include a first channel and a second channel. The first channel may be configured to receive one or more inputs comprising a movement command, to produce an output to control a component of the system, and to receive feedback from the component respective of movement of the component. The first channel may comprise a fault detection module configured to compare the feedback to the command to determine if the first channel is functioning properly. The second channel may be configured to receive the one or more inputs and, if the first channel is not functioning properly, to produce an output to control the component.

Fault tolerant electronic control architecture for aircraft actuation system

A system that improves on known systems for reducing output torque by a motor in the event of a jam may include an electromechanical actuator (EMA), a motor configured to drive the EMA and a controller. The controller may be coupled to the motor and configured to receive a speed of the EMA and a position of the EMA. The controller may be further configured to determine whether a jam of the EMA is imminent or is occurring according to the EMA speed, EMA position, and a known range of motion of the EMA, and to provide an input signal to the motor to reduce a torque of the motor if a jam of the EMA is imminent or is occurring.

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Kentwood, MI, United States of America

John David Neely