The Boeing Company

Jeffrey Charles Coffman

David E Blanding

Jimmy Manansala Quiambao

Neal Van Huynh

James L Peck, Jr

Arun Muley

Julie Fatemeh Asfia

Jim L Peck

Doug Van Affelen

David Blanding

Jr Peck James L

Jimmy M Quiambao

A method for monitoring remaining useful life (RUL) of an actuation system in a vehicle that includes receiving position data of the actuation system from a position sensor, maintaining a total distance traveled for the actuation system, and calculating the RUL of the actuation system. The calculating includes estimating force data using an output variable estimator, determining motor torque, weighing the estimated force data using a confidence level, predicting a total life of the actuation system based on the weighted force data, and comparing the predicted total life with the total distance traveled to determine the remaining useful life.

System and method for monitoring the remaining useful life of a ball screw in actuation system

In general, certain embodiments of the present disclosure provide an electro-hydrostatic actuator comprising a piston assembly and a hydraulic cylinder. The piston assembly, having a piston head and a piston rod extending from the piston head, is located and movable within the hydraulic cylinder. The hydraulic cylinder includes a hydraulic fluid chamber region including a piston side chamber and a rod side chamber, a reservoir for storing hydraulic fluid located within the hydraulic cylinder which is in fluid communication with the hydraulic fluid chamber region. The electro-hydrostatic actuator includes a hydraulic pump system for moving hydraulic fluid in the reservoir and the hydraulic fluid chamber region, the hydraulic pump system in fluid communication with a flow control network in a hydraulic cylinder boss for controlling a direction and flow magnitude of hydraulic fluid within the hydraulic fluid chamber region, and an electric motor for driving the hydraulic pump system.

Low profile electro-hydrostatic actuator

A dual-independent hybrid actuator system includes an actuator body defining a hydraulic chamber. The actuator system includes a hydraulic piston assembly, including a hydraulic piston disposed within the hydraulic chamber and dividing the hydraulic chamber into a first hydraulic sub-chamber in fluid communication with a first hydraulic fluid passage and a second hydraulic sub-chamber in fluid communication with a second hydraulic fluid passage. The actuator system further includes a piston rod mounted to the hydraulic piston that passes through the second hydraulic sub-chamber with a distal end that projects outward from the actuator body. The actuator system further includes an electric motor mounted to the actuator body, and a threaded axle mechanically coupled to a motor shaft of the electric motor. The threaded axle passes through the first hydraulic sub-chamber and engages with a threaded port formed in the hydraulic piston assembly.

Dual-independent hybrid actuator system

Systems for compensating for force fighting in multi-actuator systems are provided. A drive controller unit comprises a first feedforward controller in communication with a first actuator and configured to receive a drive command signal. A first feedback regulator is configured to output a first feedback input into the first feedforward controller, and to receive as input a first actuator position and a first actuator force. The drive controller unit further comprises a second feedforward controller in communication with a second actuator and configured to receive the drive command signal. A second feedback regulator is configured to output a second feedback input into the second feedforward controller, and to receive as input a second actuator position and a second actuator force. The drive controller unit utilizes both feedforward controllers and both feedback regulators to minimize force fighting while driving a common aileron.

Adaptive feedback control of force fighting in hybrid actuation systems

A system for controlling multiple actuators that are attached to a structure for moving and positioning the structure include a magnetic flux sensor in a motor of each actuator. The magnetic flux sensor senses a magnetic flux in an associated motor and generates an electrical signal that corresponds to the magnetic flux in the associated motor. The system also includes a control unit that receives the electrical signal from the magnetic flux sensor of each actuator. The control unit is configured to generate a drive command signal to each actuator that balances a torque applied to the structure by each actuator in response to the magnetic flux sensed in the motor of each actuator.

Multiple electromechanical actuator control system

A control system may include a fault detection system, an electromechanical actuator, the electromechanical actuator electronically coupled to the fault detection system, and a failure simulation apparatus mechanically coupled between the electromechanical actuator and a load, the failure simulation apparatus selectively applies an external resistive force to the electromechanical actuator.

Apparatus and method for simulating a failure response in an electromechanical actuator

Disclosed embodiments include a structurally integrated thermal management system that uses the structure of an aerospace vehicle as part of the heat dissipation system. In this system, structural elements of the aerospace vehicle function as a thermal bus, and are thermally connected with heat-generating electrical components, so that heat from those components is directed away from the component by the structure of the vehicle itself, into lower temperature surfaces of the vehicle.

Structurally integrated thermal management system for aerospace vehicles

Systems and methods for operating flight control surfaces are provided. One system includes a control device having a two piece shaft including a first shaft portion and a second shaft portion, a spline key detachably coupling the first shaft portion and the second shaft portion, and a crankshaft operatively coupling the two piece shaft and a flight control surface. The control device further includes a driving mechanism coupled to the spline key and operable to move the spline key to engage and disengage the first and second shaft portions, wherein the first and second shaft portions are disengaged when a failure to the flight control surface is detected, causing the second shaft portion to drive the flight control surface to a safe position.

Systems and methods for operating flight control surfaces

Provided are mechanisms and processes for a pneumatic shaft positioning system. According to various examples, the pneumatic shaft positioning system includes a pyrotechnic valve that is configured to control the flow of gas from a pressurized gas source into a pressure chamber. The pressure chamber includes a first piston that is slidably coupled to the pressure chamber. When gas from the pressurized gas source fills the pressure chamber, the piston is configured to slide through the pressure chamber and force a shaft into a predetermined position.

Pneumatic positioning system

A de-icing system and method. An electromechanical actuator heat sink is operable to receive heat from an electromechanical actuator, and a heat distribution element is operable to distribute heat to a surface. A heat transportation device is operable to transport heat from the electromechanical actuator heat sink to the heat distribution element.

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Huntington Beach, CA, United States of America

Jeffrey Charles Coffman