The Boeing Company

Patrick Joseph McCormick

Neal Van Huynh

Matthew A Moser

Alan D Marx

Timothy G Overton

Robert J Atmur

James Leo Peck, Jr

Mark William Lesyna

Christopher J Heiberg

Patrick M Fahey

Paul R Smith

Matthew D Uhlman

Barry D Hance

Christopher P Beamis

Robert J Hawk

Ellen A Pifer

Ali Abdelmagid

Herbert Guttler

Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a non-responsive component detector to determine a position difference between a first position of a first control surface of an aircraft and a second position of a second control surface of the aircraft, the first position lagging the second position, and a command generator, in response to determining that the position difference satisfies a threshold, the command generator is to cease movement of the second control surface at the second position, attempt to move the first control surface to the second position, and cease movement of the first control surface when moved to the second position.

Methods and apparatus for a distributed aircraft actuation system

A hydraulic system (e.g., of an aircraft or other vehicle) includes a pump, a pressure line coupled to the pump and configured to distribute pressurized hydraulic fluid, and a return line configured to return hydraulic fluid to a reservoir. The hydraulic system also includes an auxiliary leakage valve coupled to the pressure line, to the return line, and to an actuator. The auxiliary leakage valve is configured to receive a control signal and, based on the control signal, selectively open a restricted fluid path. The restricted fluid path couples the pressure line to the return line to allow a restricted amount of the hydraulic fluid to flow from the pressure line to the return line.

Hydraulic fluid warming system and method

A method and apparatus for positioning a control surface. A desired position for the control surface associated with an aerodynamic aircraft structure is identified. The control surface is moved to the desired position using an electronically controlled rotary actuator system located inside of the aerodynamic aircraft structure, wherein a shape of the aerodynamic aircraft structure with the electronically controlled rotary actuator system has a desired aerodynamic performance.

Electronically controlled rotary actuator for an aircraft control surface

Actuators for high lift devices on aircraft are disclosed herein. An example apparatus includes an actuator for a high lift device of an aircraft including a motor and a transmission, where the transmission includes a first gear stage and a second gear stage, the first gear stage including a first worm gear and the second gear stage including a second worm gear, the first worm gear, the second worm gear and the motor operative to prevent backdrive of the actuator.

Actuators for high lift devices on aircraft

Methods and apparatus for controlling aircraft flight control surfaces are disclosed. An example apparatus includes a flight control surface controller to move a control surface of an aircraft to a target position via at least one of a first actuator or a second actuator associated with the control surface based on a command input received by the flight control surface controller. The flight control surface controller to: obtain a flight characteristic of the aircraft; compare the flight characteristic to a flight characteristic threshold; in response to a first comparison result, cause the first actuator to move the control surface to the target position based on the command input without moving the second actuator; and in response to a second comparison result, cause the first actuator and the second actuator to move the control surface to the target position based on the command input.

Methods and apparatus for controlling aircraft flight control surfaces

Methods, apparatus, and articles of manufacture for a distributed aircraft actuation system are disclosed. An example apparatus includes a collection engine to obtain first monitoring information corresponding to a first set of control surfaces of an aircraft, the first set including a first control surface on a first side of the aircraft and a second control surface on a second side of the aircraft, the second side opposite the first, and obtain second monitoring information corresponding to a second set of control surfaces of the aircraft, the second set including a third control surface on the first side and a fourth control surface on the second side. The example apparatus further includes a non-responsive component detector to determine if one of the control surfaces is non-responsive based on the first and the second monitoring information, and a command generator to deactivate the first set when the non-responsive component detector determines that the first control surface is non-responsive while the second set remains active.

A system of an aircraft includes a system pump and a booster pump. The system pump is configured to provide hydraulic fluid to the hydraulic system at a first working pressure. The booster pump is configured to supply hydraulic fluid to at least one boostable actuator at a second working pressure higher than the first working pressure. The boostable actuator is operatively coupled to and configured to actuate at least one flight control surface of an aircraft. The booster pump is configured as a high-pressure accumulator and an accumulator energizer, or as a hydraulic actuator pump and a variable speed motor.

Hydraulic system and method for a flight control system of an aircraft

A system and method for controlling one or more flaps of a wing of an aircraft include a first flap moveably secured to a first wing of the aircraft. The first flap is moveable between an extended position and a retracted position. First and second actuators are coupled to the first flap. A flap control unit is in communication with the first and second actuators. The flap control unit is configured to operate the first and second actuators to move the first flap between retracted and extended positions, monitor a first electrical signal provided to the first actuator, monitor a second electrical signal provided to the second actuator, and determine that the first and second actuators are synchronized by monitoring the first and second electrical signals.

System and method for controlling aircraft wing flap motion

A hydraulic system of an aircraft may include a system pump configured to provide hydraulic fluid to the hydraulic system at a first working pressure. The hydraulic system may further include a booster pump configured to supply hydraulic fluid to at least one boostable actuator at a second working pressure higher than the first working pressure. The boostable actuator may be operatively coupled to and configured to actuate at least one flight control surface of an aircraft.

Hydraulic system and method for an aircraft flight control system

A system and methods for alleviating an anomaly in a structure are presented. At least one anomaly detector structural member is embedded in the structure. A measurement signal is sent to the anomaly detector structural member and a feedback signal is received from the anomaly detector structural member in response to the measurement signal. A difference between the measurement signal and the feedback signal is calculated to determine a change in the structure, and at least one non-optimal event is identified in real-time if the change exceeds an event threshold.

Growing community of inventors

Mercer Island, WA, United States of America

Patrick Joseph McCormick