The Boeing Company

John A Standley

Neal Van Huynh

Robert J Bleeg

Ralph Scott Pepper

Brian L Bocksch

Mark Steven Good

Steven Paul Walker

Michael K Klein

Joseph E Elliott

Charuhas M Soman

Andrew Sones

Ramón Burin

Kyle Steven Wydock

Kim R Lisenko

Timothy Paul Zazynski

Scott Pepper

An aircraft includes a wing and a leading-edge aerodynamic surface coupled to the wing. An actuator is disposed within the wing and coupled to the leading-edge aerodynamic surface via a linkage system. Two or more hinge systems are coupled to the leading-edge aerodynamic surface and configured to rotate about a fixed axis internal to the wing to move the leading-edge aerodynamic surface between a retracted position and a drooped position.

Leading-edge droop actuation system

A rotary actuator, including a manifold block and a rotor assembly that includes a rotor shaft and a plurality of arcuate pistons attached to the rotor shaft, each arcuate piston curving at a set radial distance from the rotor shaft, and each piston attached to the rotor shaft via a crank arm. A pressure chamber assembly coupled to the manifold block defines a plurality of piston pressure chambers that receive and at least partially enclose each arcuate piston, including a plurality of gland seals disposed adjacent the entrance of each piston pressure chamber to create a seal between the inner surface of the pressure chamber and the outer surface of the arcuate piston. Each gland seal includes an inner seal that engages the piston surface of the arcuate piston, and plural outer seals that engage the inner surface of the piston pressure chamber, forming a hydraulic seal.

Rotary actuator

Methods and apparatus for reacting rotary actuator and control surface loads into a wing structure using reaction links. The apparatus incorporates a structural interface feature that can facilitate a change of the component(s) in the load loop, such as the path connecting a control surface to a fixed aircraft structure via a rotary actuator. In particular, the structural interface between the rotary actuator and the rear spar of a wing can be tuned for stiffness to achieve an optimized load path that reacts actuator and control surface loads back into the wing structure. An actuator integration objective can be met for any rotary actuator using an integration method which tolerates wing and/or hinge line deflection.

Methods and apparatus for integrating rotary actuators in flight control systems

An apparatus for controlling the pitch of an aircraft. The apparatus includes a horizontal control column extending from a control wheel horizontally towards a front wall of a cockpit. A pitch output link is connected to a downstream pitch control mechanism to transfer a force applied at the pitch output link to the downstream pitch control mechanism. A transfer assembly is connected to the horizontal control column and to the pitch output link. The transfer assembly translates a horizontal force applied to the horizontal control column to the pitch output link to provide the force applied to the downstream pitch control mechanism.

Optimized pitch and roll control apparatus for an aircraft

Systems, methods, and devices are configured to implement hydraulic actuators. Devices may include a housing having an internal surface defining an internal cavity that may have a substantially circular cross sectional curvature. The devices may include a rotor that includes a first slot having a substantially circular curvature. The devices may include a first vane disk partially disposed within the first slot of the rotor, where the first vane disk has a substantially circular external geometry. The first vane disk may be mechanically coupled to the rotor via the first slot, and the first vane disk may be configured to form a first seal with the internal surface of the housing. The devices may include a first separator device that may be configured to form a second seal with the internal surface of the housing and a third seal with an external surface of the rotor.

Systems, methods, and apparatus for rotary vane actuators

Systems and methods for controlling aircraft flaps and spoilers are disclosed. Systems in accordance with some embodiments include a wing having a trailing edge, and a flap positioned at least partially aft of the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position by operation of a first actuator. A spoiler can be positioned at least proximate to the trailing edge and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap.

Systems and methods for controlling aircraft flaps and spoilers

Systems and methods for controlling aircraft flaps and spoilers. Systems in accordance with some embodiments include a wing having a trailing edge, and a flap positioned proximate to the wing trailing edge and being deployable relative to the wing between a first flap position and a second flap position by operation of a first actuator. A spoiler can be positioned at least proximate to the trailing edge and can be movable among at least three positions, including a first spoiler position in which the spoiler forms a generally continuous contour with an upper surface of the wing, a second spoiler position deflected downwardly from the first, and a third spoiler position deflected upwardly from the first. A second actuator can be operatively coupled to the spoiler to move the spoiler among the first, second and third spoiler positions in a manner that is mechanically independent of the motion of the flap.

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Seattle, WA, United States of America

John A Standley