The Boeing Company

The Boenig Company

Mark Steven Good

Matthew August Lassen

Mark John Gardner

Jan A Kordel

Steven Paul Walker

Kevin Raylin Tsai

Kelly Thomas Jones

Stephen John Fox

Michael E Renzelmann

Seiya Sakurai

Michael R Finn

Charles E Jokisch

Gregory M Santini

Matthew A Moser

Seth E Gitnes

Mark William Lesyna

Keith Townsend

Bruce Robert Fox

Quentin Theodor Pietersen

Jonathan J Paul

Brian Curtis Hill

Nicholas Seth Tyler

Glynn Michael Thomas

Keily Madison Gleason-Chapell

Neal Van Huynh

Stephen Roger Amorosi

Bryan Gruner

Paul W Dees

Adam P Malachowski

Paul M Vijgen

Alan K Prichard

Lisa G Schleuter

John A Standley

Dan Onu

Kwan-Ho Bae

Patrick M Fahey

Alan D Marx

George Moy

Rickie Hansken

Christopher D Feet

Gary A Emch

Paul E Johnson

Nicholas I Bennett

Gregor William Dempster

Kyle Steven Wydock

Ramón Burin

Stephen P Walker

Paul Dees

Monica Thommen

Selya Sakurai

Gregory J Seehusen

Richard I Apfel

Monica E Thommen

Sarah A Jones

Jared Chung Houten

Rene T Nguyen

Paul M Viigen

Gregor W Dempster

Matthew A Lassen

Mark J Gardner

Paul Johnson

Michael Edward Renzelmann

Quentin T Pietersen

Glynn M Thomas

Bryan J Gruner

S Paul Walker

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

Embodiments are shown for a machine and process to rotate and fix a second structure relative to a first structure via a hinge that may include a central axis, a lock-plate, and a moveable, a stationary, and a driving, member. The process may include: attaching a hinge to the first structure; moving a pin, extending parallel to the central axis through the stationary and driving members, out of a first notch of the movable member toward the central axis via rotating the driving member around the central axis; rotating the movable member via rotating the second structure around the central axis; fixing the movable member by latching the hinge via moving the pin away from the central axis and into a second notch in the movable member; and locking the latch by moving, along a length of the central axis, the lock-plate toward the driving member and the pin.

Process and machine for rotating and fixing a structure

According to one aspect of the present disclosure, an apparatus for shortening a wingspan of an aircraft is disclosed. The apparatus comprises a first link extending from a wingtip of the aircraft and moveably coupled to a fixed wing of the aircraft. A second link also extends from the wingtip and is moveably coupled to the fixed wing. An actuator is coupled to the fixed wing and to the second link. The actuator is configured to move the second link and cause the wingtip to move between an extended position and a stowed position.

Shortening wingspan of an aircraft

A flap actuation mechanism incorporates a coupler rod eccentrically supported at an aft end and at a forward end. The coupler rod is configured to translate from an aft position to a forward position. An inboard crank arm is coupled to the rotary actuator and engaged to the aft end of the coupler rod. The inboard crank is configured rotate responsive to rotation of the rotary actuator thereby inducing translation of the coupler rod. An outboard crank arm engaged to a forward end of the coupler rod and is configured to rotate responsive to translation of the coupler rod. A flap drive arm is attached to the outboard crank arm and is configured to rotate with the outboard crank arm from a stowed position to a deployed position responsive to translation of the coupler rod from the aft position to the forward position.

Thin wing drive mechanism

An apparatus for shortening a wingspan of an aircraft is disclosed. The apparatus comprises a first bracket and a second bracket extending from a wingtip of the aircraft, and a motor coupled to a fixed wing of the aircraft. A first outboard link is rotatably coupled to the first bracket and to the motor, and a second outboard link is rotatably coupled to the second bracket and to the motor. A first inboard link is rotatably coupled to the first bracket and to the fixed wing, and a second inboard link is rotatably coupled to the second bracket and to the fixed wing. The motor is configured to rotate the first outboard link and the second outboard link to move the wingtip between an extended position and a stowed position.

According to one aspect of the present disclosure, an apparatus for shortening a wingspan of an aircraft is disclosed. The apparatus comprises a first track affixed to a fixed wing of the aircraft. A first roller assembly is affixed to a wingtip of the aircraft, with the first roller assembly moveably captured within the first track. A second track is also affixed to the fixed wing. A second roller assembly is affixed to the wingtip and is moveably captured within the second track. A wingtip actuation assembly is configured to translate the first roller assembly within the first track and the second roller assembly within the second track to move the wingtip between an extended position and a stowed position under the fixed wing.

Assemblies for air vehicle control surfaces and related methods are disclosed. An example apparatus includes a control surface; a bullnose carried by the control surface, the bullnose moveable relative to the control surface; a first actuator operatively coupled to the control surface to cause the control surface to rotate; and a second actuator operatively coupled to the control surface, the second actuator to cause the bullnose to move from a first position to a second position to cause an opening to be formed relative to the control surface, the movement of the bullnose independent of rotation of the control surface.

Assemblies for air vehicle control surfaces including a bullnose

Methods and apparatus to measure multiple control surfaces with a sensor are disclosed. A disclosed example apparatus for determining a condition associated with first and second control surfaces includes a sensor to measure a rotation of a shaft operatively coupled thereto. The apparatus also includes a first differential operatively coupled between the shaft and a first pivot of the first control surface, and a second differential operatively coupled between the first differential and a second pivot of the second control surface.

Methods and apparatus to measure multiple control surfaces with a sensor

Methods, apparatus, and articles of manufacture for actuating control surfaces of an aircraft are disclosed. An example apparatus to control a control surface of an aerodynamic body includes a track rotatable about a pivot of a support structure of the aerodynamic body, the control surface slidably coupled to the track, a first actuator operatively coupled to the track, the first actuator to cause rotation of the track and the flaperon about the pivot, and a second actuator operatively coupled to the control surface, the second actuator to cause translation of the control surface along the track.

Methods, apparatus, and articles of manufacture for actuating control surfaces of an aircraft

Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a plurality of outer tracks, wherein each outer track of the plurality of outer tracks include: an inner roller channel; and an outer roller channel positioned above the inner roller channel; an aerodynamic surface connected to a carrier, wherein the carrier includes: a plurality of rollers configured to move within inner roller channels of the plurality of outer tracks; and a carrier rack; a plurality of fixed rollers mounted to a plurality of longitudinal structural elements in an aerodynamic structure, wherein the plurality of fixed rollers are disposed within outer roller channels of the plurality of outer tracks; and a plurality of fixed racks, wherein each fixed rack of the plurality of fixed racks is mounted to a longitudinal structural element of the plurality of longitudinal structural elements.

Actuation and support system for aerodynamic surfaces

An actuation apparatus for an aerodynamic surface includes a cam track plate having a forward cam track and an aft cam track, a support arm coupled to the leading edge slat panel, the support arm having a forward roller and an aft roller thereon, the forward roller disposed in the forward cam track and the aft roller disposed in the aft cam track, and a bell crank pivotally mounted to the cam track plate, the bell crank having an aft end coupled by an aft link to the wing structure and a forward end coupled by a forward link to the support arm. The forward roller translates within the forward cam track and the aft roller translates within the aft cam track to cause downward rotation of the aerodynamic surface and increased camber of the aerodynamic surface as the aerodynamic surface is extended toward a deployed position.

Telescoping mechanisms for control of aerodynamic surfaces

Aircrafts having foldable wings are disclosed. An example aircraft includes a fixed wing portion, a foldable wing tip, and a hinge interface to pivotally couple the foldable wing tip and the fixed wing portion. The hinge interface has a first hinge defining a hinge axis that is substantially parallel to a fuselage centerline. The first hinge has a first dimension in a spanwise direction and a second dimension in a chordwise direction. The first dimension is greater than the second dimension.

Aircraft having foldable wings

Example methods and apparatus for mitigating aerodynamic flutter of aircraft wing flaps are disclosed. An example apparatus includes a fairing, an actuator, and a damper. The fairing is located on a bottom side of a wing of an aircraft. The actuator is disposed in the fairing. The actuator is coupled to and extends between the wing and a flap of the wing. The damper is disposed in the fairing. The damper is coupled to and extends between the fixed wing and the moveable flap.

Methods and apparatus for mitigating aerodynamic flutter of aircraft wing flaps

Example apparatus and methods are disclosed herein for moving control surfaces on an aircraft wing to control airloads during a wing tip folding operation (from a folded position to an extended position or from an extended position to a folded position). An example method includes determining a position of a control surface on a wing of an aircraft. In the example method, the wing has a fixed wing portion and a wing tip moveably coupled to the fixed wing portion. The example method includes determining a change in the position of the control surface from a first position to second position for facilitating movement of the wing tip while the aircraft is not in flight. The example method also includes moving the control surface to the second position and moving the wing tip between an extended position and a folded position.

Controlling airloads on aircraft folding wing tips

An actuation system for controlling flight control members of a vehicle. Each flight control member is controlled by two or more linear hydraulic actuators. Synchronization members extend between the hydraulic actuators on the same flight control members to synchronize the movements of the hydraulic actuators for consistent movement across the length of the flight control members. Brakes can maintain the positions of the synchronization members and thus the flight control members. Motors can provide for moving the synchronization members to control the positioning of the hydraulic actuators and flight control members.

Distributed linear hydraulic high lift actuation system with synchronization members

Growing community of inventors

Seattle, WA, United States of America

Mark Steven Good