At Leading Edge Patents (Class 244/214)
  • Patent number: 11932389
    Abstract: The present disclosure defines a morphing airfoil having a dynamic flexible skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and deflect in response to control inputs to change a lift force without separate movable control surfaces. The anisotropic skin is attached to underlying structure that is both actively controlled and passively supported. A control system causes the underlying support structure to move to a desired location which in turn causes the skin to bend and/or flex without exceeding a stress threshold and thus vary the lift profile along a span of the airfoil.
    Type: Grant
    Filed: December 22, 2020
    Date of Patent: March 19, 2024
    Assignee: United States of America as represented by the Secretary of the Air Force
    Inventors: Jared Neely, James Joo
  • Patent number: 11866156
    Abstract: This invention is an apparatus for vortex generation by combining the function of means for vortex generation with the functions of the leading-edge aerodynamic surface, the airfoil, and/or the trailing-edge aerodynamic surface.
    Type: Grant
    Filed: November 21, 2021
    Date of Patent: January 9, 2024
    Inventor: Wei Liu
  • Patent number: 11866155
    Abstract: An actuator arrangement for a fixed leading edge member of an aircraft wing. The fixed leading edge member has an inner cavity defined by the outer skin and ribs. The actuator arrangement comprises at least one geared rotary actuator which moves relative to the other parts along a circular arc section during extending and retracting of the high-lift device between a fully retracted position and a fully extended position. In the fully retracted position, the actuator is predominantly accommodated within the inner cavity and in the extended position the actuator is predominantly positioned outside the inner cavity, preferably protruding through a D-nose cut-out.
    Type: Grant
    Filed: September 14, 2020
    Date of Patent: January 9, 2024
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Bernhard Schlipf, Norbert Geyer
  • Patent number: 11845536
    Abstract: Certain aspects of the present disclosure provide techniques for an aerodynamic surface actuation system, including: a middle track connected to an aerodynamic surface and configured to move along a plurality of intermediate tracks, wherein one or more inner surfaces of the middle track are configured to interface with one or more outer surfaces of the plurality of intermediate tracks; a plurality of outer tracks, each including a flange and configured to interface with one or more inner surfaces of the plurality of intermediate tracks; and an actuator configured to control a position of the middle track and a position of the plurality of intermediate tracks via a plurality of linkages.
    Type: Grant
    Filed: July 26, 2021
    Date of Patent: December 19, 2023
    Assignee: The Boeing Company
    Inventors: Matthew Edmunds, Robert Hoffenberg, Gregory M. Santini, Steven P Walker
  • Patent number: 11840331
    Abstract: A wing for an aircraft, including a main wing, and a leading edge high lift assembly including a high lift body, and a connection assembly connecting the high lift body to the main wing such that the high lift body is movable relative to the main wing between a stowed position and a deployed position. The connection assembly includes at least one rotation element mounted to the high lift body and mounted to the main wing rotatably about an axis of rotation. The high lift body includes a rigid portion and a flexible skin portion. The rigid portion is mounted to the rotation element. The flexible skin portion is connected to a leading edge portion of an upper skin panel of the main wing and is connected to the rigid portion of the high lift body The flexible skin portion is configured to be deformed between a stowed deformation state and a deployed deformation state, when the high lift body is moved between the stowed position and the deployed position.
    Type: Grant
    Filed: March 16, 2022
    Date of Patent: December 12, 2023
    Assignee: Airbus Operations GmbH
    Inventor: Rainer Gartelmann
  • Patent number: 11820512
    Abstract: A wing for an aircraft is disclosed including a main wing, a slat, and a connection assembly movable connecting the slat to the main wing. The connection assembly includes an elongate slat track, wherein the front end of the slat track is mounted to the slat, wherein the rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing including a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track.
    Type: Grant
    Filed: January 21, 2022
    Date of Patent: November 21, 2023
    Assignee: AIRBUS OPERATIONS GmbH
    Inventors: Alexander Huber, Bernhard Schlipf
  • Patent number: 11794887
    Abstract: A rotor blade assembly for a rotary wing aircraft includes a main rotor blade body comprising an upper blade skin, a lower blade skin, an inboard end, an outboard end, and a trailing edge. The rotor blade assembly further includes a trailing edge actuator assembly. The trailing edge actuator assembly includes an upper actuator skin and a lower actuator skin defining a cavity and a trailing edge flap, a control panel disposed in the cavity and coupled to one of the upper actuator skin or the lower actuator skin and one or more actuators disposed in the cavity and configured to apply force to the control panel to cause the trailing edge flap to deflect. The trailing edge actuator assembly is coupled to the trailing edge of the main rotor blade body.
    Type: Grant
    Filed: April 6, 2022
    Date of Patent: October 24, 2023
    Assignee: LOCKHEED MARTIN CORPORATION
    Inventors: Matthew Walter DiPalma, Timothy James Conti, Claude George Matalanis
  • Patent number: 11738861
    Abstract: A propelling system with variable aerodynamic controls is a system used to generate and control the flight forces of an aircraft. The system includes a stator, a rotor, a plurality of propelling units, and a control system. The stator serves as the stationary connection to the aircraft. The rotor revolves the propelling units about a central rotation axis. The control system enables the control of the propelling units. The propelling units generate the flight forces for the aircraft in the desired direction. In addition, each of the propelling units include a blade body, a shaft channel, a spar shaft, and at least one aileron assembly. The shaft channel receives the spar shaft within the blade body. The spar shaft connects the blade body to the rotor. The blade body passively corrects its angle of attack and supports the aileron assembly. The aileron assembly adjusts the pitch of the blade body.
    Type: Grant
    Filed: June 21, 2019
    Date of Patent: August 29, 2023
    Inventor: Thomas Norman Hesse
  • Patent number: 11713106
    Abstract: An aircraft wing is provided having a wing leading edge, a cut-out opening in the wing leading edge, a telescopic tube extending through the cut-out opening and connected to an internal duct of a wing leading edge slat to establish fluid communication with heated air associated with an aircraft anti-icing system, wherein the telescopic tube is moveable between retracted and extended conditions in response to the wing leading edge slat being moved between slat retraction and deployment positions, respectively, and a cover assembly comprising a cover member operatively connected to the telescopic tube to close the cut-out opening and allow synchronous movement of the cover member with the telescopic tube in response to the telescopic tube being moved between the retracted and extended conditions thereof.
    Type: Grant
    Filed: March 12, 2020
    Date of Patent: August 1, 2023
    Assignee: EMBRAER S.A.
    Inventor: Marco Antonio Antunes
  • Patent number: 11685517
    Abstract: Installation of powered actuators in the leading edge of a control surface in order to have a better weight distribution. The systems described herein propose an actuation system with a static ground structure used to move a control surface of an aircraft. The actuation system, and the ground structure are aligned with the center of rotation of the control surface, providing the aircraft with flutter suppression. This proposal is an approach to use the actuator in a place favorable to the mass balancing and reducing or even dismissing the usage of mass balancing, saving weight and cost.
    Type: Grant
    Filed: August 11, 2021
    Date of Patent: June 27, 2023
    Assignee: Embraer S.A.
    Inventors: Marcelo Galväo, Rodolfo de Souza Martins
  • Patent number: 11628930
    Abstract: A lift control device actively controls the lift force on a lifting surface. The device has a protuberance near a trailing edge of its lifting surface, which causes flow to separate from the lifting surface, generating regions of low pressure and high pressure which combine to increase the lift force on the lifting surface. The device further includes a means to keep the flow attached around the protuberance or to modify the position of the protuberance in response to a command from a central controller, so as to provide an active control of the lift between a maximum value and a minimum value.
    Type: Grant
    Filed: May 18, 2021
    Date of Patent: April 18, 2023
    Assignee: Arctura, Inc.
    Inventors: Neal E. Fine, John A. Cooney, Jr.
  • Patent number: 11608157
    Abstract: Method for assembling a slat, for an aircraft wing, comprising providing a skin and a plurality of stiffeners; assembling the stiffeners to the skin obtaining a skin sub-assembly; providing a spar and a plurality of lugs; assembling the lugs to the spar obtaining a spar sub-assembly; assembling the spar sub-assembly to the skin sub-assembly to obtain the slat.
    Type: Grant
    Filed: January 17, 2020
    Date of Patent: March 21, 2023
    Assignee: Asco Industries NV
    Inventor: Bob Armand Henri Everaert
  • Patent number: 11603182
    Abstract: A variable camber wing for mounting to a vehicle chassis has an actuator shaft and a static pin extending from the chassis. The wing's nose segment defines a proximal edge and a distal edge and has a channel therethrough between the proximal and distal edges, an arcuate aperture therethrough aft of the channel, and a second aperture therethrough aft of the arcuate aperture. The wing has a first linkage defining a clevis on a proximal end and hingeably connected to the nose segment. The clevis can rotatably engage with the static pin extending through the arcuate aperture. A second linkage defines a second clevis on a proximal end and a distal edge. The second linkage is configured to hingeably connect to the first linkage.
    Type: Grant
    Filed: August 5, 2022
    Date of Patent: March 14, 2023
    Inventor: Richard E Dooley
  • Patent number: 11597500
    Abstract: A variable camber wing for mounting to a vehicle chassis has an actuator shaft and a static pin extending from the chassis. The wing's nose segment defines a proximal edge and a distal edge and has a channel therethrough between the proximal and distal edges, an arcuate aperture therethrough aft of the channel, and a second aperture therethrough aft of the arcuate aperture. The wing has a first linkage defining a clevis on a proximal end and hingeably connected to the nose segment. The clevis can rotatably engage with the static pin extending through the arcuate aperture. A second linkage defines a second clevis on a proximal end and a distal edge. The second linkage is configured to hingeably connect to the first linkage.
    Type: Grant
    Filed: August 5, 2022
    Date of Patent: March 7, 2023
    Inventor: Richard E Dooley
  • Patent number: 11591086
    Abstract: A hybrid unmanned aerial vehicle (10) is provided which comprises a multicopter frame (14) having a plurality of operable multicopter propulsion units (22) thereon, and an airframe body (16) which is connected to the multicopter frame (14). There is also a pair of wings (34) positioned on opposite sides of the airframe body (16) and a wing control means for manipulating the pair of wings (34) with respect to the airframe body (16) to alter an angle-of-attack of the pair of wings (34). In a first wing condition, the angle-of-attack of the pair of wings (34) is alterable with respect to a relative airflow so as to produce zero lift, and, in a second wing condition, the angle-of-attack of the pair of wings (34) is alterable with respect to the relative airflow so as to produce an optimum or near optimum lift. A method of improving the manoeuvrability of the hybrid unmanned aerial vehicle (10) is also provided, as is a method of improving the operational range of unmanned aerial vehicles.
    Type: Grant
    Filed: July 10, 2018
    Date of Patent: February 28, 2023
    Inventor: Graham Lee Kelly
  • Patent number: 11591068
    Abstract: A wing assembly includes a swept wing body, a leading edge of the wing body extending outward and rearward from a wing root to a wing edge; a first slat selectively movably connected to the wing body; and a second slat selectively movably connected to the wing body, the second slat being disposed outboard of the first slat, a flexible sealing member disposed and connected between the first slat and the second slat; at least a portion of the first slat, at least a portion of the second slat, and at least a portion of the flexible sealing member defining a slat gap therebetween, at least a majority of the slat gap being substantially parallel to a predetermined local airflow direction. An aircraft is also disclosed which includes a fuselage; and two oppositely disposed wing assemblies connected to the fuselage.
    Type: Grant
    Filed: June 9, 2020
    Date of Patent: February 28, 2023
    Assignee: BOMBARDIER INC.
    Inventors: Stephen Colavincenzo, Robby Lapointe, Mohammad Tabesh
  • Patent number: 11492096
    Abstract: Noise-abatement for a leading edge wing slat is provided by a noise-abatement airflow shield integral with the lower trailing edge of the slat, wherein the shield is reciprocally autonomously curveable from a substantially planar configuration when the slat is in a retracted position thereof and into a convexly curved configuration when the slat is in a deployed position thereof.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: November 8, 2022
    Assignees: EMBRAER S.A., USP—UNIVERSIDADE DE SÃO PAULO
    Inventors: Danillo Cafaldo Dos Reis, Leandro Guilherme Crenite Simões, Micael Gianini Valle Do Carmo, Fábio Santos Da Silva, Eduardo Lobão Capucho Coelho, Leandro Souza De Moura Lima, Paulo Anchieta Da Silva, Fernando Martini Catalano, Cecil Wagner Skaleski, Francisco Keller Klug, Marcus Felipe Hori Ochi
  • Patent number: 11465732
    Abstract: A method and apparatus for positioning a control surface. An apparatus comprises an arm, first link, and second link. The arm has first and second ends, the first end of the arm rotatably coupled to a wing structure to define a first pivot point. The first link has first and second ends, the first end being rotatably coupled to the second end of the arm. The second link has first and second ends, the first end rotatably coupled to the first end of the arm. When the second end of the first link is rotatably coupled to a first control surface and the second end of the second link is rotatably coupled to a second control surface, movement of the first control surface away from the wing structure rotates the arm about the first pivot point such that the second control surface moves in coordination with the first control surface.
    Type: Grant
    Filed: May 23, 2018
    Date of Patent: October 11, 2022
    Assignee: The Boeing Company
    Inventors: Kevin Tsai, Lisa Schleuter
  • Patent number: 11420727
    Abstract: An airfoil arrangement which allows an increased reliability and increased aerodynamic performance of airfoils. A catching bracket is provided which is mounted in a track device opening to reduce the area of the track device opening and, when there is a failure of at least one support roller, the catching bracket engages the track device.
    Type: Grant
    Filed: July 24, 2020
    Date of Patent: August 23, 2022
    Assignee: Airbus Operations GmbH
    Inventors: Florian Lorenz, Dustin Shapi
  • Patent number: 11407492
    Abstract: A leading edge (3) of a control surface (1) for an aircraft includes a balance weight (6) attached to the forward-most region of the leading edge (3). The control surface (1) rotates with respect to the stabilizer (2) around a hinge line (5). The balance weight (6) is ahead of and adjacent to the most frontal portion (7) of the leading edge (3) of the control surface (1) are is inside the trailing edge of the stabilizer (2). This arrangement allows to have an anti-flutter balance weight without any impact in aerodynamic drag.
    Type: Grant
    Filed: October 27, 2020
    Date of Patent: August 9, 2022
    Assignee: AIRBUS OPERATIONS, S.L.U.
    Inventors: Alberto Balsa-Gonzalez, Miguel Ángel Mendez Rodriguez, Robert Kobierecki, Juan Antonio Sánchez Ruiz
  • Patent number: 11383821
    Abstract: A wing leading-edge device includes a flow body having a front side, a back side, a plurality of ribs arranged in ribs, wherein at least one of the ribs is a load introduction rib having at least one first lug for coupling with a drive mechanism, a second load path component, which includes at least one second lug, wherein the second load path component is at least connected to the load introduction rib, such that a second opening of the at least one second lug is co-axial with a first opening of the at least one first lug.
    Type: Grant
    Filed: March 4, 2020
    Date of Patent: July 12, 2022
    Inventors: Stefan Bensmann, Marcus Erban, Martin Fees
  • Patent number: 11377197
    Abstract: High-lift systems and related methods are described. An example apparatus includes a fixed wing and a Krueger flap movably coupled to the fixed wing between a stowed position and a deployed position. The Krueger flap includes a first flap portion movably coupled to the fixed wing and a second flap portion movable coupled to the first flap portion. The first flap portion moves relative to the second flap portion between a retracted position and an extended position. The first flap is to move to the retracted position in response to the Krueger flap moving to the stowed position. The first flap is to move to the extended position to define an aerodynamic surface in response to the Krueger flap moving to the deployed position.
    Type: Grant
    Filed: July 10, 2019
    Date of Patent: July 5, 2022
    Assignee: The Boeing Company
    Inventors: Arvin Shmilovich, Eric David Dickey
  • Patent number: 11338905
    Abstract: Offset drive arm actuation of inboard flaps is disclosed. A disclosed example apparatus includes an inboard flap support for moving an inboard flap. The inboard flap support includes an offset drive arm extending between a first attachment point of the inboard flap and a first pivot of a support, and a linkage extending between a second attachment point of the inboard flap positioned at a different position from the first attachment point and a second pivot of the support.
    Type: Grant
    Filed: November 11, 2019
    Date of Patent: May 24, 2022
    Assignee: The Boeing Company
    Inventor: Michael T. Mortland
  • Patent number: 11332245
    Abstract: A vehicle, such as a micro-aerial vehicle or underwater vehicle, includes at least one lift structure, such as a low-aspect-ratio wing or a fin, respectively. The at least one lift structure comprises one or more alulas. A leading surface of each alula is (a) flush with a leading surface of the lift structure or (b) offset from the leading edge of the lift surface by up to approximately 10% of the chord length of the lift structure. The length of each alula is no more than approximately 20% of a lift structure length corresponding to the lift structure. In various embodiments, the alula is deflected or canted with respect to a plane defined by the lift structure. In an example embodiment, the alulas may be slid or translated along at least a portion of the span of the lift structure.
    Type: Grant
    Filed: December 10, 2019
    Date of Patent: May 17, 2022
    Assignee: University of Florida Research Foundation, Incorporated
    Inventors: Kamran Mohseni, Thomas I. Linehan
  • Patent number: 11312472
    Abstract: A section of an aircraft wing including a leading edge of the aircraft wing. A leading edge part of the section includes ribs; and a skin fixedly attached to the ribs to form a spanwise series of adjacent cells. Each cell includes an enclosed volume bounded by the skin at the leading edge and a pair of the ribs. At least one cell of the series of adjacent cells is a dry cell include a mounting point for mounting a leading edge high-lift device support apparatus in the dry cell. The skin at the leading edge provides a primary load path for carrying at least some of a spanwise primary load experienced by the section when in use on an aircraft.
    Type: Grant
    Filed: December 10, 2019
    Date of Patent: April 26, 2022
    Assignee: Airbus Operations Limited
    Inventor: David Brakes
  • Patent number: 11299255
    Abstract: A slat (50) for an aircraft wing comprises a leading edge (51) defining a leading edge line (61), a trailing edge (52) defining a trailing edge line (62), the leading and trailing edges line defining a slat plane, the chord distance (69) extending normal to the leading edge and measured along the slat plane; an inboard edge extending between the leading and trailing edges; and an outboard edge (56) extending between the leading and trailing edges. The outboard edge comprises a first side portion having a projection on the plane defining a first side line (63), and a second side portion having a projection on the plane defining a second side line (64), the second side line being disposed at a first angle to the first side line and at a second angle to the leading edge line as it extends toward the inboard and trailing edges. A wing assembly and an aircraft including the slat are also disclosed.
    Type: Grant
    Filed: November 16, 2017
    Date of Patent: April 12, 2022
    Assignee: BOMBARDIER INC.
    Inventors: Fassi Kafyeke, Marc Langlois
  • Patent number: 11286033
    Abstract: A wing for an aircraft including a main wing, slat, and connection assembly movable connecting the slat to the main wing and including an elongate slat track. A front end of the slat track is mounted to the slat. A rear end and an intermediate portion of the slat track are mounted to the main wing by a roller bearing that includes a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The wing has redundant main load paths. The guide rail includes a guide rail primary structure engaging with the first roller unit and an additional reinforcement structure additionally reinforcing the guide rail primary structure in a lateral direction. The guide rail primary structure forms a first main load path. The reinforcement structure forms a redundant second main load path.
    Type: Grant
    Filed: March 26, 2020
    Date of Patent: March 29, 2022
    Assignee: Airbus Operations GmbH
    Inventors: Florian Lorenz, Dennis Krey, Bernhard Schlipf, Dustin Shapi
  • Patent number: 11254414
    Abstract: Aircraft wing droop leading edge apparatus and methods are described. An example aircraft includes a wing having a front spar and an outer skin covering the front spar. The outer skin includes a forward portion located forward of the front spar. The forward portion of the outer skin includes a leading edge movable between a neutral position and a drooped position deflected downward relative to the neutral position. The forward portion of the outer skin has a continuous outer mold line when the leading edge is in the drooped position.
    Type: Grant
    Filed: April 15, 2020
    Date of Patent: February 22, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Arvin Shmilovich, Eric D. Dickey
  • Patent number: 11214355
    Abstract: A wing for an aircraft is disclosed having a main wing, a slat, and a connection assembly movable connecting the slat to the main wing. The connection assembly includes an elongate slat track, and the front end of the slat track is mounted to the slat. The rear end and the intermediate portion of the slat track are mounted to the main wing by a roller bearing that includes a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail, and wherein the roller bearing having a second roller unit that is mounted to the main wing and that engages an engagement surface of the slat track. The slat track is supported in a wing span direction by a lateral support.
    Type: Grant
    Filed: January 30, 2019
    Date of Patent: January 4, 2022
    Assignee: AIRBUS OPERATIONS GmbH
    Inventors: Bernhard Schlipf, Florian Lorenz, Dennis Krey, Stefan Bensmann
  • Patent number: 11192625
    Abstract: Apparatus for improving flow characteristics around aircraft wings by obstructing air flow through an aperture formed in a wing skin for a movable duct or track are disclosed. In one embodiment, the apparatus comprises a substantially rigid panel movable at least partially across the aperture for at least partially occluding the aperture and for accommodating movement of a slat track extending through the aperture. In another embodiment, the apparatus comprises a hinged panel configured to swing outwardly from an outer side of the wing skin toward an open position to accommodate movement of an anti-icing duct extending through the aperture and to swing toward a closed position at least partially occluding the aperture.
    Type: Grant
    Filed: June 9, 2017
    Date of Patent: December 7, 2021
    Assignee: BOMBARDIER INC.
    Inventors: Matthew Poloni, Julien Lardy, Jeffrey Massey, Faris Jasem
  • Patent number: 11192635
    Abstract: An actuator arrangement for an aircraft flexible control surface comprises a base and a rotary element having a joint axle articulated on the base. The actuator arrangement comprises at least two attachment struts, each having three joint axles. A first joint axle is rotatably articulated on the rotary element. A second joint axle, arranged at a first strut end, is configured to be articulated on a first control surface skin panel. A third joint axle, arranged at a second strut end, is configured to be articulated on a second control surface skin panel. The actuator arrangement also comprises at least one connecting element having one joint axle at both ends, a first joint axle being articulated on the base and a second joint axle being articulated on one of the two struts, and an actuator configured to rotate the rotary element relative to the base.
    Type: Grant
    Filed: September 17, 2018
    Date of Patent: December 7, 2021
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Marc Antonio Bentivoglio, Marco Biondini, Michael Hoeft, Henrik Luettmann, Malte Werwer, Andre Thomas
  • Patent number: 11186356
    Abstract: A wing for an aircraft includes a main wing, slat, and connection assembly movable connecting the slat and main wing. The connection assembly includes an elongate slat track, a front end of which is mounted to the slat. The rear end and intermediate portion of the slat track are mounted to the main wing by a roller bearing including a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The roller bearing includes a second roller unit mounted to the main wing and engaging an engagement surface at the intermediate portion of the slat track. The slat track profile has upper and lower flange portions and a web portion connecting them. The second roller unit is in a recess between upper and lower flange portions and engages the engagement surface at the upper flange portion and/or at the lower flange portion.
    Type: Grant
    Filed: October 25, 2019
    Date of Patent: November 30, 2021
    Assignee: Airbus Operations GmbH
    Inventors: Bernhard Schlipf, Florian Lorenz, Stefan Bensmann, Dustin Shapi
  • Patent number: 11174003
    Abstract: A flap and spoiler system of an aircraft wing including a spoiler having a spoiler leading edge and a spoiler trailing edge. The flap and spoiler system also includes a flap having a flap leading edge and a flap trailing edge, an axis of rotation through the flap, and a top surface portion above the axis of rotation. The top surface portion has a first semi-circular shape such that, when the flap rotates about the axis of rotation, the spoiler trailing edge remains substantially stationary. When the spoiler trailing edge remains substantially stationary the spoiler is not driven by a spoiler drive.
    Type: Grant
    Filed: June 20, 2019
    Date of Patent: November 16, 2021
    Inventor: Farzad Mokhtarian
  • Patent number: 11174002
    Abstract: An edge-morphing arrangement for an airfoil includes a compliant upper surface and a compliant lower surface that are joined together. An actuator is coupled to a driven surface and actuated to move the driven surface and change the shape thereof, with the non-driven surface changing its shape in response to actuation of the driven surface. The upper and lower surfaces can be part of a sub-flap mounted to a traditional flap of the fixed wing of an airplane. The upper and lower surfaces can be mounted to existing structure in the flap, or the flap components can be mounted to the sub-flap. The upper and lower surfaces can alternatively replace the traditional flap in the fixed wing of an aircraft. The upper and lower surfaces are continuous and can be deflected upward, downward, or twisted in a span-wise direction relative to the flap or wing.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: November 16, 2021
    Assignee: FlexSys, Inc.
    Inventors: Sridhar Kota, Gregory F. Ervin, Jia-Hsuan Lo, Kerr-Jia Lu, Dragan Maric, Mark R. Trost, Ruey-Khan K. Tsang
  • Patent number: 11034433
    Abstract: An aircraft wing includes a main wing having an outer skin defining an interior space of the main wing, a slat, and a connection assembly for movably connecting the slat to the main wing, such that the slat is movable in a predefined motion between a retracted position and at least one extended position. The assembly includes an elongate guide arranged within the interior space, a bearing at least partly arranged outside the interior space, an elongate slat track with a first end section connected to the slat and a second end section movably and rotatable connected to the guide, such that the second end section is movable along a predefined pathway defined by the guide while being connected to the main wing. An intermediate section of the slat track is movably and rotatably supported on the main wing, such that the guide and the bearing support the predefined motion.
    Type: Grant
    Filed: April 23, 2018
    Date of Patent: June 15, 2021
    Inventor: Stefan Bensmann
  • Patent number: 11027820
    Abstract: A wing comprising a fixed main part and a leading edge slat with upper and lower surface rear edges. The wing main part has an upper surface wall, which extends downstream and in alignment with the upper surface rear edge, and a lower surface wall, which extends downstream and in alignment with the lower surface rear edge. The wing has an upper surface gap between the end of the upper surface rear edge and the end of the upper surface wall and a lower surface gap between the end of the lower surface rear edge and the end of the lower surface wall. The wing has an upper surface channel downstream of the upper surface gap and a lower surface channel downstream of the lower surface gap. The wing comprises a suction system connected to each channel and arranged to suck the air contained in the channel.
    Type: Grant
    Filed: November 5, 2018
    Date of Patent: June 8, 2021
    Assignee: Airbus Operations SAS
    Inventor: Mathias Farouz-Fouquet
  • Patent number: 10988233
    Abstract: [Object] To provide a wing achieving reduction of friction drag and easy to design and also easy to manufacture and an aircraft including such a wing. [Solving Means] A wing 1 is typically used as a main wing of an aircraft 100. The wing 1 is a swept-back wing having a swept-back angle A. The wing 1 is configured such that a surface pressure (pressure distribution (Cp)) on an upper surface of a vicinity of a leading edge 11 in a fluid increases from a wing root 17 to a wing tip 15. A cross-flow component of an external streamline of a surface of the wing 1 is reduced in the vicinity of the leading edge 11, and boundary layer transition is not easily induced in the vicinity of the leading edge 11. With this, friction drag caused by cross-flow instability can be reduced.
    Type: Grant
    Filed: February 21, 2017
    Date of Patent: April 27, 2021
    Assignee: JAPAN AEROSPACE EXPLORATION AGENCY
    Inventors: Yoshine Ueda, Naoko Tokugawa
  • Patent number: 10889365
    Abstract: Described herein is an auxiliary support system for a flap coupled to a wing of an aircraft. The auxiliary support system comprises a base fixable relative to the wing. The auxiliary support system also comprises a first track engagement assembly fixed to the base. The auxiliary support system further comprises a second track engagement assembly fixed to the base. The auxiliary support system additionally comprises a track arm attachable to the flap and comprising a first rail, movably engaged with the first track engagement assembly, and a second rail, movably engaged with the second track engagement assembly. The first rail is spaced apart from and non-parallel to the second rail.
    Type: Grant
    Filed: March 15, 2018
    Date of Patent: January 12, 2021
    Assignee: The Boeing Company
    Inventors: Bret A. Bowers, Mirela Isic
  • Patent number: 10836465
    Abstract: A main aircraft wing slat assembly comprising a slat and two elongate slat tracks. A drive arrangement drivingly engages the two slat tracks and effects parallel synchronous movement of the slat tracks between retracted and extended positions. The connection between the slat and one or both slat tracks is realized by an interconnection portion extending between at least part of the slat and at least part of the respective slat track. The interconnection portion is elastically deformable and constructed such that a first stiffness against deformation about a first axis, is at least ten times a second stiffness against deformation about a second axis, which extends perpendicularly to the first axis and between the first and second portions of the interconnection portion, and at least ten times a third stiffness against deformation about a third axis, which extends perpendicularly to the first and second axes.
    Type: Grant
    Filed: November 23, 2017
    Date of Patent: November 17, 2020
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Bernhard Schlipf, Dort Daandels
  • Patent number: 10800511
    Abstract: An end seal device for a high-lift device on an airfoil leading edge of an airfoil includes an end seal body configured to be coupled to the airfoil and having a seal body spanwise portion and a seal end. The end seal body is configured to be in a seal extended position when the high-lift device is in a device extended position. The seal body spanwise portion is disposed adjacent to the aircraft body or the airfoil leading edge and the seal end is disposed adjacent to a device end of the high-lift device when the end seal body is in the seal extended position and the high-lift device is in the device extended position. The end seal body in the seal extended position fills a discontinuity otherwise occurring between the device end and the aircraft body or airfoil leading edge if the end seal body were omitted.
    Type: Grant
    Filed: May 31, 2018
    Date of Patent: October 13, 2020
    Assignee: The Boeing Company
    Inventors: Eric David Dickey, Norman Henry Princen, Pichuraman Sundaram, Dharmendra Nathubhai Patel
  • Patent number: 10737763
    Abstract: A slat track device (7) for an aircraft wing (1) including a beam-shaped main load bearing track structure (9) connected to a slat (5) and movably connected to a main wing (3), a guidance surface (11) at the track structure (9) and guided along a corresponding guidance device (19) at the main wing, a connection device (13) at the track structure (9) connecting the track structure (9) to the slat (5), and an engagement device (15) at the track structure (9) and configured to engage a drive member (33) of a drive unit (37) provided at a main wing (3). The slat track device has redundant main load paths achieved by the track structure (9) having a first track member (41) and a separate second track member (43) both connected to the connection device (13) and the engagement device (15).
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: August 11, 2020
    Assignee: Airbus Operations GmbH
    Inventors: Bernhard Schlipf, Stefan Bensmann, Lutz Wiese
  • Patent number: 10633079
    Abstract: An aircraft wing system and method comprising: an aircraft wing including upper and lower surfaces, and a leading edge between the upper and lower surfaces; a fairing coupled to the leading edge; and actuation means configured to move the fairing relative to the aircraft wing between a stowed position, a first deployed position, and a second deployed position. The stowed position is when the fairing is in contact with the aircraft wing and serves as a continuation of the aircraft wing. The first deployed position is when the fairing is in contact with the aircraft wing and located below the stowed position. The second deployed position is when the fairing is spaced apart from the leading edge to create a gap between the fairing and the leading edge.
    Type: Grant
    Filed: June 17, 2016
    Date of Patent: April 28, 2020
    Assignee: BAE Systems plc
    Inventor: Robert Brown
  • Patent number: 10569859
    Abstract: A high-lift device comprising an airfoil shaped body having a leading edge and a trailing edge and extending in a spanwise direction configured mainly to generate aerodynamic force; a profile structure arranged to be mounted inside of the airfoil shaped body and extending in spanwise direction of the airfoil shaped body that is configured to provide most of the mechanical strength and stiffness; wherein the airfoil shaped body is provided with an opening extending in spanwise direction at one side through which the profile structure can be fastened and remains accessible inside of the airfoil shaped body.
    Type: Grant
    Filed: April 11, 2017
    Date of Patent: February 25, 2020
    Assignee: ASCO INDUSTRIES NV
    Inventors: Bob Armand Henri Everaert, Alexander Jean M. Verhuizen, Raf Thys, Tom Robert Adelin De Baere, Michaël Raets
  • Patent number: 10543899
    Abstract: An adjustable, or all-moving, horizontal stabiliser for an aircraft, the stabiliser having a leading edge, a trailing edge, a root and a tip, and a strake fixed with respect to the stabiliser and attached to, or integrally formed with, the stabiliser leading edge adjacent the root.
    Type: Grant
    Filed: October 18, 2010
    Date of Patent: January 28, 2020
    Assignees: AIRBUS OPERATIONS LIMITED, AIRBUS OPERATIONS GMBH, AIRBUS OPERATIONS SAS
    Inventors: Ian Roy Whitehouse, Carsten Weber, Markus Fischer, Alain Tanguy
  • Patent number: 10513326
    Abstract: A section of an aircraft wing including a leading edge of the aircraft wing. A leading edge part of the section includes ribs; and a skin fixedly attached to the ribs to form a spanwise series of adjacent cells. Each cell includes an enclosed volume bounded by the skin at the leading edge and a pair of the ribs. At least one cell of the series of adjacent cells is a dry cell include a mounting point for mounting a leading edge high-lift device support apparatus in the dry cell. The skin at the leading edge provides a primary load path for carrying at least some of a spanwise primary load experienced by the section when in use on an aircraft.
    Type: Grant
    Filed: December 15, 2016
    Date of Patent: December 24, 2019
    Assignee: Airbus Operations Limited
    Inventor: David Brakes
  • Patent number: 10507909
    Abstract: An aerofoil has a main portion of aerofoil cross section and a trailing edge portion (12) movable with respect to the main portion by an actuating device (14), the trailing edge portion (12) is movable at or about an area/point of flexion A, the area/point of flexion A is located at or adjacent a pressure or suction surface of the aerofoil, the trailing edge portion (12) is connected to the main portion by first and second connection members (18, 20), the first connection member (18) extends inwardly away from the area/point of flexion A and has an end which is directly or indirectly connected to the main portion, the first and second connection members (18, 20) are flexible.
    Type: Grant
    Filed: April 21, 2016
    Date of Patent: December 17, 2019
    Assignee: AGUSTAWESTLAND LIMITED
    Inventors: Andrew Cave, Simon Stacey
  • Patent number: 10472977
    Abstract: An erosion shield assembly includes an erosion shield, a carbon allotrope heater attached to an inner surface of the erosion shield, and an adhesive layer between the carbon allotrope heater and the erosion shield. The carbon allotrope heater includes at least one layer of a carbon allotrope material.
    Type: Grant
    Filed: December 29, 2016
    Date of Patent: November 12, 2019
    Assignee: Goodrich Corporation
    Inventors: Wenping Zhao, Galdemir Cezar Botura, Tommy M. Wilson, Jr., Brad Hartzler, Zaffir A. Chaudhry
  • Patent number: 10006436
    Abstract: Rotor blades for a wind turbines include a structural support member disposed internal the rotor blade that extends for at least a portion of a rotor blade span length and an airfoil structure supported by the structural support member, the airfoil structure comprising a shell portion and at least one load-transferring exterior panel. The shell portion and the at least one load-transferring exterior panel combine to form an aerodynamic profile comprising a leading edge opposite a trailing edge and a pressure side opposite a suction side. Moreover, the shell portion and the at least one load-transferring exterior panel are independently connected to the structural support member.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: June 26, 2018
    Assignee: General Electric Company
    Inventors: Christopher Daniel Caruso, Edward McBeth Stewart, Aaron Alpheus Yarbrough
  • Patent number: 9950802
    Abstract: An aircraft wing has a plurality of wing segments mounted on a wing spar by joints that allow relative movement between the spar and the wing segments. Tuning of coefficients of thermal expansion is employed to reduce induced stresses from changes in temperature.
    Type: Grant
    Filed: October 12, 2015
    Date of Patent: April 24, 2018
    Assignee: THE BOEING COMPANY
    Inventors: Robert Erik Grip, Blaine Knight Rawdon
  • Patent number: 9771141
    Abstract: A slat control system for an aircraft may include a flight control computer configured to generate a gap command in response to an occurrence of a gap-command condition. The slat control system may further include an edge control system including an edge control device having a plurality of control device positions including at least one designated control device position. The slat control system may additionally include a device actuation system configured to move a leading edge device of an aircraft. The edge control system may be configured to automatically command the device actuation system to extend the leading edge device from a sealed position to a gapped position when the edge control device is in the designated control device position and the gap command is received by the edge control system.
    Type: Grant
    Filed: September 24, 2013
    Date of Patent: September 26, 2017
    Assignee: The Boeing Company
    Inventors: Matthew A. Moser, Michael R. Finn, Duk Park, Christopher A. Konings