Airfoil Construction Patents (Class 244/123.1)
  • Patent number: 11565787
    Abstract: The present disclosure defines a morphing airfoil having a dynamic flexible anisotropic skin system that is capable of carrying high level aerodynamic (or fluid) pressure loads over a structural surface. The structural surface can morph and bend in response to control inputs to change a lift force without separate movable control surfaces. The anisotropic skin is attached to underlying active and compliant structures. 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: January 31, 2023
    Assignee: United States of America as represented by the Secretary of the Air Force
    Inventors: Jared Neely, James Joo
  • Patent number: 11548616
    Abstract: A split-flap wing assembly having a wing with a flap frame, a flap having a lateral pivot axis, and one, two or more flap sweep members having a forward end attached at a hinge in a forward end of the flap frame of the wing, and a rearward end attached pivotally to a flap hinge of the flap along the lateral pivot axis. The flap sweep members are pivotable at the forward end from a neutral sweep position within the flap frame, to a deployment angle at which the rearward end of the flap sweep members are farther away from the wing's camber line, to form a slot between the flap frame and a forward edge of the flap that allows airflow from along the lower surface of the wing to flow through the slot and to the interior surface of the flap.
    Type: Grant
    Filed: March 1, 2021
    Date of Patent: January 10, 2023
    Inventor: Lucas Kai-Luen Hung
  • Patent number: 11485473
    Abstract: An airfoil body for an aircraft extending from an inner end to an outer end, and between a leading edge and a trailing edge. The airfoil body comprises an internal structure and an airfoil skin covering the internal structure. The skin has a pressure side and a suction side, and the suction side includes a light transmitting portion. The internal structure includes an array of transduce elements attached to a planar sheet with the airfoil body. The present disclosure further relates to wings and aerial vehicles.
    Type: Grant
    Filed: October 31, 2020
    Date of Patent: November 1, 2022
    Assignee: SolAero Technologies Corp.
    Inventor: Matthew Kruse
  • Patent number: 11479336
    Abstract: Pressure decks, aircraft that incorporate the pressure decks, and methods of manufacturing the pressure decks, where the pressure decks include a planar center deck section configured to be attached to a keel beam of the aircraft and a pair of diagonal deck panels each extending inwardly and downwardly from a front wing spar to the planar center deck section. The pressure deck attaches the front wing spar to the keel beam at positions selected to minimize deflection stresses on the pressure deck exerted by relative movement between the front wing spar and the keel beam.
    Type: Grant
    Filed: December 19, 2019
    Date of Patent: October 25, 2022
    Assignee: The Boeing Company
    Inventors: David Leibov, Ryan Scott Carruthers, Mark Ronald McLaughlin, Daniel Cox
  • Patent number: 11459083
    Abstract: A bridging structure for a deforming foil, such as a morphing wing, that provides a fluid-dynamic surface throughout foil deformation that forms a curved fluid-dynamic surface with a relatively low drag. A high extent of foil deformation can be provided, with lower actuation force, providing a fluid-dynamic surface with a simple or complex curve in one direction, by providing a set of rail-mounted members that are joined at one end to a deforming sheet. By coupling the members with high elongation, resilient bodies, adjacent members can support each other, while permitting extension, and accommodating curvature.
    Type: Grant
    Filed: July 3, 2020
    Date of Patent: October 4, 2022
    Assignee: National Research Council of Canada
    Inventors: Jaye Mangione, Amin Fereidooni, Yong Chen, Viresh Wickramasinghe, Jan Marchwica
  • Patent number: 11440636
    Abstract: A fuel tank dam comprises a first section, a second section, a third section, and a flange section. The first section can be fixed to a first structural component, and the second section can be fixed to a second structural component. The third section has a bellows comprising a plurality of folded sections and is disposed between the first section and the second section. The flange section extends along an outer plate at least from an edge section of the third section and can be fixed to the outer plate.
    Type: Grant
    Filed: June 28, 2018
    Date of Patent: September 13, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Eizaburo Yamaguchi, Tadasuke Kurita, Hajime Tada, Yoko Taguchi, Kana Sakon, Akihisa Okuda, Ryoji Okabe
  • Patent number: 11420726
    Abstract: A split-flap wing assembly having a wing with a flap frame, a flap having a lateral pivot axis, and one, two or more flap sweep members having a forward end attached at a hinge in a forward end of the flap frame of the wing, and a rearward end attached pivotally to a flap hinge of the flap along the lateral pivot axis. The flap sweep members are pivotable at the forward end from a neutral sweep position within the flap frame, to a deployment angle at which the rearward end of the flap sweep members are farther away from the wing's camber line, to form a slot between the flap frame and a forward edge of the flap that allows airflow from along the lower surface of the wing to flow through the slot and to the interior surface of the flap.
    Type: Grant
    Filed: March 1, 2021
    Date of Patent: August 23, 2022
    Inventor: Lucas Kai-Luen Hung
  • Patent number: 11273899
    Abstract: A wing includes an upper wing skin, a lower wing skin, and a wing rib positioned between the upper wing skin and the lower wing skin. The wing rib includes: a corrugated composite web comprising a wave pattern and a first fitting coupling said corrugated composite web with one of said upper wing skin and said lower wing skin.
    Type: Grant
    Filed: January 25, 2018
    Date of Patent: March 15, 2022
    Assignee: The Boeing Company
    Inventors: Gerfried R. Achtner, Young L. Zeon
  • Patent number: 11161593
    Abstract: A T-tail joint assembly is described that is used to mechanically couple a left and right horizontal stabilizer to a vertical stabilizer. In one embodiment, the T-tail joint assembly comprises a plurality of lower rib chord members, each having a first base member, a first fin projecting from a first surface of the first base member, notches in the first fin proximate to ends of the first base member, and attachment members projecting from a second surface of the first base member that opposes the first surface. The T-tail joint assembly further comprises a plurality of upper rib chord member, each having a second base member, a second fin projecting from a surface of the second base member, and notches in the second fin proximate to ends of the second base member.
    Type: Grant
    Filed: August 5, 2019
    Date of Patent: November 2, 2021
    Assignee: The Boeing Company
    Inventor: Corey Adam Rolfes
  • Patent number: 11156203
    Abstract: This invention relates to a method of manufacturing a bulkhead unit, a method of installing a bulkhead unit, a bulkhead, a bulkhead unit and a wind turbine blade. The bulkhead is manufactured by vacuum forming or rotational moulding and has a set of predetermined openings formed during manufacturing. Various additional elements are pre-mounted or pre-integrated into the bulkhead before installation of the bulkhead unit. This pre-assembled unit can then be positioned inside the blade root section and connected to the blade section.
    Type: Grant
    Filed: October 31, 2017
    Date of Patent: October 26, 2021
    Assignee: LM WIND POWER US TECHNOLOGY APS
    Inventor: Willem Schuring Roelof
  • Patent number: 11124285
    Abstract: An aerodynamic profile including a skin defining the outer surface of the aerodynamic profile, a leading edge, a trailing edge and a central portion representing at least 50% of the chord of the profile. The profile includes a hollow core of composite material reinforced with a textile having unidirectional fibers. The hollow core has, in cross section, an oblong shape that is rounded, in particular at each of its ends. The skin bears against the hollow core over the length of the central portion of the aerodynamic profile, both on the pressure side and on the suction side of the profile. The reinforcement with a textile having unidirectional fibers permits an ideal orientation of reinforcing fibers in order to optimize mechanical properties in certain directions. The shape of the hollow core, elongate along the chord of the profile and rounded, lends it great resistance to deformation.
    Type: Grant
    Filed: July 17, 2018
    Date of Patent: September 21, 2021
    Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)
    Inventors: Rodolphe Trouve, Jean-Claude Lacombe, Julien Rodes, Thomas Schutz
  • Patent number: 11097507
    Abstract: A structure includes a skin and a foam member. The foam member has a molded contour, the mold contour being configured to provide tooled surface for the skin. When the skin is a composite skin, the foam member provides support for the skin so that the skin can be cured under heat and pressure. A method of making the foam member for a foam stiffened structure includes creating a mold having an interior cavity which resembles a desired shape the foam member. A subsequent step involves introducing a foam mixture into the mold. Next, the foam mixture is allowed to polymerize so as to expand and distribute within the cavity of the mold. The method further includes selectively controlling a density of the foam member in the mold. The foam member is at least partially cured. The foam member is assembled with a skin to produce the foam stiffened structure.
    Type: Grant
    Filed: June 28, 2016
    Date of Patent: August 24, 2021
    Assignee: Textron Innovations Inc.
    Inventors: Ramesh Thiagarajan, Suvankar Mishra, Mark Chris, William Evans, III, Mike Mikel
  • Patent number: 10994835
    Abstract: An inertia weight assembly positionable within a receiving portion of a rotor blade for use on a rotorcraft. The inertia weight assembly includes a weighted core and a casing having a closed outboard end and forming a cavity. The weighted core is disposed in the cavity such that the casing at least partially encloses the weighted core. The weighted core is formed from a first material and the casing is formed from a second material that is dissimilar to the first material. The casing provides an interface between the weighted core and the receiving portion of the rotor blade. The second material is more bondable to the receiving portion of the rotor blade than the first material.
    Type: Grant
    Filed: September 28, 2017
    Date of Patent: May 4, 2021
    Assignee: Textron Innovations Inc.
    Inventors: John Richard McCullough, Paul K. Oldroyd, Brett Rodney Zimmerman
  • Patent number: 10906629
    Abstract: A leading edge skin panel for an aerodynamic structure of an aircraft. The skin panel includes attachment components for attaching the leading edge skin panel to the structure. A primary attachment component is configured to substantially prevent spanwise relative movement between the leading edge skin panel and the structure. The remaining attachment component are configured to permit a predetermined amount of spanwise relative movement between the leading edge skin panel and the structure.
    Type: Grant
    Filed: June 25, 2018
    Date of Patent: February 2, 2021
    Assignee: Airbus Operations Limited
    Inventors: Vernon John Holmes, Rodney Evans
  • Patent number: 10858944
    Abstract: There is disclosed a method of manufacturing a fan blade for a gas turbine engine, the method comprising: providing a root insert comprising quasi-isotropic short fibre reinforced resin, providing a first sub-laminate of a fibre-reinforcement pre-form for the fan blade on a first mould surface, placing the root insert on the first sub-laminate at a position corresponding to a root of the fan blade, providing a second sub-laminate of the pre-form over the root insert and the first-sub-laminate, so that the root insert is at an intermediate position between the first and second sub-laminates; and applying heat and pressure to form the pre-form.
    Type: Grant
    Filed: February 15, 2019
    Date of Patent: December 8, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Vincent Gill
  • Patent number: 10814962
    Abstract: An flow body comprises a curved suction skin having a first perforation, a leading edge and two skin sections extending therefrom, wherein each skin section has an outer end facing away from the leading edge, an interior suction duct having a second perforation and extending through an inside of the curved suction skin in a distance from the leading edge, and two sidewall members, connected to the outer ends, wherein the sidewall members are made of a composite material. The suction skin comprises a profiled contour shape, which determines a pressure distribution over at least one of the two skin sections when air flows over the curved suction skin, wherein the pressure distribution comprises a stagnation point, a suction peak and a subsequent local pressure maximum downstream of the suction peak, wherein the first perforation extends from a stagnation point on the suction skin to the local pressure maximum.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: October 27, 2020
    Assignee: AIRBUS OPERATIONS GmbH
    Inventor: Martin Gerber
  • Patent number: 10801340
    Abstract: A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a flow path, and a turbine fluidly connected to the combustor via the flow path. At least one multi-piece structure is disposed within the flow path such that the multi-piece structure at least partially radially spans the flow path. The at least one multi-piece structure includes a fore portion defining a leading edge, a consumable aft portion defining a trailing edge, a pressure surface at least partially defined by a first surface of the fore portion and a first surface of the consumable aft portion, and a suction surface at least partially defined by a second surface of the fore portion and a second surface of the consumable aft portion.
    Type: Grant
    Filed: October 20, 2015
    Date of Patent: October 13, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Jesse M. Carr
  • Patent number: 10793250
    Abstract: A composite structure comprises stacked sets of laminated fiber reinforced resin plies and metal sheets. Edges of the resin plies and metal sheets are interleaved to form a composite-to-metal joint connecting the resin plies with the metal sheets.
    Type: Grant
    Filed: December 20, 2016
    Date of Patent: October 6, 2020
    Assignee: The Boeing Company
    Inventors: Gary Ernest Georgeson, Kenneth Harlan Griess
  • Patent number: 10745103
    Abstract: Aircraft, aircraft wings and associated shear ties are disclosed. An example apparatus includes a first panel coupled to a second panel to define a wing box; a rib disposed chordwise within the wing box; and a stringer disposed spanwise within the wing box immediately adjacent at least one of the first panel or the second panel, the rib including a shear tie including first and second legs extending in opposite directions, the first and second legs to be coupled to at least one of the first panel, the second panel, or the stringer.
    Type: Grant
    Filed: May 31, 2017
    Date of Patent: August 18, 2020
    Assignee: The Boeing Company
    Inventors: David Wesley Trop, Patrick B. Stickler, William John Koch, IV, Benjamin Joseph Palmer
  • Patent number: 10730605
    Abstract: An aircraft joint includes a first component having an outer aerodynamic surface and an inner surface, a second component having an outer aerodynamic surface and an inner surface, and a strap assembly bridging between the inner surfaces of the first and second components. The strap assembly has a first strap part attached to the inner surface of the first component, a second strap part attached to the inner surface of the second component, and a third strap part received in the first and second strap parts in a sliding manner. The third strap part when received in the first and second strap parts constrains movement of the first component relative to the second component in a direction normal to the outer aerodynamic surfaces of the first and second components in the vicinity of the strap assembly.
    Type: Grant
    Filed: May 11, 2017
    Date of Patent: August 4, 2020
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: Ross Salisbury
  • Patent number: 10720064
    Abstract: Avionic display systems and methods are provided for generating avionic displays, which include symbology and other graphics pertaining to forecast overpressure events, which are forecast to occur during supersonic aircraft flight. In various embodiments, the avionic display system includes a display device on which an avionic display is produced. A controller architecture is operably coupled to the display device. Storage media contains computer-readable code or instructions that, when executed by the controller architecture, cause the avionic display system to determine whether an overpressure event is forecast to occur due to the predicted future occurrence of a sonic boom, which has a magnitude exceeding a boom tolerance threshold. When the controller architecture determines that an overpressure event is forecast to occur, the avionic display system further generates symbology on the avionic display indicative of or visually signifying the forecast overpressure event.
    Type: Grant
    Filed: December 28, 2018
    Date of Patent: July 21, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: John G. Suddreth, Marisela Mendez Tapia, Jerry Ball, Mark Giddings
  • Patent number: 10710321
    Abstract: Methods for forming rotor blades, rotor blade mold assemblies, and cores for rotor blade mold assemblies are disclosed. A method includes providing a first shell substrate on a first mold, providing a generally hollow core on the first shell substrate, providing a second shell substrate on the generally hollow core, and providing a second mold on the second shell substrate. The method further includes flowing a resin into a mold interior defined between the first mold and the second mold.
    Type: Grant
    Filed: August 29, 2016
    Date of Patent: July 14, 2020
    Assignee: General Electric Company
    Inventors: Madireddi Vasu Datta, Afroz Akhtar, Jacob Johannes Nies
  • Patent number: 10647405
    Abstract: An aerodynamic structure incorporated in an aircraft control surface provides a spar extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.
    Type: Grant
    Filed: June 13, 2019
    Date of Patent: May 12, 2020
    Assignee: The Boeing Company
    Inventor: David C. Reusch
  • Patent number: 10639854
    Abstract: A method of manufacturing a tiltrotor wing structure including providing a spar mold having a plurality of bores extending from an exterior surface of the mold to an interior surface of the mold, the plurality of bores corresponding to a plurality of primary coordination holes in a spar member, the spar mold having a periphery defined by a top edge, a bottom edge and outboard ends; selecting a plurality of resin impregnated plies to ensure that the plies continuously extend beyond the periphery of the spar mold; laying the plies in the spar mold; curing the plies in the mold to form a cured spar member that extends beyond the periphery of the spar mold; and accurately drilling a plurality of primary coordination holes in the cured spar member in the spar mold using a tool positioned in the plurality of bores.
    Type: Grant
    Filed: February 3, 2017
    Date of Patent: May 5, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: David G. Carlson, John R. McCullough, Douglas K. Wolfe, George R. Decker, Keith A. Stanney
  • Patent number: 10532804
    Abstract: An aerodynamic control surface including an upper panel having an upper panel aft end portion, a lower panel having a lower panel aft end portion, mechanical fasteners connecting the upper panel aft end portion to the lower panel aft end portion, and a fairing having a fairing forward end portion and a fairing aft end portion, wherein the fairing forward end portion is connected to either the upper panel or the lower panel, and wherein the fairing aft end portion is connected to the other of the upper panel or the lower panel.
    Type: Grant
    Filed: February 8, 2017
    Date of Patent: January 14, 2020
    Assignee: The Boeing Company
    Inventor: Gregory M. Santini
  • Patent number: 10532807
    Abstract: A leading edge section with laminar flow control includes: a perforated outer skin, a perforated inner skin, and a plurality of suction chambers formed between the outer skin and the inner skin. The leading edge section includes a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin, such that the inner skin is joined to the stringers. A method for manufacturing a leading edge section integrating a laminar flow control system is described, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers integrally formed with the outer skin, such that suction chambers are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.
    Type: Grant
    Filed: January 10, 2017
    Date of Patent: January 14, 2020
    Assignee: Airbus Operations, S.L.
    Inventors: Carlos García Nieto, Enrique Guinaldo Fernández, Pablo Cebolla Garrofe, Iker Vélez De Mendizabal Alonso, Soledad Crespo Peña, Francisco Javier Honorato Ruiz, Álvaro Torres Salas, Álvaro Calero Casanova
  • Patent number: 10494083
    Abstract: Aerodynamic drag associated with a flap hinge assembly used to pivotally mount a flap to the trailing edge of an aircraft wing can be reduced when the cross-sectional area of the hinge fairing which surrounds the flap hinge assembly is reduced in size. The reduction in cross-sectional area of the hinge fairing is enabled when the flap hinge assembly attachment footprint to the underside of the flap box is also reduced. The flap hinge assembly has an internal support rib positioned between spars of the flap box structure internal to the skin, a hinge fitting exhibiting an actuation point and a hinge point positioned proximate a front spar of the flap box structure external to the skin, and a link passing through an aperture in the lower skin of the flap and coupling the internal support rib to the hinge fitting.
    Type: Grant
    Filed: November 21, 2016
    Date of Patent: December 3, 2019
    Assignee: The Boeing Company
    Inventors: Andrew S. Currie, Tony Sanders
  • Patent number: 10479474
    Abstract: Provided are wingtip torque boxes and methods of fabricating such boxes using friction stir welding. Specifically, a wingtip torque box may be formed by friction stir welding two monolithic clamshells along their respective spars thereby forming a new monolithic structure. Use of the friction stir welding and monolithic clamshells simplifies the overall fabrication process and yields a robust wingtip torque box that can be bolted on or otherwise attached to an aircraft wing. The wingtip torque box may include internal grid stiffeners and/or external stiffeners that may be also monolithic with other components of the box. For example, the stiffeners may be machined in spars or skin portions of the clamshells during fabrication of clamshells. The wingtip torque box may have a continuous cavity extending between the ends and, in some embodiments, between spars of the box and providing access for performing various operations inside the box.
    Type: Grant
    Filed: July 14, 2016
    Date of Patent: November 19, 2019
    Assignee: The Boeing Company
    Inventors: Michael P. Shemkunas, Kenneth D. Cominsky, Steven S. Heer, David P. Heck, Benjamin D. Smith, John A. Baumann, Matthew D. Uhlman, Burke L. Reichlinger, Eric E. Thomas, James P. Dobberfuhl
  • Patent number: 10407155
    Abstract: A slat can assembly with a slat can body includes at least one full ply of a composite fiber sheet material and a plurality of elongated, unidirectional fiber ply strips that are arranged into the shape of the slat can body. At least some of the unidirectional fiber ply strips are laid over the full ply. And, the full ply and the elongated, unidirectional fiber ply strips cooperate to provide a contoured shape defined by a cellular core member.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: September 10, 2019
    Assignee: Aerosud Technology Solutions (Pty) Ltd.
    Inventors: William L. Rodman, Wouter T. Gerber, Jacobus Frederik Swart
  • Patent number: 10315779
    Abstract: In an embodiment, a rotorcraft includes: tail rotor blades; a tail rotor actuator coupled to the tail rotor blades such that the pitch of the tail rotor blades varies according to a current extension of the tail rotor actuator; pilot flight controls electrically coupled to the tail rotor actuator; and a flight control computer electrically coupled to the tail rotor actuator and the pilot flight controls, the flight control computer configured to: determine the current extension of the tail rotor actuator; determine whether the current extension of the tail rotor actuator is within a margin of a maximum extension of the tail rotor actuator; and indicate a first warning to a pilot in response to the current extension of the tail rotor actuator being within the margin of the maximum extension of the tail rotor actuator.
    Type: Grant
    Filed: September 19, 2017
    Date of Patent: June 11, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Christopher M. Bothwell, Robert Earl Worsham, II, Sung Kyun Kim, Brandon Jeffrey Thomas
  • Patent number: 10279922
    Abstract: The disclosure generally relates to baffle fuel dams and tank boundary fuel dams having a single-piece or two-piece construction. In one example, a baffle fuel dam is a single piece having slotted holes sized and spaced to accommodate for tolerance variations during installation. The baffle fuel dams also include a base angle that allows installation at multiple locations. The disclosure also relates to tank boundary fuel dams that include a two-piece configuration which incorporates slotted holes to accommodate tolerance variations and that are sized/spaced for different installation locations. The tank boundary fuel dams may also include a base angle that allows installation at multiple locations.
    Type: Grant
    Filed: April 10, 2018
    Date of Patent: May 7, 2019
    Assignee: THE BOEING COMPANY
    Inventors: Fernando L. Perez Diaz, Richard Tanner, Brendamari Rodriguez
  • Patent number: 10246177
    Abstract: The present invention has an objective to provide a leading-edge structure for an aircraft that is capable of, in the case of a collision with an airborne object, effectively absorbing the energy of the collision with the airborne object, with no increase in its weight. A leading-edge structure (10) for an aircraft according to the present invention includes a spar (11) extending in a predetermined direction, a plurality of ribs (13) provided in the predetermined direction of the spar (11) at intervals, and a skin (17) supported by the plurality of ribs (13). The ribs (13) includes first ribs 14 and a plurality of second ribs 15 that are disposed between the pair of first ribs (14). The second ribs (15) do not support the skin in the vicinity of their front ends.
    Type: Grant
    Filed: August 18, 2016
    Date of Patent: April 2, 2019
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Kazuki Tachibana, Kohei Hara
  • Patent number: 10214277
    Abstract: A system and method for improving fuel storage within the wing of an aircraft. In one exemplary embodiment, the system and method eliminate the traditional spars and ribs, and any spanwise and cordwise connecting vertical webs, within a wing. Instead, the system comprises a plurality of modified flared spars, each having a length defined by an angled hat section, to form a wing structure. The modified flared spars may also comprise one or more lengths defined by a specialized section configured to accommodate a portion of a box section, or any other internal component of the wing. The system and method may also involve a contiguous fuel bladder of any size/type. The fuel bladder for the wing may comprise a fabric coated or impregnated with an elastomeric material that may include a polyurethane dispersion layer combined with a sealant.
    Type: Grant
    Filed: August 3, 2017
    Date of Patent: February 26, 2019
    Assignee: ROBERTSON FUEL SYSTEMS, L.L.C.
    Inventors: Quinn Canole, William York, Jeffrey Bracken
  • Patent number: 10155581
    Abstract: An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Composite laminate skins are bonded to unitized and stiffened understructure to reduce weight and improve damage containment.
    Type: Grant
    Filed: June 24, 2016
    Date of Patent: December 18, 2018
    Assignee: The Boeing Company
    Inventor: Eugene A. Dan-Jumbo
  • Patent number: 10123465
    Abstract: A method of forming a power-module assembly includes arranging power stages in a cavity of a container such that the power stages are spaced apart from walls of the container. The method further includes inserting a core between each of the power stages, and installing a manifold on top of the power stages. The method also includes putting resin into the cavity to form a housing of the power-module assembly, and removing the core to reveal coolant chambers between each of the power stages.
    Type: Grant
    Filed: April 15, 2015
    Date of Patent: November 6, 2018
    Assignee: Ford Global Technologies, LLC
    Inventors: Guangyin Lei, Michael W. Degner, Edward Chan-Jiun Jih
  • Patent number: 10023293
    Abstract: A panel assembly comprising: a panel (11); a stiffener (12) having a foot (12a), an upstanding web (12b) and a run-out region at one end; and a fitting (13), wherein the stiffener foot is bonded to the panel, and wherein the fitting is attached to the stiffener web and to the panel outboard of the end of the stiffener foot. The outboard end of the web may overhang an outboard end of the foot in the run-out region, of the stiffener.
    Type: Grant
    Filed: September 22, 2011
    Date of Patent: July 17, 2018
    Assignee: Airbus Operations Limited
    Inventors: Martin Gaitonde, Enzo Cosentino
  • Patent number: 9944402
    Abstract: The disclosure generally relates to baffle fuel dams and tank boundary fuel dams having a single-piece or two-piece construction. In one example, a baffle fuel dam is a single piece having slotted holes sized and spaced to accommodate for tolerance variations during installation. The baffle fuel dams also include a base angle that allows installation at multiple locations. The disclosure also relates to tank boundary fuel dams that include a two-piece configuration which incorporates slotted holes to accommodate tolerance variations and that are sized/spaced for different installation locations. The tank boundary fuel dams may also include a base angle that allows installation at multiple locations.
    Type: Grant
    Filed: June 3, 2015
    Date of Patent: April 17, 2018
    Assignee: THE BOEING COMPANY
    Inventors: Fernando L. Perez Diaz, Richard Tanner, Brendamari Rodriguez
  • Patent number: 9862164
    Abstract: Methods for manufacturing composite panels for use in the interior of an aircraft are disclosed, specifically, methods of manufacturing joggled composite panels comprising metal inserts and the resulting composite panels and inserts.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: January 9, 2018
    Assignee: The Boeing Company
    Inventors: Kyle L. Gray, Nathanial C. Cuddy, Harold G. Erickson
  • Patent number: 9862502
    Abstract: As a component of an aerial vehicle, a power management system having an active power control device is provided. The system includes a solar cell converting solar energy into electric energy; a fuel cell provided in the aerial vehicle and converting fuel energy into electric energy by electrochemical reaction; a battery compensating for a lack of electric power supplied from the solar cell and the fuel cell to the aerial vehicle and storing surplus electric power; and an active power control device connecting with all the solar cell, the fuel cell and the battery and combining and distributing electric power generated in the solar cell, the fuel cell and the battery to loads. The system efficiently distributes the power from the respective power sources through the controllable output of the fuel cell in accordance with power required by the aerial vehicle and the solar cell's performance depending on weather.
    Type: Grant
    Filed: October 29, 2013
    Date of Patent: January 9, 2018
    Assignee: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventors: Keun Bae Kim, Bo Hwa Lee, Poo Min Park, Chun Taek Kim, Seok Min Ahn, Soon Bae Chung, Dong Sung Kim
  • Patent number: 9845119
    Abstract: An aerodynamically effective attachment part or spoiler extension is disclosed. The spoiler extension includes a guide arrangement having a first guide element formed between the spoiler extension and a base body of the spoiler arrangement. Transfer of the spoiler extension is guided from a release position, in which the spoiler extension is detachable from the base body, along at transfer direction into a locking position, in which the spoiler extension is secured on the base body. The spoiler extension includes a securing element able to secure the spoiler extension automatically on the base body of the spoiler arrangement in the locking position.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: December 19, 2017
    Assignee: GM GLOBAL TECHNOLOGY OPERATIONS LLC
    Inventors: Michael Fuchs, Friedrich Hein
  • Patent number: 9764817
    Abstract: The invention relates to a method for covering light aircraft and/or parts thereof with a polyester covering fabric, and to a dispersion hot-melt adhesive and to the use thereof for covering. The invention further relates to a light aircraft or to a part of the same which is covered with a polyester covering fabric by means of the method according to the invention.
    Type: Grant
    Filed: September 15, 2009
    Date of Patent: September 19, 2017
    Inventor: Siegfried Lanitz
  • Patent number: 9751613
    Abstract: A brace (200) for geometrically interlocking stringer pairs A of first stringers (106), coupled to a first panel (102), and stringer pairs B of second stringers (108), coupled to a second panel (104), of a structure (100). The brace (200) comprises a chassis (202) comprising first interlocks (204) and second interlocks (206) opposite the first interlocks (204). The first interlocks (204) geometrically engage with one of the stringer pairs A of the first stringers (106) and the second interlocks (206) geometrically engage with one of the stringer pairs B of the second stringers (108) to constrain the brace (200) in all directions along a plane (112) perpendicular to the first stringers (106) and the second stringers (108).
    Type: Grant
    Filed: November 4, 2016
    Date of Patent: September 5, 2017
    Assignee: The Boeing Company
    Inventor: Steven R. Kent
  • Patent number: 9745058
    Abstract: An ornithopter includes a main wing mounted on a fuselage, and a control system configured to control a flapping motion of the main wing. The main wing includes an inner spar, an outer spar, and a wrist portion disposed between the inner spar and the outer spar and which varies a bending angle, which is a relative angle between the inner spar and the outer spar, within a predetermined angle range. The control system includes an actuator which performs a raising motion and a lowering motion of the inner spar by moving the inner spar in an upward direction and in a downward direction, an angle sensor which measures the bending angle, and a control unit which controls the actuator to move the inner spar in response to the measured bending angle.
    Type: Grant
    Filed: February 19, 2014
    Date of Patent: August 29, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Satoshi Kuroda, Tomoyuki Mori, Kazuya Hattori, Masato Tahara, Oki Takayama
  • Patent number: 9745057
    Abstract: An ornithopter includes a main wing mounted on a fuselage. The main wing includes a main spar extending outwardly from the fuselage, and a rib extending rearwardly from the main spar. The rib has an S-shaped camber.
    Type: Grant
    Filed: February 19, 2014
    Date of Patent: August 29, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Satoshi Kuroda, Tomoyuki Mori, Kazuya Hattori, Masato Tahara, Oki Takayama
  • Patent number: 9533750
    Abstract: A flight control surface such as a slat capable of keeping and achieving a minimum basic functions even when it is damaged by collisions of birds or the like, and a wing using the same are provided. Both ends of one wire cable 15 or more are fixed to paired ribs 10A and 10B provided in a short direction of the slat. This wire cable 15 is placed so as to pass through a through-hole 13 formed in each of the ribs 10 positioned between the paired ribs 10A and 10B. Even if birds or the like collide with slat 3 at the time of a flight of the aircraft to damage and deform not only a skin 4 of the slat 3 but also any rib 10, the wire cable 15 between the paired ribs 10A and 10B prevents the slat 3 from being broken into pieces.
    Type: Grant
    Filed: August 21, 2012
    Date of Patent: January 3, 2017
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Hideaki Tanaka
  • Patent number: 9517833
    Abstract: A structure (100) comprises a first panel (102); first stringers (106), coupled to the first panel (102) and comprising stringer pairs A; a second panel (104) opposite the first panel (102); and second stringers (108), coupled to the second panel (104) and opposite the first stringers (106). The second stringers (108) comprise stringer pairs B. The structure (100) also comprises braces (200). Each of the braces (200) is geometrically interlocked with one of the stringer pairs A of the first stringers (106) and one of the stringer pairs B of the second stringers (108) in all directions along a plane (112) perpendicular to the first stringers (106) and the second stringers (108).
    Type: Grant
    Filed: April 28, 2015
    Date of Patent: December 13, 2016
    Assignee: The Boeing Company
    Inventor: Steven R. Kent
  • Patent number: 9481109
    Abstract: A bracket is described for clamping a mould to a supporting structure. The bracket includes a first part and a second part for attaching to the mould and to the supporting structure, respectively, or vice versa. The first and second parts are connected together and configured to provide constrained relative movement along a first axis to accommodate thermal expansion of the mould relative to the supporting structure in a first direction parallel to the first axis. The first and second parts of the bracket are connected via an articulated joint that allows the first and second parts to pivot relative to one another without moving the first axis such that the bracket can independently accommodate misalignments between the mould and the supporting structure.
    Type: Grant
    Filed: September 27, 2012
    Date of Patent: November 1, 2016
    Assignee: Vestas Wind Systems A/S
    Inventors: Leif Kappel Petersen, Paul Todd, Nathaniel Colman
  • Patent number: 9371128
    Abstract: Structural component including at least one covering shell and a carrier structure, the covering shell designed in the form of a sandwich and formed by an inner skin section, an outer skin section and a shear-load absorbing core layer disposed between the two sections and connecting the inner and the outer skin sections to one another in a planar manner. The carrier structure is formed by at least one panel-shaped connecting part extending between and transversely to the inner and outer skin sections and connected along a reference longitudinal direction to the covering shell. The connecting part is located outside the carrier structure and fastened to the inner skin section resting thereon in a planar manner, wherein at least one profiled support extending along the reference longitudinal direction is provided in the covering shell in order to form a reinforcing section in the connecting region of the panel-shaped connecting part.
    Type: Grant
    Filed: January 16, 2013
    Date of Patent: June 21, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Ichwan Zuardy, Pierre Zahlen, Axel Siegfried Herrmann
  • Patent number: 9315254
    Abstract: A joint assembly for an aircraft is provided. The joint assembly includes a single main fitting including a first flange, a second flange, and a third flange, an external spar component coupled to the first flange using at least one fastener, an internal spar component coupled to the second flange using at least one fastener, and a body rib coupled to the third flange using at least one fastener.
    Type: Grant
    Filed: October 11, 2013
    Date of Patent: April 19, 2016
    Assignee: The Boeing Company
    Inventors: Steven Paul Walker, Joanna Mara Sergiane Veit, Isaac G. Cambronero, Jr., James Donald Davis, Michael D. Pagliarini
  • Patent number: 9272769
    Abstract: A wing joint including a T-chord and a splice plate for connecting an inboard wing panel assembly and an outboard wing panel assembly. The wing panel assemblies include a stringer co-bonded or co-cured with a wing skin. The webbing and cap of the stringer may be trimmed to expose a noodle and base flange. The noodle and base flange interface with the bottom of the T-chord and the wing skin interfaces with the splice plate. The exposed noodle may be non-flush with the base flange of the trimmed stringer. The bottom of the T-chord may include a groove to accommodate a non-flush noodle so that a gap does not exist between the T-chord and the base flange. Alternatively, shims may be used to compensate for a non-flush noodle or the base flange and web may include sacrificial plies permitting the base flange and web to be trimmed flush with the noodle.
    Type: Grant
    Filed: November 13, 2012
    Date of Patent: March 1, 2016
    Assignee: THE BOEING COMPANY
    Inventors: Chun-Liang Lin, Ryan M Mahn, Karl B Lee