Airfoil Construction Patents (Class 244/123.1)
  • 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
  • Patent number: 9248900
    Abstract: A tip fairing of a horizontal airfoil of an aircraft is provided. The tip fairing comprises stiffening elements and a skin covering the stiffening elements. The stiffening elements comprise a central web and two flanges located at the tips of the web, with contact between the skin and the stiffening elements being made through the flanges of the stiffening elements. The tip fairing is manufactured from a composite material, is manufactured from a single part, and the planes defining the webs of any pair of stiffening elements taken in twos form an angle less than about 30°.
    Type: Grant
    Filed: October 2, 2013
    Date of Patent: February 2, 2016
    Assignee: AIRBUS OPERATIONS S.L.
    Inventor: José Juan Jare{hacek over (n)}o Diz Lois
  • Patent number: 9227718
    Abstract: Lower joints of aircraft wing assemblies are disclosed. In some embodiments, a lower joint includes an outboard lower wing panel, a center lower wing panel, a rib, and a lower joint assembly that includes two outboard flanges operatively coupled to the outboard lower wing panel, an inboard flange operatively coupled to the center lower wing panel, and an upper flange operatively coupled to the rib. In some embodiments, a lower joint assembly includes one or more splice plates, an upper T-fitting, and one or more intermediate plates. In some embodiments, the outboard lower wing panel, the center lower wing panel, and the lower joint assembly are constructed substantially of different materials.
    Type: Grant
    Filed: June 7, 2013
    Date of Patent: January 5, 2016
    Assignee: The Boeing Company
    Inventors: Kenneth D. Cominsky, Jordan Daniel Charles
  • Patent number: 9033283
    Abstract: Embodiments of an aerodynamic structural insert frame comprise a leading edge, a trailing edge opposite the leading edge, and at least one cavity between the leading edge and trailing edge, wherein the aerodynamic structural insert frame is configured to deflect upon activation by an external stimulus; at least one deformable buckling member extending the distance between opposite edges of the cavity, wherein the deflection of the aerodynamic structural insert frame is configured to trigger deflection of the deformable buckling member; a pivot region; and at least one stopper bar attached to and extending from one edge of the cavity a distance less than the distance between opposite edges of the cavity, wherein the stopper bar is configured to stop the deflection of the aerodynamic structural insert and the buckling member when the stopper bar strikes an opposite edge of the cavity.
    Type: Grant
    Filed: March 13, 2013
    Date of Patent: May 19, 2015
    Assignee: Cornerstone Research Group, Inc.
    Inventors: Christopher Douglas Hemmelgarn, Bryan Michael Pelley
  • Patent number: 9027881
    Abstract: Provided is a composite material structure enabled to be reduced in weight. The composite material structure includes a front section (3a) extending in one direction and formed as a composite material made of fiber reinforced plastics, a rear section (3c) separated from the front section (3a) by a predetermined space, extending in the one direction, and formed as a composite material made of fiber reinforced plastics, and access panels (5) provided between the front section (3a) and the rear section (3c) and having a dimension in the one direction shorter than the front section (3a) and the rear section (3c). The access panels (5) are fixed to the front section (3a) and the rear section (3c) in an orthogonal direction substantially orthogonal to the one direction and set to be displaceable in the one direction and are removable.
    Type: Grant
    Filed: January 26, 2012
    Date of Patent: May 12, 2015
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Yuya Tanaka, Hideyuki Suzuki, Yutaka Kanayama, Kazuki Sato, Masatake Hatano, Satoru Saito, Akihisa Watanabe, Ryo Abe
  • Patent number: 9016551
    Abstract: The invention relates to a mounting device in an aircraft. In one aspect of the invention, a method is disclosed for assembling a metal securement member of the mounting device. In another aspect of the invention, a mounting device is disclosed. In another aspect of the invention, a method is disclosed for installing and using a mounting device in an aircraft.
    Type: Grant
    Filed: November 2, 2006
    Date of Patent: April 28, 2015
    Assignee: The Boeing Company
    Inventors: Brad L. Kirkwood, Paul S. Gregg, Gerry D. Miller, Jeff D. Will, David W. Evans
  • Patent number: 9017510
    Abstract: An airfoil is fabricated by assembling cured skins with spars having cured spar webs and uncured spar chords. The skins are bonded to the spars by curing the spar chords.
    Type: Grant
    Filed: December 13, 2011
    Date of Patent: April 28, 2015
    Assignee: The Boeing Company
    Inventor: Martin Wayne Hansen
  • Patent number: 9004406
    Abstract: An aircraft wing box spanwise joint, comprising a rib having a web, and a pair of rib fittings joined together, each rib fitting forming a closed loop around the periphery of the rib, wherein the rib is integrally formed with one of the rib fittings. Also, an aircraft wing including two or more of the joints. Also, a method of forming an aircraft wing box spanwise joint, the method comprising forming a pair of rib fittings, wherein one of the rib fittings is integrally formed with a rib having a web, each rib fitting forming a closed loop around the periphery of the rib, bringing the rib fittings together, and joining the rib fittings together.
    Type: Grant
    Filed: June 3, 2011
    Date of Patent: April 14, 2015
    Assignee: Airbus Operations Limited
    Inventor: Mochamad Agoes Soenarjo
  • Patent number: 9004405
    Abstract: A load introducing element for a control surface of an aircraft or a spacecraft comprises at least one first component, one second component and one first flange. At least one surface area of the first component is adapted to conform to the inner contour of the control surface. The second component has at least one eye for receiving bearing means for mounting the control surface. A cross sectional profile of the first component has two or more essentially straight legs, which are connected together on their upper side by an upper edge which is adapted to an upper contour of the control surface. The load introducing element is formed by a fiber reinforced composite material having an integral type of construction in which all of the components are jointly infiltrated and cured. The invention also provides a method for producing such a load introducing element, a drive armature and an aircraft that includes such a load bearing element.
    Type: Grant
    Filed: September 16, 2009
    Date of Patent: April 14, 2015
    Assignees: EADS Deutschland GmbH, AIRBUS Operations GmbH
    Inventors: Marco Goettinger, Tamas Havar, Xavier Hue, Franz Stadler
  • Patent number: 8973871
    Abstract: There is provided a box structure for carrying load having upper and lower composite integrated sandwich panels. The panels have facesheets sandwiching one or more core portions and adjacent dense packs oriented in an axial direction. The box structure further has a plurality of spars. Each spar has a web and web attachments and has a spar length in the axial direction. The plurality of spars are connected to the panels with the web attachments located at the dense packs. The facesheets are configured to carry primarily torsion and pressure loads in shear and no significant axial loads. The dense packs are configured to carry all significant box bending in axial tension and compression loads.
    Type: Grant
    Filed: January 26, 2013
    Date of Patent: March 10, 2015
    Assignee: The Boeing Company
    Inventors: Jeffery L. Marcoe, Paul S. Nordman, Stephen T. Brown, William G. Roeseler, Terry K. Isomura, Willard N. Westre
  • Patent number: 8974885
    Abstract: A structural element for reinforcing a fuselage cell of an aircraft is provided. The structural element comprises a reinforcement profile which is made in one piece from a metallic material. The profile is provided with a strap at least in regions. As a result of the strap which is made of a fiber-reinforced layer material or fiber metal laminate and is adhesively bonded, at least in regions, to a flange of the reinforcement profile the structural element has high damage tolerance and advantageous fatigue properties. The fiber metal laminate or layer material is made of a plurality of metal layers and fiber-reinforced plastics material layers which are stacked in alternating fashion and adhesively bonded to one another over the entire surface. The reinforcement profile and the strap are joined by means of a joining layer. Said joining layer is preferably constructed from two prepreg layers and a non-fiber-reinforced adhesive layer.
    Type: Grant
    Filed: April 7, 2011
    Date of Patent: March 10, 2015
    Assignee: Airbus Operations GmbH
    Inventors: Nikolaus Ohrloff, Thomas Beumler, Derk Daverschot, Matthijs Plokker
  • Publication number: 20150048207
    Abstract: The invention provides a leading edge structure for providing an aerodynamic surface of an aircraft, the leading edge structure comprising a skin structure, the skin structure providing an outer aerodynamic surface and an inner surface, both surfaces extending in a chordwise and spanwise direction of the structure, and a plurality of structural members, each structural member being connected to the inner surface of the skin structure and extending in the chordwise direction along the inner surface, wherein the structural members are integrally formed with the inner surface of the skin structure. The invention also provides an aircraft wing, aircraft tailplane, wing box structure, wing or wing structure and an aircraft including the leading edge structure.
    Type: Application
    Filed: November 22, 2012
    Publication date: February 19, 2015
    Inventors: Llifon Williams, Ross Salisbury, Marcus Rafla, Hugh Theobald, Christopher Payne, Robert McCormick, Heinz Hansen, Timothy Evans
  • Publication number: 20150041589
    Abstract: An aircraft includes a wing and a wing box. The wing is joined to the wing box at a side of body joint. The wing and the wing box each includes lower skin and a plurality of stringers on the skin. Ends of at least some of the stringers at the side of body joint have a web cutout and a base that is spanwise tapered to a knife edge at the skin.
    Type: Application
    Filed: August 9, 2013
    Publication date: February 12, 2015
    Applicant: THE BOEING COMPANY
    Inventors: Zeaid Fouad Hasan, Jeffrey F. Stulc, Phillip Roger Pratt, James A. Backlund, JR., Nickolas Scott Ellerbeck, Lyle Ray Deobald
  • Publication number: 20150041590
    Abstract: An airfoil includes a main portion formed of a base material and having an inner core comprising a hollow region. Also included is a trailing edge region of the main portion. Further included is a trailing edge supplement structure comprising a low-melt superalloy operatively coupled to the base material proximate the trailing edge region. Yet further included is at least one cooling passage fluidly coupling the inner core of the main portion to an inner region of the trailing edge region. Also included is a trailing edge region exhaust path disposed in the inner region and configured to route a cooling airflow in a span-wise direction of the airfoil.
    Type: Application
    Filed: August 9, 2013
    Publication date: February 12, 2015
    Applicant: General Electric Company
    Inventors: Kevin Richard Kirtley, David Edward Schick, Aaron Ezekiel Smith
  • Patent number: 8936216
    Abstract: The invention relates to a composite structuring panel (1) for the trailing edge of an aircraft element, having: an upper surface (3); a lower surface (5); an edge (7) connecting said upper (3) and lower (5) surfaces; the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9) and the structuring panel being made of a unitary part forming the upper surface (3), the lower surface (5), the edge (7), and the transverse stiffeners (9). The invention also relates to a method for manufacturing such a panel (1), and to an aircraft element comprising such a panel (1).
    Type: Grant
    Filed: May 28, 2010
    Date of Patent: January 20, 2015
    Assignee: Societe Lorraine de Construction Aeronautique
    Inventors: Didier Remene, Denis Millepied, Paulo Francisco, Valérian Montagne, Jean-Luc Pacary, Arnaud Bertrand
  • Patent number: 8919697
    Abstract: A structural assembly for an aircraft comprising a cover with outer and inner faces, an inner support element and urging means on the inner support element, wherein opposing edges of the cover are fixedly mounted relative to the inner support element, and the urging means acts on the inner face of the cover to urge the cover to distend outwardly and locate in a predetermined position. Another aspect of the invention relates to a method of forming a structural assembly for an aircraft comprising an cover with outer and inner faces, an inner support element and urging means on the inner support element, the method comprising the steps of fixedly mounting opposing edges of the cover relative to the inner support element and operating the urging means to act on the inner face of the cover so that the cover is urged to distend outwardly into a predetermined position.
    Type: Grant
    Filed: May 17, 2011
    Date of Patent: December 30, 2014
    Assignee: Airbus Operations Limited
    Inventor: Simon John Parker
  • Patent number: 8919696
    Abstract: A method for stiffening a skin field of an aircraft fuselage includes providing a skin field for an aircraft fuselage, manufacturing an integral lattice-shaped stiffening structure including a plurality of longitudinal stiffeners and connecting the stiffening structure to the skin field. The manufacturing can include the use of a tool mold having a plurality of longitudinal recesses configured to form longitudinal stiffeners and a plurality of sunken areas disposed between the longitudinal recess. The sunken areas are configured for forming respective mounts that are configured for connection to circumferential stiffeners.
    Type: Grant
    Filed: December 29, 2010
    Date of Patent: December 30, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Georg Lonsdorfer, Hauke Seegel, Klaus Rode, Andreas Pau, Hartmut Herter, Kevin Danke
  • Publication number: 20140374536
    Abstract: A wing including a spar, a box shaped sleeve in the spar running substantially the entire length of the wing, a skin affixed to spar and to the corners of the sleeve and shaped to from a leading edge and trailing edge of the wing, a spoiler affixed to an upper surface of the trailing edge of the spar, a vent affixed to the lower surface of the trailing edge of the spar below the spoiler.
    Type: Application
    Filed: January 14, 2014
    Publication date: December 25, 2014
    Inventor: William M. OTTO
  • Patent number: 8870120
    Abstract: A composite structure has a first section, a second section, and a curved corner joining the first and second sections. The structure has a stack of fiber-reinforced plies including first and second external plies which run from the first section into the second section on an inside and an outside of the corner, respectively. A discontinuous first internal ply is sandwiched between the first and second external plies so that more of the first internal ply is located within the first section than within the second section. A second internal ply is sandwiched between the first and second external plies. The fibers of the first internal ply run at an angle ? to the fibers of the second internal ply. In some embodiments the angle ? is greater than 3° but less than 20°. In one embodiment the angle ? is between 35° and 42°.
    Type: Grant
    Filed: February 22, 2012
    Date of Patent: October 28, 2014
    Assignee: Airbus Operations Limited
    Inventors: Timothy J. Sanderson, Stephen Williams
  • Patent number: 8864074
    Abstract: A multi layer composite L-shaped stringer for use in an aerospace structure comprises a foot and a web extending from an edge of the foot. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. The geometry of the stringer may vary along its length (L) so that as the first surface is displaced towards the second surface, the fourth surface is displaced towards the third surface. The developed width (DW) from the distal edge of the foot to the distal edge of the web of the stringer may be substantially constant for all cross-sections along a length of the stringer.
    Type: Grant
    Filed: June 24, 2008
    Date of Patent: October 21, 2014
    Assignee: Airbus Operations Limited
    Inventor: John Flood
  • Patent number: 8864075
    Abstract: A composite material elongate structural member, such as a spar, for use in an aerospace structure, comprises a web disposed between upper and lower flanges. The web may include a clockwise twist about an axis parallel to the length L at a first portion towards the wing-root-end of the spar and a counter-twist in the anticlockwise direction at a second portion towards the wing-tip-end of the spar. The geometry of the spar may vary non-linearly along its length (L) so that the developed width of the spar as measured from a distal edge of the upper flange via the web to a distal edge of the lower flange varies linearly with increasing distance along the length (L). The risk of causing, during fabrication of the spar, undesirable creasing, stressing or stretching of composite material layers in a region in which the geometry of the member varies non-linearly may be reduced by means of such an arrangement.
    Type: Grant
    Filed: June 24, 2008
    Date of Patent: October 21, 2014
    Assignee: Airbus Operations Limited
    Inventor: Ian L. Gray
  • Patent number: 8864076
    Abstract: A composite material elongate structural member, such as a spar or stringer, for use in an aerospace structure, comprises a web having an angled portion, for example in the form of a chamfer, curved surface or the like, which joins a foot of the member to the rest of the web. A first surface on the foot is shaped to abut a structure to be stiffened. The foot also has a second surface opposite the first surface. The web has a third surface and a fourth surface at the same layer in the composite material as the first and third surfaces, respectively. On/in the interposed portion there is a fifth surface which joins the first and third surfaces. The geometry of the member may vary along its length (L) so that with increasing distance, the first surface is displaced towards the second surface as the width of the fifth surface decreases.
    Type: Grant
    Filed: June 24, 2008
    Date of Patent: October 21, 2014
    Assignee: Airbus Operations Limited
    Inventor: Eric Stephen Wood
  • Patent number: 8864072
    Abstract: A structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection.
    Type: Grant
    Filed: May 12, 2011
    Date of Patent: October 21, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Jens Telgkamp, Wolfgang Schulze, Thomas Kruse
  • Publication number: 20140299713
    Abstract: An opening portion of a vent member is prevented from being blocked, and thus ventilation is reliably performed. A plurality of opening portions (40A, 40B) are formed in a single vent stringer (20), and thus even in a case where one of the opening portions (40A, 40B) is blocked, ventilation is secured by the other opening portion. At this time, since the opening portions (40A, 40B) are formed in surfaces different from each other in the vent stringer (20), a possibility that both the opening portions (40A, 40B) may be simultaneously blocked is less.
    Type: Application
    Filed: November 27, 2012
    Publication date: October 9, 2014
    Inventors: Ushio Komoda, Hideto Motohashi
  • Patent number: 8851421
    Abstract: The present invention relates to an aerofoil having an erosion resistant leading edge. The aerofoil comprises an aerofoil main body portion and a leading edge portion. The leading edge portion comprises a plurality of functionally distinct parts, including at least; a first part for resisting abrasion of the leading edge portion, and a second part for resisting a bending force applied to the leading edge portion, and located behind the first part.
    Type: Grant
    Filed: August 9, 2010
    Date of Patent: October 7, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Matthew P. Jevons, Kristofer J. Bottome
  • Patent number: 8851422
    Abstract: A unitized composite aircraft wing includes upper and lower composite laminate wing skins that have differing stiffnesses and are bonded to a composite grid structure. The grid structure includes grid spars extending in a span-wise direction, and cross beams extending in a chord-wise direction of the wing. The grid spars include caps bonded to the upper and lower wing skins.
    Type: Grant
    Filed: August 28, 2012
    Date of Patent: October 7, 2014
    Assignee: The Boeing Company
    Inventor: Eugene Dan-Jumbo
  • Patent number: 8844872
    Abstract: A composite structure has first and second sections, and a curved corner joining the first and second sections. The structure includes a stack of fiber-reinforced plies. First and second external plies run from the first section into the second section round an inside and an outside of the corner, respectively. First and second internal plies are sandwiched between the first and second external plies, and run from the first section into the second section round the corner. The first internal fly is dropped off inside the second section. The second internal ply is dropped off inside the first section. The structure has an increased thickness where the first and second internal plies overlap.
    Type: Grant
    Filed: February 21, 2012
    Date of Patent: September 30, 2014
    Assignee: Airbus Operations Limited
    Inventors: Timothy J. Sanderson, Stephen Williams
  • Patent number: 8844873
    Abstract: In an embodiment of the disclosure, there is provided an apparatus to provide a panel stiffening element. The apparatus has an outer braided thermoplastic tube and an inner braided thermoplastic tube disposed within the outer braided thermoplastic tube. The apparatus further has a separation ply layer co-consolidated between the outer braided thermoplastic tube and the inner braided thermoplastic tube. The separation ply layer provides reinforcement and impact damage resistance to the inner braided thermoplastic tube in order to avoid a loss in structural loading capability.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: September 30, 2014
    Assignee: The Boeing Company
    Inventor: Jeffery Lee Marcoe
  • Publication number: 20140284424
    Abstract: The present invention relates to a panel, especially for a component having a box structure in an airplane airfoil, comprising a surface shaped body and grid-like reinforcement bars protruding from the body on one side of the body, and the body and the grid-like reinforcement bars are integral molded. Since the body and the grid-like reinforcement bars of the panel are integral molded, no additional connecting process is required, so that the disconnection phenomenon as happened between the skin and the stiffener or stringer of the prior art would not occur, and the assembly complexity can be decreased.
    Type: Application
    Filed: November 30, 2011
    Publication date: September 25, 2014
    Applicant: AIRBUS SAS
    Inventor: Jun Li