Joints And Connections Patents (Class 244/131)
  • Patent number: 10894389
    Abstract: Described is laminate of a stack of mutually bonded adhesive layers and metal layers. An outer metal layer has spliced metal sheets having overlapping end parts and/or abutting metal sheet edges extending in a first and a different second planar direction of the laminate to define first and second splice lines. Connected to an outer surface are first and second splice straps covering the first and second splice lines. A lateral edge part of each splice strap has a lower bending stiffness than the bending stiffness of the outer metal layer sheets, the edge part being defined as extending from an outer lateral edge of a splice strap over a lateral distance of at least 5 times the edge part average thickness. The laminate may be used for making large structural components, such as a wing or fuselage of an aircraft.
    Type: Grant
    Filed: November 23, 2017
    Date of Patent: January 19, 2021
    Assignee: GTM-Advanced Products B.V.
    Inventors: Jan Willem Gunnink, Simon Gunnink, Johannes Jan Homan
  • Patent number: 10875656
    Abstract: In one embodiment of the present disclosure, there is provided an aircraft having a bi-folding cowl for providing full access to equipment without completely removing the cowl. The bi-folding cowl has an upper portion and a lower portion mechanically connected along the adjacent edges, where the upper and lower portions fold so that the inner surfaces face each other when opened. In another embodiment, the bi-folding cowl has at least three maintenance positions, including partially-opened, fully-opened, and fully-opened, lying flat on the surface of the aircraft.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: December 29, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Brent Scannell, Thomas Mast
  • Patent number: 10792893
    Abstract: Described is a laminate, including a stack of mutually bonded adhesive layers and metal sheets. The laminate includes abutting and/or overlapping metal sheet edges that extend along a length direction within a splicing region. A splice strap is connected to the laminate at an outer surface of the laminate across said splicing region. The splice strap includes one layer of fiber-reinforced adhesive or of metal sheet, or stacked layers of fiber-reinforced adhesive and/or metal sheets. A widest splice strap layer is connected to the laminate over a transverse distance of at least 5 times the widest strap layer thickness, and the widest strap layer has a lower bending stiffness than the bending stiffness of one of the spliced metal sheets.
    Type: Grant
    Filed: September 15, 2016
    Date of Patent: October 6, 2020
    Assignee: GTM-Advanced Products B.V.
    Inventors: Jan Willem Gunnink, Simon Gunnink
  • Patent number: 10787241
    Abstract: An aircraft joint between overlapping first and second components includes a fastener assembly. The fastener assembly includes a threaded fastener and a boss having an outer diameter and a threaded internal bore. The boss is fixedly attached to the second component at the overlap region. The first component has a through hole having a diameter sized to receive the outer diameter of the boss. The boss is received in the through hole from a first side of the first component. The fastener extends through the through hole from a second side of the first component opposite the first side. The fastener is threadably received in the internal bore of the boss and reacts against the second side of the first component to fasten the first component to the second component.
    Type: Grant
    Filed: May 11, 2017
    Date of Patent: September 29, 2020
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Vernon Holmes, Rodney Evans, Stefanos Kosteletos
  • Patent number: 10772246
    Abstract: The present invention relates to the use of additive manufacturing as applied to radiation shielding. In particular, additive manufacturing formulations are described which provide shielding for neutron and photon radiation and which can extend the useful operation life of remote sensing devices utilized to conduct surveillance and inspection work where such radiation fields are present.
    Type: Grant
    Filed: November 13, 2018
    Date of Patent: September 8, 2020
    Assignee: SOUTHWEST RESEARCH INSTITUTE
    Inventors: Daniel P. Speaker, Albert J. Parvin, Jr., Nathan B. Hall
  • Patent number: 10696383
    Abstract: A flight device includes a device body with a surface, a plurality of arm structures disposed in the device body and a plurality of rotor modules disposed to the arm structures respectively. Each arm structure includes a fixing base, a second screw element, a connecting unit, a rod body and a position-limiting element. The fixing base is disposed in the device body and includes a first screw element having a first screw part. The second screw element has a second screw part matched with the first screw part. The connecting unit drills through the second screw element. The connecting unit is locked to the fixing base by screwing the first and second screw parts with each other. The rod body drills through the connecting unit. The position-limiting element is disposed between the second screw element and the connecting unit. The position-limiting element abuts against the second screw element.
    Type: Grant
    Filed: August 10, 2017
    Date of Patent: June 30, 2020
    Assignee: Coretronic Intelligent Robotics Corporation
    Inventors: Chi-Tong Hsieh, Kuan-Chou Ko, Ying-Chieh Chen, Hsu-Chih Cheng
  • Patent number: 10618627
    Abstract: An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.
    Type: Grant
    Filed: February 13, 2018
    Date of Patent: April 14, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Levi Charles Hefner, Danielle Lynn Moore, Dakota Charles Easley
  • Patent number: 10589863
    Abstract: Apparatus and methods to attach an object to an overhead section of a cabin of an aircraft. An example apparatus includes a bracket to be positioned between rails in a cabin of an aircraft. The bracket includes edges having first attachment points to align with second attachment points of each of the rails. The bracket is positionable along a length of the rails by aligning the first attachment points of the bracket with a portion of the second attachment points of the rails. The bracket also includes flanges disposed between the edges. The flanges have respective third attachment points and fourth attachment points aligned to receive fasteners for hanging a device used in the cabin of the aircraft.
    Type: Grant
    Filed: May 8, 2017
    Date of Patent: March 17, 2020
    Assignee: The Boeing Company
    Inventors: William Maclay, Peter Zarkowskyj
  • Patent number: 10513324
    Abstract: In one aspect, there is a rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The plurality of skin flanges can be attached to the top and the bottom of the rib web such that the second portion of the base member and the vertical member are attached to the rib web.
    Type: Grant
    Filed: February 3, 2017
    Date of Patent: December 24, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: David G. Carlson, John R. McCullough, Paul K. Oldroyd, Carl A. May, James E. Kooiman
  • Patent number: 10508005
    Abstract: Provided herein is an assembly for carrying or supporting a load. The assembly comprises a plurality of members connectable in an assembled arrangement for carrying or supporting the load. Each member comprises a first end and a second end, at least one of the first end and the second end has a pair of connecting members comprising two lugs that each has defined therein two holes. The lugs are configured for alignment with a corresponding pair of lugs formed on another member in the assembly. Fasteners extend through the holes formed in the lugs when the holes are aligned. Further provided are members for use in the assembly and connector elements for attaching two or more members in the assembly.
    Type: Grant
    Filed: August 23, 2017
    Date of Patent: December 17, 2019
    Inventor: John Rene Spronken
  • Patent number: 10493677
    Abstract: Overmolded inserts and methods for forming the same The present disclosure is directed to overmolded inserts (100) with reduced internal residual stress and corresponding methods for forming the overmolded inserts. The overmolded inserts have a polymer housing; metal or metal allow tapered insert (104, 302) and a compression element (106, 304) disposed between the housing and the distal end of the tapered insert. During formation, the tapered insert and compression element are placed within a mold. The polymer housing material is heated and filled into the mold. As the polymer housing cools, the compression element is compressed between the polymer housing and the tapered insert. The overmolded inserts formed have reduced internal residual stress relative to a corresponding insert formed from non-tapered insert.
    Type: Grant
    Filed: November 17, 2015
    Date of Patent: December 3, 2019
    Assignee: SOLVAY SPECIALTY POLYMERS USA, LLC
    Inventors: Philippe Martin, Michel Magdelyns
  • Patent number: 10155594
    Abstract: The invention includes an aircraft engine mounting system for mounting an aircraft engine to an aircraft. The mounting system includes a yoke member having a first end and a second end, with an aircraft attachment between the first end and the second end, the aircraft attachment for interfacing the yoke member with the aircraft, the yoke member having a yoke member length (YL) from the first end to the second end. The mounting system preferably includes a first engine mount, the yoke member first end contained by the first engine mount, with the first engine mount having first engine mount housing grounded to the aircraft engine. The mounting system preferably includes a second engine mount, the yoke member second end contained by the second engine mount, with the second engine mount having a second engine mount housing grounded to the aircraft engine.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: December 18, 2018
    Assignee: LORD Corporation
    Inventors: Gerald P. Whiteford, Daniel Zameroski
  • Patent number: 10144516
    Abstract: The invention relates to a floor attachment assembly for mechanically connecting two aircraft seats to a floor structure of an aircraft, which assembly comprises four attachment points. The floor attachment assembly can be attached to the floor structure by means of one attachment element in each case at the four attachment points. The floor attachment assembly comprises two adapter plates, the two adapter plates being interconnected by means of a connection element. The mechanical connection between at least one of the adapter plates and at least one of the attachment elements is movable along at least one axis. Furthermore, the invention relates to a corresponding aircraft seat.
    Type: Grant
    Filed: September 26, 2014
    Date of Patent: December 4, 2018
    Assignee: LUFTHANSA TECHNIK AG
    Inventor: Oliver Thomaschewski
  • Patent number: 10122080
    Abstract: The invention provides a connection head (40) for using with a supply cable for supplying power to a device, which device is within a housing. A first end (41) of the connection head is for mounting outside the housing of the device. A second end (43) of the connection head is for mounting inside the housing of the device. A closed loop antenna has at least one coil and a pair of feed lines, wherein the feed lines extend from the first end (41) to the second end (43), and the at least one coil is located within the first end (41). The connection head of the supply cable provides protection for an antenna and enables the antenna to be mounted outside the housing.
    Type: Grant
    Filed: September 30, 2015
    Date of Patent: November 6, 2018
    Assignee: PHILIPS LIGHTING HOLDING B.V.
    Inventors: Bing Lai, Yunfeng Li
  • Patent number: 10112717
    Abstract: An aircraft storage bin that includes an upper housing with first and second side panels, a bucket that includes a bottom and first and second sides, a first clevis assembly that includes a first inner plate and a first outer plate that extend between the first side panel and the first side wall, and a second clevis assembly that includes a second inner plate and a second outer plate that extend between the second side panel and the second side wall. The first inner plate includes a first outer protrusion and the first outer plate includes first inner protrusion that cooperate to form a first pivot axle. The second inner plate includes a second outer protrusion and the second outer plate includes second inner protrusion that cooperate to form a second pivot axle.
    Type: Grant
    Filed: October 6, 2017
    Date of Patent: October 30, 2018
    Assignee: C&D ZODIAC, INC.
    Inventor: Scott Savian
  • Patent number: 10017239
    Abstract: A dynamic conformal aerodynamic seal that bridges the gap between an aircraft control surface and an aircraft wing, stabilizer or tail. The seal has a first edge and a second edge, where the first edge of the seal is rigidly coupled to the aircraft wing, stabilizer or tail and the second edge of the seal is slidably coupled to the control surface by magnetic coupling so that when the control surface pivots relative to the aircraft wing, stabilizer or tail, the second edge of the seal slides along the control surface.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: July 10, 2018
    Assignee: Northrop Grumman Systems Corporation
    Inventors: Matthew A. Neal, Charles R. Smith
  • Patent number: 10005539
    Abstract: The invention relates to an interior trim part (2, 3, 4, 5, 6) for the planar installation with similar interior trim parts for producing a wall covering inside an aircraft cell, wherein the interior trim part (2, 3, 4, 5, 6) can be rigidly connected to the aircraft cell. The interior trim part has a support structure (20, 21, 22, 23), wherein at least one holding position (9) is provided, which is designed to bear a load in the interior.
    Type: Grant
    Filed: November 20, 2014
    Date of Patent: June 26, 2018
    Assignee: Helikopter Air Transport GmbH
    Inventors: Martin Weger, Wolfgang Burger
  • Patent number: 10005543
    Abstract: An actuator for hinging a first element to a second element about a first pivot axis (A1), the actuator comprising a motor-drive device, a first mounting plate (4) connected to a body (2) of the motor-drive device, a second mounting plate (5) connected to the second element, the second mounting plate being mounted in the first mounting plate in order to pivot about the first axis, and a bush (6) mounted in the second mounting plate to pivot about a second axis (A2) perpendicular to the first axis. The motor-drive device has an outlet shaft (3) pivotable about a third axis (A3) perpendicular to the first axis and intersecting the first axis, and it is extended by a pin (7) that is pivotally received in the bush and that has a central axis (A4) intersecting the first axis and the third axis, and forming an acute angle with the third axis. An aircraft guidance assembly including such an actuator.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: June 26, 2018
    Assignee: Safran Electronics & Defense
    Inventors: Oleg Gomolko, Etienne Merlet
  • Patent number: 10005540
    Abstract: A method for wing-to-fuselage integration is disclosed. The method includes attaching a fitting to a wing box assembly of an aircraft at an early stage of integration and then attaching the fitting to a stub beam attached to a fuselage panel of the aircraft at a later stage of integration. The fitting eliminates the need to attach the stub beam directly to the wing box assembly.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: June 26, 2018
    Assignee: The Boeing Company
    Inventors: Charles B. Lockin, Marcus A. Erickson, Oladele A. Adedeji, Kevin R. Puzey
  • Patent number: 9868508
    Abstract: The invention relates to a rib foot having a blade formed by first and second blade parts that are connected by a bite. The rib foot has a first base part that is connected to the first blade part by a first corner and a second base part that is connected to the second blade part by a second corner. The rib foot also has a first flange that is connected to and extends away from the first base part and a second flange that is connected to and extends away from the second base part. The blade and base parts are formed from a composite material that includes reinforcement fibers embedded in a matrix. At least some of the reinforcement fibers run continuously from the first base part into the second base part via the first corner, the blade and the second corner.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: January 16, 2018
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventor: Oliver Marks
  • Patent number: 9862477
    Abstract: A structure having a panel, a stringer, and a rib is disclosed. The stringer includes a stringer flange that is joined to the panel and a stringer web that extends away from the stringer flange. The rib includes a rib web that has first and second faces and a rib foot that has a first rib foot flange that is joined to the stringer web, a second rib foot flange that is joined to the panel and a rib foot web that is joined to the first face of the rib web. The first rib foot flange is connected to the rib foot web by a first corner that includes at least one layer which runs continuously from the first rib foot flange into the rib foot web via the first corner. The second rib foot flange is connected to the rib foot web by a second corner that includes at least one layer which runs continuously from the second rib foot flange into the rib foot web via the second corner.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: January 9, 2018
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Oliver Marks, Steven Evans
  • Patent number: 9808988
    Abstract: A stringer and corresponding method is provided having a runout design that softens the stringer. According to one aspect, the stringer includes a base flange, a web, and a noodle. The noodle includes a unidirectional fiber top portion and a stacked laminate bottom portion coupled to the top portion. The bottom portion includes a number of stacks, each stack including three plies having three corresponding fiber orientations within an acreage region of the stringer. In a transition region of the stringer, the stacked laminate bottom portion includes a number of stacks, each stack including the first and third plies of the acreage region. According to another aspect, the base flange is softened by dropping plies within the transition region. Yet another aspect includes trimming the web down to the noodle, while trimming through the noodle according to a trim radius to a height proximate the base flange.
    Type: Grant
    Filed: November 30, 2015
    Date of Patent: November 7, 2017
    Assignee: The Boeing Company
    Inventors: Hyukbong Kwon, Douglas A. Frisch, Arman Rowhani
  • Patent number: 9771140
    Abstract: The invention provides an integrated aircraft structure, such as a fuselage, with reinforcing elements in areas of the structure that need them because they have openings or are subjected to high loads. The structure comprises a skin, a plurality of stringers and a plurality of frames with mouseholes for the passage of stringers at their crossing zones. The reinforcing elements are configured with a suitable shape to be superimposed to the stringers in said areas. A manufacturing processes of said integrated aircraft structure is also provided.
    Type: Grant
    Filed: December 25, 2013
    Date of Patent: September 26, 2017
    Assignee: Airbus Operations S.L.
    Inventors: Elena Arevalo Rodriguez, Estelle Baligand
  • Patent number: 9764816
    Abstract: An aircraft structure part comprising a floor structure, a hull structure, and a connecting element. The connecting element comprises a rod attached, at its first end, to one of the hull and the floor; an attachment element, attached to the other of the hull and the floor, and provided with an opening in which the second end of the rod is slidably mounted; and an endstop attached to the rod so as to engage with the attachment element, to limit the sliding amplitude of the rod in the opening. When the connection between the floor and the hull is loaded in tension, the endstop makes it possible to comply with the standards for withstanding acceleration towards the aircraft front. When the connection is loaded in compression, the rod slides freely in the opening, which limits the constraints of withstanding compressive stresses, reducing the weight of the connecting element.
    Type: Grant
    Filed: May 28, 2015
    Date of Patent: September 19, 2017
    Assignee: Airbus Operations (SAS)
    Inventors: Francis Dazet, Jerome Antypas, Laurent Bel, Philippe Delorme, Raphael Brisbart
  • Patent number: 9764849
    Abstract: A structural system for accommodating the thermal expansion of a nacelle lip skin and supporting structure has a lip skin and a first angle element attached to the lip skin. The first angle element has a free edge that is scalloped to accommodate thermal stresses. A bulkhead is attached to the first angle element.
    Type: Grant
    Filed: September 18, 2014
    Date of Patent: September 19, 2017
    Assignee: The Boeing Company
    Inventor: Richard L. Stark
  • Patent number: 9718488
    Abstract: A carriage having a frame, where the frame is foldable between a use position and a storage position. The frame includes an attachment point for a plurality of frame components and a pivot lock for retaining the frame in the use position. The pivot lock is operated by rotating a portion of the frame of the carriage to unlock the pivot lock, permitting the carriage to be folded to the storage position.
    Type: Grant
    Filed: October 31, 2014
    Date of Patent: August 1, 2017
    Assignee: Thule Canada Inc.
    Inventors: Paramjit Singh, Wesley Justin Fleming, Miao Kaihua
  • Patent number: 9698452
    Abstract: A battery pack including a plurality of battery arrays, each battery array including unit batteries that each have a terminal, the plurality of battery arrays being stacked in a first direction; an insulator on at least one side of the battery arrays, terminals of the unit batteries being on the one side; and a sensing bar on the insulator, wherein the insulator includes at least one opening therein, at least one terminal being exposed through the at least one opening, and the sensing bar is electrically connected to the at least one terminal exposed through the at least one opening to sense a state of the battery array.
    Type: Grant
    Filed: February 9, 2015
    Date of Patent: July 4, 2017
    Assignee: SAMSUNG SDI CO., LTD.
    Inventors: Man-Sik Cho, Kum-Yul Hwang
  • Patent number: 9611029
    Abstract: A floor beam assembly, system, and method for supporting floor beams within a structure are provided. According to one embodiment, a floor beam assembly for installing a floor beam within a structure is provided. The assembly includes at least one floor beam, wherein at least a portion of each floor beam comprises a composite material. The assembly also includes at least one support bracket attached to a structure, wherein each support bracket is configured to support at least a portion of a floor beam thereon. In addition, the assembly includes at least one conductive element extending from the at least one support bracket and configured for electrically communicating with the at least one support bracket.
    Type: Grant
    Filed: October 11, 2006
    Date of Patent: April 4, 2017
    Assignee: The Boeing Company
    Inventors: Jeffrey H. Wood, Charles R. Saff
  • Patent number: 9593699
    Abstract: A fastener device provided with at least one movable stud and a stationary stud, the movable stud including first magnetization means co-operating with second magnetization means of the stationary stud. One magnetization means is carried by a ball joint, each magnetization means being carried by movement means in order to move the first magnetization means in translation in a plane and to move the second magnetization means in translation along a longitudinal axis that is substantially orthogonal to the plane from an engagement position to a disengagement position in reversible manner, the magnetization means being strongly magnetically attracted to each other when they are facing and each in the engagement position and being magnetically attracted only slightly or not at all when at least one magnetization means is in the disengagement position.
    Type: Grant
    Filed: May 5, 2015
    Date of Patent: March 14, 2017
    Assignee: AIRBUS HELICOPTERS
    Inventors: Jean-Michel Giacalone, Clement Peyrusaubes, Marc Denavaux
  • Patent number: 9586667
    Abstract: A splice assembly may include a first splice bracket including first longitudinal axis, a first connecting member, and a first mating member extending from the first connecting member along the first longitudinal axis, the first mating member including a first mating surface disposed as a non-zero first angle relative to the first longitudinal axis. The disclosed slice assembly may further include a second splice bracket including second longitudinal axis, a second connecting member, and a second mating member extending from the second connecting member along the second longitudinal axis, the second mating member including a second mating surface disposed as a non-zero second angle relative to the second longitudinal axis. The first mating surface and the second mating surface are complementary. Surface contact between the first mating surface and the second mating surface defines a fastening location for connecting the first splice bracket and the second splice bracket.
    Type: Grant
    Filed: December 2, 2014
    Date of Patent: March 7, 2017
    Assignee: The Boeing Company
    Inventor: Andrew C. Reeves
  • Patent number: 9537443
    Abstract: To obtain a reinforcing frame capable of securing sufficient reinforcing strength and adhesive strength while suppressing a manufacturing cost by omitting a rim-like frame. A reinforcing frame is adhered to a rear surface, which is a non-light receiving surface of a solar battery panel, and includes a cylindrical portion that has a cylindrical shape along a longitudinal direction of the reinforcing frame and on which an adhesive surface for adhering to the solar battery panel is formed, and protruding portions that protrude from end portions along a longitudinal direction of the adhesive surface and that are substantially parallel to the adhesive surface.
    Type: Grant
    Filed: April 22, 2013
    Date of Patent: January 3, 2017
    Assignee: MITSUBISHI ELECTRIC CORPORATION
    Inventors: Taisuke Sueda, Daisuke Echizenya, Hiroo Sakamoto, Atsushi Michimori
  • Patent number: 9517832
    Abstract: An aircraft wing assembly including: a wing having a wing box structure with an upper wing cover and a lower wing cover, and a wing tip device attached to the outboard end of the wing, the wing tip device including an upper cover and a lower cover, wherein a gap between opposing edges of the wing tip device lower cover and the lower wing cover is at least 5 mm, a seal assembly aerodynamically seals the gap, wherein the seal assembly includes a bridging component on an interior side of the gap, and a seal which fills the gap and is supported by the bridging component.
    Type: Grant
    Filed: April 23, 2012
    Date of Patent: December 13, 2016
    Assignee: Airbus Operations Limited
    Inventors: Huw Davies, Nigel McKenna
  • Patent number: 9499252
    Abstract: Illustrative embodiments may provide for an apparatus and method of controlling the folding of a wing. The apparatus may include a sensor, an actuator, and a wing fold controller. The method may include receiving a status of at least one of an aircraft and a wing fold system of the aircraft by the wing fold controller of the wing fold system. The method may also include receiving an automated command by the wing fold controller in response to receiving the status. The method may also include operating the wing fold system by the wing fold controller based on the automated command and the status. The method may also include transitioning a wingtip of a wing of the aircraft to one of a flight position and an on-ground position by an actuator of the wing fold system in response to commands from the wing fold controller.
    Type: Grant
    Filed: July 18, 2014
    Date of Patent: November 22, 2016
    Assignee: THE BOEING COMPANY
    Inventors: Matthew August Lassen, Mark Steven Good
  • Patent number: 9481467
    Abstract: A modular floor track adapter system including a plurality of adapter plates laterally sized to span existing aircraft floor beams, each of the plurality of adapter plates shaped to interlock with an adjacent adapter plate in a side-by-side arrangement and including a series of holes for attaching seat track crown sections and panel attachment tabs for securing an aircraft floor panel thereto.
    Type: Grant
    Filed: October 21, 2014
    Date of Patent: November 1, 2016
    Assignee: B/E Aerospace, Inc.
    Inventor: Michael L. Oleson
  • Patent number: 9434463
    Abstract: A structural component, in particular for an aircraft, having a skin and at least one stiffening element for stiffening the skin. Opposite to a run-out of the stiffening element at least one supporting element is positioned. The at least one supporting element defines a supporting area that is opened to the stiffening element run-out in longitudinal direction of the stiffening element run-out and that is closed in transversal direction of the stiffening element run-out.
    Type: Grant
    Filed: September 9, 2013
    Date of Patent: September 6, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Matteo Borghini-Lilli, Marc'Antonio Bentivoglio, Henrik-Bro Henriksen, Ruslan Zagreba
  • Patent number: 9427772
    Abstract: The present invention provides a fireproof bulkhead, having a highly porous structure with an intumescent coating, the highly porous structure being formed as a reticulated foam or as a highly porous pimple or nub structure.
    Type: Grant
    Filed: January 24, 2014
    Date of Patent: August 30, 2016
    Assignee: Airbus Operations GmbH
    Inventor: Berend Schoke
  • Patent number: 9415575
    Abstract: A laminate material may include a first flexible layer, and a self-healing composite layer in contact with the first flexible layer. The composite layer includes an elastomer matrix, a plurality of first capsules including a polymerizer, and a corresponding activator for the polymerizer. The laminate material may self-heal when subjected to a puncture or a tear.
    Type: Grant
    Filed: January 26, 2009
    Date of Patent: August 16, 2016
    Assignee: The Board of Trustees of the University of Illinois
    Inventors: Brett A. Beiermann, Michael W. Keller, Scott R. White, Nancy R. Sottos
  • Patent number: 9346121
    Abstract: A method for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft, said method comprising the following method steps: positioning the two components relative to one another in such a way that a connection region is formed between the two components; friction stir welding the two components by means of a friction stir welding tool which penetrates the connection region in order to produce a weld which permeates the connection region with the formation of an unpenetrated weld edge portion of the connection region; and introducing internal compressive stresses, at least in the weld edge portion of the connection region. Further a device for the friction stir welding of two components, in particular of two shell components of a fuselage structure of an aircraft and spacecraft is provided.
    Type: Grant
    Filed: February 27, 2015
    Date of Patent: May 24, 2016
    Assignee: Airbus Operations GmbH
    Inventors: Domenico Furfari, Marco Pacchione
  • Patent number: 9254927
    Abstract: The present invention provides an aircraft assembly with a fixed structure and a high-lift device. The fixed structure has a spar, a forward part which provides a foremost edge of an aircraft wing, and a lower part which provides a lower surface of the aircraft wing. A high-lift device is downwardly movable relative to the fixed structure from a stowed configuration to a deployed configuration. The high-lift device has a forward part which provides a foremost edge of the aircraft wing and a lower part which provides a lower surface of the aircraft wing. Downward movement of the high-lift device causes progressive opening of a lateral gap between the lower part of the high-lift device and the lower part of the fixed structure. A retractable infill panel is arranged to progressively extend from a retracted configuration to an extended configuration to fill the lateral gap.
    Type: Grant
    Filed: November 20, 2013
    Date of Patent: February 9, 2016
    Inventors: Mark Hodkisson, James Wilson, Samuel Evans
  • Patent number: 9187166
    Abstract: An elongated supporting pillar for a high-strength structural component is designed to absorb bending forces that act transversely to a longitudinal direction of extension of the supporting pillar. The supporting pillar comprises a wall which at least partially encloses an elongated cavity of the supporting pillar. A reinforcement structure is arranged within the cavity and transversely to the direction of longitudinal extension in such a manner that the reinforcement structure can absorb at least some of the bending forces. The reinforcement structure is designed integrally with the wall, wherein both the wall and the reinforcement structure comprise a meltable material. The supporting pillar has a conical shape, and wherein a first end of the supporting pillar is wider than a second end of the supporting pillar.
    Type: Grant
    Filed: January 9, 2015
    Date of Patent: November 17, 2015
    Assignee: Airbus Operations GmbH
    Inventors: Christoph Klahn, Rüdy Gysemberg, Olaf Rehme
  • Patent number: 9150302
    Abstract: A pinned lug joint comprising: a first part comprising two first lugs projecting from a bridge which extends between them; a second part pivotally coupled to the first part, the second part comprising a second lug positioned between the first lugs; and a sealing member, the sealing member being mounted to the first lugs and extending between them to seal an air gap between the second lug and the bridge at least when the second part is in a first position. The pinned lug joint may be used to attach a panel assembly to part of an aircraft.
    Type: Grant
    Filed: August 10, 2010
    Date of Patent: October 6, 2015
    Assignee: Airbus Operations Limited
    Inventors: Eric Wildman, Mohamed Saffique AdbulKader
  • Patent number: 9038951
    Abstract: A coupling assembly for joining a first component to a second component, the assembly comprising a shaft for connecting to a first component, and a bracket including a mounting plate for connecting to a second component. The bracket has a bracket arm extending from the mounting plate, and a head having a through-bore on the bracket arm. The shaft is received in the through-bore. A setting device acts between the head and the shaft for setting of the position of the shaft with respect to the head in the axial direction of the shaft. The assembly further includes one or more spherical bearing surfaces, which permit self-alignment of the setting device to accommodate tilting of the shaft with respect to the head about a central point in two orthogonal directions. Also, a joint comprising a first component joined to a second component by one or more of the coupling assemblies. Also, a method of forming a joint using one or more of the coupling assemblies.
    Type: Grant
    Filed: March 31, 2010
    Date of Patent: May 26, 2015
    Assignee: Airbus Operations Limited
    Inventors: Steven Coulter, Paul Hadley, Geraint Hopkins
  • Patent number: 9038952
    Abstract: According to one embodiment, a windshield attachment device for coupling a windshield to a body includes a fastener portion, a bolt, and an elastomeric load isolator. The fastener portion has an opening therethrough. The bolt is configured to extend through the opening of the fastener portion and couple the fastener portion to the body. The elastomeric load isolator surrounds at least a portion of the fastener portion and separating the fastener portion from the windshield.
    Type: Grant
    Filed: January 18, 2013
    Date of Patent: May 26, 2015
    Assignee: Bell Helicopter Textron Inc.
    Inventors: William A. Amante, Carl A. May
  • Patent number: 9038953
    Abstract: The invention provides an arrangement and methods for thermally insulating aircraft, particularly but not exclusively for when the aircraft is operating in extremely hot or cold conditions, and describes an aircraft skin construction including a foam-stiffened CFC sandwich panel forming part of the aircraft outer skin mounted to an underlying load bearing aircraft structure, wherein the panel at the mounting to the structure includes two outer layers of CFC material with an inner layer of foam material sandwiched therebetween.
    Type: Grant
    Filed: July 19, 2011
    Date of Patent: May 26, 2015
    Assignee: BAE SYSTEMS PLC
    Inventors: Matthew Lang, Ruben James Joseph Fernandes
  • Patent number: 9019719
    Abstract: A module in the form of a pallet or a closed container includes a grouping together of the electrical devices in an avionics bay, in which the electrical devices are interconnected and attached so as to facilitate the mounting and thus limit the time it takes to mount the electrical devices in the avionics bay.
    Type: Grant
    Filed: September 20, 2012
    Date of Patent: April 28, 2015
    Assignee: Airbus Operations SAS
    Inventors: Marc Tomasi, Matthieu De Kergommeaux, Laurent Bertandeau, Christian Banis
  • Patent number: 9010684
    Abstract: A system and method that allow inspection of hollow structures made of composite material, such as an integrally stiffened wing box of an aircraft. A wing box comprises top and bottom skins connected by a plurality of spaced spars. The system employs a plurality of scanners for inspecting different portions of each spar. The system uses dynamically controlled magnetic coupling to connect an external drive tractor to computer-controlled scanners that carry respective sensors, e.g., linear ultrasonic transducer arrays. A system operator can control the various components by means of a graphical user interface comprising multiple interaction regions that represent the individual scanner motion paths and are associated with respective motion script files.
    Type: Grant
    Filed: June 27, 2012
    Date of Patent: April 21, 2015
    Assignee: The Boeing Company
    Inventors: William P. Motzer, James C. Kennedy, Michael C. Hutchinson, Martin L. Freet, Ronald E. VonWahlde, Steven Ray Walton, Jeffry J. Garvey, Scott W. Lea, James J. Troy, Daniel James Wright, Hien T. Bui, Michael Joseph Duncan, Mark L. Little, William Joseph Tapia, Barry A. Fetzer, Richard C. Krotzer
  • Patent number: 9010688
    Abstract: Apparatus and methods provide for a structural joint utilizing overlapping blade stringers coupled to opposing sides of a continuous skin. According to embodiments described herein, a structural joint includes a number of inside blade stringers associated with a first component are coupled to an inside surface of a continuous skin. A number of outside blade stringers associated with a second component may be coupled to an outside surface of the continuous skin. The inside blade stringers and outside blade stringers may overlap on opposing surfaces of the continuous skin.
    Type: Grant
    Filed: February 7, 2012
    Date of Patent: April 21, 2015
    Assignee: The Boeing Company
    Inventor: Moushumi Shome
  • Publication number: 20150102169
    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: Application
    Filed: October 11, 2013
    Publication date: April 16, 2015
    Applicant: The Boeing Company
    Inventors: Steven Paul Walker, Joanna Mara Sergiane Veit, Isaac G. Cambronero, JR., James Donald Davis, Michael D. Pagliarini
  • Publication number: 20150102170
    Abstract: Self-aligning fitting assemblies and systems and methods including the same are disclosed herein. The self-aligning fitting assemblies include a barrel-side fitting that includes a plurality of barrel-side attachment holes and a floor-side fitting that includes a plurality of floor-side attachment holes. The self-aligning fitting assemblies also include an alignment pin recess and a fitting alignment recess. The methods include translating a floor grid relative to a fuselage barrel, operatively aligning a plurality of alignment pin recesses with a corresponding plurality of fitting alignment recesses, and locating a plurality of alignment pins within the plurality of alignment pin recesses such that each of the plurality of alignment pins extends through a respective one of the plurality of fitting alignment recesses. The methods also include lowering the floor grid relative to the fuselage barrel and installing a plurality of fasteners.
    Type: Application
    Filed: April 24, 2014
    Publication date: April 16, 2015
    Applicant: The Boeing Company
    Inventor: Tibor A. Koncz
  • Patent number: 9006119
    Abstract: Disclosed is to a composite material, a structural element comprised of the composite material, an airplane wing spar and their methods of production. Some embodiments of the present invention include composite materials comprised of multiple layers of arrays of metallic bodies separated by layers of non-metallic material, wherein the orientation of metallic bodies in some metallic layers is structurally complementing to the orientation of metallic layers in adjacent metallic layers. Other embodiments of the present invention include structural elements, such as an airplane wing spar, comprised of the composite material.
    Type: Grant
    Filed: July 11, 2010
    Date of Patent: April 14, 2015
    Assignee: A.L.D. Advanced Logistics Development Ltd.
    Inventors: Zigmund Bluvband, Viktor Shkatov