Joints And Connections Patents (Class 244/131)
  • Patent number: 11932398
    Abstract: A horizontal stabilizer assembly includes a stabilizer connector assembly having a center multi-spar box, a first horizontal stabilizer having a first multi-spar box connected to a first side of the center multi-spar box with a plurality of first lug and clevis connections, and a second horizontal stabilizer having a second multi-spar box connected to a second side of the center multi-spar box, opposite the first side, with a plurality of second lug and clevis connections.
    Type: Grant
    Filed: May 3, 2021
    Date of Patent: March 19, 2024
    Assignee: The Boeing Company
    Inventors: Joseph H. Campana, Kevin P. Ryder, William H. Pearson, James R. Harrison
  • Patent number: 11926444
    Abstract: Modular unmanned aerial vehicles (UAVs) are disclosed. A disclosed example UAV includes a fuselage that extends along a longitudinal axis, a wing support frame extending from the fuselage and along a wingspan of the UAV. The wing support frame includes distal ends to support a releasably couplable wing, the releasably couplable wing to extend along the wingspan when coupled to the wing support frame, and a motor boom that extends parallel to the longitudinal axis, the motor boom to support a motor that is oriented to generate lift for the UAV.
    Type: Grant
    Filed: August 27, 2021
    Date of Patent: March 12, 2024
    Assignee: Insitu, Inc.
    Inventors: Bryan G. Munro, Danny R. Nalley, Joel M. Reiter, Harold A. Brown, Ovidiu C. Mihai
  • Patent number: 11919617
    Abstract: Systems and methods are provided for splicing airframe components. One embodiment is a method for assembling an airframe of an aircraft. The method includes forming a first skin of a first circumferential section of fuselage, the first skin including a distal portion comprising a lip and a shoulder, aligning a second skin of a second circumferential section of fuselage with the shoulder such that the lip overlaps the second skin, and affixing the first skin and the second skin together via a circumferential splice.
    Type: Grant
    Filed: September 21, 2021
    Date of Patent: March 5, 2024
    Assignee: The Boeing Company
    Inventors: Patrick J. Macko, Byron James Autry, James R. Kendall, Samuel James Knutson, Brian T. Peters, Michael J. Bailey, Matthew S. Stauffer, Steven Wanthal, Santiago M. Mejia, Sara Murphy
  • Patent number: 11866148
    Abstract: A floor panel for installation in an aircraft includes a plurality of thermoplastic C-shaped stringers, a consolidated thermoplastic deltoid filler, a thermoplastic upper facing sheet, and a thermoplastic lower facing sheet. The stringers are disposed in a parallel arrangement with one another. The deltoid filler is disposed within a longitudinally-extending notch defined by a pair of adjacent stringers. The upper facing sheet covers an upper surface of the stringers and the deltoid filler. The lower facing sheet covers a lower surface of the stringers and the deltoid filler. The stringers, the deltoid filler, and the upper and lower facing sheets are integrally consolidated forming a unitary construction.
    Type: Grant
    Filed: August 31, 2020
    Date of Patent: January 9, 2024
    Assignee: SCIMAX TECHNOLOGIES, LLC
    Inventors: Max Gross, Joseph Bruno
  • Patent number: 11845549
    Abstract: An aircraft wing including a wingbox with an upper cover, a lower cover, a forward spar and a rear spar. A leading edge of a trailing edge panel is attached to the wingbox. A support structure is attached to the wingbox and a connector is movably mounted to the trailing edge panel on a bearing. A first end of a link is attached to the connector, and a second end of the link is attached to the support structure. During assembly, the connector is moved on the bearing from a first position to a second position where the connector is aligned with the first end of the link, then the connector at the second position is attached to the first end of the link. The connector may be moved by a rack-and-pinion mechanism.
    Type: Grant
    Filed: March 24, 2022
    Date of Patent: December 19, 2023
    Assignee: Airbus Operations Limited
    Inventor: William Tulloch
  • Patent number: 11840038
    Abstract: A method of making a wind turbine blade (10) having a shear web (20, 22) bonded between first and second half shells (16, 18) is described. The method involves providing a web locator (40) on an inner surface of a half shell. The web locator has a fixed portion (42) and a spring portion (44) extending from the fixed portion. The spring portion is moveable relative to the fixed portion between compressed and relaxed states.
    Type: Grant
    Filed: December 2, 2019
    Date of Patent: December 12, 2023
    Assignee: Vestas Wind Systems A/S
    Inventor: Anton Bech
  • Patent number: 11827385
    Abstract: Systems, methods, and apparatuses for the direct mount of secondary payload adapters to a truss structure common to a space vehicle payload adapter are disclosed herein. In one or more embodiments, a method for reacting loads into a space vehicle payload adapter comprises reacting, by more than two interstitial rings of the space vehicle payload adapter, the loads created by secondary payloads mounted onto the space vehicle payload adapter, into a truss structure of the space vehicle payload adapter. The method further comprises reacting, by struts of the truss structure, the loads to a forward ring and an aft ring of the space vehicle payload adapter. In one or more embodiments, the reacting of the loads maintains high frequency (e.g., greater than (>) thirty (30) gigahertz (GHz)) modes for the space vehicle payload adapter.
    Type: Grant
    Filed: January 18, 2022
    Date of Patent: November 28, 2023
    Assignee: The Boeing Company
    Inventors: Thomas J. Harleman, Jr., Cary D. Munger, Karsten James
  • Patent number: 11807355
    Abstract: A landing gear system for an aircraft is presented. The landing gear system comprises a composite flex beam having through-thickness stitching and a curvature having a radius greater than 5 inches; and a trunnion connected to the composite flex beam and offset from a neutral surface of the composite flex beam.
    Type: Grant
    Filed: June 28, 2019
    Date of Patent: November 7, 2023
    Assignee: The Boeing Company
    Inventors: Max Urban Kismarton, Kim Linton
  • Patent number: 11807359
    Abstract: A flow body torsion box includes a plurality of ribs, a first spar attached to a first end of the ribs, a second spar attached to a second end of the ribs, a first skin, and a second skin. The first skin and the second skin are arranged at a distance to each other to enclose the ribs and the spars. The first skin and the second skin are attached to the ribs and the spars through tie elements to form a torsion box. The tie elements comprise a first attachment end and a second attachment end between which the tie elements are at least partially curved so as to be resiliently deformable along a first direction along a connection line between the first attachment end and the second attachment end.
    Type: Grant
    Filed: March 21, 2022
    Date of Patent: November 7, 2023
    Assignee: AIRBUS OPERATIONS GMBH
    Inventor: Henrik L├╝ttmann
  • Patent number: 11772772
    Abstract: Several embodiments of buffer zones are provided that are contemplated to be disposed with respect to two or more adjacent elements on an aircraft. The buffer zones adjust for dynamic spacing between the elements to help control different gapping requirements between the elements installed in the aircraft. Embodiments include an aircraft interior panel configuration, an aircraft interior wall panel configuration, an adjustable width aircraft bulkhead, and an aircraft personal service unit.
    Type: Grant
    Filed: April 14, 2021
    Date of Patent: October 3, 2023
    Assignee: BOMBARDIER INC.
    Inventors: Bruce Malek, Stefan Holowka, Nikolas Beaudin
  • Patent number: 11708146
    Abstract: A multispar lifting surface including a multispar torsion box having corner reinforcements, a movable control surface, and an axial rod fitting. The movable control surface includes a movable element, a hinged connection joined to the movable element, and an axial rod joining the hinged connection to the rear spar of the multispar torsion box. The axial rod fitting is configured to join the axial rod and the multispar torsion box; and includes a longitudinal profile resting against the rear spar, and a lug joined to the longitudinal profile at one end and to the axial rod at another end; the lug defining a plane including the longitudinal axis of the axial rod. This multispar lifting surface is able to support sideward forces without any additional structure.
    Type: Grant
    Filed: November 23, 2021
    Date of Patent: July 25, 2023
    Assignee: Airbus Operations S.L.U.
    Inventors: Robert Kobierecki, Alberto Balsa-Gonzalez
  • Patent number: 11554847
    Abstract: Lock apparatus and related methods for use with drones are disclosed. A disclosed drone assembly includes a wing, a keel-beam, an adapter positioned on an end of the keel-beam, and a lock configured to receive the adapter. The lock includes a first lock portion coupled to the wing and a second lock portion rotatable relative to the first lock portion between a first position and a second position. The lock is configured to (a) couple the keel-beam to the wing when the second lock portion is in the second position and (b) decouple the keel-beam from the wing when the second lock portion is in the first position.
    Type: Grant
    Filed: February 28, 2020
    Date of Patent: January 17, 2023
    Assignee: Skyeton USA Inc.
    Inventors: Oleksandr Volodymyrovych Stepura, Mykola Mykolaiovytch Toptun
  • Patent number: 11524762
    Abstract: A fuselage structure splice may include a panel having an edge and a strap connected to the first panel along the panel edge. A strap surface not in contact with the panel tapers toward the panel with distance from the panel edge. A stringer is mounted on the panel and extends away from the edge of the panel and has a flange mounted to the panel. A fitting has a stringer base portion and a strap base portion. The stringer base portion is connected to the stringer flange and extends along a first line extending in a plane normal to the panel edge. The strap base portion of the fitting is mounted on the strap surface and extends along a second line in the plane. The second line is transverse to the first line and the strap base portion of the fitting has a constant thickness along the second line.
    Type: Grant
    Filed: February 21, 2020
    Date of Patent: December 13, 2022
    Assignee: The Boeing Company
    Inventors: Zachary Nathaniel Stoddard, Ronald Leroy McGhee
  • Patent number: 11493081
    Abstract: A connection rod comprising first and second connection elements. The first element comprises a shaft, a first connector at a shaft proximal end and a piercing body at a shaft distal end. The second element comprises a hollow casing with a fluid barrier therein, which, when intact, forms first and second reactive fluid material reservoirs, both within the casing. The second connection element comprises a second proximal end connector and a distal end inlet hole to the second reservoir. The piercing body fits within the casing and the shaft slidably engages the inlet hole such that the first element slides relative to the second element. The piercing body pierces the fluid barrier such that the reactive fluid materials mix between the reservoirs and react to form a reacted solid material restraining the piercing body within the casing to prevent relative sliding between the first and the second connection elements.
    Type: Grant
    Filed: December 23, 2019
    Date of Patent: November 8, 2022
    Assignee: AIRBUS OPERATIONS GMBH
    Inventors: Benjamin Ehring, Florian Lorenz
  • Patent number: 11440635
    Abstract: An aircraft includes a fuselage, a wing extending out from the fuselage, and a joint coupling the wing to the fuselage. The joint includes a first fitting fixed to the fuselage, a second fitting fixed to the wing, a link assembly pivotably coupled to the first fitting and to the second fitting, and a strap coupled to the link assembly at the first fitting and at the second fitting based on the free play clearance as defined by the manufacturing of the link assembly. The link assembly is configured to support the wing during operation of the aircraft and has a free play clearance defined by a manufacturing of the joint falling within a designed dimensional tolerance of the joint. The strap is further configured to bias the link assembly to restrict movement of the link assembly within the free play clearance during load reversal in the joint.
    Type: Grant
    Filed: April 14, 2021
    Date of Patent: September 13, 2022
    Assignee: Gulfstream Aerospace Corporation
    Inventors: Vijay Sekhar Kandavalli, Linga Rajagopal Movva, Kevin Jones
  • Patent number: 11414173
    Abstract: To facilitate the assembly of the wing unit of an aircraft, this wing unit includes two wings each having a lateral wing box extended toward the interior by a center wing box half having an interior end, the two wings being attached to one another using attachment bolts linking the two interior ends of the two center wing box halves, and passing through an intermediate wall connecting two fuselage frame walls.
    Type: Grant
    Filed: December 23, 2019
    Date of Patent: August 16, 2022
    Assignee: Airbus Operations (S.A.S.)
    Inventor: Laurent Gauthie
  • Patent number: 11332230
    Abstract: The method for producing an assembly is a method for producing an assembly equipped with a member to be reinforced (20), a reinforcing member body (41), and a filler (42), wherein the reinforcing member body (41) has a pair of flanges (44) arranged spaced on the surface (20B) of the member to be reinforced (20), a web (45), and a connection portion (46) which connects the flanges (44) and the web (45) and forms a filler space (V) with the surface (20B). The method for producing an assembly includes a step for inserting a filler (42) into the filler space (V), a step for attaching a crack control member (43) to cover the end of the filler (42), a step for joining the flanges (44) and the member to be reinforced (20), and a step for curing at least the member to be reinforced (20).
    Type: Grant
    Filed: November 26, 2018
    Date of Patent: May 17, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Akihito Suzuki, Kenji Murakami, Kana Sakon, Akihisa Okuda, Takayuki Shimizu, Takumi Shinohara, Jun Eto, Yukifumi Toyama, Junichiro Miyagaki, Kenichi Kawakami
  • Patent number: 11254415
    Abstract: An aircraft including a flap support assembly for a flap support. An aircraft includes a fuselage comprising a pressure deck, where at least a portion the pressure deck is substantially horizontal. The aircraft further includes a wing extending from the fuselage, where the wing includes a leading edge and a trailing edge. The wing additionally includes a flap assembly on the trailing edge of the wing, where the flap assembly is configured to move between an extended position and a retracted position. The aircraft further includes a flap support coupled to the flap assembly comprising a plurality of load-bearing connection points, where at least one of the load-bearing connection points is coupled to the pressure deck.
    Type: Grant
    Filed: December 12, 2019
    Date of Patent: February 22, 2022
    Assignee: THE BOEING COMPANY
    Inventors: Kevin Tsai, Kyle Johnson
  • Patent number: 11136107
    Abstract: An aircraft includes an aircraft body including a longitudinal axis and a wing box extending through the aircraft body. The aircraft also includes an attachment assembly coupled to the aircraft body and to the wing box. The attachment assembly includes a first attachment member coupled to the aircraft body and a second attachment member coupled to the wing box. The second attachment member is configured to couple to the first attachment member. The attachment assembly also includes a plurality of fasteners extending through the first attachment member and the second attachment member such that the plurality of fasteners are loaded in shear during a wing loading condition.
    Type: Grant
    Filed: October 5, 2018
    Date of Patent: October 5, 2021
    Assignee: THE BOEING COMPANY
    Inventors: Kenneth D. Cominsky, Brent Edward Beneke
  • Patent number: 11052941
    Abstract: A rod-end front suspension is provided for an off-road vehicle. The rod-end front suspension comprises a spindle assembly that is pivotally coupled with an upper suspension arm by way of a first rod-end joint and pivotally coupled with a lower suspension arm by way of a second rod-end joint. A steering rod-end joint coupled with the spindle assembly pivotally receives a steering rod. An axle assembly coupled with the spindle assembly conducts torque from a transaxle to a wheel coupled with the spindle assembly. Each of the first and second rod-end joints comprises a ball rotatably retained within a casing. The ball is fastened within a recess between parallel prongs extending from the spindle assembly. A threaded shank extending from the casing is threadably fixated with the suspension arm, such that the spindle assembly may be moved with respect to the casing and the suspension arm.
    Type: Grant
    Filed: May 2, 2019
    Date of Patent: July 6, 2021
    Inventor: Robby Gordon
  • 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: 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: 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: 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