Joints And Connections Patents (Class 244/131)
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Patent number: 9537443Abstract: 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: GrantFiled: April 22, 2013Date of Patent: January 3, 2017Assignee: MITSUBISHI ELECTRIC CORPORATIONInventors: Taisuke Sueda, Daisuke Echizenya, Hiroo Sakamoto, Atsushi Michimori
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Patent number: 9517832Abstract: 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: GrantFiled: April 23, 2012Date of Patent: December 13, 2016Assignee: Airbus Operations LimitedInventors: Huw Davies, Nigel McKenna
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Patent number: 9499252Abstract: 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: GrantFiled: July 18, 2014Date of Patent: November 22, 2016Assignee: THE BOEING COMPANYInventors: Matthew August Lassen, Mark Steven Good
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Patent number: 9481467Abstract: 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: GrantFiled: October 21, 2014Date of Patent: November 1, 2016Assignee: B/E Aerospace, Inc.Inventor: Michael L. Oleson
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Patent number: 9434463Abstract: 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: GrantFiled: September 9, 2013Date of Patent: September 6, 2016Assignee: Airbus Operations GmbHInventors: Matteo Borghini-Lilli, Marc'Antonio Bentivoglio, Henrik-Bro Henriksen, Ruslan Zagreba
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Patent number: 9427772Abstract: 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: GrantFiled: January 24, 2014Date of Patent: August 30, 2016Assignee: Airbus Operations GmbHInventor: Berend Schoke
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Patent number: 9415575Abstract: 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: GrantFiled: January 26, 2009Date of Patent: August 16, 2016Assignee: The Board of Trustees of the University of IllinoisInventors: Brett A. Beiermann, Michael W. Keller, Scott R. White, Nancy R. Sottos
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Patent number: 9346121Abstract: 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: GrantFiled: February 27, 2015Date of Patent: May 24, 2016Assignee: Airbus Operations GmbHInventors: Domenico Furfari, Marco Pacchione
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Patent number: 9254927Abstract: 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: GrantFiled: November 20, 2013Date of Patent: February 9, 2016Inventors: Mark Hodkisson, James Wilson, Samuel Evans
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Patent number: 9187166Abstract: 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: GrantFiled: January 9, 2015Date of Patent: November 17, 2015Assignee: Airbus Operations GmbHInventors: Christoph Klahn, Rüdy Gysemberg, Olaf Rehme
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Patent number: 9150302Abstract: 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: GrantFiled: August 10, 2010Date of Patent: October 6, 2015Assignee: Airbus Operations LimitedInventors: Eric Wildman, Mohamed Saffique AdbulKader
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Patent number: 9038952Abstract: 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: GrantFiled: January 18, 2013Date of Patent: May 26, 2015Assignee: Bell Helicopter Textron Inc.Inventors: William A. Amante, Carl A. May
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Patent number: 9038951Abstract: 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: GrantFiled: March 31, 2010Date of Patent: May 26, 2015Assignee: Airbus Operations LimitedInventors: Steven Coulter, Paul Hadley, Geraint Hopkins
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Patent number: 9038953Abstract: 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: GrantFiled: July 19, 2011Date of Patent: May 26, 2015Assignee: BAE SYSTEMS PLCInventors: Matthew Lang, Ruben James Joseph Fernandes
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Patent number: 9019719Abstract: 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: GrantFiled: September 20, 2012Date of Patent: April 28, 2015Assignee: Airbus Operations SASInventors: Marc Tomasi, Matthieu De Kergommeaux, Laurent Bertandeau, Christian Banis
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Patent number: 9010688Abstract: 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: GrantFiled: February 7, 2012Date of Patent: April 21, 2015Assignee: The Boeing CompanyInventor: Moushumi Shome
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Patent number: 9010684Abstract: 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: GrantFiled: June 27, 2012Date of Patent: April 21, 2015Assignee: The Boeing CompanyInventors: 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
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Publication number: 20150102170Abstract: 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: ApplicationFiled: April 24, 2014Publication date: April 16, 2015Applicant: The Boeing CompanyInventor: Tibor A. Koncz
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Publication number: 20150102169Abstract: 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: ApplicationFiled: October 11, 2013Publication date: April 16, 2015Applicant: The Boeing CompanyInventors: Steven Paul Walker, Joanna Mara Sergiane Veit, Isaac G. Cambronero, JR., James Donald Davis, Michael D. Pagliarini
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Patent number: 9004405Abstract: 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: GrantFiled: September 16, 2009Date of Patent: April 14, 2015Assignees: EADS Deutschland GmbH, AIRBUS Operations GmbHInventors: Marco Goettinger, Tamas Havar, Xavier Hue, Franz Stadler
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Patent number: 9004406Abstract: 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: GrantFiled: June 3, 2011Date of Patent: April 14, 2015Assignee: Airbus Operations LimitedInventor: Mochamad Agoes Soenarjo
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Patent number: 9004404Abstract: A sealing member for forming a seal in an aircraft, the sealing member comprising: a sealing material; and a stiffening element which provides structural support to the sealing material and comprises a material with a glass transition temperature below +50° C. The stiffening element is relatively flexible when the aircraft is at low altitude (high temperature) but becomes relatively stiff (increasing resistance to seal flutter) when the aircraft is at cruise altitude (low temperature).Type: GrantFiled: January 6, 2009Date of Patent: April 14, 2015Assignee: Airbus Operations LimitedInventor: Colin John West
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Patent number: 9006119Abstract: 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: GrantFiled: July 11, 2010Date of Patent: April 14, 2015Assignee: A.L.D. Advanced Logistics Development Ltd.Inventors: Zigmund Bluvband, Viktor Shkatov
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Publication number: 20150097076Abstract: An aircraft includes a fuselage, a wing, and a decoupled joint interconnecting the fuselage and the wing. The decoupled joint can be an active suspension system. A method of adapting an aircraft to attenuate forces between a main wing and a fuselage thereof includes providing a plurality of sensors upon the aircraft, configured for sensing motion and/or mechanical stress of the main wing and/or the fuselage and producing signals indicative thereof, and providing a plurality of active suspension elements interconnecting the wing and the fuselage, the active suspension elements being configured to move at least in response to the signals to adjust a position of the wing with respect to the fuselage.Type: ApplicationFiled: October 9, 2013Publication date: April 9, 2015Inventors: Branko Lakic, Jonathan B Vance
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Patent number: 8998142Abstract: A device for linking a frame and a stringer of an aircraft structure, including a first portion connected to a support surface of a frame, a second portion connected to a support surface of a stringer and a third portion referred to as intermediary portion connecting the first portion to the second portion. The second portion is connected to the intermediary portion by means of an articulation allowing for a relative movement between the two portions along a rotation axis perpendicular to the support surface of the stringer. The first portion is connected to the intermediary portion by means of an articulation allowing for a relative movement between the two portions along a rotation axis parallel to the support surface of the frame and to the support surface of the stringer.Type: GrantFiled: August 31, 2012Date of Patent: April 7, 2015Assignee: Airbus Operations (SAS)Inventor: Thierry Loupias
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Patent number: 8999097Abstract: A fabrication method for providing a relatively smooth surface associated with lightning strike protection for composite materials joined with fasteners recessed below the surface is described. The method includes coating at least one of a head of the fastener and a preformed dielectric insert with an adhesive, inserting the preformed dielectric insert into the recess such that the adhesive engages both contours of the recess and the preformed dielectric insert, and removing any excess adhesive from the surface area of the composite material and a top surface of the insert.Type: GrantFiled: April 12, 2010Date of Patent: April 7, 2015Assignee: The Boeing CompanyInventors: Kathryn Louise Gehrett, James Francis Kirchner, Kelly Lee Clark
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Patent number: 8991762Abstract: A wing-fuselage connection of an aircraft, in which a wing (2) that is arranged in the upper region of the fuselage (1) is connected to the fuselage (1) by means of a number of couplings (3, 4, 5, 6), wherein the couplings (3, 4, 5, 6) are provided for taking up forces in various directions and are designed for a maximum load carrying capacity, in particular for a nominal flight- and landing load (10) or a nominal crash load. According to the invention, the load carrying capacity of the individual wing couplings (3, 4, 5, 6) and their direction of force take-up are matched to each other such that in the case of a defect in one of the couplings (3, 4, 5, 6) the maximum load carrying capacity of the remaining couplings (3, 4, 5, 6) is adequate for safe normal flight operation.Type: GrantFiled: November 2, 2007Date of Patent: March 31, 2015Assignee: Airbus Operations GmbHInventors: Ursula Voss, Joel Rocker
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Patent number: 8991759Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting. The balancer fitting is an adjustable fitting, being locked in a Z and Y directions of a Cartesian axis and being movable along an X direction of the Cartesian axis providing guidance for the tail cone end and the rest of the rear fuselage.Type: GrantFiled: September 23, 2011Date of Patent: March 31, 2015Assignee: Airbus Operations, S.L.Inventors: Ma Aránzazu García Patino, Angel Postigo Rodríguez, David López Fernández
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Patent number: 8985515Abstract: A structural joint includes a first member having a first base portion and a first leg portion. The structural joint further includes a second member having a second base portion and a second base portion. The first base portion and the second base portion are coupled together at an overlapping portion. The first leg portion and the second leg portion form a cavity for structurally coupling to a structural member.Type: GrantFiled: December 28, 2010Date of Patent: March 24, 2015Assignee: Textron Innovations Inc.Inventors: John R. McCullough, David Gordon Carlson, James Donn Hethcock, Paul K. Oldroyd, Carl A. May
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Patent number: 8985514Abstract: Structural panel assemblies include first and second composite panels positioned in edgewise alignment, with at least one tab extending from a mating edge of the first panel and including an exterior surface in facing registration with a corresponding portion of an interior surface of the second composite panel. The corresponding portion includes a recessed area to interfit with the tab or is otherwise configured to receive the tab. The exterior surface of the tab is spaced from the corresponding portion, to receive a bonding material therebetween for bonding the composite panels.Type: GrantFiled: June 20, 2012Date of Patent: March 24, 2015Assignee: The Boeing CompanyInventor: Rachel Cardin
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Patent number: 8974891Abstract: Methods of forming ceramic matrix composite structures include joining at least two lamina together to form a flexible ceramic matrix composite structure. Ceramic matrix composite structures include at least one region of reduced inter-laminar bonding at a selected location between lamina thereof. Thermal protection systems include at least one seal comprising a ceramic matrix composite material and have at least one region of reduced inter-laminar bonding at a selected location between lamina used to form the seal. Methods of forming thermal protection systems include providing one or more such seals between adjacent panels of a thermal protection system.Type: GrantFiled: October 26, 2007Date of Patent: March 10, 2015Assignee: COI Ceramics, Inc.Inventor: James A. Riedell
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Patent number: 8973870Abstract: The present disclosure relates to a wall component for an aircraft for forming an outer wall comprising at least one first wall element, at least one second wall element and at least one connecting device for connecting the first wall element to the second wall element. On wall regions that are to be directed towards each other, the first and the second wall element comprise connecting regions. Furthermore, a joint element is provided, which comprises a joint region with a joint region surface that is to be arranged towards the outside of the aircraft, wherein the joint region is designed to be received with a matching fit into a recess formed by the connecting regions of the wall elements, and wherein the joint region surface, when the joint element is inserted, is flush with the outer surfaces of the wall elements.Type: GrantFiled: September 12, 2012Date of Patent: March 10, 2015Assignee: Airbus Operations GmbHInventors: Gregor Christian Endres, Hans-Juergen Weber
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Patent number: 8967540Abstract: A frame of an aircraft fuselage structure made from composite material, which includes a skin and several stringers fixed on the skin. The frame includes a profile elongated in a longitudinal direction which is hollow over at least a portion of its length. The profile is mounted on two legs. Each leg, intended to be fixed on the skin, includes a first portion extending continuously over the whole length of the profile and a second portion extending from this continuous portion so as to form several openings spaced apart in the longitudinal direction of the profile, in each of which a stringer passes. The presence of the hollow profile in the frame and the structure of the legs makes it possible to dispense with clips and cleats.Type: GrantFiled: December 17, 2012Date of Patent: March 3, 2015Assignee: Airbus Operations SASInventors: Jean-Claude Lacombe, Laurent Giuseppin
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Patent number: 8968500Abstract: A method for joining, by adhesive bonding, at least two large joining partners in vehicle construction, in particular in aircraft construction, comprises the following steps: detecting the geometric data of the joining partners in an automated manner, detecting the joint gap dimensions of the joining partners from the geometric data, applying adhesive to one or both joint faces of the two joining partners to be joined as a function of the joint gap dimensions, joining the joining partners in the joining position, and sequentially applying joining pressure to the joint faces along the joint gap to bring the joining partners into the final joining position.Type: GrantFiled: August 30, 2011Date of Patent: March 3, 2015Assignee: Airbus Operations GmbHInventors: Dirk Niermann, Holger Frauen
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Patent number: 8967541Abstract: The present invention pertains inter alia to a structural arrangement, comprising a box structure, a first fibre portion which extends in a first plane, a second fibre portion which extends in a second plane, the first and the second fibre portion being interconnected at a crossing point thereof, the first fibre portion comprising a first portion on one side of the crossing point and a second portion on the other side of the crossing point, the first portion being connected to a first portion of the box structure and the second portion being connected to a second portion of the box structure, the second fibre portion forming, on one side of the crossing point, an inner web inside the box structure and, on the other side of the crossing point, an outer web outside the box structure.Type: GrantFiled: October 11, 2012Date of Patent: March 3, 2015Assignee: Airbus Operations GmbHInventors: Oliver Seack, Alexander Bruns
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Publication number: 20150053818Abstract: An upper joint of a wing assembly of an aircraft includes an outboard upper wing panel, a center upper wing panel, a rib, and an upper joint assembly operatively interconnecting the outboard upper wing panel, the center upper wing panel, and the rib. In some embodiments, outboard upper stringers may be configured differently than center upper stringers. In some embodiments, a subset of the center upper stringers may not directly oppose the outboard upper stringers. In other embodiments, for at least a substantial fore/aft span of the upper joint, each of the center upper stringers may directly oppose an outboard upper stringer.Type: ApplicationFiled: August 23, 2013Publication date: February 26, 2015Applicant: The Boeing CompanyInventors: Jordan Daniel CHARLES, Jason Hamada
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Publication number: 20150053819Abstract: A system is disclosed including at least one indexing stub secured to a fuselage in the place of one or more wing stubs and including indexing members protruding from opposite sides of the fuselage. A pair of receivers are mounted to a container and define channels to receive the indexing members. The channels may include an upper flared portion and a lower straight portion. The indexing members are lowered into the channels and the flared portions guide the indexing members into the straight portions. In some embodiments, a pair of clamping members are configured to selectively lock the indexing members within the channels. The indexing members may have a cylindrical shape and may be rotatably mounted to the at least one indexing stub.Type: ApplicationFiled: August 23, 2013Publication date: February 26, 2015Applicant: Becklin Holdings, Inc.Inventors: Dennis S. Becklin, Dean A. Weathers, Adrian P. Tayne
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Patent number: 8960606Abstract: The disclosed shell structure splice and method may include a first panel having a first edge, a second panel having a second edge, the second edge being positioned in edgewise alignment with the first edge to form a splice joint, a strap bridging the splice joint and attached to the first panel and the second panel, the strap having a first tapered region and a second tapered region, a first fitting having a tapered section and a flat section, the tapered section being attached to the first tapered region of the strap, and a second fitting having a tapered section and a flat section, the tapered section being attached to the second tapered region of the strap.Type: GrantFiled: October 31, 2012Date of Patent: February 24, 2015Assignee: The Boeing CompanyInventors: Paul Diep, Bernhard Dopker
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Patent number: 8960605Abstract: The invention relates to an elongated supporting pillar for a high-strength structural component, wherein the supporting pillar 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.Type: GrantFiled: July 30, 2009Date of Patent: February 24, 2015Assignee: Airbus Operations GmbHInventors: Christoph Klahn, Rüdy Gysemberg, Olaf Rehme
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Publication number: 20150048209Abstract: A structural spacecraft component comprising internal microstructure; wherein said microstructure comprises a plurality of parallel layers and a plurality of spacers that connect adjacent parallel layers; wherein said structural spacecraft component is a product of an additive manufacturing process.Type: ApplicationFiled: August 18, 2014Publication date: February 19, 2015Inventors: Robert Hoyt, Jonathan Wrobel, Jesse Cushing, Mark Jaster, Nestor Voronka, Scott Frank, Jeffrey Slostad, Leonid Paritsky
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Patent number: 8950969Abstract: A force introduction fitting for lightweight constructional components comprises at least one radial force introduction surface, at least one axial force introduction surface, and at least one receiving means for holding the force introduction fitting and for introducing loads into the force introduction fitting. The radial force introduction surface and the axial force introduction surface enclose a hollow space. The radial force introduction surface and the axial force introduction surface form a single-piece component. Such a force introduction fitting can be produced with the use of a selective laser melting method. The force introduction fitting can thus be adjusted in a particularly flexible manner to the load conditions, comprises particularly advantageous materials characteristics and features a lightweight construction.Type: GrantFiled: June 14, 2012Date of Patent: February 10, 2015Assignee: Airbus Operations GmbHInventor: Frank-Michael Klaukien
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Patent number: 8950707Abstract: A connection arrangement for at least two abutting components to be firmly connected to one another, includes a self-piercing rivet having a rivet head for punching of a hole and subsequent riveting of the components, wherein a washer is allocated to the self-piercing rivet at the distal end region opposite to the rivet head, with the washer including a frontal area for the insertion of a circular indentation to create a firm compression connection between a hole in the washer and the distal end region of the self-piercing rivet.Type: GrantFiled: May 31, 2012Date of Patent: February 10, 2015Assignee: Airbus Operations GmbHInventor: Rolf Bense
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Patent number: 8944369Abstract: An aircraft engine assembly including a mounting pylon including a rigid structure fitted with a central box, together with a forward extension and a rear extension each including an attached upper organ supported on an upper surface of the central box, and an attached lower organ supported on a lower surface of the front end. The forward and rear extensions support at least a part of the first fasteners interposed between the rigid structure and a turbine engine.Type: GrantFiled: November 30, 2009Date of Patent: February 3, 2015Assignee: Airbus Operations S.A.S.Inventor: Jacques Hervé Marche
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Patent number: 8936217Abstract: A method for interconnecting electronic equipment within an aircraft includes installing a multi-dimensional backplane within the aircraft across a plurality of frame bays associated with the aircraft, the backplane including a plurality of connectors mounted thereon, contacts associated with the connectors interconnected by electrical conductors formed within the backplane, attaching shipside wiring to a first portion of the connectors on the backplane, and attaching electrical connectors of the electronic equipment to corresponding connectors on the backplane.Type: GrantFiled: September 27, 2011Date of Patent: January 20, 2015Assignee: The Boeing CompanyInventors: Mark Stephen Shander, Robert Thomas Johnson
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Patent number: 8936215Abstract: An aircraft including: at least one floor cross-member; at least one support carrying the cross-member; and at least one bearing including at least one flexible material and connecting the cross-member to the support.Type: GrantFiled: May 28, 2010Date of Patent: January 20, 2015Assignee: Airbus Operations (S.A.S)Inventors: Guillaume Gallant, Romain Delahaye
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Publication number: 20150014484Abstract: Apparatus and method for joining composite structures of aircrafts are disclosed. An example apparatus disclosed herein includes an inboard composite wing panel having a first end portion configured to be coupled to upper and lower inboard fittings composed of a metallic material and an outboard composite wing panel having a first end portion configured to be coupled to upper and lower outboard fittings composed of a metallic material. A side of body rib has a plate shaped first end portion composed of a metallic material. A fuselage frame is configured to be joined at one end of the upper inboard fitting, and the upper and lower inboard fittings and the upper and lower outboard fittings are coupled to the side of body rib at the plate shaped first end portion.Type: ApplicationFiled: July 10, 2013Publication date: January 15, 2015Inventors: Young Zeon, Gerfried Rudolf Achtner, Joseph Strachila
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Patent number: 8925864Abstract: A component for building a fuselage section of an aircraft includes a border area connectable to a corresponding further border area of a further component so as to form an electrically conductive joint, wherein the component includes a composite structure.Type: GrantFiled: June 9, 2010Date of Patent: January 6, 2015Assignee: Airbus Operations GmbHInventors: Cihangir Sayilgan, Robert Alexander Goehlich
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Publication number: 20150001343Abstract: An aircraft fuselage member and a frame are linked by a clip and a spacer. An assembly includes an aircraft fuselage member, having a skin and stringers linked to the skin, a reinforcing frame, and a clip rigidly linking the fuselage member and the frame. The clip is rigidly linked to the skin via a spacer, independent from the stringers, interposed between the fuselage member and the clip. An aircraft fuselage part includes several assemblies so defined. The cost of a fuselage is thereby reduced by standardization of the clips and/or reduction of the maximum width of the stringers.Type: ApplicationFiled: June 24, 2014Publication date: January 1, 2015Inventors: Philippe BERNADET, Yannick MARIN
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Patent number: 8919703Abstract: A hinge sealing element to substantially prevent airflow between an edge of a moveable aero surface structure and an edge of a fixed skin of an aircraft wing in the vicinity of the ribs to which the moveable aero surface structure is pivotally mounted is disclosed. The hinge sealing element comprising a deformable elongate, resiliently flexible strip having an upper face to contact a trailing edge of a fixed skin and one end attachable to a moveable aero surface structure such that said strip extends from an upper surface of said moveable aero surface structure beyond its leading edge and into a space between the edge of the fixed skin and the rib of the aircraft wing to a second, free end. The strip is configured such that it deforms during pivotal movement of the moveable aero surface structure to maintain contact between the upper face of the flexible element and the trailing edge of the fixed skin.Type: GrantFiled: May 13, 2010Date of Patent: December 30, 2014Assignee: Airbus Operations LimitedInventor: Simon John Parker
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Patent number: 8919696Abstract: 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: GrantFiled: December 29, 2010Date of Patent: December 30, 2014Assignee: Airbus Operations GmbHInventors: Georg Lonsdorfer, Hauke Seegel, Klaus Rode, Andreas Pau, Hartmut Herter, Kevin Danke