Materials Of Construction Patents (Class 244/133)
  • Patent number: 10501163
    Abstract: A pressure bulkhead for an aircraft fuselage including a sandwich structure defining a central axis and extending between a circumferential border area, the sandwich structure including an inner face sheet and an outer face sheet extending transverse to the central axis, and a core assembly sandwiched between the inner face sheet and the outer face sheet. The pressure bulkhead can receive pressure loads and can be used as a structural bearing element for receiving loads introduced by other structural parts. The inner face sheet and/or the outer face sheet has a corrugated shape. The distance between the outer face sheet and the inner face sheet increases and subsequently decreases from the border area to a central area about the central axis, forming a thickened area where the distance between the outer face sheet and the inner face sheet has a peak.
    Type: Grant
    Filed: May 19, 2016
    Date of Patent: December 10, 2019
    Assignee: Airbus Operations GmbH
    Inventors: Paul Jörn, Markus Müller
  • Patent number: 10457405
    Abstract: A heated composite structure and a method for forming a heated composite structure. The structure includes carbon fibers embedded within a thermoplastic matrix. The carbon fibers are connected with first and second electrodes that are configured to be connected with an electric source such that applying current to the electrodes causes current to flow through the embedded carbon fibers to provide resistive heating sufficient to heat the composite structure to impede formation of ice on the composite structure.
    Type: Grant
    Filed: April 24, 2019
    Date of Patent: October 29, 2019
    Assignee: TRIUMPH AEROSTRUCTURES, LLC.
    Inventors: Kyle B. Hardman, Mark A. Calder, Ian C. Derx
  • Patent number: 10435133
    Abstract: A stringer for having a runout with a raised area configured to reduces stress while improving drainage across the runout when utilized in a close structural component of a vehicle such as an aileron of an aircraft. In one or more configurations, the raised area of the runout of the stringer includes multiple tapered surfaces adjacent to one another oriented and configured as ramps to collectively guide water up, over and down the raised area of the stringer.
    Type: Grant
    Filed: July 24, 2018
    Date of Patent: October 8, 2019
    Assignee: The Boeing Company
    Inventors: Jan T. Jansen, Ryan Stott, William Vallellanes, Jack Van Es
  • Patent number: 10245864
    Abstract: A method of manufacturing a sheet metal flame includes a step of forming at least one drawn portion in a frame main body formed into a flat plate shape, and a step of engraving groove portions into a linear shape in the frame main body at constant distances from outer edge portions of the at least one drawn portion so as to sandwich the at least one drawn portion between at least opposing sides.
    Type: Grant
    Filed: June 30, 2014
    Date of Patent: April 2, 2019
    Assignee: KYOCERA DOCUMENT SOLUTIONS INC.
    Inventor: Yasuhiro Miyake
  • Patent number: 10183450
    Abstract: A method of impregnating a fiber preform with an impregnation composition, includes applying a liquid on a structure, the structure including a chamber in which a fiber preform for impregnating is present, the chamber being defined between a rigid support on which the fiber preform is placed and a wall, the wall having a face situated facing the fiber preform; and an impregnation composition for impregnating the fiber preform, the impregnation composition being present in the chamber; the liquid being applied against the wall on its side opposite from the chamber, the wall being configured so that its face situated facing the fiber preform conserves its shape during the application of the liquid, the applied liquid enabling sufficient pressure to be created to move the wall towards the rigid support and impregnate the fiber preform with the impregnation composition.
    Type: Grant
    Filed: November 25, 2014
    Date of Patent: January 22, 2019
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN
    Inventors: Philippe Henrio, Thierry Godon
  • Patent number: 9951641
    Abstract: A method of making a rub strip includes resin transfer molding an arcuate composite structure. The resin transfer molding step includes inserting a honeycomb core into a mold cavity having an arcuate base so that the honeycomb core assumes an arcuate shape. The resin transfer molding step further includes directing liquid resin into the mold cavity to form the composite structure comprising the liquid resin and the honeycomb core, and curing the liquid resin for a sufficient period of time. The resin transfer molding step further includes removing the composite structure from the mold. The method further includes repeating the resin transfer molding step until a sufficient number of arcuate composite structures are produced. The method further includes coupling a plurality of the arcuate composite structures together to form the rub strip.
    Type: Grant
    Filed: July 14, 2016
    Date of Patent: April 24, 2018
    Assignee: CTL Aerospace, Inc.
    Inventors: Simeon Copple, Nathan Sizemore, Tyler Weber, Joseph Fackey
  • Patent number: 9580161
    Abstract: Aspects of the disclosure relate to fabricating balloon envelopes for high-altitude balloons. One or more segments of reinforcing tape are applied to gore segments of the balloon envelope. The segments are arranged in a ring to circumscribe an upper portion of the balloon envelope, and may be affixed by a pressure sensitive adhesive. Should a catastrophic failure of the balloon envelope occur, the reinforcing tape acts as a ripstop to prevent a tear from extending upward toward the apex of the balloon envelope. Tendons secured to the apex and to a base of the balloon envelope are configured to keep the top film of the envelope in a parachute configuration in the event of a catastrophic failure. The reinforcing tape is positioned above an equator of the balloon envelope, for instance approximately ? of the distance down from the apex to the base of the envelope.
    Type: Grant
    Filed: October 8, 2014
    Date of Patent: February 28, 2017
    Assignee: X Development LLC
    Inventor: Kevin Roach
  • Patent number: 9481443
    Abstract: A rear fuselage section of an aircraft comprises at least one closed frame constructed as a unitary body, and a horizontal tail plane comprising a box-type central element and two lateral torsion boxes, said horizontal tail plane trimmable with respect to a pivot axis. The horizontal tail plane is mounted at the closed frame and the pivot axis is contained in a horizontal plane below the lowest end of said closed frame.
    Type: Grant
    Filed: July 29, 2014
    Date of Patent: November 1, 2016
    Assignee: Airbus Operations S.L.
    Inventors: Alfonso Gonzalez Gozalbo, Raul Carlos Llamas Sandin
  • Patent number: 9297394
    Abstract: Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing these metal sheets and plates are disclosed herein. In an embodiment, there is provided a transportation vessel that includes at least one metal product having at least one surface that is substantially grooved, wherein the substantially grooved surface forms a riblet topography, the riblet topography including a multiplicity of adjacent permanently rolled longitudinal riblets running along at least a part of the surface, and wherein the riblet topography is coated with at least one coating sufficiently designed and applied to preserve the riblet topography. In an embodiment, the multiplicity of adjacent permanently rolled longitudinal riblets results in a friction-reducing textured surface. In an embodiment, metal product is used in fabricating at least a portion of an aircraft. In an embodiment, metal product is used in fabricating at least a portion of a rotor blade.
    Type: Grant
    Filed: November 11, 2013
    Date of Patent: March 29, 2016
    Assignee: Alcoa Inc.
    Inventors: Ming Li, James M. Marinelli, Jiantao Liu, Paul E. Magnusen, Simon Sheu, Markus B. Heinimann, John Liu, Luis Fanor Vega
  • Patent number: 9222006
    Abstract: A method and apparatus comprising a sol-gel solution. Zirconium n-propoxide is aged in a solvent to form a first part for the sol-gel solution. The first part is combined with deionized water to form a second part for the sol-gel solution. Aminoaryltrialkoxysilane is combined with an alcohol to form a third part for the sol-gel solution. The third part is combined with the second part to form a mixture for the sol-gel solution. The deionized water, or the alcohol, or a combination thereof is combined with the mixture to form a solution. The solution is aged to form the sol-gel solution comprising a mole balance ratio of approximately 1:5 between the zirconium n-propoxide and the aminoaryltrialkoxysilane.
    Type: Grant
    Filed: February 28, 2013
    Date of Patent: December 29, 2015
    Assignee: THE BOEING COMPANY
    Inventors: Kay Youngdahl Blohowiak, Kristin L. Krieg, Robert A. Anderson, Jr.
  • Patent number: 9096316
    Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.
    Type: Grant
    Filed: February 1, 2012
    Date of Patent: August 4, 2015
    Assignee: Textron Innovations Inc.
    Inventors: Wei-Yueh Lee, Paul Oldroyd
  • Publication number: 20150136910
    Abstract: A morphing skin for an air vehicle structure, the skin being formed by a composite material which includes: a multiplicity of fibres, a matrix incorporating the fibres, and a thermo-sensitive material, such as a thermo-plastic. The thermo-sensitive material can be reversibly transitionable in response to a change in temperature, between (i) an ambient temperature mode in which the thermo-sensitive material is capable of transferring loads in the composite material, and (ii) a heated mode in which the ability of the thermo-sensitive material to transfer the loads is reduced. This can allow the stiffness of the skin to be temporarily reduced to enable the skin to be morphed into a different shape.
    Type: Application
    Filed: March 28, 2013
    Publication date: May 21, 2015
    Applicant: MBDA UK Limited
    Inventors: Mohammed Azad Hussain, Anthony Machell, Paul Robinson, Henry Alexander Maples, Chamwit Tridech, Alexander Bismarck
  • Patent number: 9011616
    Abstract: The shape of a laminated composite structure is optimized using finite element analysis. The optimized shape minimizes the weight of the structure while satisfying minimum strength and stiffness requirements.
    Type: Grant
    Filed: August 30, 2008
    Date of Patent: April 21, 2015
    Assignee: The Boeing Company
    Inventors: Ethan W. Hunter, Thomas J. Falasco, Kurt M. Swanson
  • 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: 9004404
    Abstract: 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: Grant
    Filed: January 6, 2009
    Date of Patent: April 14, 2015
    Assignee: Airbus Operations Limited
    Inventor: Colin John West
  • Patent number: 8998134
    Abstract: A fiber-reinforced, organic matrix, composite structural member includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the structural member exhibits a non-linear stress-strain response when mechanically loaded to failure. A helicopter landing gear includes a pair of skids and one or more cross members extending between the pair of skids. The one or more cross members includes a plurality of layers of fiber-reinforced, organic matrix, composite material in which adjacent layers are bonded to one another, wherein the cross members exhibit non-linear stress-strain responses when mechanically loaded to failure.
    Type: Grant
    Filed: June 19, 2009
    Date of Patent: April 7, 2015
    Assignee: Textron Innovations Inc.
    Inventors: Robert Clive Fews, Bijan Derisi, Suong Van Hoa, Mehdi Hojjati
  • Patent number: 8925864
    Abstract: 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: Grant
    Filed: June 9, 2010
    Date of Patent: January 6, 2015
    Assignee: Airbus Operations GmbH
    Inventors: Cihangir Sayilgan, Robert Alexander Goehlich
  • Patent number: 8882023
    Abstract: Disclosed in this application is a novel method and apparatus for reducing electrical resistance of a carbon-reinforced plastic structure to thereby reduce damage due to lightning strikes or precipitation static. This apparatus includes a galvanically compatible conductive interface layer positioned between a nonconductive substrate and a conductive outer surface. The interface layer is electrically conductive to transmit electrical current from the outer surface to the substrate.
    Type: Grant
    Filed: April 11, 2011
    Date of Patent: November 11, 2014
    Assignee: The Boeing Company
    Inventor: Arlene McKeeman Brown
  • Patent number: 8876049
    Abstract: The disclosed embodiments concern an aircraft fuselage section made of composite material with an internal skeleton having frames that form the radial structure of the fuselage and stringers that form the longitudinal structure of said fuselage, and a skin made of composite material, surrounding the internal skeleton, with said skin having an evolving thickness along a longitudinal axis X, with an approximately constant, regular interior profile. The disclosed embodiments also concern a process for manufacturing the skin of an aircraft fuselage section made of composite material, having a draping operation for strips of fibers precoated with resin around a mold, with the number of strips of fibers varying longitudinally depending on the area of the fuselage being considered so as to create a skin with an evolving thickness.
    Type: Grant
    Filed: September 29, 2009
    Date of Patent: November 4, 2014
    Assignee: Airbus Operations SAS
    Inventors: Cedric Meyer, Jocelyn Gaudin
  • Patent number: 8870120
    Abstract: A composite structure has a first section, a second section, and a curved corner joining the first and second sections. The structure has a stack of fiber-reinforced plies including first and second external plies which run from the first section into the second section on an inside and an outside of the corner, respectively. A discontinuous first internal ply is sandwiched between the first and second external plies so that more of the first internal ply is located within the first section than within the second section. A second internal ply is sandwiched between the first and second external plies. The fibers of the first internal ply run at an angle ? to the fibers of the second internal ply. In some embodiments the angle ? is greater than 3° but less than 20°. In one embodiment the angle ? is between 35° and 42°.
    Type: Grant
    Filed: February 22, 2012
    Date of Patent: October 28, 2014
    Assignee: Airbus Operations Limited
    Inventors: Timothy J. Sanderson, Stephen Williams
  • Patent number: 8864072
    Abstract: A structural component includes a fiber composite material structure having an outer surface and an electrically conductive metal profile disposed on the outer surface of the fiber composite material structure. The metal profile provides provide improved electrical conductivity of the structural component and component protection.
    Type: Grant
    Filed: May 12, 2011
    Date of Patent: October 21, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Jens Telgkamp, Wolfgang Schulze, Thomas Kruse
  • Patent number: 8857764
    Abstract: Techniques and apparatus for providing a fly away caul plate are disclosed. In an embodiment, a method for curing a composite structure includes placing a pre-cured caul plate proximate an uncured composite lay-up, the lay-up may or may not include one or more stiffeners extending substantially perpendicular to the lay-up surface, the caul plate including an aperture for receiving the at least one stiffener. A force may be exerted against the caul plate to engage the composite lay-up. Heat and/or pressure may be applied to the composite lay-up to cure the stiffener panel and co-bond the caul plate to the composite lay-up.
    Type: Grant
    Filed: August 9, 2012
    Date of Patent: October 14, 2014
    Assignee: The Boeing Company
    Inventors: Thomas A. Albertson, Karl R. Bernetich, Robert J. Freeman
  • Patent number: 8844877
    Abstract: A passive non-ablating thermally protective structure body is disclosed. An improved-reliability heat pipe edge comprises a non-porous material formed into a wedge-shaped chamber, and a porous layer. The porous layer extends from interior surfaces of the non-porous material to provide capillary wicking.
    Type: Grant
    Filed: September 2, 2010
    Date of Patent: September 30, 2014
    Assignee: The Boeing Company
    Inventors: Daniel E. Driemeyer, John C. Waldrop, III, Victor Blakemore Slaughter, Jonathan D. Embler, James P. Ledesma, Robert D. Keeler, Jr.
  • Patent number: 8844872
    Abstract: A composite structure has first and second sections, and a curved corner joining the first and second sections. The structure includes a stack of fiber-reinforced plies. First and second external plies run from the first section into the second section round an inside and an outside of the corner, respectively. First and second internal plies are sandwiched between the first and second external plies, and run from the first section into the second section round the corner. The first internal fly is dropped off inside the second section. The second internal ply is dropped off inside the first section. The structure has an increased thickness where the first and second internal plies overlap.
    Type: Grant
    Filed: February 21, 2012
    Date of Patent: September 30, 2014
    Assignee: Airbus Operations Limited
    Inventors: Timothy J. Sanderson, Stephen Williams
  • Patent number: 8844873
    Abstract: In an embodiment of the disclosure, there is provided an apparatus to provide a panel stiffening element. The apparatus has an outer braided thermoplastic tube and an inner braided thermoplastic tube disposed within the outer braided thermoplastic tube. The apparatus further has a separation ply layer co-consolidated between the outer braided thermoplastic tube and the inner braided thermoplastic tube. The separation ply layer provides reinforcement and impact damage resistance to the inner braided thermoplastic tube in order to avoid a loss in structural loading capability.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: September 30, 2014
    Assignee: The Boeing Company
    Inventor: Jeffery Lee Marcoe
  • Patent number: 8800911
    Abstract: A lightning strike protection material may include a fiber reinforced composite aircraft component including carbon fibers in a resin matrix. The carbon fibers may have a length greater than at least about 6 mm and include carbon nanotubes grown on the fibers, and the nanotubes may be substantially uniformly distributed on the fibers and have a length between about 1 and 100 microns. The nanotubes may decrease a surface resistance of the resin matrix.
    Type: Grant
    Filed: September 25, 2013
    Date of Patent: August 12, 2014
    Assignee: Rohr, Inc.
    Inventors: Teresa M. Kruckenberg, Vijay V. Pujar
  • Patent number: 8802213
    Abstract: A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch adapted to cover the inconsistent area and bonded to the structure by a layer of adhesive. The patch includes a plurality of composite plies having a tapered cross section, and at least first and second regions respectively having differing fracture toughnesses.
    Type: Grant
    Filed: May 27, 2013
    Date of Patent: August 12, 2014
    Assignee: The Boeing Company
    Inventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman
  • Patent number: 8765042
    Abstract: In accordance with the method, an inside layer of a fuselage section skin made from first fibers is placed on a manufacturing surface, the first fibers being placed in one or more first fiber directions. On the inside layer, a stiffening structure is formed from stiffening fibers, the stiffening fibers being placed in one or more stiffening fiber directions. An outside layer of the fuselage section skin, comprising fourth fibers, is placed on the stiffening structure formed from stiffening fibers, the fourth fibers being placed in one or more fourth fiber directions. The stiffening structure is designed and developed in such a way that the fuselage section does not require an additional stiffening structure, is connected with the fuselage section skin, and comprises the inside layer, the stiffening structure, and the outside layer; in particular, an additional stiffening structure in the form of stringers and frames is not required.
    Type: Grant
    Filed: June 7, 2011
    Date of Patent: July 1, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Holger Frauen, Robert Alexander Goehlich
  • Publication number: 20140151507
    Abstract: A composite laminate, method of forming same, and use for same are disclosed. One example of a composite laminate has multiple layers or plies (305A-305E) composed of generally parallel reinforcing fibers (315A-315E) embedded in a matrix (305M). The reinforcing fibers have orientations in the ranges of 3 to 8 degrees, ?3 to ?8 degrees, 10 to 40 degrees, ?10 to ?40 degrees, and approximately 90 degrees, the orientations being with respect to a predetermined axis (320), such as an axis of tension (T). A method of manufacturing a composite laminate includes laying a resin and fibers having these orientations and then curing the resulting laminate. One example of a use is for the skin on the fuselage or wing of an aircraft.
    Type: Application
    Filed: December 3, 2012
    Publication date: June 5, 2014
    Applicant: THE BOEING COMPANY
    Inventor: The Boeing Company
  • Patent number: 8733702
    Abstract: A reduced solar aborptivity appliqué having a surface layer for adhering to an surface and high aspect ratio microstructures extending from the surface layer having pigmentation or spectral tailoring.
    Type: Grant
    Filed: December 2, 2009
    Date of Patent: May 27, 2014
    Assignee: The Boeing Company
    Inventors: Diane C. Rawlings, George M. Roe, Peter C. Keller
  • Patent number: 8720828
    Abstract: Heat exchange systems, devices and methods are provided. A particular heat exchange device includes a housing defining an inlet and an outlet. The heat exchange device also includes at least one ceramic foam member inside the housing. The at least one ceramic foam member defines a plurality of pores. The heat exchange device also includes a plurality of extended plugs that extend from a first side of the housing through the at least one ceramic foam member to a second side of the housing. The first side of the housing is spaced apart from the at least one ceramic foam member by first ends of the plurality of extended plugs.
    Type: Grant
    Filed: December 3, 2009
    Date of Patent: May 13, 2014
    Assignee: The Boeing Company
    Inventors: William W. Behrens, Andrew R. Tucker
  • Patent number: 8720825
    Abstract: An aerospace vehicle includes a plurality of composite stiffeners. Each stiffener of the plurality has a stack of plies of reinforcing fibers. At least some of the plies in the stack have reinforcing fibers oriented at ±? with respect to an axis of primary loading, where ? is between 2 and 12 degrees. At least some of the plies in the stack have reinforcing fibers oriented at ±? with respect to the axis of primary loading, where ? is between 50 and 85 degrees.
    Type: Grant
    Filed: October 4, 2010
    Date of Patent: May 13, 2014
    Assignee: The Boeing Company
    Inventor: Max U. Kismarton
  • Patent number: 8709584
    Abstract: An aircraft floor system includes a composite panel which generally includes an inboard layer, an inboard interlock layer, a core layer, an outboard interlock layer and an outboard layer. The advanced sandwich core material may include K-Cor™ or X-Cor™ which is pinned through at least one ply of dry composite reinforcement to provide a mechanical lock between the pins and an inboard and outboard interlock layer. Bonding of the locked-in ply with the inboard and outboard results in improved structural performance and damage tolerance.
    Type: Grant
    Filed: January 26, 2007
    Date of Patent: April 29, 2014
    Assignee: Sikorsky Aircraft Corporation
    Inventors: Thomas A. Carstensen, David M. Cournoyer, Dan Ursenbach
  • Patent number: 8662449
    Abstract: An apparatus having a composite air-based structure with a first carbon nanotube infused material and a second carbon nanotube infused material. The first and second carbon nanotube infused materials each having a range of carbon nanotube loading selected to provide different functionalities.
    Type: Grant
    Filed: November 23, 2010
    Date of Patent: March 4, 2014
    Assignee: Applied NanoStructured Solutions, LLC
    Inventors: Tushar K. Shah, Mark R. Alberding, Harry C. Malecki, Samuel J. Markkula, John Anthony Hughes, Shawn C. Kline
  • Patent number: 8651421
    Abstract: An aircraft fuselage structure which is constructed from a plurality of shells which are joined together is disclosed. Each shell forms part of the aircraft fuselage and comprises a support structure and a skin which is arranged on the latter and outwardly seals the aircraft fuselage in a compression-proof manner. The aircraft fuselage structure comprises an upper and side shell and a lower shell, of which the lower shell has a radius which is essentially significantly larger than the radius of the upper and side shell. The upper and side shell and the lower shell are joined together at transition regions extending in the longitudinal direction of the aircraft. The support structure of the lower shell is designed in terms of its strength in such a manner that it is capable of absorbing the internal pressure loading of the lower shell without the use of a main crossmember.
    Type: Grant
    Filed: June 5, 2007
    Date of Patent: February 18, 2014
    Assignee: Airbus Operations GmbH
    Inventor: Cord Haack
  • Patent number: 8613406
    Abstract: Low weight and non-square carpet tile suitable for use in mass transit vehicles, particularly passenger aircraft. The carpet tile preferably weighs less than about 82 ounces per square yard. The carpet tile of this invention may have a carpet pile and at least one backing layer. The backing layer may use a low weight filler material. The carpet tiles satisfy transportation industry standards for flame, smoke and toxicity. Tiles may be sized during manufacture and installed in configurations that minimize the number of tile sizes needed and minimize the need for cutting tiles during installation. The patterns used for such tiles may be orthogonally ambiguous or otherwise suitable for “random” installation. In other embodiments, a passenger aircraft cabin includes a floor having rectangular carpet tiles installed thereon, and the carpeting can be installed in the aircraft without removing seats from the aircraft.
    Type: Grant
    Filed: September 2, 2009
    Date of Patent: December 24, 2013
    Assignee: Interface, Inc.
    Inventors: Stuart Jones, James Hobbs, Joel Sheppard, William Jones
  • Patent number: 8592042
    Abstract: A coating composition and a method for coating metallic substrates, such as aircraft components exposed to elevated temperatures and/or oxidative conditions. The coating composition includes an aqueous mixture having about 2 vol % to about 50 vol % organosilane, about 0.3 to about 25 vol % metal alkoxide, and about 0.1 to about 30 vol % organic complexing agent. The coating composition may be deposited on a metallic substrate and cured to form a sol-gel coating on the surface of the substrate that is adherent to the substrate, and oxidation and discoloration resistant.
    Type: Grant
    Filed: November 9, 2006
    Date of Patent: November 26, 2013
    Assignee: The Boeing Company
    Inventors: Kay Y. Blohowiak, Jacob W. Grob, Joseph H. Osborne
  • Patent number: 8550398
    Abstract: Optimization of structures subjected to hot gas streams. The invention refers to a fairing (10) for aircraft horizontal stabilizer (3) comprising a front part (11) and a rear part (12), the front part (11) covering a limited extent of the fairing (10) surface, which is the part of the fairing (10) receiving hot air stream (6) coming from the aircraft engines (4), this front part (11) being made of an anti-erosion material, the rear part (12) covering the rest of the surface of the fairing (10), this rear part (12) being made of a material resisting the aerodynamic loads existing on the fairing (10). The invention also refers to an aircraft comprising a horizontal stabilizer (3) with a fairing (10) such as the one described.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: October 8, 2013
    Assignee: Airbus Operations S.L.
    Inventors: José Javier Almendros Gómez, Yolanda De Gregorio Hurtado
  • Patent number: 8540909
    Abstract: A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch adapted to cover the inconsistent area and bonded to the structure by a layer of adhesive. The patch includes a plurality of composite plies having a tapered cross section, and at least first and second regions respectively having differing fracture toughnesses.
    Type: Grant
    Filed: March 9, 2009
    Date of Patent: September 24, 2013
    Assignee: The Boeing Company
    Inventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman
  • Patent number: 8517300
    Abstract: A composite material, the composite material comprising a prepreg, said prepreg comprising at least one polymeric resin and at least one conductive fibrous reinforcement, electrically conducting particles dispersed in the polymeric resin and a top layer of a metal-coated carbon fiber comprising a further resin component, wherein the metal comprises one or more metals selected from nickel, copper, gold, platinum, palladium, indium and silver.
    Type: Grant
    Filed: March 6, 2009
    Date of Patent: August 27, 2013
    Assignee: Hexcel Composites Limited
    Inventors: Martin Simmons, John Cawse
  • Patent number: 8496206
    Abstract: Structural panels for use in manufacturing aircraft fuselages and other structures are disclosed herein. In one embodiment, a structural panel configured in accordance with the invention includes a skin and at least first and second stiffeners. The first stiffener can have a first flange portion mated to the skin and a first raised portion projecting away from the skin. The second stiffener can have a second flange portion mated to the skin and a second raised portion projecting away from the skin. At least one of the first flange portion of the first stiffener and the second flange portion of the second stiffener can extend toward the other of the first flange portion and the second flange portion to form an at least approximately continuous support surface to which a frame can be attached.
    Type: Grant
    Filed: April 16, 2010
    Date of Patent: July 30, 2013
    Assignee: The Boeing Company
    Inventors: Kent E. Johnson, Mark A. Ulvin
  • Patent number: 8490365
    Abstract: The invention relates to an aircraft side fairing, with a component (9) in the form of individual hollow chambers (12, 13, 14) which are arranged essentially in a preferably curved plane and are arranged between two cover layers (1, 2), wherein a gastight film which completely encases the component (9) with the hollow chambers (12, 13, 14) is provided and, after application of a vacuum to evacuate the hollow chambers (12, 13, 14), surrounds the component (9) with the hollow chambers in a gastight manner.
    Type: Grant
    Filed: June 22, 2007
    Date of Patent: July 23, 2013
    Assignee: AIRBUS Deutschland GmbH
    Inventors: Rainer Mueller, Georg Muehlthaler
  • Patent number: 8473122
    Abstract: The present invention relates to a method for actively deforming, by feedback control, an aerodynamic profile comprising an elastic material, applied to a part of the surface of the aerodynamic profile, said elastic material being in contact with a fluid flow; said elastic material being able to be deformed by one or more shape memory actuators placed in contact with the elastic material, said actuators being controlled by a computer connected to sensors. This method applies notably to a deformation of an aerofoil of a wing of an aircraft in flight, notably subsonic.
    Type: Grant
    Filed: February 2, 2009
    Date of Patent: June 25, 2013
    Assignee: Thales
    Inventor: Georges-Henri Simon
  • Patent number: 8444087
    Abstract: Composite stringer and skin structures and methods for forming the same are disclosed. In one embodiment, a composite stringer and skin structure includes a polymer-based elongated stringer portion having reinforcing fibers positioned in a plurality of adjacent plies, a first portion of the reinforcing fibers being oriented at a relatively shallow angle relative to a selected reference direction, and a second portion of the reinforcing fibers being oriented at a relatively broad angle relative to the selected reference direction. A polymer-based and fiber reinforced skin member adjoins the stringer portion, and an adhesive material is interposed between the stringer portion and the skin member.
    Type: Grant
    Filed: April 28, 2005
    Date of Patent: May 21, 2013
    Assignee: The Boeing Company
    Inventor: Max U. Kismarton
  • Patent number: 8444092
    Abstract: Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing these metal sheets and plates are disclosed herein. In an embodiment, there is provided a transportation vessel that includes at least one metal product having at least one surface that is substantially grooved, wherein the substantially grooved surface forms a riblet topography, the riblet topography including a multiplicity of adjacent permanently rolled longitudinal riblets running along at least a part of the surface, and wherein the riblet topography is coated with at least one coating sufficiently designed and applied to preserve the riblet topography. In an embodiment, the multiplicity of adjacent permanently rolled longitudinal riblets results in a friction-reducing textured surface. In an embodiment, metal product is used in fabricating at least a portion of an aircraft. In an embodiment, metal product is used in fabricating at least a portion of a rotor blade.
    Type: Grant
    Filed: August 5, 2009
    Date of Patent: May 21, 2013
    Assignee: Alcoa Inc.
    Inventors: Ming Li, James M. Marinelli, Jiantao Liu, Paul E. Magnusen, Simon Sheu, Markus B. Heinimann, John Liu, Luis Fanor Vega
  • Patent number: 8426007
    Abstract: A laminate of metal layers and plastic bonding layers situated between the metal layers includes two external metal layers extending substantially continuously and at least one internal metal layer. At least one of the internal metal layers has at least one opening, and at the position of the opening the other metal layers and plastic bonding layers are bonded together to the form of a packet of lower thickness. The relatively thick parts of the laminate can be used for the transfer of forces.
    Type: Grant
    Filed: July 2, 2004
    Date of Patent: April 23, 2013
    Assignee: Fokker Aerostructures B.V.
    Inventors: Abdoel Faziel Rajabali, Max Arjan Markestein
  • Patent number: 8418963
    Abstract: The present invention relates to an aircraft load frame (1) made of a composite material, characterized in that it comprises two side elements (2, 3) and a base element (7), the side elements (2, 3) being joined at the inner part of the frame (1) by means of the base element (7) and each of the side elements (2, 3) comprising a leg (4) joining the frame (1) to the aircraft fuselage skin, a web (5) and a lower flange (6) joining the web (5) and the base element (7).
    Type: Grant
    Filed: March 29, 2007
    Date of Patent: April 16, 2013
    Assignee: Airbus Operations S.L.
    Inventors: Elena Arévalo Rodríguez, Cesar Bautista De La Llave, Cristina Ortega Juaristi
  • Patent number: 8398021
    Abstract: An aircraft forward pressure bulkhead and an aircraft crown panel are described herein. The forward pressure bulkhead includes a malleable and deformable dome that is configured to “catch” foreign objects, such as birds. The dome is intentionally designed to deform in response to a foreign object strike that imparts at least a threshold amount of impact energy to the bulkhead. The dome is free of rigid stiffeners and non-deformable reinforcement members that would otherwise hinder the flexible characteristic of the dome. Practical embodiments of the bulkhead utilize fewer parts, are less heavy, and are less expensive than traditional bulkheads that utilize rigid stiffeners. The crown panel has similar compliant characteristics. The crown panel is designed to simultaneously deform and deflect in response to foreign object impacts such as birds and hail. The crown panel is formed from a monolithic one-piece material, such as aluminum, and various reinforcing features are integrally formed in the material.
    Type: Grant
    Filed: March 6, 2007
    Date of Patent: March 19, 2013
    Assignee: The Boeing Company
    Inventors: William J. Koch, Donald P. Matheson
  • Patent number: 8387915
    Abstract: A skid rail for aircrafts comprising (i) a base member comprising a long board fixed to a bottom surface of an aircraft fuselage, and bosses integrally projecting from an outer surface of the long board with longitudinal intervals, (ii) cores bonded to the long board between the bosses to form a rail-shaped, integral structure, and (iii) a skin covering the bosses and the cores, the base member and the skin being formed by a first fiber-reinforced plastic having fabrics of glass fibers and/or carbon fibers, and the cores being formed by a second fiber-reinforced plastic having fabrics of fibers having higher wear resistance than that of fibers in the first fiber-reinforced plastic.
    Type: Grant
    Filed: March 17, 2010
    Date of Patent: March 5, 2013
    Assignee: Honda Patents & Technologies North America, LLC
    Inventors: Jun Nakazawa, Hirohide Azuma
  • Patent number: 8387994
    Abstract: A surface seal for sealing a riveted and/or screwed joint between a first and a second component of an aircraft. The surface seal is arranged in the region of joining surfaces of the first and the second component. The surface seal is formed with a pressure-resistant plastic film that is provided with a pressure-sensitive adhesive layer on both sides. The surface seal 1 may furthermore comprise elements for detecting cracks. A method for producing a riveted and/or screwed joint between a first and a second component of an aircraft is also provided, with the joint being sealed with the surface seal.
    Type: Grant
    Filed: January 23, 2007
    Date of Patent: March 5, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Heiner Stehmeier, Thomas Beumler