Aircraft Patents (Class 361/218)
  • Patent number: 10301039
    Abstract: The present application relates to a static discharger and an aircraft including the static discharger. According to an aspect of the present application, a static discharger is provided which includes: a basement; and a discharger body adapted to be installed to the basement. The static discharger further includes a first fixing mechanism adapted to fix the discharger body to the basement. A pivoting mechanism is provided between the basement and the discharger body, the pivoting mechanism allowing the discharger body to pivot with respect to the basement so as to adjust an installation orientation of the discharger body with respect to the basement during an on-site-installation of the static discharger. According to the present application, for example, installation adaptation and universality of the static discharger can be improved.
    Type: Grant
    Filed: March 14, 2016
    Date of Patent: May 28, 2019
    Assignee: AIRBUS (BEIJING) ENGINEERING CENTRE COMPANY LIMITED
    Inventors: Zengli Han, Yumin Sun
  • Patent number: 10080286
    Abstract: A spar includes a conductive layer laminated and formed on a carbon-fiber prepreg, and a jumper formed of a conductor which penetrates through the conductive layer and the carbon-fiber prepreg.
    Type: Grant
    Filed: February 15, 2012
    Date of Patent: September 18, 2018
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Hiroyuki Waku
  • Patent number: 10040568
    Abstract: An electrical protector with a central axis includes a cap defining a top and a downwardly extending cap wall, and insert defining a ring and an upwardly extending insert wall, at least three protrusions extending inwardly from an interior surface of the insert wall toward the central axis, and a sealant disposed at least within the cap. The cap wall engages the insert wall, thereby establishing a connection between the cap and the insert. The protrusions are adapted to engage a structure, thereby securing the electrical protector onto the structure.
    Type: Grant
    Filed: January 27, 2014
    Date of Patent: August 7, 2018
    Assignee: SHORT BROTHERS PLC
    Inventors: Lynsey Rebbeck, Paolo Ballocchi, Peter Quigley, Sam Wilson
  • Patent number: 9811766
    Abstract: An electronic device includes a controller and a unit section. The controller is configured to control operation of the electronic device. The unit section is drawable from a main body of the electronic device on which multiple loads and the controller are mounted. The unit section includes a first load, a second load, and a third load. Each of the first load and the second load is connected to a serial communication unit that enables serial communication with the control unit. The third load is connected to a communication line used for communication with the controller, without being connected to the serial communication unit.
    Type: Grant
    Filed: April 8, 2014
    Date of Patent: November 7, 2017
    Assignee: Ricoh Company, Ltd.
    Inventors: Kazumasa Kinoda, Shohgo Miura
  • Patent number: 9533770
    Abstract: An aircraft assembly comprising a plurality of structural components and an electrically conductive bonding network, wherein at least one of the structural components is formed of material of low electrical conductivity, and the bonding network includes either: at least one substantially planar strip of highly electrically conductive material attached to at least the one structural component, and wherein the strip includes a substantially omega-shaped loop extending out of the plane of the strip; or at least one strip of highly electrically conductive material attached to at least the one structural component, wherein the strip comprises first and second planar attachment portions for attaching the strip to the structural component(s) and an intermediate portion extending between the first and second attachment portions, and wherein the intermediate portion includes a loop which extends outwards from the plane of the first attachment portion.
    Type: Grant
    Filed: March 9, 2012
    Date of Patent: January 3, 2017
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Alan Quayle, James Wilson, Jon McAlinden, Paul Hadley
  • Patent number: 9422065
    Abstract: A static discharge device includes a body and an electrical path carried in the body for discharging static electricity. Carried on the body is visual indicia indicating a present operational status of the electrical path to discharge static electricity effectively. The visual indicia is observable to an airplane operator or technician to quickly determine the operational or non-operational status of the static discharge device.
    Type: Grant
    Filed: January 5, 2015
    Date of Patent: August 23, 2016
    Inventor: Grady L. Skelton
  • Patent number: 9408283
    Abstract: An electrical grounding arm is described and which has a predetermined geometry that dissipates stress imparted to the electrical grounding arm by the repeated movement of the electrical grounding arm, so as to inhibit stress related damage from being imparted to the electrical grounding arm, and which further, inhibits a source of fluid from pooling or collecting on the exterior facing surface thereof in order to prevent an unsanitary condition from developing.
    Type: Grant
    Filed: June 23, 2014
    Date of Patent: August 2, 2016
    Assignee: Key Technology, Inc.
    Inventors: Michael T. Jones, Christopher A. Woiler, Dean Dunham
  • Patent number: 9346559
    Abstract: A static discharge device includes a body an an electrical path carried in the body for discharging static electricity. Carried on the body is visual indicia indicating a present operational status of the electrical path to discharge static electricity effectively. The visual indicia is observable to an airplane operator or technician to quickly determine the operational or non-operational status of the static discharge device.
    Type: Grant
    Filed: August 23, 2015
    Date of Patent: May 24, 2016
    Inventor: Grady L. Skelton
  • Patent number: 9343900
    Abstract: Embodiments of the invention provide an electrostatic discharge protection device or network for an integrated circuit. The network includes a first circuit branch and a second circuit branch connected in a parallel configuration. The first branch has a first inductance, a first resistance, and includes a first capacitive component. The second branch has a second inductance, a second resistance, and includes a second capacitive component. A first end of the first circuit branch and a first end of the second circuit branch are coupled to a first node, and a second end of the first circuit branch and a second end of the second circuit branch are coupled to zero-voltage reference level. The network is capable of providing a low impedance path away from a terminal of the integrated circuit during an electrostatic discharge event.
    Type: Grant
    Filed: June 24, 2009
    Date of Patent: May 17, 2016
    Assignee: Robert Bosch GmbH
    Inventors: Cyrous F. Rostamzadeh, Paul Janos
  • Patent number: 9309005
    Abstract: A fastener assembly for attaching a component or bracket to the inner surface of the skin of an aircraft wing is disclosed. The fastener assembly comprises a bolt having a shaft and a bolt retaining member that threadingly cooperates with the shaft to retain the bolt in a position in which it extends through a hole in the skin. The fastener also includes a component or bracket retaining member that also threadingly cooperates with a portion of the shaft protruding through said bolt retaining member to attach a component or bracket to said inner surface.
    Type: Grant
    Filed: January 25, 2012
    Date of Patent: April 12, 2016
    Assignee: AIRBUS OPERATIONS LIMITED
    Inventors: Martin Geoffrey Warren, Phillip Vincent Teague
  • Patent number: 9221547
    Abstract: There is provided a method for mitigating static discharge in a fuel container. The method provides a static dissipative coating having a volume resistivity of 1.0×109 ?-m (ohm-meter) or less when measured at 40 V (volts) or less, having a surface resistivity of 1.0×1011 ?/sq (ohm per square) or less when measured at 100 V (volts) or less, having a breakdown voltage of 4000 V (volts) or less, and having a charge decay of 60 seconds or less. The method further provides applying the static dissipative coating to a surface of the fuel container to form a coated surface.
    Type: Grant
    Filed: June 25, 2010
    Date of Patent: December 29, 2015
    Assignee: The Boeing Company
    Inventors: Alexander Chao, Eric Richard Steele, Kevin Darrell Pate, Megan J. Hurt, Michael G. Anderson, Theresa Nadine Ward, Judson Sid Clements
  • Patent number: 9217811
    Abstract: The present disclosure teaches a lightning damage index is that used to predict the propensity of a lightning strike to an aircraft and the degree of damage to the aircraft that the lightning strike will cause. This index can help to obviate operational issues and other losses related to subsequent repairs to the aircraft that are required because of lightning damage. The disclosed method of predicting lightning strike damage to an aircraft involves generating data relating to the aircraft by measuring the dimensions of the aircraft, assessing the design features of the aircraft, and/or obtaining electromagnetic density data associated with regions of the aircraft. The method further involves creating a lightning damage index that provides a numeric representation for predicted lightning strike damage to the aircraft based on the generated data. The numeric representation may be further modified by factors associated with operation of the aircraft.
    Type: Grant
    Filed: December 15, 2011
    Date of Patent: December 22, 2015
    Assignee: THE BOEING COMPANY
    Inventor: Gregory J. Sweers
  • Patent number: 9140291
    Abstract: A method and apparatus for covering a fastener system. In one illustrative embodiment, an apparatus comprises a cover. The cover is configured to be placed over a fastener system at a surface of an object in which the fastener system is installed. The cover is comprised of a number of composite materials selected such that the cover is configured to reduce an effect of an electrical discharge, which occurs around the fastener system, on an environment outside the cover.
    Type: Grant
    Filed: September 28, 2012
    Date of Patent: September 22, 2015
    Assignee: THE BOEING COMPANY
    Inventors: Ilsop Steven Yoon, Jeffrey D. Eichinger, Kevin Darrell Pate
  • Patent number: 9036324
    Abstract: A lightning conductor system for a support structure having an external face intended to be subjected to a flow of air and an internal face opposite the external face, the lightning conductor system comprising an electrically conducting lightning conductor strip, intended to be placed on the side of the internal face of the support structure while being connected to ground, and means of fixing the lightning conductor strip to the support structure, the fixing means comprising fixing studs intended to be inserted into orifices formed in the support structure, said fixing studs being in electrical contact with the lightning conductor strip. The lightning conductor system includes the lightning conductor strip being mounted in an offset manner with respect to the main axes of the fixing studs.
    Type: Grant
    Filed: December 17, 2013
    Date of Patent: May 19, 2015
    Assignee: Airbus Operations (SAS)
    Inventors: Jean-Claude Marty, Jacques Fournie, Christophe Bernus, Thony Dupas
  • Patent number: 9036323
    Abstract: A system for lightning protection for power feeders may include at least one unshielded power feeder conductor; and a grounded wire extending adjacent the at least one unshielded power feeder conductor and being electrically isolated therefrom, whereby lightning current flowing through the grounded wire establishes a magnetic field sufficient to oppose and reduce lightning-induced current on the at least one power feeder conductor.
    Type: Grant
    Filed: March 22, 2013
    Date of Patent: May 19, 2015
    Assignee: The Boeing Company
    Inventor: Jeffrey J. White
  • Patent number: 9019683
    Abstract: A method for sealing an interface to attenuate high energy currents and voltages traveling thereacross may include forming a cover defining an inner volume shaped to enclose the interface; forming a filled sealant including a semi-rigid sealant mixed with a filler having a multiplicity of discrete particles of different composition than the semi-rigid sealant; placing the filled sealant within the inner volume; and placing the cover containing the filled sealant over the interface such that the filled sealant is adjacent the interface.
    Type: Grant
    Filed: April 24, 2014
    Date of Patent: April 28, 2015
    Assignee: The Boeing Company
    Inventors: Arthur C. Day, James P. Irwin, Eddie Kwon, Carl R. McIver, Kevin E. McCrary
  • Patent number: 8998124
    Abstract: A device has a first electrically conductive component, a second electrically conductive component, and an electrically conductive nanocoating (ECN) electrically connecting the first electrically conductive component to the second electrically conductive component. An aircraft has an engine, a fuselage, and a device having a first electrically conductive component, a second electrically conductive component, and an electrically conductive nanocoating (ECN) electrically connecting the first electrically conductive component to the second electrically conductive component. A method of providing an electrical conduction path includes providing a first electrically conductive component, providing a second electrically conductive component, and decreasing an electrical resistance between the first electrically conductive component and the second electrically conductive component using an electrically conductive nanocoating (ECN).
    Type: Grant
    Filed: March 7, 2013
    Date of Patent: April 7, 2015
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Daniel P. Sottiaux, Hunter Davis
  • Patent number: 8995108
    Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.
    Type: Grant
    Filed: December 11, 2013
    Date of Patent: March 31, 2015
    Assignee: Mitsubishi Aircraft Corporation
    Inventors: Koji Kawahara, Hideo Yamakoshi, Yuichiro Kamino, Atsuhiro Iyomasa, Toru Hashigami
  • Patent number: 8947847
    Abstract: A method for forming a structure having lightning strike protection includes receiving at least one structural layer, receiving at least one lightning strike protection strip disposed on at least one reinforcement layer, automatically applying the at least one lightning strike protection strip disposed on the at least one reinforcement layer onto the at least one structural layer, and forming the at least one structural layer, the at least one lightning strike protection strip, and the at least one reinforcement layer, into the structure. The at least one lightning strike protection strip comprises a first material, and the at least one reinforcement layer comprises a second material different from the first material. The automatically applying may include using at least one of fiber placement equipment, tape laying equipment, and similar automated equipment.
    Type: Grant
    Filed: November 16, 2011
    Date of Patent: February 3, 2015
    Assignee: ADC Acquisition Company
    Inventors: Robert J. Langone, Robert D. Becker
  • Patent number: 8922970
    Abstract: A lightning protection system is provided, typically for use on an outer surface of an aircraft, which includes the use of a lightning protection sheet that includes an electrically conductive film patterned into a plurality of hill features. The lightning protection sheet may additionally include an electrically non-conductive discriminator layer over the electrically conductive film.
    Type: Grant
    Filed: April 15, 2010
    Date of Patent: December 30, 2014
    Assignee: 3M Innovative Properties Company
    Inventor: Larry S. Hebert
  • Patent number: 8918993
    Abstract: Apparatus for bleeding electrical charge and methods for installing a ground stud in a composite structure. The apparatus includes a ground stud and a composite structure including a hole. In one embodiment the ground stud engages the hole in the composite structure in a transition fit. In another embodiment the ground stud is countersunk within the composite structure. Embodiments of the present methods include drilling a hole in the composite structure; inserting the ground stud into the hole such that the ground stud is in electrical contact with conductive fibers within the composite structure; securing the ground stud to the composite structure; and attaching a connective device to the ground stud such that the connective device is in electrical contact with the ground stud. In some embodiments the ground stud and the composite structure engage one another in a transition fit.
    Type: Grant
    Filed: January 24, 2011
    Date of Patent: December 30, 2014
    Assignee: The Boeing Company
    Inventors: Stephen M. Braden, John R. Porter, Nick I. Tavernarakis
  • Publication number: 20140363637
    Abstract: Embodiments of the presently disclosed system include a thin thermoplastic or thermosetting polymer film loaded with non-polymeric inclusions that are susceptible to heating under a time-varying magnetic field. Insertion of this additional heating layer into a structural or semi-structural heterogeneous laminate provides an “on-demand” de-bonding site for laminate deconstruction. For example, in some embodiments when the heating layer is inserted between a cured Carbon-Fiber Reinforced Plastic (CFRP) layer and a Polymeric/Metallic film stackup layer, the heating layer can be selectively heated above its softening point (e.g., by using energy absorbed from a locally-applied time-varying magnetic field) to allow for ease of applique separation from the CFRP layer.
    Type: Application
    Filed: June 6, 2013
    Publication date: December 11, 2014
    Inventors: Daniel J Kovach, Gary E Georgeson, Robert J Miller, Jeffrey D Morgan, Diane C Rawlings
  • Patent number: 8894014
    Abstract: A firing prevention structure of a fuel tank is provided with a double sleeve to pass through a hole formed in a rib, and a supporting structure to support a pipe to pass through the double sleeve. The supporting structure is attached to the rib. The supporting structure is provided with an insulating section which electrically insulates the pipe and the rib. The double sleeve is formed of electrically insulating material. Thus, an ignition source in the fuel tank is prevented.
    Type: Grant
    Filed: February 17, 2010
    Date of Patent: November 25, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventor: Futoshi Yonezawa
  • Patent number: 8876482
    Abstract: A blade for use in a gas turbine engine has an airfoil including a leading edge and a trailing edge. A sheath is positioned at the leading edge and secured to the airfoil by a first adhesive formed of a first material. The sheath is formed of a second material that is distinct from said first material. The first material is less electrically conductive than the second material. A grounding element is in contact with the sheath. The grounding element is in contact with a portion of the airfoil formed of a third material that is more electrically conductive than the first material. The grounding element and the portion of the airfoil together form a ground path from the sheath into the airfoil.
    Type: Grant
    Filed: September 11, 2012
    Date of Patent: November 4, 2014
    Assignee: United Technologies Corporation
    Inventor: James R. Murdock
  • Patent number: 8854787
    Abstract: A bonding lead comprising a core; and a sheath bonded to the core. The core comprises a substrate of fibers coated with nano-objects with at least one dimension between 1 nm and 200 nm. The nano-objects form a continuous electrically conductive network from one end of the bonding lead to the other with some of the nano-objects coating the fibers and others forming bridges between adjacent fibers. The nano-objects may be carbon nanotubes and the core may be woven or knitted. A conductive connector is provided at each end of the bonding lead, for instance a tab formed from an electrically conductive polymer. The lead can be used to dissipate static charge and/or lightning current between components, typically within an aircraft fuel tank.
    Type: Grant
    Filed: August 18, 2011
    Date of Patent: October 7, 2014
    Assignee: Airbus Operations Limited
    Inventors: Andrew Paul Limmack, David Alistair Sutton, Colin John West
  • Publication number: 20140293497
    Abstract: According to an embodiment a current return network assembly, for an aircraft having a predetermined potential lightning strike zone, is mounted within the predetermined potential lightning strike zone. The current return network assembly includes an electrically conductive honeycomb central core that conducts electrical current both through the assembly and through the predetermined potential lightning strike zone. The electrical current is caused by a lightning strike on the aircraft at the predetermined potential lightning strike zone. According to an embodiment, an aircraft has a predetermined potential lightning strike zone. A current return network assembly is within the zone. An electrically conductive honeycomb central core is provided for conducting electrical current through the assembly and through the zone wherein the electrical current has been caused by a lightning strike on the aircraft at the zone.
    Type: Application
    Filed: March 29, 2013
    Publication date: October 2, 2014
    Inventor: The Boeing Company
  • Publication number: 20140293498
    Abstract: A lightning protection system is provided, typically for use on an outer surface of an aircraft, which includes the use of a lightning protection sheet that includes an electrically conductive film and at least one patterned, electrically non-conductive discriminator layer.
    Type: Application
    Filed: June 12, 2014
    Publication date: October 2, 2014
    Inventor: Larry S. Hebert
  • Patent number: 8784589
    Abstract: A method for reworking an electrically conductive layer of a composite skin is disclosed in which a patch replaces the altered section of the electrically conductive layer. The method is performed by removing a portion of the electrically conductive layer to reveal the underlying composite skin. A patch is formed, having an electrically conductive section coupled to an adhesive having a low dielectric breakdown strength, and is then introduced over the underlying composite skin such that the adhesive layer covers the underlying composite skin and overlaps an unremoved portion of the electrically conductive layer. The patch is applied such that the electrically conductive section within the patch covers the adhesive layer and overlaps the unremoved section of the electrically conductive layer. The adhesive layer preferably has a low dielectric breakdown strength, so that electricity from lightning which strikes the composite skin may be conducted through the adhesive.
    Type: Grant
    Filed: April 17, 2012
    Date of Patent: July 22, 2014
    Assignee: The Boeing Company
    Inventors: Patrice K. Ackerman, Steven D. Blanchard, Daniel J. Kovach
  • Patent number: 8760838
    Abstract: A lightning protection system is provided, typically for use on an outer surface of an aircraft, which includes the use of a lightning protection sheet that includes an electrically conductive film and at least one patterned, electrically non-conductive discriminator layer.
    Type: Grant
    Filed: May 6, 2013
    Date of Patent: June 24, 2014
    Assignee: 3M Innovative Properties Company
    Inventor: Larry S. Hebert
  • Patent number: 8755164
    Abstract: The aircraft includes at least one piece of equipment and a composite material part to which the equipment is connected. It is arranged in such a manner that a fault current circuit of the equipment passes via the part.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: June 17, 2014
    Assignee: Airbus Operations (S.A.S)
    Inventors: Francois Pons, Nicolas Larrose
  • Publication number: 20140132289
    Abstract: A lining/fairing panel, in particular a lining/fairing panel for an airborne vehicle such as an aircraft or a spacecraft is provided. The lining/fairing panel includes a panel body having a first surface and a second surface opposite to the first surface, an electrically conductive coating applied to the first surface or the second surface, and a via arranged in the panel body reaching from the first surface to the second surface of the panel body. The via is formed in an inner region of the panel body. The borders of the inner region are spaced apart by a predetermined distance from the borders of the first and second surface of the panel body.
    Type: Application
    Filed: October 30, 2013
    Publication date: May 15, 2014
    Inventors: Matthias Grossmann, Michael Kaste
  • Patent number: 8717735
    Abstract: A seal for attenuating energy from an electrical discharge across an interface may include a cover defining an inner volume containing a filled sealant including a semi-rigid sealant mixed with a filler having a multiplicity of discrete particles of different composition than the semi-rigid sealant such that the filled sealant is adjacent the interface when the cover is placed over said interface. A method for sealing an interface may include forming a cover defining an inner volume shaped to enclose the interface, forming a filled sealant including a semi-rigid sealant mixed with a filler having a multiplicity of discrete particles of different composition than said semi-rigid sealant, placing the filled sealant within said inner volume and placing the cover containing the filled sealant over the interface such that the filled sealant is adjacent the interface.
    Type: Grant
    Filed: December 14, 2011
    Date of Patent: May 6, 2014
    Assignee: The Boeing Company
    Inventors: Arthur C. Day, James P. Irwin, Eddie Kwon, Carl R. McIver, Kevin McCrary
  • Patent number: 8717736
    Abstract: A sealant 34 filled into a cap 30A is caused to overflow through both an opening in a first end portion 30a of the cap 30A and a through-hole 40 of the cap 30A when the cap 30A is pressed against a fastener member 25. With regard to the cap 30A, a ratio between inside diameter D1 of the opening on the side of the first end portion 30a and hole diameter D2 of the through-hole 40 in the second end portion 30b is set as follows: 0.10?D2/D1?0.27.
    Type: Grant
    Filed: January 10, 2013
    Date of Patent: May 6, 2014
    Assignee: Mitsubishi Aircraft Corporation
    Inventors: Yuji Asahara, Hideo Yamakoshi, Atsuhiro Iyomasa, Wataru Nishimura, Takeyasu Tarumi, Yasunori Watanabe, Toru Hashigami, Hiroshi Rikukawa, Hideo Imamura, Naoki Taniguchi
  • Patent number: 8717734
    Abstract: The present disclosure is related to articles, such as aircraft windows and canopies, including a non-conductive substrate and a conductor pattern including one or more trace lines deposited onto the outside of the substrate such that the entire outside surface of the substrate is not coated with the conductor pattern. The present disclosure also provides methods of dissipating electrostatic charge from non-conductive substrates.
    Type: Grant
    Filed: December 12, 2011
    Date of Patent: May 6, 2014
    Assignee: The Boeing Company
    Inventors: Scott R. Johnston, John Koval, Matthew M. Thomas, Robert R. Johnson, Michael P. Gleason, Michael R. Miller, Gregory M. Sisti
  • Patent number: 8711541
    Abstract: In an insulating cover 50A according to the present invention, a dimension of each of an outer-circumferential-side cylindrical part 50c and an inner-circumferential-side cylindrical part 50b fitting in step parts 40 and 41 in an axial direction of a fastener body 25 is set large with respect to a tip covering part 50a covering a tip surface 26a of a fastening member 26. As a result, on an outer circumferential side and an inner circumferential side of the fastening member 26, a distance from a member 22 is sufficiently ensured by the cylindrical part 50b and 50c. The tip covering part 50a is thinner than the cylindrical part 50B and 50c. Therefore, when the fastener body 25 and the fastening member 26 are fastened together, the amount of deformation of the tip covering part 50a in a thickness direction can be made small.
    Type: Grant
    Filed: March 28, 2012
    Date of Patent: April 29, 2014
    Assignee: Mitsubishi Aircraft Corporation
    Inventors: Soichiro Umemoto, Hideo Yamakoshi, Atsuhiro Iyomasa, Toru Hashigami
  • Patent number: 8711540
    Abstract: A device (1) for the installation of a conducting component (2) on a structure (3) made from composite material, the inside of this structure (3) comprising a substance which can be ignited, which comprises an installation element (4) onto which the conducting component (2) is positioned, a conducting insert element (5), by means of which the installation element (4) is joined to the composite material structure (3) by its internal part, a conducting layer (6) arranged on the external part of the installation element (4) and a conducting fixing element (7) which joins the structure (3) and the installation element (4) to the insert element (5) and the conducting layer (6) so that the device (1) defines a low impedance current path through the conducting layer (6) and the insert element (5) through which the energy is dissipated from an atmospheric discharge to the component (2) or to the structure (3), the interior face of the structure (3) remaining isolated.
    Type: Grant
    Filed: February 10, 2011
    Date of Patent: April 29, 2014
    Assignee: Airbus Operations, S.L.
    Inventor: José Ignacio López-Reina Torrijos
  • Patent number: 8699203
    Abstract: A system for dissipating a lightning current produced by a thunderstorm discharge on an avionic equipment installed on the external skin of an aircraft, the external skin being made of a composite material covered with a layer of expanded metal and including an orifice in which there is positioned an aerodynamic plate covering the avionic equipment. The aerodynamic plate is attached to the external skin by a doubler. The system includes at least one metal plate at least partially surrounding the aerodynamic plate and mounted so as to ensure electrical continuity between the doubler and the layer of expanded metal so as to dissipate the lightning current into the layer of expanded metal.
    Type: Grant
    Filed: June 16, 2009
    Date of Patent: April 15, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Amelie Le Louarn, Frederic Labal
  • Patent number: 8687342
    Abstract: A lightning strike protection system for protecting composite structures, an improved lightning strike appliqué (LSA) for such a lightning strike protection system, and a method of protecting composite structures, such as an aircraft fuselage. The LSA is electrically connected to adjacent conductive surfaces, e.g., by a fuzz button or a wire bond inserted in the bottom of the LSA. An adjacent conductive surface may be another LSA, a lightning diverter overlay, or a current return network. Charge, e.g., from a lightning strike to the LSA, flows to the conductive layer through the electrical connector.
    Type: Grant
    Filed: December 21, 2010
    Date of Patent: April 1, 2014
    Assignee: The Boeing Company
    Inventors: Diane C. Rawlings, J. Scott Bauman
  • Patent number: 8675335
    Abstract: In the formation of a fiber reinforced composite material component produced by a resin transfer infusion process such as to have an electrically conductive surface layer for lightning strike protection wherein the component is to be drilled and countersunk to receive an electrically conductive fastener, a localized part of the electrically conductive mesh is deformed so as to be relocated in the countersunk recess thus to ensure electrical contact with the fastener when inserted and to eliminate any gap between the mesh and the fastener, thus determining the electrical conductive integrity of the mesh to avoid arcing in the event of lightning strike attachment.
    Type: Grant
    Filed: October 3, 2008
    Date of Patent: March 18, 2014
    Assignee: Short Brothers PLC
    Inventors: Robert Samuel Wilson, William James Trevor Millar, Jonathan James McConnell
  • Publication number: 20140055906
    Abstract: Fasteners are inserted into a stack of members and terminated with parts having at least one of a dry dielectric coating and an inner dry dielectric seal at select locations to protect against electromagnetic effects (EME).
    Type: Application
    Filed: November 6, 2013
    Publication date: February 27, 2014
    Applicant: THE BOEING COMPANY
    Inventors: Richard P. Whitlock, Peter A. Coronado, Sean D. Morden, Randall A. Rogers
  • Patent number: 8654500
    Abstract: There is provided a lightning-resistant fastener that can secure sufficient lightning-resistance performance at low cost and realize efficiency of field work and improvement of reliability. An insulating coat film 40 is formed in a region opposed to a structural member 22 in a shaft section 25c of a fastener main body 25 and an insulating layer is interposed between the structural member 22 and the shaft section 25c of the fastener main body 25, whereby an electric current is fed along a head section 25b side of the fastener main body 25 and a wing panel 21 when lightning occurs. This suppresses the electric current from flowing to the front end portion side of the fastener main body 25, i.e., the interior side of a wing 20 and prevents arc discharge from occurring inside the wing 20.
    Type: Grant
    Filed: December 15, 2011
    Date of Patent: February 18, 2014
    Assignee: Mitsubishi Aircraft Corporation
    Inventor: Koji Satake
  • Patent number: 8651413
    Abstract: A lightning-protection fastener is provided that is capable of reliably preventing peeling off of an insulation layer during the operation of an aircraft and improving the anti-lightning-strike capability and reliability. There is a lightning-protection fastener that fastens a skin of an aircraft and a structural member positioned inside the skin, in which an insulation layer is melt adhered so as to cover one end surface of a head portion and also to mechanically engage with a fastener-side engagement portion (engagement portion) formed on the end surface.
    Type: Grant
    Filed: September 25, 2008
    Date of Patent: February 18, 2014
    Assignee: Mitsubishi Heavy Industries
    Inventors: Masahiro Kashiwagi, Yuichiro Kamino, Kazuyuki Oguri, Takeyasu Tarumi, Masahiro Bessho, Hideo Yamakoshi, Naomoto Ishikawa
  • Patent number: 8634177
    Abstract: Provided is a coupling structure for airframe components that is capable of ensuring sufficient lightning protection capability. A conductive pattern part 40 made of a conductive material is formed around each fastener member 24 between wing surface panels 21A and 21B. The conductive pattern part 40 is formed, for example, around each of holes 21c and 21d on the plane on which the wing surface panel 21A and the wing surface panel 21B abut against each other. Then, the conductive pattern part 40 is pushed against both the wing surface panel 21A and the wing surface panel 21B by the fastening power of the fastener members 24, whereby electrical conduction between the wing surface panel 21A and the wing surface panel 21B can be achieved.
    Type: Grant
    Filed: March 13, 2012
    Date of Patent: January 21, 2014
    Assignee: Mitsubishi Aircraft Corporation
    Inventors: Koji Kawahara, Hideo Yamakoshi, Yuichiro Kamino, Atsuhiro Iyomasa, Toru Hashigami
  • Patent number: 8625250
    Abstract: A compression-molded part has a conductive layer embedded in the part during molding of the part. The conductive layer is generally adjacent an outer surface of the part and is preferably formed from a mesh, a foil, a pulled screen, or multiple layers of conductive elements. The part is preferably optimized for use on the exterior of an aircraft for lightning-strike or EMI protection or for use as an antenna. Methods for forming the panels of the invention include placing the conductive layer against a mold surface of a compression mold, then forming the compression-molded part with the conductive layer embedded in the part.
    Type: Grant
    Filed: July 19, 2012
    Date of Patent: January 7, 2014
    Assignee: Textron Innovations Inc.
    Inventors: Anthony P. Bergerson, Jason L. Hoyle
  • Publication number: 20140002947
    Abstract: An aircraft assembly comprising a plurality of structural components and an electrically conductive bonding network, wherein at least one of the structural components is formed of material of low electrical conductivity, and the bonding network includes either: at least one substantially planar strip of highly electrically conductive material attached to at least the one structural component, and wherein the strip includes a substantially omega-shaped loop extending out of the plane of the strip; or at least one strip of highly electrically conductive material attached to at least the one structural component, wherein the strip comprises first and second planar attachment portions for attaching the strip to the structural component(s) and an intermediate portion extending between the first and second attachment portions, and wherein the intermediate portion includes a loop which extends outwards from the plane of the first attachment portion.
    Type: Application
    Filed: March 9, 2012
    Publication date: January 2, 2014
    Applicant: Airbus Operations Limited
    Inventors: Alan Quayle, James Wilson, Jon Mcalinden, Paul Hadley
  • Publication number: 20130329333
    Abstract: A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. The aerospace vehicle is operated. The fluid transport system in the aerospace vehicle is comprised of materials selected such that the fluid transport system has an electrical configuration. The intensity of the electrical discharge that occurs within the fluid transport system during operation of the aerospace vehicle is reduced to within selected tolerances by the electrical configuration of the fluid transport system.
    Type: Application
    Filed: January 23, 2013
    Publication date: December 12, 2013
    Applicant: THE BOEING COMPANY
    Inventors: David William Minteer, James Patrick Irwin, Benjamin A. Johnson, John Thomas Axtell
  • Patent number: 8587916
    Abstract: A long-life lightning protection fastener or the like to prevent explosion for aircrafts at low cost is provided, the fastener having a light weight, ensuring sufficient lightning protection, and having extremely less failures and high reliability. A ring-shaped ring member 40A made of resin is mounted on a collar 26. This ring member 40A is interposed between a member 22 and the collar 26 and is in intimate contact with both of the member 22 and the collar 26, thereby sealing an interface with the member 22 for sealing and preventing the occurrence of an arc at an outer perimeter edge of the collar 26.
    Type: Grant
    Filed: March 14, 2012
    Date of Patent: November 19, 2013
    Assignee: Mitsubishi Aircraft Corporation
    Inventors: Hideo Yamakoshi, Yuichiro Kamino, Yuji Asahara, Yasunori Watanabe, Atsuhiro Iyomasa, Toru Hashigami, Kohei Murakami, Tomonori Okumura
  • Patent number: 8544508
    Abstract: A telescoping tube for fuel transfer operations has a fixed part and a moving part, the moving part further having a dynamic sealing system which guarantees the sealing of the moving part against the fixed part, a cushioning system which absorbs the energy of the impact of the moving part against the fixed part in operations for extending and retracting the tube and protection systems against electrical discharges which ground the moving part to the fixed part, the aforementioned dynamic sealing, cushioning and protection systems all being incorporated in a single unit in the moving part of the telescoping tube. Additionally, the invention relates to an in-flight refuelling system for a tanker aeroplane, to carry out in-flight fuel transfer operations to a receiving aircraft, having a telescoping tube with the abovementioned characteristics.
    Type: Grant
    Filed: March 9, 2010
    Date of Patent: October 1, 2013
    Assignee: EADS Construcciones Aeronauticas, S.A.
    Inventor: Ricardo Fernández Calviño
  • Publication number: 20130242453
    Abstract: A lightning protection system is provided, typically for use on an outer surface of an aircraft, which includes the use of a lightning protection sheet that includes an electrically conductive film and at least one patterned, electrically non-conductive discriminator layer.
    Type: Application
    Filed: May 6, 2013
    Publication date: September 19, 2013
    Applicant: 3M INNOVATION PROPERTIES COMPANY
    Inventor: Larry S. Hebert
  • Patent number: 8520358
    Abstract: There are provided a lightning-resistant fastener and a cap, which, while assuring sufficient insulation properties, provide improved workability and highly stable quality to thereby enable a reduction in the manufacturing cost of an airframe, and a method of mounting the lightning-resistant fastener. A hole 32 is formed in a cap 30, and a screw groove 32a is formed in the hole 32. The configuration enables the cap 30 to be reliably and easily positioned and installed on a fastener member 24 and reliably prevents the cap 30 from coming off after the installation thereof. This improves the workability to reduce the production cost while assuring sufficient insulation properties and enables the cap 30 to be installed with stable quality irrespective of workers. Preferably, the cap 30 is made of a resin in view of mass producibility, weight reduction, and the like.
    Type: Grant
    Filed: April 2, 2010
    Date of Patent: August 27, 2013
    Assignee: Mitbushi Aircraft Corporation
    Inventors: Masahiro Bessho, Wataru Nishimura, Naomoto Ishikawa, Yuichiro Kamino, Toshikatsu Nohara, Toru Hashigami, Tamaki Tsuzuki