US20140117022A1 - Composite Structures Having Bondlines with Matched Electrical Conductivity - Google Patents

Composite Structures Having Bondlines with Matched Electrical Conductivity Download PDF

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Publication number
US20140117022A1
US20140117022A1 US13/663,543 US201213663543A US2014117022A1 US 20140117022 A1 US20140117022 A1 US 20140117022A1 US 201213663543 A US201213663543 A US 201213663543A US 2014117022 A1 US2014117022 A1 US 2014117022A1
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US
United States
Prior art keywords
laminates
bondline
scrim
adhesive
electrical impedance
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US13/663,543
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English (en)
Inventor
Patrice K. Ackerman
Diane L. Heidlebaugh
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Priority to US13/663,543 priority Critical patent/US20140117022A1/en
Assigned to THE BOEING COMPANY reassignment THE BOEING COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ACKERMAN, PATRICE K., HEIDLEBAUGH, DIANE L.
Priority to PT137739108T priority patent/PT2922756T/pt
Priority to KR1020157007320A priority patent/KR101901003B1/ko
Priority to BR112015006821-9A priority patent/BR112015006821B1/pt
Priority to EP13773910.8A priority patent/EP2922756B9/en
Priority to PT181629932T priority patent/PT3375712T/pt
Priority to PCT/US2013/059329 priority patent/WO2014070313A2/en
Priority to ES13773910.8T priority patent/ES2681344T3/es
Priority to JP2015539599A priority patent/JP6306600B2/ja
Priority to ES18162993T priority patent/ES2794907T3/es
Priority to EP18162993.2A priority patent/EP3375712B1/en
Priority to CA2883719A priority patent/CA2883719C/en
Priority to CN201380049712.6A priority patent/CN104661916B/zh
Publication of US20140117022A1 publication Critical patent/US20140117022A1/en
Priority to US15/914,128 priority patent/US10981336B2/en
Priority to JP2018041512A priority patent/JP6585212B2/ja
Abandoned legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/4855—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by their physical properties, e.g. being electrically-conductive
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5021—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being multi-layered
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5007—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like
    • B29C65/5028—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like characterised by the structure of said adhesive tape, threads or the like being textile in woven or non-woven form
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/50—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like
    • B29C65/5057—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding using adhesive tape, e.g. thermoplastic tape; using threads or the like positioned between the surfaces to be joined
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/112—Single lapped joints
    • B29C66/1122—Single lap to lap joints, i.e. overlap joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/01—General aspects dealing with the joint area or with the area to be joined
    • B29C66/05—Particular design of joint configurations
    • B29C66/10—Particular design of joint configurations particular design of the joint cross-sections
    • B29C66/11—Joint cross-sections comprising a single joint-segment, i.e. one of the parts to be joined comprising a single joint-segment in the joint cross-section
    • B29C66/114—Single butt joints
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/41—Joining substantially flat articles ; Making flat seams in tubular or hollow articles
    • B29C66/43—Joining a relatively small portion of the surface of said articles
    • B29C66/434—Joining substantially flat articles for forming corner connections, fork connections or cross connections
    • B29C66/4344—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces
    • B29C66/43441—Joining substantially flat articles for forming fork connections, e.g. for making Y-shaped pieces with two right angles, e.g. for making T-shaped pieces, H-shaped pieces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/731—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the intensive physical properties of the material of the parts to be joined
    • B29C66/7314—Electrical and dielectric properties
    • B29C66/73141—Electrical conductivity
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/02—Tanks
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/02—Lightning protectors; Static dischargers
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/40—Maintaining or repairing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72141—Fibres of continuous length
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72143—Fibres of discontinuous lengths
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/712—Containers; Packaging elements or accessories, Packages
    • B29L2031/7172—Fuel tanks, jerry cans
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
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    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49826—Assembling or joining
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T403/00—Joints and connections
    • Y10T403/47—Molded joint
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/13—Hollow or container type article [e.g., tube, vase, etc.]
    • Y10T428/1352—Polymer or resin containing [i.e., natural or synthetic]
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24942—Structurally defined web or sheet [e.g., overall dimension, etc.] including components having same physical characteristic in differing degree

Definitions

  • This disclosure generally relates to techniques for bonding composite structures, and deals more particularly with methods for mitigating the effects of lightning strikes at bondlines.
  • Fiber reinforced composite structures such as, without limitation, carbon fiber reinforced plastics (CFRP) may be bonded together along a bondline using a structural adhesive.
  • the bondline may be strengthened and reinforced by introducing one or more layers of scrim into the adhesive.
  • an electrically conductive scrim may be placed in the bondline.
  • a problem arises, however, when portions of the bondline are exposed to the ambient environment. A lightning strike may generate an undesirable electrical potential across the bondline.
  • the exposed areas of the bondline are covered with an electrically insulating sealant.
  • sealants are effective, they increase the weight of the aircraft, and are both time-consuming and labor-intensive, adding to manufacturing costs.
  • the disclosed methods provide composite structures joined together along bondlines that have electrical conductivities which are matched to the structures which they join.
  • the use of bondlines having conductivities matched to those of the structures reduces an electrical potential across exposed portions of the bondline.
  • the use of sealants to cover exposed portions of bondlines may be reduced or eliminated, thereby reducing aircraft weight and manufacturing costs.
  • a composite laminate structure comprising first and second fiber reinforced plastic resin laminates each having an electrical impedance, and a structural bondline joining the first and second laminates together.
  • the bondline has an electrical impedance substantially matching the electrical impedance of the first and second laminates.
  • the fiber reinforcement in each of the first and second fiber reinforced plastic resin laminates are carbon fibers, and the bondline includes an adhesively impregnated scrim having an electrical impedance that substantially matches the electrical impedance of the first and second laminates. At least a portion of the bondline is exposed to an ambient environment.
  • the first and second laminates and the bondline may form a T-joint.
  • the first and second laminates may form part of a fuel tank having an open interior, and in which a portion of the bondline is exposed to the open interior of the fuel tank.
  • the bondline includes an adhesively impregnated scrim having an AC (alternating current) conductivity that substantially matches the AC conductivity of the first and second laminates.
  • a composite laminate structure comprising a first carbon fiber reinforced plastic laminate having a first electrical impedance, and a second carbon fiber reinforced plastic laminate having a second electrical impedance substantially matching the first electrical impedance.
  • the laminate structure further includes an adhesive bondline between the first and second laminates.
  • the adhesive bond includes an adhesive and a scrim having a third electrical impedance substantially matching the first and second electrical impedances.
  • the first and second laminates may form part of a fuel tank having an open interior adapted to store fuel, wherein a portion of the adhesive bondline is exposed to the open interior of the fuel tank.
  • the first and second laminates and the adhesive bondline may form a T-joint.
  • Each of the first, second and third electrical impedances include a resistive component and a reactive component.
  • the resistive components are substantially equal, and the reactive components are substantially equal.
  • the scrim may be formed of carbon fibers.
  • the first and second laminates and the bondline have substantially the same AC conductivity.
  • a composite aircraft fuel tank is provided with lightning protection.
  • the lighting protection comprises at least a first carbon fiber reinforced plastic laminate wall, at least a second carbon fiber reinforced plastic laminate wall, and an adhesive bondline joining the first and second laminate walls, the adhesive bondline including an electrically conductive scrim having an electrical impedance substantially matching the electrical impedance of each of the first and second laminate walls. At least a portion of the adhesive bondline is adapted to be exposed to fuel vapors within the fuel tank.
  • a method of providing lightning protection for a bond joint between two cured carbon fiber reinforced plastic laminates comprises installing scrim in the bond joint having an electrical impedance that substantially matches the electrical impedance each of the two carbon fiber reinforced plastic laminates.
  • Installing the scrim includes impregnating the scrim with an adhesive.
  • the adhesive may be one of a film adhesive and a paste adhesive.
  • the scrim may be formed of carbon fibers.
  • the laminates and the scrim may possess substantially the same electrical conductivity.
  • Installing the scrim in the bond joint includes assembling the two laminates in a T-shaped configuration, and placing the scrim between an edge of one of the two laminates, and a face of the other of the two laminates.
  • a method is provided of reducing the electrical potential across an exposed bondline between two, carbon fiber reinforced plastic laminates. The method comprises determining the electrical conductivity of each of the two laminates, selecting a scrim having an electrical conductivity substantially matching the determined electrical conductivity of each of the two laminates, installing the scrim and an adhesive between the two laminates, and curing the adhesive.
  • a method is provided of fabricating a composite structure having an exposed bond protected against lightning strikes.
  • the method comprises laying up first and second carbon fiber reinforced plastic pre-preg laminates, curing the first and second pre-preg laminates, and joining the first and second cured laminates with a bond joint.
  • Joining the first and second cured laminates with the bond joint may include selecting a scrim having an electrical impedance substantially matching the electrical impedance of each of the first and second laminates, impregnating the scrim with a bonding adhesive, installing the impregnated scrim between the first and second laminates to form a bondline, and curing the adhesive.
  • FIG. 1 is an illustration of a perspective view of a bonded composite structure having a bondline employing electrically conductive scrim according to the disclosed embodiments.
  • FIG. 2 is an illustration of an end view of the area designated as FIG. 2 in FIG. 1 .
  • FIG. 3 is an illustration of a cross-sectional view of two laminate structures joined together by a lap joint employing the disclosed scrim.
  • FIG. 4 is an illustration of a perspective view of the scrim along with two layers of adhesive used to form the bondline.
  • FIG. 5 is an illustration of a graph showing electrical current flow resulting from a typical lightning strike.
  • FIG. 6 is an illustration of a circuit diagram of an impedance.
  • FIG. 7 is an illustration of a perspective view of an aircraft fuel tank, portions broken away to reveal the interior of the tank.
  • FIG. 8 is an illustration of a flow diagram of a method of co-curing two composite pre-pregs along a bondline.
  • FIG. 9 is an illustration of a flow diagram of a method of fabricating a bonded precured structure employing the disclosed scrim.
  • FIG. 10 is an illustration of a flow diagram of aircraft production and service methodology.
  • FIG. 11 is an illustration of a block diagram of an aircraft.
  • a composite structure 20 comprises first and second composite pre-pregs 24 , 26 , which may be formed of by laying up pre-preg plies, such as a CFRP.
  • the first and second pre-pregs 24 , 26 together are joined together along a bondline 22 between a face 29 of the first pre-preg 24 and an edge 27 of the second pre-preg 26 , effectively forming a butt joint 31 .
  • the bondline 22 includes exposed portions 28 , 30 at the ends of the bondline 22 , which are exposed to the surrounding ambient environment.
  • the bondline 22 has an electrical conductivity ⁇ 1 and impedance Z 1 that substantially match the electrical conductivity ⁇ 2 and impedance Z 2 of each of the first and second pre-pregs 24 , 26 .
  • This matching of the electrical conductivities ⁇ 1 , ⁇ 2 and impedances Z 1 , Z 2 reduces or eliminates build-up of an undesirable electrical potential or charge “V” ( FIG. 2 ) between the pre-pregs 24 , 26 along the exposed portions 28 , 30 of the bondline 22 .
  • the disclosed bondline 22 may be employed to form other types of bonded joints between two laminate structures.
  • the disclosed bondline 22 may be employed to form a lap joint 35 between first and second composite pre-pregs 24 , 26 .
  • the bondline 22 also has exposed portions 28 , 30 which need not be sealed as a result of the electrical conductivity ⁇ l and impedance Z 1 of the bondline 22 being matched to the electrical conductivity ⁇ 2 and impedance Z 2 of the first and second pre-pregs 24 , 26 .
  • FIG. 4 illustrates the components used to form the bondline 22 .
  • a scrim 32 is sandwiched between two layers 34 , 36 of a suitable structural adhesive.
  • the scrim 32 may be in any of the numerous configurations such as, without limitation, a mesh, knitted mat or random fiber mat comprising intersecting strands of electrically conductive fibers.
  • the conductive fibers have an AC conductivity ⁇ 1 and an impedance Z 1 respectively matching the AC conductivity ⁇ 2 and impedance Z 2 of the first and second pre-pregs 24 , 26 .
  • the fibers may comprise a single material, or may comprise fibers of multiple types of materials which collectively have the required AC conductivity ⁇ 1 and impedance Z 1 matched to the AC conductivity ⁇ 2 and impedance Z 2 of the pre-pregs 24 , 26 .
  • first and second pre-pregs 24 , 26 comprising CFRPs
  • the fibers of the scrim 32 may also be formed of carbon fibers similar or identical to those forming the carbon fiber reinforcement in the first and second pre-pregs 24 , 26 . While only a single layer of scrim 32 is illustrated in FIG. 4 , multiple layers of the scrim 32 may be employed in a single bondline 22 .
  • Each of the adhesive layers 34 , 36 may comprise an adhesive resin film or an adhesive resin paste which adheres to the CFRP plies of the pre-pregs 24 , 26 .
  • the scrim 32 may be embedded into and adhere to each of the adhesive layers 34 , 36 , as by pressing the scrim 32 into the adhesive layers 34 , 36 .
  • Other techniques for integrating bonding adhesive with the scrim 32 may be possible, including impregnating the scrim 32 with the adhesive.
  • the scrim 32 is configured to provide continuous electrical conductivity throughout the bondline 22 and may also serve as a binding matrix.
  • the scrim 32 possesses an AC conductivity ⁇ 1 and an impedance Z 1 that substantially match the electrical conductivity ⁇ 2 and impedance Z 2 of each of the composite pre-pregs joined by the bondline 22 .
  • Electrical conductivity ⁇ is a measure of the material's ability to conduct electric current. In the case of a lightning strike causing electrical current to flow through the pre-pregs 24 , 26 , and through the bondline 22 , the current flow is typically not constant, but varies, similar to an alternating current (AC).
  • FIG. 5 is a graph showing electrical current flow 37 over time 39 , produced by a typical lightning strike.
  • the current flow begins with a sharp spike 43 at the initial lightning attachment 41 , then decays slowly during time period “B”, may be somewhat constant during time period “C”, and then quickly increases during time period “D”, forming another sharp spike 45 immediately before detachment at 47 .
  • the pre-pregs 24 , 26 , and the scrim 32 each have respective AC conductivities ⁇ 1 , ⁇ 2 and respective impedances Z 1 , Z 2 ( FIGS. 2 and 3 ).
  • FIG. 6 is a circuit diagram representing the components of each of the impedances Z 1 , Z 2 .
  • the reactive component X or “reactance”, includes inductance L and capacitance C, and represents the opposition of the scrim 32 , viewed as a circuit, to a change of electric current or voltage caused by the lightning strike.
  • the current flow through the pre-pregs 24 , 26 passes unimpeded through the bondline 22 , rather “seeing” a discontinuity in the bondline 22 which may results in the build-up of an undesirable electrical potential or charge “V” ( FIG. 2 ) across the bondline 22 in the area of the exposed portions 28 , 30 .
  • the bondline 22 described above having a “matched” electrical conductivity ⁇ 1 and a “matched” impedance Z 1 may be used in a wide variety of composite laminate structures to mitigate the effects electrical current flows due to lightning strikes.
  • the disclosed bondline 22 may be employed in a composite aircraft fuel tank 42 shown in FIG. 7 .
  • the fuel tank 42 includes a composite laminate top 44 , bottom 46 and sides 48 , 50 forming an internal volume 55 .
  • the fuel tank 42 may further include internal ribs 52 as well as a baffle walls 54 , each of which are bonded along its top and bottom edges to the top and bottom walls 44 , 46 respectively, by a T-joint and bondline 22 similar to that shown in FIGS. 1 and 2 which use the scrim 32 shown in FIG. 4 .
  • the disclosed bondline 22 may also be employed to bond the repair patches (not shown) to underlying composite structures, such as CFRP laminate skins.
  • FIG. 8 illustrates the overall steps of a method of reducing the buildup of an electrical potential or charge across a bond line 22 in the area of exposed portions 28 , 30 of the bondline 22 between two pre-pregs 24 , 26 subjected to the effects of lightning strikes.
  • the electrical conductivities ⁇ 2 of each of the two pre-pregs 24 , 26 are determined.
  • scrim used in the bondline 22 is selected which has an electrical conductivity ⁇ 1 substantially matching the electrical conductivity ⁇ 2 of each of the two pre-pregs 24 , 26 .
  • the scrim 32 along with the adhesive is installed between the pre-pregs 24 , 26 , following which the pre-pregs 24 , 26 and the pre-pregs and the adhesive are co-cured at step 62 .
  • FIG. 9 broadly illustrates the steps of a method of fabricating a CFRP laminate structure 20 having bondlines 22 provided with lightning protection.
  • first and second CFRP pre-pregs 24 , 26 are laid up, and formed to shape, as required.
  • each of the first and second CFRP pre-pregs 24 , 26 are cured to form laminates.
  • a scrim 32 is selected having an electrical impedance Z 1 substantially matching the electrical impedance Z 2 of the first and second pre-preg laminates 24 , 26 .
  • the scrim 32 is impregnated or otherwise integrated into a suitable bonding adhesive.
  • the impregnated scrim is installed between surfaces of the first and second pre-preg laminates 24 , 26 to form a bondline 22 which may include exposed portions 28 , 30 .
  • the adhesive is cured.
  • Embodiments of the disclosure may find use in a variety of potential applications, particularly in the transportation industry, including for example, aerospace, marine, automotive applications and other application where autoclave curing of composite parts may be used.
  • embodiments of the disclosure may be used in the context of an aircraft manufacturing and service method 76 as shown in FIG. 10 and an aircraft 78 as shown in FIG. 11 .
  • Aircraft applications of the disclosed embodiments may include, for example, without limitation, fabrication of composite laminate assemblies and subassemblies requiring bonded joints that require protection against the effects of lightning strikes on an aircraft.
  • exemplary method 76 may include specification and design 80 of the aircraft 78 and material procurement 82 .
  • component and subassembly manufacturing 84 and system integration 86 of the aircraft 78 takes place. Thereafter, the aircraft 78 may go through certification and delivery 88 in order to be placed in service 90 . While in service by a customer, the aircraft 78 is scheduled for routine maintenance and service 92 , which may also include modification, reconfiguration, refurbishment, and so on.
  • Each of the processes of method 76 may be performed or carried out by a system integrator, a third party, and/or an operator (e.g., a customer).
  • a system integrator may include without limitation any number of aircraft manufacturers and major-system subcontractors
  • a third party may include without limitation any number of vendors, subcontractors, and suppliers
  • an operator may be an airline, leasing company, military entity, service organization, and so on.
  • the aircraft 78 produced by exemplary method 76 may include an airframe 94 with a plurality of systems 96 and an interior 98 .
  • high-level systems 96 include one or more of a propulsion system 100 , an electrical system 102 , a hydraulic system 104 , and an environmental system 106 . Any number of other systems may be included.
  • an aerospace example is shown, the principles of the disclosure may be applied to other industries, such as the marine and automotive industries.
  • Systems and methods embodied herein may be employed during any one or more of the stages of the production and service method 76 .
  • components or subassemblies corresponding to production process 84 may be fabricated or manufactured in a manner similar to components or subassemblies produced while the aircraft 96 is in service.
  • one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during the production stages 84 and 86 , for example, by substantially expediting assembly of or reducing the cost of an aircraft 78 .
  • apparatus embodiments, method embodiments, or a combination thereof may be utilized while the aircraft 78 is in service, for example and without limitation, to maintenance and service 92 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Textile Engineering (AREA)
  • Laminated Bodies (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
US13/663,543 2012-10-30 2012-10-30 Composite Structures Having Bondlines with Matched Electrical Conductivity Abandoned US20140117022A1 (en)

Priority Applications (15)

Application Number Priority Date Filing Date Title
US13/663,543 US20140117022A1 (en) 2012-10-30 2012-10-30 Composite Structures Having Bondlines with Matched Electrical Conductivity
CN201380049712.6A CN104661916B (zh) 2012-10-30 2013-09-12 包括具有匹配导电率的胶层的复合结构
PCT/US2013/059329 WO2014070313A2 (en) 2012-10-30 2013-09-12 Composite structures having bondlines with matched electrical conductivity
JP2015539599A JP6306600B2 (ja) 2012-10-30 2013-09-12 一致した導電率を有するボンドラインを有する複合構造
BR112015006821-9A BR112015006821B1 (pt) 2012-10-30 2013-09-12 Estrutura laminada compósita, método para reduzir o potencial elétrico através de uma linha de contato exposta, e, tanque de combustível de aeronave
EP13773910.8A EP2922756B9 (en) 2012-10-30 2013-09-12 Composite structures having bondlines with matched electrical conductivity
PT181629932T PT3375712T (pt) 2012-10-30 2013-09-12 Estruturas compósitas que têm linhas de adesão com impedância elétrica correspondente
PT137739108T PT2922756T (pt) 2012-10-30 2013-09-12 Estruturas compósitas que têm linhas de adesão com condutividade elétrica correspondente
ES13773910.8T ES2681344T3 (es) 2012-10-30 2013-09-12 Estructuras de material compuesto que tienen líneas de unión con conductividad eléctrica empareada
KR1020157007320A KR101901003B1 (ko) 2012-10-30 2013-09-12 전기 전도도가 정합하는 접합면을 가지는 복합 구조체
ES18162993T ES2794907T3 (es) 2012-10-30 2013-09-12 Estructuras de material compuesto que tienen líneas de unión con impedancia eléctrica empareada
EP18162993.2A EP3375712B1 (en) 2012-10-30 2013-09-12 Composite structures having bondlines with matched electrical impedance
CA2883719A CA2883719C (en) 2012-10-30 2013-09-12 Composite structures having bondlines with matched electrical conductivity
US15/914,128 US10981336B2 (en) 2012-10-30 2018-03-07 Composite structures having bondlines with matched electrical conductivity
JP2018041512A JP6585212B2 (ja) 2012-10-30 2018-03-08 一致した導電率を有するボンドラインを有する複合構造

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US13/663,543 US20140117022A1 (en) 2012-10-30 2012-10-30 Composite Structures Having Bondlines with Matched Electrical Conductivity

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EP (2) EP3375712B1 (pt)
JP (2) JP6306600B2 (pt)
KR (1) KR101901003B1 (pt)
CN (1) CN104661916B (pt)
BR (1) BR112015006821B1 (pt)
CA (1) CA2883719C (pt)
ES (2) ES2681344T3 (pt)
PT (2) PT3375712T (pt)
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JP6585212B2 (ja) 2019-10-02
KR101901003B1 (ko) 2018-09-20
CA2883719C (en) 2018-05-29
PT3375712T (pt) 2020-04-07
EP2922756B9 (en) 2018-08-22
ES2794907T3 (es) 2020-11-19
KR20150079568A (ko) 2015-07-08
US10981336B2 (en) 2021-04-20
EP3375712B1 (en) 2020-03-11
US20180194073A1 (en) 2018-07-12
JP6306600B2 (ja) 2018-04-04
WO2014070313A3 (en) 2014-06-26
EP2922756A2 (en) 2015-09-30
EP3375712A1 (en) 2018-09-19
CN104661916B (zh) 2016-11-09
PT2922756T (pt) 2018-07-30
CA2883719A1 (en) 2014-05-08
WO2014070313A2 (en) 2014-05-08
EP2922756B1 (en) 2018-04-25
CN104661916A (zh) 2015-05-27
ES2681344T3 (es) 2018-09-12
JP2018127211A (ja) 2018-08-16
JP2016502477A (ja) 2016-01-28
BR112015006821A2 (pt) 2017-07-04
BR112015006821B1 (pt) 2022-05-24

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