WO1999051494A1 - Adhesively bonded joints in carbon fibre composite structures - Google Patents
Adhesively bonded joints in carbon fibre composite structures Download PDFInfo
- Publication number
- WO1999051494A1 WO1999051494A1 PCT/GB1999/001032 GB9901032W WO9951494A1 WO 1999051494 A1 WO1999051494 A1 WO 1999051494A1 GB 9901032 W GB9901032 W GB 9901032W WO 9951494 A1 WO9951494 A1 WO 9951494A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- adhesive
- carbon fibre
- composite structures
- carbon
- fibres
- Prior art date
Links
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 title claims abstract description 58
- 229910052799 carbon Inorganic materials 0.000 title claims abstract description 58
- 239000000835 fiber Substances 0.000 title claims abstract description 42
- 239000002131 composite material Substances 0.000 title claims abstract description 41
- 239000000853 adhesive Substances 0.000 claims abstract description 35
- 230000001070 adhesive effect Effects 0.000 claims abstract description 35
- 239000011347 resin Substances 0.000 claims abstract description 4
- 229920005989 resin Polymers 0.000 claims abstract description 4
- 230000005540 biological transmission Effects 0.000 claims abstract description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical group [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 5
- 229910052802 copper Inorganic materials 0.000 claims description 5
- 239000010949 copper Substances 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 3
- 239000002828 fuel tank Substances 0.000 description 5
- 239000000446 fuel Substances 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 239000012141 concentrate Substances 0.000 description 2
- 239000000945 filler Substances 0.000 description 2
- 238000004026 adhesive bonding Methods 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000012768 molten material Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- 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
- 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
- B29C65/4865—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding containing additives
- B29C65/487—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding containing additives characterised by their shape, e.g. being fibres or being spherical
- B29C65/488—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding containing additives characterised by their shape, e.g. being fibres or being spherical being longitudinal, e.g. 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
- 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
- B29C65/4865—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding containing additives
- B29C65/4885—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding containing additives characterised by their composition being non-plastics
-
- 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
- B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
- B29C65/562—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits using extra joining elements, i.e. which are not integral with the parts 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
- B29C66/13—Single flanged joints; Fin-type joints; Single hem joints; Edge joints; Interpenetrating fingered joints; Other specific particular designs of joint cross-sections not provided for in groups B29C66/11 - B29C66/12
- B29C66/131—Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area
-
- 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
- B29C66/47—Joining single elements to sheets, plates or other substantially flat surfaces
- B29C66/474—Joining single elements to sheets, plates or other substantially flat surfaces said single elements being substantially non-flat
-
- 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
- B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
- B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
- B29C66/52—Joining tubular articles, bars or profiled elements
- B29C66/524—Joining profiled elements
-
- 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
- B29C66/72—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
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- 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
- B29C65/4805—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 the type of adhesives
- B29C65/483—Reactive adhesives, e.g. chemically curing adhesives
-
- 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
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
- B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2307/00—Use of elements other than metals as reinforcement
-
- 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
Definitions
- This invention relates to adhesively bonded joints in carbon fibre composite structures or hybrids thereof.
- Carbon fibre composites or hybrids thereof comprising one or more laminates or plies are being used increasingly for aircraft structures in place of the aluminium or metallic compounds formerly used. Although carbon fibre composite structures are generally stronger and stiffer than their metallic counterparts, nevertheless they lack the lightning strike tolerance of the metallic components.
- a lightning strike to an aircraft causes a high electric current, which may typically be of the order of a hundred thousand amps, to flow through the aircraft frame.
- the carbon fibre plies act as very high resistance conductors and the resin in the composite acts as a highly capacitive dielectric so that lightning striking carbon fibre composite results in an increasing potential difference across the ply structure but no readily available electrically conductive path for discharging the current.
- the current therefore tends to concentrate at the structural joints making them particularly vulnerable to damage.
- Lightning current flowing in an airframe can produce voltage stresses across adhesively bonded joints. If the stresses exceed the joint's dielectric strength, the insulation will break down. This may lead to arcing and sparking which can cause extensive damage to the joint and explosive fuel ignition if in contact with fuel or fuel vapour.
- the present invention seeks to overcome the problems of high electric currents flowing across adhesively bonded joints in carbon fibre composite structures, including those close to fuel, without compromising structural integrity.
- a structural joint for the transmission and control of high current flows in a carbon fibre or carbon fibre hybrid composite structure comprising:- at least two composite structures comprising a multiplicity of resin bonded carbon fibre plies; an adhesive applied there between and capable of conducting high currents through and away from the joint; said adhesive including a conductive carrier film comprising carbon fibres, wherein the adhesive has an electrical conductivity comparable with that of the adjacent composite structures.
- the carbon fibres in the adhesive are in the form of a lightweight scrim.
- the carbon fibres in the adhesive may be in the form of chopped fibres.
- An electrically conductive layer may be incorporated in or be applied to an outer surface of at least one of said composite structures.
- This electrically - 3 - conductive layer is preferably a copper strip.
- Conductive fasteners may be in contact with the electrically conductive layer.
- an adhesive for bonding carbon fibre or carbon fibre hybrid composite structures and capable of conducting high current comprises a conductive carrier film comprising carbon fibres.
- the electrical conductivity of the adhesive is comparable with that of the carbon fibre or carbon fibre hybrid composite structures to be bonded.
- the carbon fibres in the adhesive are preferably in the form of a lightweight scrim.
- the carbon fibres may be in the form of chopped fibres.
- a method of forming a structural joint includes the steps of providing two or more carbon fibre or carbon fibre hybrid composite structures, applying an adhesive therebetween and curing the joint, wherein the adhesive comprises a conductive carrier film including carbon fibres and has an electrical conductivity comparable with that of the adjacent composite structures.
- the adhesive comprises few, if any, metallic fillers.
- Structural joints according to the present invention allow composite structures to be adhesively bonded together without the need for mechanical fasteners whilst displaying similar strength characteristics as traditionally fastened joints, making them ideal for applications requiring high performance, lightning resistant, joints.
- structural joints according to the present invention having a conductivity comparable to that of the carbon fibre composite are advantageous in aircraft lightning protection arrangements, particularly in bonding aircraft skin panels to an aircraft substructure, which may for example be the wall of the fuel tank, where the panels and substructure are made from carbon fibre composites.
- Figure 1 is a cross-section through an adhesively bonded joint in a carbon fibre composite structure
- Figure 2 is a cross-section through an alternative form of adhesively bonded joint in a carbon fibre composite structure
- Figure 3 is a cross-section through a further form of adhesively bonded joint in a carbon fibre composite structure.
- a structural adhesive 3 is shown securing a ⁇ kin panel 1 of an aircraft structure to an inner substructure 2 comprising the wall of a fuel tank.
- Both the skin panel 1 and the substructure 2 are made of carbon fibre composite material of low weight and high strength, having a percentage of 50-60% carbon fibre in the composite material.
- the adhesive 3 is a film adhesive containing a conductive carbon fibre carrier film, where the carbon fibres may typically be in the form of a lightweight scrim or chopped fibres.
- the adhesive 3 has an electrical conductivity comparable to that of the composites 1 and 2. Ideally, the percentage of carbon fibre in the adhesive 3 is typically 10-25%, and the adhesive 3 comprises little or no metallic fillers.
- a thin copper strip 4 is incorporated in the outside surface of the skin 1 and runs the full length of the joint.
- the copper strip 4 is in electrical contact with the carbon fibre composite structure and further enhances the lightning tolerance of the joint by providing a preferential low resistance path for the lightning current.
- Figure 3 shows a further embodiment, again using identical reference numerals to indicate similar parts to those shown in Figures 1 and 2.
- Figure 3 illustrates a structural arrangement having mechanical fasteners 5 placed across a joint where the mechanical fasteners 5 are in contact with the copper strip 4. This embodiment further enhances the lightning tolerance of the joint by reducing the voltage stress across the joint.
- structural joints according to the invention may be used in applications other than aircraft bodies, for example they may be used in the structures of launch vehicles and missiles, and indeed any application where the joints may be exposed to a lightning strike or other high voltage.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Adhesives Or Adhesive Processes (AREA)
- Laminated Bodies (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE69908924T DE69908924D1 (en) | 1998-04-04 | 1999-04-01 | ADHESIVE JOINTS FOR USE IN CARBON FIBER COMPOSITE MATERIAL |
EP99913513A EP1068130B1 (en) | 1998-04-04 | 1999-04-01 | Adhesively bonded joints in carbon fibre composite structures |
AU31624/99A AU758909B2 (en) | 1998-04-04 | 1999-04-01 | Adhesively bonded joints in carbon fibre composite structures |
JP55018599A JP3391467B2 (en) | 1998-04-04 | 1999-04-01 | Joint with adhesive bond in carbon fiber composite structure |
US09/397,867 US6320118B1 (en) | 1998-04-04 | 1999-09-17 | Adhesively bonded joints in carbon fibre composite structures |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB9807198.8A GB9807198D0 (en) | 1998-04-04 | 1998-04-04 | Adhesively bonded joints in carbon fibre composite structures |
GB9807198.8 | 1998-04-04 |
Related Child Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US09/397,867 Continuation US6320118B1 (en) | 1998-04-04 | 1999-09-17 | Adhesively bonded joints in carbon fibre composite structures |
Publications (1)
Publication Number | Publication Date |
---|---|
WO1999051494A1 true WO1999051494A1 (en) | 1999-10-14 |
Family
ID=10829818
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/GB1999/001032 WO1999051494A1 (en) | 1998-04-04 | 1999-04-01 | Adhesively bonded joints in carbon fibre composite structures |
Country Status (8)
Country | Link |
---|---|
US (1) | US6320118B1 (en) |
EP (1) | EP1068130B1 (en) |
JP (1) | JP3391467B2 (en) |
AU (1) | AU758909B2 (en) |
DE (1) | DE69908924D1 (en) |
ES (1) | ES2196792T3 (en) |
GB (1) | GB9807198D0 (en) |
WO (1) | WO1999051494A1 (en) |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102006003160A1 (en) * | 2006-01-24 | 2007-09-06 | Airbus Deutschland Gmbh | Surface seal and method for producing sealed joints with the surface seal |
FR2914622A1 (en) * | 2007-04-04 | 2008-10-10 | Airbus France Sas | AIRCRAFT COMPRISING STRUCTURE ENSURING STRUCTURAL AND ELECTRICAL FUNCTIONS |
FR2924685A1 (en) * | 2007-12-11 | 2009-06-12 | Airbus France Sas | PARAFOUDRE AND AIRCRAFT SYSTEM COMPRISING SUCH A SYSTEM. |
WO2009118509A1 (en) * | 2008-03-28 | 2009-10-01 | Hexcel Composites Limited | Improved composite materials |
WO2010046684A1 (en) * | 2008-10-20 | 2010-04-29 | Airbus Operations Limited | Joint between aircraft components |
WO2010099052A3 (en) * | 2009-02-26 | 2010-11-11 | The Boeing Company | Distributing power in systems having a composite structure |
GB2510133A (en) * | 2013-01-24 | 2014-07-30 | Bae Systems Plc | Conductive bonded composites |
EP2832645A4 (en) * | 2012-03-26 | 2015-12-02 | Mitsubishi Heavy Ind Ltd | Fuel tank, main wing, aircraft fuselage, aircraft, and mobile body |
EP2979977A4 (en) * | 2013-03-26 | 2016-12-14 | Mitsubishi Heavy Ind Ltd | Fuel tank, main wings, aircraft fuselage, aircraft, and moving body |
EP3213989A1 (en) * | 2016-03-04 | 2017-09-06 | The Boeing Company | Conductive radius filler system and method |
US10014593B2 (en) | 2013-02-04 | 2018-07-03 | The Boeing Company | Conductive sleeved fastener assembly |
US10046849B2 (en) | 2013-03-26 | 2018-08-14 | Mitsubishi Heavy Industries, Ltd. | Fuel tank, main wings, aircraft fuselage, aircraft, and moving body |
US10186788B2 (en) | 2013-02-04 | 2019-01-22 | The Boeing Company | Sleeved fastener assembly |
EP3511579A1 (en) * | 2018-01-15 | 2019-07-17 | Subaru Corporation | Fastening structure |
US10574018B2 (en) | 2008-11-17 | 2020-02-25 | The Boeing Company | Conductive sleeved fastener assembly |
Families Citing this family (34)
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US7115323B2 (en) * | 2003-08-28 | 2006-10-03 | The Boeing Company | Titanium foil ply replacement in layup of composite skin |
US20050055180A1 (en) * | 2003-09-08 | 2005-03-10 | Pischke Gina C. | Method and system for seat placement |
US7194391B2 (en) * | 2003-09-30 | 2007-03-20 | The Boeing Company | Method and system for seat placement |
US7052573B2 (en) * | 2003-11-21 | 2006-05-30 | The Boeing Company | Method to eliminate undulations in a composite panel |
FR2866991B1 (en) * | 2004-02-26 | 2006-05-19 | Airbus France | ELECTRIC FEED RETURN DEVICE FOR AVIONIC EQUIPMENT |
GB0417473D0 (en) * | 2004-08-05 | 2004-09-08 | Airbus Uk Ltd | Fuel tank |
GB0417472D0 (en) * | 2004-08-05 | 2004-09-08 | Airbus Uk Ltd | Fuel tank system |
WO2006051147A1 (en) * | 2004-11-11 | 2006-05-18 | Gamesa Innovation And Technology, S.L. | Lightning conductor system for wind generator blades comprising carbon fibre laminates |
US7721495B2 (en) * | 2005-03-31 | 2010-05-25 | The Boeing Company | Composite structural members and methods for forming the same |
US7740932B2 (en) | 2005-03-31 | 2010-06-22 | The Boeing Company | Hybrid fiberglass composite structures and methods of forming the same |
US8444087B2 (en) * | 2005-04-28 | 2013-05-21 | The Boeing Company | Composite skin and stringer structure and method for forming the same |
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Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3347978A (en) * | 1963-06-03 | 1967-10-17 | Lockheed Aircraft Corp | Electrically conductive joints and gaskets |
US4556591A (en) * | 1981-09-25 | 1985-12-03 | The Boeing Company | Conductive bonded/bolted joint seals for composite aircraft |
DE3606464A1 (en) * | 1986-02-28 | 1987-09-03 | Licentia Gmbh | Device provided on solar generators for preventing static charges |
WO1992009992A1 (en) * | 1990-12-01 | 1992-06-11 | Henkel Kommanditgesellschaft Auf Aktien | Composition of electrically insulating polymers and electrically conductive fillers |
EP0685389A1 (en) | 1994-06-02 | 1995-12-06 | British Aerospace Public Limited Company | Method of fastening composite aircraft skins |
US5613862A (en) * | 1992-07-18 | 1997-03-25 | Central Research Laboratories Limited | Anisotropic electrical connection |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE2362801C3 (en) | 1973-12-18 | 1979-02-08 | Hoechst Ag, 6000 Frankfurt | Process for applying metallic contact strips to surface heating elements |
US4479163A (en) * | 1982-09-30 | 1984-10-23 | The Boeing Company | Integral lightning protection system for composite aircraft skins |
GB8628555D0 (en) * | 1986-11-28 | 1987-01-07 | British Aerospace | Anti lightning strike fasteners |
JPH0764962B2 (en) * | 1986-12-05 | 1995-07-12 | 日本ユニカ−株式会社 | Heat-resistant conductive adhesive resin composition |
US5127601A (en) * | 1989-01-23 | 1992-07-07 | Lightning Diversion Systems | Conformal lightning shield and method of making |
FR2668580B1 (en) * | 1990-10-30 | 1993-01-22 | Aerospatiale | ANTI-SPARKING STRUCTURE, ESPECIALLY FOR AIRCRAFT. |
US5686703A (en) | 1994-12-16 | 1997-11-11 | Minnesota Mining And Manufacturing Company | Anisotropic, electrically conductive adhesive film |
US5698316A (en) * | 1996-10-07 | 1997-12-16 | The Boeing Company | Apparatus and methods of providing corrosion resistant conductive path across non conductive joints or gaps |
-
1998
- 1998-04-04 GB GBGB9807198.8A patent/GB9807198D0/en not_active Ceased
-
1999
- 1999-04-01 DE DE69908924T patent/DE69908924D1/en not_active Expired - Lifetime
- 1999-04-01 AU AU31624/99A patent/AU758909B2/en not_active Ceased
- 1999-04-01 ES ES99913513T patent/ES2196792T3/en not_active Expired - Lifetime
- 1999-04-01 JP JP55018599A patent/JP3391467B2/en not_active Expired - Fee Related
- 1999-04-01 WO PCT/GB1999/001032 patent/WO1999051494A1/en active IP Right Grant
- 1999-04-01 EP EP99913513A patent/EP1068130B1/en not_active Expired - Lifetime
- 1999-09-17 US US09/397,867 patent/US6320118B1/en not_active Expired - Lifetime
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3347978A (en) * | 1963-06-03 | 1967-10-17 | Lockheed Aircraft Corp | Electrically conductive joints and gaskets |
US4556591A (en) * | 1981-09-25 | 1985-12-03 | The Boeing Company | Conductive bonded/bolted joint seals for composite aircraft |
DE3606464A1 (en) * | 1986-02-28 | 1987-09-03 | Licentia Gmbh | Device provided on solar generators for preventing static charges |
WO1992009992A1 (en) * | 1990-12-01 | 1992-06-11 | Henkel Kommanditgesellschaft Auf Aktien | Composition of electrically insulating polymers and electrically conductive fillers |
US5613862A (en) * | 1992-07-18 | 1997-03-25 | Central Research Laboratories Limited | Anisotropic electrical connection |
EP0685389A1 (en) | 1994-06-02 | 1995-12-06 | British Aerospace Public Limited Company | Method of fastening composite aircraft skins |
Non-Patent Citations (1)
Title |
---|
F.A.FISHER, J.A. PLUMER, R. A. PERALA: "aircraft lightning protection handbook", DOT/FAA/CT-89/22 |
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Also Published As
Publication number | Publication date |
---|---|
JP3391467B2 (en) | 2003-03-31 |
GB9807198D0 (en) | 1998-06-03 |
JP2001510422A (en) | 2001-07-31 |
EP1068130A1 (en) | 2001-01-17 |
US6320118B1 (en) | 2001-11-20 |
DE69908924D1 (en) | 2003-07-24 |
EP1068130B1 (en) | 2003-06-18 |
ES2196792T3 (en) | 2003-12-16 |
AU758909B2 (en) | 2003-04-03 |
AU3162499A (en) | 1999-10-25 |
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