GB2212580B - Methods of fastening composite aircraft skins - Google Patents

Methods of fastening composite aircraft skins

Info

Publication number
GB2212580B
GB2212580B GB8726711A GB8726711A GB2212580B GB 2212580 B GB2212580 B GB 2212580B GB 8726711 A GB8726711 A GB 8726711A GB 8726711 A GB8726711 A GB 8726711A GB 2212580 B GB2212580 B GB 2212580B
Authority
GB
United Kingdom
Prior art keywords
skin panel
methods
composite aircraft
contact
surface region
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.)
Expired - Lifetime
Application number
GB8726711A
Other versions
GB8726711D0 (en
GB2212580A (en
Inventor
Christopher Charles Rawl Jones
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.)
BAE Systems PLC
Original Assignee
British Aerospace PLC
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 British Aerospace PLC filed Critical British Aerospace PLC
Priority to GB8726711A priority Critical patent/GB2212580B/en
Publication of GB8726711D0 publication Critical patent/GB8726711D0/en
Publication of GB2212580A publication Critical patent/GB2212580A/en
Application granted granted Critical
Publication of GB2212580B publication Critical patent/GB2212580B/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B33/00—Features common to bolt and nut
    • F16B33/004—Sealing; Insulation
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R4/00—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation
    • H01R4/58—Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation characterised by the form or material of the contacting members
    • H01R4/64—Connections between or with conductive parts having primarily a non-electric function, e.g. frame, casing, rail
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • 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

Abstract

An anti-lightning fastener for joining an aircraft skin panel 5 made of composite material to a substructural member 6, comprising a bevel headed countersunk bolt 1 and captive nut 4, wherein the bolt 1 has a head surface region 8 of an electrically conductive material 10 for contact with the outer plies 11 of the skin panel 5, and a shank surface region coated with a layer 12 of electrically insulating material for contact with the inner plies of the skin panel and substructural member, whereby lightning is conducted and dissipated controllably and without arcing into the aircraft structure. <IMAGE>
GB8726711A 1987-11-14 1987-11-14 Methods of fastening composite aircraft skins Expired - Lifetime GB2212580B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB8726711A GB2212580B (en) 1987-11-14 1987-11-14 Methods of fastening composite aircraft skins

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB8726711A GB2212580B (en) 1987-11-14 1987-11-14 Methods of fastening composite aircraft skins

Publications (3)

Publication Number Publication Date
GB8726711D0 GB8726711D0 (en) 1987-12-16
GB2212580A GB2212580A (en) 1989-07-26
GB2212580B true GB2212580B (en) 1992-03-25

Family

ID=10626972

Family Applications (1)

Application Number Title Priority Date Filing Date
GB8726711A Expired - Lifetime GB2212580B (en) 1987-11-14 1987-11-14 Methods of fastening composite aircraft skins

Country Status (1)

Country Link
GB (1) GB2212580B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0685389A1 (en) 1994-06-02 1995-12-06 British Aerospace Public Limited Company Method of fastening composite aircraft skins

Families Citing this family (30)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8924231D0 (en) * 1989-10-27 1989-12-13 British Aerospace Carbon fibre composite structures
FR2668580B1 (en) * 1990-10-30 1993-01-22 Aerospatiale ANTI-SPARKING STRUCTURE, ESPECIALLY FOR AIRCRAFT.
FR2718706B1 (en) * 1994-04-15 1996-06-14 Aerospatiale Anti-spark structure, especially for aircraft.
ES2163951B1 (en) * 1998-07-29 2003-05-16 Airbus Espana Sl A PROTECTION SYSTEM AGAINST ELECTRIC SHOCK, ESPECIALLY RAYS, OF STRUCTURAL COMPONENTS OF AIRCRAFT.
ES2162718A1 (en) * 1998-07-29 2002-01-01 Const Aeronauticas Sa Lightning protection system for composite aircraft structures
GB2431213B (en) * 2005-10-14 2007-09-26 Siemens Magnet Technology Ltd Electrically isolating, thermally conducting mechanical joints
EP1832513B1 (en) * 2006-03-06 2008-12-10 Eads Construcciones Aeronauticas S.A. Lightning protected aircraft telescopic refueling mast
GB0620522D0 (en) * 2006-10-16 2006-11-22 Airbus Uk Ltd Lockable fastener assembly
FR2914622B1 (en) 2007-04-04 2009-05-15 Airbus France Sas AIRCRAFT COMPRISING STRUCTURE ENSURING STRUCTURAL AND ELECTRICAL FUNCTIONS
DE102007029337B4 (en) * 2007-06-26 2010-07-22 Airbus Deutschland Gmbh Corrosion resistant connection between a first component and a second component
ES2376323B1 (en) * 2009-02-27 2013-01-24 Airbus Operations, S.L. IMPROVEMENT OF PROTECTION AGAINST DIRECT IMPACT OF RAYS IN RIVED PANEL AREAS IN CFRP.
DE102009026686A1 (en) * 2009-06-03 2010-12-23 Airbus France Arrangement for lightning protection of an electronic unit
DE102010040338A1 (en) * 2010-09-07 2012-03-08 Airbus Operations Gmbh Attachment element e.g. countersunk rivet for use as aircraft component, has head that is provided with electrical isolating portion in region of electrical conductive layers of component
JP5473892B2 (en) * 2010-12-28 2014-04-16 三菱航空機株式会社 Lightning-resistant fasteners, aircraft
GB201101311D0 (en) * 2011-01-26 2011-03-09 Airbus Uk Ltd Fastener assembly
US9802715B2 (en) * 2012-03-29 2017-10-31 The Boeing Company Fastener systems that provide EME protection
FR3008754B1 (en) * 2013-07-19 2015-09-04 Lisi Aerospace METAL FASTENING
US9908637B2 (en) * 2014-05-23 2018-03-06 The Boeing Company Modified shank fasteners for electromagnetic effect (EME) technology
US9939004B2 (en) 2014-09-17 2018-04-10 Arconic Inc Coated fasteners with conforming seals
CA2955271C (en) 2014-09-17 2019-04-23 Arconic Inc. Fasteners with coated and textured pin members
FR3026446B1 (en) 2014-09-30 2017-12-01 Lisi Aerospace LUBRICATED INTERFERENCE FASTENING
WO2017039779A1 (en) * 2015-08-28 2017-03-09 Arconic Inc. Coated fasteners with conforming seals
US10329030B2 (en) * 2016-03-04 2019-06-25 The Boeing Company Conductive radius filler system and method
EP3231713A1 (en) * 2016-04-13 2017-10-18 Airbus Operations GmbH Fastener system for ignition prevention triggered by a lightning strike, structure comprising the fastener system, and method for manufacturing the structure
US10495130B2 (en) 2016-11-11 2019-12-03 The Boeing Company Fasteners having enhanced electrical energy dispersion properties
JP6852176B2 (en) 2016-12-13 2021-03-31 アーコニック インコーポレイテッドＡｒｃｏｎｉｃ Ｉｎｃ． Reduced electromagnetic signature of conformal conical seal fastener system
CN107379961A (en) * 2017-07-20 2017-11-24 河北世昌汽车部件有限公司 A kind of fuel tank
GB2569315A (en) 2017-12-13 2019-06-19 Airbus Operations Ltd Assembly with captive nut
US11137014B2 (en) 2019-01-08 2021-10-05 The Boeing Company Conductive fastening system and method for improved EME performance
CN114180083B (en) * 2021-11-19 2023-09-01 中国直升机设计研究所 Method for conducting electricity between composite structural members by using copper cups

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1261249A (en) * 1968-05-17 1972-01-26 Ernst Beer A method of improving an electrically conductive connection
GB1394130A (en) * 1971-09-01 1975-05-14 Illinois Tool Works Fasteners
GB1444427A (en) * 1972-10-20 1976-07-28 Wennersten B Electrical cable connector
GB1460888A (en) * 1972-10-25 1977-01-06 Seward W H Bolts or studs
WO1984000255A1 (en) * 1982-06-30 1984-01-19 Boeing Co Fastening device and method for composite structures
EP0226229A2 (en) * 1985-12-16 1987-06-24 The Boeing Company Lightning protection fastener
GB2189563A (en) * 1986-04-25 1987-10-28 Camloc Ind Fixings Fastener with non-conductive cap
US4718801A (en) * 1986-07-24 1988-01-12 Microdot Inc. Composite core fastener

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1261249A (en) * 1968-05-17 1972-01-26 Ernst Beer A method of improving an electrically conductive connection
GB1394130A (en) * 1971-09-01 1975-05-14 Illinois Tool Works Fasteners
GB1444427A (en) * 1972-10-20 1976-07-28 Wennersten B Electrical cable connector
GB1460888A (en) * 1972-10-25 1977-01-06 Seward W H Bolts or studs
WO1984000255A1 (en) * 1982-06-30 1984-01-19 Boeing Co Fastening device and method for composite structures
EP0226229A2 (en) * 1985-12-16 1987-06-24 The Boeing Company Lightning protection fastener
GB2189563A (en) * 1986-04-25 1987-10-28 Camloc Ind Fixings Fastener with non-conductive cap
US4718801A (en) * 1986-07-24 1988-01-12 Microdot Inc. Composite core fastener

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0685389A1 (en) 1994-06-02 1995-12-06 British Aerospace Public Limited Company Method of fastening composite aircraft skins

Also Published As

Publication number Publication date
GB8726711D0 (en) 1987-12-16
GB2212580A (en) 1989-07-26

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Legal Events

Date Code Title Description
PE20 Patent expired after termination of 20 years

Effective date: 20071113