GB2226801A - Screw fasteners for lightning strike protection of composite structures in aircraft - Google Patents
Screw fasteners for lightning strike protection of composite structures in aircraft Download PDFInfo
- Publication number
- GB2226801A GB2226801A GB8926942A GB8926942A GB2226801A GB 2226801 A GB2226801 A GB 2226801A GB 8926942 A GB8926942 A GB 8926942A GB 8926942 A GB8926942 A GB 8926942A GB 2226801 A GB2226801 A GB 2226801A
- Authority
- GB
- United Kingdom
- Prior art keywords
- aircraft structure
- threaded member
- screw fastener
- fastener assembly
- component
- 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.)
- Granted
Links
- 239000002131 composite material Substances 0.000 title description 7
- 238000013022 venting Methods 0.000 claims abstract description 3
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 239000002184 metal Substances 0.000 claims description 7
- 101100334009 Caenorhabditis elegans rib-2 gene Proteins 0.000 description 12
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 9
- 229910052799 carbon Inorganic materials 0.000 description 7
- 239000000835 fiber Substances 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 239000011208 reinforced composite material Substances 0.000 description 4
- 239000000565 sealant Substances 0.000 description 3
- 239000002828 fuel tank Substances 0.000 description 2
- 229910002804 graphite Inorganic materials 0.000 description 2
- 239000010439 graphite Substances 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 229920003023 plastic Polymers 0.000 description 2
- 239000004033 plastic Substances 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 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
- 230000006378 damage Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000011810 insulating material Substances 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 229920000573 polyethylene Polymers 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
-
- 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
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
- F16B35/04—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws with specially-shaped head or shaft in order to fix the bolt on or in an object
- F16B35/041—Specially-shaped shafts
-
- 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
- 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
-
- 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
-
- 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
- F16B35/00—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws
- F16B35/04—Screw-bolts; Stay-bolts; Screw-threaded studs; Screws; Set screws with specially-shaped head or shaft in order to fix the bolt on or in an object
-
- 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
- F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
- F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
- F16B5/0208—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread using panel fasteners, i.e. permanent attachments allowing for quick assembly
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
A screw fastener assembly for attaching one component 1 of an aircraft structure to another 2, comprising a male threaded member 4 for passing through a hole 10 in a first component of an aircraft and co-operating with a second female threaded member 21 adapted to engage a second component 2 of the aircraft structure, wherein there is provided means 24 for venting hot gaseous spark products generated at the interface between the first and second components of the aircraft structure and the male threaded member in the event of a lightning strike to the aircraft structure in the region of the screw fastener assembly either to the outside of the aircraft structure or to an enclosed ballast volume 23 forming part of the female threaded member. <IMAGE>
Description
Screw Fasteners for Aeronautical Use
The present invention relates to screw fasteners for attaching one component of an air or spacecraft structure to another.
Hereinafter, the term aircraft is to be understood as including spacecraft where appropriate.
Modern aircraft incorporate skin panels and other structural components which are made of fibre reinforced composite materials. Usually the composite materials consist of graphite fibres in a matrix of a plastics material. Typically, the electrical conductivity of such composite materials is some three orders of magnitude less than those of the aluminium or magnesium based alloys which conventionally are used to build aircraft. Graphite fibre composite aircraft structures can be damaged by transient electrical currents arising from events such as lightning strikes.
Lightning currents can be concentrated at screw fasteners and the resultant current density at the composite/fastener interface can destroy the composite locally. Under these conditions it is not possible to prevent hot gaseous spark products being formed.
According to the present invention there is provided a screw fastener assembly for attaching one component of an aircraft structure to another, comprising a male threaded member for passing through a hole in a first component of an aircraft and co-operating with a second female threaded member adapted to engage a second component of the aircraft structure, wherein there is provided means for venting hot gaseous spark products generated at the interface between the first and second components of the aircraft structure and the male threaded member in the event of a lightning strike to the aircraft structure in the region of the screw fastener assembly either to the outside of the aircraft structure or to an enclosed ballast volume forming part of the female threaded member.
In one embodiment of the invention the female threaded member comprises two concentric cylinders joined together at one end so as to provide an annular chamber the inner wall of which projects beyond the outer wall there being a series of longitudinal corrugations formed in the outer face of the inner wall and a screw thread for receiving the male threaded member formed on its inner surface.
The projection of the inner wall beyond the outer wall is such that in use the outer wall buts against the second component and the junction is sealed by an insultating washer. Thus the space between the inner and outer walls of the female threaded member forms the enclosed ballast volume into which spark products produced when lightning current flows betweeen the two components of the aircraft structure pass via the corrugations in the outer wall of the female threaded member.
Preferably the corrugations are in the form of splines and the fastener is used in conjunction with a hole in the second component of a size such that the inner member is an interference fit within it.
In a second embodiment of the invention, holes are formed in the male threaded member which in use provide communication between the interface between the male threaded member and the two components of the aircraft and the exterior of the aircraft so that any spark products produced when lightning current flows between the two components of the aircraft structure are vented to the outside of the aircraft structure.
The invention will now be explained and described with reference to the accompanying drawings, in which:
Figure 1 is a cross-section of a portion of a
conventional bolted joint in a carbon
reinforced composite aircraft wing fuel
tank,
Figure 2 is a cross-sectional view of a similar
joint embodying the present invention,
Figure 3 is a cross-sectional view of another joint
embodying the present invention,
Figure 4 is a cross-sectional view of another joint
embodying the invention,
Figure 5 is a cross-sectional view of another joint
embodying the invention
Figure 6 is a cross-sectional view of another joint
embodying the invention.
Referring to Figure 1, there is shown a portion of a conventional bolted joint between a skin panel 1 made of a carbon reinforced composite material which forms part of an aircraft wing fuel tank and a supporting rib 2, which also is made of carbon fibre reinforced composite material.
Between the inner surface of the panel 1 and the rib 2 is a layer of non-conducting sealant 3. The panel 1 and rib 2 are clamped together by means of a countersunk screw 4, passing through holes 10 and 11 in the panel 1 and rib 2, respectively, a washer 5 and a nut 6. The screw 4 has a cross-head driving recess 7. Alternatively, the nut 6 may be of the captive type and form one of a series attached directly to the rib 2 or to a metal strip positioned along the rib 2. In this case, the washer 5 is omitted.
In the event of a lightning strike, pulse currents will penetrate into and flow through the panel 1 but will have difficulty in crossing the joint between the panel 1 and the rib 2 both because of the layer 3 of sealant and because the process of manufacture of panels of carbon fibre reinforced composite materials results in matrix rich layers on each surface in which there are no carbon fibres.
On the other hand, cut ends of carbon fibres are exposed in the side of the hole 10 in the panel 1 through which the screw 4 passes. However, the cylindrical part 8 of the hole 10 has to be of a clearance size with respect to the screw 4 so at best there will be only line contact between the screw 4 and the panel 1. Therefore the only region where good electrical contact will be made between the screw 4 and the exposed ends of the carbon fibres in the panel 1 will be the conical portion 9 of the hole 10. A similar problem arises in connection with the hole 11 in the rib 2, which again has to be of a clearance size. Thus although lightning pulse currents have a reasonably good path into the screw 4 via the conical portion 9 of the hole 10 in the panel 1, they will have difficulty leaving it.
The problem is even worse should a lightning strike actually attach to the screw 4 in which case the local current density will be much greater. The poor nature of the exit contact from the screw 4 results in localised heating and sparking which cause both electrical interference on internal wiring and the danger of igniting fuel vapour in the 'wing tank of which the panel 1 and rib 2 form part.
Figure 2 shows a corresponding portion of a joint embodying the present invention, and similar features are given the same reference numerals. Referring to Figure 2, the hole 11 in the rib 2 is made to be considerably oversize in relation to the screw 4 and the nut 6 is replaced by a female member consisting of two concentric cylinders 21 and 22 which are joined together at one end to provide an annular chamber 23. The inner cylinder 21 has a series of splines 24 machined in its outer surface and a screw thread 25 formed on its inner surface. To make this clearer, a cross-section of the appropriate part of the cylinder 21 also is hown in Figure 2.The inner cylinder 21 projects beyond the outer cylinder 22 by an amount somewhat less than the combined thickness of the second component of the aircraft structure 2 and an insulating washer 26 so that, in use, when the screw 4 is tightened the outer cylinder 22 buts firmly against the insulating washer 26 so as to seal the annular chamber 23 and so provide a containment vessel for any spark products formed at the interface between the screw 4 and the components 1 and 2 of the aircraft structure as a result of lightning currents flowing in the aircraft structure. The spark products gain access to the chamber 23 via the splines 24 in the inner wall 21 of the chamber 23. In this way the ejection of hot spark products into the region surrounding the rib 2 of the aircraft structure via channels forced through the sealant 3 by the spark products is prevented.
Figure 3 shows another embodiment of the invention.
Again components which correspond to those already described have the same reference numerals. In this embodiment of the invention the screw 4 has a series of holes and channels 31 formed in it which provide communication between the interface between the screw 4 and the components 1 and 2 of the aircraft structure and the outside of the aircraft structure. Thus any spark products formed at the interface between the screw 4 and the components 1 and 2 of the aircraft structure and in the region of the joint between them as a result of lightning currents circulating in the aircraft structure are vented to the outside of the aircraft structure.As a further precaution in the arrangement shown in Figure 3, the nut 6 is replaced by a blind nut 34 which has a counterbore 32 in its open end, which provides a containment volume for any spark products which are not vented to the outside of the aircraft structure.
Figure 4 shows another arrangement in which the nut 6 retains a sintered metal tube 41 which again forms a containment vessel 23 into which gases and spark products are allowed to vent. In this case however the gases are allowed to escape through the sintered metal tube 41 having been cooled to below an incendive temperature during their passage through the sintered metal tube 41. Spark particles, however, are retained by the sintered metal tube 41. In this way, a build up of pressure within the containment 23 is prevented.
Figure 5 shows another embodiment of the invention.
Again features common with features at other embodiments have the same reference numerals. In this embodiment of the invention, a double containment vessel is used. The nut 6 is replaced by a cylindrical blind nut 51 the outer surface of which has a land 52 formed in it. An inner cylinder 53 rests on this land and is an interference fit with the nut 51. Also formed in the periphery of the nut 51 are grooves for two O-rings 54. An outer cylinder 55 surrounds the nut 51 and the inner cylinder 53 and co-operates with the O-rings 54 to provide an outer containment vessel 56 surrounding an inner containment vessel 57. A series of dished spring washers 58 bears against the free end of the cylinder 55 and urges it against the insulating washer 5. Loading is applied to the washers 58 via a cap nut 59.
The shank of the screw 4 has a series of slots 60 milled in it which enable gases and spark products formed at the interface between the screw 4 and the components 1 and 2 of the aircraft structure in the region of the joint between them as a result of lightning currents circulating in the aircraft structure to be vented into the inner containment vessel 57.
The inner cylinder 53 is urged against the washer 5 by the land 52 on the nut 51 as the screw 4 is tightened into it. If during service there is a slackening of the screw 4, for example because of local destruction of the skin 1 of the aircraft, due to the passage of lightning current so that the seal between the cylinder 53 and the washer 5 is lost, then any gas or spark products escaping into the outer vessel 56 will be trapped there because the seal between the outer cylinder 55 and washer 5 will be maintained by the spring washers 58.
Figure 6 shows another embodiment of the invention which is similar to that described with reference to figure 2 except that it includes an outer cap 61 which has a flange 62 by means of which it is attached to the rib 2 by means of countersunk rivets 63, the insulating washer 26 being extended appropriately. The rivets 63 also are isolated electrically from the outer envelope 61.
The base of the inner cylinder 21 is in the form of a nut 64 with an abutment 65 on which the outer cylinder 22 bears. Alternatively, the cylinders 21, 22 and nut 64 can be integral. The bottom of the nut 64, as shown, has a square cross-section and an abutment 66 is formed in it.
The inner surface of the bottom of the outer cap 61 is shaped to conform to the bottom of the nut 64 but with an annular gap 67 which is filled by a hollow square section torque-transmitting member 68. The torque-transmitting member 68 is made of a plastic insulating material. A polythene insulating disk 69 is interposed between the nut 64 and the outer cap 61. The whole assembly acts as a captive nut for the bolt 4 thus removing the need for internal access or a spanner for assembly as well as a double containment system like that described with reference to Figure 5.
Claims (9)
1 A screw Fastener assembly for attaching one component of an aircraft structure to another, comprising a male threaded member for passing through a hole in a first component of an aircraft and co-operating with a second female threaded member adapted to engage a second component of the aircraft structure, wherein there is provided means for venting hot gaseous spark products generated at the interface between the first and second components of the aircraft structure and the male threaded member in the event of a lightning strike to the aircraft structure in the region of the screw fastener assembly either to the outside of the aircraft structure or to an enclosed ballast volume forming part of the female threaded member.
2 A screw fastener assembly according to claim 1 wherein the female threaded member comprises two concentric cylinders joined together at one end so as to provide an annular chamber the inner wall of which projects beyond the outer wall there being a series of longitudinal corrugations formed in the outer face of the inner wall and a screw thread for receiving the male threaded member formed on its inner surface.
3 A screw fastener according to claim 2 wherein the corrugations are in the form of splines.
4 A screw fastener assembly according to any preceding claim wherein the closed ballast volume is surrounded by an outer containment volume adaptd to retain any spark products which escape from the ballast volume.
5 A screw fastener assembly according to claim 4 wherein the outer containment volume is capable of moving longitudinally with relation to the ballast volume and there is provided resilient means for urging the outer containment volume against the second component of the aircraft structure.
6 A screw fastener assembly according to claim 4 wherein the outer containment volume is adapted to be attached permanently to the second component of the aircraft structure.
. . .
7 A screw fastener assembly according to claim 1 wherein there is included a blind nut, a sintered metal tube adaptd to cooperate with the blind nut, and the male threaded member has a shank portion with longitudinal depressions formed therein, the arrangment being such that in use the sintered metal tube is caused to abut the second component of the aircraft structure to form the closed ballast volume surrounding the male threaded member and the longitudinal depressions formed in the shank of the male threaded member provide communication between the interface between the male-threaded member and the first and second components of the aircraft structure and the ballast volume.
8 A screw fastener assembly according to claim 1 wherein the male threaded member has holes formed in it such that in use there is provided communication between the interface between the male threaded member and the two components of the aircraft structure so that any spark products produced when lightning current flows between the two components of the aircraft structure are vented to the outside of the aircraft structure.
9 A screw fastener assembly for attaching one component of an aircraft structure to another substantially as hereinbefore described and with reference to figures 2 to 6 of the accompanying drawings.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB888828025A GB8828025D0 (en) | 1988-12-01 | 1988-12-01 | Screw fasteners for aeronautical use |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB8926942D0 GB8926942D0 (en) | 1990-01-17 |
| GB2226801A true GB2226801A (en) | 1990-07-11 |
| GB2226801B GB2226801B (en) | 1992-07-08 |
Family
ID=10647768
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB888828025A Pending GB8828025D0 (en) | 1988-12-01 | 1988-12-01 | Screw fasteners for aeronautical use |
| GB8926942A Expired - Fee Related GB2226801B (en) | 1988-12-01 | 1989-11-29 | Screw fasteners for aeronautical use |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB888828025A Pending GB8828025D0 (en) | 1988-12-01 | 1988-12-01 | Screw fasteners for aeronautical use |
Country Status (1)
| Country | Link |
|---|---|
| GB (2) | GB8828025D0 (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5175665A (en) * | 1989-10-27 | 1992-12-29 | British Aerospace Public Limited Company | Lighting resistant composite structures |
| FR2718706A1 (en) * | 1994-04-15 | 1995-10-20 | Aerospatiale | Anti-spark structure, especially for aircraft. |
| US6913225B2 (en) * | 2000-11-24 | 2005-07-05 | Saab Ericsson Space Ab | Construction and method of use in a carrier rocket or satellite |
| FR2917475A1 (en) * | 2007-06-13 | 2008-12-19 | Airbus France Sa | REVOLUTION PIECES HAVING DUST EVACUATION GROOVES. |
| WO2010113523A1 (en) * | 2009-04-02 | 2010-10-07 | 三菱航空機株式会社 | Lightning-resistant fastener, cap, and method of mounting lightning-resistant fastener |
| EP2256030A1 (en) * | 2008-03-24 | 2010-12-01 | Mitsubishi Heavy Industries, Ltd. | Aircraft assembly |
| JP2012061873A (en) * | 2010-09-14 | 2012-03-29 | Mitsubishi Aircraft Corp | Lightning-resistant fastener, cap, and method of the mounting lightning-resistant fastener |
| WO2012107741A1 (en) | 2011-02-10 | 2012-08-16 | Airbus Operations Limited | Cap for forming sealed cavity around fastener |
| EP2620360A1 (en) * | 2012-01-24 | 2013-07-31 | EADS Construcciones Aeronauticas, S.A. | Fire protection device for aircraft |
| JP2013224142A (en) * | 2009-04-02 | 2013-10-31 | Mitsubishi Aircraft Corp | Lightning-resistant fastener, aircraft and method of mounting lightning-resistant fastener |
| CN105473445A (en) * | 2013-08-21 | 2016-04-06 | 空中客车营运有限公司 | Cap with injected sealant |
| EP3078597A1 (en) * | 2015-04-10 | 2016-10-12 | The Boeing Company | Lightning damage resistant aircraft skin fasteners |
| EP3225555A1 (en) * | 2016-03-31 | 2017-10-04 | The Boeing Company | Conformal clearance fit fastener, fastener system, and method for composite structures |
| EP3498609A1 (en) * | 2017-12-13 | 2019-06-19 | Airbus Operations Limited | Assembly with captive nut |
| US10385907B2 (en) | 2015-02-20 | 2019-08-20 | Airbus Operations Limited | Cap with injected sealant |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0334011A1 (en) * | 1988-02-18 | 1989-09-27 | The Boeing Company | Arc suppression around fasteners during a lightning strike |
-
1988
- 1988-12-01 GB GB888828025A patent/GB8828025D0/en active Pending
-
1989
- 1989-11-29 GB GB8926942A patent/GB2226801B/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0334011A1 (en) * | 1988-02-18 | 1989-09-27 | The Boeing Company | Arc suppression around fasteners during a lightning strike |
Cited By (33)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5175665A (en) * | 1989-10-27 | 1992-12-29 | British Aerospace Public Limited Company | Lighting resistant composite structures |
| FR2718706A1 (en) * | 1994-04-15 | 1995-10-20 | Aerospatiale | Anti-spark structure, especially for aircraft. |
| WO1995028319A1 (en) * | 1994-04-15 | 1995-10-26 | Aerospatiale Societe Nationale Industrielle | Sparkproof structure |
| US5709356A (en) * | 1994-04-15 | 1998-01-20 | Aerospatiale Societe Nationale Industrielle | Anti-spark structure, in particular for aircraft |
| US6913225B2 (en) * | 2000-11-24 | 2005-07-05 | Saab Ericsson Space Ab | Construction and method of use in a carrier rocket or satellite |
| US8240945B2 (en) | 2007-06-13 | 2012-08-14 | Airbus Operations Sas | Axisymmetric parts equipped with dust removal grooves |
| FR2917475A1 (en) * | 2007-06-13 | 2008-12-19 | Airbus France Sa | REVOLUTION PIECES HAVING DUST EVACUATION GROOVES. |
| EP2256030A4 (en) * | 2008-03-24 | 2013-10-02 | Mitsubishi Heavy Ind Ltd | Aircraft assembly |
| EP2256030A1 (en) * | 2008-03-24 | 2010-12-01 | Mitsubishi Heavy Industries, Ltd. | Aircraft assembly |
| WO2010113523A1 (en) * | 2009-04-02 | 2010-10-07 | 三菱航空機株式会社 | Lightning-resistant fastener, cap, and method of mounting lightning-resistant fastener |
| US9334065B2 (en) | 2009-04-02 | 2016-05-10 | Mitsubishi Aircraft Corporation | Lightning-resistant fastener, cap, and method of mounting lightning-resistant fastener |
| JP2010254287A (en) * | 2009-04-02 | 2010-11-11 | Mitsubishi Aircraft Corp | Lightning-resistant fastener, cap, and method of mounting lightning-resistant fastener |
| US8520358B2 (en) | 2009-04-02 | 2013-08-27 | Mitbushi Aircraft Corporation | Lightning-resistant fastener, cap, and method of mounting lightning-resistant fastener |
| JP2013224142A (en) * | 2009-04-02 | 2013-10-31 | Mitsubishi Aircraft Corp | Lightning-resistant fastener, aircraft and method of mounting lightning-resistant fastener |
| JP2012061873A (en) * | 2010-09-14 | 2012-03-29 | Mitsubishi Aircraft Corp | Lightning-resistant fastener, cap, and method of the mounting lightning-resistant fastener |
| US9228604B2 (en) | 2011-02-10 | 2016-01-05 | Airbus Operations Limited | Cap for forming sealed cavity around fastener |
| EP3366593A1 (en) * | 2011-02-10 | 2018-08-29 | Airbus Operations Limited | Cap for forming sealed cavity around fastener |
| US9506493B2 (en) | 2011-02-10 | 2016-11-29 | Airbus Operations Limited | Cap for forming sealed cavity around fastener |
| WO2012107741A1 (en) | 2011-02-10 | 2012-08-16 | Airbus Operations Limited | Cap for forming sealed cavity around fastener |
| EP2620360A1 (en) * | 2012-01-24 | 2013-07-31 | EADS Construcciones Aeronauticas, S.A. | Fire protection device for aircraft |
| US10415623B2 (en) | 2013-08-21 | 2019-09-17 | Airbus Operations Limited | Cap with injected sealant |
| CN105473445B (en) * | 2013-08-21 | 2017-10-03 | 空中客车营运有限公司 | The cap of sealant with injection |
| CN105473445A (en) * | 2013-08-21 | 2016-04-06 | 空中客车营运有限公司 | Cap with injected sealant |
| US10774869B2 (en) | 2013-08-21 | 2020-09-15 | Airbus Operations Limited | Cap with injected sealant |
| US10385907B2 (en) | 2015-02-20 | 2019-08-20 | Airbus Operations Limited | Cap with injected sealant |
| US9669942B2 (en) | 2015-04-10 | 2017-06-06 | The Boeing Company | Lightning damage resistant aircraft skin fasteners |
| EP3078597A1 (en) * | 2015-04-10 | 2016-10-12 | The Boeing Company | Lightning damage resistant aircraft skin fasteners |
| EP3225555A1 (en) * | 2016-03-31 | 2017-10-04 | The Boeing Company | Conformal clearance fit fastener, fastener system, and method for composite structures |
| US10385908B2 (en) | 2016-03-31 | 2019-08-20 | The Boeing Company | Conformal clearance fit fastener, fastener system, and method for composite structures |
| EP3498609A1 (en) * | 2017-12-13 | 2019-06-19 | Airbus Operations Limited | Assembly with captive nut |
| EP3677512A1 (en) * | 2017-12-13 | 2020-07-08 | Airbus Operations Limited | Assembly with captive nut |
| US11286031B2 (en) | 2017-12-13 | 2022-03-29 | Airbus Operations Limited | Assembly with captive nut |
| US20220169365A1 (en) * | 2017-12-13 | 2022-06-02 | Airbus Operations Limited | Assembly with captive nut |
Also Published As
| Publication number | Publication date |
|---|---|
| GB8828025D0 (en) | 1989-01-05 |
| GB2226801B (en) | 1992-07-08 |
| GB8926942D0 (en) | 1990-01-17 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |
Effective date: 19951129 |