WO2007063146A1 - Estructura de material compuesto con fibra optica embebida en una de sus capas superficiales y procedimiento para su conexión y reparacion - Google Patents
Estructura de material compuesto con fibra optica embebida en una de sus capas superficiales y procedimiento para su conexión y reparacion Download PDFInfo
- Publication number
- WO2007063146A1 WO2007063146A1 PCT/ES2005/070167 ES2005070167W WO2007063146A1 WO 2007063146 A1 WO2007063146 A1 WO 2007063146A1 ES 2005070167 W ES2005070167 W ES 2005070167W WO 2007063146 A1 WO2007063146 A1 WO 2007063146A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- optical fiber
- embedded
- composite material
- repair
- composite
- Prior art date
Links
- 239000013307 optical fiber Substances 0.000 title claims abstract description 54
- 239000002131 composite material Substances 0.000 title claims abstract description 32
- 238000000034 method Methods 0.000 title claims abstract description 23
- 239000002344 surface layer Substances 0.000 title claims abstract description 14
- 230000008439 repair process Effects 0.000 claims abstract description 32
- 239000010410 layer Substances 0.000 claims abstract description 14
- 230000001681 protective effect Effects 0.000 claims abstract description 10
- 238000012544 monitoring process Methods 0.000 claims abstract description 7
- 239000000835 fiber Substances 0.000 claims description 19
- 230000008030 elimination Effects 0.000 claims description 4
- 238000003379 elimination reaction Methods 0.000 claims description 4
- 239000000853 adhesive Substances 0.000 claims description 2
- 230000001070 adhesive effect Effects 0.000 claims description 2
- 238000000605 extraction Methods 0.000 claims description 2
- 239000004744 fabric Substances 0.000 claims description 2
- 239000011152 fibreglass Substances 0.000 claims description 2
- 238000012423 maintenance Methods 0.000 description 9
- 238000007596 consolidation process Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 230000010354 integration Effects 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 230000004083 survival effect Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- 239000012783 reinforcing fiber Substances 0.000 description 2
- 239000011157 advanced composite material Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000036541 health Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 230000000930 thermomechanical effect Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D5/00—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable
- G01D5/26—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light
- G01D5/32—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light with attenuation or whole or partial obturation of beams of light
- G01D5/34—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells
- G01D5/353—Mechanical means for transferring the output of a sensing member; Means for converting the output of a sensing member to another variable where the form or nature of the sensing member does not constrain the means for converting; Transducers not specially adapted for a specific variable characterised by optical transfer means, i.e. using infrared, visible, or ultraviolet light with attenuation or whole or partial obturation of beams of light the beams of light being detected by photocells influencing the transmission properties of an optical fibre
-
- 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
- B29C73/00—Repairing of articles made from plastics or substances in a plastic state, e.g. of articles shaped or produced by using techniques covered by this subclass or subclass B29D
- B29C73/24—Apparatus or accessories not otherwise provided for
- B29C73/26—Apparatus or accessories not otherwise provided for for mechanical pretreatment
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M11/00—Testing of optical apparatus; Testing structures by optical methods not otherwise provided for
- G01M11/08—Testing mechanical properties
- G01M11/083—Testing mechanical properties by using an optical fiber in contact with the device under test [DUT]
- G01M11/086—Details about the embedment of the optical fiber within the DUT
-
- 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
- Y10T428/00—Stock material or miscellaneous articles
- Y10T428/12—All metal or with adjacent metals
- Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
- Y10T428/12535—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.] with additional, spatially distinct nonmetal component
Definitions
- the present invention relates to a composite material structure carrying embedded optical fiber for structural monitoring purposes, and more particularly to a composite structure of an aircraft, as well as to a method for its connection and repair.
- Fiber optic sensors can be used effectively to measure thermomechanical deformation, and even detect damage events operating both individually in passive structural monitoring systems, and in combination with other devices, forming active monitoring system.
- One of its main advantages is its ability to be embedded in composite structures, being intimately integrated into those.
- one of the drawbacks of this integration is the difficulty of the integration of the optical fiber in real laminate manufacturing conditions, and the repair of these same fibers once embedded.
- the optical fiber has extremely small dimensions, and due to its fragility, its handling is difficult during the handling operations associated with the integration processes during the manufacture of the laminate, manufacture of the vacuum bag and autoclave curing (or any other process of consolidation of alternative laminates), connectorization and subsequent maintenance and / or repair operations of the same optical fiber of the host laminate.
- the scarce possibilities of accessing the optical fiber once embedded are very small, and those of its repair with even lower success, this is incompatible with the requirements of reparability required when the criteria of structural health and maintenance meet linked to the correct operation of the sensor network integrated in the structure.
- the present invention is directed to the solution of that inconvenience.
- the present invention proposes a composite material structure formed by a plurality of layers that includes an optical fiber for structural monitoring purposes that is, at least in part, embedded in said structure in a surface layer thereof and which also includes insulating means of the areas of said optical fiber susceptible to repair with respect to the surface layer in which they are integrated.
- These insulating means protect the optical fiber during the manufacturing process of the structure and allow subsequent access to it for maintenance (connection, modification of the line or repair of damage in service) without significantly affecting the integrity of the structure.
- the present invention proposes a method of repairing the optical fiber embedded in said composite structure comprising the following steps: - Elimination of the insulating means of the area of optical fiber in need of repair. - Extraction of the fiber optic zone in need of repair of the composite structure.
- the fiber optic integration techniques proposed in this invention allow optical fiber to be embedded in composite structures ensuring the survival of that at the points of entry into the structure and allowing access to the fiber at these points of entry or intermediate points for its maintenance (connection, modification of the line or repair of damage in service), all without significantly affecting the structural integrity of the laminate.
- Figure 1 shows a schematic perspective view of a composite structure known in the art consisting of six layers with an optical fiber embedded in one of its faces longitudinally to the reinforcing fibers and a cross-sectional view of the area A of said structure.
- Figure 2 shows a cross-sectional view of the structure of Figure 1 in which using conventional repair techniques of composite structures, parts of the surface layer and the second layer have been removed by sanding until the embedded optical fiber is reached which has been damaged during the process.
- Figure 3 shows elevation, plan and cross-sectional views of a composite structure according to a first embodiment of the invention in which the optical fiber is embedded in a surface layer.
- Figure 4 shows elevational, plan and cross-sectional views of a composite structure according to a second embodiment of the invention in which the optical fiber is embedded inside the structure leaving only a part of it in a surface layer.
- Figure 5 shows views similar to those of Figures 3 and 4 after the consolidation process of the structure in which the optical fiber, the separating films and the outer protection layer are embedded in the structure.
- Figure 6 shows the same view of FIG. 5 after removing the outer protection layer and the outer separating film, the optical fiber being exposed.
- Figure 7 shows the same view of Figure 6 in which, after performing the required maintenance operations, the previously cut fiber optic ends are reconnected.
- Figure 8 shows the same view of FIG. 7 after completing the repair procedure.
- Figure 9 shows a view similar to that of Figure 7 in which the embedded optical fiber is repaired by an external fiber optic line.
- Figure 10 shows the same view of Figure 9 after completing the repair procedure.
- Figure 1 shows a composite structure 11 known in the art formed by a plurality of layers 13, 15, 17, 19, 21, 23 with an optical fiber 25 embedded in it that can be part of both a network of sensors as of an element of data transmission, embedded within it.
- the integration of this fiber 25 in the structure 11 is a complex and delicate process, especially in what concerns the entry points of the fiber 25 in said structure, necessary for its connection with the outside, and the survival of these points during The consolidation process.
- optical fiber 25 is a very fragile element, and the mentioned operations of elimination of parts of the layers of the structure can damage it, as reflected in Figure 2.
- the structure 11 includes means for isolating the optical fiber 25 of the layers in which it is embedded that increase its chances of survival and facilitate access to it at those points where it is capable of performing maintenance operations (connection, modification of the line or repair of damage in service).
- the separating films 31 and 33 are made with a material resistant to the temperature and pressure of the consolidation process that is incompatible with the resin of the laminate and the protective cover 27 is made of pre-impregnated fiberglass fabric or a similar material.
- optical fiber 25 may not be completely embedded in the surface layer 13 as shown in Figure 4, it is sufficient that those areas be considered convenient.
- Figures 6-7 sequentially illustrate the fundamental steps of a first embodiment of the fiber optic repair procedure in the structures we have just described.
- the optical fiber 25 that is embedded in the structure 11 is removed, but separated from it by the lower separating film 33, the optical fiber is repaired by, for example, a fusion joint 45 of the ends 41, 43 of the optical fiber 25 and the eliminated part of the structure is restored being in the situation illustrated in Figure 8.
- FIGS 8 and 9 illustrate the second embodiment of the repair procedure that differs only from the first in that the repair of the optical fiber
- 25 is carried out by joining, for example, a fusion joint 47 one of its ends 51 to the end 53 of an outer optical fiber 55, the optical signal being redirected by an alternative path.
- the repair may include the restitution of the separating films 31, 33 and the protective cover 27, providing a small amount of adhesive 29 on the upper separating film 33 and applying a usual consolidation process in the repair of laminates of material compound.
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Mechanical Coupling Of Light Guides (AREA)
- Light Guides In General And Applications Therefor (AREA)
- Laminated Bodies (AREA)
- Optical Transform (AREA)
Abstract
Description
Claims
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP2008542781A JP4862048B2 (ja) | 2005-11-30 | 2005-11-30 | 表面層のうちの一つに光ファイバが埋設された複合構造体、および、光ファイバの結合と修理方法 |
CA2631614A CA2631614C (en) | 2005-11-30 | 2005-11-30 | Composite structure with optical fiber embedded in one of its surface layers and a process for its connection and repair |
AU2005338589A AU2005338589B2 (en) | 2005-11-30 | 2005-11-30 | Composite material structure having an embedded optical fibre in one of the surface layers thereof and method for connecting and repairing same |
PCT/ES2005/070167 WO2007063146A1 (es) | 2005-11-30 | 2005-11-30 | Estructura de material compuesto con fibra optica embebida en una de sus capas superficiales y procedimiento para su conexión y reparacion |
ES05825333.7T ES2457023T3 (es) | 2005-11-30 | 2005-11-30 | Estructura de material compuesto con fibra óptica embebida en una de sus capas superficiales y procedimiento para su conexión y reparación |
EP05825333.7A EP1962123B1 (en) | 2005-11-30 | 2005-11-30 | Composite material structure having an embedded optical fibre in one of the surface layers thereof and method for connecting and repairing the same |
US11/441,273 US7542632B2 (en) | 2005-11-30 | 2006-05-25 | Composite structure with optical fiber embedded in one of its surface layers and a process for its connection and repair |
IL191870A IL191870A0 (en) | 2005-11-30 | 2008-06-01 | Composite material structure having an embedded optical fibre in one of the surface layers thereof and method for connecting and repairing same |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/ES2005/070167 WO2007063146A1 (es) | 2005-11-30 | 2005-11-30 | Estructura de material compuesto con fibra optica embebida en una de sus capas superficiales y procedimiento para su conexión y reparacion |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2007063146A1 true WO2007063146A1 (es) | 2007-06-07 |
Family
ID=38087638
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/ES2005/070167 WO2007063146A1 (es) | 2005-11-30 | 2005-11-30 | Estructura de material compuesto con fibra optica embebida en una de sus capas superficiales y procedimiento para su conexión y reparacion |
Country Status (8)
Country | Link |
---|---|
US (1) | US7542632B2 (es) |
EP (1) | EP1962123B1 (es) |
JP (1) | JP4862048B2 (es) |
AU (1) | AU2005338589B2 (es) |
CA (1) | CA2631614C (es) |
ES (1) | ES2457023T3 (es) |
IL (1) | IL191870A0 (es) |
WO (1) | WO2007063146A1 (es) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2368541A1 (es) * | 2008-10-16 | 2011-11-18 | Rodriser Industria Aeronáutica Española, S.L. | Procedimiento de implantación de parches para reparación de estructuras aeronáuticas y parche utilizado en dicho procedimiento. |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1965237A4 (en) * | 2005-11-30 | 2012-07-18 | Airbus Operations Sl | COMPOSITE MATERIAL STRUCTURE WITH INTEGRATED OPTICAL FIBER AND REPAIR METHOD THEREOF |
DE102007030025B3 (de) | 2007-06-29 | 2008-10-16 | Airbus Deutschland Gmbh | Verfahren zur Reparatur eines beschädigten Bereichs eines Faserverbundbauteils mit integrierter Faseroptik sowie Vorrichtung |
DE102008062700A1 (de) | 2008-12-17 | 2010-07-01 | Airbus Deutschland Gmbh | Vorinstalliertes, anpassbares Leitungsnetz für Flugzeuge |
DE102010039153B4 (de) * | 2010-08-10 | 2012-04-19 | Airbus Operations Gmbh | Verfahren zum Verbinden eines in ein Faserverbundbauteil eingebetteten Lichtleiters mit einem externen Lichtleiter |
JP5725455B2 (ja) | 2011-06-08 | 2015-05-27 | 国立大学法人 東京大学 | 複合材構造体の埋込光ファイバ修理方法と修理構造 |
DE102016121662A1 (de) * | 2016-11-11 | 2018-05-17 | Saurer Germany Gmbh & Co. Kg | Verfahren und Vorrichtung zur Beurteilung der Qualität eines längsbewegten strangförmigen Gutes |
RU179119U1 (ru) * | 2017-09-14 | 2018-04-26 | Российская Федерация, от имени которой выступает ФОНД ПЕРСПЕКТИВНЫХ ИССЛЕДОВАНИЙ | Устройство выхода волоконно-оптического датчика из композита |
ES2925907T3 (es) * | 2019-07-03 | 2022-10-20 | Airbus Operations Slu | Sistema para monitorización de flujo de resina |
DE102019134544A1 (de) * | 2019-12-16 | 2021-06-17 | Deutsches Zentrum für Luft- und Raumfahrt e.V. | Verfahren und System zur Überprüfung einer Klebverbindung |
WO2022223765A1 (en) * | 2021-04-23 | 2022-10-27 | Politecnico Di Milano | Hybrid structural device with sensors |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1599442A (en) * | 1977-03-10 | 1981-10-07 | Fort F | Multi-fibre optic cable |
EP0101766A1 (en) * | 1982-08-23 | 1984-03-07 | AMP INCORPORATED (a New Jersey corporation) | Laminated optical fibre ribbon cable |
JPS60176006A (ja) * | 1984-02-22 | 1985-09-10 | Kanai Hiroyuki | 光フアイバ−接合方法 |
US4836030A (en) * | 1985-05-20 | 1989-06-06 | Lockheed Corporation | Method of testing composite materials for structural damage |
US5309533A (en) * | 1991-12-11 | 1994-05-03 | Thomson-Csf | Structure with intrinsic damage control, manufacturing processes and method of use |
US20020136498A1 (en) * | 2000-01-11 | 2002-09-26 | Aldridge Nigel Bruce | Optically connecting embedded optical fibers in composite panels |
Family Cites Families (19)
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US3466219A (en) | 1965-08-09 | 1969-09-09 | Us Air Force | Fiber reinforced plastic composite material |
US3716869A (en) | 1970-12-02 | 1973-02-13 | Nasa | Millimeter wave antenna system |
US3755713A (en) | 1972-07-25 | 1973-08-28 | Boeing Co | Electrically conductive surface for aircraft |
US4221041A (en) | 1978-10-02 | 1980-09-09 | Boeing Commercial Airplane Company | Semi-tubular rivets and method of using |
US4318954A (en) | 1981-02-09 | 1982-03-09 | Boeing Aerospace Company | Printed wiring board substrates for ceramic chip carriers |
IT1218709B (it) | 1981-06-30 | 1990-04-19 | Boeing Co | Metodo di fabbricazione di un preformato utilizzando un materiale composito rinforzato con fibre |
US5346367A (en) | 1984-12-21 | 1994-09-13 | United Technologies Corporation | Advanced composite rotor blade |
US6086975A (en) | 1991-01-16 | 2000-07-11 | The Boeing Company | Lighting protection for electrically conductive or insulating skin and core for honeycomb structure |
BE1005172A3 (nl) * | 1991-08-09 | 1993-05-11 | Bell Telephone Mfg | Konstruktie voor het optisch koppelen, substraat daarvoor en werkwijze voor het verwezenlijken van dergelijke konstruktie. |
US5851645A (en) * | 1995-06-07 | 1998-12-22 | Mcdonnell Douglas Corporation | Composite structure having an externally accessible electrical device embedded therein and a related fabrication method |
US6035084A (en) * | 1997-11-13 | 2000-03-07 | Mcdonell Douglas Corporation | Fiber optic connector and associated method for establishing an optical connection with an optical fiber embedded within a composite structure |
US6173090B1 (en) * | 1998-10-29 | 2001-01-09 | The United States Of America As Represented By The Secretary Of The Navy | Apparatus for ingress and egress of fiber optic sensor leads from the surface of composite parts and a method for the manufacture thereof |
JP3699614B2 (ja) * | 1999-05-31 | 2005-09-28 | 京セラ株式会社 | 配線基板およびその製造方法 |
JP3243461B2 (ja) | 1999-07-30 | 2002-01-07 | 川崎重工業株式会社 | サンドイッチ構造 |
DE19956394B4 (de) | 1999-11-24 | 2005-02-03 | Airbus Deutschland Gmbh | Verfahren zur Herstellung eines Profiles aus einem Hybridwerkstoff |
GB0000405D0 (en) * | 2000-01-11 | 2000-03-01 | British Aerospace | Improvements relating to interfacing embedded optical transmission structures |
EP1342554B1 (de) | 2002-03-08 | 2010-02-03 | Airbus Deutschland GmbH | Verfahren zum Herstellen textiler Vorformlinge aus textilen Halbzeugen |
DE10326422A1 (de) | 2003-06-10 | 2005-01-05 | Eads Deutschland Gmbh | Verfahren zur Herstellung von sich in einer Längsrichtung erstreckenden FVK-Hohlprofilen |
CA2604152A1 (en) * | 2005-04-05 | 2006-10-12 | Agency For Science, Technology And Research | Fiber bragg grating sensor |
-
2005
- 2005-11-30 JP JP2008542781A patent/JP4862048B2/ja not_active Expired - Fee Related
- 2005-11-30 AU AU2005338589A patent/AU2005338589B2/en not_active Ceased
- 2005-11-30 CA CA2631614A patent/CA2631614C/en active Active
- 2005-11-30 WO PCT/ES2005/070167 patent/WO2007063146A1/es active Application Filing
- 2005-11-30 ES ES05825333.7T patent/ES2457023T3/es active Active
- 2005-11-30 EP EP05825333.7A patent/EP1962123B1/en not_active Not-in-force
-
2006
- 2006-05-25 US US11/441,273 patent/US7542632B2/en not_active Expired - Fee Related
-
2008
- 2008-06-01 IL IL191870A patent/IL191870A0/en active IP Right Grant
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1599442A (en) * | 1977-03-10 | 1981-10-07 | Fort F | Multi-fibre optic cable |
EP0101766A1 (en) * | 1982-08-23 | 1984-03-07 | AMP INCORPORATED (a New Jersey corporation) | Laminated optical fibre ribbon cable |
JPS60176006A (ja) * | 1984-02-22 | 1985-09-10 | Kanai Hiroyuki | 光フアイバ−接合方法 |
US4836030A (en) * | 1985-05-20 | 1989-06-06 | Lockheed Corporation | Method of testing composite materials for structural damage |
US5309533A (en) * | 1991-12-11 | 1994-05-03 | Thomson-Csf | Structure with intrinsic damage control, manufacturing processes and method of use |
US20020136498A1 (en) * | 2000-01-11 | 2002-09-26 | Aldridge Nigel Bruce | Optically connecting embedded optical fibers in composite panels |
Non-Patent Citations (2)
Title |
---|
PATENT ABSTRACTS OF JAPAN vol. 10, no. 22 (P - 424) 28 January 1986 (1986-01-28) * |
See also references of EP1962123A4 * |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2368541A1 (es) * | 2008-10-16 | 2011-11-18 | Rodriser Industria Aeronáutica Española, S.L. | Procedimiento de implantación de parches para reparación de estructuras aeronáuticas y parche utilizado en dicho procedimiento. |
Also Published As
Publication number | Publication date |
---|---|
ES2457023T3 (es) | 2014-04-24 |
AU2005338589B2 (en) | 2013-01-31 |
EP1962123A1 (en) | 2008-08-27 |
JP4862048B2 (ja) | 2012-01-25 |
CA2631614C (en) | 2012-11-13 |
US7542632B2 (en) | 2009-06-02 |
CA2631614A1 (en) | 2007-06-07 |
AU2005338589A1 (en) | 2007-06-07 |
US20070122099A1 (en) | 2007-05-31 |
EP1962123B1 (en) | 2014-01-08 |
JP2009517680A (ja) | 2009-04-30 |
EP1962123A4 (en) | 2012-05-09 |
IL191870A0 (en) | 2008-12-29 |
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