DE102009022175A1 - Support system for arranging lines in aircraft, particularly airplanes, comprises support element for receiving line, and connecting element for fastening support element at structural section of aircraft - Google Patents
Support system for arranging lines in aircraft, particularly airplanes, comprises support element for receiving line, and connecting element for fastening support element at structural section of aircraft Download PDFInfo
- Publication number
- DE102009022175A1 DE102009022175A1 DE200910022175 DE102009022175A DE102009022175A1 DE 102009022175 A1 DE102009022175 A1 DE 102009022175A1 DE 200910022175 DE200910022175 DE 200910022175 DE 102009022175 A DE102009022175 A DE 102009022175A DE 102009022175 A1 DE102009022175 A1 DE 102009022175A1
- Authority
- DE
- Germany
- Prior art keywords
- aircraft
- holder system
- section
- securing
- retaining element
- 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.)
- Withdrawn
Links
- 238000000034 method Methods 0.000 claims abstract description 13
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 239000000463 material Substances 0.000 description 6
- 239000000243 solution Substances 0.000 description 4
- 230000008719 thickening Effects 0.000 description 4
- 238000005553 drilling Methods 0.000 description 3
- 230000002093 peripheral effect Effects 0.000 description 3
- 239000004033 plastic Substances 0.000 description 2
- 229920002647 polyamide Polymers 0.000 description 2
- BUHVIAUBTBOHAG-FOYDDCNASA-N (2r,3r,4s,5r)-2-[6-[[2-(3,5-dimethoxyphenyl)-2-(2-methylphenyl)ethyl]amino]purin-9-yl]-5-(hydroxymethyl)oxolane-3,4-diol Chemical compound COC1=CC(OC)=CC(C(CNC=2C=3N=CN(C=3N=CN=2)[C@H]2[C@@H]([C@H](O)[C@@H](CO)O2)O)C=2C(=CC=CC=2)C)=C1 BUHVIAUBTBOHAG-FOYDDCNASA-N 0.000 description 1
- 239000004952 Polyamide Substances 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003313 weakening 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
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L3/00—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets
- F16L3/02—Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets partly surrounding the pipes, cables or protective tubing
-
- 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
- B64C1/40—Sound or heat insulation, e.g. using insulation blankets
- B64C1/403—Arrangement of fasteners specially adapted therefor, e.g. of clips
- B64C1/406—Arrangement of fasteners specially adapted therefor, e.g. of clips in combination with supports for lines, e.g. for pipes or cables
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/26—Installations of cables, lines, or separate protective tubing therefor directly on or in walls, ceilings, or floors
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02G—INSTALLATION OF ELECTRIC CABLES OR LINES, OR OF COMBINED OPTICAL AND ELECTRIC CABLES OR LINES
- H02G3/00—Installations of electric cables or lines or protective tubing therefor in or on buildings, equivalent structures or vehicles
- H02G3/30—Installations of cables or lines on walls, floors or ceilings
- H02G3/32—Installations of cables or lines on walls, floors or ceilings using mounting clamps
Abstract
Description
Die Erfindung betrifft ein Haltersystem zur Anordnung von Leitungen in Luftfahrzeugen, insbesondere Flugzeugen, nach dem Oberbegriff des Patentanspruch 1 sowie ein Verfahren zur Befestigung des Haltersystems.The The invention relates to a holder system for the arrangement of lines in aircraft, in particular aircraft, according to the generic term of claim 1 and a method for fixing the holder system.
Leitungen bzw. Flugzeugsysteme in Luftfahrzeugen werden meistens über Halter bzw. Haltersysteme an der Primärstruktur wie Stringern angebunden. Die Anbindung der Halter erfolgt bei bekannten Lösungen über mindestens zwei Nieten, wobei ein Niet zur Befestigung des Halters und ein Niet als Verdrehsicherung und somit als Sicherungselement des Halters dient. Zur Aufnahme der Nieten sind in dem Halterfuß entsprechende vorgebohrte Niet- bzw. Befestigungslöcher vorgesehen. Zur Befestigung der Halter werden diese im jeweiligen Bereich des Stringers positioniert und es wird eine mit dem einen Nietloch fluchtende Heftbohrung in den Stringer eingebracht. Dann wird der Halter durch einen Hefter in der Heftbohrung und in dem einen fluchtenden Nietloch an dem Stringer fixiert und eine zweite Bohrung wird in den Stringer eingebracht, die mit dem anderen Nietloch fluchtet. Die zweite Bohrung und das Nietloch werden auf Endmaß bearbeitet und es wird ein Niet eingesetzt. Nach dem Setzern des Niets wird die Heftung gelöst und dieses Bohrungspaar auf Endmaß gebohrt und endgültig mit einem Niet versehen. Das vorbeschriebene Verfahren erfordert eine hohe Genauigkeit, da die Positionen der Bohrungen in dem Stringer genau zu den Nietlöchern ausgerichtet sein müssen. Ein fehlerhaftes Setzen einer Bohrung in dem Stringer ist nahezu nicht korrigierbar. Ferner müssen die Halter zueinander richtig positioniert sein. Des Weiteren verursacht das bekannte Verfahren durch das Vorbohren der Stringerbohrungen, das Heften und das Endbohren einen erheblichen Arbeits- und damit Kostenaufwand.cables or aircraft systems in aircraft are usually over Holder or holder systems on the primary structure such as stringers tethered. The connection of the holder takes place in known solutions at least two rivets, with a rivet for attachment of the holder and a rivet as anti-rotation and thus as a security element the holder serves. To accommodate the rivets are in the Halterfuß appropriate predrilled rivet or mounting holes provided. to Fixing the holder these are in the respective area of the stringer positioned and it is aligned with the one rivet hole Bolt hole introduced into the stringer. Then the holder goes through a stapler in the handle hole and in the one aligned rivet hole Fixed the stringer and a second hole is in the stringer introduced, which is aligned with the other rivet hole. The second hole and the rivet hole are machined to gauge and it will a rivet inserted. After setting the rivet, the stitch becomes solved and drilled this bore pair to final gauge and finally provided with a rivet. The above Method requires a high accuracy, since the positions of the Holes in the stringer aligned exactly to the rivet holes have to be. An incorrect setting of a hole in the Stringer is almost uncorrectable. Furthermore, the Holder be properly positioned to each other. Furthermore caused the known method by pre-drilling the stringer bores, The stapling and the final drilling a considerable work and thus Cost.
Aus
der deutschen Patentanmeldung
Aufgabe der vorliegenden Erfindung ist es, ein Haltersystem zur Anordnung von Leitungen in Luftfahrzeugen, das die vorgenannten Nachteile beseitigt und einfach an einem Strukturabschnitt des Luftfahrzeugs zu befestigen ist, sowie ein Verfahren zur Befestigung des Haltersystems an einem Strukturabschnitt des Luftfahrzeugs zu schaffen.task It is the object of the present invention to provide a holder system for assembly of lines in aircraft, the above-mentioned disadvantages eliminated and easily attached to a structural section of the aircraft to attach, and a method for attaching the holder system to create at a structural portion of the aircraft.
Diese Aufgabe wird gelöst durch ein Haltersystem mit den Merkmalen des Patentanspruchs 1 und durch ein Verfahren nach Patentanspruch 9.These Task is solved by a holder system with the features of claim 1 and by a method according to claim 9th
Ein erfindungsgemäßes Haltersystem zur Anordnung von Leitungen in Luftfahrzeugen, insbesondere Flugzeugen, hat ein Halteelement zur Aufnahme von zumindest einer Leitung, ein Verbindungselement zum Befestigen des Halteelements an einem Strukturabschnitt des Luftfahrzeugs und ein Sicherungselement zur Lagesicherung des Halteelements am Strukturabschnitt. Erfindungsgemäß ist das Sicherungselement relativ zum Verbindungselement versetzbar.One Inventive holder system for the arrangement of Lines in aircraft, especially aircraft, has a holding element for receiving at least one line, a connecting element for fastening the retaining element to a structural section of the Aircraft and a securing element for securing the position of the retaining element at the structure section. This is according to the invention Locking element displaceable relative to the connecting element.
An der erfindungsgemäßen Lösung ist insbesondere vorteilhaft, dass das Sicherungselement nicht in einem festen Abstand zum Verbindungselement angeordnet ist, so dass eine Fehlpositionierung des Verbindungselements ausgeglichen werden kann. Je nach Ausrichtung des Haltersystems in dem Luftfahrzeug können somit Befestigungs- bzw. Montage- und Bauteiltoleranzen sowie Bohrungspositionstoleranzen des Haltersystems in y-, x- oder z-Richtung des Luftfahrzeugs ausgeglichen werden.At the solution according to the invention is in particular advantageous in that the securing element is not at a fixed distance is arranged to the connecting element, so that a mispositioning of the connecting element can be compensated. Depending on the orientation of the holder system in the aircraft, mounting or assembly and component tolerances and bore position tolerances of the holder system in the y, x or z direction of the aircraft.
Bei einem Ausführungsbeispiel hat das Sicherungselement einen Verriegelungsabschnitt zum bereichsweisen Umgreifen des Strukturabschnitts. Dies hat den Vorteil, dass für das Sicherungselement keine Bohrung in den Strukturabschnitt eingebracht werden muss, wodurch der Strukturabschnitt nicht geschwächt wird und keine Montagekosten für Bohrungen entstehen.at In one embodiment, the securing element has a Locking section for partially encompassing the structural section. This has the advantage that for the security element no hole must be introduced into the structural section, whereby the structural section not weakened and no assembly costs for Boreholes arise.
Bevorzugterweise ist der Verriegelungsabschnitt konturnah zum umgreifenden Strukturabschnitt und federnd ausgebildet. Durch die konturnahe und federnde Ausbildung des Verriegelungsabschnitts liegt dieser eng und formschlüssig an dem Strukturabschnitt an und verhindert Kipp- bzw. Drehbewegungen des Haltersystems.preferably, the locking portion is contour close to the encompassing structure section and resilient. Due to the contoured and resilient training of the locking portion of this is close and positive on the structural portion and prevents tilting or rotational movements of the holder system.
Bei einem konkreten Ausführungsbeispiel befinden sich das Halteelement und das Sicherungselement im Schiebeeingriff miteinander. Insbesondere kann das Sicherungselement eine Ausnehmung haben, in der das Halteelement mit einem Führungsabschnitt eintaucht. Hierdurch wird eine sichere Verbindung zwischen dem Halteelement und dem Sicherungselement erzielt.at a concrete embodiment, the holding element are and the securing element in sliding engagement with each other. Especially the securing element may have a recess in which the retaining element with a guide section dips. This will be a secure connection between the retaining element and the securing element achieved.
Vorzugsweise weisen das Sicherungselement und das Halteelement jeweils eine Verzahnung auf, die sich im am Strukturabschnitt verriegelten Zustand im Wirkeingriff miteinander befindet. Hierdurch wird das Sicherungselement in einer Position an dem Halteelement fixiert, so dass das Halteelement unbewegbar an dem Strukturabschnitt angebunden ist.Preferably, the Sicherungsele ment and the holding element in each case a toothing, which is in the locked state on the structural portion in operative engagement with each other. As a result, the securing element is fixed in a position on the holding element, so that the holding element is immovably connected to the structure section.
Das Verbindungselement kann in eine Bohrung des Strukturabschnitts einsetzbar sein. Vorzugsweise ist es stift-, niet-, bolzen- bzw. zapfenartig. Diese ermöglicht eine sichere Befestigung des Halteelements an dem Strukturabschnitt. Beispiele sind Vollniete, Blindbolt, Lockbolt und High Lock sowie Schraub und Schraubpresslösung.The Connecting element can be inserted into a bore of the structural section be. Preferably, it is pin, rivet, bolt or pin-like. These allows a secure attachment of the retaining element the structural section. Examples are full rivets, blindbolt, lockbolt and high lock as well as screw and screw press solution.
Das Haltersystem ist besonders einfach, gewichtsoptimiert und kostengünstig herstellbar, wenn das Halteelement und das Sicherungselement z. B. durch Spritzgussverfahren aus dem Material Polyamid herstellbar sind.The Holder system is particularly simple, weight-optimized and cost-effective produced when the holding element and the fuse element z. B. produced by injection molding of the material polyamide are.
Bei einem Verfahren zur Befestigung eines erfindungsgemäßen Haltersystems wird ein Halteelement an einem Strukturabschnitt mittels eines Verbindungselements befestigt. Anschließend wird ein Sicherungselement zur Vermeidung von Lageveränderungen des Halteelements positioniert, dass einen Formschluss mit dem Strukturabschnitt bildet und mit dem Halteelement im Wirkeingriff steht.at a method for fixing a device according to the invention Holder system is a holding element on a structural section means attached to a connecting element. Subsequently, will a security element to avoid changes in position the retaining element positioned that a positive connection with the structural portion forms and is in operative engagement with the retaining element.
Das erfindungsgemäße Verfahren hat den Vorteil, dass eine Toleranzkompensation erfolgen kann und nur eine Bohrung in den Strukturabschnitt eingebracht werden muss. Dies vereinfacht die Montage und reduziert die Montagedauer. Dabei kann diese Bohrung direkt auf Endmaß gebohrt werden. Des Weiteren kann dieses Bohrloch relative Positionsschwankungen aufweisen, da es nicht in einem präzisen Abstand zu einem anderen Bohrloch liegen muss. Ebenso entfällt ein Heften des Haltersystems. Ferner erfolgt durch den Formschluss des Sicherungselements keine Materialschwächung des Strukturabschnitts.The inventive method has the advantage that Tolerance compensation can be made and only one hole in the structural section must be introduced. This is simplified the assembly and reduces the installation time. This hole can be drilled directly to final gauge. Furthermore, this can Borehole relative positional fluctuations, as it is not in must be at a precise distance from another well. Likewise eliminates stapling of the holder system. Furthermore, it takes place by the positive connection of the fuse element no material weakening of the structure section.
Vorzugsweise wird vor der Befestigung des Halteelements an dem Strukturabschnitt ein Schiebeeingriff zwischen dem Halteelement und dem Sicherungselement hergestellt. Dies hat den Vorteil, dass das Sicherungselement bereits an dem Halteelement verschiebbar angeordnet ist, so dass die Sicherung bzw. Montage schnell und einfach erfolgen kann.Preferably is prior to attachment of the retaining element to the structural portion a sliding engagement between the retaining element and the securing element produced. This has the advantage that the security element already is slidably disposed on the retaining element, so that the fuse or assembly can be done quickly and easily.
Sonstige vorteilhafte Ausführungsbeispiele sind Gegenstand weiterer Unteransprüche.other advantageous embodiments are the subject of further Dependent claims.
Im Folgenden wird ein bevorzugtes Ausführungsbeispiel der Erfindung anhand schematischer Darstellungen näher erläutert. Es zeigenin the Below is a preferred embodiment of Invention explained in more detail with reference to schematic representations. Show it
In den Figuren tragen gleiche konstruktive Elemente die gleichen BezugsziffernIn the same structural elements carry the same reference numerals
Das
Haltersystem
Das
Haltesystem
Gemäß
Das
Sicherungselement
Das
Sicherungselement
Gemäß den
Das
erfindungsgemäße Haltersystem
In
den folgenden
Gemäß
According to
Offenbart
ist ein Haltersystem
- 22
- Haltersystemholder system
- 44
- Leitungencables
- 66
- StringerStringer
- 88th
- Halteelementretaining element
- 1010
- Verbindungselementconnecting element
- 1212
- Stegabschnittweb section
- 1414
- Aufnahmeadmission
- 1616
- Sicherungselementfuse element
- 1818
- Kopfabschnittheader
- 2020
- Ausnehmungrecess
- 2222
- Führungsabschnittguide section
- 2424
- Bohrungdrilling
- 2626
- Verzahnunggearing
- 2828
- Anlageflächecontact surface
- 3030
- Verriegelungsabschnittlocking section
- 3232
- Vorsprunghead Start
- 3434
- InnenumfangsflächeInner circumferential surface
- 3636
- StringerkopfkanteStringerkopfkante
- 3838
- Materialverdickungmaterial thickening
- 4040
- Verlängerungrenewal
- 4242
- Verzahnunggearing
- 4444
- Befestigungslochmounting hole
- 4646
- Befestigungslochmounting hole
- 4848
- Basisflächefootprint
- h1h1
- Abstanddistance
- h2h2
- Abstanddistance
- ss
- Versatzoffset
ZITATE ENTHALTEN IN DER BESCHREIBUNGQUOTES INCLUDE IN THE DESCRIPTION
Diese Liste der vom Anmelder aufgeführten Dokumente wurde automatisiert erzeugt und ist ausschließlich zur besseren Information des Lesers aufgenommen. Die Liste ist nicht Bestandteil der deutschen Patent- bzw. Gebrauchsmusteranmeldung. Das DPMA übernimmt keinerlei Haftung für etwaige Fehler oder Auslassungen.This list The documents listed by the applicant have been automated generated and is solely for better information recorded by the reader. The list is not part of the German Patent or utility model application. The DPMA takes over no liability for any errors or omissions.
Zitierte PatentliteraturCited patent literature
- - DE 102006053966 A1 [0003] DE 102006053966 A1 [0003]
Claims (10)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200910022175 DE102009022175A1 (en) | 2009-05-20 | 2009-05-20 | Support system for arranging lines in aircraft, particularly airplanes, comprises support element for receiving line, and connecting element for fastening support element at structural section of aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE200910022175 DE102009022175A1 (en) | 2009-05-20 | 2009-05-20 | Support system for arranging lines in aircraft, particularly airplanes, comprises support element for receiving line, and connecting element for fastening support element at structural section of aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102009022175A1 true DE102009022175A1 (en) | 2010-12-09 |
Family
ID=43049068
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE200910022175 Withdrawn DE102009022175A1 (en) | 2009-05-20 | 2009-05-20 | Support system for arranging lines in aircraft, particularly airplanes, comprises support element for receiving line, and connecting element for fastening support element at structural section of aircraft |
Country Status (1)
Country | Link |
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DE (1) | DE102009022175A1 (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011085450A1 (en) | 2011-10-28 | 2013-05-02 | Airbus Operations Gmbh | Connection arrangement for connecting secondary carrier structure to floor cross beam of airplane for receiving e.g. installation spacer, has connector and receiving element whose relative movement is made towards axis of movement |
FR2983558A1 (en) * | 2011-12-02 | 2013-06-07 | Airbus Operations Sas | Supporting part for connecting e.g. non-heavy element to wall surface of structure of aircraft, has base plate comprising centering portion to be placed in hole to center spacer and self-locking clip, which encloses plate and spacer |
EP2740982A1 (en) | 2012-12-06 | 2014-06-11 | Airbus Operations GmbH | Attachment arrangement and installation method |
FR3001088A1 (en) * | 2013-01-11 | 2014-07-18 | Airbus Operations Sas | DEVICE FOR MOUNTING FEED SYSTEMS FOR AIRCRAFT |
FR3001837A1 (en) * | 2013-02-01 | 2014-08-08 | Airbus Operations Sas | Electric cable holder part for use in fastening assembly on e.g. wing for fastening electric cable in interior of transportation aircraft, has cable holder plate including upper face, which has holder directions defined along round shape |
CN104110527A (en) * | 2014-07-27 | 2014-10-22 | 成都高普石油工程技术有限公司 | Oil pipeline support device |
CN104110528A (en) * | 2014-07-27 | 2014-10-22 | 成都高普石油工程技术有限公司 | Oil pipeline support system |
DE102013214776A1 (en) | 2013-07-29 | 2015-01-29 | Airbus Operations Gmbh | Fuselage structure of an aircraft and / or spacecraft and method |
EP2908038A1 (en) | 2014-02-13 | 2015-08-19 | Airbus Operations GmbH | A method and a robotic system for the attachment of an arrangement |
CN106641454A (en) * | 2017-01-18 | 2017-05-10 | 朱海斌 | Bridge pipeline supporting structure |
CN108331971A (en) * | 2018-01-30 | 2018-07-27 | 刘凤云 | A kind of highway bridge pipeline support equipment |
DE102013222444B4 (en) * | 2013-11-05 | 2020-03-26 | Airbus Operations Gmbh | Fastening device and method for fastening elements |
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10012141A1 (en) * | 1999-04-02 | 2000-10-05 | Hyundai Electronics Ind | Single electron transistor having a quantum dot size of a few tens of nanometers is produced by forming the upper gate on trench side walls in an insulation film |
DE102004021513A1 (en) * | 2004-04-30 | 2005-11-24 | Airbus Deutschland Gmbh | Suspension clamping holder e.g. for support structure, has free carrier, support and clamping valve with free carrier laterally at upper end of support and perpendicularly formed with support having back with carrier extension |
DE102004026224A1 (en) * | 2004-05-28 | 2005-12-22 | Airbus Deutschland Gmbh | Holder for use in aircraft for use with cable and pipe runs is based around a double -T section beam |
DE102006053966A1 (en) | 2006-11-16 | 2008-05-21 | Airbus Deutschland Gmbh | Universal line holder for aircraft, has function module fastened to base module, which has attachment surface with hole and locking surface, and bolt attached for fixing holder in borehole in reinforcement structure |
-
2009
- 2009-05-20 DE DE200910022175 patent/DE102009022175A1/en not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
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DE10012141A1 (en) * | 1999-04-02 | 2000-10-05 | Hyundai Electronics Ind | Single electron transistor having a quantum dot size of a few tens of nanometers is produced by forming the upper gate on trench side walls in an insulation film |
DE102004021513A1 (en) * | 2004-04-30 | 2005-11-24 | Airbus Deutschland Gmbh | Suspension clamping holder e.g. for support structure, has free carrier, support and clamping valve with free carrier laterally at upper end of support and perpendicularly formed with support having back with carrier extension |
DE102004026224A1 (en) * | 2004-05-28 | 2005-12-22 | Airbus Deutschland Gmbh | Holder for use in aircraft for use with cable and pipe runs is based around a double -T section beam |
DE102006053966A1 (en) | 2006-11-16 | 2008-05-21 | Airbus Deutschland Gmbh | Universal line holder for aircraft, has function module fastened to base module, which has attachment surface with hole and locking surface, and bolt attached for fixing holder in borehole in reinforcement structure |
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102011085450A1 (en) | 2011-10-28 | 2013-05-02 | Airbus Operations Gmbh | Connection arrangement for connecting secondary carrier structure to floor cross beam of airplane for receiving e.g. installation spacer, has connector and receiving element whose relative movement is made towards axis of movement |
US9279439B2 (en) | 2011-10-28 | 2016-03-08 | Airbus Operations Gmbh | Attachment arrangement, a connecting device, and also a method |
FR2983558A1 (en) * | 2011-12-02 | 2013-06-07 | Airbus Operations Sas | Supporting part for connecting e.g. non-heavy element to wall surface of structure of aircraft, has base plate comprising centering portion to be placed in hole to center spacer and self-locking clip, which encloses plate and spacer |
EP2740982A1 (en) | 2012-12-06 | 2014-06-11 | Airbus Operations GmbH | Attachment arrangement and installation method |
US9618021B2 (en) | 2012-12-06 | 2017-04-11 | Airbus Operations Gmbh | Attachment arrangement and installation method |
FR3001088A1 (en) * | 2013-01-11 | 2014-07-18 | Airbus Operations Sas | DEVICE FOR MOUNTING FEED SYSTEMS FOR AIRCRAFT |
US9216705B2 (en) | 2013-01-11 | 2015-12-22 | Airbus Operations (Sas) | Mounting device for aircraft supply systems |
FR3001837A1 (en) * | 2013-02-01 | 2014-08-08 | Airbus Operations Sas | Electric cable holder part for use in fastening assembly on e.g. wing for fastening electric cable in interior of transportation aircraft, has cable holder plate including upper face, which has holder directions defined along round shape |
DE102013214776B4 (en) * | 2013-07-29 | 2015-08-13 | Airbus Operations Gmbh | Fuselage structure of an aircraft and / or spacecraft and method |
DE102013214776A1 (en) | 2013-07-29 | 2015-01-29 | Airbus Operations Gmbh | Fuselage structure of an aircraft and / or spacecraft and method |
DE102013222444B4 (en) * | 2013-11-05 | 2020-03-26 | Airbus Operations Gmbh | Fastening device and method for fastening elements |
EP2908038A1 (en) | 2014-02-13 | 2015-08-19 | Airbus Operations GmbH | A method and a robotic system for the attachment of an arrangement |
CN104110528A (en) * | 2014-07-27 | 2014-10-22 | 成都高普石油工程技术有限公司 | Oil pipeline support system |
CN104110528B (en) * | 2014-07-27 | 2016-06-22 | 成都来宝石油设备有限公司 | Oil pipeline props up support system |
CN104110527B (en) * | 2014-07-27 | 2017-01-25 | 江苏庆海石油机械有限公司 | Oil pipeline support device |
CN104110527A (en) * | 2014-07-27 | 2014-10-22 | 成都高普石油工程技术有限公司 | Oil pipeline support device |
CN106641454A (en) * | 2017-01-18 | 2017-05-10 | 朱海斌 | Bridge pipeline supporting structure |
CN108331971A (en) * | 2018-01-30 | 2018-07-27 | 刘凤云 | A kind of highway bridge pipeline support equipment |
CN108331971B (en) * | 2018-01-30 | 2018-11-13 | 刘凤云 | A kind of highway bridge pipeline support equipment |
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