WO2009130082A1 - Procédé d’insertion d’une douille dans un composant et douille - Google Patents

Procédé d’insertion d’une douille dans un composant et douille Download PDF

Info

Publication number
WO2009130082A1
WO2009130082A1 PCT/EP2009/052577 EP2009052577W WO2009130082A1 WO 2009130082 A1 WO2009130082 A1 WO 2009130082A1 EP 2009052577 W EP2009052577 W EP 2009052577W WO 2009130082 A1 WO2009130082 A1 WO 2009130082A1
Authority
WO
WIPO (PCT)
Prior art keywords
bushing
component
socket
flange
hole
Prior art date
Application number
PCT/EP2009/052577
Other languages
German (de)
English (en)
Inventor
Enno Stoever
Pierre Zahlen
Christian Luebbering
Hauke Lengsfeld
Holger Mueller
Original Assignee
Airbus Operations Gmbh
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 Airbus Operations Gmbh filed Critical Airbus Operations Gmbh
Publication of WO2009130082A1 publication Critical patent/WO2009130082A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/40—General aspects of joining substantially flat articles, e.g. plates, sheets or web-like materials; Making flat seams in tubular or hollow articles; Joining single elements to substantially flat surfaces
    • B29C66/47—Joining single elements to sheets, plates or other substantially flat surfaces
    • B29C66/474—Joining single elements to sheets, plates or other substantially flat surfaces said single elements being substantially non-flat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
    • B29C65/52—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive
    • B29C65/54—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive between pre-assembled parts
    • B29C65/542—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive between pre-assembled parts by injection
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/64—Joining a non-plastics element to a plastics element, e.g. by force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/74—Joining plastics material to non-plastics material
    • B29C66/742—Joining plastics material to non-plastics material to metals or their alloys
    • B29C66/7428—Transition metals or their alloys
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2105/00—Condition, form or state of moulded material or of the material to be shaped
    • B29K2105/06—Condition, form or state of moulded material or of the material to be shaped containing reinforcements, fillers or inserts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/737—Articles provided with holes, e.g. grids, sieves

Definitions

  • the invention relates to the positive joining of components and in particular, but not exclusively a method for inserting a socket into a component according to the preamble of claim 1, and a socket with sealing element for insertion into a component according to the preamble of claim 7.
  • core holes are made in the component with a first tool. 2.
  • the holes are spindled twice with a second tool, rubbed once with a third tool and lowered with a fourth and fifth tool. 3.
  • the bushes are then pressed into the component in the same drilling position. 4.
  • the bushes are spindled with a sixth tool in the drilling position and planned with a seventh tool.
  • the requirements for the accuracy of the hole and the pressing of the bushings are very high, and the wear of the tools is significant due to the properties of the CFRP material. The costs associated with the consumption of tools are correspondingly high.
  • the object of the invention is to simplify the process for assembling components, in particular CFRP components by means of bush connections, and to reduce the costs for tools and the expenditure of time.
  • Preferred embodiments of the invention are the subject of the respective subclaims.
  • the invention is not to bring the bore in the component to nominal size and then squeeze the sockets, but the hole with the core drill somewhat larger (about 1, 5 mm) réellebohren so that the socket after insertion has a residual small game , A pressing is thus eliminated, the socket can be easily put by hand or automatically without much effort. Then the set socket is received in a device and fixed so that it has the best position for later fuselage connection.
  • the remaining gap between the bushing and the component is filled with a filling material (shim mass, quick shim), which is then cured.
  • a filling material shim mass, quick shim
  • the filling with filling material can be done in various ways, for example via injection at the component or via channels in the socket. After the shim has hardened, the spindle is spindled and planed.
  • the method according to the invention for inserting a bushing into a component comprises the steps of: creating a through-bore in the component for the bushing having a predetermined diameter that is greater than the outside diameter of the bushing so that a gap remains between the component and the bushing, Insert the bush into the through hole and fill the space with a filler.
  • this is realized as a further feature or - as far as is technically possible and meaningful - as further features that:
  • the predetermined diameter of the through hole between 1 mm and 2 mm and in particular 1, 5 mm larger than the outer diameter of the bushing;
  • the insertion of the socket comprises: aligning the socket in the through hole in a desired direction, fixing the socket in a holding device and screwing the socket with a union nut;
  • the filling of the intermediate space with filling material comprises an injection via channels in the component
  • the filling of the intermediate space with filling material comprises an injection via channels in the bushing and / or the union nut;
  • the component consists of a carbon fiber reinforced plastic.
  • the corresponding socket according to the invention with a sealing element for insertion into a component wherein the socket comprises a flange at one end and a sealing element at an opposite end, is characterized by at least one channel in the flange and / or the sealing element for injecting filling material into one Space between the bush and the component.
  • the at least one channel for injecting filler material into the flange and / or the sealing member has a distance from a pipe section of the bush which is between 1 mm and 2 mm.
  • the bushing at an end opposite the flange has an external thread onto which a union nut is screwed as a sealing element.
  • Advantages of the invention include that fewer tools are needed. Furthermore, a readjustment of the socket due to their play in the bore even after insertion into the component is possible. Conversely, this means that the initial drilling no longer has to meet such high requirements in terms of precise alignment, but that the alignment can be corrected if necessary later.
  • Fig. 1 shows a center box of a rudder with longitudinal force fittings to which the invention is applicable, in perspective view.
  • Fig. 2 shows a part of the center box of FIG. 1 in magnification, in a perspective view.
  • Fig. 3 shows a bushing according to the prior art in cross section.
  • Fig. 4 shows an embodiment of the socket according to the invention in cross section.
  • Fig. 5 shows the embodiment of the socket according to the invention in the installed state in a perspective view.
  • a center box 1 of a vertical tail of an aircraft is shown.
  • this center box 1 In order to firmly connect this center box 1 with the (not shown) fuselage of the aircraft, 1 tabs are attached to one side of the center box, which absorb the longitudinal force acting on the compound.
  • the tabs 2 are therefore referred to as longitudinal force fittings. They are preferably welded to the center box 1 or are a part of the same.
  • the center box 1 is made in modern aircraft from carbon fiber reinforced plastics (CFRP).
  • CFRP carbon fiber reinforced plastics
  • the connecting bolts are usually made of titanium.
  • the bolt must be accurately received in the through hole 3. If this is not the case, then it comes to (small) movements of the bolt in the bore 3, so that it is knocked out after some time and thus reduces the fit accuracy increasingly with time. Therefore, the hole 3 is lined in the center box 1 with a metal bushing whose inner diameter substantially coincides with the outer diameter of the bolt. The insertion of the metal bush in the through hole 3 according to the prior art will be briefly explained below.
  • the rudder With the longitudinal force fittings 2, the rudder is mounted with bolts on the fuselage section of the aircraft. For Lekskraftbeyersbuchsen 4 are introduced into the component. The essential steps are automated.
  • the production plant is a drilling rig. With him, the holes 3 are processed for the Lekssskraftbeschlagsbuchsen and the bushes 4 pressed.
  • the drilling rigs for the assembly of the center turrets 1 of the vertical stabilizers are identical for both "single aisle" (SA) aircraft and “twin aisle” (TA) aircraft, but it is possible for them to be rotated by 90 ° be used. They each have two workstations on which the longitudinal force fittings 2 can be machined. In the drilling stand, after testing and measuring, the following operations are performed on the structure:
  • the testing and measuring of the positions for the longitudinal force fitting bushes 4 is as follows:
  • the longitudinal force fittings 2 are pre-drilled in the shell production, so that the components equipped with pilot holes (VBL) 3 come to the assembly station.
  • VBL pilot holes
  • the exact hole positions must be determined. This is done by means of (not shown) buttons.
  • Such a probe is used for this purpose in the drilling. With the probe, the drilling rig checks the position of the pilot holes and determines the exact position of the longitudinal fitting holes 3. Since the fin is connected to the fuselage via the longitudinal force fitting bushings, very high demands are placed on the bore quality.
  • the boring of the longitudinal force fitting bore is as follows: With the drill stand, the bores for the longitudinal force fitting bushings 4 are reworked. For this purpose, several tools are used successively in the drill stand, with which the respective processing is performed. These tools include tool carriers equipped with multiple indexable inserts. To approximate the holes 3 to the final gauge, they are drilled with a boring head. Subsequently, the holes are machined with a so-called. Reibtechnikmaschine. The hole is finished with the reaming tool. The reaming tool is similar to a drill bit, but with the reaming tool the cutters are also on the circumference and not just on the tip as in the drill.
  • Reaming tools may have different cutting shapes, either spiral shaped (as in a drill) or grooved. When working with the reaming tool, only a few tenths of a millimeter of material is removed in the hole, the hole is then a perfect fit and has a high surface quality. In addition, higher accuracies are achieved with respect to the shape tolerances. Overall, a grated hole has a more accurate roundness and has a higher cylindricity than a drilled hole.
  • the lowering of the hole joins it as another step.
  • the bore is lowered from both sides.
  • the counterbores are introduced to facilitate the insertion of the longitudinal force fitting bushes.
  • the self-injection, the screwing and the spindle of the longitudinal force fitting bushings takes place in the following manner:
  • the longitudinal force fitting bushes 4 are made of titanium. They consist of two parts, a bush 4 and a sealing element, in particular a nut 5. They are pressed into the holes and screwed together with a prescribed torque. A possibly existing material supernatant 8 at the hole edge of the sockets 4 is milled away. Finally, the sockets 4 are spinded to final dimensions.
  • the fitting bushes 4 have a flange 7.
  • the method according to the prior art for producing a positive connection of at least two CFRP components 1 has essentially the following steps:
  • the socket 4 is pressed into the fastening tab 2. Apart from friction and bonding in the tab 2, it is held in the tab 2 by a flange 7 on both sides of the bore 3.
  • the flange 7 is fixedly connected on one side with a pipe section 6 of the bush 4, on the other side of the pipe section 6, the flange 7 is placed on the sleeve projection 8, which projects beyond the bore 3, separately or is screwed in particular as a union nut.
  • this complicated method can surprisingly be simplified considerably by providing the through-bore 3 with a predetermined diameter which is greater than the outer diameter of the bushing 4. This becomes clear in FIG. 4. Due to the different diameters of bushing 4 and bore 3, a space 10 between the component 1 and the bushing 4 remains free in addition to the bushing 4 in the material of the center box 1. In this way, the insertion of the sleeve 4 in the bore 3 can be simplified, and by the resulting game of the socket in the bore, the sleeve 4 can be aligned later in the bore 3. On the other hand, however, to ensure a sufficient strength and thus resilience of the bush 4 in the bore 3, the gap 10 is filled with a (not shown) filling material.
  • This filling material can be injected, for example via a channel 1 1 in the flange 7 of the bushing 4 in the gap 10.
  • a channel 12 can be provided through which additionally or alternatively filling material can be injected into the gap 10.
  • the filler is in particular a so-called shim material, wherein the shim material is preferably fast curing. In this way it is ensured that the socket can be aligned, then shim material can be injected into the gap 10, which cures quickly, and then the socket is fully loadable.
  • the bushing 4 When hardening the shim material, the bushing 4 is preferably fixed in a (not shown) holding device, and then the bushing 4 is screwed to the nut 5. If the bushing 4 is slightly inclined to the surface after alignment, the surface of the longitudinal force fitting 2 can subsequently be milled flat in a further processing step.
  • the bush 4 is shown in a perspective view after it has been inserted into the longitudinal force fitting 2, aligned and fixed with filler. Visible is the borehole 3 in the fitting 2 and the flange 7 of the bushing 4. In the flange 7 are injection openings 13 for the filling material. After a final surface treatment, the bushing 4 flush with the surface of the tab 2.
  • the distance of the injection holes 13 from the bore 3 is preferably between 1 mm and 2 mm and in particular less than 1, 5 mm, so that the predetermined diameter of the through hole 3 is substantially 1, 5 mm larger than the outer diameter of the sleeve 4 without flange. 7 is, ie as the outer diameter of the pipe section 6.
  • the invention is not restricted to the fact that the filling material is injected via the channels 11 and 12 in the flange 7 or the union nut 5 of the bushing 4. Instead, the filling of the intermediate space 10 with filling material can also take place via channels (not shown) in the component 1 itself.
  • a socket according to the invention with a union nut for receiving a connecting bolt is provided with channels 1 1 and 12 respectively. Consequently, the bushing 4 comprises at one end of the pipe section 6 a flange 7 and at an opposite end of the pipe section 6 an external thread 9 for the union nut 5.
  • the flange 7 and in the union nut 5 is at least one channel 1 1, 12 for injection of filler material in a gap 10 adjacent to the bushing 4.
  • four channels are arranged symmetrically around the pipe section 6 around.
  • the process according to the invention is thus considerably shortened compared with the process according to the prior art.
  • the core holes are made in the component with a first tool and lowered the bore with a second tool.
  • the bush is inserted (if necessary without tools) and fixed in the device (best fit).
  • a filling compound (shim) is filled in and cured.
  • the bush is spindled with a third tool and then planned with a fourth tool.
  • the invention described herein is not limited to aircraft and not to the connection of a rudder with a fuselage. Instead, the invention may also find application in the absorption of shear forces and in all component connections where a highly accurate fit of connecting bolts is necessary.
  • the invention is particularly advantageous applicable to components made of CFRP material, but it can just as well be used for components made of aluminum.
  • the invention is not limited to sockets with union nut, instead, a smooth-walled socket can be used, in which the gap 10 between the socket and the component is closed by a pressed-on lid or other sealing device.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Bolts, Nuts, And Washers (AREA)

Abstract

L'invention concerne un procédé d'insertion d'une douille (4) dans un composant (1), ainsi qu'une douille correspondante. Afin de faciliter l'insertion de la douille dans le composant et de réduire les coûts d'outillage ainsi que le temps consacré, en particulier dans le cas de composants en matière plastique renforcé de fibres de carbone (CFK), il est proposé selon l'invention que le procédé comprenne les étapes suivantes : réalisation d'un trou traversant (3) dans le composant pour la douille (4), avec un diamètre prédéterminé qui est supérieur au diamètre extérieur de la douille (4), si bien qu'un espace (10) subsiste entre le composant (1) et la douille (4), insertion de la douille (4) dans le trou traversant (3) et remplissage de l'espace (10) à l'aide d'un matériau de remplissage. La douille correspondante possède au moins une ouverture (11) dans la bride (7) et/ou dans l'élément d'étanchéité (5) pour l'injection de matériau de remplissage dans un espace (10) entre la douille (4) et le composant (1).
PCT/EP2009/052577 2008-04-24 2009-03-05 Procédé d’insertion d’une douille dans un composant et douille WO2009130082A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008020614A DE102008020614A1 (de) 2008-04-24 2008-04-24 Verfahren zum Einsetzen einer Buchse in ein Bauteil und Buchse
DE102008020614.8 2008-04-24

Publications (1)

Publication Number Publication Date
WO2009130082A1 true WO2009130082A1 (fr) 2009-10-29

Family

ID=40740116

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2009/052577 WO2009130082A1 (fr) 2008-04-24 2009-03-05 Procédé d’insertion d’une douille dans un composant et douille

Country Status (2)

Country Link
DE (1) DE102008020614A1 (fr)
WO (1) WO2009130082A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114905776A (zh) * 2022-05-30 2022-08-16 浙江万丰飞机制造有限公司 一种复合材料孔的维修方法

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GB2017857A (en) * 1978-03-25 1979-10-10 Camloc Fastener Gmbh An insert for installation in a sandwich panel
US4763399A (en) * 1986-03-14 1988-08-16 The Boeing Company Method of bolt hole strengthening in a fibrous composite laminate
US4981735A (en) * 1989-09-05 1991-01-01 The United States Of America As Represented By The Secretary Of The Army Two piece threaded mounting insert with adhesive for use with honeycomb composite
US5093957A (en) * 1991-07-08 1992-03-10 Atr International, Inc. Compression fitting for use in a two-sided honeycomb panel
DE4118282C1 (en) * 1991-06-04 1992-08-13 Riese, Dominik, 2000 Hamburg, De Assembling or repairing plain bearing - has bush with conical bore glued by hardenable adhesive esp. 2-component epoxy] resin in support
FR2681003A1 (fr) * 1991-09-10 1993-03-12 Aerospatiale Procede d'assemblage d'une piece en materiau sandwich et d'une piece metallique, outillage pour la mise en óoeuvre du procede, et assemblage obtenu.
DE19520065A1 (de) * 1995-06-06 1996-12-12 Michael Prof Dr Ing Schlimmer Verfahren zur Herstellung einer Klebverbindung und damit hergestellte Anordnung
DE19812814A1 (de) * 1998-03-17 1999-09-23 Gebo Gmbh Glasbalkenanschluß
US20040265091A1 (en) * 2003-06-30 2004-12-30 Cheung Kwun-Wing W. Universal bulkhead fitting

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DE2750829C2 (de) * 1977-11-14 1982-12-16 Camloc Fastener Gmbh, 6233 Kelkheim Vorrichtung zum Einsetzen und Vergießen eines in einer Leichtbau-Schichtverbundplatte mit Vergußmasse zu befestigenden Gewindedübels o.dgl.
DE3132828C2 (de) * 1981-08-19 1986-02-13 Rudolf Dr.-Ing. 8000 München Sell Anschlußmittel für Holzstäbe und Verfahren zum Einbau des Anschlußmittels
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EP0461299B1 (fr) * 1990-06-11 1996-01-03 Atr International, Inc. Appareillage pour fixer un élément insérable de fixation dans un panneau en nid d'abeilles
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Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2017857A (en) * 1978-03-25 1979-10-10 Camloc Fastener Gmbh An insert for installation in a sandwich panel
US4763399A (en) * 1986-03-14 1988-08-16 The Boeing Company Method of bolt hole strengthening in a fibrous composite laminate
US4981735A (en) * 1989-09-05 1991-01-01 The United States Of America As Represented By The Secretary Of The Army Two piece threaded mounting insert with adhesive for use with honeycomb composite
DE4118282C1 (en) * 1991-06-04 1992-08-13 Riese, Dominik, 2000 Hamburg, De Assembling or repairing plain bearing - has bush with conical bore glued by hardenable adhesive esp. 2-component epoxy] resin in support
US5093957A (en) * 1991-07-08 1992-03-10 Atr International, Inc. Compression fitting for use in a two-sided honeycomb panel
FR2681003A1 (fr) * 1991-09-10 1993-03-12 Aerospatiale Procede d'assemblage d'une piece en materiau sandwich et d'une piece metallique, outillage pour la mise en óoeuvre du procede, et assemblage obtenu.
DE19520065A1 (de) * 1995-06-06 1996-12-12 Michael Prof Dr Ing Schlimmer Verfahren zur Herstellung einer Klebverbindung und damit hergestellte Anordnung
DE19812814A1 (de) * 1998-03-17 1999-09-23 Gebo Gmbh Glasbalkenanschluß
US20040265091A1 (en) * 2003-06-30 2004-12-30 Cheung Kwun-Wing W. Universal bulkhead fitting

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114905776A (zh) * 2022-05-30 2022-08-16 浙江万丰飞机制造有限公司 一种复合材料孔的维修方法

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