WO2006008106A1 - Procede pour produire une piece de tole courbee de maniere cylindrique, en particulier une piece de tole de l'enveloppe exterieure d'un aeronef - Google Patents

Procede pour produire une piece de tole courbee de maniere cylindrique, en particulier une piece de tole de l'enveloppe exterieure d'un aeronef Download PDF

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Publication number
WO2006008106A1
WO2006008106A1 PCT/EP2005/007783 EP2005007783W WO2006008106A1 WO 2006008106 A1 WO2006008106 A1 WO 2006008106A1 EP 2005007783 W EP2005007783 W EP 2005007783W WO 2006008106 A1 WO2006008106 A1 WO 2006008106A1
Authority
WO
WIPO (PCT)
Prior art keywords
metal part
sheet metal
stringers
areas
stringer
Prior art date
Application number
PCT/EP2005/007783
Other languages
German (de)
English (en)
Inventor
Gerd K. H. Sepold
Henri Lajain
Original Assignee
Sepold Gerd K H
Henri Lajain
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 Sepold Gerd K H, Henri Lajain filed Critical Sepold Gerd K H
Publication of WO2006008106A1 publication Critical patent/WO2006008106A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass

Definitions

  • the present invention relates to a method for producing a curved outer skin sheet metal part of a missile, in particular the fuselage of an aircraft, which is provided with ribs and stringers. Furthermore, the present invention relates to a corresponding Vor ⁇ direction and an outer skin sheet metal part of a missile.
  • a cylindrically curved sheet-metal part provided with ribs and stringers such as, for example, the outer skin sheet metal part of a missile, in particular the fuselage of an aircraft. All known methods have in common that first a planar sheet metal part is brought into the required curved shape, for example by ironing or hot calibration. Only then is the surface of the curved sheet-metal part to be provided with the ribs and stringers prepared for the application of the ribs and stringers, in particular by the introduction of so-called zone areas, for example by chemical etching, in which the sheet metal part has a smaller thickness than in the others areas. Subsequently, the stringers and frames are applied.
  • the application of the stringers and frames is usually done by riveting, the stringers and frames are connected to each other or indirectly with the sheet metal part via so-called clips.
  • stringer connections are also made by welding or gluing.
  • the processing of the curved sheet metal part ie in particular the introduction of the pocket areas and the Applying the stringers and ribs on the curved sheet metal part, but brings ferti ⁇ technology technically quite a lot of effort.
  • the ironing requires a smooth surface, ie an introduction of pocket areas before the curvature of the sheet metal part, ie in a flat state of the sheet metal part is not possible.
  • the present invention is therefore based on the object of specifying a manufacturing process which is simpler with regard to the production effort and a corresponding production device. Furthermore, a simple to be manufactured sheet metal part should be specified.
  • a corresponding manufacturing device is specified in claim 11.
  • a cylindrically curved sheet-metal part manufactured according to the method according to the invention is specified in claim 12.
  • Advantageous embodiments are specified in the subclaims.
  • the invention is based on the recognition that it is much easier to manufacture pocket areas in the sheet metal part and to apply the stringer on the Blech ⁇ part, if it is planar and not yet curved manufacturing technology.
  • For the introduction of the pocket areas can thus be used quite different manufacturing processes, such as milling process.
  • the application of the stringers is much easier, so that other manufacturing processes can be used for this purpose. If, as erfin ⁇ according to provision, only after the sheet metal part is curved, can also be a achieve significantly higher production accuracy.
  • the sheet metal part is plastically deformed to achieve the required curvature
  • an elastic deformation for example, with suitable negative and positive forms
  • the sheet metal part in the desired, cylindrically curved position hold until the last pre-curved frames are applied to the sheet metal part in a final step.
  • These frames thus hold the elastically deformed sheet metal part in its curved shape.
  • the curvature of the sheet metal part is thus much easier to accomplish than in the known methods in which a permanent, plastic deformation must be made.
  • the inventive method unlike the known method in which the sheet metal part is plastically deformed, the deformation of different thickness sheet metal areas possible.
  • the stringer and the ribs are applied directly to the sheet metal part, in particular by a thermal method, such as laser welding, laser soldering or electron beam welding. Also hybrid methods such as e.g. Arc and laser processes are conceivable. This applies in particular when the sheet metal part is manufactured according to the inventive method described above; In principle, however, such welding can also be used in all other production methods.
  • so-called clips ie connecting pieces between stringers and ribs or between stringers or ribs and sheet metal part, are dispensed with; the frames and stringers are rather directly welded together and directly on the sheet metal part.
  • many intermediate steps for the attachment of the clips can be omitted, which means a significant reduction in time in the production.
  • the elimination of the clips leads to a reduction in weight, since the stringer and frames also need no special foot for attaching the clips more.
  • connection methods such as soldering, gluing, riveting, electron beam welding or other joining methods
  • laser welding, laser soldering or the above-mentioned hybrid method are preferably used, since they are particularly fast and accurate in production.
  • the ribs have recesses in places where they run above the stringers, and that the ribs are connected directly to the stringers.
  • the frames can thus be connected directly between the Stringem with the sheet metal part in this embodiment and do not extend in a uniform distance above the sheet metal part and on the stringers away, as is the case with some known methods. This achieves an integral construction in which the frames and the stringers are connected directly, permanently and without clips to one another, something that could not previously be achieved with the known methods.
  • the frames are welded or soldered to the stringers passing through the recesses, in particular on the edge of a recess facing the stringer, substantially parallel to the sheet metal part, with the edge of the stringer facing this edge. If required for reasons of strength, the seam between stringer and bulkhead can also be continued until at most the foot of the stringer is reached.
  • the methods preferably used for welding namely laser welding, laser hybrid welding and protective gas welding, have a higher gap bridging capability, so that a larger gap, which can not be bridged, between the stringer and bulkhead in the region of the recess is bridged and the stringer with the bulkhead can be welded there.
  • the raised So ⁇ ckel regions between the pocket areas at least partially have a groove for introducing an edge of the there applied formers or stringer.
  • These grooves can be continuous or only in sections and serve as positioning aids in the application of the stringer or ribs.
  • the groove may be advantageous when using a laser (hybrid) welding process.
  • the grooves are given in claims 6 and 8.
  • the grooves can also be filled with additional wire in order to effect a uniform element distribution into the depth.
  • the grooves can be used to influence the thermal behavior.
  • the specific design of the groove possibly in conjunction with a corresponding Aus ⁇ design of the introduced into the groove edge of the spar or stringer, it also makes it possible to ver ⁇ change the angle of the laser heads for welding in a suitable manner. For example, it can be achieved by means of a funnel-shaped groove and sharpened edges that the laser heads can be tilted (perpendicular to the outer skin sheet metal part) during laser welding.
  • chord is carried out according to a further preferred embodiment with the following steps: d1) placing the clip on the stringer passing through the recess and bringing one edge of the chime into the groove provided in the corresponding frame base area, d2) welding or Soldering of the introduced into the groove edge of the bulkhead with the frame base portion and d3) welding or soldering the stringer assigning, extending substantially parallel to the sheet metal part edge of a recess of the frame with this edge facing edge of the extending through the recess stringer.
  • the groove in which a bulkhead is introduced, has some air when the bulkhead is placed on the underlying in the recess stringers, so that in any case prevents an air gap at the weld between the stringers and bulkhead in this recess remains.
  • the Doppelpas ⁇ solution is repealed.
  • an air gap remaining in the grooves may be filled with additional material (e.g., solder) prior to or during welding - i.a. also by hybrid methods - be filled. With this configuration, a particularly reliable connection between stringers and frame can be achieved.
  • additional material e.g., solder
  • welding or soldering is continued up to the foot of the stringer.
  • the pocket areas are grooves, in particular by a milling method, in particular a high-speed milling method, introduced into areas of the surface of the planar sheet-metal part grooves.
  • a corresponding manufacturing device according to the present invention is specified in An ⁇ claim 11. This can be made considerably simpler than known production devices, since the production steps are still partially carried out with the planar sheet-metal part.
  • the pocket regions can thus be introduced, for example, by means of a suitable milling device. Of course, however, as in the known method, chemically erosive methods can be used.
  • the stringer and ribs are preferably applied by welding devices, in particular laser welding devices.
  • negative molds for elastic deformation of the provided with the stringers sheet metal part to introduce the desired curvature
  • negative molds for example, negative molds can be used, in which the planar sheet metal part is inserted, then pressed with a corresponding positive shape and thus pressed against the negative mold.
  • the sheet metal part is optionally held with suitable clamping means until the (circular) curved frames are applied, which then hold the sheet metal part, for example by joining with the laser beam in its curved shape.
  • FIG. 1 shows a known outer skin sheet metal part of the fuselage of an aircraft in a rivet construction
  • Fig. 2 shows an inventive outer skin sheet metal part of the fuselage of an aircraft in
  • FIG. 3 to 8 different embodiments of the invention used grooves for receiving stringers or frames.
  • Figure 1 shows a known, provided with frames and stringers outer skin sheet metal part 10 of the fuselage of an aircraft, which was prepared by a known manufacturing process.
  • the curvature of the outer skin sheet metal part 10 which corresponds to the curvature of the fuselage of the aircraft.
  • Evident are further two parallel to each other and extending in the longitudinal direction of the fuselage of the aircraft stringer 11 and a transversely extending bulkhead 12, which has the same curvature as the outer skin sheet metal part 10.
  • the stringers 11 are applied directly to the outer skin sheet metal part 10, for example as riveted in the case shown.
  • the bulkhead 12 is also riveted directly to the outer skin sheet metal part 10 in some areas.
  • the bulkhead 12 In other areas in which the bulkhead 12 leads over the stringers 11, the bulkhead 12 has recesses 13, through which the stringers 11 each pass. At these recesses, the bulkhead 12 is connected indirectly to the stringers 11 by means of so-called clips 14, which are riveted to the bulkhead 12 and the stringers 11, respectively.
  • outer skin sheet metal part 10 takes place in the order that initially the pure outer skin sheet metal part, which is still in planar state, is plastically curved, so that the curvature remains permanently in the outer skin sheet metal part 10. This can be done for example by means of an ironing process. Thereafter, the stringers 11 and then finally the bulkhead 12 are applied.
  • this application of the stringers 11 and the bulkhead 12 to the curved outer skin sheet metal part is not optimal in terms of production and can lead to inaccuracies, so that strands and / or ribs may not exactly abut each other when assembling a plurality of outer skin sheet metal parts and their Position must sometimes be corrected mechanically afterwards.
  • FIG. 1 An outer skin sheet metal part 20 of the fuselage of an aircraft according to the invention, provided with frames and stringers, which was produced by the method according to the invention, is shown in FIG.
  • two stringers 21 arranged parallel to one another and extending in the longitudinal direction of the fuselage and a bulkhead 22 extending transversely thereto are mounted directly on the outer skin sheet metal part 20, in the case shown welded up.
  • the bulkhead 22 also has recesses 23.
  • the outer skin panel 20 also has a curvature corresponding to the curvature of the fuselage of the aircraft.
  • the outer skin sheet metal part 20 is produced by first introducing so-called pocket regions 24 into the still planar outer skin sheet metal part 20 in areas in which neither stringer 21 nor the bulkhead 22 are applied to the outer skin sheet metal part 20. This is preferably done by means of a milling process, but can also be carried out by other methods, for example by a chemical etching process. In these pockets 24, the outer skin sheet metal part 20 thus has a smaller thickness than in the remaining so-called base areas, namely the stringer base areas 25, in which the stringers 21 are arranged, and the frame base area 26, in wel ⁇ chem later, the bulkhead 22 is arranged.
  • the stringer 21 are also applied in ebenflambaigem state of the outer skin sheet metal part 20 in the stringer base areas 25, welded in the present example by laser welding.
  • a groove 27 is provided in the stringer base regions 25, which, before or after introduction of the pocket regions 24, is introduced into the outer skin sheet metal part 20 there, for example by milling.
  • the lower edge of the stringer 21 is then inserted, so that the stringer sits exactly at the vorge- see position before it is firmly connected to the outer skin sheet metal part 20.
  • the stringers 21 When the stringers 21 are applied to the skin panel 20, it is then elastically deformed in a flexurally-slippery direction to provide the desired curvature.
  • This can be done, for example, by means of a suitable negative mold into which the outer skin sheet metal part 20 is pressed by means of a positive mold.
  • the already pre-curved bulkhead 22 is then applied in the frame base area 26 provided for this purpose.
  • a groove 28 is likewise provided, in which the lower edge of the rib 22 is inserted, before the bulkhead 22 is secured to the outer skin sheet metal part 20 by a joint. process is connected.
  • the application of the bulkhead 22 is carried out according to the invention preferably such that the bulkhead 22 is first placed on the stringers 21 in the recesses 23, wherein the lower edge is introduced into the groove 28.
  • the groove 28 is designed so deep that in no case air between bulkhead 22 and stringers 21 in the region of the recesses 23 in which the welds 29 are to be attached, remains, but that at most air below the lower edge of the bulkhead 22 within the groove 28 remains , Then, the bulkhead 22 is connected to the stringers 21 by a weld seam 29, preferably by means of laser welding, laser soldering or hybrid welding. Only then is the bulkhead 22 connected to the outer skin sheet metal part 20 at the weld seam 30, again preferably by laser welding or laser soldering.
  • the grooves 27 and 28 may be provided continuously or only in sections.
  • the groove as shown in Figure 3a (before welding), a rectangular cross section.
  • Figure 3b shows the weld 30, which results after joining.
  • the advantage here is that a low heat input for welding is er ⁇ required.
  • Figure 3c shows an alternative weld 30 ' which results when the frame-base portion shown in Figure 3a and designated 26' is substantially narrower than the original frame-base portion 26, indicated by the dotted line.
  • no additional material ie no additional wire, needs to be used, but the shoulders of the frame base region 26 'are directly melted off. This solution thus also results in a lower weight, and the process is simplified.
  • these grooves enable improved welding in connection with the base areas, since the welding unit (s), for example a laser used for welding, can be almost perpendicular to angled (eg up to about 45 °) to the weld, as shown by way of example in FIG. 3 a, dashed lines for a laser 50 without integrated wire feed, can be introduced.
  • the welding unit must therefore not, as usual, under at a much smaller angle obliquely laterally be introduced to the weld as shown in Figure 3 for a laser 40, resulting in a significant reduction of the so-called Zeppelins effect, that brings less deformation at the opposite surface of the weld sheet metal part with it. Furthermore, can be omitted by suitable Nut joint the additional wire for joining. An improvement of the fatigue behavior is also achievable.
  • strippers for attachment in a groove 27 of a stringer base region 25 have a widened foot region 21a, which is placed directly down to the bottom of the groove 27.
  • laser welding units 40 such a stringer can be melted into the groove without having to introduce additional welding material.
  • FIG. 32 An embodiment of a groove 32 with a funnel-shaped cross section is shown in FIG.
  • additional material so for example powder, wire or solder, introduced, which preferably also takes place in advance.
  • strips can be inserted in advance in the groove, which are then fused during welding.
  • the lower edge of the bulkhead 22 has a rectangular cross-section, but the lower edge may also be wedge-shaped (with an angle adapted to the angle of the funnel of the groove 32) to allow welding with laser heads inclined obliquely from above ,
  • FIG. 5a A further embodiment with a negative groove 33, which is shown by way of example on a frame base region 26, is shown in FIG. 5a (before welding) and FIG. 5b (after welding).
  • the bulkhead 22 in this case has one of the positive groove 33, which may be formed, for example, as a rectangular elevation, corresponding negative groove 22a in the foot area.
  • additional material for welding is introduced into the gap between the foot region of the bulkhead 22 and the surface of the positive groove 33 or of the frame base region 26.
  • FIG. 1 A further embodiment of grooves, which is particularly suitable for welding stringers 21, is shown in FIG. There, two parallel, groove-like grooves 35 are introduced into the surface of the stringer base region 25, in which corresponding projections 21 b engage in the foot region of the stringer 21.
  • Such a configuration is for 07783
  • FIG. 7a A further embodiment, which is likewise preferred for attaching stringers, is shown in FIG. 7a.
  • the surface of the stringer base region 25 is formed in a stepped manner with a step 36.
  • a corresponding step 21b has the foot of the stringer 21.
  • additional material 45 can be introduced for soldering or welding so that no gap remains after soldering or welding. It does not have to be welded / soldered on both sides, but it can only be soldered on one side in position I or II.
  • tensioning devices e.g., pressure rollers
  • the gap can be set to zero, as shown in Figure 7b.
  • FIG. 8 shows an embodiment in which an air gap 60 remains between the upper side of the stringer 21 and the lower side of the overhanging rib 22, in which case the stringer 21 is inserted completely into the groove in the associated stringer base region 25.
  • additional material depending on the method.
  • Such an embodiment of the joining method allows the bridging of this gap 60. Problems of the double-fit described above can thus be achieved by a suitable hybrid welding method, e.g. MIG + laser, or be remedied by a protective gas process alone with regulated wire feed.
  • the method according to the invention is preferably used for producing fuselage parts of an aircraft.
  • the method according to the invention can also be used in the transport of lightweight components, such as Scha ⁇ len, or for the production of outer skin sheet metal parts for wing noses or tail on aircraft.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laser Beam Processing (AREA)

Abstract

L'invention concerne un procédé pour produire une pièce de tôle (10) courbée de manière cylindrique comportant des couples (12) et des raidisseurs (11), en particulier une pièce de tôle de l'enveloppe extérieure d'un aéronef, telle que le fuselage d'un avion. Le procédé selon l'invention comprend les étapes qui consistent : a) à introduire des zones formant des poches (24) dans des zones d'une surface d'une pièce de tôle (10) plane, dans lesquelles aucun couple ou/ni aucun raidisseur n'est monté, de manière que la pièce de tôle présente, à cet endroit, une épaisseur plus faible que dans les zones de socle dans lesquelles les couples et/ou les raidisseurs sont montés ; b) à monter un ou plusieurs raidisseurs (11) disposés de manière sensiblement parallèle les uns par rapport aux autres, sur la pièce de tôle (10) plane, dans des zones convexes de socle à raidisseur, entre les zones formant des poches (24) ; c) à déformer élastiquement la pièce de tôle (10) de l'enveloppe extérieure qui comporte les raidisseurs (11), de manière que la pièce de tôle (10) soit courbée de manière voulue ; d) à monter un ou plusieurs couples (12) qui sont disposés de manière sensiblement parallèle les uns par rapport aux autres et perpendiculaire par rapport aux raidisseurs (11) et qui présentent la même courbure que la pièce de tôle courbée, sur la pièce de tôle courbée, dans des zones convexes de socle à couple, entre les zones formant des poches (24), de manière que la pièce de tôle reste courbée.
PCT/EP2005/007783 2004-07-21 2005-07-16 Procede pour produire une piece de tole courbee de maniere cylindrique, en particulier une piece de tole de l'enveloppe exterieure d'un aeronef WO2006008106A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004035170.8 2004-07-21
DE200410035170 DE102004035170B3 (de) 2004-07-21 2004-07-21 Verfahren zur Fertigung eines zylindrisch gekrümmten Blechteils, insbesondere eines Außenhaut-Blechteils eines Flugkörpers

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WO2006008106A1 true WO2006008106A1 (fr) 2006-01-26

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PCT/EP2005/007783 WO2006008106A1 (fr) 2004-07-21 2005-07-16 Procede pour produire une piece de tole courbee de maniere cylindrique, en particulier une piece de tole de l'enveloppe exterieure d'un aeronef

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DE (1) DE102004035170B3 (fr)
WO (1) WO2006008106A1 (fr)

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CN103241360A (zh) * 2012-02-07 2013-08-14 波音公司 具有带内部与外部纵梁的连续蒙皮的结构性接头
CN107443023A (zh) * 2017-08-31 2017-12-08 武汉理工大学 一种带筋薄壁大型铝合金筒的柔性加工方法

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DE102007019821B4 (de) 2007-04-26 2012-11-22 Airbus Operations Gmbh Strukturelement eines Flugzeugrumpfs
DE102008025646B4 (de) * 2008-05-28 2012-11-22 Lfk-Lenkflugkörpersysteme Gmbh Schweißverbindung zwischen einem Hautblech und einem Stringer
DE102009007730B4 (de) * 2009-02-05 2017-12-14 Mbda Deutschland Gmbh Strukturbauteil
DE102010010185A1 (de) * 2010-03-03 2011-09-08 Airbus Operations Gmbh Bauteilsverbindungsanordnung sowie Verfahren zur umformtechnischen Erzeugung derselben
ES2400771B1 (es) * 2011-03-30 2014-02-14 Airbus Operations S.L. Fuselaje de aeronave con cuadernas altamente resistentes.
US9840041B2 (en) 2013-12-20 2017-12-12 Saab Ab Stiffening element and reinforced structure
CN103693031B (zh) * 2013-12-26 2017-02-08 麻城市博远制动科技有限公司 一种铝镁合金储气筒及其制造方法
CN110480262B (zh) * 2019-08-13 2021-08-03 成都飞机工业（集团）有限责任公司 大型高精度变截面曲面长桁制造工艺
US11613340B2 (en) * 2020-05-21 2023-03-28 North West Heli-Structures Incorporated Panel systems and methods for helicopters

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CN103241360B (zh) * 2012-02-07 2016-08-24 波音公司 具有带内部与外部纵梁的连续蒙皮的结构性接头
CN107443023A (zh) * 2017-08-31 2017-12-08 武汉理工大学 一种带筋薄壁大型铝合金筒的柔性加工方法

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