WO2005007507A1 - Composant structurel en aluminium soude et pourvu d'elements realises dans un materiau aluminium coule - Google Patents

Composant structurel en aluminium soude et pourvu d'elements realises dans un materiau aluminium coule Download PDF

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Publication number
WO2005007507A1
WO2005007507A1 PCT/DE2004/001387 DE2004001387W WO2005007507A1 WO 2005007507 A1 WO2005007507 A1 WO 2005007507A1 DE 2004001387 W DE2004001387 W DE 2004001387W WO 2005007507 A1 WO2005007507 A1 WO 2005007507A1
Authority
WO
WIPO (PCT)
Prior art keywords
structural component
welded
cast
connecting element
welding
Prior art date
Application number
PCT/DE2004/001387
Other languages
German (de)
English (en)
Other versions
WO2005007507B1 (fr
Inventor
Frank Palm
Original Assignee
Eads Deutschland 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 Eads Deutschland Gmbh filed Critical Eads Deutschland Gmbh
Publication of WO2005007507A1 publication Critical patent/WO2005007507A1/fr
Publication of WO2005007507B1 publication Critical patent/WO2005007507B1/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
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/14—Working by laser beam, e.g. welding, cutting or boring using a fluid stream, e.g. a jet of gas, in conjunction with the laser beam; Nozzles therefor
    • B23K26/1462—Nozzles; Features related to nozzles
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/20—Bonding
    • B23K26/21—Bonding by welding
    • B23K26/211—Bonding by welding with interposition of special material to facilitate connection of the parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/20—Bonding
    • B23K26/21—Bonding by welding
    • B23K26/24—Seam welding
    • B23K26/242—Fillet welding, i.e. involving a weld of substantially triangular cross section joining two parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/20—Bonding
    • B23K26/32—Bonding taking account of the properties of the material involved
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/18—Sheet panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/08—Non-ferrous metals or alloys
    • B23K2103/10—Aluminium or alloys thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/18—Dissimilar materials

Definitions

  • the present invention relates to a welded aluminum structural component with cast aluminum material elements according to the preamble of claim 1, and an aircraft fuselage according to claim 9, which at least partially consists of such an aluminum structural component.
  • DE 196 39 667 describes a method for laser beam welding of profiles on large-format aluminum structural components, in which two laser beams are used which are guided to the weld seam from two sides simultaneously by means of a seam search system.
  • An aircraft shell part produced by means of laser beam welding is known, for example, from DE 19844 035.
  • the wire or foil-shaped welding filler material has to be supplied in a suitable manner during laser welding and serves to suppress the formation of hot cracks during welding.
  • the present invention is therefore based on the object of creating a welded aluminum structural component which is simplified in terms of production technology and can be produced with high manufacturing reliability even in the case of complicated geometric conditions.
  • a welded aluminum structural component with cast aluminum material elements which has a skin field and at least one reinforcing element to which at least one connecting element is attached, by means of which the reinforcing element is attached to the skin field by means of welding, and thereby is characterized in that the connecting element consists of a cast aluminum material.
  • the cast aluminum material itself supplies the metallic welding filler material required to suppress hot cracking during welding, so that the use and supply of additional welding filler materials can be dispensed with entirely.
  • the manufacturing safety during welding can be increased considerably, because due to the local geometric restriction, the tracking and exact assignment of a welding filler is no longer necessary.
  • Another advantage is that the sweat-based, integral construction can be expanded further, and in principle can therefore be extended to all areas of the fuselage. This leads to a further reduction in the structural weight and reduced operating costs, since riveted structures can be completely replaced.
  • the connecting element preferably consists of an AlMg cast connection with 3 to 10% by weight of Mg, an AISi cast connection with 5 to 20% by weight of Si, an AICu cast connection with 3 to 15% by weight. % Cu or an AlZi cast connection with 4 - 20% by weight Zi.
  • a connecting element made of such an aluminum casting material is preferably used, which is produced by means of die casting, investment casting or sand casting processes or thixo or rheo casting. These manufacturing processes ensure that the cast structure has a low residual gas content and is therefore suitable for welding.
  • the skin field and reinforcing element each consist of aviation-certified aluminum alloys, such as alloys of the 2xxx, 4xxx, 5xxx, 6xxx, 7xxx and / or 8xxx alloys (according to the American alloy designation). Any combination of materials is possible, so that the structure according to the invention is flexibly suitable for aviation applications.
  • the connecting element which consists of the cast aluminum material
  • the reinforcing element is a frame, to which the clip or push comb is attached by means of rivets.
  • connection methods can also be used for fastening the connection element to the reinforcing element, such as, for example, gluing, welding, etc.
  • the welded aluminum structural component according to the invention is used in particular in aircraft, where it at least partially forms lower, upper and / or side shells of the pressure fuselage.
  • Fig. 1 shows a schematically illustrated aluminum structural component in the form of a skin field stringer clip connection.
  • FIG. 1 shows a welded aluminum structural component 1 in the form of a skin field stringer-clip connection.
  • the structural component 1 has a skin field 2, to which a multiplicity of reinforcing elements 3a, 3b are attached.
  • the reinforcements Kung elements 3a are so-called stringers that run in the longitudinal direction of an aircraft pressure fuselage.
  • three stringers 3a are attached to the skin field 2 by means of laser welding.
  • such an aluminum structural component 1 for use in aircraft pressure fuselages also has, in addition to the stringers, so-called frames, which represent reinforcing elements running in the pressure fuselage circumferential direction.
  • 1 shows a single frame 3b of this type, which is fastened to the skin field 2 by means of a connecting element 4.
  • the connecting elements 4 are typically connected to the frame by riveting, which is also shown in FIG. 1.
  • the connecting element 4 is then welded to the skin field 2 on its side opposite the frame 3b, in order thus to create a stable or reinforced aluminum structural component 1.
  • a welding filler material has previously been supplied separately, usually in the form of a wire or a foil. Due to the complex geometry, especially in the corner areas A, the problem arises that the laser welding head can only work reliably with great difficulty. In addition, the positioning of the welding filler material is considerably hampered by the stringer 3a which has already been welded on. There is therefore a very great risk that the connection cannot be welded without hot cracks, especially in the corner areas which are already at risk (local voltage increase in operation).
  • a connecting element 4 which consists of an aluminum casting material.
  • the alumi- Cast nium material can be an established or new or further developed material.
  • the choice of material for the connecting element 4 ensures that the welding filler material required for reliable and low-crack welding is dispensed by the connecting element 4 itself. It reduces the risk of hot cracking and thus ensures greater manufacturing reliability, since there is always enough filler metal on site.
  • the welding process control is simplified since no welding filler material has to be tracked or prepositioned. At the same time, the manufacturing costs for the connecting element are reduced by near-net-shape production.
  • the connecting element 4 preferably consists of an AlMg cast material with approx. 3 to 10 wt.% Mg, which additionally contains 0 to 2 wt.% Mn, Si, Sc (alternatively Zr, Ti, Y, Tb, Hf, Nb, Ta, V and / or the lanthanides) Cu, Ag and / or Fe can be added.
  • the lanthanides are preferably cerium (Ce), neodymium (Nd), europium (Eu), gadolinium (Gd), dysprosium (Dy), holmium (Ho) and / or erbium (Er).
  • the connecting element 4 can consist of an AISi cast material with 5-20% by weight of Si, to which 0-5% by weight of Mg, Cu, Fe and / or Mn can be added.
  • an AICu cast material with 3 - 15% by weight Cu is used. 0-5% by weight of Mg, Ag, Cu, Fe, Ti or Mn can be added to this.
  • the connecting element 4 consists of an AlZi compound with 4-20% by weight of Zi, to which Mg, Ag, Cu or other or further elements customary in AlZn alloys can be added.
  • these cast materials can of course also contain classic, established alloy additions that bring about a refinement of the structure (eg Sr for AISi alloys, Be for AlMg alloys or TiB 2 for general grain refinement).
  • classic, established alloy additions that bring about a refinement of the structure (eg Sr for AISi alloys, Be for AlMg alloys or TiB 2 for general grain refinement).
  • the skin field 2 and the reinforcing element 3 consist of known aeronautically certified aluminum alloys.
  • the aviation-certified alloys are, for example, alloys of the types 2xxx, 4xxx, 5xxx, 6xxx, 7xxx and / or 8xxx. According to the American alloy designation, these are AICu alloys (2xxx), AlMg alloys (6xxx), AlMgSi alloys (7xxx), AlZn alloys (8xxx) or other material systems.
  • the clip was welded to the skin area without hot cracks using laser welding using the welding filler material AA 4047 (AISM2).
  • the weld material therefore contains a mixture of the three components with the following composition: * AI Si2-4 MgO.3-0.6 CuO.2-0.4.
  • the connecting element was welded to the skin field by means of laser beam welding without the use of an additional welding filler.
  • the material of the weld seam then contains a mixture of the two components and has the following composition: «AISi3-4 Mg0.3-0.6Cu0.1-0.2 ....
  • the AISi7Mg0.6 cast clip is produced using a casting process that enables it to be welded well (low residual gas content of the cast structure).
  • HERO or SOPHIA which are qualified for aviation, but also other new die casting processes, such as thixo or rheo casting.
  • the weld material consists of a mixture of the three components: a) AI Si2-4 CuO.6-1.2 MgO.2-0.4 b) AI Cu 5-6 MgO.4-0.8 Mn c) AI Cu 6-8 MgO.2- 0.4 mn
  • the connecting element was in turn welded to the skin field without the use of an additional welding filler material.
  • the material of the weld seam is a mixture of the above components: a) AISi3-4 Cu0.8-1.4 Mg0.4-0.6 b) AICu3-4Mg0.4-0.6 c) AICu4-7Mg0.3-0.5
  • the weld material consists of a mixture of the three components:
  • Material pairing according to the invention skin field material: AIMg4.0MnScZr clip: a) AIMg3.0-5.0MnScZr b) AIMg3.0-5.0SiMn (Sc-free)
  • the clip was welded to the skin field without the use of a welding filler.
  • the weld material contains a mixture of the two components with the following composition: AIMg3.5-5.0MnScZr.
  • the cast connecting element was produced using a casting process which enables it to be welded well.
  • the Rheo-Casting process is particularly suitable in addition to the fine and sand casting processes, since this enables a mixed crystal oversaturated with Sc to be obtained after casting.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Mechanical Engineering (AREA)
  • Plasma & Fusion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laser Beam Processing (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Arc Welding In General (AREA)

Abstract

La présente invention concerne un composant structurel (1) en aluminium soudé, pourvu d'éléments réalisés dans un matériau aluminium coulé et destiné notamment aux avions. Ce composant structurel comprend un champ de revêtement (2) et au moins un élément de renforcement (3b) auquel est fixé au moins un élément de liaison (4) qui permet de fixer par soudage l'élément de renforcement (3b) au champ revêtement (2). L'invention est caractérisée en ce que l'élément de liaison (4) est constitué d'un matériau aluminium coulé.
PCT/DE2004/001387 2003-07-14 2004-07-01 Composant structurel en aluminium soude et pourvu d'elements realises dans un materiau aluminium coule WO2005007507A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10332003A DE10332003B3 (de) 2003-07-14 2003-07-14 Geschweißtes Aluminium-Strukturbauteil mit Aluminium-Guss-Werkstoffelementen
DE10332003.2 2003-07-14

Publications (2)

Publication Number Publication Date
WO2005007507A1 true WO2005007507A1 (fr) 2005-01-27
WO2005007507B1 WO2005007507B1 (fr) 2005-05-26

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PCT/DE2004/001387 WO2005007507A1 (fr) 2003-07-14 2004-07-01 Composant structurel en aluminium soude et pourvu d'elements realises dans un materiau aluminium coule

Country Status (2)

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DE (1) DE10332003B3 (fr)
WO (1) WO2005007507A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007009796A1 (fr) * 2005-07-21 2007-01-25 Airbus Deutschland Gmbh Procede pour assembler au moins deux structures planes, notamment au moins deux toles de metal pour une structure de construction legere, assemblage et construction legere

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006026918B4 (de) * 2006-06-09 2017-01-12 Airbus Operations Gmbh Rumpfstruktur
EP1880791A1 (fr) 2006-07-21 2008-01-23 Aleris Aluminum Koblenz GmbH Procédé et appareil pour l'assemblage par laser de deux composants utilisant un flux laminiare de gaz inert coaxial avec un fil d'apport métallique
DE102007048283A1 (de) 2007-10-08 2009-04-16 Eads Deutschland Gmbh Versteifungsprofil für Flugzeugstrukturen
US11613340B2 (en) * 2020-05-21 2023-03-28 North West Heli-Structures Incorporated Panel systems and methods for helicopters

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5560789A (en) * 1994-03-02 1996-10-01 Pechiney Recherche 7000 Alloy having high mechanical strength and a process for obtaining it
US5749980A (en) * 1993-08-28 1998-05-12 Kabushiki Kaisha Kobe Seiko Sho Method for improving aluminum alloy cast structural member
DE19844035C1 (de) * 1998-09-25 1999-11-25 Daimler Chrysler Aerospace Schalenbauteil für ein Flugzeug und Verfahren zur Herstellung
WO2002083389A2 (fr) * 2001-04-10 2002-10-24 Icom Engineering Corporation Raidisseurs pour panneaux de structure d'aeronef
US20020178583A1 (en) * 2001-03-14 2002-12-05 Holman Wrenn P. Modular monolithic bulkhead panel
US6531004B1 (en) * 1998-08-21 2003-03-11 Eads Deutschland Gmbh Weldable anti-corrosive aluminium-magnesium alloy containing a high amount of magnesium, especially for use in aviation
US6569542B2 (en) * 1999-12-28 2003-05-27 Pechiney Rhenalu Aircraft structure element made of an Al-Cu-Mg alloy

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19639667C1 (de) * 1996-09-27 1998-03-12 Daimler Benz Aerospace Airbus Verfahren zum Schweißen von Profilen auf großformatigen Aluminium-Strukturbauteilen mittels Laserstrahlen
DE19941924B4 (de) * 1999-09-03 2004-07-01 Airbus Deutschland Gmbh Großflächiges Flugzeugstrukturbauteil und Verfahren zur Herstellung des Flugzeugstrukturbauteils

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5749980A (en) * 1993-08-28 1998-05-12 Kabushiki Kaisha Kobe Seiko Sho Method for improving aluminum alloy cast structural member
US5560789A (en) * 1994-03-02 1996-10-01 Pechiney Recherche 7000 Alloy having high mechanical strength and a process for obtaining it
US6531004B1 (en) * 1998-08-21 2003-03-11 Eads Deutschland Gmbh Weldable anti-corrosive aluminium-magnesium alloy containing a high amount of magnesium, especially for use in aviation
DE19844035C1 (de) * 1998-09-25 1999-11-25 Daimler Chrysler Aerospace Schalenbauteil für ein Flugzeug und Verfahren zur Herstellung
US6569542B2 (en) * 1999-12-28 2003-05-27 Pechiney Rhenalu Aircraft structure element made of an Al-Cu-Mg alloy
US20020178583A1 (en) * 2001-03-14 2002-12-05 Holman Wrenn P. Modular monolithic bulkhead panel
WO2002083389A2 (fr) * 2001-04-10 2002-10-24 Icom Engineering Corporation Raidisseurs pour panneaux de structure d'aeronef

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007009796A1 (fr) * 2005-07-21 2007-01-25 Airbus Deutschland Gmbh Procede pour assembler au moins deux structures planes, notamment au moins deux toles de metal pour une structure de construction legere, assemblage et construction legere
US8110054B2 (en) 2005-07-21 2012-02-07 Airbus Deutschland Gmbh Method for connection at least two pieces of sheet material, particularly at least two metal sheets for a lightweight structure as well a joining and lightweight structure

Also Published As

Publication number Publication date
WO2005007507B1 (fr) 2005-05-26
DE10332003B3 (de) 2004-12-16

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