WO2005007507A1 - Welded aluminium structural component provided with cast-aluminium elements - Google Patents

Welded aluminium structural component provided with cast-aluminium elements 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
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WO
WIPO (PCT)
Prior art keywords
structural component
welded
cast
connecting element
welding
Prior art date
Application number
PCT/DE2004/001387
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German (de)
French (fr)
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WO2005007507B1 (en
Inventor
Frank Palm
Original Assignee
Eads Deutschland Gmbh
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Publication of WO2005007507A1 publication Critical patent/WO2005007507A1/en
Publication of WO2005007507B1 publication Critical patent/WO2005007507B1/en

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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)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Laser Beam Processing (AREA)
  • Arc Welding In General (AREA)

Abstract

The invention relates to a structural component (1) made of welded aluminium and provided with cast-aluminium elements, mainly for aircrafts. The inventive structural component comprises a coating area (2) and at least one reinforcing element (3b) to which at least one connection element is fixed in order to make it possible to fix by welding the reinforcing element (3b) to the coating area (2). Said invention is characterised in that the connection element (4) is made of a cast-aluminium material.

Description

Geschweißtes Aluminium-Strukturbauteil mit Aluminium-Guss-Werkstoffelementen Welded aluminum structural component with cast aluminum material elements
Die vorliegende Erfindung betrifft ein geschweißtes Aluminium-Strukturbauteil mit Aluminium-Guss-Werkstoffelementen gemäß dem Oberbegriff des Anspruchs 1, sowie einen Flugzeugdruckrumpf gemäß Anspruch 9, der zumindest teilweise aus einem derartigen Aluminium-Strukturbauteil besteht.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.
Im Flugzeugbau sind Aluminium-Strukturbauteile für Druckrumpfschalen, die im Wesentlichen aus Hautfeld-Stringer-(Clip)-Verbindungen bestehen, bisher mit dem Fertigungsverfahren Nieten oder Kleben hergestellt worden. Dabei werden sowohl Stringer- als auch Winkelelemente, sogenannte Clips, die zur Befestigung von in Druckrumpfumfangsrichtung verlaufenden Spante dienen, an dem Hautfeld befes- tigt.In aircraft construction, aluminum structural components for pressure fuselage shells, which essentially consist of skin field stringer (clip) connections, have so far been produced using the manufacturing process of riveting or gluing. Both stringer and angle elements, so-called clips, which are used to fasten frames running in the circumferential direction of the pressure fuselage, are attached to the skin field.
In jüngster Zeit hat sich für die Fertigung von großflächigen Aluminium- Strukturbauteilen für Flugzeug-Druckrumpfschalen das Laserschweißen als Herstellungsverfahren durchgesetzt. Derartige geschweißte Hautfeld-Stringer-(Clip)- Verbindungen zeichnen sich vorteilhafterweise gegenüber den bisherigen mittels Nieten oder Kleben hergestellten Verbindungen durch ein geringeres Gewicht und deutlich reduzierte Fertigungszeiten aus.Laser welding has recently become established as a manufacturing method for the production of large-area aluminum structural components for aircraft pressure fuselage shells. Such welded skin field stringer (clip) connections are advantageously distinguished from the previous connections made by riveting or gluing by a lower weight and significantly reduced manufacturing times.
In DE 196 39 667 ist beispielsweise ein Verfahren zum Laserstrahlschweißen von Profilen auf großformatigen Aluminium-Strukturbauteilen beschrieben, bei dem zwei Laserstrahlen verwendet werden, die von zwei Seiten gleichzeitig mittels Nahtsuchsystem an die Schweißnaht geführt werden. Ein mittels Laserstrahlschweißen hergestelltes Flugzeug-Schalenteil ist z.B. aus DE 19844 035 bekannt. Gegenwärtig werden bei der Herstellung von Aluminium-Strukturbauteilen in Flugzeuglängsrichtung verlaufende Verstärkungselemente (= Stringer) unter Verwendung von Schweißzusatzwerkstoffen am Hautfeld angeschweißt. Der draht- oder folienförmige Schweißzusatzwerkstoff muss dabei während des Laserschweißens in geeigneter Weise zugeführt werden und dient zur Unterdrückung der Heißrissbildung während des Verschweißens.DE 196 39 667, for example, 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. At present, reinforcement elements (= stringers) running in the longitudinal direction of the aircraft are welded to the skin field using welding filler materials in the manufacture of aluminum structural components. 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.
In Zukunft sollen auch die quer dazu verlaufenden Versteifungselemente (= Spante) bzw. die zum Befestigen der Spante notwendigen blechförmigen Verbindungs- beschläge, die sogenannten Clips bzw. Schubkämme, direkt an die Druckrumpfhaut geschweißt werden. Dies ist jedoch bisher sehr problematisch, da sämtliche zur Zeit verwendeten Blechwerkstoffe nur mit Schweißzusatzwerkstoffen rissarm geschweißt werden können. Auf Grund der schwierigen geometrischen Verhältnisse ist das Zuführen des Schweißzusatzwerkstoffes allerdings problematisch und fertigungstechnisch sehr aufwendig. Damit ist in der Regel die Herstellung nicht fertigungssicher durchführbar.In the future, the transverse stiffening elements (= frame) or the sheet-metal connection fittings required to fasten the frame, the so-called clips or push combs, will also be welded directly to the pressure hull skin. However, this has been very problematic so far, since all sheet materials currently used can only be welded with low-crack filler materials. Due to the difficult geometric conditions, however, the supply of the welding filler material is problematic and very expensive to manufacture. As a rule, therefore, the manufacture cannot be carried out reliably.
Somit liegt der vorliegenden Erfindung die Aufgabe zu Grunde, ein geschweißtes Aluminium-Strukturbauteil zu schaffen, das fertigungstechnisch vereinfacht und mit hoher Fertigungssicherheit auch bei komplizierten geometrischen Verhältnissen herstellbar ist.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.
Diese Aufgabe wird durch ein geschweißtes Aluminium-Strukturbauteil mit Alumi- nium-Guss-Werkstoffelementen gelöst, das ein Hautfeld sowie mindestens ein Verstärkungselement aufweist, an dem mindestens ein Verbindungselement angebracht ist, über welches das Verstärkungselement mittels Schweißen an dem Hautfeld befestigt ist, und dadurch gekennzeichnet ist, dass das Verbindungselement aus einem Aluminium-Guss-Werkstoff besteht. Erfindungsgemäß liefert der Aluminium-Guss-Werkstoff selbst den zur Unterdrückung einer Heißrissbildung während des Schweißens erforderlichen metallischen Schweißzusatzwerkstoff, so dass auf die Verwendung und Zuführung von zusätzlichen Schweißzusatzwerkstoffen gänzlich verzichtet werden kann. Damit verein- facht sich das Fertigungsverfahren drastisch, so dass es zu signifikanten Kosteneinsparungen bei der Herstellung kommt. Zudem lässt sich die Fertigungssicherheit beim Schweißen erheblich steigern, da auf Grund der lokalen geometrischen Restriktion die Nachführung und exakte Zuordnung eines Schweißzusatzwerkstoffes entfällt. Ein weiterer Vorteil ist, dass die schweißgestützte, integrale Bauweise weiter ausgedehnt werden kann, und somit prinzipiell auf alle Bereiche des Flugzeugrumpfes erstreckt werden kann. Dies führt zu einer weiteren Senkung des Strukturgewichtes sowie reduzierten Betriebskosten, da genietete Strukturen gänzlich ersetzt werden können.This object is achieved by 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. According to the invention, 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. This simplifies the manufacturing process drastically, resulting in significant manufacturing cost savings. In addition, 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.
Bevorzugt besteht das Verbindungselement aus einer AlMg-Guss-Verbindung mit 3 - 10 Gew.-% Mg, einer AISi-Guss-Verbindung mit 5 - 20 Gew.-% Si, einer AICu- Guss-Verbindung mit 3 - 15 Gew.-% Cu oder einer AlZi-Guss Verbindung mit 4 - 20 Gew.-% Zi. Diese Gusswerkstoffe stellen sicher, dass der zum gussarmen Schweißen erforderliche Schweißzusatzstoff durch den Werkstoff des Verbin- dungselements selbst gespendet wird, so dass ein separates Zuführen eines Schweißzusatzwerkstoffes nicht nötig ist.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. These cast materials ensure that the welding filler required for low-casting welding is donated by the material of the connecting element itself, so that a separate feed of a welding filler material is not necessary is.
Bevorzugt wird ein Verbindungselement aus einem derartigen Aluminium-Guss- Werkstoff verwendet, das mittels Druckguss-, Feinguss- oder Sandguss-Verfahren bzw. Thixo- oder Rheo-Casting hergestellt ist. Diese Herstellungsverfahren gewährleisten, dass das Gussgefüge einen geringen Restgasgehalt aufweist und somit eine gute Schweißeignung hat. Gemäß einer bevorzugten Ausführungsform bestehen Hautfeld und Verstärkungselement jeweils aus luftfahrtzertifizierten Aluminium-Legierungen, wie beispielsweise Legierungen vom Typ 2xxx, 4xxx, 5xxx, 6xxx, 7xxx und/oder 8xxx (gemäß amerikanischer Legierungsbezeichnung). Dabei sind beliebige Werkstoffkombina- tionen möglich, so dass die erfindungsgemäße Struktur flexibel für Luftfahrtanwendungen geeignet ist.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. According to a preferred embodiment, 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.
Gemäß einer besonders bevorzugten Ausführungsform ist das Verbindungselement, welches aus dem Aluminium-Guss-Werkstoff besteht, ein Clip oder Schub- kämm, und das Verstärkungselement ist ein Spant, an dem der Clip bzw. Schubkamm mittels Nieten angebracht ist. Selbstverständlich können auch andere Verbindungsverfahren zum Befestigen des Verbindungselementes an dem Verstärkungselement verwendet werden, wie beispielsweise Kleben, Schweißen etc.According to a particularly preferred embodiment, the connecting element, which consists of the cast aluminum material, is a clip or push comb, and the reinforcing element is a frame, to which the clip or push comb is attached by means of rivets. Of course, other connection methods can also be used for fastening the connection element to the reinforcing element, such as, for example, gluing, welding, etc.
Das erfindungsgemäße, geschweißte Aluminium-Strukturbauteil findet insbesondere in Flugzeugen Anwendung, wo es zumindest teilweise Unter-, Ober- und/oder Seitenschalen des Druckrumpfes bildet.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.
Anhand der beigefügten Abbildung wird die Erfindung im Folgenden in näheren Einzelheiten beschrieben.The invention is described in more detail below with reference to the attached figure.
Es zeigt:It shows:
Fig. 1 ein schematisch dargestelltes Aluminium-Strukturbauteil in Form einer Hautfeld-Stringer-Clip-Verbindung.Fig. 1 shows a schematically illustrated aluminum structural component in the form of a skin field stringer clip connection.
Fig. 1 zeigt ein geschweißtes Aluminium-Strukturbauteil 1 in Form einer Hautfeld Stringer-Clip-Verbindung. Das Strukturbauteil 1 weist ein Hautfeld 2 auf, an dem eine Vielzahl von Verstärkungselementen 3a, 3b angebracht ist. Die Verstär- kungselemente 3a sind sogenannte Stringer, die in Längsrichtung eines Flugzeugdruckrumpfes verlaufen. In Fig. 1 sind drei Stringer 3a an dem Hautfeld 2 mittels Laserschweißen befestigt. Bekanntlich weist ein derartiges Aluminium- Strukturbauteil 1 zur Verwendung in Flugzeugdruckrümpfen neben den Stringern auch sogenannte Spante auf, die in Druckrumpfumfangsrichtung verlaufende Verstärkungselemente darstellen. In Fig. 1 ist ein einzelner derartiger Spant 3b dargestellt, der mittels Verbindungselement 4 an dem Hautfeld 2 befestigt ist. Das in Fig. 1 dargestellte Verbindungselement 4 ist als sogenannter Schubkamm ausgebildet, der über mehrere Stringer 3a hinweg läuft. Selbstverständlich können auch nichtübergreifende Einzelelemente in Form von sogenannten Clips verwendet werden. Typischerweise werden die Verbindungselemente 4 (Clips bzw. Schubkamm) mit dem Spant durch Nieten verbunden, was auch in Fig. 1 dargestellt ist. Anschließend wird das Verbindungselement 4 an seiner dem Spant 3b gegenüberliegenden Seite mit dem Hautfeld 2 verschweißt, um somit ein stabiles bzw. verstärktes Aluminium-Strukturbauteil 1 zu schaffen.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. In Fig. 1, three stringers 3a are attached to the skin field 2 by means of laser welding. As is known, 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 element 4 shown in FIG. 1 is designed as a so-called push comb that runs across several stringers 3a. Of course, non-comprehensive individual elements in the form of so-called clips can also be used. The connecting elements 4 (clips or push comb) 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.
Um die Heißrissbildung während des Schweißens zu unterdrücken, wird bisher separat ein Schweißzusatzwerkstoff zugeführt, meist in Form eines Drahtes oder einer Folie. Dabei ergibt sich auf Grund der komplexen Geometrie, insbesondere in den Eckbereichen A, das Problem, dass der Laserschweißkopf nur unter sehr großen Schwierigkeiten prozesssicher arbeiten kann. Zusätzlich wird die Positionierung des Schweißzusatzwerkstoffes durch die bereits zuvor angeschweißten Stringer 3a erheblich behindert. Damit besteht eine sehr große Gefahr, dass besonders in den schon ohnehin gefährdeten Eckbereichen (lokale Spannungsüber- höhung im Betriebsfall), die Verbindung nicht heißrissfrei geschweißt werden kann.In order to suppress the formation of hot cracks during welding, 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).
Das Problem wird erfindungsgemäß dadurch gelöst, dass ein Verbindungselement 4 verwendet wird, das aus einem Aluminium-Guss-Werkstoff besteht. Der Alumi- nium-Guss-Werkstoff kann ein etablierter oder neuer bzw. weiterentwickelter Werkstoff sein. Auf Grund der Materialauswahl des Verbindungselementes 4 wird gewährleistet, dass der für eine zuverlässige und heißrissarme Schweißung erforderliche Schweißzusatzwerkstoff durch das Verbindungselement 4 selbst gespen- det wird. Es verringert sich die Gefahr der Heißrissbildung und gewährleistet damit mehr Fertigungssicherheit, da immer genügend Schweißzusatzwerkstoff vor Ort ist. Ferner ist die Schweißprozessführung vereinfacht, da kein Schweißzusatzwerkstoff mehr nachgeführt oder vorpositioniert werden muss. Gleichzeitig werden die Fertigungskosten für das Verbindungselement durch endkonturnahe Herstel- lung reduziert. Zudem besteht bei passender Werkstoffauswahl die Möglichkeit der Wärmenachbehandlung des Aluminium-Strukturbauteiles 1 (nicht formgebend oder auch formgebend bis hin zur Kriechumformung (s. auch AlMgSc- Werkstofftechnik)), welche die Eigenschaften in der Schweißnaht und ihren Einflussbereich verbessern kann, beispielsweise hinsichtlich Festigkeit, Eigenspan- nungen etc.The problem is solved according to the invention in that a connecting element 4 is used, 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. Furthermore, 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. In addition, with the right choice of material, there is the possibility of post-heat treatment of the structural aluminum component 1 (not shaping or also shaping up to creep forming (see also AlMgSc material technology)), which can improve the properties in the weld seam and its area of influence, for example with regard to strength, Residual stresses etc.
Vorzugsweise besteht das Verbindungselement 4 aus einem AlMg-Guss- Werkstoff mit ca. 3 - 10 Gew.-% Mg, dem zusätzlich 0 - 2 Gew.-% Mn, Si, Sc (ersatzweise Zr, Ti, Y, Tb, Hf, Nb, Ta, V und/oder den Lanthaniden) Cu, Ag und/oder Fe beigemengt sein kann. Die Lanthaniden sind dabei bevorzugt Cer (Ce), Neodym (Nd), Europium (Eu), Gadolinium (Gd), Dysprosium (Dy), Holmium (Ho) und/oder Erbium (Er).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).
Alternativ kann das Verbindungselement 4 aus einem AISi-Guss-Werkstoff mit 5 - 20 Gew.-% Si bestehen, dem 0 - 5 Gew.-% Mg, Cu, Fe und/oder Mn beigemengt sein können. Gemäß einer weiteren Alternative wird ein AICu-Guss-Werkstoff mit 3 - 15 Gew.- % Cu verwendet. Diesem können 0 - 5 Gew.-% Mg, Ag, Cu, Fe, Ti oder Mn beigemengt sein.Alternatively, 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. According to a further alternative, 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.
Gemäß einer weiteren Alternative besteht das Verbindungselement 4 aus einer AlZi-Verbindung mit 4 - 20 Gew.-% Zi, dem Mg, Ag, Cu oder andere bzw. weitere bei AlZn-Legierungen gebräuchliche Elemente beigemengt sein kann.According to a further alternative, 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.
Zur weiteren Eigenschaftsverbesserung können natürlich diese Gusswerkstoffe noch klassische, etablierte Legierungszugaben enthalten, welche eine Verfeinerung des Gefüges bewirken (z.B. Sr bei AISi-Legierungen, Be bei AlMg- Legierungen oder TiB2 zur allgemeinen Kornfeinung).To further improve the properties, 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).
Das Hautfeld 2 und das Verstärkungselement 3 bestehen aus bekannten luftfahrt- zertifizierten Aluminium-Legierungen. Die luftfahrtzertifizierten Legierungen sind beispielsweise Legierungen vom Typ 2xxx, 4xxx, 5xxx, 6xxx, 7xxx und/oder 8xxx. Nach amerikanischer Legierungsbezeichnung sind dies AICu-Legierungen (2xxx), AlMg-Legierungen (6xxx), AlMgSi-Legierungen (7xxx), AlZn-Legierungen (8xxx) bzw. andere Werkstoffsysteme.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.
BEISPIELE:EXAMPLES:
Im Folgenden werden einige erfindungsgemäße Beispiele für die Werkstoffpaarung Hautfeld/Verbindungselement aufgeführt und mit dem Stand der Technik verglichen: 1. Beispiel:In the following, some examples according to the invention for the material pairing skin field / connecting element are listed and compared with the prior art: 1st example:
Stand der Technik: Hautfeldwerkstoff: AA 6013 T4 oder T6 (AA 6013 = AlMgl Cu0.8Si0.75Mn0.5) Clip: AA 6013 T4 oder T6State of the art: Skin field material: AA 6013 T4 or T6 (AA 6013 = AlMgl Cu0.8Si0.75Mn0.5) Clip: AA 6013 T4 or T6
Der Clip wurde mittels Laserstrahlen unter Verwendung des Schweißzusatzwerkstoffes AA 4047 (AISM2) heißrissfrei an das Hautfeld geschweißt. Der Schweiß- nahtwerkstoff enthält somit eine Mischung der drei Komponenten mit folgender Zusammensetzung: * AI Si2-4 MgO.3-0.6 CuO.2-0.4.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.
Erfindungsgemäß e Werkstoffpaarung:Material pairing according to the invention:
Hautfeldwerkstoff: AA 6013 T4 oder T6 (AA 6013 = AlMgl Cu0.8Si0.75Mn0.5) Clip: A357 T4 oder T6 (A357 = AISi7Mg0.6)Skin field material: AA 6013 T4 or T6 (AA 6013 = AlMgl Cu0.8Si0.75Mn0.5) Clip: A357 T4 or T6 (A357 = AISi7Mg0.6)
Das Verbindungselement wurde mittels Laserstrahlschweißen ohne Verwendung eines zusätzlichen Schweißzusatzwerkstoffes an das Hautfeld angeschweißt. Der Werkstoff der Schweißnaht enthält dann eine Mischung aus den zwei Komponen- ten und weist folgende Zusammensetzung auf: « AISi3-4 Mg0.3-0.6Cu0.1-0.2....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 ....
Ohne Einschränkung ist es möglich, eine hei risssichere Verbindungen darzustellen, wobei die Restriktion des bisher erforderlichen Zuführens eines Schweißzu- satzwerkstoffes umgangen wird. Hierzu muss lediglich gewährleistet sein, dass der AISi7Mg0.6 Guss-Clip mit einem Gussverfahren hergestellt wird, welches eine gute Schweißeignung (geringer Restgasgehalt des Gussgefüges) ermöglicht. Dies können das Feingussverfahren HERO bzw. SOPHIA, welche für die Luftfahrt qualifiziert sind, aber auch andere neue Druckgussverfahren, wie beispielsweise Thi- xo- oder Rheo-Casting sein. 2. Beispiel:Without restrictions, it is possible to produce a hot-crack-proof connection, whereby the restriction of the previously required supply of a welding filler material is avoided. All that needs to be ensured is that 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). These can be the investment casting process HERO or SOPHIA, which are qualified for aviation, but also other new die casting processes, such as thixo or rheo casting. 2nd example:
Stand der Technik:State of the art:
Hautfeldwerkstoff: AA 2024 T3 (AA 2024 = AI Cu4.5 Mg2 Mn)Skin field material: AA 2024 T3 (AA 2024 = AI Cu4.5 Mg2 Mn)
Clip: AA 2024 T3Clip: AA 2024 T3
Laserstrahl geschweißt (heißrissfrei) mit Schweißzusatzwerkstoff: a) AA 4047 (AISi12) b) AA 2319 (AICu6Mn), oder besser c) GUS 1217 (AICulOSc)Laser beam welded (hot crack free) with filler metal: a) AA 4047 (AISi12) b) AA 2319 (AICu6Mn), or better c) GUS 1217 (AICulOSc)
Der Schweißnahtwerkstoff besteht aus einer Mischung der drei Komponenten: 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 MnThe 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
Erfindungsgemäße Werkstoffpaarung: Hautfeldwerkstoff: AA 2024 T3 (AA 2024 = AICu4.5Mg2Mn) Clip: a) A360 T6 (A360 = AISM 0Mg0.3) b) A201 T6 (A201 = AICu4.5TiAg) c) AICu6 bzw. AICul OScMaterial pairing according to the invention: skin field material: AA 2024 T3 (AA 2024 = AICu4.5Mg2Mn) clip: a) A360 T6 (A360 = AISM 0Mg0.3) b) A201 T6 (A201 = AICu4.5TiAg) c) AICu6 or AICul OSc
Das Verbindungselement wurde wiederum ohne Verwendung eines zusätzlichen Schweißzusatzwerkstoffes an das Hautfeld angeschweißt. Der Werkstoff der Schweißnaht ist eine Mischung aus den vorgenannten Komponenten: a) AISi3-4 Cu0.8-1.4 Mg0.4-0.6 b) AICu3-4Mg0.4-0.6 c) AICu4-7Mg0.3-0.5The 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
Als Herstellungsverfahren dienen die gleichen wie unter Beispiel 2 aufgeführt. 3. Beispiel:The same production processes as listed under Example 2 are used. 3rd example:
Stand der TechnikState of the art
Hautfeldwerkstoff: AIMg4.0MnScZrSkin field material: AIMg4.0MnScZr
Clip: AIMg4.0MnScZrClip: AIMg4.0MnScZr
Laserstrahl-geschweißt (heißrissfrei) mit Schweißzusatzwerkstoff:Laser beam welded (hot crack free) with filler metal:
AA 5025 (AA 5025 = AIMg5Sc0.3)AA 5025 (AA 5025 = AIMg5Sc0.3)
Der Schweißnahtwerkstoff besteht aus einer Mischung der drei Komponenten:The weld material consists of a mixture of the three components:
« AI Mg4-5Mn0.2-0.4Sc0.2-0.3«AI Mg4-5Mn0.2-0.4Sc0.2-0.3
Erfindungsgemäße Werkstoffpaarung: Hautfeldwerkstoff: AIMg4.0MnScZr Clip: a) AIMg3.0-5.0MnScZr b) AIMg3.0-5.0SiMn (Sc-frei)Material pairing according to the invention: skin field material: AIMg4.0MnScZr clip: a) AIMg3.0-5.0MnScZr b) AIMg3.0-5.0SiMn (Sc-free)
Der Clip wurde ohne Verwendung eines Schweißzusatzwerkstoffes am Hautfeld angeschweißt. Der Schweißnahtwerkstoff enthält eine Mischung aus den zwei Komponenten mit folgender Zusammensetzung: AIMg3.5-5.0MnScZr.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.
Wie zuvor muss hier gewährleistet sein, dass das Guss-Verbindungselement mit einem Gussverfahren hergestellt wurde, welches eine gute Schweißeignung ermöglicht. Bei Sc-haltigen AlMg-Gusswerkstoffen bietet sich neben den Fein- und Sandguss-Verfahren besonders auch das Rheo-Casting-Verfahren an, da so über die besondere Wärmeführung ein mit Sc übersättigter Mischkristall nach dem Gießen erzielt werden kann. As before, it must be ensured here that the cast connecting element was produced using a casting process which enables it to be welded well. In the case of Sc-containing AlMg cast materials, 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.

Claims

Patentansprüche claims
1 . Geschweißtes Aluminium-Strukturbauteil (1 ) mit Aluminium-Guss- Werkstoffelementen, insbesondere für Flugzeuge, umfassend ein Hautfeld (2) sowie mindestens ein Verstärkungselement (3), an dem mindestens ein Verbindungselement (4) angebracht ist, über welches das Verstärkungselement (3) mittels Schweißen an dem Hautfeld (2) befestigt ist, dadurch gekennzeichnet, dass das Verbindungselement (4) aus einem Aluminium- Guss-Werkstoff besteht.1 . Welded aluminum structural component (1) with cast aluminum material elements, in particular for aircraft, comprising a skin field (2) and at least one reinforcing element (3), to which at least one connecting element (4) is attached, via which the reinforcing element (3) is attached to the skin field (2) by means of welding, characterized in that the connecting element (4) consists of a cast aluminum material.
2. Geschweißtes Aluminium-Strukturbauteil (1 ) nach Anspruch 1 , dadurch gekennzeichnet, dass der Aluminium-Guss-Werkstoff aus einer AlMg- Verbindung mit 3-10 Gew.-% Mg, einer AlSi-Verbindung mit 5 - 20 Gew.-% Si, einer AICu-Verbindung mit 3 - 15 Gew.-% Cu oder einer AlZi- Verbindung mit 4 - 20 Gew.-% Zi besteht.2. Welded aluminum structural component (1) according to claim 1, characterized in that the cast aluminum material from an AlMg compound with 3-10 wt .-% Mg, an AlSi compound with 5 - 20 wt .-% Si, an AICu compound with 3 - 15 wt .-% Cu or an AlZi compound with 4 - 20 wt .-% Zi.
3. Geschweißtes Aluminium-Strukturbauteil (1 ) nach Anspruch 2, dadurch gekennzeichnet, dass das Verbindungselement (4) aus Aluminium-Guss- Werkstoff mittels Druck-, Fein-, Sand-, Thixo- oder Rheo-Gussverfahren hergestellt ist.3. Welded aluminum structural component (1) according to claim 2, characterized in that the connecting element (4) is made of cast aluminum material by means of pressure, fine, sand, thixo or rheo casting processes.
4. Geschweißtes Aluminium-Strukturbauteil (1 ) nach Anspruch 1 , dadurch gekennzeichnet, dass das Hautfeld (2) und das Verstärkungselement (3) aus luftfahrtzertifizierten Aluminium-Legierungen bestehen.4. Welded aluminum structural component (1) according to claim 1, characterized in that the skin field (2) and the reinforcing element (3) consist of aviation-certified aluminum alloys.
5. Geschweißtes Aluminium-Strukturbauteil (1 ) nach Anspruch 4, dadurch gekennzeichnet, dass die luftfahrtzertifizierten Legierungen vom Typ 2xxx, 4xxx, 5xxx, 6xxx, 7xxx und/oder 8xxx sind. 5. Welded aluminum structural component (1) according to claim 4, characterized in that the aviation-certified alloys are of the type 2xxx, 4xxx, 5xxx, 6xxx, 7xxx and / or 8xxx.
6. Geschweißtes Aluminium-Strukturbauteil (1 ) nach einem der vorangegangenen Ansprüche, dadurch gekennzeichnet, dass das Verbindungselement (4) ein Clip oder Schubkamm ist.6. Welded aluminum structural component (1) according to one of the preceding claims, characterized in that the connecting element (4) is a clip or push comb.
7. Geschweißtes Aluminium-Strukturbauteil (1 ) nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass das Verstärkungselement (3) ein Spant (3b) ist.7. Welded aluminum structural component (1) according to one of claims 1 to 6, characterized in that the reinforcing element (3) is a frame (3b).
8. Geschweißtes Aluminium-Strukturbauteil (1 ) nach Anspruch 6 oder 7, dadurch gekennzeichnet, dass Clip bzw. Schubkamm mittels Nieten an dem Spant (3b) angebracht ist.8. Welded aluminum structural component (1) according to claim 6 or 7, characterized in that clip or push comb is attached to the frame (3b) by means of rivets.
9. Flugzeugdruckrumpf, dadurch gekennzeichnet, dass dessen Unter-, Ober- und/oder Seitenschale zumindest teilweise aus einem Al- Strukturbauteil (1) gemäß einem der Ansprüche 1 - 8 besteht. 9. Aircraft pressure fuselage, characterized in that its lower, upper and / or side shell consists at least partially of an Al structural component (1) according to one of claims 1-8.
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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

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