EP1320430B1 - Verfahren zum umformen von strukturen aus aluminium-legierungen - Google Patents

Verfahren zum umformen von strukturen aus aluminium-legierungen Download PDF

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Publication number
EP1320430B1
EP1320430B1 EP01965216A EP01965216A EP1320430B1 EP 1320430 B1 EP1320430 B1 EP 1320430B1 EP 01965216 A EP01965216 A EP 01965216A EP 01965216 A EP01965216 A EP 01965216A EP 1320430 B1 EP1320430 B1 EP 1320430B1
Authority
EP
European Patent Office
Prior art keywords
structural part
holding device
shaped
alloys
process according
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP01965216A
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German (de)
English (en)
French (fr)
Other versions
EP1320430A1 (de
Inventor
Stephane Jambu
Knut Juhl
Blanka Lenczowski
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Defence and Space GmbH
Original Assignee
EADS Deutschland GmbH
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Filing date
Publication date
Application filed by EADS Deutschland GmbH filed Critical EADS Deutschland GmbH
Publication of EP1320430A1 publication Critical patent/EP1320430A1/de
Application granted granted Critical
Publication of EP1320430B1 publication Critical patent/EP1320430B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/021—Deforming sheet bodies
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D22/00—Shaping without cutting, by stamping, spinning, or deep-drawing
    • B21D22/02—Stamping using rigid devices or tools
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21D26/00—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces
    • B21D26/02—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure
    • B21D26/053—Shaping without cutting otherwise than using rigid devices or tools or yieldable or resilient pads, i.e. applying fluid pressure or magnetic forces by applying fluid pressure characterised by the material of the blanks
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/047—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with magnesium as the next major constituent

Definitions

  • the present invention relates to a method for reshaping structures
  • Aluminum alloys in particular of natural hard AlMg, natural hard AlMgSc, and / or curable AlMgLi alloys.
  • Such structures or Moldings capture, for example, wing skin surfaces, cover and tank elements for Spacecraft, aircraft hulls with structural stiffening elements such as stringers and frame.
  • structural stiffening elements such as stringers and frame.
  • the contour-accurate and drawing fair production of such moldings Aluminum alloys are usually difficult and usually require several Forming steps of the individual components with appropriate intermediate annealing treatments.
  • the outer skin panels are converted from sheets of the alloy AA2024 in the solution-annealed condition by means of ironing.
  • stretch drawing which can be carried out both in the cold and in the warm state, the structure to be reshaped is known to be formed in one or more steps or phases (see DE 195 04 649 C1).
  • the structure to be reshaped can first be pulled in the longitudinal direction and then over a shaped part which has the desired final contour.
  • the disadvantage here is that internal stresses due to the molding process in the material caused by overlay of operating loads to the failure of the structure being able to lead. Further, forming into a structure with spherical curvature, i. with curvatures along different spatial directions, difficult and requires appropriately designed machines and dimensionally stable tools. In addition, the structure to be formed by attaching jaws mostly on the outer edges violated, so that these areas e.g. must be removed by contour milling. this leads to not only to a loss of material, but also requires another Processing step, which leads to unnecessary effort and associated loss of time.
  • the group of AlMg alloys has a planar anisotropy having a r minimum value in the L direction (rolling direction). This means that the Material flow during ironing takes place for the most part from the sheet thickness and therefore the Form to be reshaped earlier for localized thinning and premature failure inclines. Furthermore, the reduction of the sheet thickness by the extension causes the Reaching a final drawing thickness consistent only with uniform degrees of elongation can be achieved and thus for components with large processing differences only hard to realize.
  • a hardening process is also used for forming used, for example, under pressure and temperature in a Autoclave or oven is performed at the same time a curing effect occurs.
  • This so-called “age forming” process is used for hardenable Al alloys of 2xxx, 6xxx, 7xxx and 8xxx series used. It is initially under pressure or force an elastic shaping of the structure to be formed. The structure to be reshaped clings to a molding that has a smaller radius of curvature than the finished one Component has to take into account the so-called. "Springback" effect. The structure to be formed is thus first shaped beyond the desired final shape.
  • curable alloys used today e.g., AA2024, AA6013, AA6056
  • non-curable Alloys have been developed that in contrast to the established alloys metallurgical reasons can not be solution annealed, as this is a irreversible loss of strength.
  • the new materials can not be easily transformed by conventional methods. Because of that, alternatives are required for the production of double curved or spherical skin fields.
  • the component without significant springback under Heat is transformed and thereby by the elastic shaping embossed final shape almost maintained.
  • the component thus has after forming and subsequent cooling, in principle, the same curvature on as before Heat treatment.
  • This has the advantage that those used for elastic molding Moldings or holding devices with sufficient accuracy the same shape as the have theoretical shape of the component and thus a complex simulation for Predicting the "Springback" effect is not required.
  • the elastic shaping of the component before the heat treatment, wherein the component already assumes its desired final shape according to a first embodiment such be carried out that after inserting the component to be formed into a Holding device acts an external force on the component, whereupon the component under elastic shaping conforms to the contour of the holding device.
  • the external force can be transmitted via a mechanical printing or stamping device, which presses the component in the direction of holding device.
  • the elastic shaping be effected by the action of an external pressure, for example, in an evacuated Space is generated.
  • an external force acts such that the component elastically deflected in the direction of the holding device, so that between the component and Holding device creates a cavity.
  • This cavity is then filled with a Sealed sealing material and then evacuated.
  • the advantage is not only that the contour of the holding device of the desired Endform of the component to be formed corresponds, but also in the fact that the Forming by the action of external forces is purely elastic nature. This means, that the component returns to its original shape when no external forces more on the component. Thus, corrections or reloading easily possible.
  • the elastic shaping of the component by the action of the external Forces can thus be repeated at any time.
  • the component at a heating rate of 20 ° C / s to 10 ° C / h to a maximum temperature above that for creep forming and Stress relaxation of the alloy to heat required temperature and then cool the component at a rate between 200 ° C / s to 10 ° C / h.
  • the maximum temperature is between 200 ° C and 450 ° C and is typically held constant for a period of 0 to 72 hours.
  • the heating or Cooling rate and the maximum temperature to the alloy used or to the desired physical properties can be adjusted.
  • a re-forming of the component take place what with the known method is not or only partially possible.
  • Another advantage of the method according to the invention is that both simple curved as well as spherical structures are transformed in one step can.
  • the holding device has curvatures which are in extend different spatial directions and the finished final contour of the Correspond to the component to be formed.
  • 2D and complex 3D structures where stringer and frame are already attached, in a simple way and Way to be reshaped.
  • deformations are caused by Thermal stresses through a previous welding process, through the Balanced forming process according to the invention.
  • Fig. 1 shows a schematic representation for explaining the insertion of a to be formed component 1 in a holding device 2.
  • the reshaped component 1 can a two-dimensional sheet of hard-rolled, natural-hard material.
  • stiffening elements (not shown), so that the to be formed structure has a three-dimensional shape. In this case, that will Sheet so inserted into the holding device 2 that the reinforcing structures of the Keep holding device 2 away.
  • any complex, three-dimensional structure are inserted into the holding device for forming, the in particular from a naturally hard, i. non-hardenable aluminum alloys consists.
  • These non-hardenable aluminum alloys can be AlMg alloys or in particular AlMgSc alloys. But also curable AlMgLi alloys can be used.
  • the holding device 2 in which the component to be formed 1 is inserted has a shape or contour 2a, which corresponds to the desired final shape of the formed component 1
  • the final shape of the component 1 is designated by the reference numeral 1a.
  • the component 1 is first in its unshaped state in the holding device. 2 inserted. In this case, a cavity 3 is formed between component 1 and holding device 2.
  • the unshaped component 1 acts from above, i. from the holding device 2 opposite side of the component 1, a force F a.
  • This force F can, for example via a in Fig. 1 only schematically illustrated punch or pressure assembly 4 the component 1 are transmitted.
  • Other suitable means for acting on these outer Power is also possible.
  • This can e.g. the action of an external pressure P be within an evacuated room in which holding device and component are located.
  • a combination of forces F and P is possible.
  • the component 1 Due to the action of the external force F and / or P, the component 1 becomes such elastically shaped, that it bends in the direction of holding device 2. As is apparent from Fig. 2 is seen, while the radius of curvature of the elastically deformed component 1 is greater than the holding device 2, so that further a cavity 3 between the component 1 and Holding device 2 is present. However, the volume of the cavity 3 is compared to the initial state shown in Fig. 1 smaller.
  • the elastic shaping of the Component 1 by the action of external forces also leads to the bearing surface between the component 1 and holding device 2 is larger and thus the cavity 3 below Use of a sealing material 5 can be completed airtight.
  • the Sealant 5 is typically a temperature-resistant, modified Silicone material, which is applied to the edge region of the component 1.
  • the component 1 is initially in elastically shaped state, so that the shaping is reversible and the process of the new could be performed when external force no longer act on the component would. That is, when no external force is applied to the component to be formed, returns return it back to its unshaped original starting position. Thus, corrections easily possible at any time.
  • the component 1 After the component by the above steps under elastic shaping in his End mold 1a was brought, the component 1 is within the closed housing. 7 heat treated while maintaining the vacuum. By the warming becomes that Component 1 under stress relaxation during the elastic molding in the material transformed stresses introduced. After completion of the stress relaxation by Heat, the vacuum can be switched off and a cooling phase closes on. The component almost retains this through the contour of the holding device given final shape 1a, without significant re-springing occurs.
  • the heat treatment is carried out according to the schematic T (t) process shown in FIG.
  • the component 1 In the evacuated state, that is, the component 1 is completely on the contour 2a of the holding device 2, the component 1 is heated to a maximum temperature T 1 , which is above the temperature required for creep deformation and stress relaxation of the alloy, which is typically greater than or equal 200 ° C is.
  • the component is heated at a heating rate between 20 ° C / s and 10 ° C / h within a first time interval At 1 to the desired target temperature T 1 .
  • the heating rate may, in contrast to the continuous course shown in FIG. 4, also vary stepwise or in another suitable manner within the interval ⁇ t 1 .
  • the maximum temperature T 1 which is typically between 220 ° C and 450 ° C, is reached at time t 1 .
  • This temperature is then kept constant for a period ⁇ t 2 , wherein ⁇ t 2 is typically between 0 and 72 h.
  • ⁇ t 2 is typically between 0 and 72 h.
  • the vacuum can be switched off and a cooling phase at a rate of typically 200 ° C / s to 10 ° C / h follows.
  • the cooling can, as shown schematically in Fig. 4, continuously or stepwise.
  • the cooling can be done by normal air cooling or other suitable way.
  • the holding device 2 predetermined end shape 1a almost retains.
  • a significant Springback in a shape with a larger radius of curvature than the holding device occurs not a.
  • the holding device with sufficient accuracy with the Dimensions of the desired final shape are produced.
  • a complicated simulation the springback effect, as for example in conventional curable Alloys formed by the "age forming" process is the case not mandatory.
  • the inventive method also has the advantage that it such bumps almost completely compensated without complicated Aftertreatment process or straightening processes are required.

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Fluid Mechanics (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
EP01965216A 2000-09-26 2001-08-25 Verfahren zum umformen von strukturen aus aluminium-legierungen Expired - Lifetime EP1320430B1 (de)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE10047491A DE10047491B4 (de) 2000-09-26 2000-09-26 Verfahren zum Umformen von Strukturen aus Aluminium-Legierungen
DE10047491 2000-09-26
PCT/EP2001/009821 WO2002026414A1 (de) 2000-09-26 2001-08-25 Verfahren zum umformen von strukturen aus aluminium-legierungen

Publications (2)

Publication Number Publication Date
EP1320430A1 EP1320430A1 (de) 2003-06-25
EP1320430B1 true EP1320430B1 (de) 2004-10-13

Family

ID=7657566

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01965216A Expired - Lifetime EP1320430B1 (de) 2000-09-26 2001-08-25 Verfahren zum umformen von strukturen aus aluminium-legierungen

Country Status (9)

Country Link
US (1) US7217331B2 (ja)
EP (1) EP1320430B1 (ja)
JP (1) JP4776866B2 (ja)
CN (1) CN1230265C (ja)
CA (1) CA2423566C (ja)
DE (2) DE10047491B4 (ja)
ES (1) ES2228944T3 (ja)
RU (1) RU2271891C2 (ja)
WO (1) WO2002026414A1 (ja)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10324366A1 (de) * 2003-05-27 2004-12-16 Feldbinder & Beckmann Fahrzeugbau Gmbh & Co Kg Verfahren und Vorrichtung zur Herstellung eines Formteiles, sowie Formteil, insbesondere ein Behälterboden
DE102005001829B4 (de) * 2005-01-14 2009-05-07 Audi Ag Verfahren zum Umformen einer Platine
EP3587105B1 (en) 2006-10-30 2022-09-21 ArcelorMittal Coated steel strips, methods of making the same, methods of using the same, stamping blanks prepared from the same, stamped products prepared from the same, and articles of manufacture which contain such a stamped product
DE102011006032A1 (de) 2011-03-24 2012-09-27 Airbus Operations Gmbh Verfahren zur Herstellung eines Strukturbauteils sowie Strukturbauteil
US9773077B2 (en) * 2012-04-09 2017-09-26 Arcelormittal Investigacion Y Desarrollo, S.L. System and method for prediction of snap-through buckling of formed steel sheet panels
EP2727665B1 (de) * 2012-10-31 2018-06-06 Airbus Defence and Space GmbH Verfahren zur Herstellung eines Formbauteils und Verwendung des Verfahrens zur Herstellung eines Formbauteils
WO2016057688A1 (en) * 2014-10-07 2016-04-14 The Penn State Research Foundation Method for reducing springback using electrically-assisted manufacturing
CN104438481B (zh) * 2014-11-28 2016-04-06 中南大学 一种大曲率铝合金整体壁板构件的制备方法
DE102016207172B3 (de) * 2016-04-27 2017-08-24 Premium Aerotec Gmbh Vorrichtung und Anordnung zum Formen eines gekrümmt flächigen Bauteils, sowie Verfahren zur Herstellung der Vorrichtung
CN106862377B (zh) * 2017-03-14 2018-12-28 中南大学 一种铝合金板的成形方法
CN106978578B (zh) * 2017-05-18 2019-01-25 中南大学 一种铝合金板蠕变时效成形方法
DE102017114663A1 (de) 2017-06-30 2019-01-03 Airbus Operations Gmbh Verfahren zum Umformen eines Bauteils
EP3880859A1 (en) * 2018-11-12 2021-09-22 Airbus SAS Method of producing a high-energy hydroformed structure from a 7xxx-series alloy
US20200222967A1 (en) * 2019-01-11 2020-07-16 Embraer S.A. Methods for producing creep age formed aircraft components
CN112207522A (zh) * 2020-10-26 2021-01-12 许晨玲 一种大型铝合金整体壁板平度控制方法

Family Cites Families (8)

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Publication number Priority date Publication date Assignee Title
US4188811A (en) 1978-07-26 1980-02-19 Chem-Tronics, Inc. Metal forming methods
US5168169A (en) * 1991-06-10 1992-12-01 Avco Corporation Method of tool development
CA2069189C (en) * 1991-08-12 1998-04-14 Aerostructures Corporation Method of developing complex tool shapes
DE4334940C2 (de) 1992-10-15 1996-10-31 Max Co Ltd Schlagschraubvorrichtung
FR2696957B1 (fr) * 1992-10-21 1994-11-25 Snecma Procédé de formage de pièces en alliages à base de titane.
US5597529A (en) * 1994-05-25 1997-01-28 Ashurst Technology Corporation (Ireland Limited) Aluminum-scandium alloys
DE19504649C1 (de) * 1995-02-13 1996-08-22 Daimler Benz Ag Verfahren und Ziehwerkzeug zum Streckziehen von Blechen
CN1489637A (zh) * 2000-12-21 2004-04-14 �Ƹ��� 铝合金产品及人工时效方法

Also Published As

Publication number Publication date
CN1455711A (zh) 2003-11-12
CA2423566A1 (en) 2003-03-25
WO2002026414A1 (de) 2002-04-04
DE10047491B4 (de) 2007-04-12
US7217331B2 (en) 2007-05-15
RU2271891C2 (ru) 2006-03-20
JP4776866B2 (ja) 2011-09-21
JP2004509765A (ja) 2004-04-02
CA2423566C (en) 2010-01-05
DE10047491A1 (de) 2002-04-18
CN1230265C (zh) 2005-12-07
US20040050134A1 (en) 2004-03-18
ES2228944T3 (es) 2005-04-16
EP1320430A1 (de) 2003-06-25
DE50104142D1 (de) 2004-11-18

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