EP0726106A1 - Procédé pour transformer un élément en forme de plaque - Google Patents

Procédé pour transformer un élément en forme de plaque Download PDF

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Publication number
EP0726106A1
EP0726106A1 EP96100262A EP96100262A EP0726106A1 EP 0726106 A1 EP0726106 A1 EP 0726106A1 EP 96100262 A EP96100262 A EP 96100262A EP 96100262 A EP96100262 A EP 96100262A EP 0726106 A1 EP0726106 A1 EP 0726106A1
Authority
EP
European Patent Office
Prior art keywords
component
hot aging
aging
hot
shaped
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.)
Granted
Application number
EP96100262A
Other languages
German (de)
English (en)
Other versions
EP0726106B1 (fr
Inventor
Heinz Bornschlegl
Winfried Dr. Köhler
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
Daimler Benz Aerospace AG
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 Daimler Benz Aerospace AG filed Critical Daimler Benz Aerospace AG
Publication of EP0726106A1 publication Critical patent/EP0726106A1/fr
Application granted granted Critical
Publication of EP0726106B1 publication Critical patent/EP0726106B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24C—ABRASIVE OR RELATED BLASTING WITH PARTICULATE MATERIAL
    • B24C1/00—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods
    • B24C1/10—Methods for use of abrasive blasting for producing particular effects; Use of auxiliary equipment in connection with such methods for compacting surfaces, e.g. shot-peening
    • 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
    • C22F1/057—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 copper as the next major constituent
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/47—Burnishing
    • Y10T29/479—Burnishing by shot peening or blasting

Definitions

  • the invention relates to a method for forming a plate-shaped component, according to the preamble of patent claim 1.
  • Shot-peening is known as an alternative manufacturing method for components of this type, in which a component blank in the hardened state is brought into a spatially curved shape with a relatively low outlay on manufacturing resources, largely with accurate contours, without the manufacturing-related difficulties of age creep forming mentioned.
  • the material properties of the finished component in particular the residual elasticity, fall short of the values that can be achieved per se for the selected material.
  • the object of the invention is to design the manufacturing process of the type mentioned at the outset in such a way that the mechanical material properties of the formed and hardened component are improved in a manner which is simple to manufacture.
  • the hot hardening temperature is kept up to about 12% and the hot hardening time up to about 20% below the values defined for the undeformed material in the hot aging process according to claim 2.
  • the impact-molded component according to claim 3 is particularly preferably pressurized during hot aging in a full-surface tool shell with a mold surface corresponding to the final component contour, so that the deformed component during the hardening due to the pressure and temperature generated creep process is kept dimensionally stable and after the impact body reshaping in the component possibly remaining contour inaccuracies and internal stresses leading to springbacks are automatically compensated in a simple manner.
  • the molding space of the pressing tool on the component side facing away from the molding surface is expedient by a flexible sealing wall which is pressurized from the outside during the hot aging, the pressurizing and hot aging preferably take place in an autoclave and the mold space between the flexible boundary wall and the molding surface is evacuated in accordance with claim 5 with regard to increased component compression.
  • a flat metal plate e.g. made of a weldable aluminum-copper alloy with a 6% copper content
  • a circular sector-shaped blank 2 and machined according to the required wall thickness profile of the tank bottom segment, so that step-shaped thickenings 4 of increased wall thickness remain.
  • the component blank 2 is cold-formed in the manner described in DE 38 42 064 C2, to which reference is hereby made in full, by means of shot-peening in such a way that it corresponds at least approximately to the spherically curved end contour of the tank bottom segment 6 to be produced (FIG. 2 ).
  • the component 6 thus formed is then inserted into a pressing tool 8 (FIG. 3) which contains a rigid molded shell 10, for example made of carbon fiber composite material, with a molded surface 12 which is spherically curved in accordance with the component end contour.
  • a pressing tool 8 (FIG. 3) which contains a rigid molded shell 10, for example made of carbon fiber composite material, with a molded surface 12 which is spherically curved in accordance with the component end contour.
  • the component 6 On the inside provided with the thickenings 4, the component 6 is covered with an air-permeable absorbent fabric 14 with a flexible vacuum film 16 which is connected at the edge to the mold shell 10 in a pressure-tight manner by means of a sealing compound 18, whereupon the pressing tool 8 with that in the mold space component 4 enclosed between the molding surface 12 and the vacuum film 16 is introduced into an autoclave (not shown) and aged there, the hot-curing temperature being kept about 12% and the hot-curing time about 20% below the values applicable to the undeformed material. Simultaneously with the heat curing, the molding space is evacuated and the autoclave pressure is kept at such a high level that the component material is caused to creep.
  • component 6 After the end of the heat-hardening cycle, component 6 is finished and can be welded together with other components manufactured in the same way to form a hemispherical tank bottom of a fuel tank for a spacecraft.
  • a circular sector-shaped, flat component blank 2 was produced from the material mentioned above with a radial length of 2500 mm and a width of 2100 mm and was machined to a wall thickness of 1.3 mm with local thickenings up to 4.5 mm brought.
  • the component was brought into a biaxially curved shape (radius of curvature R 1 about 3000 mm and radius of curvature R 2 about 2700 mm) by the shot peening.
  • the hot aging in the press tool 8 was carried out at an autoclave pressure of 5 bar with a heating rate of 30 ° C./h and a holding time of 14 hours at 160 ° C. All the contour inaccuracies still present were eliminated.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Physics & Mathematics (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Shaping Metal By Deep-Drawing, Or The Like (AREA)
  • Mounting, Exchange, And Manufacturing Of Dies (AREA)
  • Mechanical Treatment Of Semiconductor (AREA)
  • Golf Clubs (AREA)
  • Polishing Bodies And Polishing Tools (AREA)
  • Laminated Bodies (AREA)
  • Transition And Organic Metals Composition Catalysts For Addition Polymerization (AREA)
EP96100262A 1995-02-03 1996-01-10 Procédé pour transformer un élément en forme de plaque Expired - Lifetime EP0726106B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19503620A DE19503620C2 (de) 1995-02-03 1995-02-03 Verfahren zum Umformen eines plattenförmigen Bauteils
DE19503620 1995-02-03

Publications (2)

Publication Number Publication Date
EP0726106A1 true EP0726106A1 (fr) 1996-08-14
EP0726106B1 EP0726106B1 (fr) 1999-06-02

Family

ID=7753152

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96100262A Expired - Lifetime EP0726106B1 (fr) 1995-02-03 1996-01-10 Procédé pour transformer un élément en forme de plaque

Country Status (8)

Country Link
US (1) US6264771B1 (fr)
EP (1) EP0726106B1 (fr)
AT (1) ATE180699T1 (fr)
CA (1) CA2168592A1 (fr)
DE (2) DE19503620C2 (fr)
DK (1) DK0726106T3 (fr)
ES (1) ES2135117T3 (fr)
GR (1) GR3031046T3 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010118454A1 (fr) 2009-04-17 2010-10-21 Voestalpine Automotive Gmbh Procédé de fabrication d'une pièce moulée
DE102008003882B4 (de) * 2008-01-10 2011-12-15 Otto Fuchs Kg Verfahren zum Herstellen eines Gegenstandes aus Metall, insbesondere aus einer hochfesten Aluminiumlegierung sowie Verfahren zum Richten eines solchen Gegenstandes
CN111195678A (zh) * 2020-01-11 2020-05-26 中南大学 一种大型薄壁构件节约型蠕变时效成形方法

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0117066D0 (en) * 2001-07-12 2001-09-05 Bae Systems Plc Creep forming a metallic compound
GB2381764A (en) * 2001-11-08 2003-05-14 Farleydene Ltd Autoclave suitable for heat treating parts
GB0229434D0 (en) * 2002-12-18 2003-01-22 Bae Systems Plc Aircraft component manufacturing tool and method
GB0229435D0 (en) * 2002-12-18 2003-01-22 Bae Systems Plc Aircraft component manufacturing tool and method
GB0719873D0 (en) * 2007-10-12 2007-11-21 Rolls Royce Plc Shape correcting components
JP6115554B2 (ja) * 2014-12-08 2017-04-19 トヨタ自動車株式会社 ショットピーニング方法
GB2535497B (en) 2015-02-18 2021-05-05 Avic Beijing Aeronautical Mfg A die mechanism, an apparatus, and a method for shaping a component for creep-age forming
US10391536B1 (en) * 2016-03-31 2019-08-27 Shawn Hubbard Tool kit for bending a metal tray
US20200222967A1 (en) * 2019-01-11 2020-07-16 Embraer S.A. Methods for producing creep age formed aircraft components
CN110252881B (zh) * 2019-06-28 2020-09-01 中南大学 一种蠕变时效成形调控方法
CN110802220B (zh) * 2019-11-17 2023-04-07 苏州科技大学 一种大曲率壁板的蠕变时效成形方法
CN112536358B (zh) * 2020-11-13 2022-11-25 西安航空职业技术学院 一种蠕变时效成形复杂变曲率构件的工艺及模具装置

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3705511A (en) * 1969-10-17 1972-12-12 Avco Corp Low penetration ball forming process
EP0015470A1 (fr) * 1979-02-26 1980-09-17 Helmut Mischler Procédé et dispositif de fabrication de plaques en relief
EP0032780A1 (fr) * 1980-01-21 1981-07-29 The Boeing Company Grenaillage de précontrainte de contours complexes
DE3842064A1 (de) * 1988-12-14 1990-06-21 Dornier Gmbh Verfahren zum umformen von ebenen, plattenfoermigen bauteilen in eine zweiachsig gekruemmte form
US5144825A (en) * 1990-09-27 1992-09-08 The Boeing Company Elevated temperature envelope forming
EP0517982A1 (fr) * 1991-06-10 1992-12-16 Avco Corporation Procédé de développement d'un outil
EP0527570A1 (fr) * 1991-08-12 1993-02-17 Avco Corporation Procédé pour le développement d'outils à formes complexes

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU513091A1 (ru) * 1974-12-20 1976-05-05 Физико-Механический Институт Ан Усср Способ упрочнени изделий
DE4305091C1 (de) * 1993-02-19 1994-03-10 Fuchs Otto Fa Verfahren zur Herstellung eines einteiligen Leichtmetallrades aus einem Aluminium-Knetwerkstoff

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3705511A (en) * 1969-10-17 1972-12-12 Avco Corp Low penetration ball forming process
EP0015470A1 (fr) * 1979-02-26 1980-09-17 Helmut Mischler Procédé et dispositif de fabrication de plaques en relief
EP0032780A1 (fr) * 1980-01-21 1981-07-29 The Boeing Company Grenaillage de précontrainte de contours complexes
DE3842064A1 (de) * 1988-12-14 1990-06-21 Dornier Gmbh Verfahren zum umformen von ebenen, plattenfoermigen bauteilen in eine zweiachsig gekruemmte form
DE3842064C2 (fr) 1988-12-14 1990-11-08 Dornier Gmbh, 7990 Friedrichshafen, De
US5144825A (en) * 1990-09-27 1992-09-08 The Boeing Company Elevated temperature envelope forming
EP0517982A1 (fr) * 1991-06-10 1992-12-16 Avco Corporation Procédé de développement d'un outil
EP0527570A1 (fr) * 1991-08-12 1993-02-17 Avco Corporation Procédé pour le développement d'outils à formes complexes

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
MACHINERY AND PRODUCTION ENGINEERING, vol. 140, no. 3609, pages 20 - 21, XP002001441 *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008003882B4 (de) * 2008-01-10 2011-12-15 Otto Fuchs Kg Verfahren zum Herstellen eines Gegenstandes aus Metall, insbesondere aus einer hochfesten Aluminiumlegierung sowie Verfahren zum Richten eines solchen Gegenstandes
WO2010118454A1 (fr) 2009-04-17 2010-10-21 Voestalpine Automotive Gmbh Procédé de fabrication d'une pièce moulée
EP2248926A1 (fr) * 2009-04-17 2010-11-10 voestalpine Automotive GmbH Procédé de fabrication d'une pièce emboutie
CN102395699A (zh) * 2009-04-17 2012-03-28 奥地利钢铁联合汽车有限公司 用于制造成形件的方法
CN102395699B (zh) * 2009-04-17 2017-12-12 奥地利钢铁联合金属成形有限公司 用于制造成形件的方法
US10022769B2 (en) 2009-04-17 2018-07-17 Voestalpine Metal Forming Gmbh Method for producing a shaped part from an aluminum alloy sheet
CN111195678A (zh) * 2020-01-11 2020-05-26 中南大学 一种大型薄壁构件节约型蠕变时效成形方法

Also Published As

Publication number Publication date
DE59602038D1 (de) 1999-07-08
US6264771B1 (en) 2001-07-24
ES2135117T3 (es) 1999-10-16
EP0726106B1 (fr) 1999-06-02
DE19503620C2 (de) 1998-07-16
DK0726106T3 (da) 1999-12-13
GR3031046T3 (en) 1999-12-31
ATE180699T1 (de) 1999-06-15
CA2168592A1 (fr) 1996-08-04
DE19503620A1 (de) 1996-08-08

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