EP0726106B1 - 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
EP0726106B1
EP0726106B1 EP96100262A EP96100262A EP0726106B1 EP 0726106 B1 EP0726106 B1 EP 0726106B1 EP 96100262 A EP96100262 A EP 96100262A EP 96100262 A EP96100262 A EP 96100262A EP 0726106 B1 EP0726106 B1 EP 0726106B1
Authority
EP
European Patent Office
Prior art keywords
component
artificial ageing
shaped
shaping
pressing tool
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
EP96100262A
Other languages
German (de)
English (en)
Other versions
EP0726106A1 (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 claim 1.
  • a method for forming a plate-shaped Component is for example from DE-A-3842064 known.
  • Shot peening is an alternative manufacturing process for components of this type known in which a component blank in the hardened state largely accurate in contour with relatively low expenditure on production equipment without the mentioned manufacturing difficulties of age creep forming is brought into a spatially curved shape. Disadvantageous is also here, however, that the material properties of the finished Component, namely in particular the residual elasticity, behind the values that are achievable for the selected material.
  • the object of the invention is the manufacturing process of the aforementioned Kind so that the mechanical material properties of the formed and hardened component in a simple manner be improved.
  • hot aging according to claim 2, the hot curing temperature up to about 12% and the Hot curing time up to about 20% below that for the undeformed material defined values.
  • the impact body is formed Component according to claim 3 in a particularly preferred manner during hot aging in a full-surface tool tray with pressurized a mold surface corresponding to the final component contour, so that the deformed component during the by the printing and Influence of temperature during the creep process generated during hot curing is kept dimensionally stable and after the impact body deformation in the component Possibly still remaining inaccuracies and springback leading residual stresses automatically balanced in a simple manner become.
  • FIG. Is used to produce a spherically curved base segment described for the tank floors of the fuel tank of a spacecraft. 1, a flat metal plate, e.g. made of a weldable aluminum-copper alloy with a 6% Copper portion, a circular sector-shaped blank 2 produced and accordingly machining the required wall thickness profile of the tank bottom segment processed so that step-shaped thickening 4 increased wall thickness stop.
  • a flat metal plate e.g. made of a weldable aluminum-copper alloy with a 6% Copper portion
  • a circular sector-shaped blank 2 produced and accordingly machining the required wall thickness profile of the tank bottom segment processed so that step-shaped thickening 4 increased wall thickness stop.
  • the component blank 2 is made to that in DE-A-38 42 064 described way, cold-formed by shot peening such that it at least approximately with the spherically curved end contour of the one to be produced Tank bottom segment 6 matches (Fig. 2).
  • the component 6 thus formed is then placed in a press tool 8 (FIG. 3), which is a rigid molded shell 10, e.g. made of carbon fiber composite with a spherical curve corresponding to the component end contour Contains molding surface 12.
  • a press tool 8 (FIG. 3)
  • the component 6 is interposed with an air permeable Absorbent tissue 14 covered by a flexible vacuum film 16, which on the edge by a sealing compound 18 pressure-tight with the molded shell 10 is connected, whereupon the pressing tool 8 with the in the molding space Component 4 enclosed between molded surface 12 and vacuum film 16 an autoclave - not shown - introduced and aged there , the hot curing temperature by about 12% and the hot curing time about 20% below the values for the undeformed material being held.
  • the molding space becomes evacuated and the autoclave pressure kept at such a high level that the component material is made to creep.
  • component 6 After the end of the hot curing cycle, component 6 is finished and can with other components manufactured in the same way to a hemispherical Tank bottom of a fuel tank for a spacecraft welded together become.
  • 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)

Claims (5)

  1. Procédé pour transformer un élément de construction en forme de plaque à partir d'une matière métallique durcissable par traitement thermique, matière déformable élastiquement et plastiquement, procédé selon lequel l'élément est mis dans une forme courbe dans l'espace par frappe notamment par frappe à jet de billes,
    caractérisé en ce que
    l'élément est transformé par frappe avant le traitement thermique et pendant le traitement thermique il est exposé a un effet de pression externe qui dépasse la résistance au fluage de la matière.
  2. Procédé selon la revendication 1,
    caractérisé en ce que
    la température de traitement thermique et le temps du traitement thermique sont maintenus en dessous des valeurs définies pour la matière non mise en forme.
  3. Procédé selon la revendication 1 ou 2,
    caractérisé en ce que
    l'élément de construction mis en forme par frappe est sollicité en pression pendant le traitement thermique, dans un outil de presse, sur toute sa surface avec une surface de forme correspondant au contour définitif de l'élément.
  4. Procédé selon la revendication 3,
    caractérisé en ce que
    la cavité de formage de l'outil de presse est fermée de manière étanche sur le côté de l'élément de construction non tourné vers la surface de formage par une paroi souple, soumise de l'extérieur à un agent de pression pendant le traitement thermique.
  5. Procédé selon la revendication 4,
    caractérisé en ce que
    la cavité de formage entre la cloison souple et la surface de formage de l'outil de presse est mise sous vide pendant l'application de l'agent de pression externe et le traitement thermique de l'élément de construction.
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 EP0726106A1 (fr) 1996-08-14
EP0726106B1 true 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)

Families Citing this family (15)

* 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
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
EP2248926A1 (fr) * 2009-04-17 2010-11-10 voestalpine Automotive GmbH Procédé de fabrication d'une pièce emboutie
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
CN111195678B (zh) * 2020-01-11 2021-02-09 中南大学 一种大型薄壁构件节约型蠕变时效成形方法
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

Family Cites Families (9)

* 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
SU513091A1 (ru) * 1974-12-20 1976-05-05 Физико-Механический Институт Ан Усср Способ упрочнени изделий
DE2907420C3 (de) * 1979-02-26 1982-04-29 Helmut 6638 Dillingen Mischler Verfahren und Vorrichtung zur Herstellung von Reliefplatten für Türen, Fassaden u.ä. Zwecke aus Blech
US4329862A (en) * 1980-01-21 1982-05-18 The Boeing Company Shot peen forming of compound contours
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
US5168169A (en) * 1991-06-10 1992-12-01 Avco Corporation Method of tool development
CA2069189C (fr) * 1991-08-12 1998-04-14 Aerostructures Corporation Methode d'elaboration de formes complexes pour outils de formage
DE4305091C1 (de) * 1993-02-19 1994-03-10 Fuchs Otto Fa Verfahren zur Herstellung eines einteiligen Leichtmetallrades aus einem Aluminium-Knetwerkstoff

Also Published As

Publication number Publication date
DE59602038D1 (de) 1999-07-08
US6264771B1 (en) 2001-07-24
ES2135117T3 (es) 1999-10-16
DE19503620C2 (de) 1998-07-16
DK0726106T3 (da) 1999-12-13
GR3031046T3 (en) 1999-12-31
EP0726106A1 (fr) 1996-08-14
ATE180699T1 (de) 1999-06-15
CA2168592A1 (fr) 1996-08-04
DE19503620A1 (de) 1996-08-08

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