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EP1543893B1 - Verfahren zum Kröpfen eines Profils und damit hergestelltes Profil - Google Patents

Verfahren zum Kröpfen eines Profils und damit hergestelltes Profil Download PDF

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Publication number
EP1543893B1
EP1543893B1 EP04300911A EP04300911A EP1543893B1 EP 1543893 B1 EP1543893 B1 EP 1543893B1 EP 04300911 A EP04300911 A EP 04300911A EP 04300911 A EP04300911 A EP 04300911A EP 1543893 B1 EP1543893 B1 EP 1543893B1
Authority
EP
European Patent Office
Prior art keywords
thickness
wing
length
slope
joggle
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.)
Not-in-force
Application number
EP04300911A
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English (en)
French (fr)
Other versions
EP1543893A1 (de
Inventor
Franck Guinchard
Yves Judic
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 Operations SAS
Original Assignee
Airbus Operations SAS
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 Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of EP1543893A1 publication Critical patent/EP1543893A1/de
Application granted granted Critical
Publication of EP1543893B1 publication Critical patent/EP1543893B1/de
Anticipated expiration legal-status Critical
Not-in-force 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
    • B21D11/00—Bending not restricted to forms of material mentioned in only one of groups B21D5/00, B21D7/00, B21D9/00; Bending not provided for in groups B21D5/00 - B21D9/00; Twisting
    • B21D11/18—Joggling

Definitions

  • the invention relates to a method for forming a profile as indicated in the preamble of claim 5 and a seam profile as indicated in the preamble of claim 1.
  • a profile is to deform such a profile so as to create a gap between two of its parts.
  • the beam profile is a beam of any section having in its profile a mast and wings at both ends of the mast.
  • the object of the invention is to reduce a length in the offset imparted by a jog.
  • the present invention finds a particularly advantageous, but not exclusive, application in the field of aeronautics.
  • a seamed section is used to strengthen a connection between two parts, such as two parts of an aircraft, which are not aligned with each other.
  • Figure 1 shows a view of a profiled section 100 of the state of the art.
  • This profile here comprises an I-shaped section but could include any section, such as a C or U-shaped section.
  • This profile 100 includes a first and a second wing 101 and 102 and a mast 103.
  • the first wing 101 is of great thickness E1 and the second wing 102 is of small thickness E2.
  • This profile 100 is used to ensure or strengthen a connection between a part 121 and a part 122.
  • the first wing 101 and the second wing 102 each unfurl in a plane that forms a non-zero angle with a plane of the mast 103, itself located in the plane of Figure 1.
  • these wings 101 and 102 are each deploys in a plane that is perpendicular to a plane of the mast 103.
  • a linkage 104 is present between a first portion 105 and a second portion 106 of the section. This gap 104 corresponds to the portion of the profile 100 which is deformed. This gap 104 provides an offset between the first portion 105 and the second portion 106.
  • the offset extends in the plane of the mast 103 of the profile with a height H offset measured in a direction perpendicular to the plane of the wings 101 and 102, and with an offset length L measured in a direction parallel to the planes of the mast 103 and the wings 101 and 102.
  • This length L is calculated according to a thickness of a wing.
  • the length L is generally equal to six times the thickness of a wing. This ratio between the thickness of a wing and the length L varies according to the material in which the section is made. The length L is as short as possible but can not be reduced as much as desired. Indeed, the proportion of six times the thickness of the wing is a constraint that can not be transgressed without risk of deterioration of the profile.
  • the length L is therefore calculated from the thickness of the larger of the two wings.
  • the length L is equal to six times the thickness E1 of the wing 101 of great thickness.
  • the profile 100 thus has identical slopes on both sides of the wings 103 and 104
  • the object of the invention is to solve this problem of excessive space 130 between the profile 100 and the parts 121 and 122.
  • the invention implements in particular a seam profile having offset lengths calculated according to each of the thicknesses of the profile.
  • the length of the offset provided by the wing-side trimming of greater thickness is greater than the length of the offset provided by the trimming of the thin wing side. In the invention, these lengths are no longer identical.
  • the sinking of the seam profile according to the invention comprises a particular geometry in which ends of the trimming forms a quadrilateral resembling a trapezium at the difference of near slopes. In this quadrilateral, no side is parallel to another. Projections Thin edge ends of the flange are preferably located inside end projections of the flange on the wing side of great thickness.
  • the thin wing is placed on two non-aligned pieces, a connection between them is to strengthen.
  • the length of the offset provided by the flanging of the side of the thin wing is equal to N times the length of the small thickness; while this length would have been equal to N times the length of the great thickness using a method of commuting the state of the art.
  • N is in an example equal to six but varies depending on the nature of the material in which the profile is made.
  • the invention relates to a shredding method according to claim 5.
  • a method is implemented in which a punch is pressed against a section wedged between this punch and an anvil.
  • a punch which comprises a portion having a small gradient that extends over a length proportional to the thickness of the wing of great thickness.
  • An anvil is also made which comprises a portion having a steep slope which extends over a length which is proportional to a thickness of the wing of small thickness. The anvil is fixed. The punch is mobile.
  • the side of the profile with the thin wing is placed against the anvil. Then the punch is placed against the side of the profile with the wing of great thickness. The punch is placed so that projections of ends of the part of the anvil having a slope in the opposite direction of a support, are located between projections of the ends of the part of the punch having a slope in the direction of support. In particular achievements, some projections may be confused with each other.
  • the punch is then pressed so that the profile is compressed between the punch and the anvil.
  • the segments of the slope of the punch and the anvil are different, the shapes printed by this punch and this anvil on one side and the other of the profiling of the profile are different.
  • the punch has a steep slope segment and the anvil has a low slope segment.
  • the invention also relates to a profile according to claim 1.
  • FIG. 2 shows the profiled section 200 according to the invention comprising, as in FIG. 1, the mast 103, the first wing 101 of great thickness E1 and the second wing 102 of small thickness E2.
  • This profiled 200 plays a role of liaison between the parts 111 and 110, such as parts of an aircraft.
  • the linkage gap 201 provides an offset between the first portion 105 and the second portion 106 of the section 200. This offset exists relative to a plane P of alignment between these two parts. This offset extends in the plane of the mast of the profile with a height H measured in one direction perpendicular to the plane of the wings and with a length L1 or L2 measured in a direction parallel to the plane of the mast and wings.
  • the height H of the offset of the wing of large thickness and that of the side of the wing of small thickness are identical.
  • the length L1 of the offset of the wing 101 of thick thickness is greater than the length L2 of the offset of the wing 102 of thin thickness.
  • the profile 200 has a low slope, in the sear 201, the side of the wing 101 of great thickness, and a steep slope in the groove 201, the side of the wing 102 of small thickness.
  • the length L1 is proportional to the thickness E1 of the wing 101 and the length L2 is proportional to a thickness E2 of the wing 102.
  • the lengths L1 and L2 are respectively equal to six. times the great thickness E1 and six times the small thickness E2.
  • this ratio varies depending on the nature of the material in which the section 200 is made.
  • the trimming 201 of sharp slope on the side of the wing 102 of small thickness spreads between the two parts 105 and 106, over a length L2 equal to six times the thickness of this thin wing.
  • the gap 201 of small slope of the side of the wing of great thickness spreads between the two parts 105 and 106, over a length equal to six times the thickness of this wing of great thickness.
  • the ratio between the lengths L1 and L2 and the thicknesses E1 and E2 can vary within a range of real values between four and ten.
  • projections of the ends of the linkage 201, on the side of the steep slope are located between end projections of the linkage 201, on the side of the weak slope.
  • the ends of the groove 201 on the side of the wing 102 of small thickness are projected in a direction perpendicular to the wings 101 and 102, and in a direction from the small wing 102 to the large wing 101.
  • the projections of these ends are located between projections of ends of the groove 201 on the side of the wing 101 of great thickness, in the direction perpendicular to the wings 101 and 102, and in a reverse direction from the main wing 101 to the small wing 102.
  • a projection of one end of the groove 201, on the side of the steep slope, along the direction and the aforesaid direction is confused with a projection of one end of the soyage, on the side of the weak slope, in the direction and the opposite direction mentioned above.
  • the distance P1 and P2 can result in the highlighting of a distance P1 and a distance P2.
  • the distance P1 which extends in a direction parallel to the planes of the mast 103 and the wings 101 and 102, separates opposite ends of the seam 201.
  • a distance P2 which extends in the direction parallel to the plane of the mast 103 and wings 101 and 102, separates other opposite ends of the seam 201. In general, these distances P1 and P2 are different.
  • the distance D1 or the distance D2 is zero. This embodiment is shown in broken lines in the figure.
  • the jogging 201 thus has a geometry completely different from that of the jig 104 of the section of FIG. 1.
  • the ends of the jig 210 form a quadrilateral 210, in which, unlike a quadrilateral associated with the jig 104, no side n ' is parallel to another.
  • the geometry of the trimming 201 is determined according to a bulk, a geometry of an external system, or stops surrounding the section 300. This geometry can also be determined with respect to a mechanical reinforcement indicated in a specification. .
  • the space 130 between the profile 200 and the parts 121 and 122 is reduced in order to satisfy the requirements of a design office.
  • this reduction in space makes it possible to satisfy constraints related to an assembly rigidity or a resistance between the parts 110 and 111.
  • FIG. 3 shows steps of a trimming method for producing the seamed section of FIG. 2. This method is implemented on a straight profile 300 comprising the wings 101 and 102 of great thickness and of small thickness.
  • a fixed anvil 301 is produced comprising a segment 302 of steep slope which spreads between two parts 303 and 304 parallel along the length L2.
  • This length L2 is proportional to a thickness E2 of the wing 102 of small thickness.
  • a punch 311 is also made comprising a segment 312 of low slope which spreads between two parallel portions 313 and 314 on a length L1.
  • This length L1 is proportional to a thickness of the wing 101 of great thickness.
  • the lengths L1 and L2 of the segments 302 and 312 of steep slope and low slope are respectively equal to N times the thickness of the wing 101 of great thickness and N times the thickness of wing 102 of small thickness.
  • N is a real number which in an example is equal to 6. However, N varies according to the nature of the material in which the profile 300 is made.
  • FIG. 3a shows a step in which the wing 102 of small thickness of the profile 300 is placed against the anvil 301.
  • the punch 311 is then placed against the wing 101 of great thickness of the profile 300.
  • ends of the segment 302 of steep slope are placed so that projections of the ends of the steep slope segment 302 in the opposite direction of a support are located between projections in the direction of the support. ends of segment 312 of low slope.
  • the punch 311 is then in an initial position.
  • an end of the low slope segment 312 is placed so that the projection of this end is coincident with a projection of one end of the steep slope segment 302.
  • a distance P1 is observed between one end of the segment 302 of steep slope and one end of the segment 312 of low slope. There is also a distance P2 between another end of the segment 302 of steep slope and another end of the segment 312 of low slope. These distances are observed in a direction parallel to the plane of the mast 103 and the wings 101 and 102. The length of these distances P1 and P2 can be adjusted by the arrangement of shims 321 and 322.
  • the shims 321 and 322 further maintain the punch 311 during its placement against the wing 101 of great thickness.
  • the shims 321 and 322 and the anvil 301 are fixed and are interconnected by means of parts 330 that can be secured to a frame.
  • FIG. 3b shows a step in which the punch 311 is pressed so that this punch 311 and anvil 301 print their shape to the profile 300.
  • the wedge 321 is withdrawn laterally and pressure forces are exerted on the punch 311.
  • These pressure forces F1 are applied in a direction perpendicular to the plane of the wings 101 and 102 and in a direction from the wing 101 of great thickness to the wing 102 of small thickness.
  • the shim 321 is not removed and the anvil slides between the two shims 321 and 322. More specifically, in this embodiment, the wedge 322 does not move laterally to release the punch.
  • the punch 311 then has a degree of freedom allowing it to slide between the shims 321 and 322.
  • the shims 321 and 322 hold the punch 311 only during the time of its placement and then allow its movement during the support.
  • These forces F1 are applied locally in an area of the segments 302 and 312 of slopes. Alternatively, these forces F1 are not only applied in the zone of the segments 302 and 312 of slope, but also in a zone framing these segments 302 and 312 of slope. By applying the forces F1 in an area which surrounds the segments 302 and 312, it is possible to carry out a more precise trimming, the slopes made in the trimming being very sharp.
  • These F1 forces can be generated using a press or a cylinder. A screw or other mechanical machine exerting mechanical forces can also generate these forces F1.
  • FIG. 3c shows a step in which the serrated section is disengaged from the grip of the anvil 301 and the punch 311 used in the process.
  • pressure forces F 2 that are opposite to the support forces F1 are exerted first, so that the punch 311 is no longer in contact with the profile 300.
  • the shim 322 so that the punch 312 is again blocked.
  • the shim 322 is not moved laterally and the punch slides vertically between the shims 321 and 322 to return to the initial position.
  • the shims 321 and 322 then have a configuration ensuring a locking of the punch 311.
  • the starting section 300 is seant according to the dimensions of the anvil 301 and the punch. Indeed, in the jogging 201, the slopes are formed on the side of the large wing 103 and the wing of small thickness 104. Ends of the squelch 210 form the vertices of the particular quadrilateral 210. In the variant where end projections are coincident, that is to say where the distance P1 or the distance P2 is zero, the quadrilateral 210 has a side perpendicular to a horizontal plane.
  • the punch 311 may comprise the segment 302 of steep slope which extends over a length proportional to a thickness of the wing 102 of small thickness.
  • the anvil 304 then comprises the segment 312 of low slope which is spread over a length proportional to a thickness of the wing 101 of great thickness.
  • the section 300 is then returned so that each of its wings are opposite the slope segment corresponding thereto.
  • the bead profile of the invention here comprises two wings but it could have more than two wings.
  • the profile to soyer may for example have three wings or four wings parallel to each other, the smes section obtained with the same number of wings.
  • the punch then has a shape adapted to the number of wings of the profile to be soyer. In a particular embodiment, the punch has several levels coming to press against the different wings of the profile.
  • the profiling of the profile can be carried out cold or hot.
  • the determination of the temperature at which the profile is to be worn depends on the shape of the section of this section and the nature of the material in which this profile is made.

Landscapes

  • Mechanical Engineering (AREA)
  • Engineering & Computer Science (AREA)
  • Wind Motors (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Soil Working Implements (AREA)
  • Yarns And Mechanical Finishing Of Yarns Or Ropes (AREA)
  • Soy Sauces And Products Related Thereto (AREA)
  • Insertion Pins And Rivets (AREA)
  • Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Prostheses (AREA)
  • Non-Disconnectible Joints And Screw-Threaded Joints (AREA)
  • Toys (AREA)

Claims (9)

  1. Profil (200) mit zwei Flügeln (101, 102) und einem Mast (103), einem ersten Flügel (101), dessen Ebene einen Winkel nicht gleich Null mit einer Ebene des Masts bildet und eine Stärke E1 hat, die große Stärke genannt wird, und einem zweiten Flügel (102), dessen Ebene einen Winkel nicht gleich Null mit der Ebene des Masts bildet und eine Stärke E2 hat, die kleine Stärke genannt wird, wobei die Stärke E1 größer ist als die Stärke E2, wobei das Profil (200) mit einem Verbindungsdurchzug gebildet ist, der zwischen einem ersten Teil (105) und einem zweiten (106) Teil des Profils (200) angeordnet ist, wobei der Durchzug (101) einen Versatz zwischen dem ersten Teil (105) und dem zweiten Teil (106) verleiht, wobei sich der Versatz in der Ebene des Masts (103) des Profils mit einer Höhe (H), die gemäß einer Richtung senkrecht zu der Ebene der Flügel gemessen wird, und mit einer Länge (L), die in eine Richtung parallel zu den Ebenen des Masts und der Flügel gemessen wird, erstreckt, dadurch gekennzeichnet, dass es Folgendes umfasst:
    - eine Neigung mit der Länge L1, schwache Neigung in dem Durchzug (201) genannt, auf der Seite des Flügels (101) mit großer Stärke, und eine starke Neigung mit einer Länge L2, starke Neigung genannt, in dem Durchzug (201) auf der Seite des Flügels (102) mit kleiner Stärke, wobei die Länge L1 größer ist als die Länge L2.
  2. Durchzugprofil nach Anspruch 1, dadurch gekennzeichnet,
    - dass Endvorsprünge des Verbindungsdurchzugs (201) auf der Seite der starken Neigung zwischen Endvorsprüngen des Verbindungsdurchzugs auf der Seite der geringen Neigung liegen.
  3. Durchzugprofil nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass
    - ein Vorsprung eines Endes des Durchzugs (201) auf der Seite der starken Neigung mit einem Vorsprung eines Endes des Durchzugs (201) der Seite der schwachen Neigung zusammenfällt.
  4. Durchzugprofil nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet,
    - dass sich der Durchzug (201) mit starker Neigung auf der Seite des Flügels (102) mit geringer Stärke (E2) zwischen den zwei Teilen über eine Länge (L2) ausbreitet, die gleich sechs Mal der Stärke (E2) dieses Flügels (102) mit geringer Stärke ist, und
    - dass sich der Durchzug (201) mit geringer Neigung auf der Seite des Flügels (101) mit großer Stärke sich zwischen den zwei Teilen über eine Länge (L1) ausbreitet, die gleich sechs Mal der Stärke (E1) dieses Flügels (101) mit großer Stärke ist.
  5. Verfahren zum Durchziehen eines Profils (300), das einen Flügel (101) mit großer Stärke E1 aufweist, große Stärke genannt, und einen Flügel (102) mit der Stärke E2, kleine Stärke genannt, wobei die Stärke E1 größer ist als die Stärke E2, dadurch gekennzeichnet, dass es die folgenden Schritte aufweist:
    - Herstellen eines stationären Ambosses (301), der ein Neigungssegment (302) mit der Länge L2, starke Neigung genannt, aufweist, wobei sich dieses Segment (302) mit starker Neigung zwischen zwei Teilen des Ambosses (303, 304) ausbreitet, die über eine Länge L2 parallel sind, die zu einer Stärke E2 des Flügels (102) mit kleiner Stärke proportional ist,
    - Herstellen eines Stempels (311), der ein zweites Neigungssegment (312) mit der Länge L1, schwache Neigung genannt, aufweist, wobei sich dieses Segment (312) mit schwacher Neigung zwischen zwei Teilen des Stempels (313, 314) ausbreitet, die über eine Länge L1 parallel sind, die zu einer Stärke E1 des Flügels (101) mit großer Stärke proportional ist, wobei die Länge L1 größer ist als die Länge L2, und
    - Anordnen des Flügels (102) mit kleiner Stärke des Profils gegen den Amboss (301),
    - Anordnen des Flügels (311) gegen den Flügel (101) mit großer Stärke,
    - Andrücken des Stempels (311) gegen den Flügel (102) mit großer Stärke.
  6. Verfahren nach Anspruch 5, dadurch gekennzeichnet,
    - dass man den Stempel (311) seitlich während des Drückens mit Verkeilungen (321, 322) hält.
  7. Verfahren nach einem der Ansprüche 5 bis 6, dadurch gekennzeichnet,
    - dass man die Enden des Segments (312) mit geringer Neigung so anordnet, dass sich Endvorsprünge des Segments (302) mit starker Neigung in die umgekehrte Richtung des Andrückens zwischen Endvorsprüngen des Segments (312) mit geringer Neigung in die Richtung des Andrückens befinden.
  8. Verfahren nach einem der Ansprüche 5 bis 7, dadurch gekennzeichnet,
    - dass man ein Ende des Segments (321) mit geringer Neigung so anordnet, dass der Vorsprung dieses Endes mit einem Vorsprung eines Endes des Segments (302) mit starker Neigung zusammenfällt.
  9. Verfahren nach einem der Ansprüche 5 bis 8, dadurch gekennzeichnet,
    - dass man das Durchziehen warm oder kalt durchführt.
EP04300911A 2003-12-18 2004-12-16 Verfahren zum Kröpfen eines Profils und damit hergestelltes Profil Not-in-force EP1543893B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0351117 2003-12-18
FR0351117A FR2864200B1 (fr) 2003-12-18 2003-12-18 Procede pour soyer un profile et un profile soye selon ce procede

Publications (2)

Publication Number Publication Date
EP1543893A1 EP1543893A1 (de) 2005-06-22
EP1543893B1 true EP1543893B1 (de) 2006-08-23

Family

ID=34508795

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04300911A Not-in-force EP1543893B1 (de) 2003-12-18 2004-12-16 Verfahren zum Kröpfen eines Profils und damit hergestelltes Profil

Country Status (7)

Country Link
US (1) US7210275B2 (de)
EP (1) EP1543893B1 (de)
AT (1) ATE337114T1 (de)
CA (1) CA2490738C (de)
DE (1) DE602004002072T2 (de)
ES (1) ES2271817T3 (de)
FR (1) FR2864200B1 (de)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0805268D0 (en) * 2008-03-25 2008-04-30 Airbus Uk Ltd Composite joint protection
US9676469B2 (en) * 2014-04-10 2017-06-13 Lockheed Martin Corporation System and method for fastening structures

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2767763A (en) * 1953-04-13 1956-10-23 Boeing Co Joggle punch and die sets
AT361758B (de) * 1979-06-06 1981-03-25 Simmering Graz Pauker Ag Verfahren zum biegen, kroepfen od.dgl. verformen von c-traegern und vorrichtung zur durchfuehrung dieses verfahrens
DE69120895T2 (de) * 1990-11-05 1997-01-02 Kawasaki Steel Co Verfahren zum Walzen von Doppel-T-Trägern
LU88566A1 (fr) * 1994-12-07 1996-07-15 Profilarbed Sa Procédé de laminage de palplanches à section en forme de Z
DE19653959C1 (de) * 1996-12-21 1998-02-05 Benteler Werke Ag Querträger und Verfahren zum Herstellen eines Querträgers
IT1290903B1 (it) * 1997-01-29 1998-12-14 Massimo Ferrante Metodo di fabbricazione di profilati rigidi snodabili manualmente, impiegabili come ossatura di pareti, contropareti, controsoffitti e
US6420014B1 (en) * 1999-12-28 2002-07-16 L. B. Foster Company Z-shaped sheet piling

Also Published As

Publication number Publication date
ES2271817T3 (es) 2007-04-16
EP1543893A1 (de) 2005-06-22
DE602004002072D1 (de) 2006-10-05
FR2864200A1 (fr) 2005-06-24
FR2864200B1 (fr) 2006-03-10
CA2490738A1 (fr) 2005-06-18
ATE337114T1 (de) 2006-09-15
US20050230551A1 (en) 2005-10-20
US7210275B2 (en) 2007-05-01
CA2490738C (fr) 2008-06-10
DE602004002072T2 (de) 2007-02-08

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