WO2011151565A1

WO2011151565A1 - Three-dimensional construction framework, method of producing such a framework and machine for implementing the method

Info

Publication number: WO2011151565A1
Application number: PCT/FR2011/051173
Authority: WO
Inventors: Jean Martin; Alain Blanck
Original assignee: Td Structure
Priority date: 2010-06-03
Filing date: 2011-05-24
Publication date: 2011-12-08
Also published as: FR2960895B1; FR2960895A1

Abstract

The invention relates to a method of producing a three-dimensional framework (1) consisting of a plurality of chords (2, 2A) lying parallel to one another, equidistant apart and in a staggered configuration in two parallel planes (3, 3A), one chord (2, 2A) being joined to at least one other, adjacent chord (2A, 2) via members (4). According to this method: a panel P, in which cuts have been made with removal of material so as to define the chords (2, 2A) and the members (4), is placed over a first part (9) of a matrix (10) of a machine to be deployed; the panel (P) is deployed in a direction perpendicular thereto by closing the matrix (10), causing said chords (2, 2A) to be offset in two parallel planes (3, 3A); and said panel (P) is deployed in the transverse direction parallel thereto. The invention also relates to a three-dimensional construction framework and to a machine for implementing the method.

Description

THREE DIMENSIONAL CONSTRUCTION FRAME, PROCESS FOR

REALIZATION OF SUCH FRAME AND MACHINE FOR IMPLEMENTING THE METHOD

The present invention relates to a three-dimensional construction reinforcement, a method for producing such an armature and a machine for carrying out the method.

The present invention is in the field of construction reinforcement, but also in the field of metal deployment machines.

In this regard, there are already machines for deploying metal, such machines being often used for producing grids or the like.

First of all, a metal sheet is first received a multitude of slitting operations so as to reproduce a repetitive pattern.

This sheet is then placed in a machine to be stretched therein resulting, because of slitting previously made, to define in this sheet metal openings conferring the shape of a grid.

In the same way, it is known to design a three-dimensional construction reinforcement in the form of an expanded metal.

Such an armature is in the form of a plurality of ribs extending parallel to each other at equidistance and in staggered rows in two parallel planes, one chord being connected to at least one other adjacent via jambs.

To design this frame, it is again made multiple slitting cuts in a sheet metal panel so as to define what will later be the frames and jambs.

This sheet is then subjected to a deformation consisting of a first stretching by drawing in the plane of this sheet followed by a stamping operation for shifting the members in two separate planes, in a configuration as indicated above. First of all, the slitting operations that the initial phase panel undergoes consist in shearing operations having the disadvantage of creating, at each of the connection nodes between members and jambs, rupture primers making the reinforcement particularly fragile.

Furthermore, the deformation of the panel after slitting, is obtained by two separate operations, the first is a deployment operation, so stretching, and the second is a stamping operation. Obviously, this involves multiple manipulations panels for their loading and unloading in a first deployment machine and in a second stamping machine.

Document FR-2.518.611 also discloses a prefabricated panel for real estate constructions. Such a panel is constituted by an armature having the characteristics mentioned above. For the manufacture of such a panel, it is implemented a method of maintaining the members of even rank 6.2n against a reference plane while not opposing their coplanar displacement and then to leave the frames of odd rank 6.2n + 1 free to move in space. This method consists, in fact, in pulling on the members of even rank, this in the reference plane and in an oblique direction. Under the effect of this traction, the members of even rank move, then, according to an oblique displacement resulting from the concomitant combination, on the one hand, of the spacing of the even two-by-two row members in the direction perpendicular to these and, on the other hand, the translation of the two frames considered relative to each other in the direction which is that of these frames themselves.

This method consists, therefore, in exerting traction on the even-rank members while keeping them in the same plane. Under the effect of the traction exerted on these members of even rank, the chords of odd rank, free in displacement and driven by the legs, are shifted with respect to the frames of even rank and are positioned parallel to the plane in which these even-rank chords extend.

It will be observed that the displacement of the chords of odd rank operates freely and solely under the effect of the traction exerted on the even-rank chords. Consequently, this displacement is in no way controlled or controllable so that the odd-sized members adopt a position and / or a random orientation with respect to each other. These chords of odd rank can not, therefore, come to be positioned in the same plane and find themselves offset relative to each other with respect to a median plane, or extend at an angle with such a median plane which is not eligible.

The present invention proposes to overcome the aforementioned drawbacks.

To do this, the invention relates to a method for producing a three-dimensional reinforcement by three-dimensional deployment of a panel that undergoes a deformation stretching in the plane and perpendicular thereto.

The invention also proposes a machine for implementing performance of this method.

To this end, the invention relates to a method for producing a three-dimensional reinforcement consisting of a plurality of members extending parallel to each other at equidistance and staggered in two parallel planes, a member being connected to at least one other adjacent member. via jambs joining said chords at a connecting node.

This process is characterized by the fact that:

a panel is provided, in which material-blanking cuts have been made to define the chords and jambs, on a first part of a matrix that comprises a three-dimensional deployment machine;

- By descent and interlocking, on the first part of the matrix, a second portion of the matrix that comprises the three-dimensional deployment machine, the panel is deployed in a direction perpendicular to the plane of the latter producing the offset, in two parallel planes, of said frames and;

then and through the three-dimensional deployment machine comprising the matrix, said panel is deployed in the transverse direction and parallel to the plane of the latter.

The invention also relates to a three-dimensional deployment machine, particularly for implementing the method described above, characterized in that it comprises a matrix having a first portion and a second portion adapted to close on said first portion each of the parts having a comb-shaped structure consisting of one or more parallel blades, while being transversely movable relative to each other in a defined path, the blades of the second part being defined to interpose between the blades of the first part when these blades are in the closed position and at the time of closure of the matrix.

Finally, the invention relates to a three-dimensional reinforcement consisting of a plurality of members extending parallel to each other at equidistance and staggered in two parallel planes, a member being connected to at least one other adjacent member by means of jambs joining said ribs at a connecting node. This reinforcement is characterized in that it is achieved by the implementation of the method described above and / or by the use of the three-dimensional deployment machine described above.

The present invention will be better understood on reading the following description relating to an exemplary embodiment given by way of indication and not limitation.

The understanding of this description will be facilitated by reference to the accompanying drawings in which:

- Figure 1 is a top view of an armature according to the invention; FIG. 2 is a sectional view of an armature as represented in FIG. 1;

FIG. 3 is a partial view in plan of a panel intended to define, after deployment, a reinforcement according to the invention;

- Figure 4 is a schematic and elevational view of a three-dimensional deployment machine according to the invention comprising a matrix in the open position for loading a panel to be deployed;

Figure 5 is a view similar to Figure 4, illustrating the matrix in the closed position and being deployed;

FIG. 6 schematically represents one of the parts of the comb-shaped matrix whose blades are driven so as to be progressively spaced apart from each other, producing the deployment for the design of the reinforcement according to the invention.

The present invention is in the field of reinforcements for a construction. It also relates to a method and a machine for producing such frames.

More particularly, as can be seen in FIGS. 1 and 2, the invention relates to a reinforcement 1 of three-dimensional type comprising a plurality of ribs 2, 2A extending parallel to each other, equidistant and staggered in two planes 3, 3A, parallel. In sum, these ribs 2, 2A form two rib plies in each of these parallel planes 3, 3A. Moreover, a frame 2 is connected to at least one adjacent frame 2A via jambs 4. As shown in FIG. 1, the legs 4 join a frame 2, 2A at a connection node 5.

According to the invention, such a frame 1 is made by three-dimensional deployment, in other words by stretching.

In this regard, the method for producing such a reinforcement 1 is to make cuts 6 with removal of material in a strip of suitable material, plus particularly metal 5 (especially sheet metal). Such cuts 6 may be performed by stamping, laser cutting or water jet, it being specified that the present invention can not be limited to such procedures.

As it appears again in FIG. 3, a row 7 of cutouts 6 is thus produced over the entire width of the strip. Moreover, in the longitudinal direction of the strip, it is reproduced, at equal distances, in succession. such rows 7 of cuts 6.

In short, one comes to reproduce, with regular steps, on said strip cutting, including stamping, a drawing always the same. This band is then debited so as to define panels P of similar length.

Of course, the press or any other machine making it possible to make the cuts 6 in this band, may comprise a matrix allowing the realization, in a single pass, of one or more rows 7 of cuts 6. In the case of design by stamping, the number of punches included in the die of the stamping machine will depend on the number of stamping cycles that must be printed on a strip to reach the length corresponding to a panel P. Moreover, this panel P is defined by transverse cutting at regular intervals of said strip.

According to the manufacturing method of this reinforcement 1 according to the invention, the panel P thus designed and cut is disposed in a machine 8 of three-dimensional deployment.

More particularly, this panel P comes to rest on a first portion 9 of a matrix 10 in the open position. The matrix 10 is then closed by interlocking, in the first part 9 of the latter, a second part 11 of this matrix 10, this before deploying the panel P in a direction 13 perpendicular to the latter (more particularly perpendicular to the plane of this panel P) and produce the offset, in the two parallel planes 3, 3A, of the frames 2, 2A. It is then proceeded to deploy the panel P in the transverse direction, parallel to the plane of the latter P (more particularly in the plane of the latter P), in particular parallel to the plane (3; 3A) of the frames (2; 2A).

Advantageously, during the positioning of the panel P in the matrix 10, this panel P is positioned and indexed in the direction of deployment in the plane of this panel P. More precisely, this positioning and indexing is carried out with respect to all or part of the frames 2, 2A. In short, thanks to this feature, the deployment of one chord relative to another adjacent is fully managed. As a result, after separation, each frame respects a constant spacing relative to an adjacent frame.

For this purpose on the first portion 9 and / or the second portion 11 of the matrix 10 are formed retaining means 12; 12A which, by engaging in the cutting openings 6, provide this positioning function.

According to an advantageous embodiment, each of the parts 9, 11 of the matrix 10 borrows a comb-like structure consisting of one or more blades 14, 14A parallel to each other, while being transversely movable relative to one another. to the other according to a defined race 15. As for the blades 14A of the second part 11, they are defined to be interposed between the blades 14 of the first part 9 when these blades 14 are in the constricted position that is to say at the time of closure of the matrix 10.

According to another feature of the invention, each of the blades 14; 14A of a matrix 9; 11 is connected, with this relative mobility substantially corresponding to the race 15, a following blade 14, 14A, this in the manner of links of a chain.

In addition, the three-dimensional deployment machine 8, according to the invention, further comprises drive means 17 connected at least to the first blade 14 ', at one of the transverse ends 16 at least of the first portion 9 of the matrix 10. Thus, through these drive means 17, it can being exerted on said first blade 14 'a traction leading to its spacing of the next blade 14 along the aforementioned stroke 15 corresponding, moreover, to the clearance between the first link that defines this first blade 14' relative to the second link corresponding to the second blade 14. Thus, this game caught, the traction exerted by the drive means 17 on said first blade 14 'is transmitted to the second blade 14 which moves relative to the next blade 14, again on the race 15 predefined and so on until the substantially maximum spacing of the links defined by the blades 14 of this first part 9 of the matrix 10 is obtained.

As for the second part 11 of this matrix 10, it is associated with complementary drive means 18, advantageously but not necessarily designed able to cooperate with the drive means 17 to simultaneously drive the blades 14A of this second Part 11 of matrix 10 with, however, a time and a delay distance corresponding to about half of the relative mobility stroke 15 between two blades 14 or 14A. Thus, under the effect of the deployment, the blades 14A of the second part 11 of the matrix move synchronously or almost synchronously with the blades 14 of said first portion 9 while positioning themselves equidistantly between two blades 14 of the first part 9 of this matrix 10.

Substantially, if the drive means 17 can take various forms such as those of a jack, drive chain or the like, the complementary drive means 18 consist, according to an advantageous embodiment, of an abutment 19 located at the transverse end 16A of the second portion 11 of the matrix 10. This stop 19 is designed to cooperate at the beginning of deployment and beyond a race 21 corresponding substantially to half the race 15, with a driving abutment 20 associated with the transverse end 16 of the first portion 9 of the matrix 10. Substantially, the driving abutment 20 may be defined by said first blade 14 'at the transverse end 16 of the first portion 9 of the die 10.

As indicated above, during the deployment, it is ensured by the retaining means 12, 12A, the positioning of the ribs (2, 2A) between them to ensure their equidistant spacing after stretching.

According to a preferred embodiment, these retaining means 12, 12A consist of tabs 22 overlying the blades 14, 14A and designed to engage in the cuts 6 that includes the panel P.

Preferably, these tongues 22 are distributed over a blade 14, 14A, so as to maintain a frame 2, 2A in a transverse direction, parallel to the deployment.

Note that through the machine according to the invention, the panel P is stretched over a width substantially greater than the final width of the frame 1 to compensate for the elastic shrinkage of this panel P when removing it from the matrix 10.

The deployment machine 8 according to the invention comprises, mounted on a frame 23, two guide tables 24, 24A, one 24, preferentially (but not necessarily) fixed receiving the first part 9 of the matrix 10 and the other 24A preferably (but not necessarily) vertically movable relative to the first 24, ensuring the maintenance and guidance of the second portion 11 of the matrix 10. The machine 8 further comprises hydraulic lifting means and / or mechanical ensuring mobility including of the second table 24A relative to the first 24 to, as appropriate, open or close the matrix 10.

It is also through this mobility that the complementary drive means 18 come to cooperate with the drive means 17.

It should be observed that under the effect of the deployment of the panel P perpendicular to its plane and, therefore, of the insertion of the comb corresponding to the second part 11 of the matrix 10 in the comb defined in the first part 9, it may result a longitudinal shift of the frames 2 located in a plane 3, this with respect to the ribs 2A located in the parallel plane 3A.

Also, the machine can be equipped, advantageously, means for cutting the frames 2, 2A to at least one of the ends of the frame 1, after deployment of the panel P perpendicularly to its plane.

The advantages which derive from the present invention consist in obtaining a reinforcement essentially of increased mechanical strength because devoid of initiation of rupture.

In addition, through the deployment method and the machine for its implementation, the armature can be deployed in a single operation and using a single machine, in each direction, it is parallel or perpendicular to the plane of the panel P. This obviously results in a gain in production capacity and a lower cost.

Finally, the method and the machine according to the invention make it possible to ensure, manage, and control with precision and reliability the deployment of the panel P as well as the positioning of the frames (2; 2A) within the three-dimensional frame 1 In particular, this method and this machine make it possible to obtain a three-dimensional reinforcement 1 in which the ribs (2; 2A) extend in two strictly parallel planes (3; 3A).

Claims

1. A method for producing a three-dimensional reinforcement (1) consisting of a plurality of ribs (2, 2A) extending parallel to each other at equidistance and in staggered rows in two parallel planes (3, 3A), one chord (2 , 2A) being connected to at least one other (2A, 2) adjacent via jambs (4) joining said chords (2, 2A) at a connecting node (5), characterized in that :

a panel (P) is provided, in which material-blanking cuts have been made to define the chords (2, 2A) and the legs (4) on a first part (9) of a matrix (10). that comprises a three-dimensional deployment machine (8);

- by descent and interlocking, on the first part (9) of the matrix (10), a second part (11) of the matrix (10) that comprises the three-dimensional deployment machine (8), the panel is deployed ( P) in a direction perpendicular to the plane of the latter (P) producing the offset, in two parallel planes (3, 3A), of said chords (2, 2A) and;

then and through the three-dimensional deployment machine (8) comprising the matrix (10), it deploys said panel (P) in the transverse direction and parallel to the plane of the latter (P).

2. Method according to claim 1, characterized in that in a metal strip:

- Cutouts (6) are made at regular intervals to define the chords (2, 2A) and jambs (4) by stamping, laser cutting or water jet;

said strip is debited according to a given length, so as to define a panel P.

3. Method according to claim 1, characterized in that it ensures a positioning and indexing of the panel P by relative to all or part of its members (2, 2A) when engaged in the matrix (10).

4. Three-dimensional deployment machine (8), especially for the implementation of the method according to any one of claims 1 to 3, characterized in that it comprises a matrix (10) having a first portion (9) and a second part (11) able to close on said first part (9), each of the parts (9; 11) borrowing a comb-shaped structure consisting of one or more blades (14; 14A) parallel to each other , while being movable transversely relative to each other along a defined path (15), the blades (14A) of the second portion (11) being defined so as to be interposed between the blades (14) of the first portion (9) when these blades (14) are in the closed position and at the time of closure of the matrix (10).

5. Deployment machine (8) according to claim 4, characterized in that each of the blades (14; 14A) of a portion (9; 11) of the matrix (10) is connected in a mobile manner according to the race (15) to a next blade (14; 14A) in the manner of links of a chain.

6. Deployment machine (8) according to claim 4 or 5, characterized in that it comprises drive means (17) connected at least to the first blade (14 ') at one of the transverse ends (16) at least of the first part (9) of the matrix (10).

7. Deployment machine (8) according to claim 6, characterized in that the second portion (11) of the matrix (10) comprises complementary drive means (18) adapted to cooperate with the drive means ( 17) of the first part (9) of the matrix (10).

8. Deployment machine (8) according to claim 7, characterized in that the complementary drive means (18) consist of a stop (19) that comprises the second portion (11) of the matrix (10) designed adapted to cooperate with a complementary abutment (20) associated with the first part (9) of the matrix (10) beyond a stroke (21) corresponding substantially to half of the stroke (15) between two blades (14; 14A).

9. Deployment machine (8) according to claim 8, characterized in that the complementary stop (20) is defined by the first blade (14 ') at the transverse end (16) of the first portion (9) of the matrix (10).

10. Deployment machine (8) according to any one of claims 4 to 9, characterized in that it comprises, on said blades (14; 14A), retaining means (12; 12A) designed able to position and indexing a panel (P) on said first portion (9) and second portion (11) of the matrix (10).

11. Deployment machine (8) according to claim 10, characterized in that the retaining means (12, 12A) are constituted by tabs (22) surmounting the blades (14, 14A) designed adapted to engage in the cutouts (6) that comprises the panel P.

12. Deployment machine (8) according to one of claims 4 to 11, characterized in that it comprises, mounted on a frame (23), two guide tables one (24) fixed receiving the first part (9) of the matrix (10) and the other (24A) vertically movable relative to the first (24) receiving the second portion (11), the machine (8) further comprising lifting means ensuring the mobility of the second table (24A) relative to the first (24) to open and close the die (10).

13. Deployment machine (8) according to one of claims 4 to 12, characterized in that it comprises means for cutting chords (2, 2A) to at least one of the ends of the armature ( 1) after deployment of the panel (P) perpendicularly to its plane.

14. A three-dimensional armature (1) consisting of a plurality of ribs (2, 2A) extending parallel to each other at equidistance and staggered in two parallel planes (3, 3A), a chord (2, 2A) being connected to at least one other (2A, 2) adjacent via jambs (4) joining said chords (2, 2A) at a connection node (5), characterized in that it is realized by the implementation of the method according to any one of claims 1 to 3 and / or by use of the three-dimensional deployment machine (8) according to any one of claims 4 to 13.