EP3615470A1

EP3615470A1 - Method for manufacturing a mechanism

Info

Publication number: EP3615470A1
Application number: EP18717965.0A
Authority: EP
Inventors: Thomas MERCIER; Christian GUICHARD; Guy Semon
Original assignee: LVMH Swiss Manufactures SA
Current assignee: LVMH Swiss Manufactures SA
Priority date: 2017-04-25
Filing date: 2018-04-24
Publication date: 2020-03-04
Anticipated expiration: 2038-04-24
Also published as: JP2020517949A; CN111278765B; JP7184800B2; US20200192299A1; US11467542B2; EP3615470B1; CN111278765A; FR3065542B1; FR3065542A1; WO2018197516A1

Abstract

A method for manufacturing a mechanism (100) comprises the steps consisting of: i) assembling planar layers (10; 56; 58; 60; 64) together to form a substantially planar multilayer structure (68); ii) deploying the multilayer structure in a direction (Z) substantially normal to the planar layers (10; 56; 58; 60; 64). At least one first layer (60) of said layers (10; 56; 58; 60; 64) forms a flexible blade (62) in the mechanism (100). The blade (62) is attached, in the mechanism (100), to a mass (92). The mass (92) is more rigid than the blade (62). The blade (62) is attached to the mass (92) during a step that follows the step ii). This method can be implemented, in particular, for manufacturing all or part of a mechanism such as a timepiece movement.

Description

METHOD FOR MANUFACTURING A MECHANISM

The present invention relates to a method of manufacturing a mechanism, in particular a flexible mechanism, and the use of this method to manufacture all or part of a watch movement, in particular a watch movement regulator. The invention also relates to a mechanism, in particular a watch movement, made in whole or in part by implementing this method.

In the field of watchmaking, it is known to perform all or part of a watch movement in a monolithic manner. In particular, the regulator of a watch movement can be made monolithically.

The application WO-A-2016/091 823 in the name of the applicant describes such a watch movement regulator, obtained from a silicon wafer, in particular by etching the silicon wafer. Such a monolithic regulator thus has a limited number of parts moving relative to each other. This limits the number of friction zones, which are located at the level of the parts in contact, which are moving relative to each other.

The realization of a watch movement regulator from a single material slab, however, poses certain difficulties.

Firstly, it is generally necessary to use a formatting step, for example an etching step, which must be implemented in a clean room. This induces an additional cost of realization of the watch movement.

Then, the geometry of the constituent elements of the watch movement is limited. For example, it is difficult with current techniques to make any flexible blade of any orientation, having an aspect ratio greater than about 25, at this scale. It is recalled that the aspect ratio of a flexible blade is defined by the ratio of its width to its thickness. It is also recalled that the length of a blade is the dimension along the direction passing through the anchoring points of the blade. The length thus generally corresponds to the largest dimension of this blade. The thickness of the blade is its smallest dimension. Finally, the width is the "intermediate" dimension of the blade, larger than its thickness, but smaller than its length. It should be noted however that the width of a blade may, in some particular cases, be substantially equal to its length. However, such a flexible blade, or "flexure" is particularly implemented in a watch movement to achieve a regulator. A regulator is an oscillating device. A flexible blade, with the largest aspect ratio possible, is preferred in this case, especially when the width of the blade extends in a plane substantially perpendicular to the base plane of the oscillator. In this case, indeed, a large aspect ratio makes it possible to limit the oscillations of the blade out of the basic plane of the oscillator.

In addition, at constant width, the increase in the aspect ratio induces a reduction in the thickness of the flexible blade. A flexible blade of reduced thickness is also preferred because it allows oscillation of the regulator at a lower natural frequency.

Moreover, in such a monolithic regulator, the same material serves both for the flexible blades and the rigid masses which are connected by the flexible blades. This therefore limits the design possibilities of the regulator, in particular with regard to the material used.

However, it is known, for example from the application WO-A-2012/109559, a method of manufacturing a three-dimensional structure comprising the following steps.

First, we superimpose and assemble different layers of different materials, previously machined, to obtain a flat multilayer structure. The layers comprise folding primers of the layer concerned and / or rupture primers. It is then possible to develop the plane multilayer structure, by exerting traction on one of the layers, in a direction substantially normal to the planar multilayer structure. This gives a three-dimensional deployed structure.

In the case of this type of method, it is known to use rigid layers to make rigid parts of the three-dimensional structure, and flexible layers to form joints between the rigid parts. The joints thus formed can, if necessary, be blocked after the deployment of the three-dimensional structure, in particular by gluing or laser welding.

In the case of this application WO-A-2012/109559, the parts attached to a flexible layer, are in the step of superposition and assembly layers planar. This allows the easy realization of a joint between the parts attached to the flexible layer. Moreover, in the final three-dimensional structure, the flexible layer extends over a very small distance between the rigid parts that it connects, the flexible layer forming mainly an angle between the rigid parts.

Thus, the method described in this application WO-A-2012/109559 is limited as to the variety of structures it allows to achieve.

An object of the invention is to provide a method for manufacturing a wide variety of mechanisms.

To this end, the invention provides a method of manufacturing a mechanism, including a flexible mechanism, comprising the steps of:

i) assembling planar layers together to form a substantially flat multilayer structure;

ii) deploying the multilayer structure in a substantially normal direction to the planar layers;

method in which at least a first layer of said layers forms at least one flexible blade in the mechanism, the blade or blades being fixed in the mechanism to at least one mass, preferably to two masses, the or each mass being stiffer that the blade or blades, or the blades being fixed to the or each mass at a step subsequent to step ii).

Thus, advantageously, the method according to the invention makes it possible to produce a mechanism having at least one flexible blade attached to one or more rigid masses. Such a method is advantageously applicable in many fields, in particular in the mechanisms of glasses or watches. In the latter case, in particular, the method according to the invention makes it possible, for example, to produce an oscillating regulator with one or more flexible blades of reduced dimensions, for example of thickness between 2 and 25 μιη, and substantially constant, giving access at lower oscillation frequencies of the regulator than those generally obtained in the case of a monolithic regulator, realized by implementing the known methods. The method according to the invention also makes it possible to obtain one or more flexible blades having a high aspect ratio, in particular greater than that traditionally obtained in the case of a monolithic regulator, produced by placing implement the methods conventionally implemented at this scale, that is to say at the centimeter scale.

According to preferred embodiments, the method according to the invention comprises one or more of the following characteristics, taken alone or in combination:

each blade has, in the mechanism, a free length greater than one-third of the width of the blade considered, the free length being defined as being:

o the length of the blade that is not in contact with the mass, in the case where the blade is attached to a mass, or

o the length of the blade which extends between the two masses, without being in contact with one of the masses, in the case where the blade is fixed to two masses,

the or each blade preferably not being in contact with any other element of the mechanism over the free length;

the method comprises a step iii) subsequent to step ii), of blocking the multilayer structure in the deployed position;

step iii), the structure is locked in the deployed position by implementing at least one of overmoulding, brazing, clipping, gluing, welding, especially spot welding, in particular spot welding laser, and a clamping, at least a part of the mechanism, including at least one articulation of the mechanism;

the or each mass is attached at one end, preferably at a respective end, of one of said at least one blade;

the or each mass is fixed to the blade or to each blade by: overmolding; brazing; clipping; collage; welding, especially spot welding, in particular spot welding; Tightening ;

the mass or masses are produced by at least one of the flat layers assembled in step i);

the one or more masses are in one of tungsten, molybdenum, gold, silver, tantalum, platinum, alloys comprising these elements and a polymer material loaded with particles of density greater than ten, especially tungsten particles; the blade or blades are in one of silicon, glass, sapphire, diamond, in particular synthetic diamond, in particular synthetic diamond obtained by chemical vapor deposition process, titanium, a titanium alloy, in particular an alloy of the Gum metal® family and an alloy of the family of élinvars, in particular Elinvar ®, Nivarox ®, Thermelast ®, Ni-Span-C ®, Précision C ®;

in step i), between ten and fifty plane layers are assembled together; the at least one blade has a width, a thickness and an aspect ratio defined as being equal to the ratio of the width of the blade to the thickness of the blade, the aspect ratio of each blade being greater than 10, preferably greater than 25;

the blade or blades have a thickness greater than or equal to 1 μιη, preferably greater than or equal to 5 μιη, and / or less than or equal to 30 μιη, preferably less than or equal to 20 μιη, more preferably less than or equal to 15 μιη ;

the blade or blades have a width greater than or equal to 0.1 mm and / or less than or equal to 2 mm, preferably less than or equal to 1 mm;

the substantially flat multilayer structure forms at least one mounting scaffold, the method comprising a step iv), preferably subsequent to step iii) where appropriate, of detaching the structure in the deployed position from the at least one mounting scaffolding ;

each layer is subjected, preferably before assembly, to a machining step, in particular laser cutting, chemical machining, stamping, milling, wire electroerosion and / or a shaping step , in particular at a material-forming shaping step, in particular a LIGA shaping step or by injection molding;

a plurality of substantially planar multilayer structures, respectively deployed-position structures, are obtained in step ii), respectively in step iii), from a single layer assembly in step i); and the or each blade is of a softer material than the or each mass which is fixed on said blade. According to another aspect, the invention relates to a use of the method as described above, in all its combinations, to manufacture all or part of a watch movement, in particular a watch movement regulator.

According to yet another aspect, the invention relates to a mechanism, in particular a watch movement for a timepiece, made in whole or in part by implementing a method as described above in all its combinations.

More generally, there is described in the present application a method of manufacturing a mechanism, including a flexible mechanism, comprising the steps of:

method wherein at least a first layer of said layers forms at least one flexible blade in the mechanism. The blade or blades are fixed in the mechanism to at least one mass, preferably two masses, the or each mass being more rigid than the blade or blades. The blade or blades may initially extend substantially in the initial plane of said first layer, so that the length and width of the blade or blades extend in the plane of the planar multilayer structure while the thickness of the or blades corresponds to the thickness of the first layer and extends substantially perpendicular to the plane of the plane multilayer structure. In the deployed structure, however, the blade or blades extend out of the plane of the planar multilayer structure. In particular, in the deployed structure, the blade or blades may extend substantially perpendicular to the plane of the plane multilayer structure, so that the thickness and length of the blade or blades extend in a plane parallel to the plane of the flat multilayer structure, and that the width of the blade or blades extends out of plane, in particular substantially perpendicular to the plane of the plane multilayer structure.

In this most general case, the blade or blades can be attached to the mass or masses during the layer assembly step, when the mass or masses are formed by one or more layers of the multilayer structure. There is also described a mechanism, including a flexible mechanism, obtained by implementing this method. The mechanism may in particular form all or part of a watch movement, in particular all or part of a watch movement regulator.

The additional features listed above may also be implemented in this method or mechanism.

The invention will be better understood from the description which follows, given with reference to the accompanying drawings. On these drawings:

Figures 1 to 12 schematically illustrate the different steps of an exemplary method of manufacturing a mechanism, Figure 9 illustrating more particularly a detail of Figure 8;

Figure 13 is a schematic view of a timepiece comprising a watch movement; and

FIG. 14 is a block diagram of the watch movement of the timepiece of FIG. 13.

In the remainder of the description, the elements identical or of identical function of the various layers described bear the same reference sign followed by an index relating to the number of the layer of which this element is a part. The set formed by the superposition of identical elements of different layers still bears the same reference sign, without index. For brevity of the present description, these elements identical or identical function are not described with respect to each figure.

Firstly, with reference to FIGS. 1 to 12, an example of a process for manufacturing a flexible mechanism, in particular a flexible blade mechanism (s), is described. In known manner, a flexible mechanism or link with elastic articulation, is a building element fulfilling a kinematic function using the physical principle of the elasticity of the material. In a flexible blade mechanism (s), the elasticity of one or more blades is used.

Figure 1 shows a first layer 10 of a first material. Here, the first layer 10 is in the form of a substantially rectangular plate. In order to facilitate understanding of the description which follows, a trihedron X, Y, Z is defined in which:

the direction X corresponds to the transverse direction of the layer 10; the direction Y corresponds to the longitudinal direction of the layer 10; and the direction Z corresponds to the direction normal to the layer 10, such that the X, Y, Z trihedron is a direct trihedron.

Various cuts are made in the first layer 10 in order, in particular, to create fold primers and / or break primers in the first layer 10. These cuts firstly form a cross 12 _1; in the central part of the first layer 10. The cross 12χ has four branches 14a _1; 14bi perpendicular two by two. Two branches 14a _1; said longitudinal, extending substantially in the direction Y, are longer than the other two branches 14b _1; said transverse, which extend substantially in the direction X.

Firstly, the two longitudinal branches 14a are described. Along each of these longitudinal branches 14a, cutouts form, from the center of the first layer 10 towards the edge of the first layer 10:

a first ridge 16i fluted, extending in the direction X

- A second ridge 18i grooved, extending in the direction X, the grooves of the second edge 18i being complementary to the grooves of the first edge 16 _1; and

a third edge 20 _1; fluted, at the end of the branch 14ai longitudinal considered, the third edge 201 extending in the direction X.

By complementary splines is meant grooves such that they can be received one in the other, the teeth of a groove being for example each received between two adjacent teeth of the other groove.

Opposite the third edge 201 of each longitudinal branch 14ai, the first layer 10 forms a strip 22 _\ of material, extending substantially in the direction X. The strip 22 _\ of material extends from other than the longitudinal branch 14ai of the cross 12 _1; the length of the strip 22i of material being greater than the width of the longitudinal branch 14ai of the cross 12. The strip 22i of material has a fourth edge 24 i splined, vis-à-vis the third edge 20 _1; the grooves of the third and fourth edges 20 _1; 24 _\ being complementary. The fourth edge 24i extends over substantially the entire length of the strip 22i of material. The edge of the band 22 _1; opposite to the fourth edge 241 is here rectilinear, extending in the direction X. The third grooved edge 201 extends on either side of the end of the longitudinal branch 14a, opposite the fourth edge 24. This third edge 201 then partially delimits the outline of a stirrup 26 _1; to which the strip 22 _\ of material is connected by tabs 28 _\ . The contour bracket 26 _\ is also partially delimited by the extension, in the direction X, on either side of the longitudinal branch of the cross 14ai 12 _1; of the second ridge 16 ₁ fluted. The stirrup 26i still forms a cross member 30 _1; extending substantially in the X direction, two uprights 31 _1; extending substantially in the direction Y, and two elbows 32 _1; at the end of the uprights 31 i. The elbows 32i are oriented toward each other. The cross member 30i is disposed between the two bends 2 _\ and the strip of material 22 _1; in direction Y. Elbows 32 ₁ form here a right angle. The free end 33i of the bends 32 ₁ is connected via a tongue 34 _1; at a puck 6 _\ . The puck 36i is here of substantially rectangular shape.

The stirrup 26i is connected by its uprights 31 _1; at the edge 38i of the first layer 10 _1; by means of tabs 40 _\ .

Furthermore, the first edge \ 6 _\ splined extends in direction X, on either side of the longitudinal branch of the 14ai cross 12i on which it is formed, compared with the extension of the second edge 16 delimiting ₁ Longitudinal partially the stirrup 26 _\ .

The yoke 26 _\ is finally connected to the extremal portion 120i of the longitudinal branch of the cross 14ai 12 _1; by tabs 42 ₁ . The end portion 120i of the longitudinal limb 14ai extends between the second edge 18i and the third edge 20 _\ .

Moreover, each transverse branch 14bi has a substantially equivalent configuration. The identical elements of the longitudinal 14a and transverse branches 14b ₁ bear the same reference sign.

Thus, along each of the transverse branches 14b _1; cuts form, from the center of the first layer 10 to the edge of the first layer 10:

a first edge \ 6 _\ spline extending along the Y direction, a second edge 18i spline extending in the Y direction, the grooves of the second ridge 20 _\ being complementary to the first edge 18 _{1 flutes;} and a third edge 20 _\ grooved, forming the end of the transverse branch 14bi considered, the third edge 20i extending in the direction Y.

Vis-à-vis the third edge 20 _\ of each transverse branch, the first layer 10 forms a strip 22 _\ material, extending substantially in the direction Y. The 22i material web extends on both 14b transverse branch of the cross 12 _1; the length of the strip 22 _\ of material being greater than the width of the transverse branch 14b ₁ of the cross \ 2 _\ . The strip 22 _\ material has a fourth edge 2 _\ grooved, vis-à-vis the third edge 20 _1; the grooves of the third and fourth edges 201, 24 i being complementary. The fourth edge 24 i extends over substantially the entire length of the strip 22i of material.

The third fluted ridge 20i extends on either side of the end of the transverse branch 14b ₁ , vis-à-vis the fourth edge 24 ₁ . This third edge 20i then partially delimits the outline of a square 44i of material. The outline of the square 44 _\ is also partially delimited by the extension, in the Y direction, on either side of the transverse branch 14b ₁ of the cross 12 _1; second ridge 16i fluted.

The square 44i is connected to the edge 38i of the layer 10 by tabs 46i. Furthermore, the first edge 16 ₁ splined extends along the Y direction, on either side of the transverse branch of the 14bi cross 12i on which it is formed, compared with the extension of the second ridge \ 6 _\ delimiting partially the square 44 _\ .

The square 44i is also connected to the end portion 120i of the transverse branch 14b ₁ of the cross 12 _1; by tongues 120i The extremal portion of the cross 14bi branch extends between the second edge 18i and the third edge 20 _\.

Finally, strips 22 _\ en vis-à-vis the legs 14b ₁ are directly connected to transverse edge 38i of the layer 10 by tabs 50i.

It should be noted that the distance d1 between the second edge 18i and the third edge 20i is identical on each branch 14a _1; 14bi of the cross \ 2 _\ . Furthermore, the width of the strips 22 _\ is the same, the width being measured between the fourth edge 2 _\ and the side of the strip 22 _\ opposite said fourth ridge 24 _1. The distances d1 and d2 are here substantially equal.

The first layer 10 is also provided with four holes 52 _\ distributed at the corners of the first layer 10, allowing the passage of an alignment pin of the first layer with other layers superimposed on this first layer. Two holes 54 ₁ are also made in the center of the first layer 10. The function of these two holes 54i will be described later.

The first layer 10 as just described is for example made from a monolithic layer cut and / or shaped. The cuts can be made by any method adapted to the material of the first layer. The cuts can in particular be made by laser cutting, chemical cutting, stamping. The shaping can consist of adding material, in particular by a LIGA process (from the German "Roentgenlithographie, Galvanoformung, Abformung" for X-ray lithography, electroplating and forming). The cutting and / or shaping steps are preferably carried out before the assembly of the first layer 10 with other layers in order to facilitate the production thereof. The same goes for the other layers described below.

In Figure 2, the first layer 10 is covered by a second layer 56 of flexible material. The flexible material may be a polymeric film, for example polyimide. Here, for example, the flexible material is kapton®. In practice, a layer of adhesive or a layer of adhesive material, substantially identical in shape to the first layer 10 or to the second layer 56, is interposed between the first layer 10 and the second layer 56.

It should be noted that cutouts are made in the second layer 56, so that the second layer 56 has a substantially identical shape to the first layer 10. The second layer 56 forms for example a cross 12 ₂ of identical shape to the cross 12 of the first layer 10. However, the cross 12 ₂ , on the second layer 56, is full, with the exception, here, of the two holes 54 ₂ . In particular, the cross 12 ₂ on the second layer 56 is devoid of fluted ridges. More generally, the second layer 56 as a whole is devoid of fluted ridges.

Furthermore, the branches 14a ₂ , 14b ₂ of the cross 12 ₂ are not connected to the edge 38 ₂ of the second layer 56 by tabs extending in the direction X. On the contrary, the branches 14a ₂ , 14b ₂ are here connected to the edge 38 ₂ of the second layer only by their ends. In other words, the cross 12 ₂ on the second layer 56 is devoid of tabs connecting it to the edge 38 ₂ of the second layer 56. In FIG. 3, the second layer 56 is covered by a third layer 58. In practice, again, a layer of adhesive or adhesive material is interposed between the second layer 56 and the third layer 58, the layer of adhesive being example of shape identical to the third layer 58.

The third layer 58 is here of identical shape to the first layer 10.

Thus, in FIG. 3, the second layer 56 appears between the grooves of the grooved edges facing each other.

In FIG. 4, the third layer 58 is covered by a fourth layer 60. Here again, in practice, a layer of adhesive or adhesive material is interposed between the third layer 58 and the fourth layer 60. This layer of adhesive or adhesive material is substantially identical in shape to the third layer 58.

The fourth layer 60 is substantially identical in shape to the third layer 58.

The fourth layer 60 differs from the first 10 and third 58 layers essentially in that the free ends 33 ₄ of the bends 32 ₄ are connected, each via a tongue 34 ₄ respectively, to the same blade 62.

The fourth layer 60 is preferably made of a material different from the materials constituting the first and third layers 10, 58, which may, if necessary, be of the same material. In particular, the fourth layer 60 may be of a softer material than the first and third layers 10, 58. Alternatively or in addition, the fourth layer 60 may be thinner than the first and third layers 10, 58, especially in the case where all these layers are in the same material.

In the example, the fourth layer 60 is then covered with a fifth layer 64 as illustrated in FIG.

This fifth layer 64 is also attached to the fourth layer 60, for example by gluing. To do this, a layer of adhesive or adhesive material, for example of similar shape to the fifth layer 64 is interposed between the fourth 60 and fifth 64 layers.

The fifth layer 64 is of identical shape to the first and third layers 10, 58. This fifth layer 64 is for example of a material that can be brazed or welded, unlike the fourth layer 60. This fifth layer 64 does not form a blade superimposed on the blade 62 formed by the fourth layer 60. This gives a substantially flat multilayer structure 68, visible in particular in FIG.

Finally, in the exemplary method described with reference to the figures, a base 66 is disposed on the fifth layer 64, as shown in Figure 6. This base 66 is positioned relative to the multilayer structure 68 flat, including the using holes 54 which can receive guide pins. Then the base 66 receives a support 90 of two beams 92, connected to the support 90 by means of tabs 94 breakable. Again, the correct positioning of the support 90 and, therefore, the beams 92 relative to the multilayer structure 68 is obtained through holes 54 and guiding pins received therein. It should be noted here that the support 90, the beams 92 and the tabs 94 can be made in one piece. In particular, the support 90, the beams 92 and the tabs 94 can be obtained by implementing the same methods as those described above for the production of the various layers described above. It should also be noted that in the example described the support 90 is placed on the base 66, without being fixed thereto.

The method of manufacturing a mechanism then continues with a step of cutting tabs 28, 40, 42, 46, 48, 50. This step results in the multilayer structure 68, substantially flat, of Figure 7 in which, in particular :

the stirrups 26 are detached from the edge 38 of the superposed layers 10, 56, 58, 60, 64;

the strips 22 are detached from the stirrups 26; and

the squares 44 are detached from the edge 38 of the superposed layers 10, 56, 58, 60, 64 and the end portions 120 of the transverse branches 14b of the cross 12.

The manufacturing process then continues with a step of deployment along a Z axis substantially normal to the plane of the multilayer structure 68, this step being illustrated in FIGS. 8 to 10. In other words, the multilayer structure 68 of FIG. 7 is deployed to extend in the direction Z normal to the plane of the multilayer structure 68, flat. Thus, a three-dimensional deployed structure 88 is obtained.

FIG. 8 illustrates an intermediate state of the multilayer structure 68, before reaching its final state, deployed, illustrated in FIG. 10. Here, because of the traction in the Z direction, and as shown in FIG. 8, articulations - that is to say, connections essentially allowing a rotation - are formed at the fluted edges with respect to the Z direction. screw.

FIG. 9 illustrates, by way of example, the formation of a hinge 72 at the level of the third and fourth edges 20, 24 of a longitudinal branch 14a of the cross 12 and the strip 22 of material facing the screw. In this Figure 9, the grooves of the third and fourth edges 20, 24 of the third, fourth and fifth layers 58, 60, 64 come together, the teeth of a groove being received between two adjacent teeth of the other groove. On the contrary, the third and fourth edges 20, 24 of the first layer 10 move away. Under these conditions, the second layer 56, devoid of grooved edges, remains in one piece and extends, continuously, between the base of the longitudinal branch 14a (right in FIG. 9) and the extremal portion 120 of the branch 14a longitudinal (left in Figure 9). The second layer 56 then forms a hinge 72.

The grooved ridges previously mentioned thus form, in cooperation with the second layer 56, the following joints:

a first articulation 70 of X axis between the base of each longitudinal branch 14a and the corresponding end portion;

a second articulation 72 of X axis between the end portion 120 of each longitudinal branch 14a and the band 22 vis-à-vis;

two third joints 74 of X axis between each strip 22 of material vis-à-vis a longitudinal branch 14a and the stirrup 26 associated;

two fourth joints 76 of axis X between each stirrup 26 and the edge 38 of the different layers;

a fifth link 78 of Y axis between the base of each transverse branch 14b and the corresponding end portion;

a sixth articulation 80 of Y axis between the end portion of each transverse branch 14b and the band 22 vis-à-vis;

two seventh joints 82 of Y axis between each strip 22 of material vis-à-vis a transverse branch 14b and the two squares 44 associated;

an eighth articulation 84 of Y axis between each square 44 and the edge 38 of the different layers. Thus, by choosing perpendicular orientations of the joints, here is formed a mounting Sarrus 86 (English "Sarrus linkage"). This mounting Sarrus is a particular example of scaffolding mounting (English "mounting scaffold") that can be implemented in the process.

Such a mounting scaffold is made by the multilayer structure, in addition to the structure of interest that is sought to achieve. This mounting scaffolding makes it possible to connect the different movements required for the deployment of the multilayer structure, so that this deployment can be achieved by acting on the multilayer structure in a single degree of freedom. This mounting scaffold facilitates the deployment step.

The mounting Sarrus 86 thus produced allows, by pulling on a portion of the multilayer structure 68 in the direction Z, to cause a rectification of the stirrups 26. The upright of the stirrups 26 is accompanied by a rapprochement of the blades 62 of the support 66. The straightening of the stirrups 26 also causes the blades 62 to pivot, so that their width extends in a direction normal to the plane of the multilayer structure 68, the length and the thickness of the blades extending substantially in a direction. plane parallel to the plane of the multilayer structure 68, flat. Thus, from a blade initially adapted to oscillate in a plane normal to the plane of the multilayer structure 68, a blade adapted to oscillate in a plane parallel to the plane of the multilayer structure 68 is obtained.

This produces a deployed multilayer structure 88, as shown in Figure 10. It should be noted here that the structure is not a priori blocked in this deployed position. A step of blocking the multilayer structure in its deployed configuration 88 can be implemented. This step can be done in many ways. For example, here, we can block some or all of the joints mentioned above by soldering or gluing.

In addition, at this stage or after this blocking step, the pallets 36 fixed to the ends of the blades 62 can be fixed to masses 92, here made in the form of beams. This can in particular be achieved by soldering. In this case, a metal plate can be glued to each end of the masses 92, thus allowing the fixing by brazing. FIG. 11 illustrates the detachment of the assembly formed by the masses 92 secured to the blades 62 via the pallets 36, from the remainder of the deployed multilayer structure 88. This is achieved by cutting the tabs 34 connecting the pallets 36 and the blade 62 to the stirrups 26, as well as tabs 94 connecting the masses 92 to the support 90.

Finally, Figure 12 illustrates the flexible mechanism 100 finally obtained. This flexible mechanism essentially comprises the two masses 92, the two flexible blades 62 connecting the masses 92, and the pallets 36 connecting the ends of the blades 62 to the masses 92.

In the illustrated example, the blades 62 are more flexible than the masses 92 and the pallets 36. In particular the blades 62 are made of a more flexible material than the masses 92 and, possibly, the pallets 36. The flexible mechanism 100 can thus form an oscillator.

It should be noted here that the blades 62 are oriented such that they allow the flexible mechanism 100 to oscillate in a plane extending substantially in the directions X and Y. In contrast, in the multilayer structure 68, the Blades 62 were oriented so that they tended to oscillate in a plane normal to this plane.

The blades 62 are for example one of silicon, glass, sapphire or alumina, diamond, especially synthetic diamond, in particular synthetic diamond obtained by chemical vapor deposition process, titanium, an alloy titanium, including an alloy from the Gum metal ® family and an alloy from the family of élinvars, in particular Elinvar ®, Nivarox ®, Thermelast ®, NI - Span - C ® and Précision C ®.

These materials have the advantage that their Young's modulus is very insensitive to temperature variations. This is particularly advantageous in the watchmaking field, for example, where the mechanism, in particular the regulator, must keep its precision, even in the event of temperature variations.

Gum metal® are materials comprising: 23% niobium; 0.7% tantalum; 2% zirconium; 1% oxygen; optionally vanadium; and optionally hafnium. Élinvars alloys are nickel-steel alloys comprising nickel and chromium which are very insensitive to temperature. Elinvar ®, in particular, is a nickel steel alloy comprising 59% iron, 36% nickel and 5% chromium. NI-Span-C ® comprises between 41.0 and 43.5% nickel and cobalt; between 4.9 and 5.75% chromium; between 2.20 and 2.75% titanium; between 0.30 and 0.80% aluminum; not more than 0,06% of carbon; not more than 0.80% manganese; not more than 1% silicon; not more than 0.04% sulfur; not more than 0,04% of phosphorus; and the 100% iron supplement.

Precision C ® includes: 42% nickel; 5.3% chromium; 2.4% titanium; 0.55% aluminum; 0.50% silicon; 0.40% manganese; 0.02% carbon; and the 100% iron supplement.

Nivarox ® comprises: between 30 and 40% nickel; between 0.7 and 1.0% beryllium; between 6 and 9% molybdenum and / or 8% chromium; optionally 1% titanium; between 0.7 and 0.8% manganese; between 0.1 and 0.2% silicon; carbon, up to 0.2%; and the iron supplement.

Thermelast ® comprises: 42.5% nickel; less than 1% silicon; 5.3% chromium; less than 1% aluminum; less than 1% manganese; 2.5% titanium; and 48% iron.

All the above compositions are indicated in percentages by weight. The blade or blades advantageously have a thickness greater than or equal to

1 μιη, preferably greater than or equal to 5 μιη, and / or less than or equal to 30 μιη, preferably less than or equal to 20 μιη, preferably less than or equal to 15 μιη.

The blade or blades may still have a width greater than or equal to 0.1 mm and / or less than or equal to 2 mm, preferably less than or equal to 1 mm.

The blade or blades may also have a length of, for example, between 5 and 13 mm.

The or each blade 62 may also have an aspect ratio defined as the ratio between the width and the thickness of the blade, greater than 10, preferably greater than 25.

The masses 92 are, for example, one of tungsten, molybdenum, gold, silver, tantalum, platinum, alloys comprising these elements and a polymer material containing particles with a density greater than ten, in particular particles of tungsten. These materials are indeed heavy. In the case of an oscillator mechanism 100, this makes it possible to have masses 92 of small dimensions but with a relatively large weight.

The pallets 36, and therefore the first, third and fifth layers 10, 58, 64 are for example of polymeric materials. These pallets 36 can improve the resistance of the mechanism 100 to shocks.

As indicated above, the mechanism 100 may advantageously form an oscillator. In this case, one of the masses 92 may form a frame or be fixed rigidly to a frame, relative to which the other mass 92 oscillates. In this case, in this case, one of the masses 92 oscillates in a circular translation movement T relative to the other mass 92. In such a case, a high aspect ratio of the or each blade 62 allows in particular to limit the oscillation modes of this or these blades 62 out of plane.

Advantageously, the or each blade 62 has a free length L greater than or equal to one third of the width of the blade 62. In the case where the blade is fixed to a single mass, the free length is defined as being the length of the blade who is not in contact with the mass. In the case where the blade is attached to two masses, the free length refers to the length of the blade between the two masses, which is not in contact with one or the other of the masses. Preferably, over the free length of the blade 62, the latter is not in contact with any other element of the mechanism incorporating the blade or blades 62.

A flexible mechanism of the type of that of Figure 12, that is to say of the type comprising at least one flexible blade between at least one, preferably between two masses, obtained by implementing the method described above, can in particular be implemented in a watch movement in a timepiece, especially as a regulator of such a watch movement.

In known manner, a timepiece 200 such as a watch illustrated in FIG. 13 essentially comprises:

a housing 202,

a watch movement 203 contained in the casing 202,

generally, a winding 204,

a dial 205, a glass 206 covering the dial 205,

a time indicator 207, comprising for example two needles 207a, 207b respectively for hours and minutes, disposed between the glass 206 and the dial 205 and actuated by the watch movement 203.

As schematically represented in FIG. 14, the watch movement

203 can include for example:

a device 208 for storing mechanical energy, generally a mainspring,

a mechanical transmission 209 driven by the mechanical energy storage device 208,

the time indicator 207 mentioned above,

a power distribution member 210 (for example an escape wheel),

an anchor 211 adapted to sequentially retain and release the power distribution member 210,

a regulator 212, which is a mechanism comprising an oscillating regulating member controlling the anchor 211 to move it regularly so that the energy delivery member is moved step by step at constant time intervals, and possibly

a decoupling member 213, which is interposed between the regulator 212 and the anchor 211.

The invention is not limited to the single embodiment described above with reference to the figures, but is, on the contrary, capable of many variants accessible to those skilled in the art.

Firstly, in the example of the method described, the masses are fixed on the blades, more precisely at the ends of the blades, after the deployment of the multilayer structure. In the example described, this fixing is performed using a solder. Alternatively, however, the masses are fixed to the blade or blades, in particular at the ends of these blades, by overmoulding, clamping, clipping, gluing, welding, especially spot welding, in particular spot welding by laser, or any other method. accessible to those skilled in the art. The masses can be reported on the deployed multilayer structure in the form of a blank in a layer of additional material that is superimposed on the deployed multilayer structure. The cutting in the layer of additional material may in particular form receiving housings of the ends of the flexible blades, in particular pallets fixed to the ends of the blades, the reception then being preferably carried out with clamping.

Also, according to one variant, the masses can be formed by the multilayer structure. The masses are then arranged vis-à-vis the ends of the blades or pallets attached to these ends at the time of deployment of the multilayer structure.

Furthermore, in the described method example, it comprises a step of locking the structure in the deployed position. This step is a priori optional. It is, however, preferred when further manipulations of the deployed structure are desired to result in the mechanism. In the case where such a blocking is to be achieved, it can be obtained by any means accessible to those skilled in the art, in particular by gluing, overmolding, brazing, clipping, welding, including spot welding, in particular welding by laser point or, more generally, by fastening together elements of the structure in the deployed position.

In addition, the method of manufacturing a mechanism may include a step of assembling many layers on each other. Preferably, however, the number of superimposed layers of material is between ten and fifty.

Finally, in the example described, a single mechanism 100 is obtained by implementing the method. However, advantageously, it can be provided that a same stack of layers allows the formation of a plurality of multilayer structures and / or a plurality of deployed structures. It is thus possible to substantially improve the efficiency of the method of manufacturing a mechanism.

Finally, the fluted ridges mentioned in the example described can be replaced by folding primers. In particular, the bending primers can be made by partial cuts of the layers. The partial cuts may consist of dotted cuts and / or a cut on only a part of the thickness of the layers. In the case of a cut on only part of the thickness of the layers, the partial cut may possibly be continuous. A total cut of the layers can also be envisaged.

Claims

A method of manufacturing a mechanism (100), including a flexible mechanism, comprising the steps of:

i) assembling flat layers (10; 56; 58; 60; 64) together to form a substantially flat multilayer structure (68); ii) deploying the multilayer structure in a substantially normal direction (Z) to the planar layers (10; 56; 58; 60; 64);

a method wherein at least a first layer (60) of said layers (10; 56; 58; 60; 64) forms at least one flexible blade (62) in the mechanism (100) with the blade (s) (62) attached thereto, in the mechanism (100), at least one mass (92), preferably two masses (92), the or each mass (92) being more rigid than the blade (s) (62), the blade (s) (62) ) being attached to the or each mass (92) at a step subsequent to step ii).

2. The method of claim 1, wherein each blade (62) has in the mechanism (100), a free length (L) greater than one third of the width of the blade (62), the free length (L) being defined as:

the length of the blade (62) which is not in contact with the mass (92), in the case where the blade (62) is attached to a mass (92), or

the length of the blade (62) extending between the two masses (92), without being in contact with one of the masses (92), in the case where the blade (62) is attached to two masses (92); )

the or each blade (62) being preferably, on the free length (L), in contact with no other element of the mechanism (100).

3. The method of claim 1 or 2, comprising a step iii) subsequent to step ii), of blocking the multilayer structure in the deployed position (88).

4. The method of claim 3, wherein in step iii), the structure is locked in the deployed position (88) by implementing at least one of overmoulding, brazing, clipping, gluing, welding, especially welding by point, in particular laser spot welding, and clamping, at least a part of the mechanism, in particular at least one articulation of the mechanism.

5. A method according to any one of the preceding claims, wherein the or each mass (92) is attached to an end, preferably at a respective end, of one of said at least one blade (62).

The method of any one of the preceding claims, wherein the or each mass (92) is attached to the blade (92) or to each blade (62) by:

- overmoulding;

brazing;

age clip;

collage;

welding, especially spot welding, in particular spot welding;

Tightening.

7. A method according to any one of the preceding claims, wherein the one or more masses (92) are formed by at least one of the plane layers (10; 56; 58; 60; 64) assembled in step i).

A method according to any one of the preceding claims wherein the one or more masses (92) are one of tungsten, molybdenum, gold, silver, tantalum, platinum, alloys comprising these elements and a polymer material loaded with particles with a density greater than ten, in particular tungsten particles.

9. Method according to any one of the preceding claims, wherein the blade or blades (62) are in one of silicon, glass, sapphire, diamond, including synthetic diamond, in particular the synthetic diamond obtained by chemical vapor deposition process, titanium, a titanium alloy, in particular an alloy of the Gum metal® family and an alloy of the family of élinvars, in particular Γ Elinvar ®, Nivarox ®, Thermelast ®, Ni-Span-C ®, Precision C ®.

The method of any one of the preceding claims, wherein in step i), ten to fifty planar layers (10; 56; 58; 60; 64) are assembled together.

The method of any one of the preceding claims, wherein the at least one blade (62) has a width, a thickness, and an aspect ratio defined as being equal to the ratio of the width of the blade (62) to the blade. the thickness of the blade (62), the aspect ratio of each blade being greater than 10, preferably greater than 25.

12. Method according to any one of the preceding claims, wherein the blade or blades (62) have a thickness greater than or equal to 1 μιη, preferably greater than 5 μιη, and / or less than or equal to 30 μιη, preferably less than or equal to 20 μιη, more preferably less than or equal to 15 μιη.

13. A method according to any one of the preceding claims, wherein the blade or blades (62) have a width greater than or equal to 0.1 mm and / or less than or equal to 2 mm, preferably less than or equal to 1 mm. .

The method of any of the preceding claims, wherein the substantially planar multilayer structure (68) forms at least one mounting scaffold (86), the method comprising a step iv), preferably subsequent to step iii) the if appropriate, detaching the structure in the deployed position (88) from the at least one mounting scaffold (86).

15. Method according to any one of the preceding claims, wherein each layer (10; 56; 58; 60; 64) is subjected, preferably before assembly, to a machining step, in particular laser cutting, of chemical milling, stamping, milling, wire EDM and / or a shaping step, particularly at a step of shaping by adding material, in particular a shaping step by LIGA or by injection molding.

The method of any of the preceding claims, wherein a plurality of substantially plane multilayer structures (68), respectively of expanded-position structures (88), are obtained in step ii), respectively in step iii. ), from a single layer assembly in step i).

The method of any of the preceding claims, wherein the or each blade (62) is of a softer material than the or each mass (92) which is attached to said blade (62).

18. Use of a method according to any preceding claim for manufacturing all or part of a watch movement (203), including a controller (212) for watch movement (203).

19. Mechanism, in particular watch movement (203) for a timepiece (200), made in whole or in part by implementing a method according to any one of claims 1 to 17.