EP3615470B1 - Method for manufacturing a timepiece oscillator - Google Patents

Description

The present invention relates to a method of manufacturing a watch oscillator, to a watch oscillator obtained in whole or in part by implementing this method and to a watch movement comprising such a watch oscillator.

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

Requirement 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 engraving the silicon wafer. Such a monolithic regulator thus has a limited number of moving parts relative to each other. We thus limit the number of friction zones, which are located at the level of the parts in contact, which are moving relative to each other.

However, producing a watch movement regulator from a single slab of material poses certain difficulties.

First of all, it is generally necessary to use a shaping step, for example an etching step, which must be carried out in a clean room. This leads to an additional cost of producing 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 produce a flexible blade of any orientation, having an aspect ratio greater than approximately 25, at this scale. Remember that the aspect ratio of a flexible blade is defined by the ratio of its width to its thickness. We also remember that the length of a blade is the dimension following the direction passing through the anchor points of the blade. The length 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, greater than its thickness, but smaller than its length. It should be noted, however, that the width of a blade can, in certain particular cases, be approximately equal to its length.

However, such a flexible blade, or “flexure”, is notably used in a watch movement to create a regulator. A regulator is an oscillating device. A flexible blade, with the largest possible aspect ratio, is preferred in this case, in particular when the width of the blade extends along a plane substantially perpendicular to the base plane of the oscillator. In this case, in fact, a large aspect ratio makes it possible to limit the oscillations of the blade outside the base plane of the oscillator.

Furthermore, at constant width, increasing 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.

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

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

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

In the case of this type of process, it is known to use rigid layers to produce 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 deployment of the three-dimensional structure, in particular by gluing or laser welding.

In the case of this request WO-A-2012/109559 , the parts fixed to a flexible layer, are fixed during the stage of superposition and assembly of the flat layers. This in fact allows the easy creation of an articulation between the parts fixed to the flexible layer. Furthermore, in the final three-dimensional structure, the flexible layer extends over a very short distance between the rigid parts that it connects, the flexible layer mainly forming an angle between the rigid parts.

Thus, the process described in this application WO-A-2012/109559 is limited in the variety of structures it can create.

Furthermore, the demand US-A-2016/0184041 describes a method of manufacturing a voice coil actuator comprising a first step of assembling planar layers together to form a substantially planar multilayer structure. Then, the multilayer structure is deployed. A coil retaining mechanism is thus formed. An outer magnetic core, a permanent magnet, a magnetic coil and an inner magnetic core can then be attached to the coil retaining mechanism.

An aim of the invention is to propose a method of manufacturing a watch oscillator.

1. i) assembler des couches planes ensemble pour former une structure multicouche sensiblement plane ;
2. ii) déployer la structure multicouche selon une direction sensiblement normale aux couches planes ;

procédé dans lequel au moins une première couche desdites couches forme au moins une lame flexible dans l'oscillateur horloger, la ou les lames étant fixées, dans l'oscillateur horloger, à au moins une masse, de préférence à deux masses, la ou chaque masse étant plus rigide que la ou les lames, la ou les lames étant fixées à la ou à chaque masse à une étape postérieure à l'étape ii).To this end, the invention proposes a method of manufacturing a watch oscillator, comprising the steps consisting of:

1. i) assembling planar layers together to form a substantially planar multilayer structure;
2. ii) deploy the multilayer structure in a direction substantially normal to the planar layers;

method in which at least a first layer of said layers forms at least one flexible blade in the watch oscillator, the blade or blades being fixed, in the watch oscillator, to at least one mass, preferably to two masses, the or each mass being more rigid than the blade(s), the blade(s) being fixed to the(er) mass at a step subsequent to step ii).

Thus, advantageously, the method according to the invention makes it possible to produce a watch oscillator having at least one flexible blade fixed to one or more rigid masses. Such a process can advantageously be applied in the field of 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 µm, and substantially constant, giving access at lower oscillation frequencies of the regulator than those generally obtained in the case of a monolithic regulator, produced by implementing 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 higher than that traditionally obtained in the case of a monolithic regulator, produced by implementing the methods conventionally implemented at this scale, that is to say at the centimeter scale.

• chaque lame présente, dans l'oscillateur horloger, une longueur libre supérieure au tiers de la largeur de la lame considérée, la longueur libre étant définie comme étant :
  • o la longueur de la lame qui n'est pas en contact avec la masse, dans le cas où la lame est fixée à une masse, ou
  • o la longueur de la lame qui s'étend entre les deux masses, sans être en contact avec l'une des masses, dans le cas où la lame est fixée à deux masses,
  la ou chaque lame n'étant de préférence, sur la longueur libre, en contact avec aucun autre élément de l'oscillateur horloger ;
• le procédé comprend une étape iii) postérieure à l'étape ii), consistant à bloquer la structure multicouche en position déployée ;
• l'étape iii), la structure est bloquée en position déployée en mettant en oeuvre l'un au moins parmi un surmoulage, un brasage, un clipsage, un collage, un soudage, notamment un soudage par point, en particulier un soudage par point au laser, et un serrage, d'au moins une partie de l'oscillateur horloger, notamment d'au moins une articulation de l'oscillateur horloger ;
• la ou chaque masse est rapportée à une extrémité, de préférence à une extrémité respective, d'une desdites au moins une lame ;
• la ou chaque masse est fixée à la lame ou à chaque lame par : surmoulage ; brasage ; clipsage ; collage ; soudage, notamment soudage par point, en particulier soudage par point au laser ; serrage ;
• la ou les masses sont réalisées par au moins une des couches planes assemblées à l'étape i) ;
• la ou les masses sont en l'un parmi le tungstène, le molybdène, l'or, l'argent, le tantale, le platine, les alliages comprenant ces éléments et un matériau polymère chargé de particules de densité supérieure à dix, notamment de particules en tungstène ;
• la ou les lames sont en l'un parmi le silicium, le verre, le saphir, le diamant, notamment le diamant synthétique, en particulier le diamant synthétique obtenu par procédé de déposition chimique en phase vapeur, le titane, un alliage de titane, notamment un alliage de la famille des Gum métal^® et un alliage de la famille des élinvars, en particulier l'Elinvar ^®, le Nivarox ^®, le Thermelast ^®, le Ni-Span-C ^®, le Précision C ^® ;
• à l'étape i), on assemble entre dix et cinquante couches planes ensemble ;
• la ou les lames ont une largeur, une épaisseur et un rapport d'aspect défini comme étant égal au rapport de la largeur de la lame sur l'épaisseur de la lame, le rapport d'aspect de chaque lame étant supérieur à 10, de préférence supérieur à 25 ;
• la ou les lames ont une épaisseur supérieure ou égale à 1 µm, de préférence supérieure ou égale à 5 µm, et/ou inférieure ou égale 30 µm, de préférence inférieure ou égale à 20 µm, de préférence encore inférieure ou égale à 15 µm ;
• la ou les lames ont une largeur supérieure ou égale à 0,1 mm et/ou inférieure ou égale à 2 mm, de préférence inférieure ou égale à 1 mm ;
• la structure multicouche sensiblement plane forme au moins un échafaudage de montage, le procédé comprenant une étape iv), de préférence postérieure à l'étape iii) le cas échéant, consistant à détacher la structure en position déployée, du au moins un échafaudage de montage ;
• chaque couche est soumise, de préférence avant son assemblage, à une étape d'usinage, notamment de découpe laser, d'usinage chimique, d'étampage, de fraisage, d'électroérosion à fil et/ou à une étape de mise en forme, notamment à une étape de mise en forme par ajout de matière, en particulier une étape de mise en forme par LIGA ou par moulage par injection ;
• une pluralité de structures multicouches sensiblement planes, respectivement de structures en positon déployée, sont obtenues à l'étape ii), respectivement à l'étape iii), à partir d'un unique assemblage de couches à l'étape i) ; et
• la ou chaque lame est en un matériau plus souple que la ou chaque masse qui est fixée sur ladite lame.

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 watch oscillator, a free length greater than a third of the width of the blade considered, the free length being defined as being:
  • o the length of the blade which is not in contact with the mass, in the case where the blade is fixed 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, over the free length, in contact with any other element of the watch oscillator;
• the method comprises a step iii) subsequent to step ii), consisting 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 overmolding, brazing, clipping, gluing, welding, in particular spot welding, in particular spot welding by laser, and tightening, of at least a part of the watch oscillator, in particular of at least one articulation of the watch oscillator;
• the or each mass is attached to one end, preferably to 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, in particular spot welding, in particular laser spot welding; Tightening ;
• the mass(es) are produced by at least one of the flat layers assembled in step i);
• the mass(es) are one of tungsten, molybdenum, gold, silver, tantalum, platinum, alloys comprising these elements and a material polymer loaded with particles with a density greater than ten, in particular tungsten particles;
• the blade(s) are 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 from the Gum metal ^® family and an alloy from the elinvar family, in particular Elinvar ^® , Nivarox ^® , Thermelast ^® , Ni-Span-C ^® , Précision C ^® ;
• in step i), between ten and fifty flat layers are assembled together;
• the blade(s) have 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, of preferably greater than 25;
• the blade(s) have a thickness greater than or equal to 1 µm, preferably greater than or equal to 5 µm, and/or less than or equal to 30 µm, preferably less than or equal to 20 µm, more preferably less than or equal to 15 µm ;
• the blade(s) 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 planar multilayer structure forms at least one mounting scaffold, the method comprising a step iv), preferably subsequent to step iii) where appropriate, consisting of detaching the structure in the deployed position from the at least one mounting scaffold ;
• each layer is subjected, preferably before assembly, to a machining step, in particular laser cutting, chemical machining, stamping, milling, wire EDM and/or a shaping step , in particular at a shaping step by adding material, in particular a shaping step by LIGA or by injection molding;
• a plurality of substantially planar multilayer structures, respectively structures in deployed position, are obtained in step ii), respectively in step iii), from a single assembly of layers in step i); And
• the or each blade is made of a more flexible material than the or each mass which is fixed on said blade.

According to another aspect, the invention relates to a watch oscillator produced in whole or in part by implementing a method as described above, in all its combinations.

According to yet another aspect, the invention relates to a watch movement for a timepiece comprising a watch oscillator as described above, in all its combinations.

• les figures 1 à 12 illustrent schématiquement les différentes d'étapes d'un exemple de procédé de fabrication d'un mécanisme, la figure 9 illustrant plus particulièrement un détail de la figure 8 ;
• la figure 13 est une vue schématique d'une pièce d'horlogerie comprenant un mouvement horloger ; et
• la figure 14 est un schéma bloc du mouvement horloger de la pièce d'horlogerie de la figure 13.

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

• THE figures 1 to 12 schematically illustrate the different stages of an example of a mechanism manufacturing process, the Figure 9 illustrating more particularly a detail of the figure 8 ;
• there Figure 13 is a schematic view of a timepiece comprising a watch movement; And
• there Figure 14 is a block diagram of the watch movement of the timepiece of the Figure 13 .

In the remainder of the description, identical elements or elements with identical function of the different 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 whole formed by the superposition of identical elements from different layers still bears the same reference sign, without an index. For the sake of conciseness of this description, these identical elements or identical functions are not described with regard to each figure.

We first describe with regard to the figures 1 to 12 an example of a method of manufacturing a flexible mechanism, in particular a mechanism with flexible blade(s). In known manner, a flexible mechanism or elastic joint connection is a construction element fulfilling a kinematic function using the physical principle of the elasticity of matter. In a mechanism with flexible blade(s), the elasticity of one or more blades is used.

• la direction X correspond à la direction transversale de la couche 10 ;
• la direction Y correspond à la direction longitudinale de la couche 10 ; et
• la direction Z correspond à la direction normale à la couche 10, telle que le trièdre X, Y, Z soit un trièdre direct.

There figure 1 represents a first layer 10 made 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 following description, we define a trihedron X, Y, Z, in which:

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

Different cuts are made in the first layer 10 in order, in particular, to create the beginnings of folding and/or the beginnings of rupture in the first layer 10. These cuts first of all form a cross 12 ₁ , in the central part of the first layer 10. The cross 12 ₁ comprises four branches 14a ₁ , 14b ₁ perpendicular in pairs. Two branches 14a ₁ , called longitudinal, extending substantially in the direction Y, are longer than the two other branches 14b ₁ , called transverse, which extend substantially in the direction X.

• une première arête 16₁ cannelée, s'étendant selon la direction X
• une deuxième arête 18₁ cannelée, s'étendant selon la direction X, les cannelures de la deuxième arête 18₁ étant complémentaires des cannelures de la première arête 16₁, et
• une troisième arête 20₁, cannelée, à l'extrémité de la branche 14a₁ longitudinale considérée, la troisième arête 20₁ s'étendant selon la direction X.

We first describe the two longitudinal branches 14a ₁ . Along each of these longitudinal branches 14a ₁ , cutouts form, from the center of the first layer 10 towards the edge of the first layer 10:

• a first grooved edge 16 ₁ , extending in direction X
• a second grooved edge 18 ₁ , extending in direction X, the grooves of the second edge 18 ₁ being complementary to the grooves of the first edge 16 ₁ , and
• a third edge 20 ₁ , grooved, at the end of the longitudinal branch 14a ₁ considered, the third edge 20 ₁ extending in direction X.

By complementary splines we mean splines such that they can be received one inside the other, the teeth of one spline being for example each received between two neighboring teeth of the other spline.

Facing the third edge 20 ₁ of each longitudinal branch 14a ₁ , the first layer 10 forms a strip 22 ₁ of material, extending substantially in the direction X. The strip 22 ₁ of material extends from on either side of the longitudinal branch 14a ₁ of the cross 12 ₁ , the length of the strip 22 ₁ of material being greater than the width of the longitudinal branch 14a ₁ of the cross 12 ₁ . The strip 22 ₁ of material has a fourth grooved edge 24 ₁ , facing the third edge 20 ₁ , the grooves of the third and fourth edges 20 ₁ , 24 ₁ being complementary. The fourth edge 24 ₁ extends over substantially the entire length of the strip 22 ₁ of material. The edge of the strip 22 ₁ , opposite the fourth edge 24 _1, is here rectilinear, extending in the direction X.

The third grooved edge 20 ₁ extends on either side of the end of the longitudinal branch 14a ₁ , facing the fourth edge 24 ₁ . This third edge 20 ₁ then partially delimits the contour of a stirrup 26 ₁ , to which the strip 22 ₁ of material is connected by tongues 28 ₁ . The contour of the stirrup 26 ₁ is also partially delimited by the extension, in the direction X, on either side of the longitudinal branch 14a ₁ of the cross 12 ₁ , of the second grooved edge 16 ₁ . The stirrup 26 ₁ further forms a crosspiece 30 ₁ , extending substantially in direction X, two uprights 31 ₁ , extending substantially in direction Y, and two elbows 32 ₁ , at the end of the uprights 31 ₁ . The elbows 32 ₁ are oriented towards each other. The crosspiece 30 ₁ is arranged between the two bends 32 ₁ and the strip of material 22 ₁ , in the direction Y. The bends 32 ₁ here form a right angle. The free end 33 ₁ of the elbows 32 ₁ is connected, via a tongue 34 ₁ , to a puck 36 ₁ . The puck 36 ₁ is here of substantially rectangular shape.

The stirrup 26 ₁ is connected by its uprights 31 ₁ , to the edge 38 ₁ of the first layer 10 ₁ , by means of tongues 40 ₁ .

Furthermore, the first grooved edge 16 ₁ extends in the direction X, on either side of the longitudinal branch 14a ₁ of the cross 12 ₁ on which it is made, facing the extension of the second longitudinal edge 16 ₁ partially delimiting the stirrup 26 ₁ .

The stirrup 26 ₁ is finally connected to the extremal portion 120 ₁ of the longitudinal branch 14a ₁ of the cross 12 ₁ , by tongues 42 ₁ . The end portion 120 ₁ of the longitudinal branch 14a ₁ extends between the second edge 18 ₁ and the third edge 20 ₁ .

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

• une première arête 16₁ cannelée, s'étendant selon la direction Y,
• une deuxième arête 18₁ cannelée, s'étendant selon la direction Y, les cannelures de la deuxième arête 20₁ étant complémentaires des cannelures de la première arête 18₁, et
• une troisième arête 20₁ cannelée, formant l'extrémité de la branche 14b₁ transversale considérée, la troisième arête 20₁ s'étendant selon la direction Y.

Thus, along each of the transverse branches 14b ₁ , cutouts form, from the center of the first layer 10 towards the edge of the first layer 10:

• a first grooved edge 16 ₁ , extending in direction Y,
• a second grooved edge 18 ₁ , extending in the direction Y, the grooves of the second edge 20 ₁ being complementary to the grooves of the first edge 18 ₁ , and
• a third grooved edge 20 ₁ , forming the end of the transverse branch 14b ₁ considered, the third edge 20 ₁ extending in the Y direction.

Facing the third edge 20 ₁ of each transverse branch, the first layer 10 forms a strip 22 ₁ of material, extending substantially in the direction Y. The strip 22 ₁ of material extends on both sides other side of the transverse branch 14b ₁ of the cross 12 ₁ , the length of the strip 22 ₁ of material being greater than the width of the transverse branch 14b ₁ of the cross 12 ₁ . The strip 22 ₁ of material has a fourth grooved edge 24 ₁ , facing the third edge 20 ₁ , the grooves of the third and fourth edges 20 ₁ , 24 ₁ being complementary. The fourth edge 24 ₁ extends over substantially the entire length of the strip 22 ₁ of material.

The third grooved edge 20 ₁ extends on either side of the end of the transverse branch 14b ₁ , facing the fourth edge 24 ₁ . This third edge 20 ₁ then partially delimits the contour of a square 44 ₁ of material. The outline of the square 44 ₁ 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 , of the second grooved edge 16 ₁ .

The square 44 ₁ is connected to the edge 38 ₁ of the layer 10 by tabs 46 ₁ . Furthermore, the first grooved edge 16 ₁ extends in the direction Y, on either side of the transverse branch 14b ₁ of the cross 12 ₁ on which it is made, facing the extension of the second edge 16 ₁ delimiting partially the square 44 ₁ .

The square 44 ₁ is also connected to the extremal portion 120 ₁ of the transverse branch 14b ₁ of the cross 12 ₁ , by tongues 48 ₁ . The end portion 120 ₁ of the transverse branch 14b ₁ extends between the second edge 18 ₁ and the third edge 20 ₁ .

Finally, the strips 22 ₁ facing the transverse branches 14b ₁ are directly connected to the edge 38 ₁ of the layer 10 by tongues 50 ₁ .

It should be noted that the distance d1 between the second edge 18 ₁ and the third edge 20 ₁ is identical on each branch 14a ₁ , 14b ₁ of the cross 12 ₁ . Furthermore, the width of the strips 22 ₁ is identical, the width being measured between the fourth edge 24 ₁ and the side of the strip 22 ₁ opposite this fourth edge 24 ₁ . The distances d1 and d2 are here approximately equal.

The first layer 10 is also provided with four holes 52 ₁ 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 54 ₁ will be described later.

The first layer 10 as it has just been described is for example made from a monolithic layer by cutting and/or shaping. The cuts can be made by any process suitable for the material of the first layer. The cuts can in particular be made by laser cutting, chemical cutting, stamping. Shaping may consist of adding material, in particular by a LIGA process (from the German “Rδntgenlithographie, Galvanoformung, Abformung” for X-ray lithography, galvanization by electrodeposition 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 its production. The same applies to the other layers described below.

On the figure 2 , the first layer 10 is covered by a second layer 56 of flexible material. The flexible material may be a polymer film, for example polyimide. Here, as an example, the flexible material is kapton ^® . In practice, a layer of glue or a layer of adhesive material, of substantially identical shape to the first 10 or to the second layer 56, is interposed between the first layer 10 and the second layer 56.

It should be noted that cuts are made in the second layer 56, so that the second layer 56 has a shape substantially identical to the first layer 10. The second layer 56 forms for example a cross 12 ₂ of identical shape to the cross 12 ₁ of the first layer 10. However, the cross 12 ₂ , on the second layer 56, is solid, with the exception, here, of the two holes 54 ₂ . In particular, the cross 12 ₂ on the second layer 56 is devoid of grooved edges. More generally, the second layer 56 as a whole is devoid of grooved edges.

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 does not have tabs connecting it to the edge 38 ₂ of the second layer 56.

On the Figure 3 , the second layer 56 is covered by a third layer 58. In practice, here again, a layer of glue or adhesive material is interposed between the second layer 56 and the third layer 58, the glue layer being for example of identical shape to the third layer 58.

The third layer 58 is here of identical shape to the first layer 10. Thus, on the Figure 3 , the second layer 56 appears between the grooves of the facing grooved edges.

On the Figure 4 , the third layer 58 is covered by a fourth layer 60. Here again, in practice, a layer of glue or adhesive material is interposed between the third layer 58 and the fourth layer 60. This layer of glue or adhesive material is substantially identical 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 elbows 32 ₄ are connected, each via a respective tongue 34 ₄ , 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, where appropriate, be made of the same material. In particular, the fourth layer 60 can be made of a more flexible material than the first and third layers 10, 58. Alternatively or additionally, the fourth layer 60 can be thinner than the first and third layers 10, 58, particularly in the case where all these layers are made of the same material.

In the example, the fourth layer 60 is then covered with a fifth layer 64 as illustrated in figure 5 .

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

The fifth layer 64 is identical in shape to the first and third layers 10, 58. This fifth layer 64 is for example made 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.

We thus obtain a substantially flat multilayer structure 68, visible in particular at the Figure 6 .

Finally, in the example of method described with reference to the figures, a base 66 is arranged on the fifth layer 64, as illustrated in Figure 6 . This base 66 is positioned relative to the flat multilayer structure 68, in particular using the 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 breakable tabs 94. Here again, the correct positioning of the support 90 and, consequently, of the beams 92 relative to the flat multilayer structure 68 is obtained thanks to the holes 54 and the guide pins which are received there. It should be noted here that the support 90, the beams 92 and the tongues 94 can be made in a single piece. In particular, the support 90, the beams 92 and the tongues 94 can be obtained by implementing the same processes as those previously described for the production of the different 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 there.

• les étriers 26 sont détachés du bord 38 des couches 10, 56, 58, 60, 64 superposées ;
• les bandes 22 sont détachées des étriers 26 ; et
• les carrés 44 sont détachés du bord 38 des couches 10, 56, 58, 60, 64 superposées et des portions extrêmales 120 des branches 14b transversales de la croix 12.

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

• the stirrups 26 are detached from the edge 38 of the superimposed layers 10, 56, 58, 60, 64;
• the bands 22 are detached from the stirrups 26; And
• the squares 44 are detached from the edge 38 of the superimposed layers 10, 56, 58, 60, 64 and from the extreme 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 flat multilayer structure 68, this step being illustrated in figures 8 to 10 . In other words, the multilayer structure 68 of the Figure 7 is deployed to extend it in the Z direction normal to the plane of the planar multilayer structure 68. We thus obtain a three-dimensional deployed structure 88.

There figure 8 illustrates an intermediate state of the multilayer structure 68, before reaching its final, deployed state, illustrated in Figure 10 .

Here, due to traction in the Z direction, and as illustrated in figure 8 , joints - that is to say, connections essentially allowing rotation - are formed at the level of the facing grooved edges.

There Figure 9 illustrates, by way of example, the formation of a joint 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 each other. On this Figure 9 , the grooves of the third and fourth edges 20, 24 of the third, fourth and fifth layers 58, 60, 64 are bring together, the teeth of one groove being received between two neighboring 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 (on the right on the Figure 9 ) and the extremal portion 120 of the longitudinal branch 14a (on the left on the Figure 9 ). The second layer 56 then forms a joint 72.

• une première articulation 70 d'axe X entre la base de chaque branche 14a longitudinale et la portion d'extrémité correspondante ;
• une deuxième articulation 72 d'axe X entre la portion d'extrémité 120 de chaque branche 14a longitudinale et la bande 22 en vis-à-vis ;
• deux troisièmes articulations 74 d'axe X entre chaque bande 22 de matière en vis-à-vis d'une branche 14a longitudinale et l'étrier 26 associé ;
• deux quatrièmes articulations 76 d'axe X entre chaque étrier 26 et le bord 38 des différentes couches ;
• une cinquième articulation 78 d'axe Y entre la base de chaque branche 14b transversale et la portion d'extrémité correspondante ;
• une sixième articulation 80 d'axe Y entre la portion d'extrémité de chaque branche 14b transversale et la bande 22 en vis-à-vis ;
• deux septièmes articulations 82 d'axe Y entre chaque bande 22 de matière en vis-à-vis d'une branche 14b transversale et les deux carrés 44 associés ;
• une huitième articulation 84 d'axe Y entre chaque carré 44 et le bord 38 des différentes couches.

The previously mentioned fluted edges thus form, in cooperation with the second layer 56, the following articulations:

• a first articulation 70 of axis X between the base of each longitudinal branch 14a and the corresponding end portion;
• a second articulation 72 of axis X between the end portion 120 of each longitudinal branch 14a and the strip 22 facing each other;
• two third articulations 74 of axis X between each strip 22 of material facing a longitudinal branch 14a and the associated stirrup 26;
• two fourth joints 76 of axis X between each stirrup 26 and the edge 38 of the different layers;
• a fifth articulation 78 with axis Y between the base of each transverse branch 14b and the corresponding end portion;
• a sixth articulation 80 of axis Y between the end portion of each transverse branch 14b and the strip 22 facing each other;
• two seventh joints 82 of axis Y between each strip 22 of material facing a transverse branch 14b and the two associated squares 44;
• an eighth articulation 84 with axis Y between each square 44 and the edge 38 of the different layers.

Thus, by choosing perpendicular orientations of the joints, we form here a Sarrus 86 assembly (from the English “Sarrus linkage”). This Sarrus assembly is a particular example of a mounting scaffold that can be used in the process.

Such mounting scaffolding is produced by the multilayer structure, in addition to the structure of interest that we seek to achieve. This assembly scaffolding makes it possible to connect the different movements necessary for the deployment of the multi-layer structure, so that this deployment can be carried out by acting on the multilayer structure according to a single degree of freedom. This assembly scaffolding thus facilitates the deployment stage.

The assembly of Sarrus 86 thus produced thus makes it possible, by pulling on a part of the multilayer structure 68 in the direction Z, to cause a straightening of the stirrups 26. The straightening 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 a pivoting of the blades 62, so that their width extends in a direction normal to the plane of the flat multilayer structure 68, the length and thickness of the blades extending substantially in a plane parallel to the plane of the multilayer structure 68, flat. We thus obtain, from a blade adapted initially to oscillate in a plane normal to the plane of the flat multilayer structure 68, a blade adapted to oscillate in a plane parallel to the plane of the multilayer structure 68.

We thus obtain a deployed multilayer structure 88, as illustrated 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 brazing or bonding.

In addition, at this step or after this blocking step, the pallets 36 fixed to the ends of the blades 62 can be fixed to masses 92, here produced in the form of beams. This can in particular be achieved by brazing. In this case, a metal plate can be glued to each end of the masses 92, thus allowing fixing by brazing.

There Figure 11 illustrates the detachment of the assembly formed by the masses 92 secured to the blades 62 via the blades 36, from the rest of the deployed multilayer structure 88. This is achieved by cutting the tongues 34 connecting the blades 36 and the blade 62 to the stirrups 26, as well as the tabs 94 connecting the masses 92 to the support 90.

Finally, the 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 pucks 36 connecting the ends of the blades 62 to the masses 92.

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

It should be noted here that the blades 62 are oriented in such a way that they allow the flexible mechanism 100 to oscillate in a plane extending substantially in the directions X and Y. On the contrary, in the planar multilayer structure 68, the blades 62 were oriented in such a way 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, in particular synthetic diamond, in particular synthetic diamond obtained by chemical vapor deposition process, titanium, an alloy titanium, in particular an alloy from the Gum metal ^® family and an alloy from the elinvar family, 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 maintain 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.

Elinvar alloys are nickel steel alloys comprising nickel and chromium which are very insensitive to temperatures. Elinvar ^® , in particular, is a nickel steel alloy, comprising 59% iron, 36% nickel and 5% chromium.

NI-Span-C ^® includes 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; at most 0.06% carbon; at most 0.80% manganese; at most 1% silicon; at most 0.04% sulfur; at most 0.04% phosphorus; and the 100% iron supplement.

Précision 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 ^® includes: 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 iron supplement.

Thermelast ^® includes: 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 compositions above are indicated in mass percentages.

The blade(s) advantageously have a thickness greater than or equal to 1 µm, preferably greater than or equal to 5 µm, and/or less than or equal to 30 µm, preferably less than or equal to 20 µm, preferably less than or equal to 15 µm.

The blade(s) may also 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(s) may also have a length of, for example, between 5 and 13 mm.

The or each blade 62 can 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 loaded with particles of density greater than ten, in particular tungsten particles. These materials are indeed heavy. In the case of a mechanism 100 forming an oscillator, this makes it possible to have masses 92 of reduced dimensions but with a relatively large weight.

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

As indicated previously, the mechanism 100 can advantageously form an oscillator. In this case, one of the masses 92 can form a frame or be rigidly fixed to a frame, relative to which the other mass 92 oscillates. In this case, in this case, one of the masses 92 oscillates according to 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 makes it possible 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 a 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 which is not in contact with the mass. In the case where the blade is fixed to two masses, the free length means 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 integrating the blade(s) 62.

A flexible mechanism of the type of the 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 previously described, is implemented in a watch movement in a part of watchmaking, for the manufacture of an oscillator, in particular as a regulator of such a watch movement.

• un boîtier 202,
• un mouvement horloger 203 contenu dans le boîtier 202,
• généralement, un remontoir 204,
• un cadran 205,
• un verre 206 recouvrant le cadran 205,
• un indicateur de temps 207, comprenant par exemple deux aiguilles 207a, 207b respectivement pour les heures et les minutes, disposé entre le verre 206 et le cadran 205 et actionné par le mouvement horloger 203.

In known manner, a timepiece 200 such as a watch illustrated in figure 13 , essentially includes:

• a box 202,
• a watch movement 203 contained in the case 202,
• generally, a winder 204,
• a dial 205,
• a glass 206 covering the dial 205,
• a time indicator 207, comprising for example two hands 207a, 207b respectively for the hours and the minutes, placed between the glass 206 and the dial 205 and actuated by the watch movement 203.

• un dispositif 208 de stockage d'énergie mécanique, généralement un ressort de barillet,
• une transmission mécanique 209 mue par le dispositif 208 de stockage d'énergie mécanique,
• l'indicateur de temps 207 susmentionné,
• un organe de distribution d'énergie 210 (par exemple une roue d'échappement),
• une ancre 211 adaptée pour séquentiellement retenir et libérer l'organe de distribution d'énergie 210,
• un régulateur 212, qui est un mécanisme comportant un organe réglant oscillant contrôlant l'ancre 211 pour la déplacer régulièrement de façon que l'organe de distribution d'énergie soit déplacé pas à pas à intervalles de temps constants, et, éventuellement,
• un organe de découplage 213, qui est interposé entre le régulateur 212 et l'ancre 211.

As shown schematically on the Figure 14 , the watch movement 203 can include for example:

• a mechanical energy storage device 208, generally a barrel spring,
• a mechanical transmission 209 driven by the mechanical energy storage device 208,
• the aforementioned time indicator 207,
• an energy distribution member 210 (for example an escape wheel),
• an anchor 211 adapted to sequentially retain and release the energy 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 distribution member is moved step by step at constant time intervals, and, optionally,
• 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 numerous variants accessible to those skilled in the art.

First of all, 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 carried out using brazing. Alternatively, however, the masses are fixed to the blade(s), in particular at the ends of these blades, by overmolding, clamping, clipping, gluing, welding, in particular spot welding, in particular laser spot welding, or any other process accessible to those skilled in the art.

The masses can be reported on the deployed multilayer structure, in the form of a cutout in an additional layer of material which is superimposed on the deployed multilayer structure. The cutting in the layer of additional material can in particular form housings for receiving the ends of the flexible blades, in particular the pucks fixed to the ends of the blades, the reception then being, preferably, carried out with clamping.

Also, according to a variant, the masses can be formed by the multilayer structure. The masses are then arranged opposite the ends of the blades or pallets fixed at these ends at the time of deployment of the multilayer structure.

Furthermore, in the example of the method described, it includes a step of blocking the structure in the deployed position. This step is a priori optional. It is however preferred when other manipulations of the structure in the deployed position are desired to achieve the mechanism. In the case where such blocking is to be carried out, this can be obtained by any means accessible to those skilled in the art, in particular by bonding, overmolding, soldering, clipping, welding, in particular spot welding, in particular welding by laser point or, more generally, by fixing together elements of the structure in the deployed position.

In addition, the method of manufacturing a mechanism may include a step of assembling numerous layers on top of 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 the 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 significantly improve the efficiency of the process for manufacturing a mechanism.

Finally, the grooved edges mentioned in the example described can be replaced by folding tips. In particular, the beginnings of folding can be made by partial cutting of the layers. Partial cuts may consist of dotted cuts and/or cutting only part of the thickness of the layers. In the case of cutting only part of the thickness of the layers, the partial cutting can possibly be continuous. Complete cutting of the layers can also be considered.

The masses can be reported on the deployed multilayer structure, in the form of a cutout in an additional layer of material which is superimposed on the deployed multilayer structure. The cutting in the layer of additional material can in particular form housings for receiving the ends of the flexible blades, in particular the pucks fixed to the ends of the blades, the reception then being, preferably, carried out with clamping.

Also, according to a variant, the masses can be formed by the multilayer structure. The masses are then arranged opposite the ends of the blades or pallets fixed at these ends at the time of deployment of the multilayer structure.

Furthermore, in the example of the method described, it includes a step of blocking the structure in the deployed position. This step is a priori optional. It is however preferred when other manipulations of the structure in the deployed position are desired to achieve the mechanism. In the case where such blocking is to be carried out, this can be obtained by any means accessible to those skilled in the art, in particular by bonding, overmolding, soldering, clipping, welding, in particular spot welding, in particular welding by laser point or, more generally, by fixing together elements of the structure in the deployed position.

In addition, the method of manufacturing a mechanism may include a step of assembling numerous layers on top of 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 the 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 significantly improve the efficiency of the process for manufacturing a mechanism.

Finally, the grooved edges mentioned in the example described can be replaced by folding tips. In particular, the beginnings of folding can be made by partial cutting of the layers. Partial cuts may consist of dotted cuts and/or cutting only part of the thickness of the layers. In the case of cutting only part of the thickness of the layers, the partial cutting can possibly be continuous. Complete cutting of the layers can also be considered.

Claims (15)

1. Method for manufacturing a timepiece oscillator (100) 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 direction (Z) substantially normal to the flat layers (10; 56; 58; 60; 64);

   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 timepiece oscillator (100), the blade or blades (62) being fixed, in the timepiece oscillator (100), to at least one mass (92), preferably to two masses (92), the or each mass (92) being more rigid than the blade or blades (62), the blade or blades (62) being fixed to the or to each mass (92) in a step subsequent to step ii).
2. Method according to claim 1, wherein each blade (62) has, in the timepiece oscillator (100), a free length (L) greater than one third of the width of the blade (62) in question, the free length (L) being defined as being:

   - the length of the blade (62) which is not in contact with the mass (92), in the case where the blade (62) is fixed to one 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 fixed to two masses (92),

   the or each blade (62) preferably not being in contact with any other element of the timepiece oscillator (100) along the free length (L).
3. Method according to claim 1 or 2, comprising a step iii) subsequent to step ii), consisting of locking the multilayer structure in the deployed position (88), wherein, preferably, in step iii), the structure is locked in the deployed position (88) by at least one among: an overmolding, brazing, clipping, gluing, welding, particularly spot welding, more particularly laser spot welding, and clamping, of at least a part of the timepiece oscillator, in particular of at least one hinge of the timepiece oscillator.
4. Method according to any one of the preceding claims, wherein the or each mass (92) is attached to an end, preferably to a respective end, of one of said at least one blade (62).
5. Method according to any one of the preceding claims, wherein the or each mass (92) is fixed to the blade (62) or to each blade (62) by:

   - overmolding;

   - brazing;

   - clipping;

   - gluing;

   - welding, particularly spot welding, more particularly laser spot welding;

   - clamping.
6. Method according to any one of the preceding claims, wherein the mass or masses (92) are created by at least one of the flat layers (10; 56; 58; 60; 64) assembled in step i).
7. Method according to any one of the preceding claims, wherein the mass or masses (92) are of one among: tungsten, molybdenum, gold, silver, tantalum, platinum, alloys comprising these elements and a polymer material loaded with particles of a density greater than ten, in particular tungsten particles.
8. Method according to any one of the preceding claims, wherein the blade or blades (62) are of one among: silicon, glass, sapphire, diamond, particularly synthetic diamond, more particularly synthetic diamond obtained by a chemical vapor deposition process, titanium, a titanium alloy, particularly an alloy of the Gum metal^® family and an alloy of the elinvar family, more particularly Elinvar^®, Nivarox^®, Thermelast^® , Ni-Span-C^®, Precision C^®.
9. Method according to any one of the preceding claims, wherein

   - in step i), ten to fifty flat layers (10; 56; 58; 60; 64) are assembled together; and/or

   - the blade or blades (62) have a width, a thickness, and an aspect ratio defined as being equal to the ratio of the width of the blade (62) to the thickness of the blade (62), the aspect ratio of each blade being greater than 10, preferably greater than 25; and/or

   - the blade or blades (62) have a thickness greater than or equal to 1 µm, preferably greater than 5 µm, and/or less than or equal to 30 µm, preferably less than or equal to 20 µm, more preferably less than or equal to 15 µm;

   - 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.
10. Method according to any one of the preceding claims, wherein the substantially flat multilayer structure (68) forms at least one mounting scaffold (86), the method comprising a step iv), preferably subsequent to step iii) where appropriate, consisting of detaching the structure in the deployed position (88), from the at least one mounting scaffold (86).
11. Method according to any one of the preceding claims, wherein each layer (10; 56; 58; 60; 64) undergoes a machining step, preferably before its assembling, in particular laser cutting, industrial etching, stamping, milling, electrical discharge machining, and/or a shaping step, particularly a shaping step by adding material, more particularly a shaping step by LIGA or by injection molding.
12. Method according to any one of the preceding claims, wherein a plurality of substantially flat multilayer structures (68), respectively structures in the deployed position (88), are obtained in step ii), respectively in step iii), from a single assembling of layers in step i).
13. Method according to any one of the preceding claims, wherein the or each blade (62) is of a more flexible material than the or each mass (92) which is fixed to said blade (62).
14. Timepiece oscillator at least partly made by implementing a method according to any one of claims 1 to 13.
15. Timepiece movement (203) for a timepiece (200), comprising a timepiece oscillator according to claim 14.

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