LAUNCH ARM

Description

TECHNICAL FIELD OF THE INVENTION

[0001] The present invention relates to the field of target launchers for sport shooting disciplines. It finds particularly advantageous application in disciplines such as clay pigeon shooting and its derivative activities. STATE OF THE ART

[0002] Many launcher solutions offer devices in which an arm is articulated in rotation, a target is positioned on a plate, and by a rotational movement of the arm, the target is pushed by the arm and consequently ejected from the device according to a predetermined trajectory.

[0003] In order for the ejection to occur, the thrust must be strong enough to allow a shooter to attempt their luck. The thrust can tend to break the target. Indeed, for these disciplines the projectiles used are particularly fragile in order to fulfill their function. One of the challenges of solutions in this field is to allow ejection over a long distance without breaking the target. To achieve this, coatings or shock-absorbing elements are positioned at the end of the arm.

[0004] Known from the state of the art is patent application FR2696538A1, which discloses a target launching device for shooting comprising a launching plate on which at least one target is positioned, a launching arm comprising a damping element, and configured so as to be able to be movable in rotation along an axis relative to the launching plate, the arm being set into accelerated movement using a spring which triggers the movement until contact between the damping element and the target, and finally ejection.

[0005] Another target launching device is known from patent application FR3048772A1.

[0006] The projection of the target is due in particular to the angular acceleration of the throwing arm. Sometimes, during a throwing cycle, the arm rotates 360 degrees from an original position. The initial speed is then zero and the acceleration occurs over a first angular sector of approximately 130 degrees. During this phase, the target rolls along an elastomer integral with the arm to its end where the target is ejected. The energy used generally comes from the relaxation of a spring. A connecting rod can provide the connection between the spring and the arm. The spring can be tensioned by a geared motor whose end is in contact with the connecting rod. The relaxation of the spring is generally caused by exceeding an equilibrium point.

[0007] One of the challenges of these launch systems is to increase the ejection distance. One solution is to increase the rotation speed by increasing the spring stiffness. But this requires increasing the power of the geared motor and strengthening the freewheel. Another technical solution is to increase the length of the arm. Since the arm is generally a solid profile with a rectangular section and made of an aluminum alloy, increasing its length is accompanied by an increase in its peripheral mass and increases the inertia of the mechanism, which can lead to system instability.

[0008] An object of the present invention is therefore to propose a solution which makes it possible to improve the projection phase, and in particular to increase the ejection distance without increasing the power of the geared motor while preserving good stability of the device, or even to carry out a projection over usual distances in better conditions, for example by reducing the flexion of the arm or its inertia, or even the power of the geared motor.

[0009] Other objects, features, and advantages of the present invention will become apparent from the following description and accompanying drawings. It is understood that other advantages may be incorporated. SUMMARY OF THE INVENTION

[0010] To achieve this objective, according to one embodiment, a target launching device is provided, comprising a support, an arm and a plate, in which the arm is articulated in rotation relative to the support along an axis of rotation A z , extending in a direction of axis of rotation (z), so as to be able to eject a target placed on the plate, and in which the arm comprises: an elongated member having: i. a length dimension extending in a direction of extension x perpendicular to the direction of the axis of rotation z, ii. a width dimension extending in a transverse direction y, perpendicular to the direction of extension x and perpendicular to the direction of the axis of rotation z, iii. a height dimension extending in the direction of the axis of rotation z, a damping element mounted on the elongated member and capable of coming into contact with the target, device in which the elongated member comprises at least one section along its length dimension having, in section along a plane perpendicular to the direction of extension x, a first recess and a second recess arranged on either side of a core, the core being directed along the direction of the axis of rotation z and in which the damping element is fixed in the first recess.

[0011] Without this device, it would be necessary, for example, to use a longer arm, or to increase the power transmitted by a spring actuator to the arm. Indeed, a longer arm in the direction of extension allows a higher speed at the end of the arm, which is necessarily accompanied by a higher acceleration and thus a stronger projection of the target.

[0012] The inertia of the arm can be reduced by reducing its mass. This reduction in mass is the result of a first recess and a second recess. The dimension of the arm can be maintained in the direction of extension x. The damping element is advantageously positioned and fixed in the first recess.

[0013] Thus, the device makes it possible to avoid changing material and advantageously provides identical resistance to bending.

[0014] The device therefore preferably makes it possible to obtain an increase in the projection distance of a target launcher by reducing the mass of the launching arm.

[0015] For example, in order to increase the projection distance, it will be possible both to increase the length of the arm and to limit the flexion deformation of the arm by widening its base.

[0016] More specifically, one object is to propose an improvement of the throwing arm. BRIEF DESCRIPTION OF THE FIGURES

[0017] The aims, objects, as well as the characteristics and advantages of the invention will emerge more clearly from the detailed description of an embodiment thereof which is illustrated by the following accompanying drawings in which: There Figure 1A represents an example of a prior art target launcher. The Figure 1B represents an example of a launch zone of a prior art target launcher. The Figures 1C to 1D represent a zoomed-in sectional view of an example of a launch zone of a prior art launcher. The Figure 2A represents a simplified device with a throwing arm comprising an elongated member and a damping element. The Figures 2B to 2C represent a sectional view of a launching arm of the simplified device of the Figure 2A , with the arm alone in Figure 2B and with the damping element configured to come into position against the elongated member in Figure 2C. There Figure 3A represents a simplified device according to the present invention with a launching arm comprising an elongated member and a damping element. The Figures 3B to 3C represent a sectional view of a launching arm of the simplified device of the Figure 3A with the damping element configured to be positioned against the elongated member. The 3D figure represents a sectional view of the damping element and its different functional zones. The figure 4 represents a zoomed-in sectional view of an example of a launch zone of a launcher according to the present invention. The Figure 5 represents two elongated members according to the present invention.

[0018] The drawings are given by way of example and are not limiting of the invention. They constitute schematic representations of principle intended to facilitate the understanding of the invention and are not necessarily to the scale of practical applications. DETAILED DESCRIPTION

[0019] Before commencing a detailed review of embodiments of the invention, optional features that may optionally be used in combination or alternatively are set forth below: According to one example, the elongate member 210 comprises a first wing 214, a second wing 215, a third wing 216 and a fourth wing 217, the wings being directed in the transverse direction y.

[0020] According to one example, the first wing 214 comprises a first internal wall 214a, the second wing 215 comprises a second internal wall 215a and the first recess 211 extends in the direction of extension x and is delimited by the first internal wall 214a, by the second internal wall 215a and by a central wall 213a extending from the first internal wall 214a to the second internal wall 215a.

[0021] According to one example, the damping element 220 comprises a mounting portion 222 and a contact portion 221, such that the mounting portion 222 comprises coupling surfaces 222b, 222c configured so as to be able to cooperate by coupling with the first internal wall 214a and a stop wall 214c of the first wing 214, in particular in order to allow the damping element 220 to be positioned in contact with an edge of the first wing 214.

[0022] According to one example, the damping element 220 is made of an elastomeric material such as for example EPDM 70 Shore and extends in the direction of extension x and / or the elongated member 210 is made of an aluminum alloy such as for example an alloy (AlZn 5 , 5MGCu) 7075. According to one example, in the direction of the axis of rotation z, the dimension of the arm z 200 is equal to the height dimension of the elongated member z 210 , preferably equal to 12 mm.

[0023] According to one example, the elongated member 210 has a lower face 210b and the damping element 220 has a lower damping face 220b such that the lower face 210b and the lower damping face 220b are coplanar.

[0024] According to one example, the elongated member comprises a section which varies in width and decreases as it moves away from the axis of rotation Az.

[0025] According to one example, the contact portion 221 comprises a planar contact surface 221c, configured to be oriented towards the inside of the rotational movement of the launching arm 200 during the ejection phase of the target 300, and perpendicular to the transverse direction y. According to one example, the core 213 is a parallelepiped plate comprising a median plane parallel simultaneously to the extension direction x and to the rotation axis direction z, and the elongated member 210 is a part having a shape symmetry along said median plane.

[0026] According to one example, the distance between the first inner wall 214a and the second inner wall 215a is greater than 4 mm, preferably greater than 6 mm and preferably greater than 8 mm.

[0027] According to one example, in section, along a plane perpendicular to the direction of extension x, the thickness of the core 213 is equal to the respective thickness of the four wings 214, 215, 216, 217, preferably equal to 2 mm.

[0028] It is specified that in the context of the present invention, the term “launcher” is sometimes used instead of “machine” as the claimed object, it will be appropriate to consider these terms as equivalent.

[0029] In the context of the invention, the term "radial orientation" or "radially" will be understood to mean that which relates to the positioning of a mobile element in rotation relative to an axis.

[0030] The terms "substantially", "approximately", "of the order of" mean "within 10%, preferably within 5%" or, when it comes to an angular orientation, "within 10°". Thus, a direction substantially normal to a plane means a direction having an angle of 90±10° with respect to the plane.

[0031] In the remainder of the description, the term "on" does not necessarily mean "directly on". Thus, when it is indicated that a part or member A is supported "on" a part or member B, this does not mean that the parts or members A and B are necessarily in direct contact with each other. These parts or members A and B may be either in direct contact or be supported on each other by means of one or more other parts. The same applies to other expressions such as, for example, the expression "A acts on B", which may mean "A acts directly on B" or "A acts on B by means of one or more other parts".

[0032] In this document, the term mobile corresponds to a rotational movement or a translational movement or to a combination of movements, for example the combination of a rotation and a translation.

[0033] In this document, when two parts are indicated as distinct, this means that these parts are separate. They are: positioned at a distance from each other, and / or movable relative to each other and / or secured to each other by being fixed by added elements, this fixing being removable or not.

[0034] A single piece cannot therefore be made up of two separate pieces.

[0035] In this patent application, the term "integral" used to qualify the connection between two parts means that the two parts are linked / fixed relative to each other, according to all degrees of freedom, unless explicitly specified differently. For example, if it is indicated that two parts are integral in translation in an X direction, this means that the parts can be movable relative to each other except in the X direction. In other words, if one part is moved in the X direction, the other part performs the same movement. CRITICISM OF PREVIOUS ART

[0036] As illustrated in the Figure 1Aand according to an example from the prior art, there is shown a target launching device 300 comprising a support 100 on which a plate 110 is positioned. A launching arm 200 is articulated in rotation relative to the support 100 and along an axis of rotation AZ. The target 300 is able to be positioned on the plate 110. A spring system, preferentially triggers an accelerated movement of the launching arm 200 along the direction of axis of rotation z and thus drives the launching arm 200 into contact with the target 300. This contact can be related to a thrust, in which a transmission of kinetic energy is carried out from the arm towards the target 300 in order to allow a projection of the latter along a predetermined trajectory.The throwing arm 200 comprises a damping element 220 configured to be preferably positioned at the end of the arm in order to dampen the contact between the throwing arm 200 and the target 300 and thus create an adhesion surface. Without the presence of the damping element 220, the contact between the throwing arm 200 and the target 300 may cause the target 300 to break. Indeed, this type of device is intended for throwing targets 300 for sport shooting and these targets 300 are made of a brittle material which must be able to shatter into several pieces, upon contact with a projectile which may be a shot of lead.

[0037] As illustrated in Figures 1B And 1C , and according to an example of the prior art, a launch zone 112 is limited vertically between a barrel support plate 113 and the plate 110, and horizontally between a comma 111 and the launch arm 200.

[0038] As illustrated in the Figure 1Dand according to an example of the prior art, the target 300 tends to get stuck between the barrel support plate 113 and the comma 111 and in these cases, the target 300 generally breaks under the action of the launching arm 200 in the launching zone 112. As illustrated in Figure 2A and according to a simplified example of the prior art, it may be a launching arm 200 in which the elongated member 210 and the damping element 220 are found.

[0039] The support 100 is preferably fixed relative to the ground at the time of the launch phase. On the Figure 2A , it is possible to see the cooperation between the damping element 220 and the elongated member 210 distributed according to the direction of extension.

[0040] As illustrated in Figures 2B and 2C, and according to this same example, the elongated member 210 is a part which extends between a pivot joint allowing a rotational movement with the support and a free end configured to be able to fix a damping element 220. The elongated member 210 can be a solid profile, possibly with a constant rectangular section and made of a rigid material, such as for example a metal alloy.

[0041] As illustrated in the Figure 2C , and according to the same example, the damping element 220 is positioned below the elongated member 210. The damping element 220 comprises at least one face, in plane-to-plane contact with the elongated member 210. In this example, in order to guarantee good positioning of the damping element 220 on the elongated member 210, the latter two are configured to be in plane-to-plane contact via two respective adjacent surfaces.

[0042] The damping element 220 is positioned under the launching arm 200 so that it can brush against the plate 110 in order to allow the best possible contact when it comes into contact with the target 300. Such positioning of the damping element 220 on the elongated member 210 increases the height dimension z 200 of the arm.

[0043] In order to allow a further projection of the target, it would be advisable to increase the speed of the arm 200. PREFERRED EMBODIMENT

[0044] The present invention makes it possible to increase the speed of the arm by reducing its mass. This reduction in mass is the consequence of a first recess 211 and a second recess 212. The dimension of the throwing arm 200 remains unchanged compared to the solution of the prior art in the direction of extension x. The damping element is advantageously positioned and fixed in the first recess 211.

[0045] As illustrated in the Figure 3A and according to an embodiment preferred by the present invention. The launching arm 200, articulated in rotation relative to the support 100 along the axis of rotation A z comprises an elongated member 210 and a damping element 220, both mounted integrally.

[0046] As illustrated in the Figure 3B , in section along a plane perpendicular to the direction of extension x, the elongated member 210 comprises a first recess 211 as well as a second recess 212 distributed around a core 213. Preferably, the elongated member 210 comprises a first wing 214, a second wing 215, a third wing 216 as well as a fourth wing 217 distributed around the core 213. This distribution is preferably homogeneous so that the first wing 214 and the second wing 215 are symmetrical with respect to the third wing 216 and the fourth wing 217.

[0047] As illustrated in Figures 3B to 3Dand according to a particular embodiment of the invention, the damping element 220 comprises a contact portion 221 and a mounting portion 222. The mounting portion 222 is configured so that it can be positioned in contact with the first wing 214.

[0048] Preferably, the first wing 214 comprises a first inner wall 214a and the mounting portion 222 comprises a first mating surface 222b configured such that the first inner wall 214a comes into planar-to-planar contact with the first mating surface 222b.

[0049] Advantageously, the first wing 214 comprises an abutment wall 214c and the mounting portion 222 comprises a second mating surface 222c configured such that the abutment wall 214c makes planar-to-planar contact with the second mating surface 222c.

[0050] The cooperation between the damping element 220 and the elongated member 210 is advantageously optimized such that the elongated member 210 comprises a lower face 210b and the damping element comprises a lower damping face 220b so that the lower damping face 220b and the lower face 210b are preferentially coplanar when the damping element 220 is secured to the elongated member 210.

[0051] As illustrated in the 3D figure and according to one example, the damping element 220 comprises a contact portion 221 and a mounting portion 222. The contact portion 221 comprises a contact surface 221c configured to be in contact with the target 300 during the ejection phase of the target 300.

[0052] Preferably, the contact between the first wing 214 and the damping element 220 comprises at least one contact by the edge of the first wing 214, so that the forces applied by the reaction of a target during projection onto the damping element 220 are taken up, behind, by said edge. And thus a compressive deformation of the damping element 220 at this level, which makes its arrangement reliable relative to the target. Preferably, the contact is plane on plane. Alternatively, or in addition, a contact perpendicular to the direction of stress on the damping element 220 by the target can be put in place between the first wing 214 and the damping element 220, in particular at the surface 222b. This aspect makes it possible to benefit from a potentially large bearing surface between these two elements. Preferably, the contact is plane on plane.

[0053] According to a preferred embodiment of the present invention, the height dimension of the arm z 200 is equal to the height dimension of the elongated member z 210. Thus, the space between the plate 110 and the barrel support plate 113 can also be reduced, which makes the probability of the target 300 getting stuck between the barrel support plate 113 and the comma 111 zero.

[0054] Indeed, according to this same particular embodiment, the height dimension of the damping element z 220 is less than or equal to the height dimension of the elongated member z 210 so that when the damping element 220 is positioned and is held in position with the elongated member 210, the damping element 220 does not exceed the elongated member 210, in the direction of the axis of rotation z. Thus, the volume of the launch zone 112 is advantageously reduced and a target 300 can no longer become stuck there. Consequently, destruction of the target 300 within the launch zone 112 is avoided and, as a result, a maintenance operation to restore the machine to operating condition is also avoided. Finally, the present invention does not require changing the material and offers identical resistance to bending. APPROACH TO MATERIAL RESISTANCE

[0055] According to a particular embodiment, the elongated member 210 is made of a metallic material. Optionally, it could be an aluminum alloy, preferably of the “7075” type whose Young’s modulus is preferably equal to 72 N.mm -2< . Preferably, the elongated member 210 is a single unitary piece.

[0056] Furthermore, the contact between the throwing arm 100 and the target 300 results in the free end of the arm, a normal component force oriented along the direction of the rotation axis z. The throwing arm 100 must therefore structurally oppose this normal stress resulting from a bending moment.

[0057] According to a particular embodiment, in section, along a plane perpendicular to the direction of extension x, the first recess 211 and the second recess 212 are identical and distributed symmetrically on each side of the core 213.

[0058] According to the same embodiment, the thickness of the core is equal to the thicknesses of the first wing 214, the second wing 215, the third wing 216, as well as the fourth wing 217. Preferably, this thickness may be equal to 2 mm. Preferably, the elongated member 210 has a height dimension z 210 along the direction of the axis of rotation z equal to 12 mm and / or has a width dimension along the transverse direction y equal to 30 mm.

[0059] According to this same embodiment, the damping element 220 has a height dimension z 220 along the direction of the rotation axis z equal to 6 mm.

[0060] According to an example “A”, shown in Figures 1C , 2A, 2B, 2Cand originating from the prior art, the elongated member 210 has a solid rectangular section with height over width dimensions equal to 10 mm x 30 mm, a length of 342 mm and a mass of 358 grams. This elongated member 210, in the direction of extension x, is subjected to bending over a length of 307 mm. This results in a quadratic moment I x of 2500 mm 4< with a maximum deflection at the end of the arm equal to 0.64 mm.

[0061] According to a preferred embodiment of the present invention “B” and shown in Figures 3A to 3D , 4 And 5, the elongated member 210 has a section whose dimensions are included in a rectangle of 12 mm x 30 mm and having four wings 214, 215, 216, 217 distributed symmetrically with respect to the core 213. And in which the thicknesses of the wings and of the core 213 are constant and equal to 2 mm, then the quadratic moment I x is equal to 3125 mm 4< with a maximum deflection at the end of the arm equal to 0.51 mm.

[0062] Thus, the present invention allows, in addition to a reduction in mass, also better resistance to the stress resulting from the bending moment. ASSEMBLY

[0063] According to one embodiment, the mounting portion 222 comprises openings so as to be able to allow the integral connection of the damping element 220 with the elongated member 210. Advantageously, this assembly is carried out using fixing elements which may possibly be threaded elements, in particular by screwing.

[0064] According to another embodiment, the damping element 220 is fixed to the elongated member 210 using an adhesive. KINEMATIC APPROACH

[0065] According to a particular embodiment, the launching arm 200 is advantageously driven in rotation by a crank rod type system itself connected to a spring system, itself actuated by a motor. With the same motor power: in example “A” from the prior art presented to the Figures 1A to 1D , the speed of the target 300 at the end of the plate 110 can reach 109 km / h. With an inclination of the plate 110 of 15 degrees relative to a horizontal line parallel to the ground, a projection distance of 70 m is thus obtained. in example “B” from the present invention in the example of the Figures 3A to 3D, the speed of the target 300 at the end of the plate 110 can then reach 119 km / h. With an inclination of the plate 110 of 15 degrees relative to a horizontal line parallel to the ground, a projection distance of approximately 95 meters is thus obtained, i.e. a gain of 25 meters. ANOTHER EMBODIMENT.

[0066] As illustrated in the Figure 5and according to a particular embodiment, the launching arm 200 comprises in its part capable of being positioned close to the rotation axis a base 218. Furthermore, in order to allow a more distant projection of a target, it is also possible in combination with the present invention to lengthen the length of the launching arm 200 in the extension direction x. A larger launching arm 200 generally results in a greater deflection at the end of the arm due to a greater bending moment. To overcome this mechanical deformation, the present invention proposes a wider section of the base 218 in the transverse direction y.

[0067] According to one embodiment, the third wing 216 comprises a third internal wall, the fourth wing 217 comprises a fourth internal wall 215a and the second recess 212 extends in the direction of extension x and is delimited by the third internal wall, by the fourth internal wall and by a second central wall extending from the third internal wall 214a to the fourth internal wall.

[0068] According to a particular embodiment, the damping element 220 is made of an elastomeric material which extends like a profile in the direction of extension x and / or the elongated member 210 is made of an aluminum alloy.

[0069] According to a particular embodiment, the contact portion 221 comprises a planar contact surface 221c, configured to be oriented forwards in the direction of rotation. According to a particular embodiment, the articulation of the launching arm 200 with the support 100 allowing rotation in the direction of rotation axis z is positioned at a first end of the launching arm 200 and the damping element 220 extends from a second end of the launching arm 200. Digital References

[0070] 100.support 110.plate 111.comma 112.launch zone 113.barrel support plate 200.arm z 200 .dimension of the arm in height 210.elongated member, x 210 .dimension of the elongated member in length y 210 .dimension of the elongated member in width z 210 .dimension of the elongated member in height z 220 .dimension of the damping element in height 210b.lower face 211.first recess 212.second recess 213.web, 213a.central wall 214.first wing 214a.first internal wall 214c.stop wall 215.second wing 215a.second internal wall 216.third wing 217.fourth wing 218.base 220.damping element 221.contact portion 221c.contact surface 220b.lower damping face 222.mounting portion 222b, 222c.mating surfaces 300.target 400.actuator x.extension direction (x) y.transverse direction (y) z.rotation axis direction (z) Az.rotation axis

Claims

1. A target launching device, comprising a support (100), a launching arm (200) and a tray (110), wherein the launching arm (200) is rotatably hinged relative to the support (100) on a rotation axis (Az) directed along the rotation direction (z), so as to be able to eject a target (300) arranged on the tray (110), and wherein the arm comprises: an elongate member (210) having: ▪a lengthwise dimension (x210) extending in an extension direction (x) perpendicular to the direction of the rotation axis (z), ▪a widthwise dimension (y210) extending in a transverse direction (y), perpendicular to the extension direction (x) and perpendicular to the direction of the rotation axis (z), ▪a height dimension (z210) extending in the direction of the rotation axis (z), - a damping element (220) mounted on the elongate member (210) and able to come into contact with the target (300), the device being characterised in that the elongate member (210) comprises at least one section along its lengthwise dimension having, in cross-section along a plane perpendicular to the extension direction (x), a first indentation (211) and a second indentation (212) arranged on either side of a core (213), the core (213) being directed in the rotation direction (z) and in that the damping element (220) is fastened in the first indentation (211).

2. Device according to the preceding claim, wherein the elongate member (210) comprises a first wing (214), a second wing (215), a third wing (216) and a fourth wing (217), the wings being directed in the transverse direction (y).

3. Device according to the preceding claim, wherein the first wing (214) comprises a first inner wall (214a), the second wing (215) comprises a second inner wall (215a) and the first indentation (211) extends in the extension direction (x) and is delimited by the first inner wall (214a), by the second inner wall (215a) and by a central wall (213a) extending from the first inner wall (214a) up to the second inner wall (215a).

4. Device according to claim 3, wherein the damping element (220) comprises a mounting portion (222) and a contact portion (221), so that the mounting portion (222) comprises coupling surfaces (222b, 222c) configured so as to be able to cooperate by coupling with the first inner wall (214a) and a stop wall (214c) located at an edge of the first wing (214).

5. Device according to any one of the preceding claims, wherein the damping element (220) is made of an elastomeric material which extends in the extension direction (x) and the elongate member (210) is made of an aluminium alloy.

6. Device according to any one of the preceding claims, wherein, in the rotation direction (z), the dimension of the arm (z200) is equal to the height dimension of the elongate member (z210).

7. Device according to any one of the preceding claims, wherein the elongate member (210) has a lower face (210b) and the damping element (220) has a lower damping face (220b) so that the lower face (210b) and the lower damping face (220b) are coplanar.

8. Device according to any one of the preceding claims, wherein the elongate member (210) comprises a section with a width variable and decreasing when moving away from the rotation axis (Az).

9. Device according to the preceding claim, wherein the contact portion (221) comprises a planar contact surface (221c), configured to be directed towards the inside of the rotational movement of the launching arm (200) during the phase of ejection of the target (300), and perpendicular to the transverse direction (y).

10. Device according to any one of the preceding claims, wherein the core (213) is a parallelepipedic plate comprising a midplane parallel to both the extension direction (x) and the rotation direction (z), and the elongate member (210) and a part having symmetry shape in relation to said midplane.

11. Device according to claim 3 alone or in combination with any one of the other claims, wherein the distance between the first inner wall (214a) and the second inner wall (215a) is greater than 4 mm.

12. Device according to claim 3 alone or in combination with any one of the other claims, wherein, in cross-section, on a plane perpendicular to the extension direction (x), the thickness of the core (213) is equal to the respective thicknesses of the four wings (214, 215, 216, 217), preferably equal to 2 mm.