EP3660441B1 - Device for deploying a deployable element, in particular a handle, for a weapon system - Google Patents

Description

TECHNICAL AREA

The present invention relates to a device for deploying a deployable element for a weapon system.

STATE OF THE ART

More particularly, although not exclusively, the present invention applies to a weapon system, in particular to a mobile firing station, in particular of the type carried on the shoulder, such as a missile launcher or a launcher. rocket, which requires quick handling, by deploying a gripping element, such as a handle for example.

A handle of such a weapon system has a certain size. Also, to reduce this bulk, in particular during storage and transport of the weapon system when the latter is not in use, it is known to provide a handle which is folded in this situation, while being deployable. Such a deployable handle is capable of being brought from the folded position to a stable deployed position for its use and the handling of the weapon system.

In order to implement this deployment, a device is known with which an operator must carry out the following operations: press a button to unlock the movement of the handle which is initially locked in the folded position, then move the handle, in particular by rotation, to bring it into the deployed position, and finally lock it in this deployed position before it can be used.

• par le document US 2009/284963 , un dispositif de support déployable portatif qui peut notamment prendre la forme d'une valise comprenant des pieds et une perche de maintien rétractables. Ce document divulgue notamment un système de verrouillage des éléments rétractables, lesdits éléments pouvant être libérés par pression d'un bouton à ressort et être amenés par un utilisateur en position déployée par pivotement au moyen d'une charnière ; et
• par le document US 3 327 422 , un dispositif de bipied pour arme à feu, repliable le long du canon de ladite arme à feu. Ce bipied peut notamment être maintenu plaqué contre le canon de l'arme à feu au moyen d'un ressort ou verrouillé en position déployée par l'utilisateur.

Furthermore, we know:

• by document US 2009/284963 , a portable deployable support device which may in particular take the form of a suitcase comprising retractable legs and a holding pole. This document discloses in particular a locking system for the retractable elements, said elements being able to be released by pressing a spring button and being brought by a user into the deployed position by pivoting by means of a hinge; And
• by document US 3,327,422 , a bipod device for a firearm, folding along the barrel of said firearm. This bipod can in particular be held pressed against the barrel of the firearm by means of a spring or locked in the deployed position by the user.

The aforementioned usual deployment solution requires a relatively significant intervention by an operator and does not allow very rapid deployment.

This usual deployment solution is therefore not completely satisfactory.

DISCLOSURE OF THE INVENTION

The object of the present invention is to remedy this drawback, which is achieved by a deployable element and device for deploying said deployable element according to claim 1. It relates to a device for deploying a deployable element (or capable of being deployed) for a weapon system, making it possible to implement rapid deployment, at least partially automatic, with reduced intervention by an operator.

According to the invention, said deployment device comprises a support part, the deployable element is rotatably mounted on said support part and is connected via at least one elastic element to said support part, said element deployable comprises at least one pin, said pin being able to move along a curved guide of the support part and to take one or the other of two stable positions respectively in two housings provided in the support part , these stable positions corresponding respectively to a folded position and a deployed position of the deployable element, and at least said guide and said elastic element are configured to generate an automatic deployment of the deployable element to said deployed position as soon as the the deployable element is subjected to a rotation (from the folded position to the deployed position) whose angle is greater than or equal to a so-called unlocking angle.

Thus, thanks to the invention, as soon as the deployable element is pivoted (by an operator) from the folded position, by an angle corresponding to said unlocking angle, the remainder of the deployment to said deployed position (at know an important part of the deployment) is done automatically. Moreover, as this deployed position (reached at the end of the automatic deployment) is stable, no final locking is necessary.

Therefore, said deployment device allows rapid deployment of the deployment element, for example a handle of a missile launcher, with reduced intervention by the operator (consisting simply of bringing the deployable element beyond said locking angle) and a partially automatic deployment.

Said deployment device also has other advantages. In particular, as specified further below, it makes it possible in particular to hold load cases in logistics and to take up all the transverse forces in use, and it comprises a reduced number of components.

In a preferred embodiment, to generate the automatic deployment, said guide and said elastic element are configured so that the force of the deployable element on the support piece, generated by the elastic element, is located outside a friction cone created at the point of contact between the deployable element and the support part, that is to say at the point of contact of the pin on the curved guide.

dans laquelle inéquation :

• β est la valeur angulaire du cône de frottement par rapport à sa génératrice ;
• α est l'angle entre ladite force de l'élément déployable sur la pièce de support, générée par l'élément élastique, et la génératrice dudit cône de frottement ; et
• N est un coefficient de sécurité, supérieur à 1.

Advantageously, to generate said automatic deployment, at least said guide and said elastic element are configured so that the following inequality is satisfied: $$\mathrm{NOT}\mathrm{.}\mathrm{\beta }<\mathrm{\alpha }$$

in which inequality:

• β is the angular value of the friction cone with respect to its generatrix;
• α is the angle between said force of the deployable element on the support part, generated by the elastic element, and the generatrix of said friction cone; And
• N is a safety factor, greater than 1.

Furthermore, advantageously, the deployable element comprises two pins arranged on either side of said deployable element, the support piece comprises two curved guides, and each of said pins is able to move along a said curved guides of the support piece.

Furthermore, advantageously, the curved guide(s) have an arcuate shape between said two housings (defining the stable positions).

Moreover, advantageously, said deployable element is provided with at least one oblong slot, in which is mounted a pin fixed to the support piece, to allow rotation of the deployable element on said support piece. Preferably, said deployable element is provided with two oblong slots, in each of which is mounted each time a pin fixed to the support piece. In addition, advantageously, the support part is provided with leaf springs at the level of the ankle(s).

Furthermore, advantageously, said deployable element comprises a bevel between one end of the oblong slot and an edge of said deployable element.

Moreover, advantageously, said pin is a projecting element whose peripheral edge comprises a substantially semi-circular section.

In the context of the present invention, said deployment device can be applied to any type of mechanical element to be deployed (manually in the prior art) on a weapon system. In a preferred embodiment, said deployable element corresponds to one of the following elements: a gripping element such as a handle in particular, a stop, a sighting system.

The present invention also relates to a weapon system, which comprises at least one deployable element and a device for deploying said deployable element, such as that described above.

The present invention can be applied to various weapon systems, and more particularly although not exclusively to mobile, in particular portable, weapon systems.

In a preferred application, the weapon system corresponds to a missile launcher or a rocket launcher and/or said deployable element corresponds to one of the following elements of this weapon system: a gripping element such as a handle in particular, a stop, a sighting system, preferably with a handle.

BRIEF DESCRIPTION OF FIGURES

• La figure 1 est une vue latérale d'un mode de réalisation particulier d'un dispositif de déploiement d'un élément déployable correspondant à une poignée.
• La figure 2 est une vue, en perspective, d'une pièce de support du dispositif de déploiement de la figure 1.
• La figure 3 est une vue partielle, en perspective, d'une partie supérieure d'une poignée apte à être déployée par le dispositif de déploiement de la figure 1.
• La figure 4 est une vue schématique, agrandie et en perspective, d'une partie supérieure de la vue de la figure 3.
• La figure 5 est une vue schématique du dispositif de déploiement de la figure 1 lors du déploiement, destinée à expliquer le fonctionnement du déploiement automatique.
• La figure 6 est une vue schématique du dispositif de déploiement de la figure 1 dans une position déployée, permettant d'expliquer le fonctionnement du déploiement automatique en lien avec la figure 5.
• La figure 7 est une vue latérale du dispositif de déploiement dans une position repliée de la poignée, illustrant une étape initiale d'un déploiement.
• La figure 8 est une figure similaire à la figure 7, illustrant une étape intermédiaire du déploiement.
• La figure 9 est une figure similaire aux figures 7 et 8, illustrant une étape finale du déploiement.

The appended figures will make it clear how the invention can be implemented. In these figures, identical references designate similar elements.

• There figure 1 is a side view of a particular embodiment of a device for deploying a deployable element corresponding to a handle.
• There picture 2 is a view, in perspective, of a support part of the deployment device of the figure 1 .
• There picture 3 is a partial view, in perspective, of an upper part of a handle capable of being deployed by the deployment device of the figure 1 .
• There figure 4 is a schematic view, enlarged and in perspective, of an upper part of the view of the picture 3 .
• There figure 5 is a schematic view of the deployment device of the figure 1 during deployment, intended to explain how automatic deployment works.
• There figure 6 is a schematic view of the deployment device of the figure 1 in a deployed position, making it possible to explain the operation of the automatic deployment in connection with the figure 5 .
• There figure 7 is a side view of the deployment device in a folded handle position, illustrating an initial stage of a deployment.
• There figure 8 is a figure similar to figure 7 , illustrating an intermediate stage of the deployment.
• There figure 9 is a figure similar to figures 7 and 8 , illustrating a final stage of deployment.

DETAILED DESCRIPTION

The device 1 illustrating the invention and represented on the figure 1 is a device for deploying a deployable element 2 (that is to say an element suitable or intended to be deployed) for a weapon system 3, of which only a small part has been represented very schematically on the figure 1 .

The present invention can be applied to various weapon systems, and in particular to portable weapon systems, which require the deployment of a deployable element 2, and this in particular during its use.

In a preferred application, the weapon system 3 corresponds to a rocket launcher or a missile launcher, in particular an anti-tank missile or a short-range anti-aircraft missile. In addition, the deployable element 2 corresponds, for example, to one of the following elements of this weapon system: a gripping element such as a handle in particular, a stop, a sighting system, for example a sight .

In the example described below, with reference to the figures 1 to 9 , the deployable element 2 is a handle 4. The deployable handle 4 comprises a usual gripping (or gripping) zone 5, which is able to be taken in hand by an operator (not shown), in particular the operator planning to do operate the weapon system 3.

Said deployment device 1 also comprises, as shown in the figure 1 , a support piece 6.

This support part 6 can be either a part of the weapon system 3, or an independent part which is intended to be fixed on the weapon system 3 by a usual fixing means.

As shown on the figure 2 , the support piece 6 comprises a plate 7 slightly inclined at its center with respect to a mean plane Pm. The mean plane Pm of the plate 7 is orthogonal to a plane of symmetry P corresponding to a plane of symmetry of the deployment device 1. The support part 6 is also provided with two substantially flat side branches 8 and 9, arranged substantially parallel to the plane of symmetry P, symmetrically with respect to this plane of symmetry P, on either side of the latter. The support piece 6 thus has a shape rider general. The plate 7 can be attached to a part of the weapon system 3 or correspond to a part of the latter.

The deployable element 2 is mounted on the support part 6, so as to be able to pivot. To do this, the support piece 6 comprises two pegs 10 and 11 ( figure 1 and 2 ) each mounted on one of said branches 8 and 9, respectively on the internal face 8A, 9A of these branches 8 and 9.

On the figure 1 , And 7 to 9 , the support part 6 (visible in its details on the picture 2 ) is shown in thin line to illustrate a transparency allowing to see the details of the deployable element 2 mounted on this support part 6, in order to simplify the understanding of the deployment device 1.

In the following description, the internal adjective is determined towards the plane of symmetry P, on either side of said plane of symmetry P, as illustrated by arrows I1 and I2 on the figure 2 , and the external adjective is defined in reverse. In addition, the superior adjective is determined according to the meaning (illustrated by an arrow E on the figures 1 to 3 ) of the deployable element 2 towards the support part 6, and the lower adjective is determined according to the direction opposite to the direction E.

In the assembled position of the figure 1 , the pins 10 and 11 are inserted into oblong slots 12 and 13. Each of said oblong slots 12 and 13 is formed in an upper part of a branch 14, 15 of the deployable element 2. The two branches 14 and 15 planes are provided, on either side of the plane of symmetry P, at the upper part of the deployable element 2, as shown in the figures 3 and 4 .

The mounting of the pins 10 and 11 (fixed on the support part 6) in the two oblong slots 12 and 13 (of the deployable element 2) allows the rotation of the deployable element 2 with respect to said support part 6.

In addition, the deployable element 2 is linked via at least one elastic element 16 to said support piece 6. In the example shown in the figures, the elastic element 16 is a spring 17. This spring 17 comprises a loop 17A, 17B at each of its longitudinal ends, as shown in particular on the figures 5 and 6 . These loops 17A and 17B surround pins 18 and 19. Pin 18 is inserted into holes 20 ( picture 2 ) made in the support piece 6, and the pin 18 is inserted into holes 21 ( picture 3 ) practiced in the deployable element 2.

Furthermore, the deployable element 2 comprises two pins 22 represented on the figure 1 , 3 and 4 , which are arranged on either side of the deployable element 2, on the outer faces 14A and 15A ( picture 3 ) of the branches 14 and 15 of the deployable element 2. Only the pin 22 of the branch 15 is visible on these figure 1 , 3 and 4 .

The support piece 6 further comprises two guides 23 and 24 curves. The curved guides 23 and 24 represent, respectively, sections of a part of the peripheral edge of the branches 8 and 9 of the support part 6, as shown in the figure 2 .

Each of the curved guides 23 and 24 comprises a part 23A, 24A having the shape of an arc of a circle. This part 23A, 24A is defined between two housings, a housing 23B, 24B and a housing 23C, 24C. These housings 23B, 24B, 23C, 24C correspond to rounded recesses made in the peripheral edge of the branches 8 and 9, on either side of the arcuate part 23A, 24A.

Each pin 22 is able to move along the associated curved guide 23, 24 of the support part 6 and to take one or the other of two stable positions, respectively, in one or the other of the two housings (housing 23B, 24B on the one hand and housing 23C, 24C on the other hand) provided in the support part 6.

These stable positions correspond, respectively, to a folded position P1 ( figure 7 ) and a deployed position P2 ( figure 9 ) of deployable element 2.

In a particular embodiment, the support part 6 is provided with leaf springs 30 and 31 at the level of the pins 10 and 11, as represented on the picture 2 . Each spring blade 30 and 31 is formed in a branch 8, 9 of the support part 6. These spring blades 30 and 31 facilitate the insertion of the pins 10 and 11 (which can thus be pushed slightly outwards) in the oblong slots 12 and 13 of the support piece 6, and thus facilitate the mounting of the deployable element 2 on the support piece 6.

Furthermore, as shown in the figure 4 , the deployable element 2 comprises, on each of the branches 14 and 15, a bevel 27 between an upper end 28 of the oblong slot 12, 13 and an upper edge 29 of the deployable element 2. These bevels 27, of which only one is visible on the figure 4 , also facilitate the insertion of the pins 10 and 11 into the oblong slots 12 and 13 and thus the mounting of the deployable element 2 on the support part 6.

Moreover, in the particular embodiment represented in the figure 4 , each pin 22 is a projecting element, the upper peripheral edge of which comprises a section 25 substantially in a semicircle. The rest of its peripheral edge is not an arc of a circle, and is provided with a beveled zone 26. Of course, each pin 22 can also simply correspond to a projecting cylindrical section.

The deployment device 1, and in particular at least said guide 23, 24 curve and said elastic element 16 are configured (that is to say formed and arranged) so as to generate an automatic deployment of the deployable element 2 until to said deployed position P2 ( Picture 9 ), and this as soon as the deployable element 2 is subjected in the direction illustrated by an arrow H1 on the figure 7 (from the folded position P1 to the deployed position P2), to a rotation whose angle is greater than or equal to an unlocking angle θ0 ( figure 8 ). This rotation (or pivoting) is generated by an operator who presses, preferably manually, on the deployable element 2 in the direction illustrated by the arrow H1 on the figure 7 . The unlocking angle θ0 defines a unlocked position P3 (shown on the figure 8 ) of the deployable element 2. From this unlocking position P3, the end of the deployment up to the deployed position P2 of the figure 9 is carried out automatically, in the direction illustrated by an arrow H2 on the figure 8 .

In a preferred embodiment, to generate automatic deployment from the unlocked position P3 to the deployed position P2, the deployment device 1, and in particular the curved guides 23 and 24 and the elastic element 16, are configured so that the force F1 of the deployable element 2 on the support part 6, which is generated by the elastic element 16, is always located outside a friction cone C, as shown in the figures 5 and 6 respectively in an intermediate position P4 (corresponding for example to the unlocking position) and in the deployed position P2.

This friction cone C is created, in the usual way, at the point of contact PC between the deployable element 2 and the support part 6, that is to say at the point of contact of each pin 22 on the guide 23, 24 associated curve. This point of contact PC therefore moves during the rotation of the deployable element 2 with respect to the support part 6, as illustrated by an arrow J on the figure 5 . The friction cone C has a generatrix F2 which is defined along a direction normal to the tangent of the curve (of the guide 23, 24 curve) at the point of contact PC. The friction cone C has an angle β with respect to the generatrix F2. As for the force F1, it is defined from the point of contact PC parallel to the direction of the elastic element 16 (spring 17).

More specifically, to generate the automatic deployment, the deployment device 1 and in particular the curved guides 23 and 24 and the elastic element 16 are configured so that the following inequality is always satisfied: N.β<α,

In this inequality, α ( figure 6 ) is the angle between on the one hand said force F1 of the deployable element 2 on the support piece 6, generated by the elastic element 16, and on the other hand the generatrix F2 of said friction cone C. In addition, N is a safety factor which is greater than 1.

The operation of the deployment device 1, as described above, is as follows.

The deployable element 2, namely the handle 4, being in the folded state P1, as represented on the figure 7 , an operator pushes or pulls on the deployable element 2 in the direction illustrated by the arrow H1. As soon as the deployable element 2 passes the unlocking position P3, represented on the figure 8 , the deployment device 1 generates an automatic deployment of the deployable element 2 in the direction illustrated by the arrow H2, until it is brought into the deployed position P2 represented on the figure 9 .

Moreover, as in this deployed position P2, the pin 22 is located in the housing 24C, the deployed position P2 is stable and no final locking is necessary.

Thus, as soon as the deployable element 2 is pivoted (by an operator) from the folded position P1, by an angle corresponding to said unlocking angle θ0, the remainder of the deployment to said deployed position P2 (namely an very important part of the deployment) is done automatically.

In the context of the present invention, deployment means the displacement, by pivoting (or rotation on an arc of a circle) of the deployable element 2, from the folded position P1 to the deployed position P2. Of course, after use, the deployable element 2 can be brought back by an operator from the deployed position P2 to the folded position P1, in particular for transporting the weapon system.

Consequently, said deployment device 1 generates rapid deployment of the deployment element 2, for example a handle 4, with reduced operator intervention (consisting simply of bringing the deployable element beyond said locking angle ) and partially automatic deployment.

The deployment device 1 therefore allows quick handling of the weapon system 3, for example a mobile firing station carried on the shoulder or any other element requiring the integration of a quick and compact grip.

The deployment device 1 also makes it possible to achieve automatic positioning of the deployable element 2, in the deployed position P2, in which the weapon system 3 will be used, with a reduction in the number of movements of the operator which uses it.

In addition, the deployment device 1 makes it possible, by its design, to take up all the (transverse) forces on the plane normal to the axis of the deployable element 2, during its use.

Furthermore, thanks to its folded position P1 which is stable, due in particular to the arrangement of the pins 22 in the housings 23B and 24B, the deployment device 1 makes it possible to block the deployable element 2 in the event of shocks, so to avoid inadvertent deployment.

It therefore makes it possible to hold load cases, particularly in the logistics phase (storage and transport of the weapon system). This makes it possible to prevent deployment under a certain constraint in the logistics phase.

Furthermore, the number of components of the deployment device 1 is reduced, and this by more than 50% compared to a usual device. This reduction in the number of components also makes it possible to reduce the cost of the deployment device 1.

Claims (14)

1. A deployable element and device for deploying said deployable element for a weapon system, said deploying device comprising a support piece (6), said deployable element (2) being rotatably mounted on said support piece (6) and being connected by means of at least one elastic element (16) to said support piece (6), said deployable element (2) comprising at least one pin (22), said pin (22) being able to move along a curved guide (23, 24) of the support piece (6) and to adopt one or the other of two stable positions (P1, P2) respectively in two housings (23B, 24B; 23C, 24C) provided in the support piece (6), these stable positions respectively corresponding to a stowed position (P1) and a deployed position (P2) of the deployable element (2),
   characterised in that at least said guide (23, 24) and said elastic element (16) are configured to generate an automatic deployment of the deployable element (2) to said deployed position (P2) as soon as the deployable element (2) is subjected to a rotation, from the stowed position (P1) to the deployed position (P2), the angle of which is greater than or equal to a so-called unlocking angle (θ0)
2. The deployable element and deploying device according to claim 1, characterised in that, to generate the automatic deployment, said guide (23, 24) and said elastic element (16) are configured so that the force (F1) of the deployable element (2) on the support piece (6), generated by the elastic element (16), is located outside a friction cone (C) created at the point (PC) of contact between the deployable element (2) and the support piece (6).
3. The deployable element and deploying device according to claim 2,

   characterised in that, to generate the automatic deployment, at least said guide (23, 24) and said elastic element (16) are configured so that the following inequation is satisfied: $$\mathrm{N}\mathrm{.}\mathrm{\beta }<\mathrm{\alpha }$$

   

   inequation in which:

   - β is the angular value of the friction cone (C) with respect to its generatrix (F2);

   - α is the angle between said force (F1) of the deployable element (2) on the support piece (6), generated by the elastic element (16), and the generatrix (F2) of said friction cone (C); and

   - N is a safety coefficient, greater than 1.
4. The deployable element and deploying device according to any one of the preceding claims,
   characterised in that the deployable element (2) comprises two pins (22) arranged on either side of said deployable element (2), in that the support piece (6) comprises two curved guides (23, 24), and in that each of said pins (22) is able to move along one of said curved guides (23, 24) of the support piece (6).
5. The deployable element and deploying device according to any one of the preceding claims,
   characterised in that the curved guide or the curved guides (23, 24) have a shape (23A, 24A) in the form of a circular arc between said housings (23B, 24B; 23C, 24C).
6. The deployable element and deploying device according to any one of the preceding claims,
   characterised in that said deployable element (2) is provided with at least one oblong slot (12, 13), in which is mounted a peg (10, 11) fixed to the support piece (6), to allow the rotation of the deployable element (2) on said support piece (6).
7. The deployable element and deploying device according to claim 6, characterised in that said deployable element (2) is provided with two oblong slots (12, 13), in each of which is mounted each time a peg (10, 11) fixed to the support piece (6).
8. The deployable element and deploying device according to any one of claims 6 and 7,
   characterised in that the support piece (6) is provided with spring blades (30, 31) at the peg or the pegs (10, 11).
9. The deployable element and deploying device according to any one of the preceding claims,
   characterized in that said deployable element (2) comprises a bevel (27) between an end (28) of the oblong slot (12, 13) and an edge (29) of said deployable element (2).
10. The deployable element and deploying device according to any one of the preceding claims,
    characterised in that said pin (22) is a projecting element whose peripheral edge comprises a substantially semi-circular section (25).
11. The deployable element and deploying device according to any one of the preceding claims,
    characterised in that said deployable element (2) corresponds to one of the following elements: a gripping element (4), a stop, an aiming system.
12. A weapon system,
    characterised in that it comprises at least one deployable element (2) and one device (1) for deploying said deployable element (2), according to any of claims 1 to 11.
13. The weapon system according to claim 12,
    characterised in that it corresponds to one of the following: a missile launcher, a rocket launcher.
14. The weapon system according to any one of claims 12 and 13,
    characterised in that said deployable element (2) corresponds to one of the following elements of the weapon system (3): a gripping element (4), a stop, an aiming system.

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