EP3910280B1 - Device for detecting absence of mechanical barrier for a missile and missile comprising such a device - Google Patents

Description

TECHNICAL AREA

The present invention relates to a device for detecting the absence of a mechanical barrier for a missile and a missile comprising such a device.

STATE OF THE ART

Generally, the missiles are equipped with at least one DSA safety and armament device allowing the firing of the warhead of the missile. Generally, these safety and arming devices are provided with a device for detecting the missile exiting its launch tube.

These launch tube exit detection devices comprise a detection member, generally a rod (or a finger), intended to come into contact with the launch tube and more precisely with the inner surface of the launch tube. The rod, which is movable in translation in a direction radial relative to the missile, can assume different positions. Thus, when the rod is in contact with the launch tube, it assumes a given position and when it is no longer in contact with the launch tube, it assumes another given position.

Depending on the position of the rod, it is therefore possible to determine whether or not there is a mechanical barrier; in other words, in the application to a missile, whether the missile has left its launch tube or not.

• un premier dispositif de détection de sortie du missile de son tube de lancement qui comporte un organe de détection amovible qui est éjecté lorsque le missile est propulsé hors de son tube de lancement ; et
• un second dispositif de détection de sortie du missile de son tube de lancement qui comporte un organe de détection qui est maintenu sur la périphérie extérieure du missile après que celui-ci a été propulsé hors de son tube de lancement.

Various missile exit detection devices from the launch tube are known, and in particular:

• a first device for detecting when the missile exits its launch tube which comprises a removable detection member which is ejected when the missile is propelled out of its launch tube; and
• a second device for detecting the exit of the missile from its launch tube which comprises a detection member which is held on the outer periphery of the missile after it has been propelled out of its launch tube.

• dans le premier cas, l'organe de détection est éjecté avec une puissance variable selon les utilisations, ce qui peut représenter un danger pour son environnement immédiat (personnes ou systèmes situés à proximité) ; et
• dans le second cas, l'organe de détection n'est pas éjecté mais il est maintenu sur la périphérie extérieure du missile avec une partie saillante, ce qui peut représenter une gêne en créant notamment une traînée aérodynamique ou en faisant obstacle à un objet qui passerait à proximité.

Such launch tube exit detection devices have the drawback of having a detection member which becomes a troublesome element once the missile has left its launch tube. In effect :

• in the first case, the detection member is ejected with a variable power depending on the uses, which can represent a danger for its immediate environment (people or systems located nearby); and
• in the second case, the detection member is not ejected but is held on the outer periphery of the missile with a protruding part, which can represent a hindrance by creating in particular an aerodynamic drag or by obstructing an object which would pass nearby.

These usual solutions are therefore not completely satisfactory.

Moreover, we know from the document US-2,704,033 a priming device for a projectile and in particular a rocket.

DISCLOSURE OF THE INVENTION

The object of the present invention is to remedy the aforementioned drawbacks, by proposing a device for detecting the exit of a missile from its launch tube, and more generally a device for detecting the absence of a mechanical barrier for a missile, said device comprising at least a rod constrained by a first elastic element and provided with a free end capable of coming into contact with the mechanical barrier

• une position dite entrée initiale, dans laquelle la tige est maintenue en position stable entre, d'une part la came, et d'autre part la barrière mécanique ;
• une position dite sortie, dans laquelle est amenée la tige sous l'action de la came par un déplacement dans le sens de l'extrémité libre, en l'absence de la barrière mécanique ; et
• une position dite entrée terminale, dans laquelle est amenée la tige sous l'action du premier élément élastique, après libération du déplacement de la tige par la came.

According to the invention, the device further comprises at least one cam constrained by a second elastic element, said rod and said cam being configured so that the rod can assume one or the other of the following positions:

• a so-called initial entry position, in which the rod is held in a stable position between, on the one hand the cam, and on the other hand the mechanical barrier;
• a so-called extended position, in which the rod is brought under the action of the cam by a movement in the direction of the free end, in the absence of the mechanical barrier; and
• a so-called terminal entry position, into which the rod is brought under the action of the first elastic element, after release of the movement of the rod by the cam.

Thanks to this device, any nuisance likely to be caused by the rod, as described previously, is therefore avoided. Indeed, when the rod is in the terminal entry position, it is in a position specified later where it no longer presents a danger to its environment or a hindrance to the proper functioning of the missile, as specified above.

In addition, advantageously, the device for detecting the absence of a mechanical barrier comprises at least one activatable detection element, configured to be activated when the rod assumes the terminal entry position.

Furthermore, in a particular embodiment, the detection element is activated by the rod or by the cam, when said rod assumes the terminal input position. In another embodiment, the device for detecting the absence of a mechanical barrier comprises an additional cam, called an auxiliary cam, integral with said cam and the detection element is configured to be activated by said auxiliary cam.

In a particular case of the previous embodiment, the device for detecting the absence of a mechanical barrier comprises at least one elastically constrained priming finger as well as an opening made on a peripheral part of the auxiliary cam, said priming finger is part of the sensing element and said trigger finger and said aperture are configured and positioned such that the trigger finger lodges in the aperture when the rod assumes the end-in position.

Furthermore, in a particular embodiment, the mechanical barrier detection device comprises at least one sealing element arranged at the free end of the rod as well as a base comprising a bore capable of receiving said sealing element when said rod assumes the terminal entry position.

This configuration makes it possible to make the missile impermeable to a large majority of the impurities that it is likely to encounter during its trajectory.

The present invention also relates to a missile. According to the invention, said missile comprises at least one device for detecting the absence of a mechanical barrier such as that described above.

In a first embodiment, the missile comprises a launch tube exit detection device and an initialization chain for the warhead of said missile, said launch tube exit detection device corresponding to said absence of mechanical barrier described above.

In a particular embodiment of this first embodiment, the missile comprises an initialization chain for a warhead and a device for detecting the absence of a mechanical barrier comprising at least one elastically constrained priming finger as described above , said priming finger being capable of triggering the initialization chain when it lodges in the opening provided for this purpose of the auxiliary cam.

In a second embodiment, as a variant or in addition to said first embodiment, the missile comprises a holding system which comprises at least one launch tube exit detection device as mentioned above and at least one holding element arranged at the free end of the rod of said at least one of said devices, said holding element being capable of coming into contact with the mechanical barrier.

Furthermore, in a particular embodiment of this second embodiment, the missile comprises a holding system comprising a single holding element and a plurality of devices for detecting the absence of a mechanical barrier, such as the one described above, the end of each of said devices being connected to said holding element.

Advantageously, the missile can comprise a plurality of holding systems.

In a first embodiment of the embodiment described above, the holding element corresponds to a strip.

In a second embodiment of the previous embodiment, the holding element corresponds to a pad.

Moreover, in a particular embodiment, the missile comprises at least one groove capable of receiving the holding element when the rod of the mechanical barrier absence detection devices take the terminal input position.

Thus, the missile has a launch tube exit detection device capable of triggering the retraction or deployment of holding or guiding elements, such as strips or pads, so that the various elements do not interfere with the proper functioning of said missile when it leaves the launch tube.

BRIEF DESCRIPTION OF FIGURES

• The figures of the appended drawing will make it clear how the invention can be implemented. In these figures, identical references designate similar elements.
• The figure 1 schematically illustrates an example of a device for detecting the absence of a mechanical barrier comprising a rod which assumes an initial input position.
• The figure 2 schematically illustrates the example of the device for detecting the absence of a mechanical barrier of the figure 1 , in which the rod assumes an extended position.
• The picture 3 schematically illustrates the example of the device for detecting the absence of a mechanical barrier of the figure 1 , wherein the stem assumes a terminal input position.
• The figures 4A and 4B schematically illustrate an example of a device for detecting the absence of a mechanical barrier comprising a detection element which is a trigger finger, the rod taking, respectively, the initial input position and the final input position.
• The figure 5 schematically illustrates an example of a device for detecting the absence of a mechanical barrier comprising a detection element.
• The figure 6 schematically illustrates an example of a missile in its launch tube, comprising a device for detecting the absence of a mechanical barrier.
• The figure 7 schematically illustrates an example of a missile in its launch tube, comprising a holding system.

DETAILED DESCRIPTION

The device 1, represented schematically on the figure 1 and making it possible to illustrate the invention, has the objective of detecting the absence of a mechanical barrier 2, which can correspond to any solid surface. This device 1 is intended to be installed on a missile M, and in this case, the mechanical barrier 2 is, preferably, the launch tube 16 of said missile M.

The term missile is understood to mean any self-propelled flying object which can be guided over all or part of its trajectory, by self-guiding or remote-guiding, and capable of carrying at least one warhead, in particular explosive or pyrotechnic. It may in particular be an anti-tank missile, fired from a helicopter or a drone. It can also be a medium-range missile, fired from the ground.

The device 1 comprises a support element, called the base 3 which comprises, in particular, usual fixing elements (not shown) configured to fix the said device 1 to the missile M. The base 3 can also be fixed directly on the warhead of the missile M. This base 3 is provided with a bent part 3a comprising at least one opening capable of receiving at least one bearing element 4. The latter is intended to receive at least one rod 5, said rod 5 being able to slide in said element of level 4.

The rod 5 has a longitudinal axis, denoted X, and the missile M has a longitudinal axis, denoted Y ( figures 6 and 7 ). Device 1 is positioned on missile M such that the X axis is oriented radially to the Y axis.

• une extrémité 5a, dite libre, orientée selon l'axe X dans le sens illustré par une flèche E sur les figures 1 à 3 notamment, vers l'extérieur du missile M et apte à venir au contact de la barrière mécanique 2 ; et
• une extrémité 5b, orientée selon l'axe X dans le sens illustré par une flèche I, vers l'intérieur du missile M.

In addition, rod 5 has two ends:

• an end 5a, called free, oriented along the axis X in the direction illustrated by an arrow E on the figures 1 to 3 in particular, towards the outside of the missile M and capable of coming into contact with the mechanical barrier 2; and
• an end 5b, oriented along the X axis in the direction illustrated by an arrow I, towards the inside of the missile M.

In addition, the device 1 also comprises an elastic element 7 intended to elastically constrain the rod 5 with respect to the base 3. For this purpose, the rod 5 comprises a collar 6 at its end 5b. In addition, the bent part 3a is provided with a flat surface parallel to the collar 6, capable of receiving the elastic element 7 in support. The elastic element 7 is arranged around the rod 5 so as to come to bear on the collar 6 on the one hand and on the flat surface of the bent part 3a on the other hand. The elastic element 7 is thus compressed between the collar 6 and the bent part 3a. Consequently, the rod 5 is elastically constrained in translation along the axis X, the elastic element 7 exerting on said rod 5 a force in the direction illustrated by the arrow I.

The device 1 also comprises at least one cam 8, pivotally linked to the base 3. This cam 8 is constrained in torsion with respect to the base 3 by an elastic element 9, shown in dotted lines on the figure 1 , 2 and 3 . The elastic element 9 is configured to exert a torque on the cam 8, oriented in the direction indicated by an arrow R on the figure 2 . Furthermore, cam 8 has a free end 8a able to come into contact with end 5b of rod 5. The dimensions and shape of cam 8 are such that surface 8a of said cam 8 comes into contact with the surface of the end 5b of the rod 5 when the cam 8 pivots on its axis in the direction of the arrow R. The cam 8 is therefore configured to exert a force on the rod 5 in the direction illustrated by the arrow E.

The base 3 also comprises a projecting element forming an abutment 10 ( figure 1 and 3 ). In addition, the cam 8 is provided with a projecting element 8b capable of coming into contact with the stop 10 when the cam 8 pivots around its axis in the direction indicated by the arrow R. The shape 8b is configured on the cam 8 so that said cam 8 is locked in rotation by stop 10 when it assumes a position described below.

In a preferred embodiment, the device 1 is intended to detect the exit of the missile M from the launch tube 16. The method of detecting the exit of the missile M from the launch tube 16 is implemented in three stages, different elements of the device 1, in particular rod 5 and cam 8, taking a given position for each of these steps. The figure 1 , 2 and 3 illustrate, respectively, the three successive data positions P1, P2 and P3.

In position P1, called the initial entry position and illustrated on the figure 1 , the missile M is installed in the launch tube 16. The rod 5, pushed by the cam 8, is in contact with the mechanical barrier 2, namely the inner wall 16a of the launch tube 16. In this position, the rod 5 is elastically constrained by the elastic element 7 in the direction illustrated by the arrow I, and by the elastic element 9, through the cam 8, in the direction illustrated by the arrow E. However, the elastic element 9 is configured to exert, via the cam 8, a greater force on the rod 5 than that exerted by the elastic element 7 on the rod 5. The rod 5 is therefore forced to bear against the mechanical barrier 2 and assumes a position stable between cam 8 and mechanical barrier 2.

In position P2, called the extended position and illustrated on the figure 2 , at least part of the missile M comprising the device 1 has just been propelled out of the launch tube 16. There is therefore a relative displacement of the missile M with respect to the launch tube 16, as illustrated by an arrow D .The launch tube 16 is shown in dashes on the picture 2 to indicate that it is not in the same plane as the rest of the picture 2 . Rod 5 is therefore no longer in contact with mechanical barrier 2. Mechanical barrier 2 no longer blocks rod 5 in translation, and cam 8 therefore forces said rod 5 to move in the direction illustrated by arrow E, by pivoting around its axis in the direction shown by the arrow R.

Once cam 8 has pushed rod 5 into position P2, said cam 8 continues to pivot until it reaches stop 10. However, cam 8 is configured to release the translation of rod 5 after said cam 8 has pivoted in the direction of arrow R, beyond position P2. The rod 5 no longer being subjected to the force of the cam 8, the elastic element 7 forces said rod 5 to move in the direction illustrated by the arrow I. The rod 5 then penetrates completely into the missile M, and is brought into position P3, called the terminal entry position, illustrated on the picture 3 .

In this position P3, the rod 5 does not protrude from the missile M outwards and presents no discomfort. Moreover, a device 1 as described previously does not eject any part during its use, since the rod 5 is retracted into the missile M once the latter has left the launch tube 16.

Furthermore, said device 1 is autonomous, since it does not require the use of an energy source such as a power supply or a pyrotechnic device. Only the mechanical energy provided by the elastic elements 7 and 9 is necessary to set in motion the various elements of the device 1 generating the retraction of the rod 5.

In a preferred embodiment, shown in more detail in the figures 4A and 4B , the device 1 comprises an additional cam, called auxiliary cam 12. This auxiliary cam 12 is integral with the cam 8, for example via an axis, and is therefore capable of pivoting with respect to the base 3 with said cam 8.

Furthermore, in this preferred embodiment, the device 1 comprises a detection element 26, and a trigger finger 13 of longitudinal axis Z which is part of this detection element 26. The trigger finger 13 is housed in a blind hole 22, said hole 22 being made in the base 3. This hole 22 is formed and located such that the opening 22a (or mouth) of the blind hole 22 is facing a peripheral surface 12a of the auxiliary cam 12. Furthermore, an elastic element 21, for example a compression spring, is positioned at the bottom of the hole 22 so as to exert a force on the end of the priming finger 13, in the direction of the bottom from hole 22 towards opening 22a of said hole 22. Priming finger 13 is thus elastically constrained by elastic element 21 against peripheral surface 12a of auxiliary cam 12.

Furthermore, the auxiliary cam 12 has an opening 23, for example also a blind hole, on the peripheral surface 12a. This opening 23 is formed and located so that its mouth 23a is opposite the opening 22a so that the opening 23 is able to receive the priming finger 13, when the auxiliary cam 12 pivots in the direction illustrated by the arrow R and takes a given position. This given position corresponds to the situation where the elements of the device 1 take the position P3 when the missile M has left the launch tube 16.

Moreover, in a preferred embodiment, the missile M is provided with a warhead 17 and an initialization chain 18 of said warhead 17, represented on the figure 6 . The priming finger 13 is configured to be able to trigger the initialization chain 18 when it slides in the opening 23.

Thanks to the priming finger 13, the device 1 is able to trigger the initialization chain 18 of a warhead 17 of a missile M in the absence of the mechanical barrier 2.

In addition, the realization of the priming finger 13, as described above, has the advantage of allowing great flexibility as regards the positioning of said priming finger 13 with respect to the auxiliary cam 12. Indeed, the priming finger 13 can take a plurality of angular positions around the axis of rotation of the auxiliary cam 12. The plane of the priming finger 13, defined by the axes X and Z, can also take a plurality of orientations angular relative to the plane orthogonal to the Y axis of the missile M. Indeed, depending on the position and orientation of the priming finger 13, the shape of the auxiliary cam 12 can be configured so that the peripheral surface 12a is facing the priming finger 13. In addition, instead of being made in a simple cylindrical shape, as shown in the example of figures 4A and 4B , the auxiliary cam 12 can be made with a truncated cone shape and thus allow the priming finger 13 to be oriented at a given angle with respect to the plane orthogonal to the Y axis.

Such flexibility as to the positioning of the priming finger 13, which corresponds to a means of detecting the absence of a mechanical barrier, allows the implementation of the device 1 on a wide range of missiles. This flexibility also allows greater freedom with regard to the layout of the warhead(s) 17 ( figure 6 ) and their initialization string 18 ( figure 6 ) on the missile M.

In a particular embodiment, as a variant of the previous embodiment, the detection element 26 comprises a detection means 11 represented very schematically on the figure 5 . The detection means 11 can be activated and is configured to emit a signal S when the elements of the device 1 take the position P3. The signal S can match, in particular, to a mechanical control capable of triggering an initialization chain of a warhead, or the deflection of elements of the missile M, such as usual wing elements or deflectors (or even the closing of a circuit electric due to the rotation of the cam 8 or the translation of the finger 5).

In a first embodiment of the previous embodiment, the detection element 26 is configured to be activated by the rod 5 when the latter assumes the position P3. The rod 5 is, for example, provided with a projecting part or with an added part (not represented on the figure 5 ) capable of activating the detection element 26.

In a second embodiment of the previous embodiment, the detection element 26 is configured to be activated by the cam 8 when the rod 5 takes the position P3. The cam 8 is, for example, provided with a projecting part or with an opening located on its periphery (such as, in particular, the opening 23 represented on the figures 4A and 4B ) capable of activating the detection element 26.

Furthermore, in a third embodiment of the previous embodiment, the detection element 26 is configured to be activated by the auxiliary cam 12 when the latter takes the position P3. The auxiliary cam 12 is, for example, provided with a projecting part or with an opening located on its periphery, such as the opening 23 represented on the figures 4A and 4B , capable of activating the detection element 26.

The detection element 26, whether in the embodiment with the priming finger 13 associated with the opening 23 or in the more general embodiment of the detection means 11, has the advantage of decoupling the ( possible) movements of the detection element 26 of parasitic movements (possible) of the mechanical barrier 2. Indeed, the mechanical barrier 2 can, for example, transmit vibrations or jolts to the rod 5 when the missile M is mounted in the launch tube 16. These movements are only transmitted to the cam 8 (and if necessary to the auxiliary cam 12), but not to the detection element 26 (such as the priming finger 13). This has the effect of avoiding in particular preventing deterioration of the detection element 26, or false detection on the part of of the latter and therefore (in the extreme case) an untimely triggering of the warhead 17 of the missile M.

In another embodiment, in addition to the previous embodiments and shown in the examples of figure 1 , 2 and 3 , the bent part 3a of the base 3 has a bore 14 on its face oriented in the direction illustrated by the arrow E. In addition, the rod 5 is provided, at its free end 5a, with a sealing element 15 , for example an O-ring. Bore 14 is configured in such a way as to be able to accommodate sealing element 15. Thus, when rod 5 assumes position P3, sealing element 15 is housed in bore 14.

The sealing element 15 thus prevents a liquid or dust from entering the missile M. This embodiment also makes it possible to dampen any possible rebound of the rod 5, during retraction, and also to limit the vibrations of said rod 5 when it is in position P3.

Device 1, as described above, is therefore intended to be mounted on a missile M. In this case, device 1 is preferably a device for detecting the exit of missile 1 from its launch tube 16. It It can also be a device for detecting the absence of another element, in particular of support, for example a rail intended to receive or carry the missile M while waiting for it to be fired.

The figures 6 and 7 illustrate two examples of a weapon system 25. The weapon system 25 comprises the missile M provided with at least one device 1, the launch tube 16, and all usual means of propulsion and launch of such a missile M, said usual means not being represented on the figure 6 and 7 .

The examples of figures 6 and 7 respectively represent two particular embodiments of the weapon system 25 provided with the missile M

In the first embodiment, schematically illustrated in the figure 6 , the weapon system 25 therefore comprises, in particular, the missile M provided with a device 1, as well as the warhead 17 and the initialization chain 18 capable of triggering said warhead 17.

When the missile M is propelled out of the launch tube 16, various elements of the device 1 take the position P3, as described above, and activate the detection element 26 (not shown in the figure 6 ). Element 11 in turn activates initialization chain 18 thus priming warhead 17 of missile M.

In a preferred embodiment of this embodiment, the priming finger 13 (not shown in the figure 6 ) forms part of the detection element 26. In this case, the initialization chain 18 of the warhead 17 of the missile M is activated by the priming finger 13 (which functions as described above with reference to the figures 4A and 4B ).

Furthermore, in the second embodiment, as a variant or in addition to said first embodiment, which is illustrated schematically in the figure 7 , the weapon system 25 comprises, in particular, a missile M provided with a holding system 24. This holding system 24 comprises at least one device 1, and at least one holding element 19 arranged at the end 5a of the rod 5 and able to come into contact with the inner wall 16a of the launch tube 16.

When the missile M is installed in the launch tube 16, the retaining element 19 is pressed against the inner wall 16a of the launch tube 16. As soon as the missile M is propelled out of the launch tube 16, various elements of the device 1 take position P3. The rod 5 then penetrates completely into the missile M, carrying with it the holding element 19.

In a particular embodiment of the previous embodiment, illustrated in the figure 7 , the holding element 19 corresponds to a strip. By strip is meant a longitudinal element capable of coming into contact with the inner wall 16a of the launch tube 16 in order to perform a functional action for the missile M, such as a guiding action during the propulsion of said missile M For example, the inner wall 16a of the launch tube 16 can be provided with the usual support or guide elements such as grooves, tabs, or guide fingers, capable of receiving the ruler to form a system of guidance.

Preferably, the holding system 24 comprises a plurality of holding elements 19 distributed for example around the outer face of the missile M. Thus, the holding system 24 can guide the missile M out of the launch tube 16 during the propulsion phase, and the holding element(s) 19 are retracted into the missile M after said missile M has left said launch tube 16.

In addition, for each holding element 19, the missile M is provided, on its peripheral surface, with a groove 20 capable of receiving said holding element 19 so that the latter does not protrude from said missile M in the retracted position.

The missile M therefore has a holding system 24 that is retractable in the throat 20 when said missile M has left the launch tube 16, and does not include any protruding element likely to represent a hindrance to the proper functioning of said missile M.

In another particular embodiment (not shown) of the previous embodiment, the holding element corresponds to a pad. By pad is meant one or more elements of variable shapes and sizes, generally made of elastic material, intended, in particular, to hold the missile M or part of the missile M in place in a damped manner, and thus to protect it from shocks. Such a holding system corresponds to a damping system and is retractable, in the same way as for the previous embodiment.

Claims (15)

1. A device for detecting absence of a mechanical barrier for a missile, said device (1) comprising at least one rod (5) constrained by a first elastic element (7) and provided with a so-called free end (5a) capable of coming into contact with a mechanical barrier (2),
   characterised in that it also comprises at least one cam (8) constrained by a second elastic element (9), said rod (5) and said cam (8) being configured so that the rod (5) can assume one or other of the following positions:

   - a position referred to as the initial entry (P1), in which the rod (5) is held in a stable position between the cam (8) on the one hand and the mechanical barrier (2) on the other hand;

   - a position referred to as the exit (P2), in which the rod (5) is brought under the action of the cam (8) by a displacement in the direction (E) of the free end (5a), in the absence of the mechanical barrier (2); and

   - a so-called terminal entry (P3), in which the rod (5) is brought under the action of the first elastic element (7), after release of the displacement of the rod (5) by the cam (8).
2. The device according to claim 1,
   characterised in that it comprises at least one activatable detection element (26), configured to be activated when the rod (5) assumes the terminal entry position (P3).
3. The device according to claim 2,
   characterised in that the detection element (26) is configured to be activated by one of the following:

   - the rod (5);

   - the cam (8).
4. The device according to claim 2,
   characterised in that it comprises an additional cam, referred to as an auxiliary cam (12), integral with said cam (8), and in that the detection element (26) is configured so as to be activated by the auxiliary cam (12).
5. The device according to claim 4,
   characterized in that it comprises at least one elastically constrained initiating finger (13) and an opening (23) provided on a peripheral portion (12a) of the auxiliary cam (12), and in that said initiating finger (13) forms part of the detection element (26) and in that said initiating finger (13) and said opening (23) are configured and positioned so that the initiating finger (13) is housed in the opening (23) when the rod (5) assumes the terminal entry position (P3).
6. The device according to any one of the preceding claims,
   characterised in that it comprises at least one sealing element (15) arranged at the free end (5a) of the rod (5) as well as a base (3) comprising a bore (14) capable of receiving said sealing element (15) when said rod (5) takes up the terminal entry position (P3).
7. A missile,
   characterised in that it comprises at least one device (1) according to any one of claims 1 to 6.
8. The missile according to claim 7, said missile (M) comprising a device for detecting (1) a launch tube exit and an initialization chain (18) of a warhead (17), characterized in that said device for detecting a launch tube exit corresponds to said device (1) according to any one of claims 1 to 6.
9. The missile according to claim 8, comprising a device (1) according to claim 5, characterized in that the initiating finger (13) is adapted to trigger the initialization chain (18) of the warhead (17) of said missile (M), when it is housed in the opening (23) of the auxiliary cam (12).
10. The missile according to any one of claims 7 to 9, comprising at least one support system (24),
    characterised in that said support system (24) comprises at least one device (1) according to any one of claims 1 to 6 and at least one support element (19) arranged at the free end (5a) of the rod (5) of said at least one device (1), said support element (19) being able to come into contact with the mechanical barrier (2).
11. The missile according to claim 10,
    characterized in that the support system (24) comprises a single support element (19) and a plurality of devices (1) according to any one of claims 1 to 6, the free end (5a) of the rod (5) of each of said devices (1) being linked to said support element (19).
12. The missile according to any one of claims 10 and 11,
    characterised in that it comprises a plurality of support systems (24).
13. The missile according to any one of claims 10 to 12,
    characterised in that it comprises at least one groove (20) capable of receiving the support element (19) when the rod (5) of the device(s) (1) for detecting the absence of a mechanical barrier takes up the terminal entry position.
14. The missile according to any one of claims 10 to 13,
    characterised in that the support element (19) corresponds to a strip.
15. The missile according to any one of claims 10 to 13,
    characterised in that the support element corresponds to a pad.

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