Rocket for a rotating munition

Abstract

The invention relates to a rocket (1) for a gyroscopic munition, comprising a firing pin (10) and a primer (9) housed in a primer-carrying rotor (7) that rotates between a storage position where the primer is offset from the firing pin and a firing position where the primer is aligned with the firing pin. It includes a safety mechanism (B) equipped with two independent safety devices (4, 5) coupled to the rotor to maintain it in the storage position until two physical phenomena related to the firing of the munition occur. It further includes two independent drive elements (25, 26), reacting to centrifugal forces, to couple successively to the rotor and drive it in rotation, respectively, along a first section and then a second section from the storage position to the firing position, once the two safety devices are released. Figure 1

Description

Title of the invention: Rocket for a gyrating munition technical field

[0001] The present invention relates to a rocket for a gyroscopic munition, said rocket extending along a central axis, between a distal end provided with a cap and a proximal end provided with a base for assembling said rocket to a munition, said rocket comprising a striker, a primer provided in a primer-carrying rotor arranged to be mobile in rotation about an axis of rotation parallel to said central axis between at least one storage position in which said primer is offset with respect to said striker and an armed position in which said primer is aligned with said striker, and a safety mechanism provided with at least one safety device coupled to said primer-carrying rotor to maintain it in said storage position until the occurrence of at least one physical phenomenon related to the firing of said munition. Previous technique

[0002] The invention relates to gyro ammunition, which is fired from weapons with helical rifled barrels to impart a spin to the ammunition combined with a linear trajectory. The invention is particularly concerned with 40mm grenades, which are grenades that can be fired from a specific barrel but are no more powerful than hand grenades. 40mm grenades are standard. There are also 20mm and 37mm grenades for specialized weapons. The invention is, of course, not limited to this type of ammunition and extends to any other gyro ammunition or projectile, such as, for example, illuminating rounds, etc.

[0003] The rockets must perform the following two main functions: - to guarantee the safety of the ammunition and therefore the safety of its users, throughout the handling, storage, transport, deployment and use phases in the field, up to and including crossing a predetermined distance, called the safety distance; and - to guarantee the functioning of the munition once the safety distance has been crossed.

[0004] To this end, the rockets include a micromechanical device equipped with at least one safety device reacting to at least one, and preferably to two, independent physical phenomena related to the firing of said munition, in accordance with applicable standards. In the case of gyroscopic munitions, the two independent physical phenomena are, on the one hand, the linear acceleration of the projectile at the moment of firing and, on the other hand, the centrifugal force of the projectile at the moment of firing and during its flight.

[0005] This micromechanical device is particularly complex to manufacture, requiring a large number of parts to ensure its various functionalities. These parts must be manufactured to high standards of quality, reliability, and precision, far exceeding, for example, those used in a watch mechanism. Consequently, the cost of the fusees is high.

[0006] However, there is market demand for less expensive rockets, while still meeting the specifications and main requirements of applicable standards. Description of the invention

[0007] The present invention aims to overcome these drawbacks by proposing a rocket whose design has been completely rethought, implementing new technical solutions, both in the definition of the parts and in their manufacturing process, allowing several functionalities to be integrated into the same component, and to achieve reduced production costs, while guaranteeing the safety of operators during the assembly of the rocket, and that of users in accordance with the main requirements of the standards in force.

[0008] To this end, the invention relates to a rocket of the type indicated in the preamble, characterized in that the safety mechanism further comprises a motor device coupled to said primer-carrying rotor, arranged to react to the rotational speed of the munition, to use centrifugal effects during flight, to store radial kinetic energy, and to drive said primer-carrying rotor in rotation from said storage position to said armed position, as soon as said at least one safety device is lifted.

[0009] The motor device is advantageously arranged to drive said primer-carrying rotor in rotation over a determined angular stroke and comprises for this purpose at least two independent motor elements, including a first motor element and a second motor element, arranged to couple to said primer-carrying rotor successively, the first motor element driving said primer-carrying rotor in rotation over a first segment of rotation, and the second motor element taking over from the first motor element to drive said primer-carrying rotor in rotation over a second segment of rotation in order to cover the entire determined angular stroke of said primer-carrying rotor.

[0010] In a preferred embodiment of the invention, said primer-carrying rotor comprises at least a first cavity offset with respect to the center of gravity of said rotor and said central axis, arranged to contain said first drive element, and a second cavity offset with respect to the center of gravity of said rotor and said central axis, located from said first cavity by a distance less than or equal to the angular sector of said first rotation segment, and arranged to receive said second driving element. The driving elements can be made up of balls, although this example is not exhaustive.

[0011] Preferably, the safety mechanism comprises a safety-carrying plate on which said primer-carrying rotor is mounted and superimposed around said axis of rotation. Said safety-carrying plate may thus comprise a waiting housing containing said second motor element and arranged to communicate with said second cavity of the primer-carrying rotor when they are aligned to allow said second motor element to move back into said second cavity under the effects of a deceleration of the rocket during flight, or of any effect leading to its displacement (example: spring force, ...).

[0012] In the preferred embodiment, the safety mechanism includes a centrifugal safety device arranged to react to the rotational speed of the munition at the start of the shot and during flight, constituting said at least one physical phenomenon related to the firing of the munition, said centrifugal safety device comprising a centrifugal mass linked to the safety carrier plate by a flexible arm, and arranged to be radially mobile under the effects of the centrifugal force of the fuze between a locked position engaged with said primer-carrying rotor to prevent it from rotating, and an unlocked position releasing said primer-carrying rotor.

[0013] In addition, the safety mechanism includes an inertial safety device arranged to react to the linear acceleration of the munition at the start of the shot, constituting another physical phenomenon related to the firing of the munition, said inertial safety device comprising an inertial mass blocked between the primer-carrying rotor and a main well provided in said safety-carrying plate, and arranged to be axially mobile under the effects of the force generated by the linear acceleration of the fuze between a locked position engaged with said primer-carrying rotor to prevent it from rotating, and an unlocked position falling into said main well to release the primer-carrying rotor.

[0014] The inlet of the main well of the safety door plate may include retaining devices to resist the weight of said inertial mass up to a force related to the linear acceleration to move from the locked position to the unlocked position.

[0015] The safety carrier plate may include a secondary well angularly distant from the main well, and connected to the main well by a tunnel allowing the inertial mass to move under the effects of centrifugal force, and to move back up into the secondary well under the effects of sudden deceleration, to lock the primer carrier rotor and interrupt its rotational movement in the event of early impact of the munition before reaching a determined safety distance.

[0016] In the preferred embodiment of the invention, the safety mechanism further comprises a timing train coupled to said primer-carrying rotor for to regulate its rotational movement, said chronometric train comprising an escape wheel coupled to an oscillating anchor, and said primer-carrying rotor comprising a toothed sector meshed with a receiving pinion integral with the escape wheel, said toothed sector extending over an angle less than, equal to or greater than the determined angular stroke of said primer-carrying rotor. Brief description of the drawings

[0017] The present invention and its advantages will become more apparent from the following description of several embodiments given by way of non-limiting examples, with reference to the accompanying drawings, in which:

[0018] [Fig-1] is an exploded perspective view of a rocket according to the invention,

[0019] [Fig.2] is a top perspective view of the rocket safety mechanism according to [Fig.1],

[0020] [Fig.3] is a view from below of the rocket fairing according to [Fig.1],

[0021] [Fig.4] is an axial cross-sectional view of the rocket according to the [Fig.1] assembly and in storage position,

[0022] [Fig.5] is a top view of the safety mechanism of [Fig.2] in the storage position,

[0023] [Fig.6] is a perspective and cross-sectional view of the safety mechanism according to a VLVI section plane of [Fig.5],

[0024] [Fig.7] is a top view of part of the safety mechanism of [Fig.5], in a first phase of rotation of the primer-carrying rotor,

[0025] [Fig.8] is a top view of part of the safety mechanism of [Fig.5], in a second phase of rotation of the primer-carrying rotor,

[0026] [Fig.9] is a top view of part of the safety mechanism of [Fig.5], in a third phase of rotation of the primer-carrying rotor,

[0027] [Fig. 10] is an axial cross-sectional view of part of the safety mechanism of [Fig. 9],

[0028] [Fig. 11] is a top view of part of the safety mechanism of [Fig. 5], in a fourth and final phase of rotation of the primer-carrying rotor,

[0029] [Fig. 12] is a bottom view of the primer-carrying rotor and the rocket retaining plate [Fig. 1],

[0030] [Fig. 13] is an axial cross-sectional view of the rocket according to [Fig. 1] assembled and in the armed position, and

[0031] [Fig.14] is an enlarged view of a hidden detail of [Fig.13]. Description of the implementation methods

[0032] In the illustrated embodiments, identical elements or parts bear the same reference numbers. Furthermore, terms that have a relative meaning, such as Vertical, horizontal, right, left, front, back, above, below, etc., must be interpreted under normal conditions of use of the invention, and as shown in the figures. The X, Y, and Z axes are defined by an orthonormal coordinate system illustrated in [Fig. 1]. Furthermore, the geometric positions indicated in the description and claims, such as "perpendicular," "parallel," and "symmetrical," are not limited to the strict sense defined in geometry, but extend to geometric positions that are close, that is, that allow a certain tolerance within the technical field considered, without affecting the result obtained. This tolerance is notably introduced by the adverb "approximately," without this term necessarily being repeated before each adjective.

[0033] With reference to the figures, the rocket 1 according to the invention comprises four main sub-assemblies: - a basic structure A, - a regulated safety mechanism B, - a support structure C, and - a D-shaped headgear incorporating a percussion system.

[0034] The four main sub-assemblies are superimposed and secured along a central axis Z corresponding to the axis of rotation of the rocket 1 when it is assembled to a gyratory munition (not shown).

[0035] The basic structure A comprises a base 2 which provides the interface between the fuze 1 and a dedicated gyroscopic munition, for example in the form of a screw-on, push-fit, crimped fitting or any other removable or non-removable assembly means. It also comprises one or more O-rings 3 or any other similar sealing element to ensure a seal between the fuze 1 and the munition, and supports the safety mechanism B.

[0036] The safety mechanism B is regulated and ensures all the main functions of the rocket 1: - a safety function thanks to an integrated centrifugal safety device 4 and an inertial safety device 5; - a regulation function up to a predetermined safety distance thanks to a timing train 6; - a safety and arming function thanks to a primer-carrying rotor 7 offset from the central axis Z along an axis of rotation Z', driven by an innovative motor device 8 described later, engaging the timing train 6 and carrying a primer 9 aligned with a striker 10 only after crossing the determined safety distance. The safety mechanism B includes for this purpose a safety carrier plate 11, which fits into and is secured to the base 2, and carries all the components listed above.

[0037] The retaining structure C includes a retaining plate 12 which contains various specific shapes serving as a stop, housing and locking for the components of the safety mechanism B. It may also include locations for return elements 13 ensuring a so-called "graze mode" operation of the rocket 1 described later.

[0038] The cap D contains a striker-carrying cupola 14 which carries a striker 10 extending in the central axis Z of the rocket 1. Storage position

[0039] In the storage position shown in Figures 2, 4, 5 and 6, the primer-carrying rotor 7 is in a position where the primer 9 it contains is misaligned with the Z-axis of the firing pin 10. This position ensures that the primer 9 will not be initiated regardless of any events (drops, shocks, vibrations, temperature variations, etc.) experienced by the rocket 1. At least one, and in the illustrated example, two safety devices 4, 5 lock the position of the primer-carrying rotor 7 in this storage position, also called the safety position: - the centrifugal safety device 4, so named because it can only be lifted under the effects of the centrifugal force it experiences at the start of firing and during the flight of the munition, and - the inertial safety device 5, so named because it can only be activated under the effects of the linear acceleration it undergoes at the start of the firing of the munition.

[0040] The centrifugal safety device 4 is a functional component that can advantageously be integrated into the safety carrier plate 11 when it is manufactured by molding, injection, three-dimensional printing, sintering or similar in a synthetic, composite, metallic or similar material, chosen according to the specifications. The centrifugal safety device 4 comprises a centrifugal mass 15, substantially hammer-shaped, located at the end of a flexible arm 16, fixed to the safety carrier plate 11 at its end opposite the centrifugal mass 15. Thus, the centrifugal mass 15 is free to move radially in the XY plane, outwards from the plate 11, under the centrifugal effects experienced by the munition during its launch. It is therefore mobile between a locked position in which it rests on a stop 17, substantially L-shaped, provided on the primer carrier rotor 7 to prevent it from rotating ([Fig.5]), and an unlocked position escaping from the stop 17 to release the primer-carrying rotor 7. As long as the rocket 1 does not undergo centrifugal effects, the centrifugal safety device 4 remains in its initial locked position and constitutes a first rotational stop for the primer-carrying rotor 7. .

[0041] The inertial safety device 5 is a functional component consisting of an inertial mass 18, such as a ball or similar, interposed between the safety holder plate 11 and the primer rotor 7. During the assembly of the safety mechanism B, the inertial mass 18 is placed at the entrance of a main well 19 in the safety holder plate 11, from which it protrudes ([Fig. 6]). The primer rotor 7 is then assembled above it and has a main chamber 20 allowing the inertial mass 18 to be housed and to provide the second rotational stop for the primer rotor 7.

[0042] The inertial mass 18 is held between the two parts 7 and 11 by means of retaining devices 21 designed to withstand the weight of the inertial mass 18 during events such as drops, impacts, handling, etc. The retaining devices 21 may be molded into the safety carrier plate 11 and may consist of studs, lugs, or any other equivalent shapes, provided on all or part of the periphery of the main well opening 19 and capable of deforming under a certain force related to linear acceleration. Thus, the inertial mass 18 is free to move axially towards the bottom of the main well 19 under the effects of the linear acceleration experienced by the munition during its launch, which forces the retaining devices 21 through it.The inertial mass 18 can therefore move in a controlled manner between a locked position in contact with the primer-carrying rotor 7 to prevent it from rotating, and an unlocked position falling into the main well 19 to release the primer-carrying rotor 7. At the start of the blow

[0043] At the start of the shot, the munition on which the rocket 1 according to the invention is assembled undergoes two independent ballistic events: ■ A rotational speed exceeding 2000 rpm (minimum value given as a non-limiting example). This event generates significant centrifugal effects that act on the centrifugal mass 15, displacing it outwards from the safety mechanism B. This has the effect of removing the first stop and allowing the rotation of the primer carrier rotor 7 (see arrows F and R in [Fig. 5]). ■ An acceleration greater than 600g (minimum value given as a non-limiting example). This event has the effect of applying to the inertial mass 18 a force sufficient to make it pass the retaining devices 21 which hold it between the safety carrier plate 11 and the primer carrier rotor 7 in the storage position.

[0044] The inertial mass 18 is ejected from its storage position downwards in the main well 19 and travels through a tunnel 22 formed in the safety carrier plate 11, where, after being centrifuged, it positions itself opposite a secondary well 23 ([Fig. 6]). The secondary well 23 has retaining devices 21 similar to those of the main well 18, which will be breached by the inertial mass 18 in the event of a close impact, i.e., an impact that occurs before the end of the determined safety distance. The carrier rotor- The primer 7 has a secondary chamber 24 above the secondary well 23 to house the inertial mass 18 in case of ascent. This will have the effect of interrupting the rotation of the primer-carrying rotor 7 and keeping the rocket 1 in a safe, unarmed position.

[0045] Until the determined safety distance is crossed

[0046] Once the two safety devices 4 and 5 are raised, the primer-carrying rotor 7 is free to rotate and begin its alignment towards the armed position ([Fig.13]) via an innovative motor device 8. Innovative motor device

[0047] The purpose of the drive device 8 of the invention is to rotate the primer-carrying rotor 7 to move from the storage position to the armed position, once the two safety devices 4 and 5 are released, and over a controlled period of time allowing the ammunition to cross the predetermined safety distance. The drive device 8 is designed to drive the primer-carrying rotor 7 through a predetermined angular stroke, for example greater than or equal to 120°, without this value being limiting, using exclusively the driving force generated by the centrifugal energy of the ammunition, as described below, coupled with regulation generated by a simplified timing train 6, described later.

[0048] In the prior art, the primer-carrying rotor includes a centrifugal mass integrated into the rotor by design and eccentric, to offset the rotor's center of gravity from its axis of rotation and to use the centrifugal effects concentrated in the centrifugal mass as a driving force to move the rotor from its storage position to its armed position. In this configuration, the rotor's angular travel is necessarily limited by the extreme centrifugal position reached when the centrifugal mass is aligned with the rotor's center of gravity and the rocket's axis of rotation. It is therefore less than 180°, and more generally less than or equal to 120°.

[0049] In the invention, the primer-carrying rotor 7 does not have an integrated centrifugal mass, so that its center of gravity G is substantially coincident with its axis of rotation Z', although this position is not limiting. Other positions of the rotor's center of gravity G could be suitable. The innovative drive device 8 harnesses centrifugal energy via independent, offset drive elements 25 and 26, arranged to couple successively to the primer-carrying rotor 7 (Figures 7 to 11) and provide the necessary driving force over the entire determined angular stroke of the rotor, which can be equal to or greater than 120°. In the example shown, the drive device 8 comprises two drive elements 25 and 26, although this number is not limiting.A first drive element 25 is arranged to drive the primer-carrying rotor 7 over a first section of rotation (figures 7 to 9), and a second drive element 26 is arranged to take over from the first drive element 25 and drive. the primer-carrying rotor 7 on a second section of rotation (figures 9 to 11) in order to cover the entire angular stroke of said rotor, allowing the primer 9 to be aligned with the striker 10, corresponding to an armed position of the rocket ([Fig. 13]).

[0050] The drive elements 25 and 26 are made of balls or similar materials and may be identical or different, and of identical or different masses, depending on the driving force to be developed. The drive elements could also be made of other parts of different shapes but fulfilling the same function. The first drive element 25 is housed in a first cavity 27 of the primer-carrying rotor 7, eccentric with respect to the center of gravity G of the rotor. The second drive element 26 is located substantially below the first drive element 25, in a waiting recess 28 of the safety-carrying plate 11 (cavity and recess visible in [Fig. 10]).

[0051] As soon as the first driving element 25 is subjected to centrifugal effects, it wants to move towards the outside of the safety mechanism B (see arrow Fl in figures 7 to 9), and sets in motion the primer-carrying rotor 7. The rotation of the primer-carrying rotor 7 along the arrow R is regulated by an oscillating "anchor-escapement" torque of the timing train 6 (described later).

[0052] When the first motor element 25 reaches its extreme centrifugal position PCE, namely its alignment with the central axis Z of the rocket 1 and the axis of rotation Z' of the primer-carrying rotor 7 (dashed line on figures 7 to 9 and 11), it no longer produces motor effects on the primer-carrying rotor 7. Before reaching this extreme centrifugal position PCE, the second motor element 26, which was waiting, then enters a second cavity 29 of the primer-carrying rotor 7 under the effects of the deceleration of the rocket during the flight ([Fig.8]).

[0053] Subjected to centrifugal forces, the second engine element 26 adds its mass to the first engine element 25 and also tends to move outwards from the safety mechanism B (see arrow F2 in Figures 8, 9, and 11). When the first engine element 25 reaches its extreme centrifugal position PCE ([Fig. 9]), and under the effects of the rocket's deceleration during flight, it is ejected into an evacuation slot 30 in the retaining plate 12 (Figures 3 and 10). This first engine element 25 therefore no longer exerts any driving force on the primer-carrying rotor 7.

[0054] Meanwhile, the second drive element 26 has taken over in terms of motive power to complete the alignment of the primer-carrying rotor 7 on the striker 10. When the second drive element 26 arrives in the extreme centrifugal position PCE ([Fig. 11]), it finds itself under the first drive element 25 and the fuse 1 is armed ([Fig. 13]).

[0055] The rotational movement of the primer-carrying rotor 7 is stopped by a limit stop 31 of the retaining plate 12 against which a lug 32 of the primer-carrying rotor 7 is stopped (Figures 3 and 12). This limit stop 31 ensures alignment of the primer 9 with the striker 10, corresponding to the armed position of the rocket 1 ([Fig. 13]).

[0056] Simultaneously, a locking tab 33 integrated into the retaining plate 12 engages in a notch 34 in the primer-carrying rotor 7 to prevent it from coming out of its armed position ([Fig. 14]). The fuze 1 is ready to operate ([Fig. 13]). Chronometric train

[0057] The rocket 1 according to the invention may or may not include a timing train 6. The timing train 6 developed for the invention is very simplified compared to state-of-the-art timing trains. It has only one stage, which reduces the number of parts and the cost. To compensate for the reduction in the number of stages of the timing train 6, and consequently the reduction in braking on the primer-carrying rotor 7, it was necessary to lengthen the angular travel of the primer-carrying rotor 7. This lengthening required increasing the number of teeth on a toothed sector 38, and therefore the length of the toothed sector provided on the primer-carrying rotor 7 to engage the timing train 6.

[0058] In the exemplary embodiment, the timing train 6 comprises an escape wheel 35 engaging an oscillating anchor 36. The escape wheel 35 carries a driven pinion 37 which engages the toothed sector 38 provided on the periphery of the primer-carrying rotor 7. The toothed sector 38 extends over an angle that may be less than, equal to, or greater than the determined angular stroke of the primer-carrying rotor 7. As long as the timing train 6 engages the toothed sector 38, it regulates the rotation of the primer-carrying rotor 7, which is subjected to the centrifugal effects of its drive mechanism 8. As soon as the timing train 6 is no longer engaged with the toothed sector 38, the rotation of the primer-carrying rotor 7 is no longer regulated or braked, and the alignment of the primer 9 with the axis of the firing pin 10 is almost instantaneous under the driving effect of the second drive element 26. Operation upon direct impact

[0059] The deformation of the cap D under the effect of a direct impact causes the percussion of the primer 9 by the firing pin 10. The pyrotechnic chain of the munition is initiated. Operation in graze mode

[0060] In the event of a "graze" type impact, i.e. on the sides of the cap D, the energy of the impact may not be sufficient to deform the cap D and ensure that the operation of the fuze 1 is identical to that of a direct impact in the Z axis of the fuze 1. In this case, it is the return elements 13, for example three springs, which hold the assembly retaining plate 12 / rotor primer holder 7 / safety holder plate 11, pressed against the base 2, which will be compressed and ensure the stroke necessary for the penetration of the primer 9 by the firing pin 10.

[0061] The present invention is not limited to the embodiments described but extends to any modification and variant obvious to a person skilled in the art, within the limits of the appended claims. Furthermore, the technical features of the various embodiments and variants mentioned above may be combined, in whole or in part.

Claims

Demands

1. Rocket (1) for a gyroscopic munition, said rocket extending along a central axis (Z), between a distal end provided with a cap (D) and a proximal end provided with a base (2) for attaching said rocket to a munition, said rocket comprising a firing pin (10), a primer (9) provided in a primer-carrying rotor (7) arranged to be rotationally mobile about an axis of rotation (Z') parallel to said central axis (Z) between at least one storage position in which said primer (9) is offset from said firing pin (10) and an armed position in which said primer (9) is aligned with said firing pin (10), and a safety mechanism (B) provided with at least one safety device (4, 5) coupled to said primer-carrying rotor (7) to maintain it in said storage position until the occurrence of at least one physical phenomenon related to the firing of said munition,rocket characterized in that said safety mechanism (B) further comprises a motor device (8) coupled to said primer-carrying rotor (7), arranged to react to the rotational speed of the munition, to utilize centrifugal effects during flight, to utilize radial kinetic energy and to rotate said primer-carrying rotor (7) from said storage position to said armed position, as soon as said at least one safety device (4, 5) is lifted.

2. Rocket according to claim 1, characterized in that said motor device (8) is arranged to drive said primer-carrying rotor (7) in rotation over a determined angular stroke.

3. Rocket according to claim 2, characterized in that said motor device (8) comprises at least two independent motor elements (25, 26), of which a first motor element (25) and a second motor element (26), arranged to couple to said primer-carrying rotor (7) successively, the first motor element (25) driving said primer-carrying rotor (7) in rotation over a first segment of rotation, and the second motor element (26) taking over from the first motor element (25) to drive said primer-carrying rotor (7) in rotation over a second segment of rotation in order to cover the entire determined angular stroke of said primer-carrying rotor (7).

4. Rocket according to claim 3, characterized in that said primer-carrying rotor (7) comprises at least one first cavity (27) offset from a center of gravity (G) of said rotor and said central axis (Z), arranged to contain said first drive element (25), and a second cavity (29) offset from the center of gravity (G) of said rotor and said central axis (Z), distant from said first cavity (27) by a distance less than or equal to said first rotation segment, and arranged to receive said second drive element (26).

5. Rocket according to any one of claims 3 to 4, characterized in that said driving elements (25, 26) are made up of balls.

6. Rocket according to any one of claims 3 to 5, characterized in that said safety mechanism (B) comprises a safety carrier plate (11) on which said primer carrier rotor (7) is mounted and superimposed around said axis of rotation (Z').

7. Rocket according to claim 6, characterized in that said safety carrier plate (11) has a waiting housing (28) containing said second motor element (26) and arranged to communicate with said second cavity (29) of the primer carrier rotor (7) when they are aligned to allow said second motor element (26) to move back into said second cavity (29) under the effects of a deceleration of the rocket during flight.

8. Rocket according to claim 6, characterized in that said safety mechanism (B) comprises a centrifugal safety device (4) arranged to react to the rotational speed of the munition at the start of the shot and during flight, constituting said at least one physical phenomenon related to the firing of the munition, said centrifugal safety device (4) comprising a centrifugal mass (15) linked to the safety carrier plate (11) by a flexible arm (16), and arranged to be mobile radially under the effects of the centrifugal force of the rocket between a locked position engaged with said primer-carrying rotor (7) to prevent it from rotating, and an unlocked position releasing said primer-carrying rotor (7).

9. Rocket according to claim 6, characterized in that said safety mechanism (B) comprises an inertial safety device (7) arranged to react to the linear acceleration of the munition upon firing, constituting another physical phenomenon related to the firing of the munition, said inertial safety device (5) comprising an inertial mass (18) blocked between the primer-carrying rotor (7) and a main well (19) provided in said safety carrier plate (11), and arranged to be axially mobile under the effects of the force generated by the linear acceleration of the rocket between a locked position engaged with said primer carrier rotor (7) to prevent it from rotating, and an unlocked position falling into said main well (19) to release the primer carrier rotor (7).

10. Rocket according to claim 9, characterized in that the inlet of the main well (19) of the safety carrier plate (11) has retaining elements to resist the weight of said inertial mass (18) up to a force related to the linear acceleration to move from the locked position to the unlocked position.

11. Rocket according to claim 10, characterized in that the safety carrier plate (11) has a secondary well (23) angularly distant from the main well (19), and connected to the main well (19) by a tunnel (22) allowing the displacement of the inertial mass (18) under the effects of centrifugal force, and its ascent into the secondary well (23) under the effects of a sudden deceleration, to lock the primer carrier rotor (7) and interrupt its rotational movement in the event of early impact of the munition before reaching a determined safety distance.

12. Rocket according to any one of claims 1 to 11, characterized in that said safety mechanism (B) comprises a timing train (6) coupled to said primer-carrying rotor (7) to regulate its rotational movement, said timing train (6) comprising an escape wheel (35) coupled to an oscillating anchor (36), and said primer-carrying rotor (7) comprising a toothed sector (38) meshed with a receiving pinion (37) integral with the escape wheel (35), said toothed sector (38) extending over an angle less than, equal to or greater than the determined angular stroke of said primer-carrying rotor (7).

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