EP0566469A1 - Safety and arming device for the fuse of a projectile comprising an anti-vibratory means - Google Patents

Safety and arming device for the fuse of a projectile comprising an anti-vibratory means Download PDF

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Publication number
EP0566469A1
EP0566469A1 EP93400950A EP93400950A EP0566469A1 EP 0566469 A1 EP0566469 A1 EP 0566469A1 EP 93400950 A EP93400950 A EP 93400950A EP 93400950 A EP93400950 A EP 93400950A EP 0566469 A1 EP0566469 A1 EP 0566469A1
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EP
European Patent Office
Prior art keywords
rotor
rocket
lock
projectile
arming device
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP93400950A
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German (de)
French (fr)
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EP0566469B1 (en
Inventor
Jacques Nicolas
Jean-Paul Oberle
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Manurhin Defense SA
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Manurhin Defense SA
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Publication date
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Publication of EP0566469A1 publication Critical patent/EP0566469A1/en
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Publication of EP0566469B1 publication Critical patent/EP0566469B1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/18—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved
    • F42C15/188—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier
    • F42C15/192—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a carrier for an element of the pyrotechnic or explosive train is moved using a rotatable carrier rotatable in a plane which is parallel to the longitudinal axis of the projectile
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C15/00—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges
    • F42C15/20—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a securing-pin or latch is removed to arm the fuze, e.g. removed from the firing-pin
    • F42C15/22—Arming-means in fuzes; Safety means for preventing premature detonation of fuzes or charges wherein a securing-pin or latch is removed to arm the fuze, e.g. removed from the firing-pin using centrifugal force

Definitions

  • the field of the present invention is that of safety and arming devices for rockets intended to equip revolving projectiles.
  • the safety and arming devices of rockets have the function of ensuring the misaligned maintenance of the pyrotechnic initiation chain of the projectile, which guarantees safety during storage and handling of the ammunition.
  • Such devices are known and most often include a primer carrier rotor having an unbalance. This rotor is held in a misaligned position by one or more locks and it adopts by itself, by gyroscopic effect, an aligned position when the lock or locks are released.
  • Patent FR2533686 provides for placing the primer-carrying rotor inside a cage which is mounted in the rocket body with a certain axial play and which is free to rotate about the axis of the rocket.
  • the rotor is made integral with the cage in a misaligned position by means of pins held in place by a hairspring.
  • Patent FR2537265 shows a rotor which is held in the misaligned position by a socket. The latter emerges from the rotor following the unwinding of a hairspring.
  • such devices include parts (cage, rotor, hairspring) which have a certain mobility relative to the rocket body.
  • the vibrations induced on a rotor which has a certain mobility can also cause the pyrotechnic composition to leave the primer, which is extremely detrimental from the point of view of safety.
  • Patent EP360187 proposes a primer holder rotor which is held in the misaligned position by a split washer.
  • the washer is applied to the rotor by a spiral spring which bears on the rocket body.
  • the spring allows axial movements of the rotor relative to its housing, which allows elastic shock absorption to be achieved.
  • Such an arrangement does not prohibit relative movements and therefore does not prevent wear of the bearing surfaces caused by the induced vibrations.
  • the subject of the invention is a safety and arming device for a rocket intended to equip a gyrating projectile, device comprising a rotor which carries a primer and is held by a lock in a position in which the primer does not is not aligned with a main pyrotechnic chain, device characterized in that the lock is held in abutment on the rotor by immobilization means which is sufficiently rigid to maintain this abutment when the device is subjected to shock or vibration stresses, means immobilizer releasing the lock following the firing of the projectile.
  • the security and arming device comprises means ensuring that the lock is kept in a position spaced from the rotor after its release by the immobilization means.
  • This arrangement makes it possible to prevent the lock from disturbing the subsequent movements of the rotor.
  • the immobilization means comprises an elastic washer which has a peripheral rim bearing on the rocket body and a central part constituted by at least two tongues, regularly distributed angularly, and which come to bear on the bolt and are liable to deform so as to allow the latter to pass when it is driven by its inertia when the projectile is fired.
  • the lock has a flange on which the tongues come to rest and a cylindrical part capable of passing freely between the tongues and in that the means ensuring the maintenance of the lock in a separated position are constituted by the tongues themselves which form a stop for the flange after the passage of the latter through the washer.
  • the peripheral edge of the washer is housed in a groove in the rocket body.
  • the immobilization means comprises a split ring which is supported on the one hand on the rocket body and on the other hand on a conical surface of the lock, ring capable of s' thus opening and releasing the lock when it is driven by its inertia during of the projectile.
  • the means ensuring that the lock is held in a position spaced from the rotor comprises a ring carrying at least two lamellae, elastically deformable and regularly distributed angularly, lamellae kept compressed by a flat surface of the lock when the latter is supported on rotor and which release the rotor lock when it is released by the ring.
  • the ring when the ring is driven by its inertia when the projectile is fired, it keeps the crown in abutment against the rocket body.
  • the rotor may be placed inside a cage, mounted to rotate relative to the rocket body and around the axis of the latter and the lock may be constituted by a sleeve coaxial with the rocket and through which is susceptible to slide a striker intended to initiate the primer.
  • a rocket 1 intended to be disposed at the base of a projectile comprises a body 2 of light alloy (for example aluminum) inside which is arranged a device security and arming according to the invention.
  • the body is closed by a plug 4 which carries a relay pyrotechnic charge 5 in a housing.
  • This charge is intended in a known manner to ensure the ignition of a main charge (not shown), contained in the projectile.
  • the rocket also includes a self-destruct device of known type (described for example in patent FR1227037) and which in particular comprises a striker 6, which is pushed by a spring 7 towards a primer 9.
  • a self-destruct device of known type (described for example in patent FR1227037) and which in particular comprises a striker 6, which is pushed by a spring 7 towards a primer 9.
  • a support 3 is made integral with the body 2 by means of a thread.
  • the security and arming device comprises a rotor 8 having an unbalance and inside which the primer 9 is disposed.
  • the rotor is placed inside a cage 10 which has two pins 11 and 12.
  • the pins come in corresponding housings arranged respectively on the support 3 and the plug 4, the adjustment of the pins in their housings is slippery and allows relative rotation of the cage with respect to the rocket body.
  • the rotor 8 is immobilized relative to the cage 10 in a misaligned position by means of two radial pins 14, which are themselves held in place by a hairspring 13.
  • the rotor is also immobilized by a lock 15, which is, in the embodiment described here, a cylindrical sleeve inside which the striker 6 can slide.
  • the lock comprises a cylindrical part 15a which carries a flange 19 to its end furthest from rotor 8.
  • the other end of the lock is held by an immobilizing means bearing on a groove 16 made on the rotor.
  • the immobilization means is an elastic washer 17.
  • This washer 17 is shown in detail in Figures 2a and 2b. It is made of pressed spring steel sheet and has a circular shape. It has a peripheral rim 20 and a central part 24.
  • the central part consists of two tongues 21 arranged symmetrically to each other relative to the axis 26 of the washer.
  • the free ends 25 of the tongues each have a cut in the shape of an arc of a circle, the center of which is positioned on the axis 26. They are separated by a free space 22.
  • the outer diameter of the cylindrical part 15a of the latch is shown in dotted lines 36, and in dotted lines 23 the outer diameter of the flange 19 of the latch.
  • the diameter of the collar is slightly greater (of the order of mm) than that of the free ends 25 of the tabs which define the free space 22.
  • the diameter of the cylindrical part 15a is slightly smaller (of the order of mm) than that of the free ends 25 of the tongues which define the free space 22.
  • the bolt 15 will be dimensioned so that when it is thus supported on the rotor, there remains a clearance (j) of a few tenths of a mm between the flange 19 and the support 3.
  • the washer will be dimensioned (by playing in particular on the number and dimensions of the tongues) so that it ensures that the bolt remains in contact with the rotor, therefore that the play is taken up when the device is subjected to vibrations or shocks.
  • the tabs will nevertheless be dimensioned in such a way that they release the bolt when, when the projectile is fired, it is thus driven by its inertia towards the rear part D of the rocket.
  • the lock then ensures the immobilization of the rotor and the cage during the storage phases and the handling of the ammunition (maximum acceleration of the order of 30,000 times the acceleration of gravity during the placing of the ammunition in tear).
  • FIG. 3 shows the security and arming device according to this first embodiment after the release of the lock 15 under the action of its inertia and before the release of the rotor 8 by the pins 14 (therefore before the projectile leaves the from the barrel or within the first few meters of its trajectory out of the barrel).
  • the tongues 21 return to their initial position. They thus constitute a means which maintains the lock in a position spaced from the rotor.
  • the length of the cylindrical part 15a of the latch and the thickness of the washer 17 are such that, when the collar is in abutment on the washer in the arrangement shown in FIG. 3, the end of the cylindrical part 15a of the latch is completely disengaged from the rotor 8 and no longer prohibits the movements of the latter.
  • This maintenance is particularly secure due to the support of the tongues 21 on the support 3.
  • the striker is kept spaced from the primer against the action of the spring 7 (for example by means of balls as described in patent FR1227037).
  • the rotor After a time delay given by the unwinding of the hairspring, the rotor is released by the pins 14 and it assumes an aligned position.
  • the striker Upon impact on a target, the striker is thrown against the primer and initiates the latter, which causes the projectile to explode.
  • This assembly receives the striker and the rest of the self-destruction device, then the body 2 of the rocket is screwed onto the support 3.
  • the sub-assembly consisting of the cage 10 carrying the rotor 8 and the hairspring 13, is positioned on the end of the cylindrical part 15a of the latch 15.
  • the plug 4 is screwed onto the body 2 until it abutment of a peripheral shoulder 27 of the plug 4 on the body 2.
  • the dimensions of the plug are determined so that, after release of the lock, there is a functional axial clearance between the cage 10 and the support 3.
  • the axial movements of the cage / rotor / hairspring assembly relative to the rocket body are prohibited by the latch 15, held in abutment against the rotor by the washer 17.
  • the rotational movements of the cage / rotor / hairspring assembly relative to the rocket body are also prohibited.
  • the force applied by the bolt to the rotor is chosen to be large enough to prevent such rotations due to the friction of the cage 10 on the plug 4.
  • the latch 15 is however released from the first moments of the firing since this release only uses the inertial forces in an axial direction of the projectile. Thus the subsequent movement of the cage and the release of the rotor by the pins are not disturbed, which ensures the reliability of the security and arming device.
  • the security and arming device according to this first embodiment is particularly simple from the point of view of manufacture and assembly. It has a resistance to storage in severe vibratory environments which is improved with respect to that of safety devices according to the state of the art. And such an improvement does not penalize the cost of production or the reliability of the weaponry.
  • Such a security and arming device could possibly be adapted to a warhead rocket.
  • the lock will then prevent vibrations of the rotor relative to its cage which will prevent the pyrotechnic composition from leaving the primer.
  • FIG. 4 represents a rocket 1 intended to be fixed to the warhead of a projectile (not shown).
  • It comprises a body 2 of light alloy (for example aluminum) inside which is disposed a security and arming device according to a second embodiment of the invention.
  • a body 2 of light alloy for example aluminum
  • the body is closed by a plug 4 which carries a relay pyrotechnic charge 5 in a housing.
  • This charge is intended in a known manner to ensure the ignition of a main charge (not shown) contained in the projectile.
  • the rocket also includes a self-destruct device of known type (described for example in patent FR1227037) which notably comprises a striker 6 which is pushed by a spring 7 towards a primer 9.
  • a self-destruct device of known type (described for example in patent FR1227037) which notably comprises a striker 6 which is pushed by a spring 7 towards a primer 9.
  • a spacer 28 abuts on the body 2 of the rocket at a shoulder 40 and it is made integral with the body 2 by means of a support 3, itself threaded and screwed to the body 2.
  • the security and arming device comprises a rotor 8 disposed in a cage 10.
  • the cage carries two pins 11 and 12 which come in corresponding housings arranged respectively on the support 3 and the plug 4.
  • the adjustment of the pins in their housings is sliding and it allows relative rotation of the cage relative to the rocket body.
  • the rotor is immobilized by a latch 29 which is, in the embodiment described here, a socket inside which the striker 6 can slide and which has a conical surface 32 whose apex is oriented towards a front part A of the rocket.
  • the sleeve has a front cylindrical portion 29a which comes, in sliding adjustment, into a housing 33 arranged on the spacer 28.
  • a split O-ring 30 (also visible in FIG. 5) is tightened on this conical part 32 and it is also supported on the lower face 28a of the spacer 28.
  • the ring 30 constitutes a means of immobilization which ensures the support of the lock 29 on the rotor 8
  • the latch 29 has a flat surface 29c which comes into contact with a ring 31 itself in contact with the support 3.
  • the crown 31 is visible in detail in Figures 6a and 6b. It is a substantially circular stamped sheet metal plate with an axis 37 and which carries two elastic lamellae 35, arranged symmetrically with respect to the axis 37.
  • the free ends 38 of the strips have a cut in the form of arcs of a circle, the center of which is positioned on the axis 37. They are separated by a free space 34.
  • the diameter of the rear cylindrical portion 29b of the lock is slightly smaller (of the order of mm) than that of the ends 38 of the strips which define the free space 34.
  • Crown and blades constitute a means ensuring that the lock is kept in a position away from the rotor after its release by the lock.
  • the mode of action of the lamellae will be explained later.
  • the assembly of this device is carried out as follows.
  • the crown 31 is positioned in its cylindrical housing of the support 3, then the lock 29 is put in place on which the ring 30 is mounted and the lock is capped with the spacer 28.
  • the latter is in support of firstly on a shoulder 39 of the support 3 and secondly on the ring 30.
  • the self-destruct device is then positioned in the spacer 28 and the body 2 is screwed until the spacer 28 is brought into abutment on the shoulder 40 of the body.
  • the rotor mounted in its cage is then put in place in the engaged position on the latch 29 and finally the plug 4 is screwed onto the body 2 until a peripheral shoulder 27 of the plug 4 is brought into abutment on the body 2.
  • the dimensions of the plug and the total length of the latch 29 are chosen so that the latch 29 is supported on the groove 16 and that there remains a functional axial clearance between the cage 10 and the support 3 after release of the latch.
  • the operation of the device is as follows: When firing the ammunition and under the effect of the axial inertia forces exerted on the ring 30, the latter moves towards the rear part D of the rocket.
  • the conical surface 32 causes the opening of the ring.
  • the ring completes to open and comes into contact with the surface of the bore 41 under the action of the inertial forces of rotation which are exerted shortly before the exit of the barrel from the weapon.
  • the withdrawal of the ring 30 authorizes the displacement of the lock 29 towards the front part A of the rocket under the action of the lamellae 35 and the deceleration.
  • the latter are dimensioned so that they can disengage the front part 29b from the lock of the groove 16 of the rotor.
  • the housing 33 of the rear part of the socket in the spacer 28 will also be: sufficient depth to allow such clearance.
  • Figure 7 shows the security and arming device according to this second embodiment after clearing the lock and before the release of the rotor by the pins 14.
  • the ring 30, opened by the inertia forces, is applied with part against the crown 31 and on the other hand against the bore 41 of the support 3.
  • the ring thus maintains the crown relative to the rocket body and allows the latter to keep the lock stationary relative to the rocket body.
  • this embodiment of the invention makes it possible to prohibit the axial movements of the cage / rotor / hairspring assembly relative to the rocket body by virtue of the bolt 29 held in abutment against the rotor by the ring 30.
  • the force applied by the lock on the rotor is sufficient to prevent such rotations due to the friction of the cage 10 on the plug 4.
  • the lock 29 is however released from the first moments of the firing since this release only uses the inertial forces in an axial direction of the projectile. Thus the subsequent movement of the cage and the release of the rotor by the pins are not disturbed which ensures the reliability of the security and arming device.
  • the security and arming device according to this second embodiment is particularly suitable for fitting into a warhead rocket.
  • the lock will then prohibit the relative vibrations of the rotor in its cage, which will prevent the pyrotechnic composition from leaving the primer.

Abstract

The sector of the present invention is that of safety and arming devices for fuses intended for equipping spinning projectiles. The safety and arming device according to the invention comprises a rotor (8) which carries a primer (9) and which is held by a bolt (15, 29) in a position in which the primer is not aligned with a main pyrotechnic chain, this device being characterised in that the bolt (15, 29) is kept bearing on the rotor (8) by an immobilising means (17, 30) sufficiently rigid to keep up this bearing when the device is subjected to the stresses caused by impact or vibration, the immobilising means freeing the bolt (15, 29) after the projectile has been fired. The invention is used for medium-calibre ammunition. <IMAGE>

Description

Le domaine de la présente invention est celui des dispositifs de sécurité et d'armement pour les fusées destinées à équiper les projectiles girants.The field of the present invention is that of safety and arming devices for rockets intended to equip revolving projectiles.

Les dispositifs de sécurité et d'armement de fusées ont pourfonction d'assurer le maintien désaligné de la chaîne pyrotechnique d'initiation du projectile, ce qui garantit la sécurité au cours du stockage et des manipulations de la munition.The safety and arming devices of rockets have the function of ensuring the misaligned maintenance of the pyrotechnic initiation chain of the projectile, which guarantees safety during storage and handling of the ammunition.

Ils ont également pourfonction d'assurer l'alignement de cette même chaîne lors du tir, et à l'issue du parcours par le projectile d'une certaine distance hors de l'arme. On évite ainsi les mises à feu prématurées en cas d'impact sur des obstacles rapprochés.They also have the function of ensuring the alignment of this same chain during firing, and at the end of the course by the projectile from a certain distance outside the weapon. This avoids premature ignition in the event of impact on close obstacles.

De tels dispositifs sont connus et comportent le plus souvent un rotor porte amorce présentant un balourd. Ce rotor est maintenu dans une position désalignée par un ou plusieurs verrous et il adopte de lui même, par effet gyroscopique, une position alignée lorsque le ou les verrous se sont dégagés.Such devices are known and most often include a primer carrier rotor having an unbalance. This rotor is held in a misaligned position by one or more locks and it adopts by itself, by gyroscopic effect, an aligned position when the lock or locks are released.

On consultera par exemple les brevets FR2533686 et FR2537265 qui décrivent de tels dispositifs.See for example the patents FR2533686 and FR2537265 which describe such devices.

Le brevet FR2533686 prévoit de disposer le rotor porte amorce à l'intérieur d'une cage qui est montée dans le corps de fusée avec un certain jeu axial et qui est libre en rotation autour de l'axe de la fusée.Patent FR2533686 provides for placing the primer-carrying rotor inside a cage which is mounted in the rocket body with a certain axial play and which is free to rotate about the axis of the rocket.

Le rotor est rendu solidaire de la cage dans une position désalignée au moyen de goupilles maintenues en place par un spiral.The rotor is made integral with the cage in a misaligned position by means of pins held in place by a hairspring.

Le brevet FR2537265 montre un rotor qui est maintenu en position désalignée par une douille. Cette dernière se dégage du rotor suite au déroulement d'un spiral.Patent FR2537265 shows a rotor which is held in the misaligned position by a socket. The latter emerges from the rotor following the unwinding of a hairspring.

Afin de pouvoir fonctionner correctement de tels dispositifs comportent des pièces (cage, rotor, spiral) qui présentent une certaine mobilité relativement au corps de fusée.In order to be able to function properly, such devices include parts (cage, rotor, hairspring) which have a certain mobility relative to the rocket body.

On a pu constater que les vibrations, qui sont induites sur de tels dispositifs par les véhicules amenés à les transporter, provoquent l'usure des surfaces d'appui, l'arrachage des protections de surface et le desserrage des spiraux. De telles détériorations peuvent entraîner des défauts de sécurité ou encore des non fonctionnements.It has been observed that the vibrations which are induced on such devices by the vehicles brought to transport them, cause the wear of the bearing surfaces, the tearing off of the surface protections and the loosening of the hairsprings. Such damage can lead to safety faults or non-functioning.

Les vibrations induites sur un rotor qui présente une certaine mobilité peuvent également provoquer la sortie de la composition pyrotechnique hors de l'amorce ce qui est extrêmement préjudiciable du point de vue de la sécurité.The vibrations induced on a rotor which has a certain mobility can also cause the pyrotechnic composition to leave the primer, which is extremely detrimental from the point of view of safety.

Le brevet EP360187 propose un rotor porte amorce qui est maintenu en position désalignée par une rondelle fendue. La rondelle est appliquée sur le rotor par un ressort spiral qui prend appui sur le corps de fusée.Patent EP360187 proposes a primer holder rotor which is held in the misaligned position by a split washer. The washer is applied to the rotor by a spiral spring which bears on the rocket body.

Le ressort autorise des déplacements axiaux du rotor relativement à son logement, ce qui permet de réaliser un amortissement élastique des chocs éventuels.The spring allows axial movements of the rotor relative to its housing, which allows elastic shock absorption to be achieved.

Une telle disposition n'interdit pas les mouvements relatifs et ne permet donc pas d'éviter les usures des surfaces d'appui provoquées par les vibrations induites.Such an arrangement does not prohibit relative movements and therefore does not prevent wear of the bearing surfaces caused by the induced vibrations.

C'est le but de l'invention que de remédier à de tels inconvénients en proposant un dispositif de sécurité et d'armement dont les pièces mobiles ne sont pas détériorées par l'action de vibrations mais conservent néanmoins toute leur mobilité lors du tir.It is the object of the invention to remedy such drawbacks by proposing a security and arming device whose moving parts are not damaged by the action of vibrations but nevertheless retain all their mobility during shooting.

Ainsi l'invention a pour objet un dispositif de sécurité et d'armement pour une fusée destinée à équiper un projectile girant, dispositif comportant un rotor qui porte une amorce et se trouve maintenu par un verrou dans une position dans laquelle l'amorce n'est pas alignée avec une chaine pyrotechnique principale, dispositif caractérisé en ce que le verrou est maintenu en appui sur le rotor par un moyen d'immobilisation suffisamment rigide pour maintenir cet appui lorsque le dispositif est soumis à des contraintes de choc ou de vibration, moyen d'immobilisation libérant le verrou consécutivement au tir du projectile.Thus, the subject of the invention is a safety and arming device for a rocket intended to equip a gyrating projectile, device comprising a rotor which carries a primer and is held by a lock in a position in which the primer does not is not aligned with a main pyrotechnic chain, device characterized in that the lock is held in abutment on the rotor by immobilization means which is sufficiently rigid to maintain this abutment when the device is subjected to shock or vibration stresses, means immobilizer releasing the lock following the firing of the projectile.

Une telle disposition permet d'interdire les vibrations relatives du rotor et de la fusée sans perturber le fonctionnement du dispositif de sécurité et d'armement.Such an arrangement makes it possible to prohibit the relative vibrations of the rotor and the rocket without disturbing the operation of the security and arming device.

Selon une autre caractéristique de l'invention le dispositif de sécurité et d'armement comprend des moyens assurant un maintien du verrou dans une position écartée du rotor après sa libération par le moyen d'immobilisation.According to another characteristic of the invention, the security and arming device comprises means ensuring that the lock is kept in a position spaced from the rotor after its release by the immobilization means.

Cette disposition permet d'éviter que le verrou ne vienne perturber les mouvements ultérieurs du rotor.This arrangement makes it possible to prevent the lock from disturbing the subsequent movements of the rotor.

Selon un premier mode de réalisation de l'invention, le moyen d'immobilisation comprend une rondelle élastique qui présente un rebord périphérique venant en appui sur le corps de fusée et une partie centrale constituée par au moins deux languettes, régulièrement réparties angulairement, et qui viennent en appui sur le verrou et sont susceptibles de se déformer de manière à laisser passer ce dernier lorsqu'il est entrainé par son inertie lors du tir du projectile.According to a first embodiment of the invention, the immobilization means comprises an elastic washer which has a peripheral rim bearing on the rocket body and a central part constituted by at least two tongues, regularly distributed angularly, and which come to bear on the bolt and are liable to deform so as to allow the latter to pass when it is driven by its inertia when the projectile is fired.

De façon préférentielle, le verrou présente une collerette sur laquelle les languettes viennent en appui et une partie cylindrique susceptible de passer librement entre les languettes et en ce que les moyens assurant le maintien du verrou dans une position écartée sont constitués par les languettes elles-même qui forment une butée pour la collerette après le passage de cette dernière au travers de la rondelle.Preferably, the lock has a flange on which the tongues come to rest and a cylindrical part capable of passing freely between the tongues and in that the means ensuring the maintenance of the lock in a separated position are constituted by the tongues themselves which form a stop for the flange after the passage of the latter through the washer.

Selon une modalité pratique d'exécution, le rebord périphérique de la rondelle vient se loger dans une gorge du corps de fusée.According to a practical embodiment, the peripheral edge of the washer is housed in a groove in the rocket body.

Selon un deuxième mode de réalisation de l'invention, le moyen d'immobilisation comprend une bague fendue qui est en appui d'une part sur le corps de fusée et d'autre part sur une surface conique du verrou, bague susceptible de s'ouvrir et libérer ainsi le verrou lorsqu'elle est entrainée par son inertie lors du tir du projectile.According to a second embodiment of the invention, the immobilization means comprises a split ring which is supported on the one hand on the rocket body and on the other hand on a conical surface of the lock, ring capable of s' thus opening and releasing the lock when it is driven by its inertia during of the projectile.

De façon préférentielle, les moyens assurant un maintien du verrou dans une position écartée du rotor comprennent une couronne portant au moins deux lamelles, déformables élastiquement et régulièrement réparties angulairement, lamelles maintenues comprimées par une surface plane du verrou lorsque ce dernier est en appui sur le rotor et qui dégagent le verrou du rotor lorsqu'il se trouve libéré par la bague.Preferably, the means ensuring that the lock is held in a position spaced from the rotor comprises a ring carrying at least two lamellae, elastically deformable and regularly distributed angularly, lamellae kept compressed by a flat surface of the lock when the latter is supported on rotor and which release the rotor lock when it is released by the ring.

Selon une autre caractéristique de ce deuxième mode de réalisation, lorsque la bague est entraînée par son inertie lors du tir du projectile, elle vient maintenir la couronne en appui contre le corps de fusée.According to another characteristic of this second embodiment, when the ring is driven by its inertia when the projectile is fired, it keeps the crown in abutment against the rocket body.

Le rotor pourra être disposé à l'intérieur d'une cage, montée tournante relativement au corps de fusée et autour de l'axe de cette dernière et le verrou pourra être constitué par une douille coaxiale à la fusée et au travers de laquelle est susceptible de coulisser un percuteur destiné à initier l'amorce.The rotor may be placed inside a cage, mounted to rotate relative to the rocket body and around the axis of the latter and the lock may be constituted by a sleeve coaxial with the rocket and through which is susceptible to slide a striker intended to initiate the primer.

L'invention sera mieux comprise à la lecture de la description qui va suivre de modes particuliers de réalisation, description faite en référence aux dessins annexés et dans lesquels:

  • - la figure 1 représente en coupe longitudinale partielle une fusée de culot de projectile équipée d'un dispositif de sécurité et d'armement selon un premier mode de réalisation de l'invention. La fusée étant représentée dans son état de stockage.
  • - les figures 2a et 2b représentent la rondelle élastique suivant deux vues orthogonales, la figure 2a étant une coupe de la figure 2b suivant le plan BB.
  • - La figure 3 est une vue partielle de la fusée de culot de la figure 1 lorsqu'elle est soumise à l'accélération axiale résultant du tir.
  • - la figure 4 représente en coupe longitudinale partielle une fusée d'ogive d'un projectile équipée d'un dispositif de sécurité et d'armement selon un deuxième mode de réalisation de l'invention. La fusée étant représentée dans son état de stockage.
  • - la figure 5 représente la bague fendue en vue frontale.
  • - les figures 6a et 6b représentent la couronne suivant deux vues orthogonales, la figure 6b étant une coupe de la figure 6a suivant le plan CC.
  • - La figure 7 est une vue partielle de la fusée d'ogive de la figure 4 lorsqu'elle est soumise à l'accélération axiale résultant du tir.
The invention will be better understood on reading the description which follows of particular embodiments, description made with reference to the appended drawings and in which:
  • - Figure 1 shows in partial longitudinal section a projectile base rocket equipped with a safety and arming device according to a first embodiment of the invention. The rocket being represented in its storage state.
  • - Figures 2a and 2b show the elastic washer in two orthogonal views, Figure 2a being a section of Figure 2b along the plane BB.
  • - Figure 3 is a partial view of the base rocket of Figure 1 when subjected to the axial acceleration resulting from the firing.
  • - Figure 4 shows in partial longitudinal section a warhead rocket of a projectile equipped with a safety and arming device according to a second embodiment of the invention. The rocket being represented in its storage state.
  • - Figure 5 shows the split ring in front view.
  • - Figures 6a and 6b show the crown in two orthogonal views, Figure 6b being a section of Figure 6a along the plane CC.
  • - Figure 7 is a partial view of the warhead rocket of Figure 4 when subjected to axial acceleration resulting from firing.

En se reportant à la figure 1, une fusée 1 destinée à être disposée au niveau du culot d'un projectile (non représenté) comprend un corps 2 en alliage léger (par exemple d'aluminium) à l'intérieur duquel est disposé un dispositif de sécurité et d'armement selon l'invention.Referring to Figure 1, a rocket 1 intended to be disposed at the base of a projectile (not shown) comprises a body 2 of light alloy (for example aluminum) inside which is arranged a device security and arming according to the invention.

On désigne par A la partie avant de cette fusée et qui vient donc se loger dans le projectile et par D la partie arrière de la fusée.One indicates by A the front part of this rocket and which thus comes to be lodged in the projectile and by D the rear part of the rocket.

Le corps est fermé par un bouchon 4 qui porte une charge pyrotechnique relais 5 dans un logement. Cette charge est destinée de façon connue à assurer la mise à feu d'une charge principale (non représentée), contenue dans le projectile.The body is closed by a plug 4 which carries a relay pyrotechnic charge 5 in a housing. This charge is intended in a known manner to ensure the ignition of a main charge (not shown), contained in the projectile.

La fusée comporte également un dispositif d'autodestruction de type connu (décrit par exemple dans le brevet FR1227037) et qui comprend notamment un percuteur 6, qui est poussé par un ressort 7 vers une amorce 9.The rocket also includes a self-destruct device of known type (described for example in patent FR1227037) and which in particular comprises a striker 6, which is pushed by a spring 7 towards a primer 9.

Un support 3 est rendu solidaire du corps 2 au moyen d'un filetage.A support 3 is made integral with the body 2 by means of a thread.

Le dispositif de sécurité et d'armement comprend un rotor 8 présentant un balourd et à l'intérieur duquel est disposée l'amorce 9.The security and arming device comprises a rotor 8 having an unbalance and inside which the primer 9 is disposed.

Le rotor est placé à l'intérieur d'une cage 10 qui présente deux tourillons 11 et 12. Les tourillons viennent dans des logements correspondants aménagés respectivement sur le support 3 et le bouchon 4, l'ajustement des tourillons dans leurs logements est glissant et autorise une rotation relative de la cage par rapport au corps de fusée.The rotor is placed inside a cage 10 which has two pins 11 and 12. The pins come in corresponding housings arranged respectively on the support 3 and the plug 4, the adjustment of the pins in their housings is slippery and allows relative rotation of the cage with respect to the rocket body.

Le rotor 8 est immobilisé relativement à la cage 10 dans une position désalignée au moyen de deux goupilles radiales 14, elles même maintenues en place par un spiral 13.The rotor 8 is immobilized relative to the cage 10 in a misaligned position by means of two radial pins 14, which are themselves held in place by a hairspring 13.

Cette structure est décrite en détail dans le brevet FR2533686.This structure is described in detail in patent FR2533686.

Le rotor est également immobilisé par un verrou 15, qui est, dans le mode de réalisation décrit ici, une douille cylindrique à l'intérieur de laquelle peut coulisser le percuteur 6. Le verrou comprend une partie cylindrique 15a qui porte une collerette 19 à son extrémité la plus éloignée du rotor 8.The rotor is also immobilized by a lock 15, which is, in the embodiment described here, a cylindrical sleeve inside which the striker 6 can slide. The lock comprises a cylindrical part 15a which carries a flange 19 to its end furthest from rotor 8.

L'autre extrémité du verrou est maintenue par un moyen d'immobilisation en appui sur une rainure 16 réalisée sur le rotor. Dans ce premier mode de réalisation de l'invention le moyen d'immobilisation est une rondelle élastique 17.The other end of the lock is held by an immobilizing means bearing on a groove 16 made on the rotor. In this first embodiment of the invention, the immobilization means is an elastic washer 17.

Cette rondelle 17 est représentée en détail aux figures 2a et 2b. Elle est réalisée en tôle d'acier à ressort emboutie et présente une forme circulaire. Elle comporte un rebord périphérique 20 et une partie centrale 24.This washer 17 is shown in detail in Figures 2a and 2b. It is made of pressed spring steel sheet and has a circular shape. It has a peripheral rim 20 and a central part 24.

La partie centrale est constituée par deux languettes 21 disposées de façon symétrique l'une de l'autre relativement à l'axe 26 de la rondelle. Les extrémités libres 25 des languettes ont chacune une découpe en forme d'arc de cercle dont le centre est positionné sur l'axe 26. Elles sont séparées par un espace libre 22.The central part consists of two tongues 21 arranged symmetrically to each other relative to the axis 26 of the washer. The free ends 25 of the tongues each have a cut in the shape of an arc of a circle, the center of which is positioned on the axis 26. They are separated by a free space 22.

Il serait possible de prévoir un nombre de languettes N supérieur à deux, elles auront dans tous les cas une répartition angulaire régulière, c'est à dire telle que l'ensemble des languettes présente une symétrie de rotation d'ordre N autour de l'axe 26.It would be possible to provide a number of tongues N greater than two, they will in all cases have a regular angular distribution, that is to say such that the set of tongues has a symmetry of rotation of order N around the axis 26.

Ainsi la résultante des efforts qu'elles exerceront sur le verrou 15 sera colinéaire à l'axe 26 (donc à l'axe de la fusée elle même) et on évitera tout coincement du verrou par rapport au support 3.Thus the result of the forces they exert on the latch 15 will be collinear with the axis 26 (therefore on the axis of the rocket itself) and any jamming of the latch with respect to the support 3 will be avoided.

On a représenté en traits pointillés 36 le diamètre externe de la partie cylindrique 15a du verrou, et en traits pointillés 23 le diamètre externe de la collerette 19 du verrou.The outer diameter of the cylindrical part 15a of the latch is shown in dotted lines 36, and in dotted lines 23 the outer diameter of the flange 19 of the latch.

Le diamètre de la collerette est légèrement supérieur (de l'ordre du mm) à celui des extrémités libres 25 des languettes qui définissent l'espace libre 22.The diameter of the collar is slightly greater (of the order of mm) than that of the free ends 25 of the tabs which define the free space 22.

Le diamètre de la partie cylindrique 15a est légèrement inférieur (de l'ordre du mm) à celui des extrémités libres 25 des languettes qui définissent l'espace libre 22.The diameter of the cylindrical part 15a is slightly smaller (of the order of mm) than that of the free ends 25 of the tongues which define the free space 22.

En se reportant à nouveau à la figure 1 on remarque que le rebord 20 de la rondelle 17 se loge dans une gorge 18 aménagée dans le support 3. Ainsi la partie centrale 24 de la rondelle vient en appui sur le verrou 15 au niveau de sa collerette tandis que le rebord 20 est en appui sur le support 3.Referring again to Figure 1 we note that the flange 20 of the washer 17 is housed in a groove 18 formed in the support 3. Thus the central portion 24 of the washer comes to bear on the latch 15 at its flange while the rim 20 is supported on the support 3.

Une telle disposition a pour effet de maintenir le verrou 15 en appui sur le rotor et donc de rattraper les jeux axiaux relatifs entre le rotor et sa cage ainsi qu'entre la cage et le corps de fusée.The effect of such an arrangement is to keep the latch 15 in abutment on the rotor and therefore to make up for the relative axial clearances between the rotor and its cage as well as between the cage and the rocket body.

On dimensionnera le verrou 15 de telle sorte que lorsqu'il se trouve ainsi en appui sur le rotor il subsiste un jeu (j) de quelques dixièmes de mm entre la collerette 19 et le support 3.The bolt 15 will be dimensioned so that when it is thus supported on the rotor, there remains a clearance (j) of a few tenths of a mm between the flange 19 and the support 3.

On dimensionnera la rondelle (en jouant en particulier sur le nombre et les dimensions des languettes) de telle sorte qu'elle assure un maintien en appui du verrou contre le rotor, donc le maintien du rattrapage de jeu, lorsque le dispositif est soumis à des vibrations ou bien des chocs.The washer will be dimensioned (by playing in particular on the number and dimensions of the tongues) so that it ensures that the bolt remains in contact with the rotor, therefore that the play is taken up when the device is subjected to vibrations or shocks.

On dimensionnera néanmoins les languettes de telle façon qu'elles libèrent le verrou lorsque, lors du tir du projectile, il se trouve ainsi entraîné par son inertie vers la partie arrière D de la fusée.The tabs will nevertheless be dimensioned in such a way that they release the bolt when, when the projectile is fired, it is thus driven by its inertia towards the rear part D of the rocket.

Dans le cas d'un rotor monté dans une cage comme le représente ce premier mode de réalisation de l'invention il est nécessaire que la rondelle assure un appui du verrou sur le rotor qui interdise toute rotation relative entre la cage et le corps de fusée lorsque le système est soumis à des vibrations ou bien des chocs.In the case of a rotor mounted in a cage as shown in this first embodiment of the invention, it is necessary for the washer to provide support for the lock on the rotor which prevents any relative rotation between the cage and the rocket body when the system is subjected to vibrations or shocks.

Avec un verrou de masse 0.5 grammes, il suffit de dimensionner la rondelle de telle sorte qu'une fois mise en place elle exerce sur le verrou un effort de l'ordre de 3 DaN.With a 0.5 gram mass lock, it suffices to size the washer so that once it is installed, it exerts on the lock an effort of the order of 3 DaN.

Le verrou assure alors l'immobilisation du rotor et de la cage pendant les phases de stockage et les manipulations de la munition (accélération maximale de l'ordre de 30.000 fois l'accélération de la pesanteur lors de la mise à poste de la munition dans l'arme).The lock then ensures the immobilization of the rotor and the cage during the storage phases and the handling of the ammunition (maximum acceleration of the order of 30,000 times the acceleration of gravity during the placing of the ammunition in tear).

Mais le verrou s'efface au travers de la rondelle lors du tir (accélération mise en oeuvre lors du tir du projectile de l'ordre de 80.000 fois l'accélération de la pesanteur).But the bolt disappears through the washer during firing (acceleration implemented when firing the projectile of the order of 80,000 times the acceleration of gravity).

La figure 3 montre le dispositif de sécurité et d'armement selon ce premier mode de réalisation après le dégagement du verrou 15 sous l'action de son inertie et avant la libération du rotor 8 par les goupilles 14 (donc avant la sortie du projectile hors du tube de l'arme ou dans les premiers mètres de sa trajectoire hors du tube).FIG. 3 shows the security and arming device according to this first embodiment after the release of the lock 15 under the action of its inertia and before the release of the rotor 8 by the pins 14 (therefore before the projectile leaves the from the barrel or within the first few meters of its trajectory out of the barrel).

Après le passage de la collerette 19 au travers de la rondelle 17, les languettes 21 reprennent leur position initiale. Elles constituent ainsi un moyen qui assure le maintien du verrou dans une position écartée du rotor.After the flange 19 has passed through the washer 17, the tongues 21 return to their initial position. They thus constitute a means which maintains the lock in a position spaced from the rotor.

En effet la longueur de la partie cylindrique 15a du verrou et l'épaisseur de la rondelle 17 sont telles que, lorsque la collerette se trouve en appui sur la rondelle dans la disposition représentée figure 3, l'extrémité de la partie cylindrique 15a du verrou se trouve totalement dégagée du rotor 8 et n'interdit plus les mouvements de ce dernier.Indeed, the length of the cylindrical part 15a of the latch and the thickness of the washer 17 are such that, when the collar is in abutment on the washer in the arrangement shown in FIG. 3, the end of the cylindrical part 15a of the latch is completely disengaged from the rotor 8 and no longer prohibits the movements of the latter.

Ce maintien est particulièrement sûr en raison de l'appui des languettes 21 sur le support 3.This maintenance is particularly secure due to the support of the tongues 21 on the support 3.

Après libération du rotor par le verrou 15, le fonctionnement du dispositif de sécurité et d'armement est identique à celui décrit dans le brevet FR2533686.After release of the rotor by the latch 15, the operation of the security and arming device is identical to that described in patent FR2533686.

D'une façon connue, le percuteur est maintenu écarté de l'amorce contre l'action du ressort 7 (par exemple au moyen de billes comme le décrit le brevet FR1227037).In a known manner, the striker is kept spaced from the primer against the action of the spring 7 (for example by means of balls as described in patent FR1227037).

Après une temporisation donnée par le déroulement du spiral, le rotor est libéré par les goupilles 14 et il adopte une position alignée.After a time delay given by the unwinding of the hairspring, the rotor is released by the pins 14 and it assumes an aligned position.

Lors de l'impact sur une cible le percuteur est projeté contre l'amorce et initie cette dernière ce qui entraîne l'explosion du projectile.Upon impact on a target, the striker is thrown against the primer and initiates the latter, which causes the projectile to explode.

De façon connue, lorsque le projectile ne rencontre pas de cible la diminution de la vitesse de rotation du projectile va entraîner la libération du percuteur (voir brevet FR1227037). Ce dernier, projeté par son ressort, initie l'amorce ce qui provoque l'autodestruction du projectile.In known manner, when the projectile does not meet a target, the reduction in the speed of rotation of the projectile will lead to the release of the striker (see patent FR1227037). The latter, projected by its spring, initiates the initiation which causes the self-destruction of the projectile.

Le montage du dispositif selon ce premier mode de réalisation de l'invention s'effectue de la façon suivante:

  • Tout d'abord le verrou 15 est positionné dans son alésage du support 3, puis la rondelle ressort 17 est appliquée contre le verrou et son rebord périphérique est mis en place en force dans la gorge 18 du support 3.
The mounting of the device according to this first embodiment of the invention is carried out as follows:
  • First of all, the latch 15 is positioned in its bore of the support 3, then the spring washer 17 is applied against the latch and its peripheral rim is force-fitted into the groove 18 of the support 3.

On obtient ainsi un ensemble de trois pièces (3, 15, 17) totalement solidaires les unes des autres.One thus obtains a set of three parts (3, 15, 17) completely integral with one another.

Cet ensemble reçoit le percuteur et le reste du dispositif d'autodestruction, puis le corps 2 de la fusée est vissé sur le support 3.This assembly receives the striker and the rest of the self-destruction device, then the body 2 of the rocket is screwed onto the support 3.

On positionne ensuite le sous-ensemble, constitué par la cage 10 portant le rotor 8 et le spiral 13, sur l'extrémité de la partie cylindrique 15a du verrou 15. On visse enfin le bouchon 4 sur le corps 2 jusqu'à la mise en butée d'un épaulement périphérique 27 du bouchon 4 sur le corps 2. Les dimensions du bouchon sont déterminées de telle sorte qu'il subsiste, après libération du verrou, un jeu axial fonctionnel entre la cage 10 et le support 3.Then the sub-assembly, consisting of the cage 10 carrying the rotor 8 and the hairspring 13, is positioned on the end of the cylindrical part 15a of the latch 15. Finally, the plug 4 is screwed onto the body 2 until it abutment of a peripheral shoulder 27 of the plug 4 on the body 2. The dimensions of the plug are determined so that, after release of the lock, there is a functional axial clearance between the cage 10 and the support 3.

Ainsi, avec le dispositif selon l'invention, les mouvements axiaux de l'ensemble cage/rotor/spiral relativement au corps de fusée se trouvent interdits par le verrou 15, maintenu en appui contre le rotor par la rondelle 17.Thus, with the device according to the invention, the axial movements of the cage / rotor / hairspring assembly relative to the rocket body are prohibited by the latch 15, held in abutment against the rotor by the washer 17.

Avec un dimensionnement correct des composants, ces mouvements sont interdits dans les gammes de vibrations habituellement rencontrées (et dont les niveaux d'accélération se trouvent bien en deçà de ceux mis en oeuvre lors du tir).With a correct dimensioning of the components, these movements are prohibited in the ranges of vibrations usually encountered (and whose acceleration levels are well below those used during firing).

Avec le dispositif selon l'invention les mouvements de rotation de l'ensemble cage/rotor/spiral par rapport au corps de fusée sont également interdits. En effet l'effort appliqué par le verrou sur le rotor est choisi suffisamment important pour empêcher de telles rotations en raison des frottements de la cage 10 sur le bouchon 4.With the device according to the invention, the rotational movements of the cage / rotor / hairspring assembly relative to the rocket body are also prohibited. In fact, the force applied by the bolt to the rotor is chosen to be large enough to prevent such rotations due to the friction of the cage 10 on the plug 4.

Le verrou 15 se trouve cependant libéré dès les premiers instants du tir puisque cette libération n'utilise que les efforts d'inertie suivant une direction axiale du projectile. Ainsi le mouvement ultérieur de la cage et la libération du rotor par les goupilles ne se trouvent pas perturbés ce qui assure la fiabilité du dispositif de sécurité et d'armement.The latch 15 is however released from the first moments of the firing since this release only uses the inertial forces in an axial direction of the projectile. Thus the subsequent movement of the cage and the release of the rotor by the pins are not disturbed, which ensures the reliability of the security and arming device.

Le dispositif de sécurité et d'armement selon ce premier mode de réalisation est particulièrement simple du point de vue de la fabrication et du montage. Il présente une tenue au stockage en environnements vibratoires sévères qui est améliorée vis à vis de celle des dispositifs de sécurité selon l'état de la technique. Et une telle amélioration ne vient pas pénaliser le coût de production ni la fiabilité de l'armement.The security and arming device according to this first embodiment is particularly simple from the point of view of manufacture and assembly. It has a resistance to storage in severe vibratory environments which is improved with respect to that of safety devices according to the state of the art. And such an improvement does not penalize the cost of production or the reliability of the weaponry.

Un tel dispositif de sécurité et d'armement pourrait éventuellement être adapté à une fusée d'ogive.Such a security and arming device could possibly be adapted to a warhead rocket.

A titre de variante il serait bien entendu possible de remplacer le rotor à cage par un rotor susceptible de tourner dans des logements sphériques ou cylindriques aménagés dans le support et le bouchon, par exemple un rotor du type de celui décrit par le brevet FR2537265.As a variant, it would of course be possible to replace the cage rotor with a rotor capable of rotating in spherical or cylindrical housings arranged in the support and the plug, for example a rotor of the type described by patent FR2537265.

Le verrou interdira alors les vibrations du rotor par rapport à sa cage ce qui évitera la sortie de la composition pyrotechnique hors de l'amorce.The lock will then prevent vibrations of the rotor relative to its cage which will prevent the pyrotechnic composition from leaving the primer.

La figure 4 représente une fusée 1 destinée à être fixée à l'ogive d'un projectile (non représenté).FIG. 4 represents a rocket 1 intended to be fixed to the warhead of a projectile (not shown).

Elle comprend un corps 2 en alliage léger (par exemple d'aluminium) à l'intérieur duquel est disposé un dispositif de sécurité et d'armement selon un deuxième mode de réalisation de l'invention.It comprises a body 2 of light alloy (for example aluminum) inside which is disposed a security and arming device according to a second embodiment of the invention.

Le corps est fermé par un bouchon 4 qui porte une charge pyrotechnique relais 5 dans un logement. Cette charge est destinée de façon connue à assurer la mise à feu d'une charge principale (non représentée) contenue dans le projectile.The body is closed by a plug 4 which carries a relay pyrotechnic charge 5 in a housing. This charge is intended in a known manner to ensure the ignition of a main charge (not shown) contained in the projectile.

La fusée comporte également un dispositif d'autodestruction de type connu (décrit par exemple dans le brevet FR1227037) qui comprend notamment un percuteur 6 qui est poussé par un ressort 7 vers une amorce 9.The rocket also includes a self-destruct device of known type (described for example in patent FR1227037) which notably comprises a striker 6 which is pushed by a spring 7 towards a primer 9.

Une entretoise 28 vient en butée sur le corps 2 de la fusée au niveau d'un épaulement 40 et elle est rendue solidaire du corps 2 au moyen d'un support 3, lui même fileté et vissé au corps 2.A spacer 28 abuts on the body 2 of the rocket at a shoulder 40 and it is made integral with the body 2 by means of a support 3, itself threaded and screwed to the body 2.

Comme dans le mode de réalisation précédemment décrit, le dispositif de sécurité et d'armement comprend un rotor 8 disposé dans une cage 10. La cage porte deux tourillons 11 et 12 qui viennent dans des logements correspondants aménagés respectivement sur le support 3 et le bouchon 4.As in the embodiment described above, the security and arming device comprises a rotor 8 disposed in a cage 10. The cage carries two pins 11 and 12 which come in corresponding housings arranged respectively on the support 3 and the plug 4.

L'ajustement des tourillons dans leurs logements est glissant et il autorise une rotation relative de la cage par rapport au corps de fusée.The adjustment of the pins in their housings is sliding and it allows relative rotation of the cage relative to the rocket body.

Le rotor est immobilisé par un verrou 29 qui est, dans le mode de réalisation décrit ici, une douille à l'intérieur de laquelle peut coulisser le percuteur 6 et qui présente une surface conique 32 dont le sommet est orienté vers une partie avant A de la fusée.The rotor is immobilized by a latch 29 which is, in the embodiment described here, a socket inside which the striker 6 can slide and which has a conical surface 32 whose apex is oriented towards a front part A of the rocket.

La douille comporte une portion cylindrique avant 29a qui vient, en ajustement glissant, dans un logement 33 aménagé sur l'entretoise 28.The sleeve has a front cylindrical portion 29a which comes, in sliding adjustment, into a housing 33 arranged on the spacer 28.

Elle comporte également une portion cylindrique arrière 29b qui vient en appui sur une rainure 16 aménagée sur le rotor.It also includes a rear cylindrical portion 29b which bears on a groove 16 provided on the rotor.

Une bague torique fendue 30 (visible également figure 5) est serrée sur cette partie conique 32 et elle est également en appui sur la face inférieure 28a de l'entretoise 28.A split O-ring 30 (also visible in FIG. 5) is tightened on this conical part 32 and it is also supported on the lower face 28a of the spacer 28.

La bague 30 constitue un moyen d'immobilisation qui assure l'appui du verrou 29 sur le rotor 8The ring 30 constitutes a means of immobilization which ensures the support of the lock 29 on the rotor 8

Le verrou 29 comporte une surface plane 29c qui vient en contact avec une couronne 31 elle même en contact avec le support 3.The latch 29 has a flat surface 29c which comes into contact with a ring 31 itself in contact with the support 3.

La couronne 31 est visible en détail sur les figures 6a et 6b. Il s'agit d'une plaque de tôle à ressort emboutie sensiblement circulaire d'axe 37 et qui porte deux lamelles élastiques 35, disposées de façon symétrique l'une de l'autre relativement à l'axe 37.The crown 31 is visible in detail in Figures 6a and 6b. It is a substantially circular stamped sheet metal plate with an axis 37 and which carries two elastic lamellae 35, arranged symmetrically with respect to the axis 37.

Il serait possible de prévoir un nombre de lamelles N supérieur à deux, elles auront dans tous les cas une répartition angulaire régulière, c'est à dire telle que l'ensemble des lamelles présente une symétrie de rotation d'ordre N autour de l'axe 37.It would be possible to provide for a number of lamellae N greater than two, they will in all cases have a regular angular distribution, that is to say such that all of the lamellae have rotational symmetry of order N around the axis 37.

Ainsi la résultante des efforts qu'elles exerceront sur le verrou 29 sera colinéaire à l'axe 37, c'est à dire à l'axe de la fusée, et on évitera tout coincement du verrou par rapport à l'entretoise 28.Thus the result of the forces they exert on the latch 29 will be collinear with the axis 37, that is to say on the axis of the rocket, and any jamming of the latch relative to the spacer 28 will be avoided.

Les extrémités libres 38 des lamelles ont une découpe en forme d'arcs de cercle dont le centre est positionné sur l'axe 37. Elles sont séparées par un espace libre 34.The free ends 38 of the strips have a cut in the form of arcs of a circle, the center of which is positioned on the axis 37. They are separated by a free space 34.

Le diamètre de la portion cylindrique arrière 29b du verrou est légèrement inférieur (de l'ordre du mm) à celui des extrémités 38 des lamelles qui définissent l'espace libre 34.The diameter of the rear cylindrical portion 29b of the lock is slightly smaller (of the order of mm) than that of the ends 38 of the strips which define the free space 34.

Couronne et lamelles constituent un moyen assurant un maintien du verrou dans une position écartée du rotor après sa libération par le verrou. Le mode d'action des lamelles sera explicité par la suite.Crown and blades constitute a means ensuring that the lock is kept in a position away from the rotor after its release by the lock. The mode of action of the lamellae will be explained later.

Le montage de ce dispositif s'effectue de la façon suivante.The assembly of this device is carried out as follows.

Tout d'abord on positionne la couronne 31 dans son logement cylindrique du support 3, puis on met en place le verrou 29 sur lequel est montée la bague 30 et on coiffe le verrou avec l'entretoise 28. Cette dernière se trouve en appui d'une part sur un épaulement 39 du support 3 et d'autre part sur la bague 30.First of all, the crown 31 is positioned in its cylindrical housing of the support 3, then the lock 29 is put in place on which the ring 30 is mounted and the lock is capped with the spacer 28. The latter is in support of firstly on a shoulder 39 of the support 3 and secondly on the ring 30.

Les dimensions et tolérances de fabrications de ces différentes pièces sont définies de telle sorte qu'il subsiste à ce stade du montage un léger jeu (de l'ordre du dixième de mm) entre les extrémités 38 des lamelles 35 et le support 3. Les lamelles ne se trouvent donc pas en appui contre le support 3.The dimensions and manufacturing tolerances of these different parts are defined so that there remains at this stage of assembly a slight clearance (of the order of a tenth of mm) between the ends 38 of the strips 35 and the support 3. The slats are therefore not in abutment against the support 3.

On positionne ensuite le dispositif d'autodestruction dans l'entretoise 28 et on visse le corps 2 jusqu'à mise en butée de l'entretoise 28 sur l'épaulement 40 du corps.The self-destruct device is then positioned in the spacer 28 and the body 2 is screwed until the spacer 28 is brought into abutment on the shoulder 40 of the body.

Le rotor monté dans sa cage est ensuite mis en place en position engagée sur le verrou 29 et enfin on visse le bouchon 4 sur le corps 2 jusqu'à la mise en butée d'un épaulement périphérique 27 du bouchon 4 sur le corps 2.The rotor mounted in its cage is then put in place in the engaged position on the latch 29 and finally the plug 4 is screwed onto the body 2 until a peripheral shoulder 27 of the plug 4 is brought into abutment on the body 2.

Les dimensions du bouchon et la longueur totale du verrou 29 sont choisies de telle sorte que le verrou 29 soit en appui sur la rainure 16 et qu'il subsiste un jeu axial fonctionnel entre la cage 10 et le support 3 après libération du verrou.The dimensions of the plug and the total length of the latch 29 are chosen so that the latch 29 is supported on the groove 16 and that there remains a functional axial clearance between the cage 10 and the support 3 after release of the latch.

Le fonctionnement du dispositif est le suivant: Lors du tir de la munition et sous l'effet des efforts d'inertie axiaux qui s'exercent sur la bague 30, cette dernière se déplace vers la partie arrière D de la fusée.The operation of the device is as follows: When firing the ammunition and under the effect of the axial inertia forces exerted on the ring 30, the latter moves towards the rear part D of the rocket.

La surface conique 32 provoque l'ouverture de la bague.The conical surface 32 causes the opening of the ring.

La bague achève de s'ouvrir et vient en contact avec la surface de l'alésage 41 sous l'action des efforts d'inertie de rotation qui s'exercent peu de temps avant la sortie du tube de l'arme.The ring completes to open and comes into contact with the surface of the bore 41 under the action of the inertial forces of rotation which are exerted shortly before the exit of the barrel from the weapon.

Le retrait de la bague 30 autorise le déplacement du verrou 29 vers la partie avant A de la fusée sous l'action des lamelles 35 et de la décélération. Ces dernières sont dimensionnées de telle sorte qu'elles puissent dégager la partie avant 29b du verrou de la rainure 16 du rotor. Le logement 33 de la partie arrière de la douille dans l'entretoise 28 sera également de : profondeur suffisante pour permettre un tel dégagement.The withdrawal of the ring 30 authorizes the displacement of the lock 29 towards the front part A of the rocket under the action of the lamellae 35 and the deceleration. The latter are dimensioned so that they can disengage the front part 29b from the lock of the groove 16 of the rotor. The housing 33 of the rear part of the socket in the spacer 28 will also be: sufficient depth to allow such clearance.

La figure 7 montre le dispositif de sécurité et d'armement selon ce deuxième mode de réalisation après effacement du verrou et avant la libération du rotor par les goupilles 14. La bague 30, ouverte par les efforts d'inertie, est appliquée d'une part contre la couronne 31 et d'autre part contre l'alésage 41 du support 3.Figure 7 shows the security and arming device according to this second embodiment after clearing the lock and before the release of the rotor by the pins 14. The ring 30, opened by the inertia forces, is applied with part against the crown 31 and on the other hand against the bore 41 of the support 3.

La bague assure ainsi un maintien de la couronne relativement au corps de fusée et permet à cette dernière de maintenir le verrou immobile relativement au corps de fusée.The ring thus maintains the crown relative to the rocket body and allows the latter to keep the lock stationary relative to the rocket body.

On interdit ainsi les mouvements axiaux du verrou qui seraient susceptibles de venir perturber la rotation de la cage, en particulier le verrou ne risque pas de se trouver entraîné par le percuteur lors de l'impact sur une cible.This prohibits axial movements of the lock which would be likely to disturb the rotation of the cage, in particular the lock is not likely to be driven by the striker upon impact on a target.

Tout comme le précédent, ce mode de réalisation de l'invention permet d'interdire les mouvements axiaux de l'ensemble cage/rotor/spiral relativement au corps de fusée grâce au verrou 29 maintenu en appui contre le rotor par la bague 30.Like the previous one, this embodiment of the invention makes it possible to prohibit the axial movements of the cage / rotor / hairspring assembly relative to the rocket body by virtue of the bolt 29 held in abutment against the rotor by the ring 30.

Avec le dispositif selon l'invention les mouvements de rotation de l'ensemble cage/rotor/spiral par rapport au corps de fusée sont également interdits.With the device according to the invention, the rotational movements of the cage / rotor / hairspring assembly relative to the rocket body are also prohibited.

En effet l'effort appliqué par le verrou sur le rotor est suffisant pour empêcher de telles rotations en raison des frottements de la cage 10 sur le bouchon 4.In fact, the force applied by the lock on the rotor is sufficient to prevent such rotations due to the friction of the cage 10 on the plug 4.

Le verrou 29 se trouve cependant libéré dès les premiers instants du tir puisque cette libération n'utilise que les efforts d'inertie suivant une direction axiale du projectile. Ainsi le mouvement ultérieur de la cage et la libération du rotor par les goupilles ne se trouvent pas perturbés ce qui assure la fiabilité du dispositif de sécurité et d'armement.The lock 29 is however released from the first moments of the firing since this release only uses the inertial forces in an axial direction of the projectile. Thus the subsequent movement of the cage and the release of the rotor by the pins are not disturbed which ensures the reliability of the security and arming device.

Le dispositif de sécurité et d'armement selon ce deuxième mode de réalisation est particulièrement adapté à la mise en place dans une fusée d'ogive.The security and arming device according to this second embodiment is particularly suitable for fitting into a warhead rocket.

Il présente également l'avantage d'assurer pendant le stockage un blocage complet du rotor et de la cage relativement au corps de fusée donc une tenue dans les environnements vibratoires les plus sévères.It also has the advantage of ensuring during storage a complete blocking of the rotor and of the cage relative to the rocket body, therefore a resistance in the most severe vibratory environments.

Une telle tenue est assurée sans que la fiabilité de l'armement ne soit diminuée.Such behavior is ensured without reducing the reliability of the weaponry.

A titre de variante, il serait bien entendu également possible de remplacer le rotor à cage par un rotor susceptible de tourner dans des logements sphériques ou cylindriques aménagés dans le support et le bouchon, par exemple un rotor du type de celui décrit par le brevet FR2537265.As a variant, it would of course also be possible to replace the cage rotor with a rotor capable of rotating in spherical or cylindrical housings arranged in the support and the plug, for example a rotor of the type described by patent FR2537265 .

Le verrou interdira alors les vibrations relatives du rotor dans sa cage ce qui évitera la sortie de la composition pyrotechnique hors de l'amorce.The lock will then prohibit the relative vibrations of the rotor in its cage, which will prevent the pyrotechnic composition from leaving the primer.

Claims (10)

1-Dispositif de sécurité et d'armement pour une fusée (1) destinée à équiper un projectile girant, dispositif comportant un rotor (8) qui porte une amorce (9) et se trouve maintenu par un verrou (15,29) dans une position dans laquelle l'amorce n'est pas alignée avec une chaine pyrotechnique principale, dispositif caractérisé en ce que le verrou (15,29) est maintenu en appui sur le rotor (8) par un moyen d'immobilisation (17,30) suffisamment rigide pour maintenir cet appui lorsque le dispositif est soumis à des contraintes de choc ou de vibration, moyen d'immobilisation libérant le verrou (15,29) consécutivement au tir du projectile.1-Safety and arming device for a rocket (1) intended to equip a gyrating projectile, device comprising a rotor (8) which carries a primer (9) and is held by a lock (15,29) in a position in which the primer is not aligned with a main pyrotechnic chain, device characterized in that the latch (15,29) is held in abutment on the rotor (8) by an immobilizing means (17,30 ) rigid enough to maintain this support when the device is subjected to shock or vibration stresses, immobilization means releasing the bolt (15,29) following the firing of the projectile. 2-Dispositif de sécurité et d'armement selon la revendication 1, caractérisé en ce qu'il comprend des moyens (21,31) assurant un maintien du verrou (15,29) dans une position écartée du rotor (8) après sa libération par le moyen d'immobilisation (17,30).2-A security and arming device according to claim 1, characterized in that it comprises means (21,31) ensuring maintenance of the lock (15,29) in a position away from the rotor (8) after its release by the immobilization means (17,30). 3-Dispositif de sécurité et d'armement selon une des revendications 1 ou 2, caractérisé en ce que le moyen d'immobilisation comprend une rondelle élastique (17) qui présente un rebord périphérique (20) venant en appui sur un corps (2) de fusée et une partie centrale (24) constituée par au moins deux languettes (21), régulièrement réparties angulairement, et qui viennent en appui sur le verrou (15) et sont susceptibles de se déformer de manière à laisser passer ce dernier lorsqu'il est entrainé par son inertie lors du tir du projectile.3-Safety and arming device according to one of claims 1 or 2, characterized in that the immobilization means comprises an elastic washer (17) which has a peripheral rim (20) bearing on a body (2) rocket and a central part (24) consisting of at least two tabs (21), regularly distributed angularly, and which come to bear on the latch (15) and are liable to deform so as to allow the latter to pass when it is driven by its inertia when firing the projectile. 4-Dispositif de sécurité et d'armement selon la revendication 3, caractérisé en ce que le verrou (15) présente une collerette (19) sur laquelle les languettes (21) viennent en appui et une partie cylindrique (15a) susceptible de passer librement entre les languettes et en ce que les moyens assurant le maintien du verrou dans une position écartée sont constitués par les languettes (21) elles-même qui forment une butée pour la collerette (19) après le passage de cette dernière au travers de la rondelle (17).4-Security and arming device according to claim 3, characterized in that the latch (15) has a flange (19) on which the tongues (21) come to rest and a cylindrical part (15a) capable of passing freely between the tongues and in that the means ensuring the retention of the latch in a separated position are constituted by the tongues (21) themselves which form a stop for the flange (19) after the passage of the latter through the washer (17). 5-Dispositif de sécurité et d'armement selon une des revendications 3 ou 4, caractérisé en ce que le rebord périphérique (20) de la rondelle (17) vient se loger dans une gorge (18) du corps de fusée.5-Safety and arming device according to one of claims 3 or 4, characterized in that the peripheral flange (20) of the washer (17) is received in a groove (18) of the rocket body. 6-Dispositif de sécurité et d'armement selon une des revendications 1 ou 2, caractérisé en ce que le moyen d'immobilisation comprend une bague fendue (30) qui est en appui d'une part sur le corps (2) de fusée et d'autre part sur une surface conique (32) du verrou (29), bague susceptible de s'ouvrir et libérer ainsi le verrou (29) lorsqu'elle est entrainée par son inertie lors du tir du projectile.6-Security and arming device according to one of claims 1 or 2, characterized in that the immobilization means comprises a split ring (30) which is supported on the one hand on the body (2) of rocket and on the other hand on a conical surface (32) of the latch (29), ring capable of opening and thus releasing the latch (29) when it is driven by its inertia when the projectile is fired. 7-Dispositif de sécurité et d'armement selon la revendication 6, caractérisé en ce que les moyens assurant un maintien du verrou (29) dans une position écartée du rotor (8) comprennent une couronne (31) portant au moins deux lamelles (35), déformables élastiquement et régulièrement réparties angulairement, lamelles maintenues comprimées par une surface plane (29c) du verrou lorsque ce dernier est en appui sur le rotor (8) et qui dégagent le verrou (29) du rotor lorsqu'il se trouve libéré par la bague (30).7-A security and arming device according to claim 6, characterized in that the means ensuring that the lock (29) is held in a position away from the rotor (8) comprises a ring (31) carrying at least two blades (35 ), elastically deformable and regularly distributed angularly, strips kept compressed by a flat surface (29c) of the lock when the latter is in contact with the rotor (8) and which release the lock (29) from the rotor when it is released by the ring (30). 8-Dispositif de sécurité et d'armement selon la revendication 7, caractérisé en ce que lorsque la bague (30) est entraînée par son inertie lors du tir du projectile, elle vient maintenir la couronne (31) en appui contre le corps (2) de fusée.8-A security and arming device according to claim 7, characterized in that when the ring (30) is driven by its inertia when the projectile is fired, it keeps the crown (31) in abutment against the body (2 ) rocket. 9-Dispositif de sécurité et d'armement selon une des revendications 1 à 8, caractérisé en ce que le rotor (8) est disposé à l'intérieur d'une cage (10), montée tournante relativement au corps de fusée et autour de l'axe de cette dernière.9-Safety and arming device according to one of claims 1 to 8, characterized in that the rotor (8) is arranged inside a cage (10), mounted so as to rotate relative to the rocket body and around the axis of the latter. 10-Dispositif de sécurité et d'armement selon une des revendications 1 à 9, caractérisé en ce que le verrou (15,29) est constitué par une douille coaxiale à la fusée et au travers de laquelle est susceptible de coulisser un percuteur (6) destiné à initier l'amorce (9).10-Security and arming device according to one of claims 1 to 9, characterized in that the lock (15,29) is constituted by a sleeve coaxial with the rocket and through which is capable of sliding a striker (6 ) intended to initiate the primer (9).
EP93400950A 1992-04-14 1993-04-13 Safety and arming device for the fuse of a projectile comprising an anti-vibratory means Expired - Lifetime EP0566469B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9204572 1992-04-14
FR9204572A FR2689972B1 (en) 1992-04-14 1992-04-14 SECURITY AND ARMING DEVICE FOR A PROJECTILE ROCKET COMPRISING AN ANTI-VIBRATORY MEANS.

Publications (2)

Publication Number Publication Date
EP0566469A1 true EP0566469A1 (en) 1993-10-20
EP0566469B1 EP0566469B1 (en) 1996-11-13

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EP (1) EP0566469B1 (en)
AT (1) ATE145280T1 (en)
DE (1) DE69305907T2 (en)
ES (1) ES2095594T3 (en)
FR (1) FR2689972B1 (en)
GR (1) GR3022520T3 (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004065891A2 (en) * 2003-01-24 2004-08-05 Olympic Technologies Limited Safety system for the ignition chain of a projectile fuze
CN103900426A (en) * 2014-04-23 2014-07-02 安徽理工大学 Mechanical safety detonator
EP3121553A1 (en) 2015-07-24 2017-01-25 Nexter Munitions Safing and arming device for a nose mounted fuze and fuze comprising such a device
WO2023180278A1 (en) * 2022-03-23 2023-09-28 Rheinmetall Air Defence Ag Safety device for an igniter, use of the safety device and method of activating an igniter with this safety device

Families Citing this family (5)

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Publication number Priority date Publication date Assignee Title
FR2730051B1 (en) * 1995-01-30 1997-03-21 Manurhin Defense SECURITY AND ARMING DEVICE FOR PROJECTILE ROCKET
FR2944348A1 (en) 2009-04-10 2010-10-15 Nexter Munitions PERCUSSION MUNITING DEVICE
FR2959303B1 (en) 2010-04-27 2012-04-06 Nexter Munitions ELECTRICALLY INITIATED STARTING DEVICE FOR PROJECTILE
FR2959304B1 (en) 2010-04-27 2014-10-17 Nexter Munitions INFLATION-BASED INITIATION STARTING DEVICE FOR PROJECTILE
FR2965044B1 (en) 2010-09-22 2012-08-24 Nexter Munitions SAFETY AND ARMING DEVICE FOR GYROSTABILIZED EXPLOSIVE PROJECTILE AND STARTING DEVICE USING SUCH A SAFETY AND ARMING DEVICE

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US3595169A (en) * 1969-09-18 1971-07-27 Gen Electric Time delay fuze
FR2500150A1 (en) * 1981-02-18 1982-08-20 Diehl Gmbh & Co CENTRIFUGAL SENSITIVE SAFETY DEVICE FOR THE PERCUTOR OF A PROJECTILE PERCUSSION ROCKET
FR2533686A1 (en) * 1982-09-24 1984-03-30 Manurhin SECURITY DEVICE WITH A ROTATING CAGE FOR A GIRATORY PROJECTILE
US4480551A (en) * 1983-06-08 1984-11-06 Whittaker Corporation Point-detonating variable time-delayed fuze
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2004065891A2 (en) * 2003-01-24 2004-08-05 Olympic Technologies Limited Safety system for the ignition chain of a projectile fuze
WO2004065891A3 (en) * 2003-01-24 2004-09-16 Olympic Technologies Ltd Safety system for the ignition chain of a projectile fuze
US7360486B2 (en) 2003-01-24 2008-04-22 Olympic Technologies Ltd Safety system for the ignition chain of a projectile fuze
CN103900426A (en) * 2014-04-23 2014-07-02 安徽理工大学 Mechanical safety detonator
CN103900426B (en) * 2014-04-23 2015-11-18 安徽理工大学 A kind of safety mechanical detonator
EP3121553A1 (en) 2015-07-24 2017-01-25 Nexter Munitions Safing and arming device for a nose mounted fuze and fuze comprising such a device
FR3039267A1 (en) * 2015-07-24 2017-01-27 Nexter Munitions SAFETY AND ARMING DEVICE FOR AN OGIVE ROCKET AND ROCKER COMPRISING SUCH A DEVICE
US10041775B2 (en) 2015-07-24 2018-08-07 Nexter Munitions Safety and arming device for an instant impact point fuse and fuse including such a device
WO2023180278A1 (en) * 2022-03-23 2023-09-28 Rheinmetall Air Defence Ag Safety device for an igniter, use of the safety device and method of activating an igniter with this safety device

Also Published As

Publication number Publication date
FR2689972A1 (en) 1993-10-15
FR2689972B1 (en) 1995-08-11
EP0566469B1 (en) 1996-11-13
DE69305907D1 (en) 1996-12-19
ATE145280T1 (en) 1996-11-15
GR3022520T3 (en) 1997-05-31
ES2095594T3 (en) 1997-02-16
DE69305907T2 (en) 1997-03-06

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