EP2703769B1 - Device for the deconfinement of an ammunition casing - Google Patents

Device for the deconfinement of an ammunition casing Download PDF

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Publication number
EP2703769B1
EP2703769B1 EP13180938.6A EP13180938A EP2703769B1 EP 2703769 B1 EP2703769 B1 EP 2703769B1 EP 13180938 A EP13180938 A EP 13180938A EP 2703769 B1 EP2703769 B1 EP 2703769B1
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EP
European Patent Office
Prior art keywords
ring
rocket
fuze
ammunition
thread
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EP13180938.6A
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German (de)
French (fr)
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EP2703769A1 (en
Inventor
Dominique Dion
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Nexter Munitions SA
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Nexter Munitions SA
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Publication date
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Priority to PL13180938T priority Critical patent/PL2703769T3/en
Publication of EP2703769A1 publication Critical patent/EP2703769A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B39/00—Packaging or storage of ammunition or explosive charges; Safety features thereof; Cartridge belts or bags
    • F42B39/20—Packages or ammunition having valves for pressure-equalising; Packages or ammunition having plugs for pressure release, e.g. meltable ; Blow-out panels; Venting arrangements
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/02—Fuze bodies; Fuze housings

Definitions

  • the technical field of the invention is that of ammunition rockets which are intended to ensure the initiation of an explosive charge placed in an envelope and more particularly rockets that can also ensure a deconfinement of the ammunition envelope as a result to a warm-up, for example during a fire.
  • the patent US7025000 describes a projectile for which the rocket is linked to the projectile body by a fusible plastic ring.
  • the ring carries a tapping receiving the rocket and a thread engaged in the projectile body. This ring alone ensures the mechanical strength of the projectile rocket link during firing and it also ensures the deconfinement by its melting during the rise in temperature.
  • This device has disadvantages. It is thus difficult to find a material that can both withstand the shooting and handling constraints of the projectile and can also melt quickly and reproducibly to release the rocket.
  • the patent EP2079980 proposes a connecting ring which is interposed between the projectile body and the rocket. This ring carries an intermediate ring which receives the rocket. During a rise in the pressure in the ammunition body, the intermediate ring is sheared and releases the rocket.
  • the invention aims to provide a rocket incorporating means ensuring its deconfinement, means having a reduced radial size.
  • the means of the invention provide deconfinement in a reliable and reproducible manner while not weakening the mechanical strength of the rocket / projectile link to firing constraints (axial and angular accelerations).
  • the invention relates to a firing rocket intended to be secured to a shell of a munition containing an explosive charge, rocket characterized in that it comprises a smooth outer cylindrical surface on which is slidably positioned a ring bearing a thread on its outer surface, thread intended to cooperate with a tapping of the ammunition envelope, the ring being made integral in rotation with the body of the rocket by at least one longitudinal key, the rocket also carrying a rod shear forming an axial stop for the ring during the sliding thereof after mounting the rocket on the envelope.
  • the ring may have an annular shape and be housed in a groove of the rocket.
  • the ring may include a counterbore coming to cap the ring during screwing.
  • the ring may be made of steel.
  • the ring may be made of a synthetic material.
  • a firing rocket 1 according to the invention is shown integral with an envelope 2a of a munition 2 which defines an internal cavity 2b enclosing an explosive charge (not shown).
  • the ammunition 2 is for example an artillery shell.
  • the rocket 1 is shown schematically here, because the characteristics thereof being the subject of the invention are relative to the only means for fixing it to the casing 2a of the ammunition.
  • the rocket has a front portion 1a ogivĂ©e, which is schematized in part dashed, and which contains electronic or mechanical means for its operation: safety device and armament, electronic components associated with the firing control (according to the case: chronometry, proximetry), pyrotechnic priming components and their means of initiation.
  • the rear part 1b of the fuse 1 which is engaged in the internal cavity 2b of the ammunition conventionally contains a pyrotechnic detonation relay (not shown).
  • the rocket 1 is thus uniformly hatched to simplify the representation. This hatching does not prejudge the internal structure of the rocket which is neither represented nor described.
  • the rocket 1 has an outer smooth cylindrical bearing surface 3, of longitudinal axis 8, on which is slidably positioned a ring 4 carrying a thread 4a on its outer surface.
  • This thread 4a is intended to cooperate with a complementary tapping 5 carried by the shell 2a of ammunition (see also FIG. figure 3 ).
  • the ring 4 is also made integral in rotation with the body of the rocket 1 by at least one longitudinal key 6 (here there are four longitudinal keys, regularly distributed angularly).
  • each key 6 is housed in a recess 7 machined in the body of the fuse 1 and having a shape complementary to that of the key 6.
  • the keys and their fingerprints 7 have hemicylindrical ends, this for ease of machining.
  • the keys 6 are immobilized in translation by the impressions 7 in a direction parallel to the axis 8 of the rocket.
  • the ring 4 comprises longitudinal grooves 9 which each receive one of the keys 6. These grooves 9 are open from one end to the other of the ring 4. Thus, when the ring 4 is positioned on the cylindrical seat 3, it slides freely in the axial direction 8 and is integral in rotation with the rocket by the keys 6 which interpose between the grooves 9 of the ring 4 and the footprints 7 of the rocket.
  • the rocket 3 finally carries a shearable annular ring 10 which is positioned in a circular groove 11 of the rocket 1.
  • the ring 10 is made of a synthetic material, for example polytetrafluoroethylene (PTFE). It is put in place in its groove 11 by mechanical deformation.
  • PTFE polytetrafluoroethylene
  • the ring 10 forms an axial stop for the ring 4 during sliding thereof.
  • the ring 4 comprises at each end a countersink 12.
  • the counterbores have a diameter slightly greater than that of the ring 10.
  • one of the counterbores 12 caps the ring 10 (as shown figure 4b ).
  • the ring can slide because there is an axial clearance E ( figure 4a ) between the ring 4 and its housing on the seat 3, housing which has a total length P between the rod 12 and a shoulder 13 of the rocket 1.
  • the rocket according to the invention is mounted conventionally by screwing at the tapping 5 of a shell 2a of ammunition.
  • the thread of the rocket is no longer a fixed thread relative to the rocket body but a thread carried by a sliding ring 4.
  • the keys 6 prevent rotation of the ring which allows a first screwing step until abutment of the shoulder 13 of the rocket against the end of the casing 2a (see figure 4a ).
  • the screwing is no longer possible and the rocket 1 is immobilized relative to the envelope 2a.
  • a conventional solution such as a drop of glue deposited before screwing and which will dry, thus blocking the screwing, or a net stop mechanical as a radial screw engaged through the casing 2a and stopping at the thread 4a.
  • the gas pressure (arrow HP) that develops in the internal cavity 2b will be exerted on the rear part 1b of the rocket.
  • the ring 10 will be sheared and the rocket 1 will be ejected, thus ensuring deconfinement of the munition.
  • the ring 4 is made of a resistant material, for example steel.
  • the projectile rocket link is via the ring 4 and the keys 6 also made of steel.
  • the mechanical strength of this connection is excellent and the radial size of the ring is reduced (ring thickness less than 5 mm).
  • the deconfining depends only on the shear strength characteristics of the rod 10 which is dimensioned accordingly and which is made of a material chosen to be sheared at a given stress level. Furthermore the material of the ring may be softened by heating which will facilitate deconfinement.

Description

Le domaine technique de l'invention est celui des fusées de munitions qui sont destinées à assurer l'amorçage d'un chargement explosif mis en place dans une enveloppe et plus particulièrement des fusées pouvant assurer également un déconfinement de l'enveloppe de munition comme suite à un échauffement, par exemple lors d'un incendie.The technical field of the invention is that of ammunition rockets which are intended to ensure the initiation of an explosive charge placed in an envelope and more particularly rockets that can also ensure a deconfinement of the ammunition envelope as a result to a warm-up, for example during a fire.

Il est connu d'assurer un tel déconfinement en utilisant une bague fusible assurant la liaison de la fusée et de l'enveloppe de projectile.It is known to ensure such deconfinement using a fuse ring ensuring the connection of the rocket and the projectile envelope.

Le brevet US7025000 décrit un projectile pour lequel la fusée est liée au corps de projectile par une bague en matière plastique fusible. La bague porte un taraudage recevant la fusée et un filetage engagé dans le corps de projectile. Cette bague assure donc à elle seule la tenue mécanique de la liaison fusée projectile lors du tir et elle assure également le déconfinement par sa fusion lors de l'élévation de la température.The patent US7025000 describes a projectile for which the rocket is linked to the projectile body by a fusible plastic ring. The ring carries a tapping receiving the rocket and a thread engaged in the projectile body. This ring alone ensures the mechanical strength of the projectile rocket link during firing and it also ensures the deconfinement by its melting during the rise in temperature.

Ce dispositif présente des inconvénients. Il est ainsi délicat de trouver un matériau pouvant à la fois résister parfaitement aux contraintes de tir et de manipulation du projectile et pouvant également fondre de façon rapide et reproductible pour libérer la fusée.This device has disadvantages. It is thus difficult to find a material that can both withstand the shooting and handling constraints of the projectile and can also melt quickly and reproducibly to release the rocket.

Le brevet EP2079980 propose une bague de liaison qui est interposée entre le corps de projectile et la fusée. Cette bague porte une bague intermédiaire qui reçoit la fusée. Lors d'une élévation de la pression dans le corps de munition, la bague intermédiaire est cisaillée et elle libère la fusée.The patent EP2079980 proposes a connecting ring which is interposed between the projectile body and the rocket. This ring carries an intermediate ring which receives the rocket. During a rise in the pressure in the ammunition body, the intermediate ring is sheared and releases the rocket.

Cette solution fonctionne bien mais elle présente comme inconvénient d'être relativement encombrante radialement. Il est en effet nécessaire de prévoir une bague de raccordement de la fusée au corps, bague qui porte elle-même une bague intermédiaire cisaillable.This solution works well but it has the disadvantage of being relatively bulky radially. It is indeed necessary to provide a connecting ring of the rocket body, ring which itself carries a shearable intermediate ring.

Si la solution décrite par le brevet EP2079980 est bien adaptée au domaine de l'artillerie de 155 mm ou aux projectiles de char de 120mm, elle est difficilement transposable pour des raisons d'encombrement radial à des calibres inférieurs comme le 105 mm ou le 90mm.If the solution described by the patent EP2079980 is well adapted to the field of artillery of 155 mm or to projectiles of tank of 120mm, it is difficult to be transposed for reasons of radial dimensions to lower calibers like the 105 mm or the 90mm.

L'invention a pour objet de proposer une fusée incorporant des moyens assurant son déconfinement, moyens présentant un encombrement radial réduit.The invention aims to provide a rocket incorporating means ensuring its deconfinement, means having a reduced radial size.

Les moyens de l'invention assurent un déconfinement de façon fiable et reproductible tout en ne fragilisant pas la résistance mécanique de la liaison fusée / projectile aux contraintes de tir (accélérations axiales et angulaires).The means of the invention provide deconfinement in a reliable and reproducible manner while not weakening the mechanical strength of the rocket / projectile link to firing constraints (axial and angular accelerations).

Ainsi l'invention a pour objet une fusée d'amorçage destinée à être rendue solidaire d'une enveloppe d'une munition renfermant un chargement explosif, fusée caractérisée en ce qu'elle comporte une portée cylindrique lisse externe sur laquelle est positionnée de façon glissante une bague portant un filetage sur sa surface externe, filetage destiné à coopérer avec un taraudage de l'enveloppe de munition, la bague étant rendue solidaire en rotation du corps de la fusée par au moins une clavette longitudinale, la fusée portant par ailleurs un jonc cisaillable formant une butée axiale pour la bague lors du coulissement de celle-ci consécutif au montage de la fusée sur l'enveloppe.Thus, the invention relates to a firing rocket intended to be secured to a shell of a munition containing an explosive charge, rocket characterized in that it comprises a smooth outer cylindrical surface on which is slidably positioned a ring bearing a thread on its outer surface, thread intended to cooperate with a tapping of the ammunition envelope, the ring being made integral in rotation with the body of the rocket by at least one longitudinal key, the rocket also carrying a rod shear forming an axial stop for the ring during the sliding thereof after mounting the rocket on the envelope.

Avantageusement le jonc pourra avoir une forme annulaire et se loger dans une gorge de la fusée.Advantageously, the ring may have an annular shape and be housed in a groove of the rocket.

La bague pourra comporter un lamage venant coiffer le jonc lors du vissage.The ring may include a counterbore coming to cap the ring during screwing.

La bague pourra être réalisée en acier.The ring may be made of steel.

Le jonc pourra être réalisé en un matériau synthétique.The ring may be made of a synthetic material.

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

  • la figure 1 est une vue schĂ©matique en coupe longitudinale de l'extrĂ©mitĂ© avant d'une munition portant une fusĂ©e selon l'invention,
  • la figure 2 est un vue Ă©clatĂ©e de la fusĂ©e selon l'invention,
  • la figure 3 est une vue Ă©clatĂ©e en perspective de la fusĂ©e selon l'invention et de l'extrĂ©mitĂ© avant de la munition,
  • les figures 4a et 4b sont des vues partielles et agrandies en coupe longitudinale de la fusĂ©e montrant la portĂ©e cylindrique externe et la bague, la figure 4a Ă©tant la position initiale de la bague lors de la mise en butĂ©e de la fusĂ©e sur l'enveloppe après une première Ă©tape de vissage et la figure 4b Ă©tant la position finale de la bague après la deuxième Ă©tape de vissage.
The invention will be better understood on reading the following description of a particular embodiment, a description given with reference to the appended drawings and in which:
  • the figure 1 is a schematic view in longitudinal section of the front end of a munition carrying a rocket according to the invention,
  • the figure 2 is an exploded view of the rocket according to the invention,
  • the figure 3 is an exploded perspective view of the rocket according to the invention and the front end of the ammunition,
  • the Figures 4a and 4b are partial and enlarged views in longitudinal section of the rocket showing the external cylindrical bearing surface and the ring, the figure 4a being the initial position of the ring during the abutment of the rocket on the envelope after a first screwing step and the figure 4b being the final position of the ring after the second screwing step.

En se reportant à la figure 1, une fusée d'amorçage 1 selon l'invention est représentée solidaire d'une enveloppe 2a d'une munition 2 qui délimite une cavité interne 2b renfermant un chargement explosif (non représenté). La munition 2 est par exemple un obus d'artillerie.Referring to the figure 1 , a firing rocket 1 according to the invention is shown integral with an envelope 2a of a munition 2 which defines an internal cavity 2b enclosing an explosive charge (not shown). The ammunition 2 is for example an artillery shell.

La fusée 1 est représentée ici de façon schématique, car les caractéristiques de celle-ci faisant l'objet de l'invention sont relatives aux seuls moyens permettant sa fixation à l'enveloppe 2a de la munition.The rocket 1 is shown schematically here, because the characteristics thereof being the subject of the invention are relative to the only means for fixing it to the casing 2a of the ammunition.

Ainsi la fusée comporte une partie avant 1a ogivée, qui est schématisée partiellement en pointillés, et qui renferme des moyens électroniques ou mécaniques permettant son fonctionnement : dispositif de sécurité et d'armement, composants électroniques associés à la commande de mise à feu (selon le cas : chronométrie, proximétrie), composants pyrotechniques d'amorçage et leurs moyens d'initiation.Thus the rocket has a front portion 1a ogivée, which is schematized in part dashed, and which contains electronic or mechanical means for its operation: safety device and armament, electronic components associated with the firing control (according to the case: chronometry, proximetry), pyrotechnic priming components and their means of initiation.

Ces éléments sont classiques et ne font pas l'objet de la présente invention, il est donc inutile de les décrire en détails.These elements are conventional and are not the subject of the present invention, it is therefore unnecessary to describe them in detail.

La partie arrière 1b de la fusée 1 qui est engagée dans la cavité interne 2b de la munition renferme de façon classique un relais pyrotechnique de détonation (non représenté).The rear part 1b of the fuse 1 which is engaged in the internal cavity 2b of the ammunition conventionally contains a pyrotechnic detonation relay (not shown).

Sur les figures la fusée 1 est ainsi uniformément hachurée pour simplifier la représentation. Ce hachurage ne préjuge pas de la structure interne de la fusée qui n'est ni représentée, ni décrite.In the figures the rocket 1 is thus uniformly hatched to simplify the representation. This hatching does not prejudge the internal structure of the rocket which is neither represented nor described.

Conformément à l'invention, la fusée 1 comporte une portée cylindrique 3 lisse externe, d'axe longitudinal 8, sur laquelle est positionnée de façon glissante une bague 4 portant un filetage 4a sur sa surface externe.According to the invention, the rocket 1 has an outer smooth cylindrical bearing surface 3, of longitudinal axis 8, on which is slidably positioned a ring 4 carrying a thread 4a on its outer surface.

Ce filetage 4a est destiné à coopérer avec un taraudage complémentaire 5 porté par l'enveloppe 2a de munition (voir aussi la figure 3).This thread 4a is intended to cooperate with a complementary tapping 5 carried by the shell 2a of ammunition (see also FIG. figure 3 ).

La bague 4 est par ailleurs rendue solidaire en rotation du corps de la fusée 1 par au moins une clavette longitudinale 6 (il y a ici quatre clavettes longitudinales, régulièrement réparties angulairement).The ring 4 is also made integral in rotation with the body of the rocket 1 by at least one longitudinal key 6 (here there are four longitudinal keys, regularly distributed angularly).

Comme on le voit sur les figures 2 et 3, chaque clavette 6 se loge dans une empreinte 7 usinée dans le corps de la fusée 1 et ayant une forme complémentaire de celles de la clavette 6.As we see on the figures 2 and 3 each key 6 is housed in a recess 7 machined in the body of the fuse 1 and having a shape complementary to that of the key 6.

On voit sur la figure 3 que les clavettes et leurs empreintes 7 ont des extrémités hémicylindriques, ceci pour des facilités d'usinage. Les clavettes 6 sont immobilisées en translation par les empreintes 7 suivant une direction parallèle à l'axe 8 de la fusée.We see on the figure 3 that the keys and their fingerprints 7 have hemicylindrical ends, this for ease of machining. The keys 6 are immobilized in translation by the impressions 7 in a direction parallel to the axis 8 of the rocket.

La bague 4 comporte des rainures longitudinales 9 qui reçoivent chacune une des clavettes 6. Ces rainures 9 sont débouchantes d'une extrémité à l'autre de la bague 4. Ainsi, lorsque la bague 4 est positionnée sur la portée cylindrique 3, elle coulisse librement suivant la direction axiale 8 et elle est solidaire en rotation de la fusée par les clavettes 6 qui s'interposent entre les rainures 9 de la bague 4 et les empreintes 7 de la fusée.The ring 4 comprises longitudinal grooves 9 which each receive one of the keys 6. These grooves 9 are open from one end to the other of the ring 4. Thus, when the ring 4 is positioned on the cylindrical seat 3, it slides freely in the axial direction 8 and is integral in rotation with the rocket by the keys 6 which interpose between the grooves 9 of the ring 4 and the footprints 7 of the rocket.

La fusée 3 porte enfin un jonc annulaire 10 cisaillable qui se positionne dans une gorge circulaire 11 de la fusée 1.The rocket 3 finally carries a shearable annular ring 10 which is positioned in a circular groove 11 of the rocket 1.

Le jonc 10 est réalisé en un matériau synthétique, par exemple en polytétrafluoréthylène (PTFE). Il est mis en place dans sa gorge 11 par déformation mécanique.The ring 10 is made of a synthetic material, for example polytetrafluoroethylene (PTFE). It is put in place in its groove 11 by mechanical deformation.

Le jonc 10 forme une butée axiale pour la bague 4 lors du coulissement de celle-ci.The ring 10 forms an axial stop for the ring 4 during sliding thereof.

Comme on le voit plus particulièrement aux figures 4a et 4b, la bague 4 comporte au niveau de chaque extrémité un lamage 12. Les lamages ont un diamètre légèrement supérieur à celui du jonc 10. Ainsi lors du coulissement de la bague 4, un des lamages 12 vient coiffer le jonc 10 (comme représenté figure 4b).As we see more particularly in Figures 4a and 4b , the ring 4 comprises at each end a countersink 12. The counterbores have a diameter slightly greater than that of the ring 10. Thus, during the sliding of the ring 4, one of the counterbores 12 caps the ring 10 (as shown figure 4b ).

Une telle disposition permet d'assurer dans tous les cas le maintien du jonc 10 dans sa gorge 11. En effet dans ce mode de réalisation la profondeur de la gorge 11 est réduite, les dilatations à chaud ou la vitesse de rotation du projectile risqueraient alors d'éjecter le jonc hors de sa gorge.Such an arrangement ensures in all cases the maintenance of the ring 10 in its groove 11. Indeed in this embodiment the depth of the groove 11 is reduced, the hot expansion or the speed of rotation of the projectile would then to eject the rush out of his throat.

Le montage de la fusée s'opère de la façon suivante :

  • On place tout d'abord les clavettes 6 dans leurs logements 7. Les clavettes 6 sont maintenues solidaires de la fusĂ©e 1, par exemple par un ajustement lĂ©gèrement serrĂ©, ou par un point de colle.
  • On positionne ensuite la bague 4 en la faisant glisser sur la portĂ©e 3 portant les clavettes 6.
  • On fixe enfin le jonc 10 qui forme une butĂ©e arrĂŞtant la bague 4.
The assembly of the rocket is carried out as follows:
  • The keys 6 are firstly placed in their housings 7. The keys 6 are held integral with the rocket 1, for example by a slightly tight fit, or by a point of glue.
  • The ring 4 is then positioned by sliding it on the bearing surface 3 carrying the keys 6.
  • Finally, the ring 10 is fixed which forms a stop blocking the ring 4.

Une fois assemblée, la bague peut ainsi coulisser car il y a un jeu axial E (figure 4a) entre la bague 4 et son logement sur la portée 3, logement qui a une longueur totale P entre le jonc 12 et un épaulement 13 de la fusée 1.Once assembled, the ring can slide because there is an axial clearance E ( figure 4a ) between the ring 4 and its housing on the seat 3, housing which has a total length P between the rod 12 and a shoulder 13 of the rocket 1.

La fusée selon l'invention se monte de façon classique par vissage au niveau du taraudage 5 d'une enveloppe 2a de munition.The rocket according to the invention is mounted conventionally by screwing at the tapping 5 of a shell 2a of ammunition.

Cependant, conformément à l'invention, le filetage de la fusée n'est plus un filetage fixe par rapport au corps de fusée mais un filetage porté par une bague coulissante 4. Les clavettes 6 empêchent la rotation de la bague ce qui permet une première étape de vissage jusqu'à mise en butée de l'épaulement 13 de la fusée contre l'extrémité de l'enveloppe 2a (voir figure 4a).However, according to the invention, the thread of the rocket is no longer a fixed thread relative to the rocket body but a thread carried by a sliding ring 4. The keys 6 prevent rotation of the ring which allows a first screwing step until abutment of the shoulder 13 of the rocket against the end of the casing 2a (see figure 4a ).

Une fois la fusée mise en butée, la bague 4 présente un jeu axial E par rapport à la fusée, il n'y a pas blocage de la fusée, le vissage peut donc se poursuivre (deuxième étape de vissage) et il aura pour effet de faire coulisser la bague 4 (flèche V sur la figure 4b) par rapport à la fusée 1 jusqu'à sa mise en butée contre le jonc 10 (position représentée aux figures 1 et 4b).Once the rocket abuts, the ring 4 has an axial clearance E relative to the rocket, there is no blockage of the rocket, the screwing can continue (second screwing step) and it will have the effect to slide the ring 4 (arrow V on the figure 4b ) relative to the rocket 1 until it abuts against the rod 10 (position shown in FIGS. figures 1 and 4b ).

Une fois la bague 4 en butée contre le jonc 10, le vissage n'est plus possible et la fusée 1 est immobilisée par rapport à l'enveloppe 2a. Pour assurer un blocage du filetage de la fusée ainsi vissée et empêcher son dévissage comme suite aux vibrations mécaniques, on pourra prévoir une solution classique comme une goutte de colle déposée avant vissage et qui sèchera, bloquant ainsi le vissage, ou encore un arrêt de filet mécanique comme une vis radiale engagée au travers de l'enveloppe 2a et s'arrêtant au niveau du filetage 4a.Once the ring 4 abuts against the ring 10, the screwing is no longer possible and the rocket 1 is immobilized relative to the envelope 2a. To ensure a locking of the thread of the rocket thus screwed and prevent its unscrewing as a result of mechanical vibrations, there may be provided a conventional solution such as a drop of glue deposited before screwing and which will dry, thus blocking the screwing, or a net stop mechanical as a radial screw engaged through the casing 2a and stopping at the thread 4a.

Lors d'une élévation de température de la munition, la pression de gaz (flèche HP) qui se développe dans la cavité interne 2b va s'exercer sur la partie arrière 1b de la fusée. Le jonc 10 va se trouver cisaillé et la fusée 1 sera éjectée, assurant ainsi un déconfinement de la munition.During a rise in temperature of the ammunition, the gas pressure (arrow HP) that develops in the internal cavity 2b will be exerted on the rear part 1b of the rocket. The ring 10 will be sheared and the rocket 1 will be ejected, thus ensuring deconfinement of the munition.

On voit ainsi tous les avantages apportés par l'invention. La bague 4 est réalisée en un matériau résistant, par exemple en acier. La liaison fusée projectile se fait par l'intermédiaire de la bague 4 et des clavettes 6 également en acier. La résistance mécanique de cette liaison est excellente et l'encombrement radial de la bague est réduit (épaisseur de bague inférieure à 5 mm).This shows all the advantages provided by the invention. The ring 4 is made of a resistant material, for example steel. The projectile rocket link is via the ring 4 and the keys 6 also made of steel. The mechanical strength of this connection is excellent and the radial size of the ring is reduced (ring thickness less than 5 mm).

Le déconfinement ne dépend que des caractéristiques de résistance au cisaillement du jonc 10 qui est dimensionné en conséquence et qui est réalisé en un matériau choisi pour pouvoir être cisaillé à un niveau de contraintes donné. Par ailleurs le matériau de la bague pourra se trouver ramolli par l'échauffement ce qui facilitera le déconfinement.The deconfining depends only on the shear strength characteristics of the rod 10 which is dimensioned accordingly and which is made of a material chosen to be sheared at a given stress level. Furthermore the material of the ring may be softened by heating which will facilitate deconfinement.

Claims (5)

  1. A priming fuze (1) to be made integral with a housing (2a) of an ammunition enclosing an explosive load, the fuze being characterized in that it comprises an outer smooth cylindrical journal (3) on which is slidably positioned a ring (4) carrying a thread (4a) on its outer surface, the thread being intended to cooperate with a female thread (5) of the ammunition housing (2a), the ring (4) being made integral in rotation with the body of the fuze (1) by at least one longitudinal key (6), the fuze further carrying a shearable lock ring (10) forming an axial stop for the ring (4) during sliding thereof after mounting the fuze on the housing (2a).
  2. The priming fuze according to claim 1, wherein the lock ring (10) has a ring shape and is received in a groove (11) of the fuze.
  3. The priming fuze according to claim 2, wherein the ring (4) comprises a counterbore (12) covering the lock ring (10) during screwing.
  4. The priming fuze according to one of claims 1 to 3, wherein the ring (4) is made of steel.
  5. The priming fuze according to one of claims 1 to 4, wherein the lock ring (10) is made of a synthetic material.
EP13180938.6A 2012-08-29 2013-08-19 Device for the deconfinement of an ammunition casing Active EP2703769B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL13180938T PL2703769T3 (en) 2012-08-29 2013-08-19 Device for the deconfinement of an ammunition casing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1202326A FR2995075B1 (en) 2012-08-29 2012-08-29 STARTING SHELF FOR DECONFINING A MUNITION ENVELOPE

Publications (2)

Publication Number Publication Date
EP2703769A1 EP2703769A1 (en) 2014-03-05
EP2703769B1 true EP2703769B1 (en) 2015-12-23

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EP13180938.6A Active EP2703769B1 (en) 2012-08-29 2013-08-19 Device for the deconfinement of an ammunition casing

Country Status (4)

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EP (1) EP2703769B1 (en)
ES (1) ES2562202T3 (en)
FR (1) FR2995075B1 (en)
PL (1) PL2703769T3 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3090086B1 (en) 2018-12-13 2020-12-11 Thales Sa DEVICE FOR DECONFINING AN EXPLOSIVE LOAD AND AMMUNITION EQUIPPED WITH SUCH A DEVICE
US11193743B1 (en) * 2020-06-04 2021-12-07 The United States Of America, As Represented By The Secretary Of The Navy Cook-off mitigation system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2742221B1 (en) * 1995-12-12 1998-02-27 Soc D Ateliers Mecaniques De P DECONFINING DEVICE FOR AMMUNITION
US7025000B1 (en) 2002-04-11 2006-04-11 The United States Of America As Represented By The Secretary Of The Army Mechanism for reducing the vulnerability of high explosive loaded munitions to unplanned thermal stimuli
FR2906606B1 (en) * 2006-09-29 2010-12-31 Giat Ind Sa DEVICE FOR DECONFINING AN ENVELOPE OF A MUNITION.
FI122080B (en) * 2010-02-19 2011-08-15 Patria Land & Armament Oy Lifting device for projectiles

Also Published As

Publication number Publication date
FR2995075B1 (en) 2014-08-29
PL2703769T3 (en) 2016-07-29
ES2562202T3 (en) 2016-03-03
EP2703769A1 (en) 2014-03-05
FR2995075A1 (en) 2014-03-07

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