EP2923171B1 - Spin-stabilised projectile that expels a payload - Google Patents

Spin-stabilised projectile that expels a payload Download PDF

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Publication number
EP2923171B1
EP2923171B1 EP13820785.7A EP13820785A EP2923171B1 EP 2923171 B1 EP2923171 B1 EP 2923171B1 EP 13820785 A EP13820785 A EP 13820785A EP 2923171 B1 EP2923171 B1 EP 2923171B1
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EP
European Patent Office
Prior art keywords
piston
payload
projectile
projectiles
sub
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EP13820785.7A
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German (de)
French (fr)
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EP2923171A1 (en
Inventor
Nicolas Caillaut
Cédric MARTINON
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Nexter Munitions SA
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Nexter Munitions SA
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Publication of EP2923171A1 publication Critical patent/EP2923171A1/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile
    • F42B12/64—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile the submissiles being of shot- or flechette-type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/36—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information
    • F42B12/56—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect for dispensing materials; for producing chemical or physical reaction; for signalling ; for transmitting information for dispensing discrete solid bodies
    • F42B12/58—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles
    • F42B12/62—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected parallel to the longitudinal axis of the projectile

Definitions

  • the technical field of the invention is that of the gyrostabilized projectiles comprising a body containing a payload formed of a set of sub-projectiles dispersible trajectory by a pyrotechnic charge.
  • projectiles are usually medium caliber projectiles (caliber between 20mm and 70mm) and are used as part of the anti-aircraft defense.
  • Sub-projectiles are usually metal spheres or cylinders, such as steel or tungsten.
  • the dispersion of the sub-projectiles in front of a target makes it possible to destroy the latter.
  • the bullet of the projectile Prior to the expulsion, the bullet of the projectile is cracked and opens in petals following the action of another pyrotechnic device.
  • the sub-projectiles are housed in several one-piece buckets stacked on top of each other from the rear of the shell body into the warhead.
  • a rear piston is attached to the shell body and pushes the godets out of the body once the warhead and its contents ejected.
  • the body casing is sheared radially at the bulkhead and the body opens at the rear along longitudinal breakouts.
  • the object of the invention is to provide a projectile architecture of simple design and yet reliably ensuring axial and forward ejection of the sub-projectiles. Thanks to the invention this ejection is carried out with a speed which is increased relative to the residual velocity of the projectile. About 40m / s are also provided on a speed of the order of 500 to 800 m / s, an increase of 5% to 8% in the speed of the sub-projectiles.
  • the subject of the invention is a gyro-stabilized projectile according to claim 1.
  • the piston will have an external profile corresponding to that of the inner housing of the body.
  • the external profile of the piston may for example be hexagonal.
  • the piston may have a thickness of between 7.5 mm and 10 mm.
  • the front thrust plate may include an internal cavity having a hexagonal profile and receiving the payload.
  • the projectile may include a bearing ring which will be integral with the body and on which the piston will be supported.
  • a projectile 1 according to one embodiment of the invention comprises a body 2 which is closed at its front by a ballistic ogive 3 and at its rear by a base 4 screwed to the body 2.
  • the body 2 has an inner housing 12 which encloses a payload 5 which is formed of a set of trajectory-dispersible sub-projectiles 6.
  • the sub-projectiles 6 are steel or tungsten cylinders which are stacked in columns.
  • the inner housing 12 of the latter has a hexagonal profile conforming to the contour of the cylindrical sub-projectiles.
  • This hexagonal profile is the most suitable for driving cylindrical columns.
  • Other shapes would of course be possible, for example cylindrical grooves regularly distributed angularly and each corresponding to a sub-projectile column.
  • the hexagonal profile of the housing 12 has rounded grooves 12a at the vertices of the hexagon. These grooves 12a extend over the entire length of the body 2 and have a radius of curvature equal to that of the cylindrical sub-projectiles 6.
  • the housing 12 has a groove 12b at each middle of the sides of the hexagon. These grooves 12b extend over the entire length of the body 2 and each open onto a cylindrical profile 12c receiving a sub-projectile column 6.
  • each side of the hexagonal profile of the housing 12 comprises three sub-projectiles 6.
  • the column of the sub-projectiles 6 located in the middle of each side is thus maintained by a groove 12b.
  • the base 4 encloses a rocket 7 which comprises in a conventional manner a safety and arming device and a detonator 8, the initiation of which is controlled by a programmable electronic module 9.
  • This relay 10 is a detonating pyrotechnic charge which is initiated by the shock wave coming from the detonator 8 and which reacts in detonation.
  • detonation is meant a self-sustaining exothermic chemical reaction in which a shock wave precedes the reaction front and travels at a speed greater than the sonic velocity of the composition.
  • a detonation velocity is of the order of several thousand meters per second.
  • Detonation relays are typically used to detonate an explosive charge, such as a shell.
  • a relay 10 formed of compressed hexogen can be used.
  • a gas generating composition is initiated in combustion, that is to say with a reaction rate of a few meters per second. It is the same for a propellant powder whose reaction rate is of the order of a few tens of meters per second.
  • the detonation relay 10 is separated from the payload 5 by a piston 11 which is slidably mounted in the body 5.
  • the piston will have a hexagonal outer profile to follow the hexagonal profile of the housing 12 of the body 2 and be rotated with the projectile which avoids the problems of gyroscopic instability.
  • the housing 12 has another shape of profile, for example cylindrical grooves evenly spaced angularly, the piston 11 will have a profile corresponding to that of the housing 12 to be able to slide in the latter and be integral in rotation with the body 2.
  • the payload 5 is disposed between the piston 11 and a front thrust plate 14 which is itself bearing against a shoulder 13 of the ogive 3.
  • the thrust plate 14 has a bucket shape and therefore has a cavity internal wall delimited by a thin wall 20.
  • the wall 20 is interposed between the ogive 3 and the payload 5.
  • This wall 20 is cylindrical and in contact with the ogive and the inner surface of this wall 20 has a hexagonal profile similar to that of the housing 12 of the body. It is through this profile that the thrust plate 14 is rotated by the payload 5. Such an arrangement ensures the stability of the projectile in flight by avoiding a rotation of the thrust plate 14 relative to the payload 5.
  • the warhead 3 is fixed to the body 2 by a thread 15. It comprises a rupture groove 17 which will shear during the operation of the detonation relay 10 and allow the front ejection of the payload 5.
  • the piston 11 has a clearance 16 which caps and surrounds the detonation relay 10. The latter is therefore not directly in contact with the piston 11. Such an arrangement makes it possible not to damage the piston 11 during the operation of the relay. detonation 10.
  • This clearance is essential for the proper operation of the frontal ejection by detonation. It has a depth of between 2 and 4mm.
  • a support ring 18 is placed between the piston 11 and the rocket 7, its function is to recover the inertial forces of the payload 5 which apply to the piston 11 during firing. This makes it possible not to damage the rocket 7.
  • This support ring 18 may be optional in the case where the recovery of the inertial forces of the payload 5 is ensured by a support of the piston 11 directly on a body of the body 2 of the projectile (scope not shown which would be arranged in place and place of the ring 18).
  • the piston 11 is then introduced into the body 2 by the front of the latter until it bears on the support ring 18, then the payload 5 is introduced into the body 2. It will be possible for this purpose, to make the sub-projectiles 6 fast with each other temporarily, for example with a plastic film surrounding the sub-projectile stacks 6.
  • the front thrust plate 14 is then positioned on the payload 5 with the interposition of one or more axial pitching sheets 19, then the warhead 3 is screwed and glued onto the body 2 of the projectile.
  • the base 4 enclosing the rocket and carrying the detonation relay 10 is finally screwed to the rear part of the body 2.
  • the detonator 8 is initiated by the electronic module 9. It causes the detonation of the relay 10.
  • the shock wave from the relay 10 will cause the projection of the piston 11 towards the front of the projectile. This shock wave propagates through the piston 11, the payload 5 and the plug 14. It is sufficient to shear the rupture groove 17 of the nose 3 and also ensures the projection of the entire payload 5 through the front opening of the warhead 3 thus sheared.
  • the piston In order to avoid any deformation or destruction of the piston 11 by impact, the piston will be given a thickness of between 7.5 mm and 10 mm.
  • the shear of the ogive 3 is obtained reliably and quickly by the sole effect of the shock wave.
  • the tests have shown that the shock also makes it possible to eject the payload axially without it being necessary to cut the body longitudinally and without the relative sealing between the piston 11 and the body 2 being necessary.

Description

Le domaine technique de l'invention est celui des projectiles gyrostabilisés comportant un corps renfermant une charge utile formée d'un ensemble de sous-projectiles dispersables sur trajectoire par une charge pyrotechnique.The technical field of the invention is that of the gyrostabilized projectiles comprising a body containing a payload formed of a set of sub-projectiles dispersible trajectory by a pyrotechnic charge.

Ces projectiles sont habituellement des projectiles de moyen calibre (calibre compris entre 20mm et 70mm) et sont utilisés dans le cadre de la défense anti aérienne.These projectiles are usually medium caliber projectiles (caliber between 20mm and 70mm) and are used as part of the anti-aircraft defense.

Les sous-projectiles sont généralement des sphères ou des cylindres en métal, tel que l'acier ou le tungstène.Sub-projectiles are usually metal spheres or cylinders, such as steel or tungsten.

La dispersion des sous-projectiles au-devant d'une cible, telle un missile ou un aéronef, permet de détruire cette dernière.The dispersion of the sub-projectiles in front of a target, such as a missile or an aircraft, makes it possible to destroy the latter.

On connaît par le brevet GB460516 un projectile particulier dont le corps renferme sept cartouches complètes comprenant chacune un étui et une balle positionnée dans un tube rayé. Les cartouches sont immobilisées par rapport au corps au niveau de leur culot arrière qui est en appui contre une plaque d'arrêt. Chaque cartouche est dotée d'une amorce qui est percutée par un percuteur poussé par un piston. Une charge pyrotechnique est initiée sur trajectoire et pousse le piston contre l'action d'un ressort, provoquant la percussion des amorces des cartouches, donc le tir des balles. Il n'y a pas ici de projection de toute la charge utile en dehors du corps du projectile mais le tir des cartouches. Les douilles des cartouches restent dans le corps a après le tir de ces dernières. Un tel système est complexe et seules les balles, donc une faible partie de la charge utile, sont éjectées.We know by the patent GB460516 a particular projectile whose body contains seven complete cartridges each comprising a case and a bullet positioned in a striped tube. The cartridges are immobilized relative to the body at their rear base which bears against a stop plate. Each cartridge has a primer that is struck by a striker pushed by a piston. A pyrotechnic charge is initiated on trajectory and pushes the piston against the action of a spring, causing the percussion of the primers of the cartridges, thus the firing of the bullets. There is no projection here of the whole payload outside the body of the projectile but the firing of the cartridges. The cartridges cartridges remain in the body after the shooting of the latter. Such a system is complex and only the balls, so a small part of the payload, are ejected.

On connaît par le brevet CH85741 un projectile destiné à la destruction de ballons ou dirigeables qui comporte différents sous projectiles pyrophoriques qui sont éjectés hors du corps du projectile après avoir été eux même initiés. L'éjection est provoquée à l'issue d'un retard par l'initiation d'une charge. Cette charge n'est pas un relais de détonation car elle est initiée par une charge de poudre à combustion lente (retard pyrotechnique) dont la sortie ne peut initier qu'une composition pyrotechnique ou une charge de poudre noire.We know by the patent CH85741 a projectile for the destruction of balloons or airships which comprises various pyrophoric sub-projectiles which are ejected out of the body of the projectile after having been themselves initiated. The ejection is caused after a delay by the initiation of a charge. This charge is not a detonation relay because it is initiated by a charge of slow combustion powder (pyrotechnic delay) whose output can initiate a pyrotechnic composition or a charge of black powder.

On connaît par le brevet US3954060 un projectile comportant un empilement de fléchettes métalliques qui sont dispersées au moyen d'une charge pyrotechnique génératrice d'une pression de gaz.We know by the patent US3954060 a projectile comprising a stack of metal darts which are dispersed by means of a pyrotechnic charge generating a gas pressure.

Préalablement à l'expulsion, l'ogive du projectile est fissurée et elle s'ouvre en pétales suite à l'action d'un autre dispositif pyrotechnique. Les sous-projectiles sont logés dans plusieurs godets monoblocs empilés les uns sur les autres depuis l'arrière du corps d'obus jusque dans l'ogive. Un piston arrière est lié au corps d'obus et pousse les godets hors du corps une fois l'ogive et son contenu éjectés. Une telle solution est particulièrement complexe et impose la réalisation de plusieurs dispositifs pyrotechniques générateurs de gaz fonctionnant en séquence.Prior to the expulsion, the bullet of the projectile is cracked and opens in petals following the action of another pyrotechnic device. The sub-projectiles are housed in several one-piece buckets stacked on top of each other from the rear of the shell body into the warhead. A rear piston is attached to the shell body and pushes the godets out of the body once the warhead and its contents ejected. Such a solution is particularly complex and requires the realization of several pyrotechnic devices generating gas operating in sequence.

On connaît aussi par le brevet EP0698774 un projectile dans lequel la dispersion des sous-projectiles est obtenue par l'initiation, non pas d'une composition génératrice de gaz, mais d'une charge explosive qui est séparée de la charge utile par une cloison.Also known by the patent EP0698774 a projectile in which the dispersion of the sub-projectiles is obtained by the initiation, not of a gas-generating composition, but of an explosive charge which is separated from the payload by a partition.

Lors de l'initiation de la charge, l'enveloppe du corps se cisaille radialement au niveau de la cloison et le corps s'ouvre par l'arrière le long d'amorces de rupture longitudinales.During the initiation of the load, the body casing is sheared radially at the bulkhead and the body opens at the rear along longitudinal breakouts.

Un tel mode d'ouverture du corps freine l'éjection axiale des sous-projectiles qui restent maintenus un certain temps, par le corps de projectile, en appui contre l'ogive. Ce mode d'éjection avec un déploiement radial a pour inconvénient de ne pas fournir aux sous-projectiles un surplus de vitesse axiale au moment du fonctionnement, ce qui réduit l'efficacité perforante des sous-projectiles.Such a mode of opening of the body slows down the axial ejection of the sub-projectiles which remain held for a certain time, by the projectile body, bearing against the warhead. This mode of ejection with a radial deployment has the disadvantage of not providing the sub-projectiles a surplus of speed axial at the time of operation, which reduces the perforating efficiency of the sub-projectiles.

L'invention a pour but de fournir une architecture de projectile de conception simple et assurant cependant de façon fiable une éjection axiale et vers l'avant des sous-projectiles. Grâce à l'invention cette éjection s'effectue avec une vitesse qui est accrue par rapport à la vitesse résiduelle du projectile. Environ 40m/s sont fournis en plus sur une vitesse de l'ordre de 500 à 800 m/s, soit un accroissement de 5% à 8% de la vitesse des sous-projectiles.The object of the invention is to provide a projectile architecture of simple design and yet reliably ensuring axial and forward ejection of the sub-projectiles. Thanks to the invention this ejection is carried out with a speed which is increased relative to the residual velocity of the projectile. About 40m / s are also provided on a speed of the order of 500 to 800 m / s, an increase of 5% to 8% in the speed of the sub-projectiles.

Ainsi l'invention a pour objet un projectile gyrostabilisé selon la revendication 1.Thus, the subject of the invention is a gyro-stabilized projectile according to claim 1.

Avantageusement, le piston aura un profil externe correspondant à celui du logement interne du corps.Advantageously, the piston will have an external profile corresponding to that of the inner housing of the body.

Le profil externe du piston pourra être par exemple hexagonal.The external profile of the piston may for example be hexagonal.

Le piston pourra avoir une épaisseur comprise entre 7.5 mm et 10 mm.The piston may have a thickness of between 7.5 mm and 10 mm.

La plaque de poussée avant pourra comporter une cavité interne ayant un profil hexagonal et recevant la charge utile.The front thrust plate may include an internal cavity having a hexagonal profile and receiving the payload.

Selon un mode de réalisation, le projectile pourra comporter une bague d'appui qui sera solidaire du corps et sur laquelle le piston sera en appui.According to one embodiment, the projectile may include a bearing ring which will be integral with the body and on which the piston will be supported.

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 en coupe longitudinale d'un mode de réalisation d'un projectile selon l'invention.
  • La figure 2 est une vue en coupe transversale de ce projectile, coupe réalisée suivant le plan AA dont la trace est visible à la figure 1.
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 longitudinal sectional view of an embodiment of a projectile according to the invention.
  • The figure 2 is a cross-sectional view of this projectile, cut according to plane AA whose trace is visible at the figure 1 .

En se reportant à la figure 1, un projectile 1 selon un mode de réalisation de l'invention comprend un corps 2 qui est fermé à sa partie avant par une ogive balistique 3 et à sa partie arrière par un culot 4 vissé au corps 2.Referring to the figure 1 , a projectile 1 according to one embodiment of the invention comprises a body 2 which is closed at its front by a ballistic ogive 3 and at its rear by a base 4 screwed to the body 2.

Le corps 2 comporte un logement interne 12 qui renferme une charge utile 5 qui est formée d'un ensemble de sous-projectiles 6 dispersables sur trajectoire. Suivant l'exemple représenté ici, les sous-projectiles 6 sont des cylindres en acier ou en tungstène qui sont empilés en colonnes.The body 2 has an inner housing 12 which encloses a payload 5 which is formed of a set of trajectory-dispersible sub-projectiles 6. According to the example shown here, the sub-projectiles 6 are steel or tungsten cylinders which are stacked in columns.

Pour assurer l'entraînement en rotation des sous-projectiles 6 par le corps 2, le logement interne 12 de ce dernier a un profil en forme d'hexagone épousant le contour des sous-projectiles cylindriques.To ensure the rotation of the sub-projectiles 6 by the body 2, the inner housing 12 of the latter has a hexagonal profile conforming to the contour of the cylindrical sub-projectiles.

Ce profil hexagonal est le plus approprié pour l'entraînement de colonnes cylindriques. D'autres formes seraient bien entendu possibles, par exemple des rainures cylindriques régulièrement réparties angulairement et correspondant chacune à une colonne de sous-projectiles.This hexagonal profile is the most suitable for driving cylindrical columns. Other shapes would of course be possible, for example cylindrical grooves regularly distributed angularly and each corresponding to a sub-projectile column.

Comme on le voit plus particulièrement sur la figure 2, le profil hexagonal du logement 12 comporte des rainures arrondies 12a au niveau des sommets de l'hexagone. Ces rainures 12a s'étendent sur toute la longueur du corps 2 et elles ont un rayon de courbure égal à celui des sous-projectiles cylindriques 6.As we see more particularly on the figure 2 , the hexagonal profile of the housing 12 has rounded grooves 12a at the vertices of the hexagon. These grooves 12a extend over the entire length of the body 2 and have a radius of curvature equal to that of the cylindrical sub-projectiles 6.

Par ailleurs le logement 12 comporte un sillon 12b au niveau de chaque milieu des côtés de l'hexagone. Ces sillons 12b s'étendent sur toute la longueur du corps 2 et débouchent chacun sur un profil cylindrique 12c recevant une colonne de sous-projectiles 6.In addition, the housing 12 has a groove 12b at each middle of the sides of the hexagon. These grooves 12b extend over the entire length of the body 2 and each open onto a cylindrical profile 12c receiving a sub-projectile column 6.

On remarque sur la figure 2 que chaque côté du profil hexagonal du logement 12 comporte trois sous-projectiles 6. La colonne des sous-projectiles 6 située au milieu de chaque côté se trouve donc maintenue par un sillon 12b.We notice on the figure 2 that each side of the hexagonal profile of the housing 12 comprises three sub-projectiles 6. The column of the sub-projectiles 6 located in the middle of each side is thus maintained by a groove 12b.

Le culot 4 renferme une fusée 7 qui comprend d'une façon classique un dispositif de sécurité et d'armement et un détonateur 8 dont l'initiation est commandée par un module électronique programmable 9.The base 4 encloses a rocket 7 which comprises in a conventional manner a safety and arming device and a detonator 8, the initiation of which is controlled by a programmable electronic module 9.

Lorsque le détonateur 8 est amené dans sa position d'armement par le dispositif de sécurité et d'armement, il est en regard d'un relais de détonation 10.When the detonator 8 is brought into its cocking position by the safety and cocking device, it is opposite a detonation relay 10.

Ce relais 10 est une charge pyrotechnique détonante qui est initiée par l'onde de choc issue du détonateur 8 et qui réagit en détonation. On entend par détonation une réaction chimique exothermique auto-entretenue dans laquelle une onde de choc précède le front de réaction et se déplace à une vitesse supérieure à la vitesse sonique de la composition. Une vitesse de détonation est de l'ordre de plusieurs milliers de mètres par seconde.This relay 10 is a detonating pyrotechnic charge which is initiated by the shock wave coming from the detonator 8 and which reacts in detonation. By detonation is meant a self-sustaining exothermic chemical reaction in which a shock wave precedes the reaction front and travels at a speed greater than the sonic velocity of the composition. A detonation velocity is of the order of several thousand meters per second.

Les relais de détonation sont utilisés généralement pour provoquer la détonation d'un chargement explosif, par exemple celui d'un obus. On pourra utiliser un relais 10 formé d'hexogène comprimé.Detonation relays are typically used to detonate an explosive charge, such as a shell. A relay 10 formed of compressed hexogen can be used.

A titre comparatif une composition génératrice de gaz est initiée en combustion, c'est à dire avec une vitesse de réaction de quelques mètres par seconde. Il en est de même pour une poudre propulsive dont la vitesse de réaction est de l'ordre de quelques dizaines de mètres par seconde.By way of comparison, a gas generating composition is initiated in combustion, that is to say with a reaction rate of a few meters per second. It is the same for a propellant powder whose reaction rate is of the order of a few tens of meters per second.

Conformément à l'invention, le relais de détonation 10 est séparé de la charge utile 5 par un piston 11 qui est monté coulissant dans le corps 5. A cet effet le piston aura un profil externe hexagonal pour suivre le profil hexagonal du logement 12 du corps 2 et être entraîné en rotation avec le projectile ce qui évite les problèmes d'instabilité gyroscopique. Si le logement 12 a une autre forme de profil, par exemple des rainures cylindriques régulièrement réparties angulairement, le piston 11 aura un profil correspondant à celui du logement 12 pour pouvoir coulisser dans ce dernier et être solidaire en rotation du corps 2.According to the invention, the detonation relay 10 is separated from the payload 5 by a piston 11 which is slidably mounted in the body 5. For this purpose the piston will have a hexagonal outer profile to follow the hexagonal profile of the housing 12 of the body 2 and be rotated with the projectile which avoids the problems of gyroscopic instability. If the housing 12 has another shape of profile, for example cylindrical grooves evenly spaced angularly, the piston 11 will have a profile corresponding to that of the housing 12 to be able to slide in the latter and be integral in rotation with the body 2.

Comme on le voit sur la figure 1, la charge utile 5 est disposée entre le piston 11 et une plaque de poussée avant 14 qui est elle-même en appui contre un épaulement 13 de l'ogive 3. La plaque de poussée 14 a une forme en godet et comporte donc une cavité interne délimitée par une paroi mince 20. La paroi 20 est interposée entre l'ogive 3 et la charge utile 5.As we see on the figure 1 , the payload 5 is disposed between the piston 11 and a front thrust plate 14 which is itself bearing against a shoulder 13 of the ogive 3. The thrust plate 14 has a bucket shape and therefore has a cavity internal wall delimited by a thin wall 20. The wall 20 is interposed between the ogive 3 and the payload 5.

La surface externe de cette paroi 20 est cylindrique et au contact de l'ogive et la surface interne de cette paroi 20 a un profil hexagonal analogue à celui du logement 12 du corps. C'est par ce profil que la plaque de poussée 14 est entraînée en rotation par la charge utile 5. Une telle disposition assure la stabilité du projectile en vol en évitant une rotation de la plaque de poussée 14 par rapport à la charge utile 5.The outer surface of this wall 20 is cylindrical and in contact with the ogive and the inner surface of this wall 20 has a hexagonal profile similar to that of the housing 12 of the body. It is through this profile that the thrust plate 14 is rotated by the payload 5. Such an arrangement ensures the stability of the projectile in flight by avoiding a rotation of the thrust plate 14 relative to the payload 5.

L'ogive 3 est fixée au corps 2 par un filetage 15. Elle comporte une gorge de rupture 17 qui viendra se cisailler lors du fonctionnement du relais de détonation 10 et permettra ansi l'éjection frontale de la charge utile 5.The warhead 3 is fixed to the body 2 by a thread 15. It comprises a rupture groove 17 which will shear during the operation of the detonation relay 10 and allow the front ejection of the payload 5.

Suivant le mode de réalisation représenté à la figure 1, le piston 11 comporte un dégagement 16 qui coiffe et entoure le relais de détonation 10. Ce dernier n'est donc pas directement en contact avec le piston 11. Une telle disposition permet de ne pas endommager le piston 11 lors du fonctionnement du relais de détonation 10.According to the embodiment shown in figure 1 , the piston 11 has a clearance 16 which caps and surrounds the detonation relay 10. The latter is therefore not directly in contact with the piston 11. Such an arrangement makes it possible not to damage the piston 11 during the operation of the relay. detonation 10.

Ce dégagement est indispensable au bon fonctionnement de l'éjection frontale par détonation. Il a une profondeur comprise entre 2 et 4mm. Une bague d'appui 18 est placée entre le piston 11 et la fusée 7, sa fonction est de récupérer les efforts d'inertie de la charge utile 5 qui s'appliquent sur le piston 11 lors du tir. Ceci permet de ne pas endommager la fusée 7.This clearance is essential for the proper operation of the frontal ejection by detonation. It has a depth of between 2 and 4mm. A support ring 18 is placed between the piston 11 and the rocket 7, its function is to recover the inertial forces of the payload 5 which apply to the piston 11 during firing. This makes it possible not to damage the rocket 7.

Cette bague d'appui 18 peut être facultative dans le cas où la reprise des efforts d'inertie de la charge utile 5 est assurée par un appui du piston 11 directement sur une portée du corps 2 du projectile (portée non représentée qui serait disposée en lieu et place de la bague 18).This support ring 18 may be optional in the case where the recovery of the inertial forces of the payload 5 is ensured by a support of the piston 11 directly on a body of the body 2 of the projectile (scope not shown which would be arranged in place and place of the ring 18).

Le montage du projectile 1 s'effectue de la façon suivante :

  • La bague d'appui 18 est vissée et collée à sa bonne position dans le corps 2.
The mounting of the projectile 1 is carried out as follows:
  • The support ring 18 is screwed and glued to its proper position in the body 2.

Le piston 11 est ensuite introduit dans le corps 2 par l'avant de ce dernier jusqu'à ce qu'il vienne en appui sur la bague d'appui 18, puis la charge utile 5 est introduite dans le corps 2. Il sera possible pour cela de rendre les sous-projectiles 6 solidaires les uns des autres de façon temporaire, par exemple avec un film en matière plastique entourant les empilements de sous-projectiles 6.The piston 11 is then introduced into the body 2 by the front of the latter until it bears on the support ring 18, then the payload 5 is introduced into the body 2. It will be possible for this purpose, to make the sub-projectiles 6 fast with each other temporarily, for example with a plastic film surrounding the sub-projectile stacks 6.

On positionne ensuite la plaque de poussée avant 14 sur la charge utile 5 avec interposition d'une ou plusieurs feuilles de calage axial 19, puis on visse et colle l'ogive 3 sur le corps 2 de projectile.The front thrust plate 14 is then positioned on the payload 5 with the interposition of one or more axial pitching sheets 19, then the warhead 3 is screwed and glued onto the body 2 of the projectile.

Le culot 4 renfermant la fusée et portant le relais de détonation 10 est enfin vissé à la partie arrière du corps 2.The base 4 enclosing the rocket and carrying the detonation relay 10 is finally screwed to the rear part of the body 2.

Le fonctionnement du projectile selon l'invention est le suivant :

  • La fusée 7 a reçu avant tir (ou sur trajectoire) une programmation de l'instant de dispersion des sous-projectiles 6. Cette programmation ne fait pas partie de l'invention et il n'est donc pas nécessaire de la décrire en détails.
The operation of the projectile according to the invention is as follows:
  • The rocket 7 received before firing (or on trajectory) a programming of the moment of dispersion of the sub-projectiles 6. This programming is not part of the invention and it is therefore not necessary to describe it in detail.

A l'instant souhaité, le détonateur 8 est initié par le module électronique 9. Il provoque la détonation du relais 10. L'onde de choc issue du relais 10 va provoquer la projection du piston 11 vers l'avant du projectile. Cette onde de choc se propage au travers du piston 11, de la charge utile 5 et du bouchon 14. Elle suffit à cisailler la gorge de rupture 17 de l'ogive 3 et assure aussi la projection de toute la charge utile 5 au travers de l'ouverture avant de l'ogive 3 ainsi cisaillée.At the desired instant, the detonator 8 is initiated by the electronic module 9. It causes the detonation of the relay 10. The shock wave from the relay 10 will cause the projection of the piston 11 towards the front of the projectile. This shock wave propagates through the piston 11, the payload 5 and the plug 14. It is sufficient to shear the rupture groove 17 of the nose 3 and also ensures the projection of the entire payload 5 through the front opening of the warhead 3 thus sheared.

Afin d'éviter toute déformation ou destruction du piston 11 par le choc, on donnera au piston une épaisseur comprise entre 7.5 mm et 10 mm.In order to avoid any deformation or destruction of the piston 11 by impact, the piston will be given a thickness of between 7.5 mm and 10 mm.

Du fait de l'utilisation d'un relais de détonation 10, le cisaillement de l'ogive 3 est obtenu de façon fiable et rapide par le seul effet de l'onde de choc. Les essais ont montré que le choc permettait aussi d'éjecter la charge utile 5 axialement sans qu'il soit nécessaire de découper longitudinalement le corps et sans que l'étanchéité relative entre le piston 11 et le corps 2 ne soit nécessaire.Due to the use of a detonation relay 10, the shear of the ogive 3 is obtained reliably and quickly by the sole effect of the shock wave. The tests have shown that the shock also makes it possible to eject the payload axially without it being necessary to cut the body longitudinally and without the relative sealing between the piston 11 and the body 2 being necessary.

La solution est ainsi plus simple que celle décrite par le brevet EP698774 . Elle est également plus simple que celle décrite par le brevet US3954060 qui met en oeuvre une composition génératrice de gaz. En effet avec l'invention il est inutile de prévoir des moyens d'étanchéité entre le piston 11 et le corps 2, moyens qui seraient indispensables avec une composition génératrice de gaz. Par ailleurs la chaîne pyrotechnique utilisée par l'invention est une chaîne détonante classique telle que mise en oeuvre dans un projectile explosif. Le développement du projectile selon l'invention se trouve donc simplifié.The solution is thus simpler than that described by the patent EP698774 . It is also simpler than that described by the patent US3954060 which uses a gas generating composition. Indeed with the invention it is unnecessary to provide sealing means between the piston 11 and the body 2, which would be indispensable means with a gas generating composition. Moreover, Pyrotechnic chain used by the invention is a conventional detonating chain as implemented in an explosive projectile. The development of the projectile according to the invention is thus simplified.

Claims (6)

  1. - A spin-stabilised projectile (1) comprising a body (2) enclosing a payload (5) formed by a group of sub-projectiles (6) which can be dispersed over a trajectory under the action of a pyrotechnic charge (10) integral with a rear part of the body, the body carrying at its front part a ballistic warhead (3) provided with a breaking groove (17), the payload being entirely ejected from the body by projecting toward the front of the projectile a piston (11) slidably mounted in the body (2), the payload (5) being arranged between the piston (11) and a front thrust plate (14) which bears against the warhead (3), the pyrotechnic charge (10) being composed of a detonation relay (10) intended to detonate and to produce a shock wave that will spread through the piston (11), the payload (5) and the front thrust plate (14), said relay being separated from the payload (5) by the piston (11), the piston comprising a recess (16) covering and surrounding the detonation relay (10), the latter being not directly in contact with the piston (11).
  2. - The projectile according to claim 1, characterised in that the piston (11) has an external profile corresponding to that of the inner housing (12) of the body.
  3. - The projectile according to claim 2, characterised in that the external profile of the piston (11) is hexagonal.
  4. - The projectile according to one of claims 1 to 3, characterised in that the piston (11) has a thickness between 7.5 mm and 10 mm.
  5. - The projectile according to claim 1, characterised in that the front thrust plate (14) is provided with an inner recess having a hexagonal profile and receiving the payload (5).
  6. - The projectile according to one of claims 1 to 5, characterised in that it comprises a support ring (18) which is integral with the body (2) and on which the piston (11) bears.
EP13820785.7A 2012-11-23 2013-11-22 Spin-stabilised projectile that expels a payload Active EP2923171B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1203211A FR2998659B1 (en) 2012-11-23 2012-11-23 GYROSTABILIZED PROJECTILE PROJECTING A PAYLOAD
PCT/FR2013/052823 WO2014080136A1 (en) 2012-11-23 2013-11-22 Spin-stabilised projectile that expels a payload

Publications (2)

Publication Number Publication Date
EP2923171A1 EP2923171A1 (en) 2015-09-30
EP2923171B1 true EP2923171B1 (en) 2018-01-03

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US (1) US9423226B2 (en)
EP (1) EP2923171B1 (en)
ES (1) ES2658992T3 (en)
FR (1) FR2998659B1 (en)
NO (1) NO2923171T3 (en)
PT (1) PT2923171T (en)
WO (1) WO2014080136A1 (en)

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Publication number Priority date Publication date Assignee Title
US9354027B2 (en) 2013-10-24 2016-05-31 G2 Research Inc. Fragmenting projectile
KR101891016B1 (en) 2014-02-11 2018-08-22 레이던 컴퍼니 Munition with outer airframe
US10663271B2 (en) 2016-10-13 2020-05-26 G2 Research Inc. Predictably fragmenting projectiles having internally-arranged geometric features
SE545173C2 (en) * 2017-11-28 2023-05-02 Bae Systems Bofors Ab Spin stabilized projectile and method for providing a horizontal dispersion pattern
DE102018104333A1 (en) * 2018-02-26 2019-08-29 Rwm Schweiz Ag Projectile with pyrotechnic active charge
US11561075B2 (en) * 2018-12-13 2023-01-24 The United States Of America, As Represented By The Secretary Of The Navy Projectile with pyrotechnically timed release of a secondary payload
FR3100610B1 (en) * 2019-09-06 2023-11-03 Cta Int Anti-aircraft shell for telescoped ammunition with double unlocking
US11761739B2 (en) * 2020-09-20 2023-09-19 Nl Enterprises, Llc Projectile construction, launcher, and launcher accessory
US20230324154A1 (en) * 2021-12-08 2023-10-12 Nl Enterprises, Llc Projectile Construction, Launcher, and Launcher Accessory

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Publication number Priority date Publication date Assignee Title
CH85741A (en) * 1919-10-06 1920-07-01 Maschinenbauansta Hanseatische Bullet.
GB460516A (en) * 1935-06-27 1937-01-27 Giuseppe Pietro Ottino Improvements in shrapnel shells
US3802345A (en) * 1962-05-02 1974-04-09 Aai Corp Multiple projectile sabot assembly for use in rifled barrel
US3954060A (en) 1967-08-24 1976-05-04 The United States Of America As Represented By The Secretary Of The Army Projectile
DE2359758C1 (en) * 1973-11-30 1988-07-28 Buck Chemisch-Technische Werke Gmbh & Co, 7347 Bad Ueberkingen, De
US4444117A (en) * 1981-03-30 1984-04-24 The Boeing Company Stacked tube submunition dispenser
CH688727A5 (en) 1994-08-26 1998-01-30 Contraves Pyrotec Ag Spin-stabilized projectile with a payload.
ES2264958T3 (en) * 2001-11-28 2007-02-01 Rheinmetall Waffe Munition Gmbh PROJECTILES WITH HIGH EFFECT OF PENETRATION AND SIDE WITH INTEGRATED DISGREGATION DEVICE.
US7210410B1 (en) * 2006-03-29 2007-05-01 Widener Charles D Multi-projectile less lethal and breaching ammunition
FR2980843B1 (en) * 2011-10-03 2014-06-13 Nexter Munitions GYROSTABILIZED PROJECTILE

Also Published As

Publication number Publication date
FR2998659A1 (en) 2014-05-30
US20150308803A1 (en) 2015-10-29
NO2923171T3 (en) 2018-06-02
EP2923171A1 (en) 2015-09-30
WO2014080136A1 (en) 2014-05-30
US9423226B2 (en) 2016-08-23
PT2923171T (en) 2018-01-17
FR2998659B1 (en) 2017-06-23
ES2658992T3 (en) 2018-03-13

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