EP0169956A1 - Cluster ammunition - Google Patents

Cluster ammunition Download PDF

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Publication number
EP0169956A1
EP0169956A1 EP84402635A EP84402635A EP0169956A1 EP 0169956 A1 EP0169956 A1 EP 0169956A1 EP 84402635 A EP84402635 A EP 84402635A EP 84402635 A EP84402635 A EP 84402635A EP 0169956 A1 EP0169956 A1 EP 0169956A1
Authority
EP
European Patent Office
Prior art keywords
projectiles
military charge
gas
military
piston
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
EP84402635A
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German (de)
French (fr)
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EP0169956B1 (en
Inventor
Pierre Henri Hall
Jean-Pierre Rouget
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Thomson Brandt Armements SA
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Thomson Brandt Armements SA
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Publication of EP0169956A1 publication Critical patent/EP0169956A1/en
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Publication of EP0169956B1 publication Critical patent/EP0169956B1/en
Expired legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B3/00—Blasting cartridges, i.e. case and explosive
    • F42B3/006—Explosive bolts; Explosive actuators
    • 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
    • F42B12/60—Cluster or cargo ammunition, i.e. projectiles containing one or more submissiles the submissiles being ejected radially

Definitions

  • the present invention relates to the field of bombs, missiles and similar vectors, and it relates to a military charge with multiple heads intended for such vectors.
  • the invention proposes to carry out a military charge with multiple heads whose destructive power is at least equal to that of a salvo of projectiles fired by an aircraft, and to mount this multi-headed military charge in a vector carried by an aircraft so that this aircraft remains outside the range of the enemy's defensive weapons.
  • the object of the invention is a military charge with multiple heads intended to be carried by a bomb, a missile or a similar vector, in this charge groups of submunitions, such as projectiles, are arranged in crown to be radially extracted on the terminal trajectory of the carrier vector;
  • this military charge includes a streamlined supporting structure having a retractable outer casing and a central tube which carries an annular support for each of the projectile groups; this annular support comprises arranged radially and facing the projectiles of the triggerable gas ejectors and means of clamping with bolts, which bolts are erased under the effect of the displacement of the gas ejectors.
  • the figure la in a simplified form, shows a missile intended to be carried and launched by an aircraft which remains outside the perimeter of defense of the enemy; this missile is equipped with a multi-head military charge.
  • the missile 1 comprises three main sections: a front section 2 of ogival shape, in which are gathered the guide means allowing the missile to direct itself on the sensitive point of the designated objective; a middle section 3 constituted by the military charge with heads multiple and a tail fin section 4 which possibly contains the accelerator of the missile fired after its launch by the carrier aircraft.
  • the military charge 3 essentially comprises a supporting structure, closed by an envelope, in which are arranged means making it possible to radially eject groups G and G 2 of projectiles P arranged in a ring.
  • the structure carrying the military load comprises a central tube 3 secured to two connecting flanges 6 and 7 with the envelope.
  • the connection of the flanges with the envelope is temporary, and the envelope includes means of fragmentation or sliding, with the aim of completely discovering the projectiles a short instant before their ejection from the military charge.
  • the envelope 8 is equipped with a rigid beam 9 provided with attachment rings 9a and 9b to the aircraft, not shown.
  • the central tube 3 of the supporting structure carries annular supports 10 and 10 'on which the projectiles are fixed.
  • ejectors the function of which is to radially eject each of the projectiles P, which projectiles are clamped on their support by unlocking clamping means in synchronism with the movement of the ejectors.
  • missile 1 When approaching the designated objective, missile 1 is dropped by the carrier aircraft, then guided towards the sensitive point. In the vicinity of this sensitive point the envelope 8 of the military charge is ousted, then, jointly, the means for clamping the projectiles P are unlocked and then, the ejectors are actuated to impart to the projectiles a determined lateral ejection speed, which conditions the dispersal of projectiles on the ground.
  • the ejection speed is between a few meters and a few tens of meters per second. It may be noted that it is possible by dimensioning the ejectors to provide different ejection speeds for the different groups of projectiles.
  • Figure 1b is a cross section along A of the military charge.
  • the projectiles P resting on the annular support 10 are clamped by elastic flanges 14 provided with clamping means 15 deverroulllables at the instant of the extraction of the projectiles by the gas ejectors 13.
  • FIG. 2 is a partial view, in cross section, of a form of construction of a multi-head military charge according to the invention, which shows the elements associated with the annular support 10.
  • the outer casing 8 is equipped with 'a rigid powder 9 provided with attachment rings, such as the ring 9a.
  • This envelope includes pyrotechnic means 11 intended to cause the fragmentation of the envelope before the ejection of the projectiles P.
  • the number of fragmentation generators is not limited to three, as in the embodiment considered here, but can be bigger.
  • Similar pyrotechnic means (not shown) make it possible to release the fragments of the envelope from the flanges of the support structure. Since the techniques for retracting the fairing elements of missiles and rockets are widely known, these will not be described.
  • the annular support 8 at its periphery, comprises seats 12 on which rest, also spaced, the bodies of the projectiles.
  • gas ejectors 13 are incorporated which are arranged radially and facing each of the projectiles.
  • the projectiles are held rigidly on their seats by an elastic flange 14 whose ends come into pressure on the body of the adjacent projectiles Pi and Pi + 1.
  • the middle part of these retaining flanges is provided with a clamping rod 15 which comprises a conical base 16, which is engaged in a housing 17 located in the annular support 10 and in the plane of the pneumatic ejectors 13.
  • the head of the clamping rod 15 is provided with a thread which receives a clamping nut 18.
  • the gas ejector 13 comprises a stepped bore 19 inside which is placed a piston 20.
  • This piston comprises a pusher head 21 which is resting on the shoulder of the bore; this pusher head provides a means of locking the rod tightening 13 of the elastic flange 14.
  • the base of the piston is equipped with a sealing means, such as an O-ring 22, which prevents the passage of gases supplied by a pellet 23 of a pyrotechnic substance which can be primed preferably electrically.
  • the base of the bores 19 communicates with a gas source situated in the axis of the annular support.
  • the base 16 of the clamping rod 15 and the pusher head 20 of the gas ejector communicate by a housing, inside which is placed the locking piece 24, which can freely slide and disappear from the housing 17 of the clamping rod during the translational movement of the piston, as soon as the pusher head 21 leaves the shoulder of the stepped bore 19. It may be noted that a shearable pin 25 under the effect of the displacement of the piston is disposed in the piston head to ensure that it remains on the shoulder of the bore.
  • the ignition of the pyrotechnic pellet 23 produces a flow of gas which pushes the piston 20 outward. the ejector.
  • the head of the piston 21 gradually disengages and releases the locking piece 24.
  • This locking piece under the effect of the elastic stress of the flange 14, transmitted by the clamping rod 15 moves towards the body of the piston and releases totally the housing 17 of the base 16 of the clamping rod of its housing 17.
  • the head of the piston 21 continues its movement and comes into contact with the body of the projectile on which it exerts a pressure force which ensures the ejection of the projectile .
  • the speed of ejection of the projectile can be controlled.
  • FIG. 3 shows a sectional view of a construction variant of the gas ejectors.
  • the purpose of this construction variant is to prevent the piston head 21 from striking the body of the projectile, and it makes it possible to eliminate the shear pin 25 described above.
  • Inside the piston is formed a bore 26 which receives a push rod 27.
  • the upper end of the push rod is held in contact with the body by an elastic means 28 arranged between the lower end of this push rod and the bottom of the bore 26.
  • This elastic means 28 can be constituted by a helical spring, a stack of washers "Belleville” or any other equivalent means.
  • the function of the spring 28 is also to delay the pushing force on the projectile as long as the locking piece 24 of the clamping rod 15 is not retracted.
  • the lower ends of the bores 19 of the gas ejectors are in communication with a central cavity 29 in which is disposed a gas generator which will be described later.
  • FIG 4 is a partial view, in longitudinal section, of the military charge which shows the details of embodiment of the annular support of an odd grouping of P projectiles.
  • the annular support 10 is a solid element which fits on the central tube 5 of the supporting structure.
  • the two series of protuberances are sufficiently distant from each other to ensure proper seating of the projectiles.
  • the protrusions 30 and 31 preferably provide point contacts with the body of the projectiles, and these contact points are advantageously located in diametrical planes which contain the elastic forces exerted by the flanges 14 described above.
  • the central part of the annular support carries a bootable gas generator 29.
  • the gas generator comprises a tube 32 in which is placed a pyrotechnic substance and an electrical primer 33 provided with its electrical terminals 34.
  • a chamber 35 located concentrically with the tube 32 of the gas generator, has communication orifices 36 with the gas ejectors.
  • the housing 17 of one of the clamping rods of the projectile holding flanges In order to position the projectiles longitudinally, they are provided a longitudinal positioning element such as the stud 37. This stud engages freely in a recess 38 so as not to disturb the ejection of the corresponding projectile.
  • the stud 37 located in the body of the projectiles can be a retractable element intended to neutralize the arming of the projectiles.
  • the point of application of the thrust force supplied by the thrust head 27 of the gas ejectors is located precisely with respect to the center of gravity CG of the projectiles.
  • FIG. 3 represents an external view of the annular support 10 of the projectiles and it shows the following elements: the two series of protrusions 30 and 31 which provide foundations for the bodies of the projectiles; the outlets of the stepped bore of the gas ejectors, and the indentations 38 which receive the longitudinal positioning elements of the projectiles.
  • FIG. 6 in a sectional view shows a variant construction of the gas ejector and means for locking the clamping rod of the electric flange for holding the projectiles on the annular support.
  • the gas ejector 13 is of the telescopic type comprising an external hollow piston 20a placed in the stepped bore 19a, and an internal piston 27a.
  • the external piston 20a has at its base a boss 20b whose function is to provide a first bearing on the wall of the stepped bore 19a; the second bearing is provided by a ring 20c bearing on a complementary shoulder 19b of the stepped bore; this ring 20c being held in place by a cerclip 19c.
  • the base of the external piston 20a has a support piece 20d for a spring 28a which is also supported on the base of the internal piston 27a.
  • the upper part of the external piston has a piston head 21a which ensures the locking piece 24a for locking the base 16a of the clamping rod 15 of the elastic flange 14.
  • the base 16a of the clamping rod 15 is cylindrical shape to ensure its perfect guidance in the housing 17 and it includes a milling 16b in which can engage the locking piece 24a.
  • the form of construction which has just been described makes it possible to impart a high lateral ejection speed. projectiles when necessary, and together, it provides improved guidance of the clamping rod of the elastic flange holding the projectiles.
  • the construction form of the streamlined supporting structure can be varied, and, in particular, the means making it possible to retract the envelope can be of an extraction type along the longitudinal axis of the missile.
  • the spacings of the projectiles are minimized to confer maximum carrying capacity on the load; the means for fixing and ejecting the projectiles operate in perfect synchronism and cooperate judiciously to ensure uniform and controlled dispersion of the projectiles, and the simplicity of the mechanisms confers certain reliability on the military charge.
  • the invention is not limited in its applications to a military charge formed of projectiles, but it can be applied to the launches of explosive mines of various munitions etc ... which must be deposited on the ground.

Abstract

Charge militaire à têtes multiples pour bombes, missiles et vecteurs similaires dans laquelle les groupements de sous-munitions sont rangés en couronne pour être extrait radialement. Cette charge militaire comprend: une structure porteuse carénée par une enveloppe escamotable 8, cette structure porteuse comportant un support annulaire 10 sur lequel reposent des projectiles P maintenus en place par des moyens de bridage (14-18) à verrou (24), des éjecteurs à gaz (19-23) sont disposés radialement et en regard des projectiles et coopèrent avec les moyens de bridage pour libérer et extraire les projectiles.Multi-headed military charge for bombs, missiles and similar vectors in which cluster munitions are arranged in a crown to be extracted radially. This military charge comprises: a support structure faired by a retractable envelope 8, this support structure comprising an annular support 10 on which P projectiles rest held in place by latch clamping means (14-18), ejectors gas (19-23) are arranged radially and facing the projectiles and cooperate with the clamping means to release and extract the projectiles.

La charge militaire trouve son application pour le dépôt sur le terrain de projectiles, de mines explosives et de munitions similaires.

Figure imgaf001
The military charge finds its application for the deposition on the ground of projectiles, explosive mines and similar munitions.
Figure imgaf001

Description

La présente Invention se rapporte au domaine des bombes, des missiles et des vecteurs similaires, et elle concerne une charge militaire à têtes multiples destinée à de tels vecteurs.The present invention relates to the field of bombs, missiles and similar vectors, and it relates to a military charge with multiple heads intended for such vectors.

Actuellement, la méthode mise en oeuvre pour neutraliser les Installations vitales de l'ennemi, par exemple, les pistes d'envol des aérodromes, consiste à lancer contre l'objectif visé des salves de projectiles installés en grappes sur la structure d'un aéronef. Le principal inconvénient de cette méthode d'attaque réside dans le fait que l'aéronef porteur doit obligatoirement survoler l'objectif dont l'approche est particulièrement défendue.Currently, the method used to neutralize the enemy's Vital Installations, for example, the runways of aerodromes, consists in launching salvos of projectiles installed in clusters on the structure of an aircraft against the intended objective. . The main drawback of this attack method lies in the fact that the carrier aircraft must necessarily fly over the objective whose approach is particularly defended.

Dans le but d'éviter le survol de l'objectif par l'aéronef, l'invention propose de réaliser une charge militaire à têtes multiples dont la puissance destructive soit au moins égale à celle d'une salve de projectiles tirée par un aéronef, et de monter cette charge militaire à têtes multiples dans un vecteur emporté par un aéronef afin que cet aéronef reste en dehors de la portée des armes défensives de l'ennemi.With the aim of avoiding the overflight of the objective by the aircraft, the invention proposes to carry out a military charge with multiple heads whose destructive power is at least equal to that of a salvo of projectiles fired by an aircraft, and to mount this multi-headed military charge in a vector carried by an aircraft so that this aircraft remains outside the range of the enemy's defensive weapons.

Il se pose alors le problème de réaliser une charge militaire à têtes multiples dont les sous-munitions, ou projectiles, puissent être dispersées uniformément sur la partie sensible de l'objectif afin d'obtenir des effets destructeurs maximals. Le coût d'une mission de bombardement étant Important, il est nécessaire que la fiabilité de la charge militaire soit élevée. De plus la charge militaire étant un matériel consommable, la précision de dispersion et la fiabilité ne doivent pas être obtenues par un accroissement notable du coùt de production de cette charge.The problem then arises of carrying out a military charge with multiple heads whose submunitions, or projectiles, can be dispersed uniformly over the sensitive part of the objective in order to obtain maximum destructive effects. The cost of a bombing mission being important, it is necessary that the reliability of the military charge is high. In addition, the military load being a consumable material, the dispersion precision and the reliability must not be obtained by a significant increase in the cost of production of this load.

L'objet de l'invention est une charge militaire à têtes multiples destinée à être emportée par une bombe, un missile ou un vecteur similaire, dans cette charge des groupements de sous-munitions, tels que des projectiles, sont rangés en couronne pour être extraits radialement sur la trajectoire terminale du vecteur porteur ; cette charge militaire comprend une structure porteuse carénée ayant une enveloppe externe escamotable et un tube central qui porte un support annulaire pour chacun des groupements des projectiles ; ce support annulaire comporte disposés radialement et en regard des projectiles des éjecteurs à gaz déclenchables et des moyens de bridage à verrous, lesquels verrous s'effacent sous l'effet du déplacement des éjecteurs à gaz.The object of the invention is a military charge with multiple heads intended to be carried by a bomb, a missile or a similar vector, in this charge groups of submunitions, such as projectiles, are arranged in crown to be radially extracted on the terminal trajectory of the carrier vector; this military charge includes a streamlined supporting structure having a retractable outer casing and a central tube which carries an annular support for each of the projectile groups; this annular support comprises arranged radially and facing the projectiles of the triggerable gas ejectors and means of clamping with bolts, which bolts are erased under the effect of the displacement of the gas ejectors.

On comprendra mieux l'invention par la description détaillée qui va suivre d'une forme de construction de la charge militaire, faite en regard de dessins annexés, sur ces dessins :

  • - la figure la, sous une forme simplifiée montre un misssile Air-sol comprenant une charge militaire à têtes multiples.
  • - la figure lb est une coupe transversale de la charge militaire qui montre l'arrangement en couronne d'un groupement de projectiles.
  • - la figure 2 est une vue partielle, selon une coupe transversale, qui montre une forme de construction de la charge militaire.
  • - la figure 3 est une vue partielle, selon une coupe transversale, qui montre les détails de réalisation des éjecteurs à gaz.
  • - la figure 4 est une vue partielle, selon une coupe longitudinale qui montre les détails de réalisation du support annulaire des projectiles.
  • - la figure 5 représente une vue extérieure du support annulaire des projectiles.
  • - la figure 6 est une vue en coupe qui montre une variante de construction des éjecteurs à gaz.
The invention will be better understood by the detailed description which follows of a form of construction of the military charge, made with reference to the appended drawings, on these drawings:
  • - Figure la, in a simplified form shows an Air-Ground missile comprising a military charge with multiple heads.
  • - Figure lb is a cross section of the military charge which shows the crown arrangement of a group of projectiles.
  • - Figure 2 is a partial view, in a cross section, which shows a form of construction of the military charge.
  • - Figure 3 is a partial view, in a cross section, which shows the details of embodiment of the gas ejectors.
  • - Figure 4 is a partial view, in a longitudinal section which shows the details of embodiment of the annular projectile support.
  • - Figure 5 shows an external view of the annular projectile support.
  • - Figure 6 is a sectional view showing a variant construction of the gas ejectors.

La figure la sous une forme simplifiée, montre un missile destiné à être emporté et lancé par un aéronef qui demeure en dehors du périmètre de défense de l'ennemi ; ce missile est équipé d'une charge militaire à têtes multiples. Le missile 1 comprend trois sections principales : une section avant 2 de forme ogivale, dans laquelle sont rassemblés les moyens de guidage permettant au missile de se diriger sur le point sensible de l'objectif désigné ; une section médiane 3 constituée par la charge militaire à têtes multiples et une section arrière empennée 4 qui contient éventuellement le propulseur d'accélération du missile mis à feu après son lancement par l'aéronef porteur.The figure la in a simplified form, shows a missile intended to be carried and launched by an aircraft which remains outside the perimeter of defense of the enemy; this missile is equipped with a multi-head military charge. The missile 1 comprises three main sections: a front section 2 of ogival shape, in which are gathered the guide means allowing the missile to direct itself on the sensitive point of the designated objective; a middle section 3 constituted by the military charge with heads multiple and a tail fin section 4 which possibly contains the accelerator of the missile fired after its launch by the carrier aircraft.

La charge militaire 3 comprend essentiellement une structure porteuse, fermée par une enveloppe, dans laquelle sont disposés des moyens permettant d'éjecter radialement des groupements G et G2 de projectiles P rangés en couronne. La structure porteuse de la charge militaire comprend un tube central 3 solidaire de deux flasques de liaison 6 et 7 avec l'enveloppe. La liaison des flasques avec l'enveloppe est temporaire, et l'enveloppe inclut des moyens de fragmentation ou de coulissement, dans le but de découvrir totalement les projectiles un court instant avant leur éjection de la charge militaire.The military charge 3 essentially comprises a supporting structure, closed by an envelope, in which are arranged means making it possible to radially eject groups G and G 2 of projectiles P arranged in a ring. The structure carrying the military load comprises a central tube 3 secured to two connecting flanges 6 and 7 with the envelope. The connection of the flanges with the envelope is temporary, and the envelope includes means of fragmentation or sliding, with the aim of completely discovering the projectiles a short instant before their ejection from the military charge.

L'enveloppe 8 est équipée d'une poutre rigide 9 munie d'anneaux d'accrochage 9a et 9b à l'aéronef, non représenté. Le tube central 3 de la structure porteuse porte des supports annulaires 10 et 10' sur lesquels sont fixés les projectiles. Dans les supports annulaires sont disposés des éjecteurs dont la fonction est d'éjecter radialement chacun des projectiles P, lesquels projectiles sont bridés sur leurs support par des moyens de bridage déverrouillables en synchronisme avec le mouvement des éjecteurs.The envelope 8 is equipped with a rigid beam 9 provided with attachment rings 9a and 9b to the aircraft, not shown. The central tube 3 of the supporting structure carries annular supports 10 and 10 'on which the projectiles are fixed. In the annular supports are disposed ejectors the function of which is to radially eject each of the projectiles P, which projectiles are clamped on their support by unlocking clamping means in synchronism with the movement of the ejectors.

A l'approche de l'objectif désigné, le missile 1 est largué par l'aéronef porteur, puis guidé vers le point sensible. Au voisinage de ce point sensible l'enveloppe 8 de la charge militaire est évincée, puis, conjointement, les moyens de bridage des projectiles P sont déverrouillés et alors, les éjecteurs sont actionnés pour imprimer aux projectiles une vitesse d'éjection latérale déterminée, laquelle conditionne la dispersion au sol des projectiles. Selon la nature de l'objectif, le type des sous-munitions utilisées et les paramètres du tir, la vitesse d'éjection se situe entre quelques mètres et quelques dizaines de mètres par seconde. On pourra noter qu'il est possible en dimensionnant les éjecteurs de fournir des vitesses d'éjection différentes pour les différents groupements de projectiles.When approaching the designated objective, missile 1 is dropped by the carrier aircraft, then guided towards the sensitive point. In the vicinity of this sensitive point the envelope 8 of the military charge is ousted, then, jointly, the means for clamping the projectiles P are unlocked and then, the ejectors are actuated to impart to the projectiles a determined lateral ejection speed, which conditions the dispersal of projectiles on the ground. Depending on the nature of the objective, the type of submunitions used and the firing parameters, the ejection speed is between a few meters and a few tens of meters per second. It may be noted that it is possible by dimensioning the ejectors to provide different ejection speeds for the different groups of projectiles.

La figure 1b est une coupe transversale, suivant A de la charge militaire. Les projectiles P en appui sur le support annulaire 10 sont bridés par des brldes élastiques 14 munies de moyens de serrage 15 deverroulllables à l'Instant de l'extraction des projectiles par les éjecteurs à gaz 13.Figure 1b is a cross section along A of the military charge. The projectiles P resting on the annular support 10 are clamped by elastic flanges 14 provided with clamping means 15 deverroulllables at the instant of the extraction of the projectiles by the gas ejectors 13.

La figure 2 est une vue partielle, en coupe transversale, d'une forme de construction d'une charge militaire à têtes multiples conforme à l'invention, qui montre les éléments associés au support annulaire 10. L'enveloppe externe 8 est équipée d'une poudre rigide 9 munie d'anneaux d'accrochage, tel que l'anneau 9a. Cette enveloppe inclut des moyens pyrotechniques 11 destinés à provoquer la fragmentation de l'enveloppe avant l'éjection des projectiles P. Le nombre de génératrices de fragmentation n'est pas limitée à trois, comme dans la forme de réalisation considérée ici, mais peut être plus grand. Des moyens pyrotechniques similaires (non représentés) permettent de libérer les fragments de l'enveloppe des flasques de la structure porteuse. Les techniques d'escamotage des éléments de carénage des missiles et des fusées étant largement connues, celles-ci ne seront pas décrites. Le support annulaire 8, à sa périphérie, comporte des assises 12 sur lesquelles reposent, également espacés, les corps des projectiles. Dans le support annulaire 10, sont incorporés des éjecteurs à gaz 13 qui sont disposés radialement et en regard de chacun des projectiles. Les projectiles sont maintenus rigidement sur leurs assises par une bride élastique 14 dont les extrémités viennent en pression sur le corps des projectiles adjacents Pi et Pi+1. La partie médiane de ces brides de maintien est munie d'une tige de serrage 15 qui comporte une embase conique 16, laquelle est engagée dans un logement 17 situé dans le support annulaire 10 et dans le plan des éjecteurs pneumatiques 13. La tête de la tige de serrage 15 est munie d'un filetage qui reçoit un écrou de serrage 18. L'éjecteur à gaz 13 comprend un alésage étagé 19 à l'intérieur duquel est placé un piston 20. Ce piston comporte une tête de poussée 21 qui est en appui sur l'épaulement de l'alésage ; cette tête de poussée fournit un moyen de verrouillage de la tige de serrage 13 de la bride élastique 14. La base du piston est équipé d'un moyen d'étanchéité, tel qu'un joint torique 22, qui s'oppose au passage des gaz fournis par une pastille 23 d'une substance pyrotechnique amorçable de préférence électriquement. Selon une variante de construction qui sera décrite ultérieurement, la base des alésages 19 communique avec une source de gaz située dans l'axe du support annulaire. L'embase 16 de la tige de serrage 15 et la tête de poussée 20 de l'éjecteur à gaz communiquent par un logement, à l'intérieur duquel est placée la pièce de verrouillage 24, qui peut librement coulisser et s'effacer du logement 17 de la tige de serrage lors du mouvement de translation du piston, dès que la tête de poussée 21 quitte l'épaulement de l'alésage étagé 19. On pourra noter qu'une goupille cisaillable 25 sous l'effet du déplacement du piston est disposée dans la tête de piston pour assurer son maintien de celle-ci sur l'épaulement de l'alésage.Figure 2 is a partial view, in cross section, of a form of construction of a multi-head military charge according to the invention, which shows the elements associated with the annular support 10. The outer casing 8 is equipped with 'a rigid powder 9 provided with attachment rings, such as the ring 9a. This envelope includes pyrotechnic means 11 intended to cause the fragmentation of the envelope before the ejection of the projectiles P. The number of fragmentation generators is not limited to three, as in the embodiment considered here, but can be bigger. Similar pyrotechnic means (not shown) make it possible to release the fragments of the envelope from the flanges of the support structure. Since the techniques for retracting the fairing elements of missiles and rockets are widely known, these will not be described. The annular support 8, at its periphery, comprises seats 12 on which rest, also spaced, the bodies of the projectiles. In the annular support 10, gas ejectors 13 are incorporated which are arranged radially and facing each of the projectiles. The projectiles are held rigidly on their seats by an elastic flange 14 whose ends come into pressure on the body of the adjacent projectiles Pi and Pi + 1. The middle part of these retaining flanges is provided with a clamping rod 15 which comprises a conical base 16, which is engaged in a housing 17 located in the annular support 10 and in the plane of the pneumatic ejectors 13. The head of the clamping rod 15 is provided with a thread which receives a clamping nut 18. The gas ejector 13 comprises a stepped bore 19 inside which is placed a piston 20. This piston comprises a pusher head 21 which is resting on the shoulder of the bore; this pusher head provides a means of locking the rod tightening 13 of the elastic flange 14. The base of the piston is equipped with a sealing means, such as an O-ring 22, which prevents the passage of gases supplied by a pellet 23 of a pyrotechnic substance which can be primed preferably electrically. According to a construction variant which will be described later, the base of the bores 19 communicates with a gas source situated in the axis of the annular support. The base 16 of the clamping rod 15 and the pusher head 20 of the gas ejector communicate by a housing, inside which is placed the locking piece 24, which can freely slide and disappear from the housing 17 of the clamping rod during the translational movement of the piston, as soon as the pusher head 21 leaves the shoulder of the stepped bore 19. It may be noted that a shearable pin 25 under the effect of the displacement of the piston is disposed in the piston head to ensure that it remains on the shoulder of the bore.

Après l'opération d'élimination de l'enveloppe 8 de la charge militaire, laquelle opération permet de découvrir les projectiles, l'ignition de la pastille pyrotechnique 23 produit un flux de gaz qui pousse, vers l'extérieur, le piston 20 de l'éjecteur. La tête du piston 21 se dégage progressivement et vient libérer la pièce de verrouillage 24. Cette pièce de verrouillage sous l'effet de la contrainte élastique de la bride 14, transmise par la tige de serrage 15 se déplace vers le corps du piston et libère totalement le logement 17 de l'embase 16 de la tige de serrage de son logement 17. La tête du piston 21 poursuit son mouvement et vient au contact du corps du projectile sur lequel elle exerce une force de pression qui assure l'éjection du projectile. Par un choix judicieux des caractéristiques de l'éjecteur, la vitesse d'éjection du projectile peut être contrôlée.After the operation of removing the envelope 8 from the military charge, which operation makes it possible to discover the projectiles, the ignition of the pyrotechnic pellet 23 produces a flow of gas which pushes the piston 20 outward. the ejector. The head of the piston 21 gradually disengages and releases the locking piece 24. This locking piece under the effect of the elastic stress of the flange 14, transmitted by the clamping rod 15 moves towards the body of the piston and releases totally the housing 17 of the base 16 of the clamping rod of its housing 17. The head of the piston 21 continues its movement and comes into contact with the body of the projectile on which it exerts a pressure force which ensures the ejection of the projectile . By a judicious choice of the characteristics of the ejector, the speed of ejection of the projectile can be controlled.

La figure 3 représente selon une vue en coupe une variante de construction des éjecteurs à gaz. Cette variante de construction a pour but d'éviter que la tête de piston 21 ne vienne percuter le corps du projectile, et elle permet d'éliminer la goupille cisaillable 25 décrite précédemment. A l'intérieur du piston est ménagé un alésage 26 qui reçoit une tige de poussée 27. L'extrémité supérieure de la tige de poussée est maintenue au contact du corps par un moyen élastique 28 disposé entre l'extrémité inférieure de cette tige de poussée et le fond de l'alésage 26. Ce moyen élastique 28 peut être constitué par un ressort hélicoidal, un empilement de rondelles "Belleville" ou tout autre moyen équivalent. La fonction du ressort 28 est également de retarder la force de poussée sur le projectile tant que la pièce de verrouillage 24 de la tige de serrage 15 n'est pas escamoté. Les extrémités inférieures des alésages 19 des éjecteurs à gaz sont en communication avec une cavité centrale 29 dans laquelle est disposé un générateur de gaz qui sera décrit ultérieurement.Figure 3 shows a sectional view of a construction variant of the gas ejectors. The purpose of this construction variant is to prevent the piston head 21 from striking the body of the projectile, and it makes it possible to eliminate the shear pin 25 described above. Inside the piston is formed a bore 26 which receives a push rod 27. The upper end of the push rod is held in contact with the body by an elastic means 28 arranged between the lower end of this push rod and the bottom of the bore 26. This elastic means 28 can be constituted by a helical spring, a stack of washers "Belleville" or any other equivalent means. The function of the spring 28 is also to delay the pushing force on the projectile as long as the locking piece 24 of the clamping rod 15 is not retracted. The lower ends of the bores 19 of the gas ejectors are in communication with a central cavity 29 in which is disposed a gas generator which will be described later.

La figure 4 est une vue partielle, en coupe longitudinale, de la charge militaire qui montre les détails de réalisation du support annulaire d'un groupement impair de projectiles P. Le support annulaire 10 est un élément massif qui s'encastre sur le tube central 5 de la structure porteuse. Sur la périphérie du support annulaire, de part et d'autre des éjecteurs à gaz 13, sont situées deux séries de protubérances 30 et 31 constituant les assises 12 sur lesquelles les corps des projectiles sont en appui. Les deux séries de protubérances sont suffisamment distantes l'une de l'autre pour assurer une assise convenable des projectiles. Les protubérances 30 et 31 fournissent, préférentiellement des contacts ponctuels avec le corps des projectiles, et ces points de contacts sont avantageusement situés dans des plans diamétraux qui contiennent les forces élastiques exercées par les brides 14 décrites précédemment. La partie centrale du support annulaire porte un générateur de gaz amorçable 29. Le générateur de gaz comprend un tube 32 dans lequel est placée une substance pyrotechnique et une amorce électrique 33 munie de ses bornes électriques 34. Une chambre 35, située concentriquement au tube 32 du générateur de gaz, comporte des orifices de communication 36 avec les éjecteurs à gaz. Sur cette figure 4, diamétralement à l'éjecteur à gaz montré, on a représenté le logement 17 de l'une des tiges de serrage des brides de maintien des projectiles. Dans le but de positionner longitudinalement les projectiles, ceux-ci sont munis d'un élément de positionnement longitudinal tel que le téton 37. Ce téton s'engage librement dans une empreinte en creux 38 de façon a ne pas perturber l'éjection du projectile correspondant. Le téton 37 situé dans le corps des projectiles peut être un élément rétractable destiné à neutraliser l'armement des projectiles. Le point d'application de la force de poussée fournie par la tête de poussée 27 des éjecteurs à gaz est situé avec précision par rapport au centre de gravité C.G des projectiles.Figure 4 is a partial view, in longitudinal section, of the military charge which shows the details of embodiment of the annular support of an odd grouping of P projectiles. The annular support 10 is a solid element which fits on the central tube 5 of the supporting structure. On the periphery of the annular support, on either side of the gas ejectors 13, are located two series of protrusions 30 and 31 constituting the seats 12 on which the bodies of the projectiles are supported. The two series of protuberances are sufficiently distant from each other to ensure proper seating of the projectiles. The protrusions 30 and 31 preferably provide point contacts with the body of the projectiles, and these contact points are advantageously located in diametrical planes which contain the elastic forces exerted by the flanges 14 described above. The central part of the annular support carries a bootable gas generator 29. The gas generator comprises a tube 32 in which is placed a pyrotechnic substance and an electrical primer 33 provided with its electrical terminals 34. A chamber 35, located concentrically with the tube 32 of the gas generator, has communication orifices 36 with the gas ejectors. In this Figure 4, diametrically to the gas ejector shown, there is shown the housing 17 of one of the clamping rods of the projectile holding flanges. In order to position the projectiles longitudinally, they are provided a longitudinal positioning element such as the stud 37. This stud engages freely in a recess 38 so as not to disturb the ejection of the corresponding projectile. The stud 37 located in the body of the projectiles can be a retractable element intended to neutralize the arming of the projectiles. The point of application of the thrust force supplied by the thrust head 27 of the gas ejectors is located precisely with respect to the center of gravity CG of the projectiles.

La figure 3 représente une vue extérieure du support annulaire 10 des projectiles et elle montre les éléments suivants : les deux séries de protubérances 30 et 31 qui fournissent des assises aux corps des projectiles ; les orifices de sorties de l'alésage étagé des éjecteurs à gaz, et les empreintes en creux 38 qui reçoivent les éléments de positionnement longitudinal des projectiles.FIG. 3 represents an external view of the annular support 10 of the projectiles and it shows the following elements: the two series of protrusions 30 and 31 which provide foundations for the bodies of the projectiles; the outlets of the stepped bore of the gas ejectors, and the indentations 38 which receive the longitudinal positioning elements of the projectiles.

La figure 6, selon une vue en coupe montre une variante de construction de l'éjecteur à gaz et des moyens de verrouillage de la tige de serrage de la bride électrique de maintien des projectiles sur le support annulaire. L'éjecteur à gaz 13 est du type télescopique comprenant un piston creux externe 20a placé dans l'alésage étagé 19a, et un piston interne 27a. Le piston externe 20a comporte à sa base un bossage 20b dont la fonction est de fournir une première portée sur la paroi de l'alésage étagé 19a ; la seconde portée est fournie par une bague 20c en appui sur un épaulement complémentaire 19b de l'alésage étagé ; cette bague 20c étant maintenue en place par un cerclip 19c. La base du piston externe 20a comporte une pièce d'appui 20d pour un ressort 28a qui est également en appui sur la base du piston interne 27a. La partie supérieure du piston externe comporte une tête de piston 21a qui assure le blocage de la pièce 24 a de verrouillage de la base 16a de la tige de serrage 15 de la bride élastique 14. La base 16a de la tige de serrage 15 est de forme cylindrique pour assurer son parfait guidage dans le logement 17 et elle comporte un fraisage 16b dans lequel peut s'engager la pièce de verrouillage 24a. La forme de construction qui vient d'être décrite permet d'imprimer une vitesse latérale d'éjection importante des projectiles lorsque cela s'avère nécessaire, et conjointement, elle procure un guidage amélioré de la tige de serrage de la bride élastique de maintien des projectiles.Figure 6, in a sectional view shows a variant construction of the gas ejector and means for locking the clamping rod of the electric flange for holding the projectiles on the annular support. The gas ejector 13 is of the telescopic type comprising an external hollow piston 20a placed in the stepped bore 19a, and an internal piston 27a. The external piston 20a has at its base a boss 20b whose function is to provide a first bearing on the wall of the stepped bore 19a; the second bearing is provided by a ring 20c bearing on a complementary shoulder 19b of the stepped bore; this ring 20c being held in place by a cerclip 19c. The base of the external piston 20a has a support piece 20d for a spring 28a which is also supported on the base of the internal piston 27a. The upper part of the external piston has a piston head 21a which ensures the locking piece 24a for locking the base 16a of the clamping rod 15 of the elastic flange 14. The base 16a of the clamping rod 15 is cylindrical shape to ensure its perfect guidance in the housing 17 and it includes a milling 16b in which can engage the locking piece 24a. The form of construction which has just been described makes it possible to impart a high lateral ejection speed. projectiles when necessary, and together, it provides improved guidance of the clamping rod of the elastic flange holding the projectiles.

La forme de construction de la structure porteuse carénée peut être variée, et, notamment, les moyens permettant d'escamoter l'enveloppe peuvent être d'un type à extraction selon l'axe longitudinal du missile.The construction form of the streamlined supporting structure can be varied, and, in particular, the means making it possible to retract the envelope can be of an extraction type along the longitudinal axis of the missile.

On voit maintenant plus clairement les avantages fournis par l'invention : les espacements des projectiles sont minimisés pour conférer une capacité d'emport maximale à la charge ; les moyens de fixation et d'éjection des projectiles opèrent en parfait synchronisme et coopèrent judicieusement pour assurer une dispersion uniforme et contrôlée des projectiles, et la simplicité des mécanismes confère une fiabilité certaine à la charge militaire.The advantages provided by the invention can now be seen more clearly: the spacings of the projectiles are minimized to confer maximum carrying capacity on the load; the means for fixing and ejecting the projectiles operate in perfect synchronism and cooperate judiciously to ensure uniform and controlled dispersion of the projectiles, and the simplicity of the mechanisms confers certain reliability on the military charge.

L'invention n'est pas limitée dans ses applications a une charge militaire formée de projectiles, mais elle peut s'appliquer aux lancements de mines explosives de munitions diverses etc... qui doivent être déposées sur le terrain.The invention is not limited in its applications to a military charge formed of projectiles, but it can be applied to the launches of explosive mines of various munitions etc ... which must be deposited on the ground.

Claims (10)

1. Charge militaire à têtes multiples pour bombes, missiles et vecteurs similaires, dans laquelle les groupements de sous-munitions, tels que des projectiles sont rangés en couronne pour être extraits radialement, caractérisée en ce qu'elle comprend une structure porteuse carénée ayant une enveloppe escamotable (8) et un tube central (5) qui porte au moins un support annulaire (10) sur lequel reposent, les corps des projectiles ; des éjecteurs à gaz déclenchables (13) qui sont disposés, radialement et en regard des projectiles, dans le support annulaire (10),et des moyens de bridage (14-17) des projectiles, lesquels sont munis de verrous (24) escamotables sous l'effet du déplacement des éjecteurs à gaz.1. Military head with multiple heads for bombs, missiles and similar vectors, in which the groups of submunitions, such as projectiles are arranged in a crown to be extracted radially, characterized in that it comprises a streamlined bearing structure having a retractable casing (8) and a central tube (5) which carries at least one annular support (10) on which the bodies of the projectiles rest; triggerable gas ejectors (13) which are arranged, radially and facing the projectiles, in the annular support (10), and means for clamping (14-17) the projectiles, which are provided with latches (24) retractable under the effect of moving the gas ejectors. 2. Charge militaire selon la revendication 1 caractérisée en ce qu'un éjecteur à gaz est constitué d'un piston (20) disposé dans un alésage étagé (19) situé dans le support annulaire (10) des projectiles, ce piston comportant une tête (21) maintenue au contact de l'épaulement de l'alésage étagé et en regard du verrou correspondant (24) des moyens de bridage (14-17) des projectiles.2. Military charge according to claim 1 characterized in that a gas ejector consists of a piston (20) disposed in a stepped bore (19) located in the annular support (10) of the projectiles, this piston comprising a head (21) held in contact with the shoulder of the stepped bore and facing the corresponding latch (24) of the projectile clamping means (14-17). 3. Charge militaire selon la revendication 2, caractérisée en ce que l'alésage (19) des éjecteurs à gaz est un élément borgne dans lequel est disposée une pastille (23) d'une substance pyrotechnique amorçable.3. Military charge according to claim 2, characterized in that the bore (19) of the gas ejectors is a blind element in which is disposed a pellet (23) of a bootable pyrotechnic substance. 4. Charge militaire selon la revendication 2, caractérisée en ce que la base de l'alésage (19) des éjecteurs à gaz comporte un orifice de communication avec un générateur de gaz unique (29) disposé dans la partie centrale du support annulaire (10) des corps des projectiles.4. Military charge according to claim 2, characterized in that the base of the bore (19) of the gas ejectors comprises an orifice for communication with a single gas generator (29) disposed in the central part of the annular support (10 ) bodies of projectiles. 5. Charge militaire selon la revendication 2, caractérisée en ce que le piston (20) des éjecteurs à gaz comporte un alésage borgne (26) dans lequel est placée une tige de poussée (27) laquelle est maintenue en appui sur le corps des projectiles par un moyen élastique (28) disposé entre le fond de l'alésage borgne et la base de cette tige de poussée.5. Military charge according to claim 2, characterized in that the piston (20) of the gas ejectors comprises a blind bore (26) in which is placed a push rod (27) which is held in abutment on the body of the projectiles by elastic means (28) disposed between the bottom of the blind bore and the base of this push rod. 6. Charge militaire selon la revendication 5, caractérisée en ce que la base du piston (20) des éjecteurs à gaz est en communication avec la chambre annulaire (35) d'un générateur de gaz (29) situé dans la partie centrale du support annulaire (10) des projectiles.6. Military charge according to claim 5, characterized in that the base of the piston (20) of the gas ejectors is in communication with the annular chamber (35) of a gas generator (29) located in the central part of the support annular (10) projectiles. 7. Charge militaire selon la revendication 1, caractérisée en ce que les éjecteurs à gaz (13) sont du type télescopique dans lequel le piston (20a) comporte une tête (21a) destinée à assurer le blocage des verrous escamotables (24a).7. Military charge according to claim 1, characterized in that the gas ejectors (13) are of the telescopic type in which the piston (20a) comprises a head (21a) intended to ensure the locking of the retractable locks (24a). 8. Charge militaire sleon la revendication 1, caractérisée en ce que les moyens de bridage (14) dont les extrémités son en contact des corps de deux projectiles adjacents, cette bride (14) étant munie, dans sa partie médiane d'une tige de serrage (15) incluant une embase verrouillable (16), laquelle est engagée à l'intérieur d'un alésage (17) réalisé dans le support annulaire (10) des projectiles.8. Military charge sleon claim 1, characterized in that the clamping means (14) whose ends are in contact with the bodies of two adjacent projectiles, this flange (14) being provided in its median part with a rod clamping (15) including a lockable base (16), which is engaged inside a bore (17) formed in the annular support (10) of the projectiles. 9. Charge militaire selon la revendication 1, caractérisée en ce que le support annulaire (10) des projectiles comporte des moyens de positionnement (38) situés en regard de moyens de positionnement correspondants (37) disposés sur le corps du projectile pour assurer le positionnement longitudinal précis des projectiles par rapport aux éjecteurs à gaz.9. Military charge according to claim 1, characterized in that the annular support (10) of the projectiles comprises positioning means (38) located opposite corresponding positioning means (37) arranged on the body of the projectile to ensure positioning precise longitudinal of the projectiles compared to the gas ejectors. 10. Charge militaire selon la revendication 8, caractérisée en ce que les moyens de positionnement longitudinaux (37) des projectiles sont des éléments rétractables destinés à neutraliser l'armement des projectiles.10. Military charge according to claim 8, characterized in that the longitudinal positioning means (37) of the projectiles are retractable elements intended to neutralize the arming of the projectiles.
EP84402635A 1983-12-27 1984-12-18 Cluster ammunition Expired EP0169956B1 (en)

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FR8320839 1983-12-27
FR8320839A FR2557286B1 (en) 1983-12-27 1983-12-27 MULTIPLE HEAD MILITARY LOAD

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Also Published As

Publication number Publication date
FR2557286A1 (en) 1985-06-28
FR2557286B1 (en) 1986-12-05
EP0169956B1 (en) 1988-07-13
US4688486A (en) 1987-08-25
DE3472719D1 (en) 1988-08-18

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