EP0678725A1 - Ignition device for propellant charge - Google Patents

Ignition device for propellant charge Download PDF

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Publication number
EP0678725A1
EP0678725A1 EP95400556A EP95400556A EP0678725A1 EP 0678725 A1 EP0678725 A1 EP 0678725A1 EP 95400556 A EP95400556 A EP 95400556A EP 95400556 A EP95400556 A EP 95400556A EP 0678725 A1 EP0678725 A1 EP 0678725A1
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EP
European Patent Office
Prior art keywords
projectile
jacket
propellant charge
ignition device
rear part
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.)
Withdrawn
Application number
EP95400556A
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German (de)
French (fr)
Inventor
Roland Boual
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CTA International SAS
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CTA International SAS
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Publication date
Application filed by CTA International SAS filed Critical CTA International SAS
Publication of EP0678725A1 publication Critical patent/EP0678725A1/en
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0823—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition
    • F42C19/0826—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition comprising an elongated perforated tube, i.e. flame tube, for the transmission of the initial energy to the propellant charge, e.g. used for artillery shells and kinetic energy penetrators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/045—Cartridges, i.e. cases with charge and missile of telescopic type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
    • F42B5/02—Cartridges, i.e. cases with charge and missile
    • F42B5/067—Mounting or locking missiles in cartridge cases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
    • F42C19/00—Details of fuzes
    • F42C19/08—Primers; Detonators
    • F42C19/0807—Primers; Detonators characterised by the particular configuration of the transmission channels from the priming energy source to the charge to be ignited, e.g. multiple channels, nozzles, diaphragms or filters

Definitions

  • the technical field of the invention is that of devices for igniting a propellant charge of ammunition, in particular of the telescoped type.
  • Telescoped ammunition is characterized by the fact that the projectile is placed inside the envelope containing the propellant charge. This provision makes it possible to define shorter munitions, which allows the design of more compact weapons and / or at higher rates of fire.
  • the projectile is no longer stationed in the barrel of the weapon when the ammunition is placed in the chamber. It is the pressure of the gases generated by the combustion of the propellant charge which will first bring the projectile to station in the barrel of the weapon, then in a second time push it inside the tube.
  • Patent FR2647890 proposes in particular to have at the front of the ammunition a cap connecting the projectile to an annular ring secured to the casing of the ammunition. This device prevents any passage of gas at the front of the projectile, the cap being pushed by the combustion gases at the same time as the projectile.
  • the patent US4335657 describes a telescoped munition mechanically controlling the firing sequence of the propellant charge.
  • a piston acts as a barrier between the priming composition and the propellant charge.
  • the piston which has an axial stroke limited by a stop, slides while advancing the projectile until it is stationed. And it is only from this moment that the combustion gases of the primer can initiate the propellant charge through orifices released by the piston arriving at the end of the stroke.
  • Such a concept is particularly interesting because it makes it possible to ignite a propellant charge of telescoped ammunition in two stages, while protecting the fragile wall of the projectile.
  • the ignition device according to the invention ensures in a simple and effective way a two-stage ignition of the propellant charge, while not causing unnecessary increase in the mass of the ammunition.
  • the subject of the invention is a device for igniting a propellant charge contained in an envelope of a telescoped type of ammunition, comprising a jacket slidingly mounted in a tubular guide skirt integral with the envelope, a pyrotechnic composition d ignition arranged in an internal volume of the jacket and intended during its initiation to push a projectile which pulls the jacket, ignition device characterized in that the jacket is of tubular shape and has at its front end, a closing means made integral by an unlockable connecting means.
  • the means for closing the front end of the liner is produced by a rear part of the projectile, part penetrating into an internal clearance of the liner and the unlockable connecting means between the front end of the liner and the rear part of the projectile is an elastic ring resistant to a determined force.
  • the guide skirt has at its front end an annular flange which ensures the centering of the rear part of the projectile and the jacket has at its rear end a shoulder which guides it inside of the skirt, collar and shoulder which can cooperate after initiation of the pyrotechnic composition in order to produce an axial stop.
  • the jacket comprises at least one sealing means with the guide skirt, means comprising at least one seal disposed in a circular groove on the external surface of the shoulder.
  • the rear part of the projectile comprises at least one seal, arranged in a circular groove provided on the rear part and ensuring a seal with the jacket.
  • the ignition device for a propellant charge contained in an envelope closed at its front part by a guide tube whose internal housing has a diameter less than the external diameter of a projectile belt is characterized in that after initiation of the pyrotechnic composition, the shoulder of the shirt being in abutment against the collar of the skirt and the unlockable connecting means between the projectile and the shirt being released, the initiation of the propellant charge by the ignition pyrotechnic composition is only carried out when the projectile belt is engaged inside the internal housing of the guide tube in order to protect from the pressure generated by the gases of combustion of the propellant charge, a wall of the projectile located in front of the belt.
  • a telescoped munition 1 comprises a casing 2, preferably made of plastic or composite and closed at a rear end by a base 3, made of metallic material, which carries a primer 4 of the type known.
  • the envelope which contains a propellant charge 5 is closed at its front end by a guide tube 6 also made of metallic material.
  • a front seal 7 seals the propellant charge combustion gases under pressure, between the casing 2 and the guide tube 6, while a rear seal 8 seals between the casing and the base 3.
  • the base 3 receives integrally, for example by a threaded connection, a metal guide skirt 9.
  • the latter of tubular shape, has a bore 10 limited towards the front by an annular flange 11 of internal diameter smaller than that of bore 10.
  • a jacket 12 metallic and also of tubular shape, comprises on its external face a cylindrical surface 13 and a shoulder 14 located at its rear end.
  • the jacket is slidably mounted inside the skirt 9.
  • the shoulder 14 and the bore 10 on the one hand, and the cylindrical seat 13 and the flange 11 on the other hand, have sliding adjustments.
  • An O-ring seal 19 is placed in a circular groove in the shoulder 14 and provides a static and dynamic seal against the gases generated by an ignition composition 25, between the jacket 12 and the skirt 9.
  • the latter has a sliding fit with an internal housing 27 of the guide tube 6.
  • Such a cap is described in patent FR2647890.
  • a rear part 16 of the projectile 15 is made integral with the jacket 12, at the level of an internal clearance 21 produced at the front end of the latter and thus constitutes a means for closing the jacket 12.
  • This connection is here ensured by an elastic ring 20 which is housed in corresponding grooves arranged on the projectile and the jacket.
  • the ring constitutes an unlockable connection means between the rear part of the projectile and the jacket.
  • An O-ring seal 22 is placed in a groove in the rear part of the projectile and is supported on the internal clearance 21. It provides gas tightness between the projectile and the jacket 12.
  • the volume defined by an internal diameter 23 of the jacket, the rear part 16 of the projectile and the primer is filled with the pyrotechnic ignition composition 25 intended to push the projectile forward.
  • the rear part 16 of the projectile thus constitutes a means of closing the jacket which delimits a maximum volume for the pyrotechnic composition without causing a penalizing increase in the inert mass.
  • the projectile 15 has on its outside diameter a belt 26 intended to take the scratches from the barrel of a weapon not shown.
  • the outer wall 28 of the projectile (here of the explosive / fragmentable type), which is located in front of the belt, is thin and therefore fragile. It must not be subjected to the pressure generated by the combustion gases of the propellant charge 5, which would risk damaging it and causing a premature explosion.
  • Figure 2 shows the telescoped ammunition 1 after firing.
  • the primer 4 initiated by percussion or electrically, ignites the pyrotechnic composition 25.
  • the combustion of the latter generates pressure on the rear part 16 of the projectile 15 which pushes the projectile 15 / jacket 12 assembly towards the front of the munition .
  • the shoulder 14 of the jacket comes into abutment against the annular collar 11 of the skirt 9, the pressure of the combustion gases increases until the breaking or release of the unlockable connecting means 20 between the projectile and the jacket.
  • the groove of the projectile in which the elastic ring 20 is mounted has a depth substantially equal to the diameter of the ring, while the groove made in the clearance 21 of the jacket has a depth slightly greater than the diameter of the ring.
  • the elastic ring 20 which is mounted substantially at the bottom of the groove of the projectile, opens and is housed entirely in the groove of the release 21 of the shirt.
  • the projectile which is no longer retained, then continues to advance while still being guided and centered by the release 21, which ensures that the projectile is correctly placed in the barrel of the weapon.
  • the projectile belt 26 engages in the housing 27 of the guide tube.
  • the adjustment of the belt 26 in the guide tube 6 is tight.
  • the fragile wall of the projectile situated in front of the belt is protected from the pressure of the combustion gases of the propellant charge 5 by the guide tube 6.
  • the cap 18 engages inside the barrel of the weapon.
  • the cap is broken at the exit of the tube under the effect of aerodynamic forces.
  • the dimensioning of the constituent parts of the device according to the invention will be carried out in such a way that the force necessary for breaking or releasing the unlockable projectile / shirt connecting means is greater than that due to the translation of the shirt in the skirt, but less than the resistance of the axial stop between the flange 11 and the shoulder 14.
  • FIG. 3 represents the telescoped munition 1 at the time of ignition of the propellant charge 5 by the ignition pyrotechnic composition 25, when the rear part 16 of the projectile constituting the closing means leaves the jacket 12.
  • the ignition is thus effected by the front opening of the jacket 12, which is released by the separation of the rear part 16 of the projectile.
  • the ignition of the propellant charge is therefore carried out in two stages and the second stage does not begin until the belt 26 of the projectile has penetrated inside the guide tube 6, which makes it possible to provide effective protection of the fragile wall of the projectile.
  • the guide tube 6 will be dimensioned in such a way that it cannot in any case, under the rise in pressure of the combustion gases of the propellant charge, shrink on the wall 28 of the projectile whose diameter is less than that of the belt.
  • unlockable connection between the sleeve 12 and the rear part 16 of the projectile can be provided by other means than an elastic ring, for example by shearable pins.

Abstract

The firing device for a propulsive charge (5) contains inside a shell (2) consists of a tubular case (12) that can slide inside a tubular guidance skirt (9) attached to the shell (1). The case (12) contains an explosive mixture (25) that will propel the projectile (15). The front end of the case is closed by being held to the back part (16) of the projectile (15) by a connection (20) eg an elastic ring held in grooves. When the explosive mixture (25) ignites, the projectile and therefore the case (12) is pushed out until the shoulder (14) butts up against the collar (11) then the pressure of the combustion gases increase until the connection (20) ruptures which allows the second stage of ignition to take place. <IMAGE>

Description

Le domaine technique de l'invention est celui des dispositifs d'allumage de charge propulsive de munitions, notamment du type télescopées.The technical field of the invention is that of devices for igniting a propellant charge of ammunition, in particular of the telescoped type.

Les munitions télescopées sont caractérisées par le fait que le projectile se trouve disposé à l'intérieur de l'enveloppe contenant la charge propulsive. Cette disposition permet de définir des munitions plus courtes, ce qui autorise la conception d'armes plus compactes et/ou à cadences de tir plus élevées.Telescoped ammunition is characterized by the fact that the projectile is placed inside the envelope containing the propellant charge. This provision makes it possible to define shorter munitions, which allows the design of more compact weapons and / or at higher rates of fire.

Mais la mise au point de telles munitions se heurte à un certain nombre de problèmes.However, the development of such munitions faces a number of problems.

Ainsi le projectile ne se trouve plus à poste dans le tube de l'arme lorsque la munition est disposée dans la chambre. C'est la pression des gaz générés par la combustion de la charge propulsive qui va dans un premier temps amener le projectile à poste dans le tube de l'arme, puis dans un deuxième temps le pousser à l'intérieur du tube.Thus the projectile is no longer stationed in the barrel of the weapon when the ammunition is placed in the chamber. It is the pressure of the gases generated by the combustion of the propellant charge which will first bring the projectile to station in the barrel of the weapon, then in a second time push it inside the tube.

Il est donc à craindre que les gaz de combustion de la charge propulsive devancent le projectile avant qu'il n'ait suffisamment pénétré dans le tube de l'arme pour pouvoir assurer une étanchéité. Un tel phénomène entraînerait une baisse sensible des performances mais également une érosion prématurée du tube de l'arme.It is therefore to be feared that the combustion gases of the propellant charge anticipate the projectile before it has sufficiently penetrated into the barrel of the weapon to be able to ensure a seal. Such a phenomenon would lead to a significant drop in performance but also to premature erosion of the barrel.

Diverses solutions ont été envisagées pour éviter un tel inconvénient.Various solutions have been considered to avoid such a drawback.

Le brevet FR2647890 propose notamment de disposer à l'avant de la munition une coiffe reliant le projectile à une bague annulaire solidaire de l'enveloppe de la munition. Ce dispositif évite tout passage de gaz à l'avant du projectile, la coiffe étant poussée par les gaz de combustion en même temps que le projectile.Patent FR2647890 proposes in particular to have at the front of the ammunition a cap connecting the projectile to an annular ring secured to the casing of the ammunition. This device prevents any passage of gas at the front of the projectile, the cap being pushed by the combustion gases at the same time as the projectile.

Ce dispositif donne entière satisfaction dans de nombreux cas. Cependant, il est inadapté dans le cas de munition comportant un projectile à paroi mince et fragile (tel un projectile explosif / fragmentable). En effet lors de la mise à feu, la pression des gaz de combustion de la charge propulsive s'applique sur la paroi fragile du projectile ce qui entraîne un risque de détérioration sinon d'explosion prématurée de celui-ci.This device is entirely satisfactory in many cases. However, it is unsuitable in the case of ammunition comprising a projectile with a thin and fragile wall (such as an explosive / fragmentable projectile). In fact, when ignited, the pressure of the combustion gases of the propellant charge is applied to the fragile wall of the projectile, which leads to a risk of deterioration if not of premature explosion thereof.

Il est donc nécessaire de pouvoir maîtriser la séquence de mise à feu de la charge propulsive de certaines munitions télescopées, de façon à protéger une paroi fragile du projectile (paroi située en avant de la ceinture).It is therefore necessary to be able to control the firing sequence of the propellant charge of certain telescoped munitions, so as to protect a fragile wall of the projectile (wall located in front of the belt).

Il est par exemple connu d'utiliser une barrière aux gaz de propulsion qui sépare la charge propulsive en deux parties. La composition chimique de cette barrière permet de retarder l'initiation de la partie avant de la charge propulsive où se situe la paroi fragile du projectile. Cependant, la plage de température d'utilisation d'une munition étant très large, il est très difficile de maîtriser le fonctionnement d'une telle composition chimique.It is for example known to use a barrier to propellant gases which separates the propellant charge into two parts. The chemical composition of this barrier makes it possible to delay the initiation of the front part of the propellant charge where the fragile wall of the projectile is located. However, the temperature range of use of a munition being very wide, it is very difficult to control the operation of such a chemical composition.

Le brevet US4335657 décrit une munition télescopée contrôlant mécaniquement la séquence de mise à feu de la charge propulsive. Pour celà, un piston fait barrage entre la composition d'amorçage et la charge propulsive. Lors de la mise à feu de l'amorce, le piston, qui présente une course axiale limitée par une butée, coulisse en faisant avancer le projectile jusqu'à sa mise à poste. Et c'est seulement à partir de ce moment que les gaz de combustion de l'amorce peuvent initier la charge propulsive au travers d'orifices dégagés par le piston arrivé en fin de course.The patent US4335657 describes a telescoped munition mechanically controlling the firing sequence of the propellant charge. For that, a piston acts as a barrier between the priming composition and the propellant charge. When firing the primer, the piston, which has an axial stroke limited by a stop, slides while advancing the projectile until it is stationed. And it is only from this moment that the combustion gases of the primer can initiate the propellant charge through orifices released by the piston arriving at the end of the stroke.

Un tel concept est particulièrement intéressant car il permet d'assurer la mise à feu d'une charge propulsive de munition télescopée en deux temps, en protégeant la paroi fragile du projectile.Such a concept is particularly interesting because it makes it possible to ignite a propellant charge of telescoped ammunition in two stages, while protecting the fragile wall of the projectile.

Cependant, un tel piston présente aussi des inconvénients.However, such a piston also has drawbacks.

D'abord, la transmission des gaz de combustion de la composition assurant l'allumage de la charge propulsive s'effectue radialement au travers d'orifices qui sont limités en nombre et en diamètre. Il en résulte un freinage et/ou une perturbation de la transmission de l'allumage à la charge propulsive qui nuisent aux performances de la munition.First, the transmission of the combustion gases of the composition ensuring the ignition of the propellant charge takes place radially through orifices which are limited in number and in diameter. This results in braking and / or a disturbance in the transmission of the ignition to the propellant charge which adversely affects the performance of the ammunition.

Ensuite, le piston étant clos à sa partie avant, il en résulte un accroissement de la masse inerte de la munition ainsi qu'une diminution de la quantité de composition d'allumage pouvant être embarquée, ce qui diminue la vitesse de mise à poste du projectile.Then, the piston being closed at its front part, this results in an increase in the inert mass of the ammunition as well as a decrease in the quantity of ignition composition that can be loaded, which reduces the speed at which the projectile.

C'est le but de l'invention que de proposer un dispositif d'allumage d'une charge propulsive d'une munition télescopée qui ne présente pas de tels inconvénients.It is the object of the invention to propose a device for igniting a propellant charge of a telescoped munition which does not have such drawbacks.

Ainsi le dispositif d'allumage selon l'invention assure d'une façon simple et efficace un allumage en deux temps de la charge propulsive, tout en n'entraînant pas d'accroissement inutile de la masse de la munition.Thus the ignition device according to the invention ensures in a simple and effective way a two-stage ignition of the propellant charge, while not causing unnecessary increase in the mass of the ammunition.

Il permet également d'obtenir un allumage rapide de la charge propulsive principale par la composition d'allumage.It also makes it possible to obtain rapid ignition of the main propellant charge by the ignition composition.

Ainsi l'invention a pour objet un dispositif d'allumage d'une charge propulsive contenue dans une enveloppe d'une munition du type télescopée , comprenant une chemise montée coulissante dans une jupe de guidage tubulaire solidaire de l'enveloppe, une composition pyrotechnique d'allumage disposée dans un volume interne de la chemise et destinée lors de son initiation à pousser un projectile qui tire la chemise, dispositif d'allumage caractérisé en ce que la chemise est de forme tubulaire et présente à son extrémité avant, un moyen de fermeture rendu solidaire par un moyen de liaison déverrouillable.Thus the subject of the invention is a device for igniting a propellant charge contained in an envelope of a telescoped type of ammunition, comprising a jacket slidingly mounted in a tubular guide skirt integral with the envelope, a pyrotechnic composition d ignition arranged in an internal volume of the jacket and intended during its initiation to push a projectile which pulls the jacket, ignition device characterized in that the jacket is of tubular shape and has at its front end, a closing means made integral by an unlockable connecting means.

De manière avantageuse, le moyen de fermeture de l'extrémité avant de la chemise est réalisé par une partie arrière du projectile, partie pénétrant dans un dégagement interne de la chemise et le moyen de liaison déverrouillable entre l'extrémité avant de la chemise et la partie arrière du projectile est un anneau élastique résistant à un effort déterminé.Advantageously, the means for closing the front end of the liner is produced by a rear part of the projectile, part penetrating into an internal clearance of the liner and the unlockable connecting means between the front end of the liner and the rear part of the projectile is an elastic ring resistant to a determined force.

Selon d'autres caractéristiques de l'invention, la jupe de guidage comporte à son extrémité avant une collerette annulaire qui assure le centrage de la partie arrière du projectile et la chemise comporte à son extrémité arrière un épaulement qui assure son guidage à l'intérieur de la jupe, collerette et épaulement pouvant coopérer après initiation de la composition pyrotechnique afin de réaliser une butée axiale.According to other characteristics of the invention, the guide skirt has at its front end an annular flange which ensures the centering of the rear part of the projectile and the jacket has at its rear end a shoulder which guides it inside of the skirt, collar and shoulder which can cooperate after initiation of the pyrotechnic composition in order to produce an axial stop.

La chemise comporte au moins un moyen d'étanchéité avec la jupe de guidage, moyen comportant au moins un joint disposé dans une rainure circulaire de la surface externe de l'épaulement.The jacket comprises at least one sealing means with the guide skirt, means comprising at least one seal disposed in a circular groove on the external surface of the shoulder.

La partie arrière du projectile comporte au moins un joint, disposé dans une rainure circulaire aménagée sur la partie arrière et assurant une étanchéité avec la chemise.The rear part of the projectile comprises at least one seal, arranged in a circular groove provided on the rear part and ensuring a seal with the jacket.

Selon une autre caractéristique de l'invention, le dispositif d'allumage pour une charge propulsive contenue dans une enveloppe fermée à sa partie avant par un tube de guidage dont le logement interne présente un diamètre inférieur au diamètre externe d'une ceinture du projectile, est caractérisé en ce que après initiation de la composition pyrotechnique, l'épaulement de la chemise étant en butée contre la collerette de la jupe et le moyen de liaison déverrouillable entre le projectile et la chemise étant libéré, l'initiation de la charge propulsive par la composition pyrotechnique d'allumage n'est réalisée que lorsque la ceinture du projectile s'est engagée à l'intérieur du logement interne du tube de guidage afin de protéger de la pression engendrée par les gaz de combustion de la charge propulsive, une paroi du projectile située en avant de la ceinture.According to another characteristic of the invention, the ignition device for a propellant charge contained in an envelope closed at its front part by a guide tube whose internal housing has a diameter less than the external diameter of a projectile belt, is characterized in that after initiation of the pyrotechnic composition, the shoulder of the shirt being in abutment against the collar of the skirt and the unlockable connecting means between the projectile and the shirt being released, the initiation of the propellant charge by the ignition pyrotechnic composition is only carried out when the projectile belt is engaged inside the internal housing of the guide tube in order to protect from the pressure generated by the gases of combustion of the propellant charge, a wall of the projectile located in front of the belt.

L'invention sera mieux comprise à la lecture de la description qui va suivre, faite en référence des dessins annexés dans lesquels:

  • la figure 1 représente en coupe axiale une munition télescopée selon l'invention.
  • la figure 2 représente en coupe axiale une munition télescopée selon l'invention après mise à feu et rupture de la liaison projectile/chemise.
  • la figure 3 représente en coupe axiale une munition télescopée selon l'invention au moment de l'allumage de la charge propulsive.
The invention will be better understood on reading the description which follows, given with reference to the appended drawings in which:
  • Figure 1 shows in axial section a telescoped munition according to the invention.
  • 2 shows in axial section a telescoped munition according to the invention after firing and rupture of the projectile / jacket connection.
  • Figure 3 shows in axial section a telescoped munition according to the invention at the time of ignition of the propellant charge.

En se reportant à la figure 1, une munition télescopée 1 comprend une enveloppe 2, réalisée de façon préférentielle en matière plastique ou en composite et fermée à une extrémité arrière par un culot 3, réalisé en matériau métallique, qui porte une amorce 4 de type connu.Referring to Figure 1, a telescoped munition 1 comprises a casing 2, preferably made of plastic or composite and closed at a rear end by a base 3, made of metallic material, which carries a primer 4 of the type known.

L'enveloppe qui contient une charge propulsive 5 est fermée à son extrémité avant par un tube de guidage 6 également réalisé en matériau métallique.The envelope which contains a propellant charge 5 is closed at its front end by a guide tube 6 also made of metallic material.

Un joint avant 7 assure l'étanchéité à la pression des gaz de combustion de la charge propulsive, entre l'enveloppe 2 et le tube de guidage 6, tandis qu'un joint arrière 8 assure l'étanchéité entre l'enveloppe et le culot 3.A front seal 7 seals the propellant charge combustion gases under pressure, between the casing 2 and the guide tube 6, while a rear seal 8 seals between the casing and the base 3.

Le culot 3 reçoit de façon solidaire, par exemple par une liaison filetée, une jupe de guidage métallique 9. Celle-ci, de forme tubulaire, présente un alésage 10 limité vers l'avant par une collerette annulaire 11 de diamètre interne inférieur à celui de l'alésage 10.The base 3 receives integrally, for example by a threaded connection, a metal guide skirt 9. The latter, of tubular shape, has a bore 10 limited towards the front by an annular flange 11 of internal diameter smaller than that of bore 10.

Une chemise 12, métallique et également de forme tubulaire, comprend sur sa face externe une portée cylindrique 13 et un épaulement 14 situé à son extrémité arrière.A jacket 12, metallic and also of tubular shape, comprises on its external face a cylindrical surface 13 and a shoulder 14 located at its rear end.

La chemise est montée de façon coulissante à l'intérieur de la jupe 9. Pour ce faire, l'épaulement 14 et l'alésage 10 d'une part, et la portée cylindrique 13 et la collerette 11 d'autre part, présentent des ajustements glissants. Un joint d'étanchéité torique 19 est placé dans une rainure circulaire de l'épaulement 14 et assure une étanchéité statique et dynamique aux gaz engendrés par une composition d'allumage 25, entre la chemise 12 et la jupe 9.The jacket is slidably mounted inside the skirt 9. To do this, the shoulder 14 and the bore 10 on the one hand, and the cylindrical seat 13 and the flange 11 on the other hand, have sliding adjustments. An O-ring seal 19 is placed in a circular groove in the shoulder 14 and provides a static and dynamic seal against the gases generated by an ignition composition 25, between the jacket 12 and the skirt 9.

Un projectile 15, qui est ici du type gyrostabilisé, est maintenu à sa partie avant 17 par une coiffe 18 réalisée en matière plastique. Cette dernière présente un ajustement glissant avec un logement interne 27 du tube de guidage 6. Une telle coiffe est décrite dans le brevet FR2647890.A projectile 15, which is here of the gyrostabilized type, is held at its front part 17 by a cap 18 made of plastic. The latter has a sliding fit with an internal housing 27 of the guide tube 6. Such a cap is described in patent FR2647890.

Une partie arrière 16 du projectile 15 est rendue solidaire de la chemise 12, au niveau d'un dégagement interne 21 réalisé à l'extrémité avant de celle-ci et constitue ainsi un moyen de fermeture de la chemise 12. Cette solidarisation est ici assurée par un anneau élastique 20 qui se loge dans des rainures correspondantes aménagées sur le projectile et la chemise. L'anneau constitue un moyen de liaison déverrouillable entre la partie arrière du projectile et la chemise.A rear part 16 of the projectile 15 is made integral with the jacket 12, at the level of an internal clearance 21 produced at the front end of the latter and thus constitutes a means for closing the jacket 12. This connection is here ensured by an elastic ring 20 which is housed in corresponding grooves arranged on the projectile and the jacket. The ring constitutes an unlockable connection means between the rear part of the projectile and the jacket.

Un joint d'étanchéité torique 22 est disposé dans une rainure de la partie arrière du projectile et se trouve en appui sur le dégagement interne 21. Il assure l'étanchéité aux gaz entre le projectile et la chemise 12.An O-ring seal 22 is placed in a groove in the rear part of the projectile and is supported on the internal clearance 21. It provides gas tightness between the projectile and the jacket 12.

Le volume délimité par un diamètre interne 23 de la chemise, la partie arrière 16 du projectile et l'amorce est rempli par la composition pyrotechnique d'allumage 25 destinée à pousser le projectile vers l'avant. La partie arrière 16 du projectile constitue ainsi un moyen de fermeture de la chemise qui délimite un volume maximum pour la composition pyrotechnique sans entraîner d'augmentation pénalisante de la masse inerte.The volume defined by an internal diameter 23 of the jacket, the rear part 16 of the projectile and the primer is filled with the pyrotechnic ignition composition 25 intended to push the projectile forward. The rear part 16 of the projectile thus constitutes a means of closing the jacket which delimits a maximum volume for the pyrotechnic composition without causing a penalizing increase in the inert mass.

Le projectile 15 présente sur son diamètre extérieur une ceinture 26 destinée à prendre les rayures du tube d'une arme non représentée.The projectile 15 has on its outside diameter a belt 26 intended to take the scratches from the barrel of a weapon not shown.

La paroi externe 28 du projectile (ici de type explosif / fragmentable), qui se trouve en avant de la ceinture, est mince donc fragile. Elle ne doit pas être soumise à la pression engendrée par les gaz de combustion de la charge propulsive 5 qui risqueraient de la détériorer et provoquer une explosion prématurée.The outer wall 28 of the projectile (here of the explosive / fragmentable type), which is located in front of the belt, is thin and therefore fragile. It must not be subjected to the pressure generated by the combustion gases of the propellant charge 5, which would risk damaging it and causing a premature explosion.

La figure 2 représente la munition télescopée 1 après mise à feu. L'amorce 4, initiée par percussion ou électriquement, allume la composition pyrotechnique 25. La combustion de cette dernière engendre une pression sur la partie arrière 16 du projectile 15 qui pousse l'ensemble projectile 15 / chemise 12 vers l'avant de la munition. Lorsque l'épaulement 14 de la chemise arrive en butée contre la collerette annulaire 11 de la jupe 9, la pression des gaz de combustion augmente jusqu'à la rupture ou libération du moyen de liaison déverrouillable 20 entre le projectile et la chemise.Figure 2 shows the telescoped ammunition 1 after firing. The primer 4, initiated by percussion or electrically, ignites the pyrotechnic composition 25. The combustion of the latter generates pressure on the rear part 16 of the projectile 15 which pushes the projectile 15 / jacket 12 assembly towards the front of the munition . When the shoulder 14 of the jacket comes into abutment against the annular collar 11 of the skirt 9, the pressure of the combustion gases increases until the breaking or release of the unlockable connecting means 20 between the projectile and the jacket.

La rainure du projectile dans laquelle est monté l'anneau élastique 20 présente une profondeur sensiblement égale au diamètre de l'anneau, tandis que la rainure réalisée dans le dégagement 21 de la chemise présente une profondeur légèrement supérieure au diamètre de l'anneau.The groove of the projectile in which the elastic ring 20 is mounted has a depth substantially equal to the diameter of the ring, while the groove made in the clearance 21 of the jacket has a depth slightly greater than the diameter of the ring.

Ainsi, sous la pression des gaz qui tend à pousser le projectile vers l'avant de la munition, l'anneau élastique 20 qui est monté sensiblement au fond de la rainure du projectile, s'ouvre et se loge entièrement dans la rainure du dégagement 21 de la chemise. Le projectile, qui n'est plus retenu, continue alors à avancer en étant toujours guidé et centré par le dégagement 21, ce qui assure une bonne mise à poste du projectile dans le tube de l'arme.Thus, under the gas pressure which tends to push the projectile towards the front of the ammunition, the elastic ring 20 which is mounted substantially at the bottom of the groove of the projectile, opens and is housed entirely in the groove of the release 21 of the shirt. The projectile, which is no longer retained, then continues to advance while still being guided and centered by the release 21, which ensures that the projectile is correctly placed in the barrel of the weapon.

Sensiblement au moment de la rupture du moyen de liaison 20, la ceinture 26 du projectile s'engage dans le logement 27 du tube de guidage. L'ajustement de la ceinture 26 dans le tube de guidage 6 est serré. Ainsi, la paroi fragile du projectile située en avant de la ceinture est protégée de la pression des gaz de combustion de la charge propulsive 5 par le tube de guidage 6.Significantly at the time of rupture of the connecting means 20, the projectile belt 26 engages in the housing 27 of the guide tube. The adjustment of the belt 26 in the guide tube 6 is tight. Thus, the fragile wall of the projectile situated in front of the belt is protected from the pressure of the combustion gases of the propellant charge 5 by the guide tube 6.

Dès le début de la translation du projectile, la coiffe 18 s'engage à l'intérieur du tube de l'arme. La coiffe est brisée à la sortie du tube sous l'effet des forces aérodynamiques.From the start of the translation of the projectile, the cap 18 engages inside the barrel of the weapon. The cap is broken at the exit of the tube under the effect of aerodynamic forces.

Le dimensionnement des pièces constitutives du dispositif selon l'invention sera effectué de telle sorte que l'effort nécessaire à la rupture ou la libération du moyen de liaison déverrouillable projectile / chemise soit supérieur à celui dû à la translation de la chemise dans la jupe, mais inférieur à la résistance de la butée axiale entre la collerette 11 et l'épaulement 14.The dimensioning of the constituent parts of the device according to the invention will be carried out in such a way that the force necessary for breaking or releasing the unlockable projectile / shirt connecting means is greater than that due to the translation of the shirt in the skirt, but less than the resistance of the axial stop between the flange 11 and the shoulder 14.

La figure 3 représente la munition télescopée 1 au moment de l'allumage de la charge propulsive 5 par la composition pyrotechnique d'allumage 25, lorsque la partie arrière 16 du projectile constituant le moyen de fermeture quitte la chemise 12.FIG. 3 represents the telescoped munition 1 at the time of ignition of the propellant charge 5 by the ignition pyrotechnic composition 25, when the rear part 16 of the projectile constituting the closing means leaves the jacket 12.

L'allumage s'effectue ainsi par l'ouverture avant de la chemise 12, qui se trouve dégagée par la séparation de la partie arrière 16 du projectile. Une telle disposition permet une initiation rapide dans toutes les directions par un espace entre l'extrémité avant de la chemise et l'extrémité arrière du projectile dont la taille augmente au fur et à mesure que le projectile continue à avancer.The ignition is thus effected by the front opening of the jacket 12, which is released by the separation of the rear part 16 of the projectile. Such an arrangement allows rapid initiation in all directions through a space between the front end of the jacket and the rear end of the projectile, the size of which increases as the projectile continues to advance.

L'allumage de la charge propulsive, selon l'invention, s'effectue donc en deux étapes et la deuxième étape ne commence que lorsque la ceinture 26 du projectile a pénétré à l'intérieur du tube de guidage 6, ce qui permet d'assurer une protection efficace de la paroi fragile du projectile.The ignition of the propellant charge, according to the invention, is therefore carried out in two stages and the second stage does not begin until the belt 26 of the projectile has penetrated inside the guide tube 6, which makes it possible to provide effective protection of the fragile wall of the projectile.

Le tube de guidage 6 sera dimensionné de telle manière qu'il ne puisse en aucun cas, sous la montée en pression des gaz de combustion de la charge propulsive, se rétreindre sur la paroi 28 du projectile dont le diamètre est inférieur à celui de la ceinture.The guide tube 6 will be dimensioned in such a way that it cannot in any case, under the rise in pressure of the combustion gases of the propellant charge, shrink on the wall 28 of the projectile whose diameter is less than that of the belt.

Bien entendu, sans sortir du cadre de l'invention, la liaison déverrouillable entre la chemise 12 et la partie arrière 16 du projectile pourra être assuré par un autre moyen qu'un anneau élastique, par exemple par des goupilles cisaillables.Of course, without departing from the scope of the invention, the unlockable connection between the sleeve 12 and the rear part 16 of the projectile can be provided by other means than an elastic ring, for example by shearable pins.

Claims (7)

1 - Dispositif d'allumage d'une charge propulsive (5) contenue dans une enveloppe (2) d'une munition du type télescopée (1), comprenant une chemise (12) montée coulissante dans une jupe de guidage tubulaire (9) solidaire de l'enveloppe, une composition pyrotechnique d'allumage (25) disposée dans un volume interne de la chemise et destinée lors de son initiation à pousser un projectile (15) qui tire la chemise, dispositif d'allumage caractérisé en ce que la chemise (12) est de forme tubulaire et présente à son extrémité avant, un moyen de fermeture (24) rendu solidaire par un moyen de liaison déverrouillable (20). 1 - Device for igniting a propellant charge (5) contained in an envelope (2) of a munition of the telescoped type (1), comprising a jacket (12) slidably mounted in an integral tubular guide skirt (9) of the envelope, a pyrotechnic ignition composition (25) arranged in an internal volume of the jacket and intended during its initiation to push a projectile (15) which pulls the jacket, ignition device characterized in that the jacket (12) is tubular in shape and has at its front end, a closing means (24) made integral by an unlockable connecting means (20). 2 - Dispositif d'allumage selon la revendication 1, caractérisé en ce que le moyen de fermeture de l'extrémité avant de la chemise est réalisé par une partie arrière (16) du projectile, partie pénétrant dans un dégagement interne (21) de la chemise. 2 - Ignition device according to claim 1, characterized in that the means for closing the front end of the jacket is produced by a rear part (16) of the projectile, part penetrating into an internal clearance (21) of the shirt. 3 - Dispositif d'allumage selon la revendication 2, caractérisé en ce que le moyen de liaison déverrouillable entre l'extrémité avant de la chemise et la partie arrière (16) du projectile est un anneau élastique (20) résistant à un effort déterminé. 3 - Ignition device according to claim 2, characterized in that the unlockable connecting means between the front end of the jacket and the rear part (16) of the projectile is an elastic ring (20) resistant to a determined force. 4 - Dispositif d'allumage selon l'une quelconque des revendications 2 ou 3, caractérisé en ce que la jupe de guidage comporte à son extrémité avant une collerette annulaire (11) qui assure le centrage de la partie arrière du projectile et en ce que la chemise comporte à son extrémité arrière un épaulement (14) qui assure son guidage à l'intérieur de la jupe, collerette et épaulement pouvant coopérer après initiation de la composition pyrotechnique afin de réaliser une butée axiale. 4 - Ignition device according to any one of claims 2 or 3, characterized in that the guide skirt has at its front end an annular flange (11) which ensures the centering of the rear part of the projectile and in that the shirt has at its rear end a shoulder (14) which guides it inside the skirt, collar and shoulder which can cooperate after initiation of the pyrotechnic composition in order to produce an axial stop. 5 - Dispositif d'allumage selon la revendication 4, caractérisé en ce que la chemise comporte au moins un moyen d'étanchéité avec la jupe de guidage, moyen comportant au moins un joint (19) disposé dans une rainure circulaire de la surface externe de l'épaulement. 5 - Ignition device according to claim 4, characterized in that the jacket comprises at least one sealing means with the guide skirt, means comprising at least one seal (19) disposed in a circular groove of the external surface of the shoulder. 6 - Dispositif d'allumage selon l'une quelconque des revendications 2 à 5, caractérisé en ce que la partie arrière du projectile comporte au moins un joint (22), disposé dans une rainure circulaire aménagée sur la partie arrière et assurant une étanchéité avec la chemise. 6 - Ignition device according to any one of claims 2 to 5, characterized in that the rear part of the projectile comprises at least one seal (22), arranged in a circular groove arranged on the rear part and ensuring a seal with shirt. 7 - Dispositif d'allumage selon l'une quelconque des revendications 4 à 6, pour une charge propulsive (5) contenue dans une enveloppe (2) fermée à sa partie avant par un tube de guidage (6) dont le logement interne (27) présente un diamètre inférieur au diamètre externe d'une ceinture (26) du projectile, caractérisé en ce que après initiation de la composition pyrotechnique (25), l'épaulement (14) de la chemise étant en butée contre la collerette (11) de la jupe et le moyen de liaison déverrouillable (20) entre le projectile et la chemise étant libéré, l'initiation de la charge propulsive par la composition pyrotechnique d'allumage n'est réalisée que lorsque la ceinture du projectile s'est engagée à l'intérieur du logement interne du tube de guidage afin de protéger de la pression engendrée par les gaz de combustion de la charge propulsive, une paroi (28) du projectile située en avant de la ceinture. 7 - An ignition device according to any one of claims 4 to 6, for a propellant charge (5) contained in an envelope (2) closed at its front part by a guide tube (6) including the internal housing (27 ) has a diameter less than the external diameter of a belt (26) of the projectile, characterized in that after initiation of the pyrotechnic composition (25), the shoulder (14) of the jacket being in abutment against the flange (11) of the skirt and the unlockable connecting means (20) between the projectile and the jacket being released, the initiation of the propellant charge by the pyrotechnic ignition composition is only carried out when the belt of the projectile is engaged inside the internal housing of the guide tube in order to protect from the pressure generated by the combustion gases of the propellant charge, a wall (28) of the projectile located in front of the belt.
EP95400556A 1994-03-16 1995-03-15 Ignition device for propellant charge Withdrawn EP0678725A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9403063 1994-03-16
FR9403063A FR2717569B1 (en) 1994-03-16 1994-03-16 Device for igniting a propellant charge.

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EP0678725A1 true EP0678725A1 (en) 1995-10-25

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FR (1) FR2717569B1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3098292B1 (en) * 2019-07-04 2021-07-23 Cta Int Telescoped ammunition including a shell

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4335657A (en) * 1980-08-13 1982-06-22 Ford Aerospace & Communications Corp. Ammunition round with retained piston
WO1986005265A1 (en) * 1985-03-05 1986-09-12 Nico-Pyrotechnik Hanns-Jürgen Diederichs Gmbh & Co Cartridged ammunition
US4782758A (en) * 1986-02-03 1988-11-08 Aerojet-General Corporation Ammunition round
FR2647890A1 (en) * 1989-06-01 1990-12-07 France Etat Armement DEVICE FOR MAINTAINING A PROJECTILE RELATING TO THE ENVELOPE OF TELESCOPED MUNITION
US5173571A (en) * 1987-12-28 1992-12-22 Montgomery Donald N Projectile guide for telescoped ammunition

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4335657A (en) * 1980-08-13 1982-06-22 Ford Aerospace & Communications Corp. Ammunition round with retained piston
WO1986005265A1 (en) * 1985-03-05 1986-09-12 Nico-Pyrotechnik Hanns-Jürgen Diederichs Gmbh & Co Cartridged ammunition
US4782758A (en) * 1986-02-03 1988-11-08 Aerojet-General Corporation Ammunition round
US5173571A (en) * 1987-12-28 1992-12-22 Montgomery Donald N Projectile guide for telescoped ammunition
FR2647890A1 (en) * 1989-06-01 1990-12-07 France Etat Armement DEVICE FOR MAINTAINING A PROJECTILE RELATING TO THE ENVELOPE OF TELESCOPED MUNITION

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FR2717569A1 (en) 1995-09-22
FR2717569B1 (en) 1996-05-10

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