EP0884553A1 - Propulsive unit for a projectile limiting the recoil energy - Google Patents

Propulsive unit for a projectile limiting the recoil energy Download PDF

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Publication number
EP0884553A1
EP0884553A1 EP98401424A EP98401424A EP0884553A1 EP 0884553 A1 EP0884553 A1 EP 0884553A1 EP 98401424 A EP98401424 A EP 98401424A EP 98401424 A EP98401424 A EP 98401424A EP 0884553 A1 EP0884553 A1 EP 0884553A1
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EP
European Patent Office
Prior art keywords
projectile
chamber
assembly according
rod
tube
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
EP98401424A
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German (de)
French (fr)
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EP0884553B1 (en
Inventor
Pascal Gendre
Grégory Soulier
Régis Riffet
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Etienne LaCroix Tous Artifices SA
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Etienne LaCroix Tous Artifices SA
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Classifications

    • 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
    • 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
    • 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
    • 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
    • F42C19/083—Primers or igniters for the initiation or the propellant charge in a cartridged ammunition characterised by the shape and configuration of the base element embedded in the cartridge bottom, e.g. the housing for the squib or percussion cap

Definitions

  • the present invention relates to the field of sets of propulsion for projectiles, in particular the field of tube systems projectile launchers.
  • the present invention finds in particular, but not exclusively, application in the field of weapons. It is indeed not limited to this preferred application, but can be used in any launcher projectile, such as, for example, rocket launching tubes for fireworks, alarm signals, anti-hail rockets, or even in launch tubes on test benches in which projectiles can be formed by example of carriages or equivalent, in particular for impact tests, etc ...
  • launcher projectile such as, for example, rocket launching tubes for fireworks, alarm signals, anti-hail rockets, or even in launch tubes on test benches in which projectiles can be formed by example of carriages or equivalent, in particular for impact tests, etc ...
  • projectile tube launching systems include, as shown in Figure 1 attached, a barrel tube 10, a cylinder head or bottom 12 closing the tube 10 at one end and a pressure source 14, generally formed by a cartridge pyrotechnic.
  • a projectile propulsion unit of the type comprising a room that houses a pressure source and communicates with a space trigger through a passage controlled by a valve control system to control the driving pressure of the projectile and preferably adapted to define a constant pressure in the relaxation room.
  • WO-A-9107636 describes a projectile comprising timed ejection means of a load. More specifically, this document describes a launcher comprising a pressure source not shown, suitable for launching a projectile.
  • the projectile includes a payload, a first pressure chamber and a second pressure chamber.
  • a valve ensures the supply of the first pressure chamber to from the source.
  • the first pressure chamber communicates by elsewhere with the second pressure chamber through an orifice calibrated. More precisely the second chamber is defined between a piston likely to push the payload and a housing defining the first chamber, the piston and the casing being connected by a shear pin.
  • the first chamber is filled, according to the essential characteristic of this document, by a fibrous material. How this projectile works is basically the following. When launching the first room is charged at constant pressure via the valve. Pressure in the second room rises gradually until the pin. The piston then deposits the payload with a sudden rise in the pressure in the second chamber thanks to the passage thus freed from the connection between the two pressure
  • the NAVY TECHN document. DISCLOS. BULL., Vol. III, n ° 3, March 1978, DAHLGREN VIRGINIA describes a thruster provided on a system launcher or on a projectile. This document mainly relates to means for adjusting a surface ratio between an orifice leading to the relaxation room and vents.
  • GB-A-484346 describes a cartridge comprising a projectile guide means in the form of a central internal tube. A part of the propellant charge is placed inside this tube forming projectile guidance means and another part of the propellant charge is disposed outside of this guide tube. So, to allow on the one hand to guarantee a simultaneous initiation of the two parts of the propellant charge and on the other hand an equi-pressure between the interior and outside the guide tube, the latter is perforated. However, the provision described in this document in no way controls the propulsion pressure, and in particular keep it at least substantially constant.
  • the present invention now aims to improve the known projectile propulsion systems, in order to improve the performance of these.
  • a main object of the present invention is to modify the internal ballistic of the launcher tube so that the internal pressure in the tube when firing is as constant as possible.
  • a projectile propulsion unit of the type comprising a chamber which houses a pressure source, characterized in that said chamber that houses the pressure source communicates with at least one rod placed in the starter tube and comprising bores distributed over the length to be released successively during the ejection of the projectile.
  • the arrangement (including distribution, number and size) of the bores provided in the rod is suitable for ensuring propulsion pressure at least substantially constant in the launcher tube.
  • the rod with bores distributed over its length is interposed between the chamber which houses the pressure source and the expansion chamber which ensures the propulsion of the projectile.
  • the present invention also relates to suitable projectiles to be fired from such a power package.
  • the propulsion assembly according to the present invention includes a launcher tube 100.
  • a launcher tube 100 with closed barrel that is to say the bottom is closed by a cylinder head 110 or equivalent.
  • the launcher tube receives a pressure source 120.
  • a pressure source 120 are preferably a pyrotechnic cartridge.
  • the source of pressure 120 can be formed by any equivalent means.
  • the tube 100 is adapted to receive a projectile 200. This is adapted to the internal gauge of the tube 100 as seen in the figures attached.
  • the chamber which houses the pressure source 120 communicates with a rod 130 placed in the launcher tube 100.
  • the rod 130 comprises bores 132 distributed over its length to be released successively when projectile 200 is ejected.
  • the projectile 200 is provided with a chamber 210 opening on its rear end, which chamber 210 is adapted to the diameter outside of the rod 130.
  • the projectile 200 originally covers the majority of bores 132 but gradually releases these during its displacement.
  • the tube 100 and the projectile 200 can be the subject of numerous embodiments. They will therefore not be described in detail by the after.
  • the pressure source or pyrotechnic cartridge 120 is placed directly into the rod 130 so that the chamber 122 which houses the pressure source 120 communicates directly with chamber 140 which receives the projectile 200 via the bores 132.
  • an intermediate chamber 150 is interposed between the chamber very high pressure 122 which houses the source 120 and the chamber 140 receiving the projectile 200.
  • This high pressure intermediate chamber 150 communicates with the internal volume of the rod 130.
  • the rod 130 is closed at its front end by a transverse partition 134 so that the only possible communication between the internal volume of the rod 130 and the chamber 140 receiving the projectile 200 corresponds to bores 132.
  • At least one of the orifices 132 formed in the rod 130 communicates with said chamber 140 receiving the projectile 200, to allow high pressure gas circulation at from the internal volume of the rod 130 towards this chamber 140.
  • This orifice is illustrated under reference 132a in the appended figures. According to the figure 3, it is the orifice (s) closest to the cylinder head 110.
  • the orifice (orifices) 132 which opens (s) initially in room 140 is the one (s) located (s) the most forward, that is to say the closest to the wall 134 (according to FIGS. 4a at 4c, this orifice 132a is then temporarily closed by the projectile 200 after the start of the shot and before the projectile 200 leaves the tube 100).
  • the projectile 200 can be held in the tube 100 before firing by any suitable conventional means, for example by pins shearable.
  • the projectile 200 is provided with a tail unit 220 at its rear end.
  • This empennage 220 is adapted to initially seal all of the ports 132 of the cane with the sole exception of the above-mentioned port 132a.
  • the arrangement of the orifices 132 in particular their distribution, size and number, is suitable for ensuring propulsion pressure at least substantially constant in the propulsion chamber 140.
  • the wall of the rod 130 perforated by the openings 132 is inserted directly or indirectly (via the high pressure chamber 150) between the chamber which houses the pressure source 120 and the propulsion chamber 140.
  • the operation of the propellant assembly in accordance with this invention essentially comprises three successive phases.
  • the pressure prevailing in the launcher tube 100 during these three successive faces is illustrated by way of nonlimiting example in FIG. 5.
  • the pyrotechnic cartridge 120 When ignited, the pyrotechnic cartridge 120 (or the source equivalent pressure formed for example from a gas source compressed) generates very high pressure gases which fill the rod 130 (directly according to FIG. 3 and after transit via the chamber 150 according to FIG. 4) and flow into chamber 140 via the bore (or bores) 132a. Following this flow through of bore 132a, the driving pressure will increase in chamber 140 during a phase referenced phase 1 in Figure 5 to reach a regulating pressure at the end of this phase 1. Projectile 200 is moved in the tube 100 with the increase in this driving pressure.
  • the initial passage section 132a is completely closed at the end of this phase 1, but on the other hand the rear bores 132 are discovered.
  • the displacement of the projectile 200 unmask as the bores 132 formed in the rod 130 to maintain in the form of a plate substantially constant driving pressure in room 140.
  • Progressive release bores 132 increase the fluid flow rate between the source of pressure 120 and the launching chamber 140 to maintain the pressure drive at an at least substantially constant value.
  • a third phase begins when the 200 projectile has exposed all orifices 132.
  • the driving pressure can no longer be maintained at a constant regulation threshold. Then begins a low relaxation phase pressure as illustrated in figure 5.
  • FIGS. 4a, 4b and 4c the projectile 200 is illustrated respectively in the positions occupied in phase 1, phase 2 and phase 3 of Figure 5.
  • the number, size and position of the bores 132 must be adapted according to the power of the pressure source 120, the caliber and mass of the 200 projectile.
  • the rod 130 has a length of 120 mm and a diameter 26 mm and it has 24 bores 132 formed of circular orifice with a diameter of around 2 mm distributed with a variable pitch from 21 to 12 mm along the length of the rod 130 and also provided with 3 holes 132a with a diameter of 1.5mm.
  • propulsion device in accordance with this invention can be combined with any other known structure capable of reduce the force of retraction of the tube 100, for example all means shock absorbers compatible with this propulsion system.
  • the present invention finds particular application in shoulder shooting systems.
  • the present invention offers many advantages over known prior systems.
  • the rod 130 can be integrated into the cylinder head not consumable from a cannon or in a consumable socket secured to a projectile.

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)
  • Excavating Of Shafts Or Tunnels (AREA)

Abstract

The assembly comprises a chamber (122) containing a pressure source (120), connected to the launch tube (100) through a cylinder (130) with perforations (132) which are exposed in sequence as the projectile is ejected from the tube. The cylinder is located between the chamber containing the pressure source and the launch tube expansion chamber (140). The spacing, size and number of the perforations in the cylinder are designed so as to ensure a constant pressure in the launch tube behind the projectile.

Description

La présente invention concerne le domaine des ensembles de propulsion pour projectiles, notamment le domaine des systèmes de tubes lanceurs de projectiles.The present invention relates to the field of sets of propulsion for projectiles, in particular the field of tube systems projectile launchers.

La présente invention trouve en particulier, mais non exclusivement, application dans le domaine des armes. Elle n'est pas limitée en effet à cette application préférentielle, mais peut être exploitée dans tout lanceur de projectile, tel que par exemple les tubes lanceurs de fusées d'artifices, de signaux d'alarmes, de fusées anti-grêle, voire dans des tubes lanceurs sur bancs d'essai dans lesquels les projectiles peuvent être formés par exemple de chariots ou équivalents, notamment pour des tests de chocs, etc...The present invention finds in particular, but not exclusively, application in the field of weapons. It is indeed not limited to this preferred application, but can be used in any launcher projectile, such as, for example, rocket launching tubes for fireworks, alarm signals, anti-hail rockets, or even in launch tubes on test benches in which projectiles can be formed by example of carriages or equivalent, in particular for impact tests, etc ...

La plupart des systèmes de tubes lanceurs de projectiles connus comprennent, comme représenté sur la figure 1 annexée, un tube-canon 10, une culasse ou un fond 12 fermant le tube 10 à une extrémité et une source de pression 14, formée généralement d'une cartouche pyrotechnique.Most known projectile tube launching systems include, as shown in Figure 1 attached, a barrel tube 10, a cylinder head or bottom 12 closing the tube 10 at one end and a pressure source 14, generally formed by a cartridge pyrotechnic.

Le projectile 20, en attente du tir, délimite à l'intérieur du tube 10, une chambre 16 dans laquelle est placée la cartouche pyrotechnique 14.The projectile 20, awaiting the firing, delimits inside the tube 10, a chamber 16 in which the pyrotechnic cartridge 14 is placed.

Lors du tir, l'explosion de la cartouche pyrotechnique 14 génère dans cette chambre 16, une pression motrice pour le projectile 20. Celui-ci est mis en mouvement, et l'augmentation en volume de la chambre 16 induit la détente des gaz jusqu'à la mise à l'air libre de la chambre 16 lors de la sortie du projectile 20 hors du tube-canon 10 comme celà est schématisé sur la figure 2. L'intégrale, pendant cette durée, de la pression, multipliée par la section du tube-canon 10, donne l'impulsion du tir.During the firing, the explosion of the pyrotechnic cartridge 14 generates in this chamber 16, a driving pressure for the projectile 20. The latter is set in motion, and the increase in volume of the chamber 16 induces gas expansion until venting to chamber 16 when of the exit of the projectile 20 out of the barrel-tube 10 as it is shown diagrammatically in FIG. 2. The integral, during this period, of the pressure, multiplied by the section of the barrel tube 10, gives the impetus for the shot.

Ces tubes lanceurs connus présentent l'inconvénient d'une part de générer un effort de recul important ressenti par le tireur ou le support du tube lanceur, d'autre part de nécessiter une paroi de tube d'épaisseur importante, en raison du pic de pression généré immédiatement aprés l'explosion de la cartouche 14. Ce pic est particulièrement préjudiciable pour des armes de tir à l'épaule.These known launch tubes have the drawback of generate a significant backward force felt by the shooter or the support of the launcher tube, on the other hand to require a thick tube wall important, due to the pressure peak generated immediately after the explosion of the cartridge 14. This peak is particularly harmful for long guns.

On a déjà tenté d'écrêter l'effort de recul résultant de ce pic de pression en plaçant des moyens amortisseurs entre le tube lanceur et une référence, par exemple une épaulière, ou un affût support du tube lanceur.We have already tried to limit the retreat effort resulting from this peak pressure by placing damping means between the starter tube and a reference, for example a shoulder rest, or a carriage mount for the launch tube.

La Demanderesse a également proposé dans le document FR-A-2713324 un ensemble de propulsion pour projectile du type comportant une chambre qui loge une source de pression et communique avec un espace de détente par l'intermédiaire d'un passage contrôlé par un clapet d'asservissement permettant de contrôler la pression motrice du projectile et adapté de préférence pour définir une pression constante dans la chambre de détente.The Applicant also proposed in document FR-A-2713324 a projectile propulsion unit of the type comprising a room that houses a pressure source and communicates with a space trigger through a passage controlled by a valve control system to control the driving pressure of the projectile and preferably adapted to define a constant pressure in the relaxation room.

Le document WO-A-9107636 décrit un projectile comprenant des moyens d'éjection temporisés d'une charge. Plus précisément, ce document décrit un lanceur comprenant une source de pression non représentée, adapté pour lancer un projectile. Le projectile comprend une charge utile, une première chambre de pression et une seconde chambre de pression. Un clapet assure l'alimentation de la première chambre de pression à partir de la source. La première chambre de pression communique par ailleurs avec la seconde chambre de pression par l'intermédiaire d'un orifice calibré. Plus précisément la seconde chambre est définie entre un piston susceptible de pousser la charge utile et un carter définissant la première chambre, le piston et le carter étant reliés par une goupille cisaillable. En outre, la première chambre est remplie, selon la caractéristique essentielle de ce document, par un matériau fibreux. Le fonctionnement de ce projectile est essentiellement le suivant. Lors du lancement la première chambre est chargée à pression constante par l'intermédiaire du clapet. La pression dans la seconde chambre s'élève progressivement jusqu'à rupture de la goupille. Le piston dépote alors la charge utile avec élévation soudaine de la pression dans la seconde chambre grâce au passage ainsi dégagé de la liaison entre les deux chambres de pression.WO-A-9107636 describes a projectile comprising timed ejection means of a load. More specifically, this document describes a launcher comprising a pressure source not shown, suitable for launching a projectile. The projectile includes a payload, a first pressure chamber and a second pressure chamber. A valve ensures the supply of the first pressure chamber to from the source. The first pressure chamber communicates by elsewhere with the second pressure chamber through an orifice calibrated. More precisely the second chamber is defined between a piston likely to push the payload and a housing defining the first chamber, the piston and the casing being connected by a shear pin. In in addition, the first chamber is filled, according to the essential characteristic of this document, by a fibrous material. How this projectile works is basically the following. When launching the first room is charged at constant pressure via the valve. Pressure in the second room rises gradually until the pin. The piston then deposits the payload with a sudden rise in the pressure in the second chamber thanks to the passage thus freed from the connection between the two pressure chambers.

Le document NAVY TECHN. DISCLOS. BULL., vol. III, n° 3, Mars 1978, DAHLGREN VIRGINIA décrit un propulseur prévu sur un système lanceur ou sur un projectile. Ce document se rapporte essentiellement à des moyens de réglage d'un rapport de surface entre un orifice conduisant à la chambre de détente et des évents.The NAVY TECHN document. DISCLOS. BULL., Vol. III, n ° 3, March 1978, DAHLGREN VIRGINIA describes a thruster provided on a system launcher or on a projectile. This document mainly relates to means for adjusting a surface ratio between an orifice leading to the relaxation room and vents.

Le document US-A-3628415 enseigne un mortier. Il décrit essentiellement des moyens de réglage de la section libre d'un passage d'évent. Un clapet formé par une palette coopérant avec le passage sert à l'évacuation de l'humidité résiduelle à l'intérieur du mortier.Document US-A-3628415 teaches a mortar. He describes essentially means for adjusting the free section of a passage Wind. A valve formed by a pallet cooperating with the passage serves to the evacuation of residual moisture inside the mortar.

Le document GB-A-484346 décrit une cartouche comprenant un moyen de guidage de projectile sous forme d'un tube interne central. Une partie de la charge propulsive est disposée à l'intérieur de ce tube formant moyen de guidage de projectile et une autre partie de la charge propulsive est disposée à l'extérieur de ce tube de guidage. Ainsi, pour permettre d'une part de garantir une initiation simultanée des deux parties de la charge propulsive et d'autre part une équi-pression entre l'intérieur et l'extérieur du tube de guidage, ce dernier est perforé. Cependant, la disposition décrite dans ce document ne permet aucunement de contrôler la pression de propulsion, et en particulier maintenir celle-ci au moins sensiblement constante.GB-A-484346 describes a cartridge comprising a projectile guide means in the form of a central internal tube. A part of the propellant charge is placed inside this tube forming projectile guidance means and another part of the propellant charge is disposed outside of this guide tube. So, to allow on the one hand to guarantee a simultaneous initiation of the two parts of the propellant charge and on the other hand an equi-pressure between the interior and outside the guide tube, the latter is perforated. However, the provision described in this document in no way controls the propulsion pressure, and in particular keep it at least substantially constant.

La présente invention a maintenant pour but de perfectionner les systèmes connus de propulsion de projectiles, afin d'améliorer les performances de ceux-ci.The present invention now aims to improve the known projectile propulsion systems, in order to improve the performance of these.

Un but principal de la présente invention est de modifier la balistique interne du tube lanceur pour que la pression interne dans le tube lors du tir soit la plus constante possible.A main object of the present invention is to modify the internal ballistic of the launcher tube so that the internal pressure in the tube when firing is as constant as possible.

Ces buts sont atteints dans le cadre de la présente invention grâce à un ensemble de propulsion pour projectile du type comportant une chambre qui loge une source de pression, caractérisé par le fait que ladite chambre qui loge la source de pression communique avec au moins une canne placée dans le tube lanceur et comprenant des alésages répartis sur la longueur pour être libérés successivement lors de l'éjection du projectile.These objects are achieved in the context of the present invention by to a projectile propulsion unit of the type comprising a chamber which houses a pressure source, characterized in that said chamber that houses the pressure source communicates with at least one rod placed in the starter tube and comprising bores distributed over the length to be released successively during the ejection of the projectile.

Selon une autre caractéristique avantageuse de l'invention, l'agencement (notamment répartition, nombre et dimension) des alésages prévus dans la canne est adapté pour assurer une pression de propulsion au moins sensiblement constante dans le tube lanceur.According to another advantageous characteristic of the invention, the arrangement (including distribution, number and size) of the bores provided in the rod is suitable for ensuring propulsion pressure at least substantially constant in the launcher tube.

Selon une autre caractéristique avantageuse de l'invention, la canne munie d'alésages répartis sur sa longueur est intercalée entre la chambre qui loge la source de pression et la chambre de détente qui assure la propulsion du projectile.According to another advantageous characteristic of the invention, the rod with bores distributed over its length is interposed between the chamber which houses the pressure source and the expansion chamber which ensures the propulsion of the projectile.

La présente invention concerne également les projectiles adaptés pour être tirés à partir d'un tel ensemble de propulsion.The present invention also relates to suitable projectiles to be fired from such a power package.

D'autres caractéristiques, buts et avantages de la présente invention apparaitront à la lecture de la description détaillée qui va suivre et en regard des dessins annexés, donnés à titre d'exemples non limitatifs et sur lesquels :

  • la figure 1 précédemment décrite représente une vue schématique en coupe axiale d'un tube lanceur classique,
  • la figure 2 précédemment mentionnée représente l'impulsion motrice dans un tel tube lanceur classique,
  • la figure 3 représente une vue schématique en coupe longitudinale, avant lancement d'un dispositif conforme à un premier mode de réalisation de la présente invention,
  • les figures 4a, 4b, 4c représentent des vues similaires d'un dispositif conforme à un second mode de réalisation de la présente invention, à trois étapes successives de lancement d'un projectile, et
  • la figure 5 représente la pression dans le tube lanceur conforme à la présente invention.
Other characteristics, objects and advantages of the present invention will appear on reading the detailed description which follows and with reference to the appended drawings, given by way of nonlimiting examples and in which:
  • FIG. 1 previously described represents a schematic view in axial section of a conventional launcher tube,
  • FIG. 2 previously mentioned represents the driving impulse in such a conventional launching tube,
  • FIG. 3 represents a schematic view in longitudinal section, before launching a device according to a first embodiment of the present invention,
  • FIGS. 4a, 4b, 4c show similar views of a device according to a second embodiment of the present invention, in three successive stages of launching a projectile, and
  • Figure 5 shows the pressure in the launcher tube according to the present invention.

L'ensemble de propulsion conforme à la présente invention comprend un tube lanceur 100.The propulsion assembly according to the present invention includes a launcher tube 100.

Il s'agit d'un tube lanceur 100 à canon fermé, c'est-à-dire dont le fond est fermé par une culasse 110 ou équivalent.It is a launcher tube 100 with closed barrel, that is to say the bottom is closed by a cylinder head 110 or equivalent.

Le tube lanceur reçoit une source de pression 120. Il s'agit de préférence d'une cartouche pyrotechnique. Cependant, la source de pression 120 peut être formée de tous moyens équivalents. The launcher tube receives a pressure source 120. These are preferably a pyrotechnic cartridge. However, the source of pressure 120 can be formed by any equivalent means.

Le tube 100 est adapté pour recevoir un projectile 200. Celui-ci est adapté au calibre intérieur du tube 100 comme on le voit sur les figures annexées.The tube 100 is adapted to receive a projectile 200. This is adapted to the internal gauge of the tube 100 as seen in the figures attached.

Comme mentionné précédemment, dans le cadre de la présente invention, la chambre qui loge la source de pression 120 communique avec une canne 130 placée dans le tube lanceur 100. La canne 130 comprend des alésages 132 répartis sur sa longueur pour être libérés successivement lors de l'éjection du projectile 200.As mentioned earlier, in the context of this invention, the chamber which houses the pressure source 120 communicates with a rod 130 placed in the launcher tube 100. The rod 130 comprises bores 132 distributed over its length to be released successively when projectile 200 is ejected.

Très préférentiellement, il est prévu une canne 130 unique centrée sur l'axe O-O du tube 100. Cependant, le cas échéant, on peut prévoir plusieurs cannes 130 équiréparties autour de l'axe O-O.Very preferably, there is provided a single rod 130 centered on the axis O-O of the tube 100. However, if necessary, provision can be made several rods 130 evenly distributed around the axis O-O.

On notera que selon les modes de réalisation illustrés sur les figures annexées, le projectile 200 est muni d'une chambre 210 débouchant sur son extrémité arrière, laquelle chambre 210 est adaptée au diamètre extérieur de la canne 130. Ainsi le projectile 200 recouvre à l'origine la majorité des alésages 132 mais libère progressivement ceux-ci lors de son déplacement.Note that according to the embodiments illustrated in the attached figures, the projectile 200 is provided with a chamber 210 opening on its rear end, which chamber 210 is adapted to the diameter outside of the rod 130. Thus the projectile 200 originally covers the majority of bores 132 but gradually releases these during its displacement.

Le tube 100 et le projectile 200 peuvent faire l'objet de nombreux modes de réalisation. Ils ne seront donc pas décrits dans le détail par la suite.The tube 100 and the projectile 200 can be the subject of numerous embodiments. They will therefore not be described in detail by the after.

On notera cependant que selon le mode de réalisation illustré sur la figure 3, la source de pression ou cartouche pyrotechnique 120 est placée directement dans la canne 130 de sorte que la chambre 122 qui loge la source de pression 120 communique directement avec la chambre 140 qui reçoit le projectile 200 par l'intermédiaire des alésages 132.Note however that according to the embodiment illustrated in the Figure 3, the pressure source or pyrotechnic cartridge 120 is placed directly into the rod 130 so that the chamber 122 which houses the pressure source 120 communicates directly with chamber 140 which receives the projectile 200 via the bores 132.

En revanche, selon le mode de réalisation illustré sur les figures 4a, 4b et 4c, une chambre intermédiaire 150 est intercalée entre la chambre très haute pression 122 qui loge la source 120 et la chambre 140 recevant le projectile 200. Cette chambre intermédiaire 150 haute pression communique avec le volume inteme de la canne 130.However, according to the embodiment illustrated in FIGS. 4a, 4b and 4c, an intermediate chamber 150 is interposed between the chamber very high pressure 122 which houses the source 120 and the chamber 140 receiving the projectile 200. This high pressure intermediate chamber 150 communicates with the internal volume of the rod 130.

Bien entendu, la canne 130 est obturée à son extrémité avant par une cloison transversale 134 de sorte que la seule communication possible entre le volume interne de la canne 130 et la chambre 140 recevant le projectile 200 corresponde aux alésages 132.Of course, the rod 130 is closed at its front end by a transverse partition 134 so that the only possible communication between the internal volume of the rod 130 and the chamber 140 receiving the projectile 200 corresponds to bores 132.

En position d'attente de tir, l'un au moins des orifices 132 formés dans la canne 130 communique avec ladite chambre 140 recevant le projectile 200, pour permettre une circulation des gaz haute pression à partir du volume inteme de la canne 130 vers cette chambre 140. Cet orifice est illustré sous la référence 132a sur les figures annexées. Selon la figure 3, il s'agit du ou des orifices le(s) plus proche(s) de la culasse 110.In the firing standby position, at least one of the orifices 132 formed in the rod 130 communicates with said chamber 140 receiving the projectile 200, to allow high pressure gas circulation at from the internal volume of the rod 130 towards this chamber 140. This orifice is illustrated under reference 132a in the appended figures. According to the figure 3, it is the orifice (s) closest to the cylinder head 110.

Par contre, selon les figures 4a à 4c, l'orifice (les orifices) 132 qui débouche(nt) initialement dans la chambre 140 est celui (sont ceux) situé(s) le plus avant, c'est-à-dire le plus proche de la paroi 134 (selon les figures 4a à 4c, cet orifice 132a est ensuite obturé provisoirement par le projectile 200 après le départ du tir et avant que le projectile 200 ne sorte du tube 100).On the other hand, according to FIGS. 4a to 4c, the orifice (orifices) 132 which opens (s) initially in room 140 is the one (s) located (s) the most forward, that is to say the closest to the wall 134 (according to FIGS. 4a at 4c, this orifice 132a is then temporarily closed by the projectile 200 after the start of the shot and before the projectile 200 leaves the tube 100).

Le projectile 200 peut être maintenu dans le tube 100 avant le tir par tous moyens classiques appropriés, par exemple par des goupilles cisaillables.The projectile 200 can be held in the tube 100 before firing by any suitable conventional means, for example by pins shearable.

Selon le mode de réalisation illustré sur les figures 4a à 4c, le projectile 200 est muni d'un empennage 220 à son extrémité arrière.According to the embodiment illustrated in FIGS. 4a to 4c, the projectile 200 is provided with a tail unit 220 at its rear end.

Cet empennage 220 est adapté pour obturer initialement tous les orifices 132 de la canne à la seule exception de l'orifice 132a précité.This empennage 220 is adapted to initially seal all of the ports 132 of the cane with the sole exception of the above-mentioned port 132a.

Comme on l'a indiqué précédemment, dans le cadre de la présente invention, l'agencement des orifices 132, notamment leur répartition, dimension et nombre, est adapté pour assurer une pression de propulsion au moins sensiblement constante dans la chambre de propulsion 140.As previously indicated, in the context of this invention, the arrangement of the orifices 132, in particular their distribution, size and number, is suitable for ensuring propulsion pressure at least substantially constant in the propulsion chamber 140.

Pour cela, comme on le voit sur les figures annexées, la paroi de la canne 130 ajourée par les orifices 132 est intercalée directement ou indirectement (via la chambre haute pression 150) entre la chambre qui loge la source de pression 120 et la chambre de propulsion 140.For this, as can be seen in the appended figures, the wall of the rod 130 perforated by the openings 132 is inserted directly or indirectly (via the high pressure chamber 150) between the chamber which houses the pressure source 120 and the propulsion chamber 140.

Le fonctionnement de l'ensemble propulseur conforme à la présente invention, comprend essentiellement trois phases successives.The operation of the propellant assembly in accordance with this invention, essentially comprises three successive phases.

La pression régnant dans le tube lanceur 100 au cours de ces trois faces successives est illustrée à titre d'exemple non limitatif sur la figure 5. The pressure prevailing in the launcher tube 100 during these three successive faces is illustrated by way of nonlimiting example in FIG. 5.

Lors de la mise à feu, la cartouche pyrotechnique 120 (ou la source de pression équivalente formée par exemple d'une source de gaz comprimée) génère des gaz très haute pression qui remplissent la canne 130 (directement selon la figure 3 et après transit par l'intermédiaire de la chambre 150 selon la figure 4) et s'écoulent dans la chambre 140 via l'alésage (ou les alésages) 132a. Suite à cet écoulement par l'intermédiaire de l'alésage 132a, la pression motrice va croítre dans la chambre 140 pendant une phase référencée phase 1 sur la figure 5 pour atteindre une pression de régulation en fin de cette phase 1. Le projectile 200 est déplacé dans le tube 100 avec l'augmentation de cette pression motrice.When ignited, the pyrotechnic cartridge 120 (or the source equivalent pressure formed for example from a gas source compressed) generates very high pressure gases which fill the rod 130 (directly according to FIG. 3 and after transit via the chamber 150 according to FIG. 4) and flow into chamber 140 via the bore (or bores) 132a. Following this flow through of bore 132a, the driving pressure will increase in chamber 140 during a phase referenced phase 1 in Figure 5 to reach a regulating pressure at the end of this phase 1. Projectile 200 is moved in the tube 100 with the increase in this driving pressure.

De préférence, dans le cadre du second mode de réalisation illustré sur les figures 4a à 4c, grâce au déplacement du projectile 200 pendant cette phase 1, la section de passage initial 132a est totalement refermée à la fin de cette phase 1, mais en revanche les alésages arrières 132 sont découverts.Preferably, in the context of the second embodiment illustrated in FIGS. 4a to 4c, thanks to the displacement of the projectile 200 during this phase 1, the initial passage section 132a is completely closed at the end of this phase 1, but on the other hand the rear bores 132 are discovered.

Pendant la seconde phase illustrée sur la figure 5, le déplacement du projectile 200 démasque au fur et à mesure les alésages 132 formés dans la canne 130 pour maintenir sous forme d'un plateau sensiblement constant la pression motrice dans la chambre 140. La libération progressive des alésages 132 permet d'augmenter le débit de fluide entre la source de pression 120 et la chambre de lancement 140 pour maintenir la pression motrice à une valeur au moins sensiblement constante.During the second phase illustrated in FIG. 5, the displacement of the projectile 200 unmask as the bores 132 formed in the rod 130 to maintain in the form of a plate substantially constant driving pressure in room 140. Progressive release bores 132 increase the fluid flow rate between the source of pressure 120 and the launching chamber 140 to maintain the pressure drive at an at least substantially constant value.

Une troisisème phase débute lorsque le projectile 200 a démasqué tous les orifices 132. La pression motrice ne peut alors plus être maintenue à un seuil de régulation constant. Débute alors une phase de détente basse pression telle qu'illustrée sur la figure 5.A third phase begins when the 200 projectile has exposed all orifices 132. The driving pressure can no longer be maintained at a constant regulation threshold. Then begins a low relaxation phase pressure as illustrated in figure 5.

Sur les figures 4a, 4b et 4c, le projectile 200 est illustré respectivement dans les positions occupées en phase 1, phase 2 et phase 3 de la figure 5.In FIGS. 4a, 4b and 4c, the projectile 200 is illustrated respectively in the positions occupied in phase 1, phase 2 and phase 3 of Figure 5.

Bien entendu, le nombre, la taille et la position des alésages 132 doivent être adaptés en fonction de la puissance de la source de pression 120, du calibre et de la masse du projectile 200. Of course, the number, size and position of the bores 132 must be adapted according to the power of the pressure source 120, the caliber and mass of the 200 projectile.

A titre d'exemple non limitatif, pour un projectile 200 de calibre 3 pouces (7,62cm), la canne 130 a une longueur de 120 mm et un diamètre de 26 mm et elle est munie de 24 alésages 132 formés d'orifice circulaire d'un diamètre de l'ordre de 2 mm répartis avec un pas variable de 21 à 12 mm sur la longueur de la canne 130 et munie par ailleurs de 3 trous 132a d'un diamètre de 1,5mm.By way of nonlimiting example, for a 200 caliber 3 projectile inches (7.62 cm), the rod 130 has a length of 120 mm and a diameter 26 mm and it has 24 bores 132 formed of circular orifice with a diameter of around 2 mm distributed with a variable pitch from 21 to 12 mm along the length of the rod 130 and also provided with 3 holes 132a with a diameter of 1.5mm.

Bien entendu le dispositif de propulsion conforme à la présente invention peut être combiné avec toute autre structure connue susceptible de réduire l'effort de recul du tube 100, par exemple tous moyens amortisseurs compatibles avec ce dispositif de propulsion.Of course the propulsion device in accordance with this invention can be combined with any other known structure capable of reduce the force of retraction of the tube 100, for example all means shock absorbers compatible with this propulsion system.

La présente invention trouve notamment application dans les systèmes de tir à l'épaule.The present invention finds particular application in shoulder shooting systems.

La présente invention offre de nombreux avantages par rapport aux systèmes antérieurs connus.The present invention offers many advantages over known prior systems.

A titre d'exemple non limitatif, on citera :

  • une réduction des efforts de propulsion sur le projectile 200, donc possibilité de réduire la masse de sa structure et, à masse de projectile donnée, possibilité d'augmenter sa charge utile,
  • une réduction de la course de recul du tube 100 à impulsion et effort amortisseur fixés : cela minimise le déplacement du centre de gravité de l'armé en cours de tir, donc les perturbations liées à ce mouvement (bruit de visée, mouvement de rotation du tireur dans le plan vertical) ; cela réduit aussi la durée d'application de l'effort appliqué au tireur ce qui améliore le confort de tir,
  • une réduction de l'effort amortisseur à course de recul du canon et impulsion fixées : cela minimise l'effort appliqué au tireur ce qui améliore le confort de tir ;
  • une augmentation de l'impulsion de tir à effort amortisseur et à course de recul du canon 100 fixés ; cela augmente les performances de tir pour un confort inchangé,
  • une réduction de la pression interne maximale régnant dans le tube 100 d'où la possibilité de réduire l'épaisseur du tube 100 et d'alléger celui-ci.
By way of nonlimiting example, there will be mentioned:
  • a reduction in propulsion forces on the projectile 200, therefore possibility of reducing the mass of its structure and, with a given projectile mass, possibility of increasing its payload,
  • a reduction in the recoil stroke of the tube 100 with fixed impulse and damping force: this minimizes the displacement of the center of gravity of the armored vehicle during firing, therefore the disturbances linked to this movement (aiming noise, rotation movement of the shooter in the vertical plane); this also reduces the duration of application of the force applied to the shooter, which improves shooting comfort,
  • a reduction in the shock absorbing force with the barrel recoil stroke and pulse fixed: this minimizes the force applied to the shooter, which improves shooting comfort;
  • an increase in the firing pulse at shock absorbing force and at recoil stroke of the barrel 100 fixed; this increases shooting performance for unchanged comfort,
  • a reduction in the maximum internal pressure prevailing in the tube 100, hence the possibility of reducing the thickness of the tube 100 and making it lighter.

Bien entendu la présente invention n'est pas limitée aux modes de réalisation particuliers qui viennent d'être décrits, mais s'étend à toute variante conforme à son esprit.Of course, the present invention is not limited to the modes of particular achievements which have just been described, but extends to any variant according to his spirit.

En particulier la canne 130 peut être intégrée dans la culasse non consommable d'un canon ou dans une douille consommable solidaire d'un projectile.In particular the rod 130 can be integrated into the cylinder head not consumable from a cannon or in a consumable socket secured to a projectile.

Claims (16)

Ensemble de propulsion pour projectile du type comportant une chambre (122) qui loge une source de pression (120), caractérisé par le fait que ladite chambre (122) qui loge la source de pression (120) communique avec au moins une canne (130) placée dans le tube lanceur (100) et comprenant des alésages (132) répartis sur sa longueur pour être libérés successivement lors de l'éjection du projectile (200).Propulsion assembly for a projectile of the type comprising a chamber (122) which houses a pressure source (120), characterized by the fact that said chamber (122) which houses the pressure source (120) communicates with at least one rod (130) placed in the launcher tube (100) and comprising bores (132) distributed over its length to be released successively during the ejection of the projectile (200). Ensemble selon la revendication 1, caractérisé par le fait que l'agencement des alésages (132) formés dans la canne (130), notamment leur répartition, leur dimension et leur nombre, est adapté pour assurer une pression de propulsion au moins sensiblement constante dans le tube lanceur (100).Assembly according to claim 1, characterized in that the arrangement of the bores (132) formed in the rod (130), in particular their distribution, their size and their number, is adapted to ensure a at least substantially constant propulsion pressure in the tube launcher (100). Ensemble selon l'une des revendications 1 ou 2, caractérisé par le fait que la paroi de la canne (130) munie des alésages (132) est intercalée entre la chambre qui loge la source de pression (120) et la chambre de détente (140) assurant la propulsion du projectile.Assembly according to one of claims 1 or 2, characterized by the fact that the wall of the rod (130) provided with the bores (132) is interposed between the chamber which houses the pressure source (120) and the expansion chamber (140) ensuring the propulsion of the projectile. Ensemble selon l'une des revendications 1 à 3, caractérisé par le fait que la canne (130) loge la source de pression (120).Assembly according to one of claims 1 to 3, characterized by the fact that the rod (130) houses the pressure source (120). Ensemble selon l'une des revendications 1 à 3, caractérisé par le fait qu'une chambre haute pression intermédiaire (150) est intercalée entre la chambre (122) qui reçoit la source de pression (120) et le volume interne de la canne (130).Assembly according to one of claims 1 to 3, characterized by the fact that an intermediate high pressure chamber (150) is interposed between the chamber (122) which receives the pressure source (120) and the internal volume cane (130). Ensemble selon l'une des revendications 1 à 5, caractérisé par le fait qu'il comprend un projectile (200) muni d'une chambre (210) qui débouche sur sa surface arrière, laquelle chambre (210) est ajustée au diamètre extérieur de la canne (130).Assembly according to one of Claims 1 to 5, characterized by the includes a projectile (200) having a chamber (210) which opens onto its rear surface, which chamber (210) is adjusted to outside diameter of the rod (130). Ensemble selon l'une des revendications 1 à 6, caractérisé par le fait que l'un au moins des alésages (132a) de la canne (130) débouche initialement librement dans la chambre (140) qui reçoit le projectile (200).Assembly according to one of Claims 1 to 6, characterized by the causes at least one of the bores (132a) of the rod (130) to open initially freely in the chamber (140) which receives the projectile (200). Ensemble selon la revendication 7, caractérisé par le fait que l'alésage (132a) qui débouche initialement dans la chambre (140) recevant le projectile (200) est l'alésage (132a) le plus arrière formé dans la canne (130).Assembly according to claim 7, characterized in that the bore (132a) which initially opens into the chamber (140) receiving the projectile (200) is the rearmost bore (132a) formed in the rod (130). Ensemble selon la revendication 7, caractérisé par le fait que l'alésage (132a) qui débouche initialement dans la chambre (140) recevant le projectile (200) est un orifice qui est obturé provisoirement après initiation du tir, par le projectile (200), suite au déplacement de celui-ci.Assembly according to claim 7, characterized in that the bore (132a) which initially opens into the chamber (140) receiving the projectile (200) is an orifice which is provisionally closed after initiation firing, by the projectile (200), following its displacement. Ensemble selon la revendication 9, caractérisé par le fait que l'orifice (132a) qui débouche initialement dans la chambre (140) recevant le projectile (200) est obturé provisoirement par l'empennage du projectile (200) suite au déplacement de celui-ci.Assembly according to claim 9, characterized in that the orifice (132a) which initially opens into the chamber (140) receiving the projectile (200) is temporarily closed by the tail of the projectile (200) following its displacement. Ensemble selon l'une des revendications 1 à 10, caractérisé par le fait que la canne (130) est centrée dans le tube (100).Assembly according to one of claims 1 to 10, characterized by the fact that the rod (130) is centered in the tube (100). Ensemble selon l'une des revendications 1 à 10, caractérisé par le fait qu'il comprend plusieurs cannes (130) munies d'alésages (132) équiréparties autour de l'axe O-O du tube (100).Assembly according to one of claims 1 to 10, characterized by the fact that it comprises several rods (130) provided with bores (132) equally distributed around the axis O-O of the tube (100). Ensemble selon l'une des revendications 1 à 12, caractérisé par le fait que la source de pression (120) est intégrée dans le tube lanceur (100).Assembly according to one of claims 1 to 12, characterized by the fact that the pressure source (120) is integrated in the launcher tube (100). Ensemble selon l'une des revendications 1 à 13, caractérisé par le fait que la source de pression (120) est placée dans une canne (130) intégrée dans la culasse non consommable d'un canon.Assembly according to one of claims 1 to 13, characterized by the fact that the pressure source (120) is placed in a rod (130) integrated in the non-consumable breech of a barrel. Ensemble selon l'une des revendications 1 à 13, caractérisé par le fait que la source de pression (120) est placée dans une canne (130) intégrée dans une douille consommable.Assembly according to one of claims 1 to 13, characterized by the fact that the pressure source (120) is placed in a rod (130) integrated in a consumable socket. Projectile pour ensemble de propulsion conforme à l'une des revendications 1 à 15, caractérisé par le fait qu'il comprend une chambre (210) qui débouche sur son extrémité arrière et qui est ajustée au calibre externe de la canne (130).Projectile for propulsion system conforming to one of the Claims 1 to 15, characterized in that it comprises a chamber (210) which opens at its rear end and which is adjusted to the size outside of the rod (130).
EP98401424A 1997-06-11 1998-06-11 Propulsive unit for a projectile limiting the recoil energy Expired - Lifetime EP0884553B1 (en)

Applications Claiming Priority (2)

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FR9707226 1997-06-11
FR9707226A FR2764682B1 (en) 1997-06-11 1997-06-11 PROPULSION ASSEMBLY FOR A PROJECTILE LIMITING BACK-UP EFFORT

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US9448033B2 (en) * 2013-07-11 2016-09-20 The United States Of America As Represented By The Secretary Of The Army Projectile launcher with a permanent high-low pressure system
US10281248B2 (en) 2015-11-11 2019-05-07 Northrop Grumman Innovation Systems, Inc. Gas generators, launch tube assemblies including gas generators, and related systems and methods

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EP0884553B1 (en) 2003-02-12
DE69811291T2 (en) 2003-11-06
DE69811291D1 (en) 2003-03-20
CA2239154C (en) 2006-08-15
CA2239154A1 (en) 1998-12-11
US6044746A (en) 2000-04-04
FR2764682A1 (en) 1998-12-18
FR2764682B1 (en) 1999-09-03

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