EP0406114A1 - Launching device for amphibious ammunition with independant propulsive means - Google Patents

Launching device for amphibious ammunition with independant propulsive means Download PDF

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Publication number
EP0406114A1
EP0406114A1 EP90401862A EP90401862A EP0406114A1 EP 0406114 A1 EP0406114 A1 EP 0406114A1 EP 90401862 A EP90401862 A EP 90401862A EP 90401862 A EP90401862 A EP 90401862A EP 0406114 A1 EP0406114 A1 EP 0406114A1
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EP
European Patent Office
Prior art keywords
amphibious
ammunition
ejection
ignition
propellant
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Granted
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EP90401862A
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German (de)
French (fr)
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EP0406114B1 (en
Inventor
Lionel Knur
Roland Siegwald
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Airbus Group SAS
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Airbus Group SAS
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B17/00—Rocket torpedoes, i.e. missiles provided with separate propulsion means for movement through air and through water
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/08—Rocket or torpedo launchers for marine torpedoes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/08—Rocket or torpedo launchers for marine torpedoes
    • F41F3/10—Rocket or torpedo launchers for marine torpedoes from below the surface of the water

Definitions

  • the invention relates to a device for ejecting amphibious ammunition from a submarine not equipped with a hunting system.
  • amphibious ammunition in particular of the type described in French patent 2,588,241, can only be ejected by submarines equipped with hunting systems.
  • the invention aims to overcome this drawback and to allow amphibious ammunition to be ejected with maximum security from any marine or submarine vehicle provided with a torpedo tube.
  • the invention provides a device for ejecting amphibious ammunition, comprising a torpedo tube within which is disposed a powder propellant independent of the ammunition and of the torpedo tube and placed with its ignition assembly in support on the back of this ammunition.
  • the invention thus proposes to have in the launch tube a small propellant at the rear of the ammunition adapted to push it so as to allow it to reach a tube exit speed which can range in practice from 5 to 30 m / s .
  • This disposable propellant accompanies the ammunition beyond the exit of the tube.
  • the ignition assembly is composed of a primary safety ignition device comprising electric igniters and a secondary powder ignition device;
  • This propellant comprises, in a shell terminated by at least one nozzle, the secondary device and a block of powder inhibited laterally with frontal or radial combustion;
  • the shell is composite, being formed from a sealed metallic internal envelope covered with a coil;
  • the winding is made of glass, carbon, "kevlar" or equivalent;
  • Each nozzle has a sealing cap adapted to be ejected by the pressure of the combustion gases of the powder block;
  • the primary safety ignition device is electrically operated and is reversible;
  • the ignition assembly is connected to a control unit linked to the torpedo tube receiving a signal representative of the state of at least the outer door of the torpedo tube and adapted to not activate the assembly d 'ignition only when this exterior door is open.
  • the invention also relates to the aforementioned propellant per se.
  • the invention has the following advantages: - the pyrotechnic pusher allows, from a submarine torpedo tube not equipped with a hunting device, to hunt any type of ammunition (torpedoes and missiles ...) without appreciable modification of the submarine; - The lightness of this pyrotechnic pusher, its small footprint and its integrated security allow a simple implementation; - its operation and performance are practically independent of the immersion of fire; - the choice of powder technology eliminates any maintenance during the lifetime operational of the system; - the adaptation to the ammunition to be hunted (mass of the ammunition and hunting speed) is facilitated by the possibility of varying the mass of powder; - The wound composite structure of the propellant shell has the advantage in the event of bursting of avoiding any significant metallic projections which could damage the interior of the torpedo tube.
  • the propellant is dimensioned so that it can eject ammunition when the launching submarine is between 0 and 750 m deep. Its total size can be contained in a cylinder 200 to 300 mm in diameter and 300 to 400 mm in length.
  • FIG. 1 represents an ejection device 1 in accordance with the invention, adapted to eject an amphibious ammunition 2 such as a missile of weight P, devoid of autonomous propulsion means. It is preferably an amphibious missile in accordance with patent FR-2,588,241.
  • This munition has an exterior shell 2A provided with rear fins 2B. Electric connection cables 2C are also provided here.
  • This device comprises a torpedo tube 3 of any known type, here comprising a front tube 4, and a propellant 5 disposed at the rear of the munition 2.
  • the torpedo tube 3 comprises an internal door 6 and an airlock door 7 while the front tube 4 comprises an external door 8 provided with maneuvering means 8A and allowing communication with the marine environment as well as slides marked 9.
  • 7A is shown the airlock door 7 in the open position.
  • the longitudinal axis X-X of the munition 2 is here slightly offset downward relative to the longitudinal axis Y-Y of the entire torpedo tube.
  • the propellant is positioned, in contact against the bottom of the munition, thanks to a connection system 30.
  • the propellant-pusher shown in FIG. 3 consists of: - a primary safety ignition device 11; - a secondary ignition device 12; - a block of powder laterally inhibited 13; - a metal-coil composite shell marked 14 as a whole,; and - one or more nozzle (s) 15.
  • the primary safety ignition device 11 includes electrical igniters shown schematically in 11B as well as a small primary charge of ignition powder shown schematically in 11C (of all known suitable types). It is armed by means of an electric motor integrated into the igniter, shown diagrammatically in 11A. Wires 16 ensure the connection of the igniter to a control block 17. Signals from judiciously arranged sensors, conventional but not shown, are applied to this block so as to allow it to activate the electric motor only when at the less the front door 8 of the torpedo tube is open. This motor is reversible and can be returned to the safety position by reversing the electric current.
  • the secondary ignition device 12 is composed of ignition powder. It is ignited by the primary safety ignition device 11.
  • the block of powder 13 inhibited laterally is of radial combustion and operates under high pressure; it supplies the gases necessary for propulsion.
  • it presents a channel 18 with a star profile (which explains the variations in thickness appearing in FIG. 3).
  • the hull 14 of the propellant is composed of a very thin metallic internal envelope ensuring sealing, which is covered with wound glass wires coated in a thermosetting resin of any suitable known type and ensuring the mechanical resistance of the assembly.
  • the winding can be made of carbon, kevlar or the like.
  • This wound structure has the advantage, in the event of bursting, of avoiding any significant metallic projections which could damage the interior of the torpedo tube.
  • This shell is thermally protected at the front by a system 19 which also ensures, here, the wedging of the block and at the rear by a cap 20 for thermal protection of the bottom.
  • the nozzle 15, here unique, allows the ejection of the combustion gases and is kept sealed, before firing, by a cover 21 until an external pressure greater than that corresponding to the maximum depth of use of the ammunition. However, in the event of a fire, the pressure of the combustion gases is sufficient to eject this seal.
  • the propellant has a transverse face 22 adapted to be faced at the rear of the ammunition 2, by simple pressing or by positioning and / or connecting means such as ball fixing systems, shearable. Or other.
  • the connection system 30 comprises a connection plate 31 fixed to the propellant by means of holes 32, and temporarily linked to the ammunition by frangible connection members of any suitable known cooperating type. with threads conventionally provided at the rear of the ammunition.
  • the ammunition assembly 3 and its additional propellant 4 are introduced into the "dry" torpedo tube 1 through the interior of the submarine (from the right in FIG. 1) and put in place using conventional on-board tools .
  • the outer door 8 of the tube is opened and the tube is drowned.
  • the hot gases from the igniter ignite the secondary charge 12 which allows the ignition of the block 13.
  • the combustion gases exiting through the nozzle 9 create a thrust which, transmitted by the bearing face 22 and the connection system 30, allows the ammunition 2 to exit the torpedo tube with the speed necessary for the pursuit of the mission.
  • this thrust also has the effect, shortly after firing, of breaking the connecting members and the ammunition, the propellant no longer being then simply by pressing against the ammunition for its ejection.
  • the ammunition-pusher assembly is guided through the torpedo tube.
  • Said pusher at the end of combustion can disengage from the ammunition by gravity (cessation of support on the ammunition) or by ejection (in the case for example of the ignition at this instant of a propellant integrated into the missile and inert until then, as for example in the case of the patent FR-2,588,241 cited above). The pusher is then lost.
  • the pyrotechnic pusher can operate up to a depth of 750 m. Its nozzle is adapted to an intermediate depth with a corresponding outlet pressure.
  • the internal pressure of the order of 100 to 200 bars, makes it possible to obtain a good efficiency of the nozzle.
  • the duration of operation of said pyrotechnic pusher is between 0.5 and 2 seconds. It is recalled in this connection that at sea level at a temperature of 20 ° C, the effective combustion time of a mass of powder from 5 to 10 kg is between 0.5 and 2 seconds and the average force corresponding effective is of the order of 5,000 to 20,000 newton (N).

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Ocean & Marine Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Combustion & Propulsion (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Paper (AREA)
  • Automotive Seat Belt Assembly (AREA)

Abstract

Launching device for amphibious ammunition (2), comprising a torpedo launcher tube (3), within which is arranged a powder propellant (5) independent of the ammunition and arranged so as to bear on the rear of this ammunition. <IMAGE>

Description

L'invention concerne un dispositif permettant d'éjecter des munitions amphibies depuis un sous-marin non équipé d'un système de chasse.The invention relates to a device for ejecting amphibious ammunition from a submarine not equipped with a hunting system.

Actuellement, les munitions amphibies notamment du type de celui décrit dans le brevet français 2.588.241 ne peuvent être éjectés que par des sous-marins équipés de systèmes de chasse.Currently, amphibious ammunition, in particular of the type described in French patent 2,588,241, can only be ejected by submarines equipped with hunting systems.

L'invention vise à pallier cet inconvénient et de permettre d'éjecter avec un maximum de sécurité des munitions amphibies à partir de n'importe quel véhicule marin ou sous-marin pourvu d'un tube lance-torpilles.The invention aims to overcome this drawback and to allow amphibious ammunition to be ejected with maximum security from any marine or submarine vehicle provided with a torpedo tube.

L'invention propose à cet effet un dispositif d'éjection de munitions amphibies, comportant un tube lance-torpilles au sein duquel est disposé un propulseur à poudre indépendant de la munition et du tube lance-­torpilles et placé avec son ensemble d'allumage en appui sur l'arrière de cette munition.To this end, the invention provides a device for ejecting amphibious ammunition, comprising a torpedo tube within which is disposed a powder propellant independent of the ammunition and of the torpedo tube and placed with its ignition assembly in support on the back of this ammunition.

L'invention propose ainsi de disposer dans le tube lanceur un petit propulseur à l'arrière de la munition adapté à la pousser de manière à lui permettre d'atteindre une vitesse de sortie de tube pouvant aller en pratique de 5 à 30 m/s. Ce propulseur, jetable, accompagne la munition au-delà de la sortie du tube.The invention thus proposes to have in the launch tube a small propellant at the rear of the ammunition adapted to push it so as to allow it to reach a tube exit speed which can range in practice from 5 to 30 m / s . This disposable propellant accompanies the ammunition beyond the exit of the tube.

Selon des dispositions préférées de l'inven­tion, éventuellement combinées :
- l'ensemble d'allumage est composé d'un dispositif d'allumage primaire de sécurité comportant des inflam­mateurs électriques et d'un dispositif d'allumage secon­daire à poudre ;
- ce propulseur comporte, dans une coque terminée par au moins une tuyère, le dispositif secondaire et un bloc de poudre inhibé latéralement à combustion frontale ou radiale ;
- la coque est composite, étant formée d'une enveloppe interne métallique étanche recouverte d'un bobinage ;
- le bobinage est en fils de verre, carbone, "kevlar" ou équivalent ;
- chaque tuyère comporte un opercule d'étanchéité adapté à être éjecté par la pression des gaz de combustion du bloc de poudre ;
- le dispositif d'allumage primaire de sécurité est à commande électrique et est reversible ;
- l'ensemble d'allumage est connecté à un bloc de commande lié au tube lance-torpilles recevant un signal représen­tatif de l'état d'au moins la porte extérieure du tube lance-torpilles et adapté à n'activer l'ensemble d'allumage que lorsque cette porte extérieure est ouverte.According to preferred arrangements of the invention, possibly combined:
- the ignition assembly is composed of a primary safety ignition device comprising electric igniters and a secondary powder ignition device;
- This propellant comprises, in a shell terminated by at least one nozzle, the secondary device and a block of powder inhibited laterally with frontal or radial combustion;
- The shell is composite, being formed from a sealed metallic internal envelope covered with a coil;
- the winding is made of glass, carbon, "kevlar" or equivalent;
- Each nozzle has a sealing cap adapted to be ejected by the pressure of the combustion gases of the powder block;
- the primary safety ignition device is electrically operated and is reversible;
the ignition assembly is connected to a control unit linked to the torpedo tube receiving a signal representative of the state of at least the outer door of the torpedo tube and adapted to not activate the assembly d 'ignition only when this exterior door is open.

L'invention vise également le propulseur précité en soi.The invention also relates to the aforementioned propellant per se.

L'invention présente les avantages suivants :
- le pousseur pyrotechnique permet, à partir d'un tube lance-torpilles de sous-marin non équipé de dispositif de chasse, de chasser tout type de munitions (torpilles et missiles ...) sans modification sensible du sous-marin ;
- la légèreté de ce pousseur pyrotechnique, son faible encombrement et sa sécurité intégrée permettent une mise en oeuvre simple ;
- son fonctionnement et ses performances sont pratiquement indépendants de l'immersion de tir ;
- le choix de la technologie à poudre permet de s'af­franchir de toute maintenance pendant la durée de vie opérationnelle du système ;
- l'adaptation à la munition à chasser (masse de la munition et vitesse de chasse) est facilitée par la possibilité de faire varier la masse de poudre ;
- la structure composite bobinée de la coque du propulseur a l'avantage en cas d'éclatement d'éviter toutes projec­tions métalliques importantes qui pourraient détériorer l'intérieur du tube lance-torpilles.The invention has the following advantages:
- the pyrotechnic pusher allows, from a submarine torpedo tube not equipped with a hunting device, to hunt any type of ammunition (torpedoes and missiles ...) without appreciable modification of the submarine;
- The lightness of this pyrotechnic pusher, its small footprint and its integrated security allow a simple implementation;
- its operation and performance are practically independent of the immersion of fire;
- the choice of powder technology eliminates any maintenance during the lifetime operational of the system;
- the adaptation to the ammunition to be hunted (mass of the ammunition and hunting speed) is facilitated by the possibility of varying the mass of powder;
- The wound composite structure of the propellant shell has the advantage in the event of bursting of avoiding any significant metallic projections which could damage the interior of the torpedo tube.

Le propulseur est dimensionné de telle sorte qu'il puisse éjecter une munition lorsque le sous-marin lanceur est entre 0 et 750 m de profondeur. Son encombre­ment total peut être contenu dans un cylindre de 200 à 300 mm de diamètre et de 300 à 400 mm de longueur.The propellant is dimensioned so that it can eject ammunition when the launching submarine is between 0 and 750 m deep. Its total size can be contained in a cylinder 200 to 300 mm in diameter and 300 to 400 mm in length.

L'invention sera mieux comprise à l'aide de la description d'un mode de réalisation proposé à titre d'exemple non limitatif et illustré par les dessins annexés sur lesquels :

  • - la figure 1 est un schéma de principe d'un tube lance-torpilles muni d'un avant-tube, contenant une munition et son propulseur ;
  • - la figure 2 est une vue de côté de l'ensemble munition et propulseur ; et
  • - la figure 3 est une vue en coupe axiale de ce propulseur.
The invention will be better understood using the description of an embodiment proposed by way of nonlimiting example and illustrated by the appended drawings in which:
  • - Figure 1 is a block diagram of a torpedo tube provided with a front tube, containing ammunition and its propellant;
  • - Figure 2 is a side view of the ammunition and propellant assembly; and
  • - Figure 3 is an axial sectional view of this propellant.

La figure 1 représente un dispositif d'éjection 1 conforme à l'invention, adapté à éjecter une munition amphibie 2 telle qu'un missile de poids P, dépourvue de moyens autonomes de propulsion. Il s'agit de préférence d'un missile amphibie conforme au brevet FR-2.588.241.FIG. 1 represents an ejection device 1 in accordance with the invention, adapted to eject an amphibious ammunition 2 such as a missile of weight P, devoid of autonomous propulsion means. It is preferably an amphibious missile in accordance with patent FR-2,588,241.

Cette munition présente extérieurement une coque 2A munie d'ailettes arrière 2B. Des câbles 2C de connexion électrique sont ici également prévus.This munition has an exterior shell 2A provided with rear fins 2B. Electric connection cables 2C are also provided here.

Ce dispositif comporte un tube lance-torpilles 3 de tout type connu, ici comprenant un avant-tube 4, et un propulseur 5 disposé à l'arrière de la munition 2.This device comprises a torpedo tube 3 of any known type, here comprising a front tube 4, and a propellant 5 disposed at the rear of the munition 2.

De manière classique, le tube lance-torpilles 3 comporte une porte interne 6 et une porte de sas 7 tandis que l'avant-tube 4 comporte une porte extérieure 8 munie de moyens de manoeuvre 8A et permettant la communication avec le milieu marin ainsi que des glissières repérées 9. En 7A est représentée la porte de sas 7 en position ouverte.Conventionally, the torpedo tube 3 comprises an internal door 6 and an airlock door 7 while the front tube 4 comprises an external door 8 provided with maneuvering means 8A and allowing communication with the marine environment as well as slides marked 9. In 7A is shown the airlock door 7 in the open position.

On notera que l'axe longitudinal X-X de la munition 2 est ici légèrement décalé vers le bas par rapport à l'axe longitudinal Y-Y de l'ensemble du tube lance-torpilles.It will be noted that the longitudinal axis X-X of the munition 2 is here slightly offset downward relative to the longitudinal axis Y-Y of the entire torpedo tube.

Le propulseur est positionné, en contact contre le fond de la munition, grâce à un système de liaison 30.The propellant is positioned, in contact against the bottom of the munition, thanks to a connection system 30.

Le propulseur-pousseur représenté sur la figure 3 est constitué :
- d'un dispositif d'allumage primaire de sécurité 11 ;
- d'un dispositif d'allumage secondaire 12 ;
- d'un bloc de poudre inhibé latéralement 13 ;
- d'une coque composite métal-bobinage repérée 14 dans son ensemble, ; et
- d'une ou plusieurs tuyère(s) 15.The propellant-pusher shown in FIG. 3 consists of:
- a primary safety ignition device 11;
- a secondary ignition device 12;
- a block of powder laterally inhibited 13;
- a metal-coil composite shell marked 14 as a whole,; and
- one or more nozzle (s) 15.

Le dispositif d'allumage primaire de sécurité 11 comporte des inflammateurs électriques schématisés en 11B ainsi qu'une petite charge primaire de poudre d'al­lumage schématisée en 11C (de tous types connus appro­priés). Il est armé au moyen d'un moteur électrique intégré à l'allumeur, schématisé en 11A. Des fils 16 assurent la connection de l'allumeur à un bloc de commande 17. Des signaux provenant de capteurs judicieusement disposés, classiques mais non représentés, sont appliqués à ce bloc en sorte de ne lui permettre d'actionner le moteur électrique que lorsque au moins la porte avant 8 du tube lance-torpilles est ouverte. Ce moteur est réversible et peut être remis en position sécurité par inversion du courant électrique.The primary safety ignition device 11 includes electrical igniters shown schematically in 11B as well as a small primary charge of ignition powder shown schematically in 11C (of all known suitable types). It is armed by means of an electric motor integrated into the igniter, shown diagrammatically in 11A. Wires 16 ensure the connection of the igniter to a control block 17. Signals from judiciously arranged sensors, conventional but not shown, are applied to this block so as to allow it to activate the electric motor only when at the less the front door 8 of the torpedo tube is open. This motor is reversible and can be returned to the safety position by reversing the electric current.

Le dispositif d'allumage secondaire 12 est composé de poudre d'allumage. Il est amorcé par le dispositif d'allumage primaire de sécurité 11.The secondary ignition device 12 is composed of ignition powder. It is ignited by the primary safety ignition device 11.

Le bloc de poudre 13 inhibé latéralement est à combustion radiale et fonctionne sous haute pression ; il fournit les gaz nécessaires à la propulsion. Il présente ici un canal 18 à profil étoilé (ce qui explique les variations d'épaisseur apparaissant à la figure 3).The block of powder 13 inhibited laterally is of radial combustion and operates under high pressure; it supplies the gases necessary for propulsion. Here it presents a channel 18 with a star profile (which explains the variations in thickness appearing in FIG. 3).

La coque 14 du propulseur est composée d'une enveloppe interne métallique très mince assurant l'étan­chéité, qui est recouverte de fils de verre bobinés enrobés dans une résine thermodurcissable de tout type connu approprié et assurant la résistance mécanique de l'en­semble. En variante, le bobinage peut être en carbone, kevlar ou autre.The hull 14 of the propellant is composed of a very thin metallic internal envelope ensuring sealing, which is covered with wound glass wires coated in a thermosetting resin of any suitable known type and ensuring the mechanical resistance of the assembly. As a variant, the winding can be made of carbon, kevlar or the like.

Cette structure bobinée a l'avantage, en cas d'éclatement, d'éviter toutes projections métalliques importantes qui pourraient détériorer l'intérieur du tube lance-torpilles.This wound structure has the advantage, in the event of bursting, of avoiding any significant metallic projections which could damage the interior of the torpedo tube.

Cette coque est protégée thermiquement à l'avant par un système 19 qui assure en outre, ici, le calage du bloc et à l'arrière par une calotte 20 de protection thermique du fond.This shell is thermally protected at the front by a system 19 which also ensures, here, the wedging of the block and at the rear by a cap 20 for thermal protection of the bottom.

La tuyère 15, ici unique, permet l'éjection des gaz de combustion et est maintenue étanche, avant tir, par un opercule 21 jusqu'à une pression externe supérieure à celle correspondant à la profondeur maximale d'utilisation de la munition. En cas de tir, la pression des gaz de combustion suffit toutefois pour éjecter cet opercule.The nozzle 15, here unique, allows the ejection of the combustion gases and is kept sealed, before firing, by a cover 21 until an external pressure greater than that corresponding to the maximum depth of use of the ammunition. However, in the event of a fire, the pressure of the combustion gases is sufficient to eject this seal.

A l'opposé de cette tuyère le propulseur comporte une face transversale 22 adaptée à être affrontée à l'arrière de la munition 2, par simple appui ou par des moyens de positionnement et/ou de liaison tels que systèmes de fixation à billes, cisaillable ou autre. Dans l'exemple considéré ici le système de liaison 30 comporte un plateau de liaison 31 fixé au propulseur grâce à des perçages 32, et lié de manière temporaire à la munition par des organes de liaison frangible de tout type connu approprié coopérant avec des taraudages classiquement prévus à l'arrière de la munition.Opposite this nozzle, the propellant has a transverse face 22 adapted to be faced at the rear of the ammunition 2, by simple pressing or by positioning and / or connecting means such as ball fixing systems, shearable. Or other. In the example considered here, the connection system 30 comprises a connection plate 31 fixed to the propellant by means of holes 32, and temporarily linked to the ammunition by frangible connection members of any suitable known cooperating type. with threads conventionally provided at the rear of the ammunition.

Le mode de fonctionnement de l'invention est décrit ci-après.The mode of operation of the invention is described below.

L'ensemble munition 3 et son propulseur additionnel 4 sont introduits dans le tube lance-torpilles "sec" 1 par l'intérieur du sous-marin (depuis la droite à la figure 1) et mis en place grâce à un outillage de bord classique.The ammunition assembly 3 and its additional propellant 4 are introduced into the "dry" torpedo tube 1 through the interior of the submarine (from the right in FIG. 1) and put in place using conventional on-board tools .

Les câbles de liaison électrique 2C et 16 entre la munition 2 et le bloc 17 du tube, ainsi qu'entre le dispositif d'allumage primaire de sécurité 11 du pousseur et ce bloc 17 sont branchés et la porte interne 6 du tube est fermée.The electrical connection cables 2C and 16 between the ammunition 2 and the block 17 of the tube, as well as between the primary safety ignition device 11 of the pusher and this block 17 are connected and the internal door 6 of the tube is closed.

Lorsque la décision de tir est prise, la porte extérieure 8 du tube est ouverte et le tube est noyé.When the shooting decision is made, the outer door 8 of the tube is opened and the tube is drowned.

La présence de l'information "porte extérieure ouverte" est nécessaire pour permettre l'armement par le bloc 17 de l'allumeur de sécurité 16 du pousseur et la mise à feu de la charge primaire 11C de celui-ci.The presence of the information "exterior door open" is necessary to enable arming by block 17 of the safety igniter 16 of the pusher and the firing of the primary charge 11C thereof.

Les gaz chauds de l'allumeur mettent à feu la charge secondaire 12 qui permet l'allumage du bloc 13.The hot gases from the igniter ignite the secondary charge 12 which allows the ignition of the block 13.

Les gaz de combustion sortant par la tuyère 9 créent une poussée qui, transmise par la face d'appui 22 et le système de liaison 30, permet à la munition 2 de sortir du tube lance-torpilles avec la vitesse nécessaire à la poursuite de la mission.The combustion gases exiting through the nozzle 9 create a thrust which, transmitted by the bearing face 22 and the connection system 30, allows the ammunition 2 to exit the torpedo tube with the speed necessary for the pursuit of the mission.

Dans l'exemple considéré, cette poussée a également pour effet, peu après la mise la feu, de rompre les organes de liaison et la munition, le propulseur n'étant plus alors qu'en simple appui contre la munition pour son éjection.In the example considered, this thrust also has the effect, shortly after firing, of breaking the connecting members and the ammunition, the propellant no longer being then simply by pressing against the ammunition for its ejection.

Au début de son éjection, l'ensemble munition-­pousseur est guidé dans le tube lance-torpilles. Ledit pousseur en fin de combustion peut se désolidariser de la munition par gravité (cessation de l'appui sur la munition) ou par éjection (dans le cas par exemple de la mise à feu à cet instant d'un propulseur intégré au missile et inerte jusque là, comme par exemple dans le cas du brevet FR-2.588.241 précité). Le pousseur est alors perdu.At the start of its ejection, the ammunition-pusher assembly is guided through the torpedo tube. Said pusher at the end of combustion can disengage from the ammunition by gravity (cessation of support on the ammunition) or by ejection (in the case for example of the ignition at this instant of a propellant integrated into the missile and inert until then, as for example in the case of the patent FR-2,588,241 cited above). The pusher is then lost.

Le pousseur pyrotechnique peut fonctionner jusqu'à une profondeur de 750 m. Sa tuyère est adaptée à une profondeur intermédiaire avec une pression de sortie correspondante.The pyrotechnic pusher can operate up to a depth of 750 m. Its nozzle is adapted to an intermediate depth with a corresponding outlet pressure.

La pression interne, de l'ordre de 100 à 200 bars, permet d'obtenir un bon rendement de la tuyère.The internal pressure, of the order of 100 to 200 bars, makes it possible to obtain a good efficiency of the nozzle.

La durée de fonctionnement dudit pousseur pyrotechnique est comprise entre 0,5 et 2 secondes. Il est rappelé à ce propos qu'au niveau de la mer à une tempéra­ture de 20°C, le temps de combustion efficace d'une masse de poudre de 5 à 10 kg est compris entre 0,5 et 2 secondes et la force moyenne efficace correspondante est de l'ordre de 5.000 à 20.000 newton (N).The duration of operation of said pyrotechnic pusher is between 0.5 and 2 seconds. It is recalled in this connection that at sea level at a temperature of 20 ° C, the effective combustion time of a mass of powder from 5 to 10 kg is between 0.5 and 2 seconds and the average force corresponding effective is of the order of 5,000 to 20,000 newton (N).

Il va de soi que la description qui précède n'a été proposée qu'à titre d'exemple non limitatif et que de nombreuses variantes peuvent être proposées par l'homme de l'art sans sortir du cadre de l'invention.It goes without saying that the foregoing description has been offered only by way of nonlimiting example and that numerous variants can be proposed by those skilled in the art without departing from the scope of the invention.

Claims (14)

1. Dispositif d'éjection pour munition amphibie (2), comportant un tube lance-torpilles (3) au sein duquel est disposé un propulseur à poudre (5) indépendant de la munition et du tube lance-torpilles et placé avec son ensemble d'allumage en appui sur l'arrière de cette munition.1. Ejection device for amphibious ammunition (2), comprising a torpedo tube (3) within which is disposed a powder propellant (5) independent of the ammunition and the torpedo tube and placed with its assembly d 'ignition supported on the rear of this ammunition. 2. Dispositif d'éjection pour munition amphibie selon la revendication 1, caractérisé en ce que l'ensemble d'allumage comporte un dispositif d'allumage primaire de sécurité (11) comportant des inflammateurs électriques (11B) et un dispositif d'allumage secondaire (12) à poudre.2. Ejection device for amphibious ammunition according to claim 1, characterized in that the ignition assembly comprises a primary safety ignition device (11) comprising electric igniters (11B) and a secondary ignition device (12) powder. 3. Dispositif d'éjection pour munition amphibie selon la revendication 1 ou la revendication 2, caractérisé en ce que ce propulseur (5) comporte dans une coque (14) terminée par au moins une tuyère (15), le dispositif d'allumage secondaire (11, 12) et un bloc de poudre (13) inhibé latéralement à combustion radiale ou frontale.3. Ejection device for amphibious ammunition according to claim 1 or claim 2, characterized in that this propellant (5) comprises in a shell (14) terminated by at least one nozzle (15), the secondary ignition device (11, 12) and a block of powder (13) inhibited laterally with radial or frontal combustion. 4. Dispositif d'éjection pour munition amphibie selon la revendication 3, caractérisé en ce que la coque (14) est composite, étant formée d'une enveloppe interne métallique étanche recouverte d'un bobinage.4. Ejection device for amphibious ammunition according to claim 3, characterized in that the shell (14) is composite, being formed of a sealed metallic internal envelope covered with a coil. 5. Dispositif d'éjection pour munition amphibie selon la revendication 4, caractérisé en ce que le bobinage est en fils de verre, ou carbone, ou "kevlar" ou autre.5. Ejection device for amphibious ammunition according to claim 4, characterized in that the winding is glass son, or carbon, or "kevlar" or other. 6. Dispositif d'éjection pour munition amphibie selon l'une quelconque des revendications 3 à 5, carac­térisé en ce que chaque tuyère (15) comporte un opercule d'étanchéité (21) adapté à être éjecté par la pression des gaz de combustion du bloc de poudre.6. Ejection device for amphibious ammunition according to any one of claims 3 to 5, characterized in that each nozzle (15) comprises a sealing cap (21) adapted to be ejected by the pressure of the combustion gases of the block of powder. 7. Dispositif d'éjection pour munition amphibie selon l'une quelconque des revendications 2 à 6, carac­térisé en ce que le dispositif d'allumage primaire de sécurité est à commande électrique et reversible.7. Ejection device for amphibious ammunition according to any one of claims 2 to 6, characterized in that the primary safety ignition device is electrically operated and reversible. 8. Dispositif d'éjection pour munition amphibie selon l'une quelconque des revendications 2 à 7, caractérisé en ce que l'ensemble d'allumage (11, 12) est connecté à un bloc de commande (17) lié au tube lance-­torpilles recevant un signal représentatif de l'état d'au moins la porte extérieure du tube lance-torpilles et adapté à n'activer l'ensemble d'allumage que lorsque cette porte extérieure est ouverte.8. Ejection device for amphibious ammunition according to any one of claims 2 to 7, characterized in that the ignition assembly (11, 12) is connected to a control unit (17) linked to the torpedo tube receiving a signal representative of the state of at least the outer door of the tube torpedoes and adapted to activate the ignition assembly only when this exterior door is open. 9. Propulseur pour l'éjection d'une munition amphibie (2) à partir d'un tube lance-torpilles (3) comportant une coque (14) terminée par au moins une tuyère (15), contenant une partie au moins d'un ensemble d'al­lumage (11, 12) et un bloc de poudre (13) inhibé latérale­ment à combustion frontale ou radiale.9. Propellant for the ejection of an amphibious ammunition (2) from a torpedo tube (3) comprising a shell (14) terminated by at least one nozzle (15), containing at least part of an ignition assembly (11, 12) and a powder block (13) laterally inhibited for frontal or radial combustion. 10. Propulseur pour l'éjection d'une munition amphibie selon la revendication 9, caractérisé en ce que la coque (14) est composite, étant formée d'une enveloppe interne métallique étanche recouverte d'un bobinage.10. Propellant for the ejection of an amphibious ammunition according to claim 9, characterized in that the shell (14) is composite, being formed of a sealed metallic internal envelope covered with a coil. 11. Propulseur pour l'éjection d'une munition amphibie selon la revendication 10, caractérisé en ce que le bobinage est en fils de verre, carbone, "kevlar" ou autre.11. Thruster for the ejection of an amphibious ammunition according to claim 10, characterized in that the winding is made of glass, carbon, "kevlar" or other son. 12. Propulseur pour l'éjection d'une munition amphibie selon l'une quelconque des revendications 9 à 11, caractérisé en ce que chaque tuyère (15) comporte un opercule d'étanchéité (21) adapté à être éjecté par la pression des gaz de combustion du bloc de poudre.12. Propellant for the ejection of an amphibious ammunition according to any one of claims 9 to 11, characterized in that each nozzle (15) comprises a sealing cap (21) adapted to be ejected by the pressure of the gases combustion of the powder block. 13. Propulseur pour l'éjection d'une munition amphibie selon l'une quelconque des revendications 9 à 12, caractérisé en ce que l'ensemble d'allumage est à commande électrique.13. A thruster for the ejection of an amphibious ammunition according to any one of claims 9 to 12, characterized in that the ignition assembly is electrically controlled. 14. Propulseur pour l'éjection d'une munition amphibie selon la revendication 13, caractérisé en ce que l'ensemble d'allumage est composé d'un dispositif d'al­lumage primaire de sécurité (11) comportant des inflam­mateurs électriques (11B) et d'un dispositif d'allumage secondaire (12) à poudre.14. A propellant for the ejection of an amphibious ammunition according to claim 13, characterized in that the ignition assembly is composed of a primary safety ignition device (11) comprising electric igniters (11B) and a secondary powder ignition device (12).
EP19900401862 1989-06-30 1990-06-28 Launching device for amphibious ammunition with independant propulsive means Expired - Lifetime EP0406114B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8908841A FR2649194B1 (en) 1989-06-30 1989-06-30 EJECTION DEVICE FOR AMPHIBIOUS AMMUNITION AND INDEPENDENT PROPELLER THEREOF
FR8908841 1989-06-30

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EP0406114A1 true EP0406114A1 (en) 1991-01-02
EP0406114B1 EP0406114B1 (en) 1993-09-08

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EP19900401862 Expired - Lifetime EP0406114B1 (en) 1989-06-30 1990-06-28 Launching device for amphibious ammunition with independant propulsive means

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EP (1) EP0406114B1 (en)
BR (1) BR9003075A (en)
DE (1) DE69003190T2 (en)
DK (1) DK0406114T3 (en)
ES (1) ES2044483T3 (en)
FR (1) FR2649194B1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2407148A (en) * 1996-07-04 2005-04-20 Secr Defence Projectile launcher for attack of underwater targets
GB2608782A (en) * 1998-06-04 2023-01-11 Bae Systems Plc Underwater launch system

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2965913B1 (en) 2010-10-08 2013-04-05 IFP Energies Nouvelles DEVICE FOR DETECTING THE PRESENCE OF A FLUID, SUCH AS A LIQUID FLUID, IN A SPACE OF A CONTAINER AND METHOD USING SUCH A DEVICE
DE102013006003A1 (en) * 2013-04-09 2014-10-09 Diehl Bgt Defence Gmbh & Co. Kg Method for starting a guided missile
DE102018222490A1 (en) * 2018-12-20 2020-06-25 Atlas Elektronik Gmbh Device and method for starting an underwater running body from a watercraft

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE411330A (en) *
US1418795A (en) * 1916-01-12 1922-06-06 Jr John Hays Hammond Launching mechanism for torpedoes
EP0054877A1 (en) * 1980-12-23 1982-06-30 Licentia Patent-Verwaltungs-GmbH Self-contained launching device for guided missiles
FR2588241A1 (en) * 1969-11-13 1987-04-10 Aerospatiale AMPHIBIOUS ENGINE.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE411330A (en) *
US1418795A (en) * 1916-01-12 1922-06-06 Jr John Hays Hammond Launching mechanism for torpedoes
FR2588241A1 (en) * 1969-11-13 1987-04-10 Aerospatiale AMPHIBIOUS ENGINE.
EP0054877A1 (en) * 1980-12-23 1982-06-30 Licentia Patent-Verwaltungs-GmbH Self-contained launching device for guided missiles

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2407148A (en) * 1996-07-04 2005-04-20 Secr Defence Projectile launcher for attack of underwater targets
GB2407148B (en) * 1996-07-04 2005-08-03 Secr Defence Weapon system for attack of underwater targets
GB2608782A (en) * 1998-06-04 2023-01-11 Bae Systems Plc Underwater launch system
GB2608782B (en) * 1998-06-04 2024-04-10 Bae Systems Plc Underwater launch system

Also Published As

Publication number Publication date
BR9003075A (en) 1991-08-27
FR2649194B1 (en) 1994-05-13
FR2649194A1 (en) 1991-01-04
DK0406114T3 (en) 1993-10-25
DE69003190T2 (en) 1994-01-20
DE69003190D1 (en) 1993-10-14
ES2044483T3 (en) 1994-01-01
EP0406114B1 (en) 1993-09-08

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