EP3187816B9 - Launching device and projectile especially adapted for such a launching device - Google Patents

Launching device and projectile especially adapted for such a launching device Download PDF

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Publication number
EP3187816B9
EP3187816B9 EP16206899.3A EP16206899A EP3187816B9 EP 3187816 B9 EP3187816 B9 EP 3187816B9 EP 16206899 A EP16206899 A EP 16206899A EP 3187816 B9 EP3187816 B9 EP 3187816B9
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EP
European Patent Office
Prior art keywords
piston
projectile
location
tube
launcher
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.)
Active
Application number
EP16206899.3A
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German (de)
French (fr)
Other versions
EP3187816B1 (en
EP3187816A1 (en
Inventor
Yves DONIN DE ROSIERE
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Cathyor Engineering SA
Original Assignee
Cathyor Engineering SA
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Cathyor Engineering SA filed Critical Cathyor Engineering SA
Priority to RS20190145A priority Critical patent/RS58306B9/en
Priority to PL16206899T priority patent/PL3187816T3/en
Publication of EP3187816A1 publication Critical patent/EP3187816A1/en
Publication of EP3187816B1 publication Critical patent/EP3187816B1/en
Application granted granted Critical
Publication of EP3187816B9 publication Critical patent/EP3187816B9/en
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Classifications

    • 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
    • F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
    • F41F1/06—Mortars
    • 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
    • F41F7/00—Launching-apparatus for projecting missiles or projectiles otherwise than from barrels, e.g. using spigots
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B12/00—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material
    • F42B12/02—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect
    • F42B12/20—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type
    • F42B12/22—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction
    • F42B12/24—Projectiles, missiles or mines characterised by the warhead, the intended effect, or the material characterised by the warhead or the intended effect of high-explosive type with fragmentation-hull construction with grooves, recesses or other wall weakenings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B29/00—Noiseless, smokeless, or flashless missiles launched by their own explosive propellant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B30/00—Projectiles or missiles, not otherwise provided for, characterised by the ammunition class or type, e.g. by the launching apparatus or weapon used
    • F42B30/08—Ordnance projectiles or missiles, e.g. shells
    • F42B30/10—Mortar projectiles
    • 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
    • F42C19/0819—Primers or igniters for the initiation of rocket motors, i.e. pyrotechnical aspects thereof
    • 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
    • F42C19/10—Percussion caps

Definitions

  • the invention relates to armament equipment and a projectile specially adapted for such armament equipment.
  • a weapon equipment of this type corresponds to a mortar as a thrower and a grenade as a projectile operated by the company CATHYOR ENGINEERING S.A. under the name Fly-K ®.
  • This arming equipment simple and light for an operator, can contain the flame and fumes resulting from the priming of the propellant charge inside the hermetically sealed propulsion chamber.
  • These provisions make it possible to suppress the light and reduce the noise and the heat emitted during a shot.
  • the shot is thus made difficult to detect by an enemy targeted by shooting not only with his senses but also with electronic detection devices, including infrared.
  • Known armament equipment offers great efficiency because of its maneuverability, the maintenance of the operator in safety that ensures and the effect of surprise that can spare.
  • the invention aims to meet this need and proposes a weapon equipment of the aforementioned type in which the propellant load has a mass strictly greater than 2.4 g and less than 3.7 g, preferably less than 3.6. and the piston has an open recess towards the sealing member, and wherein the powder of the propellant charge is integrally placed in the recess of the piston with a loading density of between 0.9 g and 1.2 g. g per cm 3 .
  • the projectile according to the invention makes it possible to increase the range of the armament equipment in a simple way, only by increasing the propulsion load compared to the propulsion charge of the projectile operating under the name Fly-K ®.
  • the propulsion load could be increased to 3 g, 125% more than the propulsion load of the projectile operated under the name Fly-K ®, and up to 3.7 g, or 155% more than the propelling charge of the projectile operated under the name Fly-K ®.
  • the characteristics of the tube of the tail of the projectile and, in particular, the elasticity of its material make it possible to resist the energy released during the priming of the propulsion charge.
  • the increase in the propulsion load can thus be achieved at a constant loading density with respect to the propulsion charge of the projectile operated under the name Fly-K ®.
  • the recess of the piston then has an increased volume relative to the volume of the recess of the piston projectile operated under the name Fly-K ®.
  • the projectile can have a caliber of 51 mm.
  • the projectile tube may have first and second opposite ends in the vicinity of which the first and second locations are made.
  • the projectile may further comprise a body adjoining the head, the head comprising an explosive charge and the body comprising a fragment-generating sleeve, the fragment-generating sleeve being cylindrical along the projectile axis. and having an inner surface, the inner surface being provided with first and second grooves respectively extending in first and second intersecting directions.
  • the first grooves may be threads extending substantially circumferentially and the second grooves may be grooves extending substantially axially.
  • the fragment-generating sleeve may have an outside diameter of 51 mm and an internal diameter of 45 mm, and the inner surface of the splinter-forming sleeve may have threads made with a pitch of 4 mm and twenty to thirty gorges.
  • the splintering sleeve may be made of steel.
  • the launcher can be individual and portable by hand by an operator.
  • the figures 1 and 2 represent an individual armament equipment comprising a launcher 1 and one or more projectiles 25 intended to be projected remotely by the launcher 1.
  • launcher 1 is an individual mortar and hand-portable by an operator similar to the mortar operated by CATHYOR ENGINEERING SA under the name FLY-K ®.
  • the launcher 1 comprises a barrel 2 cylindrical along a barrel axis A.
  • the barrel 2 comprises a cylindrical housing 3 of circular section along the barrel axis A and adapted to receive a portion of the projectile 25.
  • the housing 3 could to be adapted to receive all the projectile 25.
  • the housing 3 extends from a bottom 4 of the barrel 2 and opens outwardly opposite the bottom 4 by a mouth 5 adapted to allow passage of the projectile 25.
  • a device retainer, in the form of one or more spring blades 6, is provided inside the housing 3 to retain the projectile 25 in the housing 3.
  • the launcher body 7 comprises in particular a launcher tube 8 connected to the bottom 4 of the shank 2 by an interface of connection 9.
  • the launcher 1 also comprises a percussion assembly 10 involved in projecting the projectile 25.
  • the percussion assembly 10 comprises a cylindrical launch rod 11 of circular section along the axis of the barrel A.
  • the launching rod 11 extends in the housing 3 of the barrel 2 from the bottom 4 to a free end 12 arranged facing the mouth 5.
  • the free end 12 has a bearing surface 13 substantially transverse to the barrel axis A, and a recess 14 formed in the bearing surface 13.
  • the percussion assembly 10 also comprises a percussion device 15 disposed in the housing 3 and in the launcher tube 8 of the launcher body 7 and coupled to a control assembly 19 in the launching tube 8 of the launcher body 7.
  • the percussion device 15 comprises a percussion tip 16 movably mounted in the launching rod 14 between a retracted position, in which the percussion tip 16 is located. in the recess 14 of the free end 12 of the launching rod 11, and a priming position, in which the percussion tip 16 protrudes with respect to the bearing surface 13 of the free end 12 of the launching rod 11.
  • the percussion tip 16 is carried by a pin 17 slidably mounted along the axis of A spindle 17 is urged towards an advanced position by one or more resilient members, such as coil springs 18, and held in a retracted position by a hook 20. of the control assembly 19 placed in the launching tube 8 of the launcher body 7.
  • the percussion tip 16 is in the priming position when the pin 17 is in the advanced position, and in the retracted position when the pin 17 is in the retracted position.
  • the movement of the hook 20 to release the pin 17 and pass the percussion tip 16 from the retracted position to the ignition position is controlled by an actuating member of the control unit 20 actuated by the operator.
  • the launcher tube 8 of the launcher body 7 has an articulated foot 21 enabling the launcher 1 to be placed on the ground, if necessary by orienting it, the inclination of the launcher 1 being given by via a clinometer 22 mounted on the launcher body 7.
  • the projectile 25 is an explosive grenade comprising an operating head 26, a body 28 and a tail 40 adjacent to a projectile axis B.
  • the projectile 25 has a caliber, that is to say a maximum external dimension, of 51 mm and a weight of between 750 g and 1000 g.
  • the operating head 26 for example of the type of the rocket operating under the name FLAME by JUNGHANS Microtec GmbH, comprises an explosive charge and is secured, for example by screwing, directly or, as shown in FIG. figure 2 , through a spacer 27, at a first end 28a of the body 28.
  • the body 28 comprises a cylindrical spark generator sleeve 29 of circular section along the projectile axis B and a first end 29a of which forms the first end 28a of the body 28.
  • the inner surface is provided with first grooves 31 in the form of threads 31 extending substantially circumferentially, and second grooves 32 in the form of grooves 32 extending substantially axially.
  • the fragment-generating sleeve 29 has an outside diameter of 51 mm and an internal diameter of 45 mm and the inner surface has threads 31 made with a pitch of 4 mm and twenty to thirty grooves 32.
  • all Another arrangement of first and second grooves extending respectively in first and second intersecting directions could be provided on the inner surface of a splinter sleeve 29 of any suitable shape.
  • the body 28 also has a connection 35 extending along the projectile axis B from a first end 35a secured, for example by screwing, to a second end 29b of the splinter sleeve 29 opposite the first end 29a.
  • the connector 35 has a central bore 36, blind on the side of the first end 35a and open on a second end 35b opposite the first end 35a and forming a second end 28b of the body 28.
  • the tail 40 is secured to the second end 28b of the body 28.
  • the tail 40 comprises a tube 41 adapted to be mounted on the launching rod 11.
  • the tube 41 of the projectile 25, made of aluminum alloy, has a first end 41a referred in the bore 36 of the fitting 35 of the body 28, and a second end 41b opposite the first end 41a.
  • the tube 41 also has a cylindrical inner surface 42 of circular section along the projectile axis B.
  • the inner surface 42 has an inner diameter Di substantially corresponding to the outer diameter of the launching rod 11 of the launcher 1.
  • the inner diameter Di is substantially constant over a stroke c along the projectile axis B between a first location E1 located in the vicinity of the first end 41a of the tube 41 and a second location E2 remote from the first location E2 and located, in the embodiment shown, at the adjacent to the second end 41b of the tube 41.
  • any other arrangement of the first location E1, the side of the operative head 26 and the second location E2 away from the first location E1 to define a suitable stroke c could be provided.
  • the inner diameter Di of the inner surface 42 is between 21.5 mm and 22.5 mm, in particular 22.05 mm.
  • the tube 41 has a length, measured along the projectile axis B, of between 140 mm and 160 mm, in particular 150 mm, so that the stroke c between the first E1 and second E2 locations can be between 120 mm and 110 mm, in particular of 115 mm.
  • the tube 41a moreover, has a thickness e in the vicinity of the first location E1 of between 4.6 mm and 5 mm, in particular 4.8 mm.
  • a empennage 43 is provided on an outer surface of the tube 41 to ensure stability during a shot.
  • the first end 41a of the tube 41 is sealed by a closure member.
  • the closure member is in the form of a plug 44 disposed in a bottom 37 of the bore 36 of the fitting 35 of the body 28 and in contact with the tube at its first end 41a.
  • a stop element is secured to the second end 41b of the tube 41.
  • the stop element is in the form of a cylindrical retaining ring 45 along the projectile axis B.
  • the ring 45 comprises a first portion 46 screwed on the second end 41b of the tube 41 and a second portion 47 extending the tube 41 beyond its second end 41b along the projectile axis B.
  • the second portion 47 of the ring retainer 45 has a frustoconical inner surface 48 of circular section converging towards the projectile axis B away from the second end 41b of the tube 41.
  • the second portion 47 of the retaining ring 45 thus internally defines a restriction 49 having a diameter less than the inner diameter Di of the inner surface 42 of the tube 41 along the stroke c.
  • An insert 50 may be removably mounted on the second portion 47 of the retaining ring 45 to close access to the interior of the tube 41 prior to use of the projectile 25.
  • the projectile 25 also comprises a piston 60 mounted in the tube 41 and positioned at the first location E1 of the race c formed on the inner surface 42 of the tube 42, in the vicinity of the first end 41a of the tube 41.
  • the piston 60 comprises a transverse wall 61 with respect to the projectile axis B and adapted to rest on the bearing surface 13 of the free end 12 of the launch rod 11. It also comprises a skirt 62 which extends perpendicularly to an edge peripheral of the transverse wall 61 to the stopper 44 forming closure element.
  • the skirt 62 has a cylindrical outer surface of circular section, placed in hermetic contact with the inner surface 42 of the tube 41 and adapted to slide along the inner surface 42 of the tube 41 along the projectile axis B to the second location E2.
  • the skirt 62 also has a cylindrical inner surface of circular section delimiting, with an upper surface of the transverse wall 61, a recess 63 open towards the cap 44.
  • the recess 63 may in particular have a volume of between 2 cm 3 and 4, 5 cm 3 , in particular 2.5 cm 3 .
  • the piston 60 further comprises a primer 64 arranged substantially centrally in the transverse wall 61 so as to be activated by the percussion tip 14 in the priming position when the piston 60 rests on the bearing surface 13 of the free end 12 of the launching rod 11.
  • the piston 60 delimits, with the tube 41 and the plug 44, a hermetically closed propulsion chamber 65 whose volume increases as the piston 60 is displaced from the first location E1 at the second location E2.
  • a propellant charge 70 is placed in the propulsion chamber 65 when the piston 60 is at the first location E1.
  • the propulsion charge 70 is adapted to be activated by the primer 64 of the piston 60 to move the piston 60 between the first E1 and second E2 locations.
  • the propellant charge 70 comprises between 2.4 g and 3.7 g, or even between 2.4 g and 3.6 g of a powder having a heat of combustion of between 3500 J / g and 4000 J / g.
  • the powder is integrally placed in the recess 63 of the piston 60 with a loading density of between 0.9 g and 1.2 g per cm 3 , in particular of 0.96 g per cm 3 .
  • the powder may especially be the same powder as that used in the grenade operated by the company CATHYOR ENGINEERING SA under the name Fly-K®, namely a spherical P3T powder developed by the company PB CLERMONT.
  • the arming equipment according to the invention is not limited to an explosive grenade of the type previously described as a projectile.
  • the figure 3 represents a smoke grenade 25 'whose operating head 26' and the body 28 'are adapted to produce a cloud of smoke.
  • the figure 4 represents a 25 "exercise grenade whose 26" operating head and 28 "body are adapted to locate the trajectory and mark the impact of the 25" grenade on the ground.
  • the tail 40 of the projectiles 25 ', 25 is, for its part, identical to that of the explosive grenade 25 previously described so as to cooperate with the launching rod 11 and the percussion device 15 of the launcher 1.
  • the projectile for example the explosive grenade of the figure 2
  • the projectile 25 is introduced by the tail 40 into the housing 3 of the barrel 2 through the mouth 5.
  • the tube 41 of the tail 40 slides on the throwing rod 11 until the transverse wall 61 of the piston 60 bears on the bearing surface 13 of the free end 12 of the throwing rod 11.
  • the spring blades 6 of the retainer deform and are returned to a rest position in which they hold the projectile 25 in the barrel 2 at the tail 40, above of the empennage 43.
  • the percussion tip 16 is in the retracted position.
  • the operator actuates the control assembly 19 which passes the percussion tip 16 from the retracted position to the priming position.
  • the percussion tip 16 activates the primer 64 of the piston 60 which, at its turn, activates the propelling charge 70.
  • the projectile 25 then moves relative to the piston 60 bearing on the free end 12 of the launching rod 11 so that the piston 60 slides from the first location E1 to the second E2 location where it is retained by the restriction 49 of the retaining ring 45.
  • the propulsion chamber 65 remains hermetically closed, thus containing the flame and fumes to suppress the light and reduce the noise and heat emitted during firing.
  • the projectile 25 then leaves the drum 2 of the launcher 1 to be projected at a distance from the launcher 1 and in particular at a distance of up to 1000 m.

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  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Toys (AREA)

Description

L'invention se rapporte à un équipement d'armement et à un projectile spécialement adapté pour un tel équipement d'armement.The invention relates to armament equipment and a projectile specially adapted for such armament equipment.

En particulier, l'invention se rapporte à un équipement d'armement du type comprenant un lanceur et au moins un projectile destiné à être projeté à distance par le lanceur,
dans lequel le lanceur comprend :

  • un fût cylindrique selon un axe de fût, le fût comportant un logement adapté pour recevoir au moins une partie du projectile, et une bouche adaptée pour permettre un passage du projectile,
  • une tige de lancement s'étendant dans le logement du fût selon l'axe de fût et ayant une extrémité libre en regard de la bouche du fût, l'extrémité libre présentant une surface d'appui et un évidement ménagé dans la surface d'appui,
  • un dispositif de percussion comportant un embout de percussion monté déplaçable dans la tige de lancement entre une position escamotée, dans laquelle l'embout de percussion est disposé dans l'évidement, et une position d'amorçage, dans laquelle l'embout de percussion fait saillie par rapport à la surface d'appui,
dans lequel le projectile a un poids compris entre 750 g et 1000 g et s'étend selon un axe de projectile, le projectile comprenant une tête opérante et une queue qui prolonge la tête opérante selon l'axe de projectile, la queue comportant :
  • un tube adapté pour être monté sur la tige de lancement, le tube étant réalisé en alliage d'aluminium et présentant une surface intérieure cylindrique de section circulaire selon l'axe de projectile, la surface intérieure ayant un diamètre intérieur constant sur une course selon l'axe de projectile entre un premier emplacement situé du côté de la tête opérante et un deuxième emplacement distant du premier emplacement, le diamètre intérieur étant compris entre 21,5 mm et 22,5 mm, en particulier de 22,05 mm, la course étant comprise entre 110 mm et 120 mm, en particulier de 115 mm, le tube ayant une épaisseur au voisinage du premier emplacement comprise entre 4,6 mm et 5 mm, en particulier de 4,8 mm,
  • un élément d'obturation fermant le tube de manière étanche au voisinage du premier emplacement,
  • un piston placé dans le tube en contact hermétique avec la surface intérieure dudit tube et adapté pour reposer sur la surface d'appui de l'extrémité libre de la tige de lancement, le piston comportant une amorce agencée pour être activée par l'embout de percussion en position d'amorçage lorsque le piston repose sur la surface d'appui de l'extrémité libre de la tige de lancement, le piston délimitant avec le tube et l'élément d'obturation une chambre de propulsion hermétiquement fermée, le piston étant placé au premier emplacement et déplaçable vers le deuxième emplacement,
  • une charge de propulsion placée dans la chambre de propulsion lorsque le piston est au premier emplacement et activable par l'amorce du piston pour déplacer le piston en appui sur la surface d'appui de l'extrémité libre de la tige de lancement depuis le premier emplacement vers le deuxième emplacement, la charge de propulsion comprenant une poudre ayant une chaleur de combustion comprise entre 3500 J/g et 4000 J/g,
  • un élément d'arrêt adapté pour retenir le piston dans le tube au deuxième emplacement.
In particular, the invention relates to armament equipment of the type comprising a launcher and at least one projectile intended to be thrown remotely by the launcher,
wherein the launcher comprises:
  • a cylindrical barrel along a shaft axis, the barrel having a housing adapted to receive at least a portion of the projectile, and a mouth adapted to allow passage of the projectile,
  • a throwing rod extending into the housing of the barrel along the barrel axis and having a free end facing the mouth of the barrel, the free end having a bearing surface and a recess formed in the surface of the barrel; support,
  • a percussion device comprising a percussion tip movably mounted in the launching rod between a retracted position, in which the percussion tip is disposed in the recess, and a priming position, in which the percussion tip makes protrusion with respect to the bearing surface,
wherein the projectile has a weight of between 750 g and 1000 g and extends along a projectile axis, the projectile comprising an operable head and a tail which extends the operative head along the projectile axis, the tail comprising:
  • a tube adapted to be mounted on the launching rod, the tube being made of aluminum alloy and having a cylindrical inner surface of circular section along the projectile axis, the inner surface having a constant inner diameter on a stroke according to the projectile axis between a first location on the operating head side and a second location remote from the first location, the inside diameter being between 21.5 mm and 22.5 mm, in particular 22.05 mm, the running being between 110 mm and 120 mm, in particular 115 mm, the tube having a thickness in the vicinity of the first location of between 4.6 mm and 5 mm, in particular of 4.8 mm,
  • a sealing member sealing the tube in the vicinity of the first location,
  • a piston placed in the tube in hermetic contact with the inner surface of said tube and adapted to rest on the bearing surface of the free end of the throwing rod, the piston comprising a primer arranged to be activated by the tip of percussion in the priming position when the piston rests on the bearing surface of the free end of the throwing rod, the piston delimiting with the tube and the sealing member a propellant chamber hermetically closed, the piston being placed at the first location and movable to the second location,
  • a propellant charge placed in the propulsion chamber when the piston is at the first location and activatable by the primer of the piston to move the piston bearing on the bearing surface of the free end of the launching rod from the first location to the second location, the propellant charge comprising a powder having a heat of combustion of between 3500 J / g and 4000 J / g,
  • a stop member adapted to retain the piston in the tube at the second location.

Un équipement d'armement de ce type correspond à un mortier comme lanceur et une grenade comme projectile exploités par la société CATHYOR ENGINEERING S.A. sous la dénomination Fly-K ®.A weapon equipment of this type corresponds to a mortar as a thrower and a grenade as a projectile operated by the company CATHYOR ENGINEERING S.A. under the name Fly-K ®.

Cet équipement d'armement, simple et léger pour un opérateur, permet de contenir la flamme et les fumées résultant de l'amorçage de la charge de propulsion à l'intérieur de la chambre de propulsion hermétiquement fermée. Ces dispositions permettent de supprimer la lumière et de réduire le bruit et la chaleur émis lors d'un tir. Le tir est ainsi rendu difficilement détectable par un ennemi visé par le tir non seulement avec ses seuls sens mais également avec des dispositifs de détection électroniques, notamment à infrarouge. L'équipement d'armement connu offre une grande efficacité du fait de sa maniabilité, du maintien de l'opérateur en sécurité qu'il assure et de l'effet de surprise qu'il peut ménager.This arming equipment, simple and light for an operator, can contain the flame and fumes resulting from the priming of the propellant charge inside the hermetically sealed propulsion chamber. These provisions make it possible to suppress the light and reduce the noise and the heat emitted during a shot. The shot is thus made difficult to detect by an enemy targeted by shooting not only with his senses but also with electronic detection devices, including infrared. Known armament equipment offers great efficiency because of its maneuverability, the maintenance of the operator in safety that ensures and the effect of surprise that can spare.

L'équipement d'armement connu est toutefois limité à une portée maximale de 650 m avec un angle d'inclinaison du lanceur de 45°. Il existe un besoin pour augmenter cette portée, notamment jusqu'à 1000 m, tout en préservant l'efficacité de l'équipement d'armement.Known arming equipment, however, is limited to a maximum range of 650 m with a pitch angle of 45 ° launcher. There is a need to increase this range, especially up to 1000 m, while preserving the efficiency of the arming equipment.

L'invention vise à répondre à ce besoin et propose un équipement d'armement du type précité dans lequel la charge de propulsion a une masse strictement supérieure à 2,4 g et inférieure à 3,7 g, de préférence inférieure à 3,6 g et le piston présente un évidement ouvert vers l'élément d'obturation, et dans lequel la poudre de la charge de propulsion est intégralement placée dans l'évidement du piston avec une densité de chargement comprise entre 0,9 g et 1,2 g par cm3.The invention aims to meet this need and proposes a weapon equipment of the aforementioned type in which the propellant load has a mass strictly greater than 2.4 g and less than 3.7 g, preferably less than 3.6. and the piston has an open recess towards the sealing member, and wherein the powder of the propellant charge is integrally placed in the recess of the piston with a loading density of between 0.9 g and 1.2 g. g per cm 3 .

Ainsi, le projectile selon l'invention permet d'augmenter la portée de l'équipement d'armement de manière simple, uniquement en augmentant la charge de propulsion par rapport à la charge de propulsion du projectile exploité sous la dénomination Fly-K ®.Thus, the projectile according to the invention makes it possible to increase the range of the armament equipment in a simple way, only by increasing the propulsion load compared to the propulsion charge of the projectile operating under the name Fly-K ®.

Il est communément admis dans le domaine de l'armement, qu'une augmentation de la charge de propulsion s'accompagne généralement d'une modification du projectile et/ou de la poudre de la charge de propulsion, notamment pour choisir une poudre moins vive, c'est-à-dire présentant une chaleur de combustion inférieure. Ainsi, le Manuel de Rechargement N°6 de René Malfatti, publié en 2004 aux éditions Crépin Leblong, pages 43-45 , stipule que « pour un même calibre, la vivacité de la poudre doit diminuer lorsque la capacité de la douille augmente ». De plus, la masse du projectile selon l'invention est supérieure à celle du projectile exploité sous la dénomination Fly-K ®. Il est également communément admis dans le domaine de l'armement qu'une augmentation de la masse d'un projectile implique une diminution de la masse de la charge de propulsion et/ou une réduction de sa vivacité. Ainsi, le Manuel de rechargement N°6 précité stipule, page 65, que « si, pour un même type de poudre et une même charge, on utilise u nprojectile plus lourd, la pression s'élève ; il est alors nécessaire : soit de réduire la charge, soit de passer à un indice de vivacité inférieur ».It is generally accepted in the field of armament that an increase in the propulsion load is generally accompanied by a modification of the projectile and / or the powder of the propulsion charge, in particular to choose a less vivid powder that is, having a lower heat of combustion. So, the Reloading Manual N ° 6 of René Malfatti, published in 2004 by Crépin Leblong, pages 43-45 , stipulates that "for the same caliber, the brightness of the powder must decrease when the capacity of the sleeve increases". In addition, the mass of the projectile according to the invention is greater than that of the projectile under the name Fly-K ®. It is also generally accepted in the field of armament that an increase in the mass of a projectile implies a decrease in the mass of the propulsion charge and / or a reduction in its liveliness. Thus, the reloading manual No. 6 mentioned above, page 65, that "if, for the same type of powder and the same load, a heavier projectile is used, the pressure rises; it is then necessary: either to reduce the load, or to pass to a lower index of vivacity ".

Les inventeurs sont donc allés à l'encontre de ces préjugés techniques et ont constaté qu'une augmentation de la charge de propulsion permettait à elle-seule d'augmenter la portée de l'équipement d'armement sans endommager le lanceur ni risquer de porter atteinte à l'intégrité de l'opérateur. En particulier, la charge de propulsion a pu être augmentée pour être de 3 g, soit 125 % de plus que la charge de propulsion du projectile exploité sous la dénomination Fly-K ®, et jusqu'à 3,7 g, soit 155 % de plus que la charge de propulsion du projectile exploité sous la dénomination Fly-K ®.The inventors went against these technical prejudices and found that an increase in the propulsion load alone allowed the range of the equipment to be increased without damaging the launcher or risking damage to the integrity of the operator. In particular, the propulsion load could be increased to 3 g, 125% more than the propulsion load of the projectile operated under the name Fly-K ®, and up to 3.7 g, or 155% more than the propelling charge of the projectile operated under the name Fly-K ®.

Sans être lié par une quelconque théorie, les caractéristiques du tube de la queue du projectile et, en particulier, l'élasticité de son matériau permettent de résister à l'énergie libérée lors de l'amorçage de la charge de propulsion.Without being bound by any theory, the characteristics of the tube of the tail of the projectile and, in particular, the elasticity of its material make it possible to resist the energy released during the priming of the propulsion charge.

L'augmentation de la charge de propulsion peut ainsi être réalisée à densité de chargement constante par rapport à la charge de propulsion du projectile exploité sous la dénomination Fly-K ®. L'évidement du piston présente alors un volume augmenté par rapport au volume de l'évidement du piston du projectile exploité sous la dénomination Fly-K ®.The increase in the propulsion load can thus be achieved at a constant loading density with respect to the propulsion charge of the projectile operated under the name Fly-K ®. The recess of the piston then has an increased volume relative to the volume of the recess of the piston projectile operated under the name Fly-K ®.

Le projectile peut avoir un calibre de 51 mm.The projectile can have a caliber of 51 mm.

Le tube du projectile peut présenter des première et deuxième extrémités opposées au voisinage desquelles les premier et deuxième emplacements sont réalisés.The projectile tube may have first and second opposite ends in the vicinity of which the first and second locations are made.

De façon complémentaire ou alternative, le projectile peut comprendre en outre un corps attenant à la tête, la tête comportant une charge explosive et le corps comportant un manchon générateur d'éclats, le manchon générateur d'éclats étant cylindrique selon l'axe de projectile et présentant une surface intérieure, la surface intérieure étant pourvue de premières et deuxièmes rainures s'étendant respectivement selon des première et deuxième directions sécantes.In a complementary or alternative manner, the projectile may further comprise a body adjoining the head, the head comprising an explosive charge and the body comprising a fragment-generating sleeve, the fragment-generating sleeve being cylindrical along the projectile axis. and having an inner surface, the inner surface being provided with first and second grooves respectively extending in first and second intersecting directions.

Les premières rainures peuvent être des filets s'étendant sensiblement circonférentiellement et les deuxièmes rainures peuvent être des gorges s'étendant sensiblement axialement.The first grooves may be threads extending substantially circumferentially and the second grooves may be grooves extending substantially axially.

Lorsque le projectile a un calibre de 51 mm, le manchon générateur d'éclats peut avoir un diamètre extérieur de 51 mm et un diamètre intérieur de 45 mm, et la surface intérieure du manchon générateur d'éclats peut présenter des filets réalisés avec un pas de 4 mm et vingt à trente gorges.When the projectile has a caliber of 51 mm, the fragment-generating sleeve may have an outside diameter of 51 mm and an internal diameter of 45 mm, and the inner surface of the splinter-forming sleeve may have threads made with a pitch of 4 mm and twenty to thirty gorges.

Le manchon générateur d'éclats peut être réalisé en acier.The splintering sleeve may be made of steel.

Le lanceur peut être individuel et portable à la main par un opérateur.The launcher can be individual and portable by hand by an operator.

Selon un deuxième aspect, l'invention concerne un projectile spécialement adapté pour un équipement d'armement tel que défini précédemment, le projectile ayant un poids compris entre 750 g et 1000 g et s'étendant selon un axe de projectile, le projectile comprenant une tête opérante et une queue qui prolonge la tête opérante selon l'axe de projectile, la queue comportant :

  • un tube adapté pour être monté sur une tige de lancement d'un lanceur, le tube étant réalisé en alliage d'aluminium et présentant une surface intérieure cylindrique de section circulaire selon l'axe de projectile, la surface intérieure ayant un diamètre intérieur constant sur une course selon l'axe de projectile entre un premier emplacement situé du côté de la tête opérante et un deuxième emplacement distant du premier emplacement, le diamètre intérieur étant compris entre 21,5 mm et 22,5 mm, en particulier de 22,05 mm, la course étant comprise entre 110 mm et 120 mm, en particulier de 115 mm, le tube ayant une épaisseur au voisinage du premier emplacement comprise entre 4,6 mm et 5 mm, en particulier de 4,8 mm,
  • un élément d'obturation fermant le tube de manière étanche au voisinage du premier emplacement,
  • un piston placé dans le tube en contact hermétique avec la surface intérieure dudit tube et adapté pour reposer sur une surface d'appui d'une extrémité libre de la tige de lancement du lanceur, le piston comportant une amorce agencée pour être activée par un embout de percussion en position d'amorçage d'un dispositif de percussion du lanceur lorsque le piston repose sur la surface d'appui de l'extrémité libre de la tige de lancement du lanceur, le piston délimitant avec le tube et l'élément d'obturation une chambre de propulsion hermétiquement fermée, le piston étant placé au premier emplacement et déplaçable vers le deuxième emplacement,
  • une charge de propulsion placée dans la chambre de propulsion lorsque le piston est au premier emplacement et activable par l'amorce du piston pour déplacer le piston en appui sur la surface d'appui de l'extrémité libre de la tige de lancement du lanceur depuis le premier emplacement vers le deuxième emplacement, la charge de propulsion comprenant une poudre ayant une chaleur de combustion comprise entre 3500 J/g et 4000 J/g,
  • un élément d'arrêt adapté pour retenir le piston dans le tube au deuxième emplacement,
dans lequel la charge de propulsion a une masse strictement supérieure à 2,4 g et inférieure à 3,7 g, de préférence inférieure à 3,6 g et le piston présente un évidement ouvert vers l'élément d'obturation, et dans lequel la poudre de la charge de propulsion est intégralement placée dans l'évidement du piston avec une densité de chargement comprise entre 0,9 g et 1,2 g par cm3.According to a second aspect, the invention relates to a projectile specially adapted for arming equipment as defined above, the projectile having a weight of between 750 g and 1000 g and extending along a projectile axis, the projectile comprising a an operable head and a tail that extends the operative head along the projectile axis, the tail comprising:
  • a tube adapted to be mounted on a launching rod of a launcher, the tube being made of aluminum alloy and having a cylindrical inner surface of circular section along the projectile axis, the inner surface having a constant inner diameter on a stroke along the projectile axis between a first location on the operating head side and a second location remote from the first location, the inside diameter being between 21.5 mm and 22.5 mm, in particular 22.05 mm, the stroke being between 110 mm and 120 mm, in particular of 115 mm, the tube having a thickness in the vicinity of the first location of between 4.6 mm and 5 mm, in particular of 4.8 mm,
  • a sealing member sealing the tube in the vicinity of the first location,
  • a piston placed in the tube in hermetic contact with the inner surface of said tube and adapted to rest on a bearing surface of a free end of the launching rod of the launcher, the piston comprising a primer arranged to be activated by a nozzle of percussion in the priming position of a percussion device of the launcher when the piston rests on the bearing surface of the free end of the launching rod of the launcher, the piston delimiting with the tube and the element of closing a hermetically closed propulsion chamber, the piston being placed in the first location and movable towards the second location,
  • a propellant charge placed in the propulsion chamber when the piston is at the first location and activatable by the primer of the piston to move the piston resting on the bearing surface of the free end of the launching rod of the launcher since the first location to the second location, the propellant charge comprising a powder having a heat of combustion of between 3500 J / g and 4000 J / g,
  • a stop member adapted to retain the piston in the tube at the second location,
wherein the propellant charge has a mass greater than 2.4 g and less than 3.7 g, preferably less than 3.6 g and the piston has an open recess towards the closure member, and wherein the powder of the propellant charge is integrally placed in the recess of the piston with a loading density of between 0.9 g and 1.2 g per cm3.

D'autres objets et avantages de l'invention apparaîtront à la lecture de la description qui suit d'un mode de réalisation particulier de l'invention donné à titre d'exemple non limitatif, la description étant faite en référence aux dessins annexés dans lesquels :

  • la figure 1 est une représentation en coupe longitudinale d'un lanceur d'un équipement d'armement selon un mode de réalisation de l'invention,
  • la figure 2 est une représentation en coupe longitudinale d'un projectile de l'équipement d'armement destiné à être projeté à distance par le lanceur de la figure 1,
  • les figures 3 et 4 sont des représentations en coupe longitudinale de variantes du projectile de l'équipement d'armement destiné à être projeté à distance par le lanceur de la figure 1,
  • les figures 5 et 6 sont des représentations en coupe longitudinale du lanceur de la figure 1 et du projectile de la figure 2, illustrant respectivement le projectile mis en place dans le lanceur préalablement à un tir et le projectile en train de quitter le lanceur au cours du tir.
Other objects and advantages of the invention will appear on reading the following description of a particular embodiment of the invention given by way of non-limiting example, the description being made with reference to the appended drawings in which :
  • the figure 1 is a longitudinal sectional representation of a launcher of a weapon equipment according to one embodiment of the invention,
  • the figure 2 is a representation in longitudinal section of a projectile of the armament equipment intended to be projected remotely by the launcher of the figure 1 ,
  • the figures 3 and 4 are representations in longitudinal section of the projectile variants of the weapon equipment intended to be projected remotely by the launcher of the figure 1 ,
  • the figures 5 and 6 are representations in longitudinal section of the launcher of the figure 1 and the projectile of the figure 2 , respectively illustrating the projectile placed in the launcher prior to a shot and the projectile leaving the launcher during shooting.

Sur les figures, les mêmes références désignent des éléments identiques ou analogues.In the figures, the same references designate identical or similar elements.

Les figures 1 et 2 représentent un équipement d'armement individuel comprenant un lanceur 1 et un ou plusieurs projectiles 25 destinés à être projetés à distance par le lanceur 1.The figures 1 and 2 represent an individual armament equipment comprising a launcher 1 and one or more projectiles 25 intended to be projected remotely by the launcher 1.

Sur la figure 1, le lanceur 1 est un mortier individuel et portable à la main par un opérateur analogue au mortier exploité par la société CATHYOR ENGINEERING S.A. sous la dénomination FLY-K ®.On the figure 1 , launcher 1 is an individual mortar and hand-portable by an operator similar to the mortar operated by CATHYOR ENGINEERING SA under the name FLY-K ®.

Le lanceur 1 comprend un fût 2 cylindrique selon un axe de fût A. Le fût 2 comporte un logement 3 cylindrique de section circulaire selon l'axe de fût A et adapté pour recevoir une partie du projectile 25. En variante, le logement 3 pourrait être adapté pour recevoir tout le projectile 25. Le logement 3 s'étend depuis un fond 4 du fût 2 et débouche vers l'extérieur à l'opposé du fond 4 par une bouche 5 adaptée pour permettre un passage du projectile 25. Un dispositif de retenue, sous la forme d'une ou plusieurs lames ressort 6, est prévu à l'intérieur du logement 3 pour retenir le projectile 25 dans le logement 3.The launcher 1 comprises a barrel 2 cylindrical along a barrel axis A. The barrel 2 comprises a cylindrical housing 3 of circular section along the barrel axis A and adapted to receive a portion of the projectile 25. Alternatively, the housing 3 could to be adapted to receive all the projectile 25. The housing 3 extends from a bottom 4 of the barrel 2 and opens outwardly opposite the bottom 4 by a mouth 5 adapted to allow passage of the projectile 25. A device retainer, in the form of one or more spring blades 6, is provided inside the housing 3 to retain the projectile 25 in the housing 3.

Un corps de lanceur 7, creux, prolonge le fût 2 du côté de son fond 4, selon l'axe de fût A. Le corps de lanceur 7 comprend notamment un tube de lanceur 8 connecté au fond 4 du fût 2 par une interface de connexion 9.A launcher body 7, hollow, extends the shank 2 on its side of its bottom 4, along the axis of the shank A. The launcher body 7 comprises in particular a launcher tube 8 connected to the bottom 4 of the shank 2 by an interface of connection 9.

Le lanceur 1 comprend également un ensemble de percussion 10 impliqué dans la projection du projectile 25. L'ensemble de percussion 10 comporte une tige de lancement 11 cylindrique de section circulaire selon l'axe de fût A. La tige de lancement 11 s'étend dans le logement 3 du fût 2 depuis le fond 4 jusqu'à une extrémité libre 12 agencée en regard de la bouche 5. L'extrémité libre 12 présente une surface d'appui 13 sensiblement transversale par rapport à l'axe de fût A, et un évidement 14 ménagé dans la surface d'appui 13. L'ensemble de percussion 10 comporte également un dispositif de percussion 15 disposé dans le logement 3 et dans le tube de lanceur 8 du corps de lanceur 7 et couplé à un ensemble de commande 19 disposé dans le tube de lanceur 8 du corps de lanceur 7. Le dispositif de percussion 15 comporte un embout de percussion 16 monté déplaçable dans la tige de lancement 14 entre une position escamotée, dans laquelle l'embout de percussion 16 se trouve dans l'évidement 14 de l'extrémité libre 12 de la tige de lancement 11, et une position d'amorçage, dans laquelle l'embout de percussion 16 fait saillie par rapport à la surface d'appui 13 de l'extrémité libre 12 de la tige de lancement 11. En particulier, l'embout de percussion 16 est porté par une broche 17 montée coulissante selon l'axe de fût A à l'intérieur d'un logement de la tige de lancement 11. La broche 17 est sollicitée vers une position avancée par un ou plusieurs organes élastiques, tels que des ressorts hélicoïdaux 18, et retenue dans une position reculée par un crochet 20 de l'ensemble de commande 19 placé dans le tube de lanceur 8 du corps de lanceur 7. L'embout de percussion 16 est dans la position d'amorçage lorsque la broche 17 est dans la position avancée, et dans la position escamotée lorsque la broche 17 est dans la position reculée. Le déplacement du crochet 20 pour libérer la broche 17 et faire passer l'embout de percussion 16 de la position escamotée à la position d'amorçage est contrôlé par un organe d'actionnement de l'ensemble de commande 20 actionnable par l'opérateur.The launcher 1 also comprises a percussion assembly 10 involved in projecting the projectile 25. The percussion assembly 10 comprises a cylindrical launch rod 11 of circular section along the axis of the barrel A. The launching rod 11 extends in the housing 3 of the barrel 2 from the bottom 4 to a free end 12 arranged facing the mouth 5. The free end 12 has a bearing surface 13 substantially transverse to the barrel axis A, and a recess 14 formed in the bearing surface 13. The percussion assembly 10 also comprises a percussion device 15 disposed in the housing 3 and in the launcher tube 8 of the launcher body 7 and coupled to a control assembly 19 in the launching tube 8 of the launcher body 7. The percussion device 15 comprises a percussion tip 16 movably mounted in the launching rod 14 between a retracted position, in which the percussion tip 16 is located. in the recess 14 of the free end 12 of the launching rod 11, and a priming position, in which the percussion tip 16 protrudes with respect to the bearing surface 13 of the free end 12 of the launching rod 11. In particular, the percussion tip 16 is carried by a pin 17 slidably mounted along the axis of A spindle 17 is urged towards an advanced position by one or more resilient members, such as coil springs 18, and held in a retracted position by a hook 20. of the control assembly 19 placed in the launching tube 8 of the launcher body 7. The percussion tip 16 is in the priming position when the pin 17 is in the advanced position, and in the retracted position when the pin 17 is in the retracted position. The movement of the hook 20 to release the pin 17 and pass the percussion tip 16 from the retracted position to the ignition position is controlled by an actuating member of the control unit 20 actuated by the operator.

A l'opposé du fût 2, le tube de lanceur 8 du corps de lanceur 7 a un pied 21 articulé permettant de poser le lanceur 1 sur le sol, le cas échéant en l'orientant, l'inclinaison du lanceur 1 étant donnée par l'intermédiaire d'un clinomètre 22 monté sur le corps de lanceur 7.Opposite the barrel 2, the launcher tube 8 of the launcher body 7 has an articulated foot 21 enabling the launcher 1 to be placed on the ground, if necessary by orienting it, the inclination of the launcher 1 being given by via a clinometer 22 mounted on the launcher body 7.

Sur la figure 2, le projectile 25 est une grenade explosive comprenant une tête opérante 26, un corps 28 et une queue 40 attenants selon un axe de projectile B. Le projectile 25 a un calibre, c'est-à-dire une dimension extérieure maximale, de 51 mm et un poids compris entre 750 g et 1000 g.On the figure 2 , the projectile 25 is an explosive grenade comprising an operating head 26, a body 28 and a tail 40 adjacent to a projectile axis B. The projectile 25 has a caliber, that is to say a maximum external dimension, of 51 mm and a weight of between 750 g and 1000 g.

La tête opérante 26, par exemple du type de la fusée exploitée sous la dénomination FLAME par la société JUNGHANS Microtec GmbH, comporte une charge explosive et est solidarisée, par exemple par vissage, directement ou, comme représenté sur la figure 2, par l'intermédiaire d'une entretoise 27, à une première extrémité 28a du corps 28.The operating head 26, for example of the type of the rocket operating under the name FLAME by JUNGHANS Microtec GmbH, comprises an explosive charge and is secured, for example by screwing, directly or, as shown in FIG. figure 2 , through a spacer 27, at a first end 28a of the body 28.

Le corps 28 comporte un manchon générateur d'éclats 29 cylindrique de section circulaire selon l'axe de projectile B et dont une première extrémité 29a forme la première extrémité 28a du corps 28. Le manchon générateur d'éclats 29, réalisé en acier, présente une surface intérieure de section circulaire. La surface intérieure est pourvue de premières rainures sous forme de filets 31 s'étendant sensiblement circonférentiellement, et de deuxièmes rainures sous forme de gorges 32 s'étendant sensiblement axialement. En particulier, le manchon générateur d'éclats 29 a un diamètre extérieur de 51 mm et un diamètre intérieur de 45 mm et la surface intérieure présente des filets 31 réalisés avec un pas de 4 mm et vingt à trente gorges 32. En variante, tout autre agencement de premières et deuxièmes rainures s'étendant respectivement selon des première et deuxième directions sécantes pourrait être prévu sur la surface intérieure d'un manchon générateur d'éclats 29 de toute forme appropriée.The body 28 comprises a cylindrical spark generator sleeve 29 of circular section along the projectile axis B and a first end 29a of which forms the first end 28a of the body 28. The splinter-forming sleeve 29, made of steel, presents an inner surface of circular section. The inner surface is provided with first grooves 31 in the form of threads 31 extending substantially circumferentially, and second grooves 32 in the form of grooves 32 extending substantially axially. In particular, the fragment-generating sleeve 29 has an outside diameter of 51 mm and an internal diameter of 45 mm and the inner surface has threads 31 made with a pitch of 4 mm and twenty to thirty grooves 32. In a variant, all Another arrangement of first and second grooves extending respectively in first and second intersecting directions could be provided on the inner surface of a splinter sleeve 29 of any suitable shape.

Le corps 28 comporte également un raccord 35 s'étendant selon l'axe de projectile B depuis une première extrémité 35a solidarisée, par exemple par vissage, à une deuxième extrémité 29b du manchon générateur d'éclats 29 opposée à la première extrémité 29a. Le raccord 35 présente un alésage 36 central, borgne du côté de la première extrémité 35a et ouvert sur une deuxième extrémité 35b opposée à la première extrémité 35a et formant une deuxième extrémité 28b du corps 28.The body 28 also has a connection 35 extending along the projectile axis B from a first end 35a secured, for example by screwing, to a second end 29b of the splinter sleeve 29 opposite the first end 29a. The connector 35 has a central bore 36, blind on the side of the first end 35a and open on a second end 35b opposite the first end 35a and forming a second end 28b of the body 28.

La queue 40 est solidarisée à la deuxième extrémité 28b du corps 28. En particulier, la queue 40 comporte un tube 41 adapté pour être monté sur la tige de lancement 11. Le tube 41 du projectile 25, réalisé en alliage d'aluminium, présente une première extrémité 41a visée dans l'alésage 36 du raccord 35 du corps 28, et une deuxième extrémité 41b opposée à la première extrémité 41a. Le tube 41 présente également une surface intérieure 42 cylindrique de section circulaire selon l'axe de projectile B. La surface intérieure 42 a un diamètre intérieur Di correspondant sensiblement au diamètre extérieur de la tige de lancement 11 du lanceur 1. Le diamètre intérieur Di est sensiblement constant sur une course c selon l'axe de projectile B entre un premier emplacement E1 situé au voisinage de la première extrémité 41a du tube 41 et un deuxième emplacement E2 distant du premier emplacement E2 et situé, dans le mode de réalisation représenté, au voisinage de la deuxième extrémité 41b du tube 41. En variante, tout autre agencement du premier emplacement E1, du côté de la tête opérante 26 et du deuxième emplacement E2 à distance du premier emplacement E1 pour définir une course c appropriée pourrait être prévu. A titre d'exemple, le diamètre intérieur Di de la surface intérieure 42 est compris entre 21,5 mm et 22,5 mm, en particulier de 22,05 mm. Le tube 41 présente une longueur, mesurée selon l'axe de projectile B, comprise entre 140 mm et 160 mm, en particulier de 150 mm, de telle sorte que la course c entre les premier E1 et deuxième E2 emplacements puisse être comprise entre 120 mm et 110 mm, en particulier de 115 mm. Le tube 41a, par ailleurs, une épaisseur e au voisinage du premier emplacement E1 comprise entre 4,6 mm et 5 mm, en particulier de 4,8 mm. Au voisinage de la deuxième extrémité 41b, un empennage 43 est prévu sur une surface extérieure du tube 41 pour en assurer la stabilité lors d'un tir.The tail 40 is secured to the second end 28b of the body 28. In particular, the tail 40 comprises a tube 41 adapted to be mounted on the launching rod 11. The tube 41 of the projectile 25, made of aluminum alloy, has a first end 41a referred in the bore 36 of the fitting 35 of the body 28, and a second end 41b opposite the first end 41a. The tube 41 also has a cylindrical inner surface 42 of circular section along the projectile axis B. The inner surface 42 has an inner diameter Di substantially corresponding to the outer diameter of the launching rod 11 of the launcher 1. The inner diameter Di is substantially constant over a stroke c along the projectile axis B between a first location E1 located in the vicinity of the first end 41a of the tube 41 and a second location E2 remote from the first location E2 and located, in the embodiment shown, at the adjacent to the second end 41b of the tube 41. Alternatively, any other arrangement of the first location E1, the side of the operative head 26 and the second location E2 away from the first location E1 to define a suitable stroke c could be provided. For example, the inner diameter Di of the inner surface 42 is between 21.5 mm and 22.5 mm, in particular 22.05 mm. The tube 41 has a length, measured along the projectile axis B, of between 140 mm and 160 mm, in particular 150 mm, so that the stroke c between the first E1 and second E2 locations can be between 120 mm and 110 mm, in particular of 115 mm. The tube 41a, moreover, has a thickness e in the vicinity of the first location E1 of between 4.6 mm and 5 mm, in particular 4.8 mm. In the vicinity of the second end 41b, a empennage 43 is provided on an outer surface of the tube 41 to ensure stability during a shot.

La première extrémité 41a du tube 41 est fermée de manière étanche par un élément d'obturation. Dans le mode de réalisation représenté, l'élément d'obturation se présente sous la forme un bouchon 44 disposé dans un fond 37 de l'alésage 36 du raccord 35 du corps 28 et en contact avec le tube à sa première extrémité 41a.The first end 41a of the tube 41 is sealed by a closure member. In the embodiment shown, the closure member is in the form of a plug 44 disposed in a bottom 37 of the bore 36 of the fitting 35 of the body 28 and in contact with the tube at its first end 41a.

A l'opposé, un élément d'arrêt est solidarisé à la deuxième extrémité 41b du tube 41. L'élément d'arrêt est réalisé sous la forme d'une bague de retenue 45 cylindrique selon l'axe de projectile B. La bague de retenue 45 comprend une première partie 46 vissée sur la deuxième extrémité 41b du tube 41 et une deuxième partie 47 prolongeant le tube 41 au-delà de sa deuxième extrémité 41b selon l'axe de projectile B. La deuxième partie 47 de la bague de retenue 45 présente une surface intérieure 48 tronconique de section circulaire convergeant vers l'axe de projectile B en s'éloignant de la deuxième extrémité 41b du tube 41. La deuxième partie 47 de la bague de retenue 45 définit ainsi intérieurement une restriction 49 présentant un diamètre inférieur au diamètre intérieur Di de la surface intérieure 42 du tube 41 le long de la course c. Un insert 50 peut être monté de manière amovible sur la deuxième partie 47 de la bague de retenue 45 pour fermer l'accès à l'intérieur du tube 41 avant utilisation du projectile 25.In contrast, a stop element is secured to the second end 41b of the tube 41. The stop element is in the form of a cylindrical retaining ring 45 along the projectile axis B. The ring 45 comprises a first portion 46 screwed on the second end 41b of the tube 41 and a second portion 47 extending the tube 41 beyond its second end 41b along the projectile axis B. The second portion 47 of the ring retainer 45 has a frustoconical inner surface 48 of circular section converging towards the projectile axis B away from the second end 41b of the tube 41. The second portion 47 of the retaining ring 45 thus internally defines a restriction 49 having a diameter less than the inner diameter Di of the inner surface 42 of the tube 41 along the stroke c. An insert 50 may be removably mounted on the second portion 47 of the retaining ring 45 to close access to the interior of the tube 41 prior to use of the projectile 25.

Sur la figure 2, le projectile 25 comprend également un piston 60 monté dans le tube 41 et positionné au premier emplacement E1 de la course c formée sur la surface intérieure 42 du tube 42, au voisinage de la première extrémité 41a du tube 41. Le piston 60 comporte une paroi transversale 61 par rapport à l'axe de projectile B et adaptée pour reposer sur la surface d'appui 13 de l'extrémité libre 12 de la tige de lancement 11. Il comporte également une jupe 62 qui s'étend perpendiculairement à un bord périphérique de la paroi transversale 61 vers le bouchon 44 formant élément d'obturation. La jupe 62 présente une surface extérieure cylindrique de section circulaire, placée en contact hermétique avec la surface intérieure 42 du tube 41 et adaptée pour coulisser le long de la surface intérieure 42 du tube 41 selon l'axe de projectile B jusqu'au deuxième emplacement E2. La jupe 62 présente également une surface intérieure cylindrique de section circulaire délimitant, avec une surface supérieure de la paroi transversale 61, un évidement 63 ouvert vers le bouchon 44. L'évidement 63 peut notamment présenter un volume compris entre 2 cm3 et 4,5 cm3, en particulier de 2,5 cm3. Le piston 60 comporte en outre une amorce 64 agencée de manière sensiblement centrale dans la paroi transversale 61 de manière à pouvoir être activée par l'embout de percussion 14 en position d'amorçage lorsque le piston 60 repose sur la surface d'appui 13 de l'extrémité libre 12 de la tige de lancement 11. Le piston 60 délimite, avec le tube 41 et le bouchon 44, une chambre de propulsion 65 hermétiquement fermée dont le volume augmente au fur et à mesure que le piston 60 est déplacé du premier emplacement E1 au deuxième emplacement E2.On the figure 2 the projectile 25 also comprises a piston 60 mounted in the tube 41 and positioned at the first location E1 of the race c formed on the inner surface 42 of the tube 42, in the vicinity of the first end 41a of the tube 41. The piston 60 comprises a transverse wall 61 with respect to the projectile axis B and adapted to rest on the bearing surface 13 of the free end 12 of the launch rod 11. It also comprises a skirt 62 which extends perpendicularly to an edge peripheral of the transverse wall 61 to the stopper 44 forming closure element. The skirt 62 has a cylindrical outer surface of circular section, placed in hermetic contact with the inner surface 42 of the tube 41 and adapted to slide along the inner surface 42 of the tube 41 along the projectile axis B to the second location E2. The skirt 62 also has a cylindrical inner surface of circular section delimiting, with an upper surface of the transverse wall 61, a recess 63 open towards the cap 44. The recess 63 may in particular have a volume of between 2 cm 3 and 4, 5 cm 3 , in particular 2.5 cm 3 . The piston 60 further comprises a primer 64 arranged substantially centrally in the transverse wall 61 so as to be activated by the percussion tip 14 in the priming position when the piston 60 rests on the bearing surface 13 of the free end 12 of the launching rod 11. The piston 60 delimits, with the tube 41 and the plug 44, a hermetically closed propulsion chamber 65 whose volume increases as the piston 60 is displaced from the first location E1 at the second location E2.

Une charge de propulsion 70 est placée dans la chambre de propulsion 65 lorsque le piston 60 est au premier emplacement E1. La charge de propulsion 70 est adaptée pour être activée par l'amorce 64 du piston 60 pour déplacer le piston 60 entre les premier E1 et deuxième E2 emplacements. En particulier, la charge de propulsion 70 comprend entre 2,4 g et 3,7 g, voire entre 2,4 g et 3.6 g d'une poudre ayant une chaleur de combustion comprise entre 3500 J/g et 4000 J/g. Dans le mode de réalisation représenté, la poudre est intégralement placée dans l'évidement 63 du piston 60 avec une densité de chargement comprise entre 0,9 g et 1,2 g par cm3, notamment de 0,96 g par cm3. La poudre peut notamment être la même poudre que celle qui est utilisée dans la grenade exploitée par la société CATHYOR ENGINEERING S.A. sous la dénomination Fly-K®, à savoir une poudre sphérique P3T développée par la société PB CLERMONT.A propellant charge 70 is placed in the propulsion chamber 65 when the piston 60 is at the first location E1. The propulsion charge 70 is adapted to be activated by the primer 64 of the piston 60 to move the piston 60 between the first E1 and second E2 locations. In particular, the propellant charge 70 comprises between 2.4 g and 3.7 g, or even between 2.4 g and 3.6 g of a powder having a heat of combustion of between 3500 J / g and 4000 J / g. In the embodiment shown, the powder is integrally placed in the recess 63 of the piston 60 with a loading density of between 0.9 g and 1.2 g per cm 3 , in particular of 0.96 g per cm 3 . The powder may especially be the same powder as that used in the grenade operated by the company CATHYOR ENGINEERING SA under the name Fly-K®, namely a spherical P3T powder developed by the company PB CLERMONT.

L'équipement d'armement selon l'invention n'est pas limité à une grenade explosive 25 du type décrit précédemment comme projectile. En variante, d'autres projectiles de calibre et de poids compatibles avec le lanceur 1 peuvent être prévus. A titre d'exemple non limitatif, la figure 3 représente une grenade fumigène 25' dont la tête opérante 26' et le corps 28' sont adaptés pour produire un nuage de fumée. La figure 4 représente une grenade d'exercice 25" dont la tête opérante 26" et le corps 28" sont adaptés pour permettre de repérer la trajectoire et de marquer l'impact de la grenade 25" sur le sol. La queue 40 des projectiles 25', 25" est, quant à elle, identique à celle de la grenade explosive 25 décrite précédemment de manière à pouvoir coopérer avec la tige de lancement 11 et le dispositif de percussion 15 du lanceur 1.The arming equipment according to the invention is not limited to an explosive grenade of the type previously described as a projectile. Alternatively, other projectiles of caliber and weight compatible with the launcher 1 may be provided. By way of non-limiting example, the figure 3 represents a smoke grenade 25 'whose operating head 26' and the body 28 'are adapted to produce a cloud of smoke. The figure 4 represents a 25 "exercise grenade whose 26" operating head and 28 "body are adapted to locate the trajectory and mark the impact of the 25" grenade on the ground. The tail 40 of the projectiles 25 ', 25 "is, for its part, identical to that of the explosive grenade 25 previously described so as to cooperate with the launching rod 11 and the percussion device 15 of the launcher 1.

En relation avec les figures 5 et 6, une utilisation de l'équipement d'armement est décrite. Sur les figures 5 et 6, seule une partie au voisinage de l'extrémité libre 12 de la tige de lancement 11 du lanceur 1 est représentée.In relation to figures 5 and 6 a use of the arming equipment is described. On the figures 5 and 6 , only a portion in the vicinity of the free end 12 of the launching rod 11 of the launcher 1 is shown.

Le projectile, par exemple la grenade explosive 25 de la figure 2, est placé dans le fût 2 du lanceur 1 par l'opérateur après que celui-ci a retiré l'insert 50 monté sur la bague de retenue 45. En particulier, le projectile 25 est introduit par la queue 40 dans le logement 3 du fût 2 au travers de la bouche 5. Le tube 41 de la queue 40 coulisse sur la tige de lancement 11 jusqu'à ce que la paroi transversale 61 du piston 60 vienne en appui sur la surface d'appui 13 de l'extrémité libre 12 de la tige de lancement 11. Ce faisant, les lames ressort 6 du dispositif de retenue se déforment et sont rappelées dans une position de repos dans laquelle elles retiennent le projectile 25 dans le fût 2 au niveau de la queue 40, au-dessus de l'empennage 43. L'embout de percussion 16 est dans la position escamotée.The projectile, for example the explosive grenade of the figure 2 , is placed in the shaft 2 of the launcher 1 by the operator after the latter has removed the insert 50 mounted on the retaining ring 45. In particular, the projectile 25 is introduced by the tail 40 into the housing 3 of the barrel 2 through the mouth 5. The tube 41 of the tail 40 slides on the throwing rod 11 until the transverse wall 61 of the piston 60 bears on the bearing surface 13 of the free end 12 of the throwing rod 11. In doing so, the spring blades 6 of the retainer deform and are returned to a rest position in which they hold the projectile 25 in the barrel 2 at the tail 40, above of the empennage 43. The percussion tip 16 is in the retracted position.

Pour réaliser un tir, l'opérateur actionne l'ensemble de commande 19 qui fait passer l'embout de percussion 16 de la position escamotée à la position d'amorçage. Dans cette position d'amorçage, l'embout de percussion 16 active l'amorce 64 du piston 60 qui, à son tour, active la charge de propulsion 70. Le projectile 25 se déplace alors par rapport au piston 60 en appui sur l'extrémité libre 12 de la tige de lancement 11 de telle manière que le piston 60 coulisse depuis le premier emplacement E1 vers le deuxième emplacement E2 où il est retenu par la restriction 49 de la bague de retenue 45. La chambre de propulsion 65 reste hermétiquement fermée, contenant ainsi la flamme et les fumées pour supprimer la lumière et réduire le bruit et la chaleur émis lors du tir. Le projectile 25 quitte ensuite le fût 2 du lanceur 1 pour être projeté à distance du lanceur 1 et notamment à une distance allant jusqu'à 1000 m.To make a shot, the operator actuates the control assembly 19 which passes the percussion tip 16 from the retracted position to the priming position. In this priming position, the percussion tip 16 activates the primer 64 of the piston 60 which, at its turn, activates the propelling charge 70. The projectile 25 then moves relative to the piston 60 bearing on the free end 12 of the launching rod 11 so that the piston 60 slides from the first location E1 to the second E2 location where it is retained by the restriction 49 of the retaining ring 45. The propulsion chamber 65 remains hermetically closed, thus containing the flame and fumes to suppress the light and reduce the noise and heat emitted during firing. The projectile 25 then leaves the drum 2 of the launcher 1 to be projected at a distance from the launcher 1 and in particular at a distance of up to 1000 m.

Claims (9)

  1. Weapon equipment comprising a launcher (1) and at least one projectile (25; 25'; 25") intended to be projected at a distance by the launcher (1),
    wherein the launcher (1) comprises:
    - a cylindrical barrel (2) along a barrel axis (A), with the barrel (2) comprising a housing (3) adapted to receive at least one portion of the projectile (25; 25'; 25"), and a mouth (5) adapted to allow for a passage of the projectile (25; 25'; 25"),
    - a launch rod (11) extending in the housing (3) of the barrel (2) along the barrel axis (A) and having a free end (12) facing the mouth (5) of the barrel (2), the free end (12) having a bearing surface (13) and a recess (14) arranged in the bearing surface (13),
    - a percussion device (15) comprising a percussion tip (16) mounted to be movable in the launch rod (11) between a retracted position, wherein the percussion tip (16) is arranged in the recess (14), and a priming position, wherein the percussion tip (16) protrudes in relation to the bearing surface (13),
    wherein the projectile (25; 25'; 25") has a weight between 750 g and 1000 g and extends along a projectile axis (A), the projectile (25; 25'; 25") comprising an operating head (26; 26'; 26") and a tail (40) that extends the operating head (26; 26'; 26") along the projectile axis (B), the tail (40) comprising:
    - a tube (41) adapted to be mounted on the launch rod (11), with the tube (41) being made of an aluminum alloy and having an inner cylindrical surface (42) of circular section along the projectile axis (B), the inner surface (42) having a constant inner diameter (Di) over a stroke (c) along the projectile axis (B) between a first location (E1) located on a side of the operating head (26; 26'; 26") and a second location (E2) separate from the first location (E1), the inner diameter (Di) being between 21.5 mm and 22.5 mm, in particular 22.05 mm, the stroke (c) being between 110 mm and 120 mm, in particular 115 mm, the tube (41) having a thickness (e) in the vicinity of the first location (E1) between 4.6 mm and 5 mm, in particular 4.8 mm,
    - a sealing element (44) closing the tube (41) in a sealed manner in the vicinity of the first location (E1),
    - a piston (60) placed in the tube (41) in sealed contact with the inner surface (42) of said tube (41) and adapted to rest on the bearing surface (13) of the free end (12) of the launch rod (11), the piston (60) comprising a primer (64) arranged to be activated by the percussion tip (16) in priming position when the piston (60) is resting on the bearing surface (13) of the free end (12) of the launch rod (11), the piston (60) defining with the tube (41) and the sealing element (44) a hermetically-sealed propulsion chamber (65), with the piston (60) being placed at the first location (E1) and able to be moved to the second location (E2),
    - a propulsion charge (70) placed in the propulsion chamber (65) when the piston (60) is at the first location (E1) and which can be activated by the primer (64) of the piston (60) in order to move the piston (60) bearing on the bearing surface (13) of the free end (12) of the launch rod (11) from the first location (E1) to the second location (E2), the propulsion charge (70) comprising a powder having a heat of combustion between 3500 J/g and 4000 J/g,
    - a stopper element (45) adapted to retain the piston (60) in the tube (41) at the second location (E2),
    with the weapon equipment being characterized in that the propulsion charge (70) has a mass strictly greater than 2.4 g and less than 3.7 g, more preferably less than 3.6 g and in that the piston (60) has a recess (63) open towards the sealing element (44), and wherein the powder of the propulsion charge (70) is entirely placed in the recess (63) of the piston (60) with a loading density between 0.9 g and 1.2 g per cm3.
  2. Weapon equipment according to claim 1, wherein the projectile (25; 25'; 25") has a caliber of 51 mm.
  3. Weapon equipment according to any of claims 1 to 2, wherein the tube (41) of the projectile (25; 25'; 25") has opposite first (41a) and second (41b) ends in the vicinity of which the first (E1) and second (E2) locations are carried out.
  4. Weapon equipment according to any of claims 1 to 3, wherein the projectile (25; 25'; 25") further comprises a body (28; 28'; 28") adjoin the head (26; 26'; 26"), with the head (26) comprising an explosive charge and the body (28) comprising a fragment-generating sleeve (29), with the fragment-generating sleeve (29) being cylindrical along the projectile axis (B) and having an inner surface, the inner surface being provided with first (31) and second (32) grooves extending respectively according to first and second secant directions.
  5. Weapon equipment according to claim 4, wherein the first grooves are threads (31) extending substantially circumferentially and the second grooves are channels (32) extending substantially axially.
  6. Weapon equipment according to claim 5 when it depends on claim 2, wherein the fragment-generating sleeve (29) has an outer diameter of 51 mm and an inner diameter of 45 mm, and wherein the inner surface of the fragment-generating sleeve (29) has threads (31) carried out with a pitch of 4 mm and twenty to thirty channels (32).
  7. Weapon equipment according to any of claims 4 to 6, wherein the fragment-generating sleeve (29) is made from steel.
  8. Weapon equipment according to any of claims 1 to 7, wherein the launcher (1) is individual and can be carried by hand by an operator.
  9. Projectile (25; 25'; 25") specially adapted for weapon equipment according to any of claims 1 to 8, the projectile (25; 25'; 25") having a weight between 750 g and 1000 g and extending along a projectile axis (B), the projectile (25; 25'; 25") comprising an operating head (26; 26'; 26") and a tail (40) which extends the operating head (26; 26'; 26") along the projectile axis (B), the tail (40) comprising:
    - a tube (41) adapted to be mounted on a launch rod (11) of a launcher (1), with the tube (41) being made of an aluminum alloy and having an inner cylindrical surface (42) of circular section along the projectile axis (B), the inner surface (42) having a constant inner diameter (Di) over a stroke (c) along the projectile axis (B) between a first location (E1) located on a side of the operating head (26; 26'; 26") and a second location (E2) separate from the first location (E1), the inner diameter (Di) being between 21.5 mm and 22.5 mm, in particular 22.05 mm, the stroke (c) being between 110 mm and 120 mm, in particular 115 mm, the tube (41) having a thickness (e) in the vicinity of the first location (E1) between 4.6 mm and 5 mm, in particular 4.8 mm,
    - a sealing element (44) closing the tube (41) in a sealed manner in the vicinity of the first location (E1),
    - a piston (60) placed in the tube (41) in sealed contact with the inner surface (42) of said tube (41) and adapted to rest on a bearing surface (13) of a free end (12) of the launch rod (11) of the launcher (1), the piston (60) comprising a primer (64) arranged in order to be activated by a percussion tip (16) in priming position of a percussion device (15) of the launcher (1) when the piston (60) is resting on the bearing surface (13) of the free end (12) of the launch rod (11) of the launcher (1), with the piston (60) defining with the tube (41) and the sealing element (44) a hermetically-sealed propulsion chamber (65), with the piston (60) being placed at the first location (E1) and able to be moved to the second location (E2),
    - a propulsion charge (70) placed in the propulsion chamber (65) when the piston (60) is at the first location (E1) and which can be activated by the primer (64) of the piston (60) in order to displace the piston (60) bearing on the bearing surface (13) of the free end (12) of the launch rod (11) of the launcher (1) from the first location (E1) to the second location (E2), the propulsion charge (70) comprising a powder having a heat of combustion between 3500 J/g and 4000 J/g,
    - a stopper element (45) adapted to retain the piston (60) in the tube (41) at the second location (E2),
    with the projectile (25; 25'; 25") being characterized in that the propulsion charge (70) has a mass strictly greater than 2.4 g and less than 3.7 g, more preferably less than 3.6 g and in that the piston (60) has a recess (63) open towards the sealing element (44), and wherein the powder of the propulsion charge (70) is entirely placed in the recess (63) of the piston (60) with a loading density between 0.9 g and 1.2 g per cm3.
EP16206899.3A 2015-12-30 2016-12-26 Launching device and projectile especially adapted for such a launching device Active EP3187816B9 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
RS20190145A RS58306B9 (en) 2015-12-30 2016-12-26 Launching device and projectile especially adapted for such a launching device
PL16206899T PL3187816T3 (en) 2015-12-30 2016-12-26 Launching device and projectile especially adapted for such a launching device

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1563479A FR3046457B1 (en) 2015-12-30 2015-12-30 ARMAMENT EQUIPMENT AND PROJECTILE ESPECIALLY ADAPTED FOR SUCH ARMOR EQUIPMENT

Publications (3)

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EP3187816A1 EP3187816A1 (en) 2017-07-05
EP3187816B1 EP3187816B1 (en) 2018-12-26
EP3187816B9 true EP3187816B9 (en) 2019-06-26

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US (1) US9921032B2 (en)
EP (1) EP3187816B9 (en)
CH (1) CH711974B1 (en)
DK (1) DK3187816T5 (en)
ES (1) ES2708660T3 (en)
FR (1) FR3046457B1 (en)
HU (1) HUE041271T4 (en)
PL (1) PL3187816T3 (en)
RS (1) RS58306B9 (en)

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Publication number Priority date Publication date Assignee Title
NL65695C (en) 1961-07-20 Energa
FR1326176A (en) * 1961-07-20 1963-05-03 Energa Projectile
CH481363A (en) 1967-10-03 1969-11-15 Batou Boris Shooting equipment comprising a mortar and a projectile
CH637761A5 (en) 1980-08-08 1983-08-15 Valinor Sa ASSEMBLY CONSISTING OF A PROJECTILE AND THE DEVICE FOR LAUNCHING THE PROJECTILE.
US4689911A (en) * 1984-06-04 1987-09-01 Napco Industries, Inc. Grenade launcher attachment for infantry weapon
US5228855A (en) * 1992-03-31 1993-07-20 Ffe International Mortar training ammunition device having independently rotatable vent closure rings
DE102013010502A1 (en) * 2013-06-25 2015-01-08 Rheinmetall Waffe Munition Gmbh An active part detonator for a mortar shell and mortar shell which can be fired from a mortise and mortar with such an active part fuze

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HUE041271T2 (en) 2019-05-28
RS58306B9 (en) 2019-08-30
CH711974B1 (en) 2020-04-15
FR3046457B1 (en) 2018-02-16
ES2708660T9 (en) 2019-08-23
EP3187816B1 (en) 2018-12-26
DK3187816T3 (en) 2019-02-25
RS58306B1 (en) 2019-03-29
US9921032B2 (en) 2018-03-20
HUE041271T4 (en) 2019-11-28
DK3187816T5 (en) 2019-09-23
EP3187816A1 (en) 2017-07-05
CH711974A2 (en) 2017-06-30
US20170299328A1 (en) 2017-10-19
ES2708660T3 (en) 2019-04-10
FR3046457A1 (en) 2017-07-07
PL3187816T3 (en) 2019-05-31

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