• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to a weapon equipment comprising a launcher and a projectile (25), the projectile (25) having a weight of between 750 g and 1000 g, the projectile (25) comprising an operating head (26) and a tail (40), the tail (40) comprising: an aluminum alloy tube (41) having an inside diameter (Di) of between 21.5 mm and 22.5 mm, a stroke (c) between first (E1) ) and second (E2) locations between 110 mm and 120 mm, and a thickness (e) in the vicinity of the first location (E1) between 4.6 mm and 5 mm, a piston (60) movable between the first (E1) ) and second (E2) locations and defining with the tube (41) a hermetically closed propellant chamber (65), a propellant charge (70) disposed in the propulsion chamber (65), the propellant charge (70) comprising a powder having a heat of combustion of between 3500 J / g and 4000 J / g, the propellant charge (70) having a strictly superior mass at 2.4 g and less than 3.7 g.
    公开号:CH711974A2
    申请号:CH00554/16
    申请日:2016-04-27
    公开日:2017-06-30
    发明作者:Henri Armand Donin De Rosière Yves
    申请人:Cathyor Eng Sa；
    IPC主号:
    专利说明:

    Description: [0001] The invention relates to armament equipment and to a projectile specially adapted for such armament equipment.
    In particular, the invention relates to an 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 shaft along an axis barrel, 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 launching rod extending into the housing of the barrel along the shaft axis and having a free end facing the mouth of the barrel, the free end having a bearing surface and a recess in the bearing surface, - 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 protrudes from the surface in which the projectile has a weight of between 750 g and 1000 g and extends along a projectile axis, the projectile comprising an operant 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 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 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 sealing contact with the inner surface of said tube and adapted to rest on the bearing surface of the free end of the tube; launching rod, the piston having a primer arranged to be activated by the percussion tip in the priming position when the piston rests on the bearing surface of the free end of the launching rod, the piston delimiting with the tube and shutter member a hermetically closed propellant chamber, the piston being located in the first location and movable to the second location; - a propulsion charge placed in the propulsion chamber when the piston is at the first location and activatable by the primer of the piston for moving the piston bearing on the bearing surface of the free end of the launching rod from the first em placement 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.
    A weapon equipment of this type corresponds to a mortar as a launcher and a grenade as a projectile operated by the company CATHYOR ENGINEERING S.A. under the name Fly-K®.
    This arming equipment, simple and lightweight 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 known arming equipment is, however, limited to a maximum range of 650 m with an angle of pitch of the launcher 45 °. There is a need to increase this range, especially up to 1000 m, while preserving the efficiency of the arming equipment.
    The invention aims to meet this need.
    For this purpose, according to a first aspect, the invention provides a weapon equipment of the aforementioned type wherein the propellant load has a mass strictly greater than 2.4 g and less than 3.7 g, preferably less than 3.6 g.
    Thus, the projectile according to the invention makes it possible to increase the range of the arming equipment in a simple manner, only by increasing the propulsion load relative to the propulsion charge of the projectile operated under the name Fly- K®.
    Although it is commonly accepted in the field of armament, an increase in the propulsion load is generally accompanied by a modification of the projectile and / or propellant charge powder, in particular to choose a less bright powder, that is to say having a lower heat of combustion, the inventors have found that an increase in the propulsion load makes it possible to increase the range of the armament equipment without damaging the launcher or risk compromising the integrity of the operator. In particular, the propulsion load could be increased to 3 g, ie 125% more than the propulsion load of the projectile operating under the name Fly-K®, and up to 3.7 g, ie 155% more than the propelling charge of the projectile operated under the name Fly-K®.
    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 can withstand the energy released during the initiation of the propulsion load.
    The piston may have an open recess towards the sealing member, and the powder of the propellant charge may be integrally placed in the recess of the piston with a loading density of between 0.9 g and 1, 2 g per cm3. The increase in the propulsion load can thus be carried out at a constant loading density with respect to the propulsion load of the projectile operating 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 may have a caliber of 51 mm.
    The projectile tube may have opposite first and second ends in the vicinity of which the first and second locations are made.
    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 having a fragment-generating sleeve, the fragment-generating sleeve being cylindrical according to the invention. 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 substantially circumferentially extending threads and the second grooves may be grooves extending substantially axially.
    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-generating sleeve may have threads made. with a pitch of 4 mm and twenty to thirty gorges.
    The splinter generator sleeve may be made of steel.
    The launcher can be individual and portable by hand by an operator.
    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 an operating head and a tail which 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 cross-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 115 mm, the tube having a thickness in the vicinity of the first location between 4.6 mm and 5 mm, in particular 4.8 mm, - a closure member sealing the tube at next to 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 percussion tip 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 sealing member a hermetically sealed propellant chamber, the piston being located in the first location and movable to the second location, - a propelling charge placed in the chamber of propulsion 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 starter 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, in which the propellant charge has a mass strictly greater than 2.4 g and less than 3.7 g, preferably less than 3.6 g.
    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 drawings. annexed in which: FIG. 1 is a longitudinal sectional representation of a launcher of a cockpit equipment according to one embodiment of the invention, FIG. 2 is a longitudinal sectional representation of a projectile of the arming equipment intended to be projected remotely by the launcher of FIG. 1, figs. 3 and 4 are longitudinal sectional views of variants of the projectile of the arming equipment intended to be projected remotely by the launcher of FIG. 1, figs. 5 and 6 are longitudinal sectional representations of the launcher of FIG. 1 and the projectile of FIG. 2, respectively illustrating the projectile placed in the launcher prior to a shot and the projectile leaving the launcher during shooting.
    In the figures, the same references denote identical or similar elements.
    Figs. 1 and 2 represent individual armament equipment comprising a launcher 1 and one or more projectiles 25 intended to be projected remotely by the launcher 1.
    In FIG. 1, the launcher 1 is an individual mortar and portable by hand by an operator similar to the mortar operated by the company CATHYOR ENGINEERING S.A. 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. Alternatively, the housing 3 could 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 retaining device, 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.
    A launcher body 7, hollow, extends the barrel 2 on the side of its bottom 4, along the barrel axis A. The launcher body 7 comprises in particular a launcher tube 8 connected to the bottom 4 of the barrel 2 by a connection interface 9.
    The launcher 1 also comprises a percussion assembly 10 involved in projecting the projectile 25. The percussion assembly 10 comprises a cylindrical launching rod 11 of circular section along the barrel axis 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 axis of A drum, 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 disposed 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 endpiece 16 is located in the recess 14 of the free end 12 of the launching rod 11, and an ignition position, in which the percussion tip 16 projects in relation to the bearing surface 13 of the free end 12 of the launch rod 11. In particular, the percussion tip 16 is carried by a pin 17 slidably mounted along the barrel axis A inside a housing of the launch rod 11 The spindle 17 is urged towards an advanced position by one or more resilient members, such as coil springs 18, and retained in a retracted position by a hook 20 of the control assembly 19 placed in the thrower tube 8 of the 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.
    In contrast to the shaft 2, the launcher tube 8 of the launcher body 7 has an articulated foot 21 for placing the launcher 1 on the ground, if necessary by orienting it, the inclination of the launcher 1 being given via a clinometer 22 mounted on the launcher body 7.
    In FIG. 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 size, 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 rocket operated under the name FLAME by the company JUN-GHANS Microtec GmbH, has an explosive charge and is secured, for example by screwing directly or, as shown in FIG. . 2, via 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 forms the first end 28a of the body 28. The splinter generator sleeve 29, made of steel, has 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.
    The body 28 also comprises a connector 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 generator 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. In particular, the tail 40 comprises a tube 41 adapted to be mounted on the launch rod 11. The tube 41 of the projectile 25, made of alloy of aluminum, 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.
    The first end 41a of the tube 41 is sealingly closed 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.
    In contrast, a stop member is secured to the second end 41b of the tube 41. The stop member is formed in the form of a cylindrical retaining ring 45 along the axis of projectile B The retaining ring 45 comprises a first portion 46 screwed onto 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 part 47 of the retaining ring 45 has a frustoconical inner surface 48 of circular section converging toward the projectile axis B away from the second end 41b of the tube 41. The second portion 47 of the retaining ring 45 thus defines a restriction internally 49 having a diameter smaller 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.
    In FIG. 2, the projectile 25 also comprises a piston 60 mounted in the tube 41 and positioned at the first location E1 of the stroke 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 perpendicular to a peripheral edge of the transverse wall 61 towards the cap 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 plug 44. The recess 63 may in particular have a volume of between 2 cm 3 and 4.5 cm3, in particular 2.5 cm3. 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 propellant 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, in particular of 0.96 g per cm. The powder may especially be the same powder as that used in the grenade operated by the company CATHYOR ENGINEERING S.A. 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. Alternatively, other projectiles of caliber and weight compatible with the launcher 1 may be provided. By way of non-limiting example, FIG. 3 represents a smoke grenade 25 'whose operating head 26' and the body 28 'are adapted to produce a cloud of smoke. Fig. 4 represents a 25 "exercise grenade whose 26" operating head and 28 "body are adapted to identify the trajectory and mark the impact of the grenade.
    权利要求:
    Claims (10)
    [1]
    Equipment for armament comprising a launcher (I) and at least one projectile (25; 25 '; 25 ") intended to be thrown remotely by the launcher (1), in which the launcher (1) comprises: barrel (2) cylindrical about a barrel axis (A), the barrel (2) having a housing (3) adapted to receive at least a portion of the projectile (25; 25 '; 25 "), and a mouth (5) adapted to allow passage of the projectile (25; 25 '; 25 "), -a throwing rod (11) extending into the housing (3) of the barrel (2) along the barrel axis (A) supporting 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) formed in the bearing surface (13). ), - a percussion device (15) comprising a percussion tip (16) movably mounted in the launching rod (11) between a retracted position, in which the percussion tip (16) is disposed in the recess ( 14), and a position of priming, wherein the hammer tip (16) protrudes with respect to the bearing surface (13), wherein the projectile (25; 25 '; 25 ") has a weight of 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 shank (40) which extends the operating head (26; 26 '; 26 ") along the projectile axis (B), the shank (40) comprising: - a tube (41) adapted to be mounted on the shank for launching (11), the tube (41) being made of aluminum alloy and having a cylindrical inner surface (42) of circular section along the projectile axis (B), the inner surface (42) having an inside diameter (Di) constant over a stroke (c) along the projectile axis (B) between a first location (E1) located on the operating head side (26; 26 '; 26 ") and a second remote location (E2) the first location (E1), the inside 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) of between 4.6 mm and 5 mm, in particular of 4.8 mm, - a sealing member (44) sealing the tube (41) in a leaktight manner in the vicinity of the first location (E1), - a piston (60) placed in the tube (41) in hermetic 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 throwing rod (11), the piston (60) having a primer (64) arranged to be activated by the percussion tip (16) in the priming position when the piston ( 60) rests on the bearing surface (13) of the free end (12) of the throwing rod (11), the piston (60) delimiting with the tube (41) and the closure element (44). ) a propellant chamber (65) hermetically closed, the piston (60) being located at the first location (E1) and movable to the second location (E2), - a propelling load (70) placed in the propulsion chamber (65) when the piston (60) is at the first location (E1) and activatable by the primer (64) of the piston (60) to move the piston (60) bearing on the surface of supporting (13) the free end (12) of the throwing rod (11) from the first location (E1) to the second location (E2), the propelling load (70) comprising a powder having a heat of combustion between 3500 J / g and 4000 J / g, - a stop element (45) adapted to retain the piston (60) in the tube (41) at the second location (E2), the arming equipment being characterized in that the propellant charge (70) has a mass strictly greater than 2.4 g and less than 3.7 g, preferably less than 3.6 g.
    [2]
    The cocking equipment according to claim 1, wherein the piston (60) has a recess (63) open to the closure member (44), and wherein the propellant charge powder (70) 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 cm3.
    [3]
    3. Weapon equipment according to any one of claims 1 and 2, wherein the projectile (25; 25 '; 25 ") has a caliber of 51 mm.
    [4]
    4. Weapon equipment according to any one of claims 1 to 3, wherein the tube (41) of the projectile (25; 25 '; 25 ") has first (41a) and second (41b) opposite ends in the vicinity which first (E1) and second (E2) locations are made.
    [5]
    The armament equipment according to any one of claims 1 to 4, wherein the projectile (25; 25 '; 25 ") further comprises a body (28; 28'; 28") adjoining the head (26; ; 26 '; 26 "), the head (26) having an explosive charge and the body (28) having a splinter sleeve (29), the splinter sleeve (29) being cylindrical along the axis of projectile (B) and having an inner surface, the inner surface being provided with first (31) and second (32) grooves respectively extending in first and second intersecting directions.
    [6]
    The cocking equipment according to claim 5, wherein the first grooves are substantially circumferentially extending threads (31) and the second grooves are grooves (32) extending substantially axially.
    [7]
    A cocking equipment according to claim 6 when dependent on claim 3, wherein the splinter sleeve (29) has an outside diameter of 51 mm and an inside diameter of 45 mm, and wherein the surface Inside the splinter sleeve (29) has threads (31) made with a pitch of 4 mm and twenty to thirty grooves (32).
    [8]
    8. cockpit equipment according to any one of claims 5 to 7, wherein the splinter sleeve (29) is made of steel.
    [9]
    9. cockpit equipment according to any one of claims 1 to 8, wherein the launcher (1) is individual and portable by hand by an operator.
    [10]
    10. A projectile (25; 25 '; 25 ") specially adapted for arming equipment according to any one of claims 1 to 9, the projectile (25; 25'; 25") having a weight of 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) extending the operative head (26; 26 '; 26 ") along the projectile axis (B), the tail (40) comprising: - a tube (41) adapted to be mounted on a launching rod (11) of a launcher (1) ), the tube (41) being made of aluminum alloy and having a cylindrical inner surface (42) of circular section along the projectile axis (B), the inner surface (42) having a constant inner diameter (Di) on a stroke (c) along the projectile axis (B) between a first location (E1) located on the operating head side (26; 26 '; 26 ") and a second location (E2) remote 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 of 115 mm, the tube (41 ) having a thickness (e) in the vicinity of the first location (E1) of between 4.6 mm and 5 mm, in particular of 4.8 mm, - a closure member (44) closing the tube (41) so as to in the vicinity of the first location (E1); - a piston (60) placed in the tube (41) in hermetic contact with the inner surface (42) of said tube (41) and adapted to rest on a bearing surface (13); ) a free end (12) of the launching rod (11) of the launcher (1), the piston (60) having a primer (64) arranged to be activated by a percussion tip (16) in position d ' priming of a percussion device (15) of the launcher (1) when the piston (60) rests on the bearing surface (13) of the free end (12) of the launcher launching rod (11) ( 1), the pist (60) delimiting with the tube (41) and the closure member (44) a hermetically closed propellant chamber (65), the piston (60) being located at the first location (E1) and movable to the second location (E2), - a propelling charge (70) placed in the propulsion chamber (65) when the piston (60) is at the first location (E1) and activatable by the primer (64) of the piston (60) to move the piston (60) bearing on the bearing surface (13) of the free end (12) of the launching rod (11) of the launcher (1) from the first location (E1) to the second location (E2 ), the propellant charge (70) comprising a powder having a heat of combustion of between 3500 J / g and 4000 J / g, - a stop member (45) adapted to retain the piston (60) in the tube ( 41) at the second location (E2), the projectile (25; 25 '; 25 ") being characterized in that the propellant charge (70) has a mass strictly greater than 2.4 g and less than 3.7 g, preferably less than 3.6 g.
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    公开号 | 公开日
    EP3187816B9|2019-06-26|
    HUE041271T4|2019-11-28|
    US20170299328A1|2017-10-19|
    FR3046457B1|2018-02-16|
    EP3187816B1|2018-12-26|
    FR3046457A1|2017-07-07|
    RS58306B1|2019-03-29|
    CH711974B1|2020-04-15|
    EP3187816A1|2017-07-05|
    DK3187816T3|2019-02-25|
    ES2708660T9|2019-08-23|
    HUE041271T2|2019-05-28|
    DK3187816T5|2019-09-23|
    RS58306B9|2019-08-30|
    PL3187816T3|2019-05-31|
    ES2708660T3|2019-04-10|
    US9921032B2|2018-03-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    BE458606A|1961-07-20|Energa|
    FR1326176A|1961-07-20|1963-05-03|Energa|Projectile|
    CH481363A|1967-10-03|1969-11-15|Batou Boris|Shooting equipment comprising a mortar and a projectile|
    CH637761A5|1980-08-08|1983-08-15|Valinor Sa|ASSEMBLY CONSISTING OF A PROJECTILE AND THE DEVICE FOR LAUNCHING THE PROJECTILE.|
    US4689911A|1984-06-04|1987-09-01|Napco Industries, Inc.|Grenade launcher attachment for infantry weapon|
    US5228855A|1992-03-31|1993-07-20|Ffe International|Mortar training ammunition device having independently rotatable vent closure rings|
    DE102013010502A1|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|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    FR1563479A|FR3046457B1|2015-12-30|2015-12-30|ARMAMENT EQUIPMENT AND PROJECTILE ESPECIALLY ADAPTED FOR SUCH ARMOR EQUIPMENT|
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