Weapon equipment and projectile especially adapted for such weapon equipment

Weapon equipment including a launcher and a projectile, the projectile having an operating head, a tail and a weight between 750 g and 1000 g. The tail includes a tube made of an aluminum alloy having an inner diameter between 21.5 and 22.5 mm, a stroke between first and second locations between 110 mm and 120 mm, and a thickness in the vicinity of the first location between 4.6 mm and 5 mm, a piston movable between the first and second locations and defining with the tube a hermetically-sealed propulsion chamber, a propulsion charge placed in the propulsion chamber, the propulsion charge including a powder having a heat of combustion between 3500 J/g and 4000 J/g, the propulsion charge having a mass greater than 2.4 g and less than 3.7 g.

FIELD OF THE INVENTION

The invention relates to weapon equipment and to a projectile specially adapted for such weapon equipment.

BACKGROUND OF THE INVENTION

In particular, the invention relates to weaponry equipment of the type comprising a launcher and at least one projectile intended to be projected at a distance by the launcher,

wherein the launcher comprises:a cylindrical barrel along a barrel axis, with the barrel comprising a housing adapted to receive at least one portion of the projectile, and a mouth adapted to allow for a passage of the projectile,a launch rod extending in the housing of the barrel along the barrel axis and having a free end facing the mouth of the barrel, with the free end having a bearing surface and a recess arranged in the bearing surface,a percussion device comprising a percussion tip mounted to be movable in the launch rod between a retracted position, wherein the percussion tip is arranged in the recess, and a priming position, wherein the percussion tip protrudes in relation to the bearing surface,

wherein the projectile has a weight between 750 g and 1000 g and extends along a projectile axis, with the projectile comprising an operating head and a tail which extends the operating head along the projectile axis, the tail comprising:a tube adapted to be mounted on the launch rod, with the tube being made from an aluminum alloy and having a cylindrical inner surface of circular section along the projectile axis, with the inner surface having a constant inner diameter over a stroke along the projectile axis between a first location located on a side of the operating head and a second location separate from the first location, the inner 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, with 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 sealing element closing the tube in a sealed manner in the vicinity of the first location,a piston placed in the tube in sealed contact with the inner surface of said tube and adapted to rest on the bearing surface of the free end of the launch rod, the piston comprising a primer arranged to be activated by the percussion tip in priming position when the piston is resting on the bearing surface of the free end of the launch rod, with the piston defining with the tube and the sealing element a hermetically-sealed propulsion chamber, with the piston being placed at the first location and able to be moved to the second location,a propulsion charge placed in the propulsion chamber when the piston is at the first location and able to be activated by the primer of the piston in order to move the piston bearing on the bearing surface of the free end of the launch rod from the first location to the second location, with the propulsion charge comprising a powder having a heat of combustion between 3500 J/g and 4000 J/g,a stopper element adapted to retain the piston in the tube at the second location.

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 weapon equipment, simple and light for an operator, makes it possible to contain the flame and the smoke resulting from the priming of the propulsion charge inside the hermetically-sealed propulsion chamber. These dispositions make it possible to suppress the light and to reduce the noise and the heat emitted during a firing. The firing is as such made difficult to detect by an enemy targeted by the firing not only with its bare senses but also with electronic detection devices, in particular infrared. The known weapon equipment provides great effectiveness due to its maneuverability, the maintaining of the operator safe that it provides for and the surprise effect that it can create.

The known weapon equipment is however limited to a maximum range of 650 m with an angle of inclination of the launcher of 45°. There is a need to increase this range, in particular up to 1000 m, while still preserving the effectiveness of the weaponry equipment.

BRIEF SUMMARY OF THE INVENTION

The invention aims to respond to this need.

To this end, according to a first aspect, the invention proposes a weapon equipment of the aforementioned type wherein the propulsion charge has a mass strictly greater than 2.4 g and less than 3.7 g, more preferably less than 3.6 g.

Hence, the projectile according to the invention makes it possible to increase the range of the weapon equipment in a simple manner, solely by increasing the propulsion charge in relation to the propulsion charge of the projectile operated under the name Fly-K®.

It is commonly admitted in the field of weaponry, that an increase of the propulsion charge is generally accompanied by a modification of the projectile and/or of the powder of the propulsion charge, in particular for choosing a powder having a less vivacity, i.e. having a lower heat of combustion. As such, the Manuel de rechargement No. 6 by René Malfatti, published in 2004 by Crépin Leblong, pages 43-45, stipulates that “for a same caliber, the vivacity of the powder has to decrease when the capacity of the cartridge case increases”. In addition, the mass of the projectile according to the invention is greater than that of the projectile operated under the name Fly-K®. It is also commonly admitted in the field of weaponry 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 vivacity. As such, the aforementioned Manuel de rechargement No. 6 stipulates, page 65, that “if, for a same type of powder and a same charge, a heavier projectile is used, the pressure rises; it is then necessary: either to reduce the charge, or to switch to a lower vivacity index”.

The inventors have therefore gone against these technical prejudices and have observed that an increase in the propulsion charge alone made it possible to increase the range of the weapon equipment without damaging the launcher or risking affecting the integrity of the operator. In particular, the propulsion charge was able to be increased to be 3 g, which is 125% more than the propulsion charge of the projectile operated under the name Fly-K®, and up to 3.7 g, which is 155% more than the propulsion 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 made it possible to resist the energy released during the priming of the propulsion charge.

The piston can have a recess opened towards the sealing element, and the powder of the propulsion charge can be entirely placed in the recess of the piston with a loading density between 0.9 g and 1.2 g par cm3. The increase in the propulsion charge can as such be carried out at a constant loading density in relation to the propulsion charge of the projectile operated under the name Fly-K®. The recess of the piston then has an increased volume in relation to volume of the recess of the piston of the projectile operated under the name Fly-K®.

The projectile can have a caliber of 51 mm.

The tube of the projectile can have opposite first and second ends in the vicinity of which the first and second locations are carried out.

In a complementary or alternative manner, the projectile can further include a body adjoining the head, with the head comprising an explosive charge and the body comprising a fragment-generating sleeve, with 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 extending respectively according to first and second secant directions.

The first grooves can be threads extending substantially circumferentially and the second grooves can be channels extending substantially axially.

When the projectile has a caliber of 51 mm, the fragment-generating sleeve can have an outer diameter of 51 mm and an inner diameter of 45 mm, and the inner surface of the fragment-generating sleeve can have threads carried out with a pitch of 4 mm and twenty to thirty channels.

The fragment-generating sleeve can be made of steel.

The launcher can be individual and able to be carried by hand by an operator.

According to a second aspect, the invention relates to a projectile specially adapted for a weapon equipment such as defined hereinabove, the projectile having a weight between 750 g and 1000 g and extending along a projectile axis, the projectile comprising an operating head and a tail that extends the operating head along the projectile axis, the tail comprising:a tube adapted to be mounted on a launch rod of a launcher, with the tube being made from an aluminum alloy and having a cylindrical inner surface of circular section along the projectile axis, with the inner surface having a constant inner diameter over a stroke along the projectile axis between a first location located on a side of the operating head and a second location separate from the first location, the inner 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, with 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 sealing element closing the tube in a sealed manner in the vicinity of the first location,a piston placed in the tube in sealed contact with the inner surface of said tube and adapted to rest on a bearing surface of a free end of the launch rod of the launcher, the piston comprising a primer arranged to be activated by a percussion tip in priming position of a percussion device of the launcher when the piston is resting on the bearing surface of the free end of the launch rod of the launcher, with the piston defining with the tube and the sealing element a hermetically-sealed propulsion chamber, with the piston being placed at the first location and able to be moved to the second location,a propulsion charge placed in the propulsion chamber when the piston is at the first location and able to be activated by the primer of the piston in order to move the piston bearing on the bearing surface of the free end of the launch rod of the launcher from the first location to the second location, with the propulsion charge comprising a powder having a heat of combustion between 3500 J/g and 4000 J/g,a stopper element adapted to retain the piston in the tube at the second location,

wherein the propulsion charge has a mass strictly greater than 2.4 g and less than 3.7 g, more preferably less than 3.6 g.

DETAILED DESCRIPTION OF THE INVENTION

In the figures, the same references designate identical or analogous elements.

FIGS. 1 and 2show an individual weapon equipment comprising a launcher1and one or several projectiles25intended to be projected at distance by the launcher1.

InFIG. 1, the launcher1is an individual mortar and able to be carried by the main by an operator similar to the mortar operated by the company CATHYOR ENGINEERING S.A. under the name FLY-K®.

The launcher1comprises a cylindrical barrel2along a barrel axis A. The barrel2comprises a cylindrical housing3of circular section along the barrel axis A and adapted to receive a portion of the projectile25. Alternatively, the housing3could be adapted to receive the entire projectile25. The housing3extends from a bottom4of the barrel2and opens towards the outside opposite the bottom4by a mouth5adapted to allow for a passage of the projectile25. A retaining device, in the form of one or several leaf springs6, is provided inside the housing3in order to retain the projectile25in the housing3.

A hollow launcher body7extends the barrel2on a side of its bottom4, along the barrel axis A. The launcher body7comprises in particular a launcher tube8connected to the bottom4of the barrel2by a connection interface9.

The launcher1also comprises a percussion set10involved in the projection of the projectile25. The percussion set10comprises a cylindrical launch rod11of circular section along the barrel axis A. The launch rod11extends in the housing3of the barrel2from the bottom4to a free end12arranged facing the mouth5. The free end12has a bearing surface13substantially transversal with respect to the barrel axis A, and a recess14arranged in the bearing surface13. The percussion set10comprises also a percussion device15arranged in the housing3and in the launcher tube8of the launcher body7and coupled to a control assembly19arranged in the launcher tube8of the launcher body7. The percussion device15comprises a percussion tip16mounted to be movable in the launch rod14between a retracted position, wherein the percussion tip16is located in the recess14of the free end12of the launch rod11, and a priming position, wherein the percussion tip16protrudes in relation to the bearing surface13of the free end12of the launch rod11. In particular, the percussion tip16is carried by a pin17slidably mounted along the barrel axis A inside a housing of the launch rod11. The pin17is urged to an advanced position by one or several elastic members, such as helical springs18, and retained in a rearward position by a hook20of the control assembly19placed in the launcher tube8of the launcher body7. The percussion tip16is in the priming position when the pin17is in the advanced position, and in the retracted position when the pin17is in the rearward position. The displacement of the hook20in order to release the pin17and switch the percussion tip16from the retracted position to the priming position is controlled by an actuating member of the control assembly20that can be actuated by the operator.

Opposite the barrel2, the launcher tube8of the launcher body7has an articulated leg21that makes it possible to set the launcher1on the ground, where applicable by orienting it, with the inclination of the launcher1being given by the intermediary of a clinometer22mounted on the launcher body7.

InFIG. 2, the projectile25is an explosive grenade comprising an operating head26, a body28and a tail40adjoining along a projectile axis B. The projectile25has a caliber, i.e. a maximum outer dimension, of 51 mm and a weight between 750 g and 1000 g.

The operating head26, for example of the type of rocket operated under the name FLAME by the company JUNGHANS Microtec GmbH, comprises an explosive charge and is made integral, for example by screwing, directly or, as shown inFIG. 2, by means of a spacer27, to a first end28aof the body28.

The corps28comprises a cylindrical fragment-generating sleeve29of circular section along the projectile axis B and of which a first end29aforms the first end28aof the body28. The fragment-generating sleeve29, made from steel, has an inner surface of circular section. The inner surface is provided with first grooves in the form of threads31extending substantially circumferentially, and with second grooves in the form of channels32extending substantially axially. In particular, the fragment-generating sleeve29has an outer diameter of 51 mm and an inner diameter of 45 mm and the inner surface has threads31carried out with a pitch of 4 mm and twenty to thirty channels32. Alternatively, any other arrangement of first and second grooves extending respectively according to the first and second secant directions could be provided on the inner surface of a fragment-generating sleeve29of any suitable shape.

The body28also comprises a connector35extending along the projectile axis B from a first end35aintegral, for example via screwing, with a second end29bof the fragment-generating sleeve29opposite the first end29a. The connector35has a central bore36, blind on the side of the first end35aand opened on a second end35bopposite the first end35aand forming a second end28bof the body28.

The tail40is integral with the second end28bof the body28. In particular, the tail40comprises a tube41adapted to be mounted on the launch rod11. The tube41of the projectile25, made from an aluminum alloy, has a first end41ascrewed into the bore36of the connector35of the body28, and a second end41bopposite the first end41a. The tube41also has an inner cylindrical surface42of circular section along the projectile axis B. The inner surface42has an inner diameter Di corresponding substantially to the outer diameter of the launch rod11of the launcher1. The inner diameter Di is substantially constant over a stroke c along the projectile axis B between a first location E1located in the vicinity of the first end41aof the tube41and a second location E2separate from the first location E2and located, in the embodiment shown, in the vicinity of the second end41bof the tube41. Alternatively, any other arrangement of the first location E1, of the side of the operating head26and of the second location E2at a distance from first location E1in order to define an appropriate stroke c could be provided. By way of example, the inner diameter Di of the inner surface42is between 21.5 mm and 22.5 mm, in particular 22.05 mm. The tube41has a length, measured along the projectile axis B, between 140 mm and 160 mm, in particular 150 mm, in such a way that the stroke c between the first E1and second E2locations can be between 120 mm and 110 mm, in particular 115 mm. The tube41has, moreover, a thickness e in the vicinity of the first location E1between 4.6 mm and 5 mm, in particular 4.8 mm. In the vicinity of the second end41b, an empennage43is provided on an outer surface of the tube41in order provide stability during a firing.

The first end41aof the tube41is closed in a sealed manner by a sealing element. In the embodiment shown, the sealing element has the form of a plug44arranged in a bottom37of the bore36of the connector35of the body28and in contact with the tube at its first end41a.

Opposite, a stopper element is integral with the second end41bof the tube41. The stopper element is carried out in the form of a cylindrical retaining ring45along the projectile axis B. The retaining ring45comprises a first portion46screwed onto the second end41bof the tube41and a second portion47extending the tube41beyond its second end41balong the projectile axis B. The second portion47of the retaining ring45has an inner tapered surface48of circular section converging towards the projectile axis B when moving away from the second end41bof the tube41. The second portion47of the retaining ring45as such interiorly defines a restriction49that has a diameter less than the inner diameter Di of the inner surface42of the tube41along the stroke c. An insert50can be mounted in a removable manner on the second portion47of the retaining ring45in order to close the access to the inside of the tube41before use of the projectile25.

InFIG. 2, the projectile25also comprises a piston60mounted in the tube41and positioned at the first location E1of the stroke c formed on the inner surface42of the tube42, in the vicinity of the first end41aof the tube41. The piston60comprises a transverse wall61with respect to the projectile axis B and adapted to rest on the bearing surface13of the free end12of the launch rod11. It also comprises a skirt62that extends perpendicularly to a peripheral edge of the transverse wall61towards the plug44forming sealing element. The skirt62has an outer cylindrical surface of circular section, placed in sealed contact with the inner surface42of the tube41and adapted to slide along the inner surface42of the tube41along the projectile axis B until the second location E2. The skirt62also has an inner cylindrical surface of circular section defining, with an upper surface of the transverse wall61, a recess63open towards the plug44. The recess63can in particular have a volume between 2 cm3 and 4.5 cm3, in particular 2.5 cm3. The piston60further comprises a primer64arranged in a substantially central manner in the transverse wall61is such a way as to be able to be activated by the percussion tip14in priming position when the piston60is resting on the bearing surface13of the free end12of the launch rod11. The piston60defines, with the tube41and the plug44, a hermetically-sealed propulsion chamber65of which the volume increases as the piston60is moved from the first location E1to the second location E2.

A propulsion charge70is placed in the propulsion chamber65when the piston60is at the first location E1. The propulsion charge70is adapted to be activated by the primer64of the piston60in order to move the piston60between the first E1and second E2locations. In particular, the propulsion charge70comprises between 2.4 g and 3.7 g, even between 2.4 g and 3.6 g of a powder having a heat of combustion between 3500 J/g and 4000 J/g. In the embodiment shown, the powder is entirely placed in the recess63of the piston60with a loading density between 0.9 g and 1.2 g per cm3, in particular 0.96 g per cm3. The powder can in particular be the same powder as that which is used in the grenade operated by the company CATHYOR ENGINEERING S.A. under the name Fly-K®, namely a P3T spherical powder developed by the company PB CLERMONT.

The weapon equipment according to the invention is not limited to an explosive grenade25of the type described hereinabove as a projectile. Alternatively, other projectiles of a caliber and weight compatible with the launcher1can be provided. By way of a non-limiting example,FIG. 3shows a smoke grenade25′ of which the operating head26′ and the body28′ are adapted to produce a cloud of smoke.FIG. 4shows an exercise grenade25″ of which the operating head26″ and the body28″ are adapted in order to make it possible to mark the trajectory and to mark the impact of the grenade25″ on the ground. The tail40of the projectiles25′,25″ is identical to that of the explosive grenade25described hereinabove in such a way as to be able to cooperate with the launch rod11and the percussion device15of the launcher1.

In relation withFIGS. 5 and 6, a use of the weapon equipment is described. In theFIGS. 5 and 6, only a portion in the vicinity of the free end12of the launch rod11of the launcher1is shown.

The projectile, for example the explosive grenade25ofFIG. 2, is placed in the barrel2of the launcher1by the operator after the latter has removed the insert50mounted on the retaining ring45. In particular, the projectile25is introduced by the tail40in the housing3of the barrel2through the mouth5. The tube41of the tail40slides over the launch rod11until the transverse wall61of the piston60bears against the bearing surface13of the free end12of the launch rod11. Doing this, the leaf springs6of the retaining device are deformed and are solicited back into a rest position wherein they retain the projectile25in the barrel2on the tail40, above the empennage43. The percussion tip16is in the retracted position.

In order to carry out a firing, the operator actuates the control assembly19that causes the percussion tip16to pass from the retracted position to the priming position. In this priming position, the percussion tip16activates the primer64of the piston60which, in turn, activates the propulsion charge70. The projectile25is then displaced in relation to the piston60bearing on the free end12of the launch rod11in such a way that the piston60slides from the first location E1to the second location E2where it is retained by the restriction49of the retaining ring45. The propulsion chamber65remains hermetically sealed, containing as such the flame and the smoke in order to suppress the light and reduce the noise and the heat emitted during the firing. The projectile25then leaves the barrel2of the launcher1to be protected at a distance from the launcher1and in particular at a distance ranging up to 1000 m.