RU2819118C1 - Ammunition with a cape for hitting aerial drones - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention relates to ammunition with a cape for hitting aerial drones. Ammunition with a cape for hitting aerial drones comprises a hollow body, open in front, having an imaginary longitudinal axis, a means of air blasting of an explosive charge, blowing charge, cape with weights and connecting threads. Weights are arranged around an imaginary longitudinal axis. Weights are located with their rear part inside the body. Each load is equipped with a thread. Each thread is attached to the corresponding weight by the first end. In addition, a cover with a barrel is introduced into the ammunition design. Barrel muzzle is turned backwards. Front part of the barrel is closed by means of air blasting of the expelling charge. Expelling charge is located in the barrel. Additionally, there is a cartridge consisting of a coil and a tubular piston. Tubular piston is located in front of the coil. Coil consists of coil bushing, rear and front flanges. Outer diameter of coil bushing is less than outer diameters of flanges. Through axial hole is made in the cartridge. Tubular piston is located inside the barrel. In addition, a cylindrical piston is introduced, the first end of which is connected to the housing, the second end of which is located in the axial hole of the cartridge. Area of the end face of the cylindrical piston is more than the annular area of the end face of the tubular piston. Weights are located with their front part inside the cover. In addition, a ring is introduced, which is located outside the coil bushing. Inner diameter of the ring in its expanded state is greater than the outer diameter of the coil bushing. Second end of each thread is attached to the ring. Each thread is compactly laid so that it can be straightened when pulled by its second end. Cover, barrel, coil, tubular piston, cylindrical piston are located on an imaginary longitudinal axis.

EFFECT: increased probability of aerial drone damage due to increased effective area of damage, as well as reduced time of cape straightening.

9 cl, 13 dwg

Description

The invention relates to means of combating aerial drones (unmanned aerial vehicles) by the method of their mechanical destruction. The ammunition rotates in flight, the rotation being provided by the means of its delivery to the target. The invention is applicable to counter terrorism when organizing security systems for facilities and public events in open areas.

The closest analogue of the claimed technical solution is ammunition for a grenade launcher against unmanned aerial vehicles, described in RF patent No. 2744227, publication date 03/03/2021. The device includes a hollow body, open at the front, an expelling charge and a means for its air detonation, and a cape for destroying aerial drones, consisting of weights and threads. The weights are located around the imaginary longitudinal axis of the body and are placed inside it with their rear part. Each weight is equipped with a thread, which is attached to it at its first end.

The second ends of the threads are connected to other threads that form the cape. It is located in the central part of the hollow body, behind the loads. When ammunition is fired, it begins to rotate around the longitudinal axis of the body. The rear parts of the cargo are pressed into the part of the body that is open at the front, which keeps them from flying apart. When an expelling charge is detonated in air, the weights leave the body, pulling the threads of the cape out of the body.

The disadvantage of the known ammunition is that with a moderate power of the expelling charge, after it is detonated, the cape cannot open to a large damaging area. If, in the system of spatial coordinates of the ammunition, we consider the projections of the expansion velocities of the cargo on a plane perpendicular to the imaginary longitudinal axis of the ammunition, the expansion occurs in the direction tangent to the circumference of the front part of the ammunition. Immediately after separation from the ammunition, the cape weights practically stop rotating around the axis of the body. At the same time, the body itself and the cape located in its middle and rear parts continue to rotate intensively. Pulled out by weights flying in different directions, the back of the cape turns out to be twisted, tangled and unable to open under the influence of forces from the threads connected to the weights. The effective area of destruction and the probability of hitting a target with such a cape are small. However, if you try to make the process of the cape leaving the body faster so that it does not have time to spin by placing a high-power expulsion charge, then the cape will remain in the body - the threads will break from excessive load caused by the inertia of the cape placed in the body. The use of threads of higher strength, that is, greater thickness, will require a reduction in their length in order to maintain the same volume of the cape placed in the ammunition; therefore, it will not increase the effective area and the probability of destruction.

Another disadvantage of the known ammunition is that the loads are pushed out of the ammunition and begin to fly apart in a non-optimal manner - not only to the sides, but also forward, along the imaginary longitudinal axis of the ammunition in its coordinate system. The velocity component of each load directed perpendicular to the imaginary longitudinal axis of the ammunition (i.e., to the side) is useful because it causes the threads to straighten and the cape to open. But the velocity component directed parallel to the imaginary longitudinal axis of the ammunition (i.e. forward) does not cause the cape to open. A consequence of the non-optimal direction of cargo dispersion is a relatively long opening time of the cape.

Disclosure of the Invention

The problem that this technical solution is aimed at is to prevent harm that drones can cause when they fly near ground objects and personnel. The technical result that this technical solution is aimed at achieving is to increase the probability of being hit by an aerial drone cape by increasing the effective area of destruction. An additional technical result is a reduction in the straightening time of the cape threads.

To solve the problem and achieve a technical result, the design of the known device has been changed. A known ammunition with a cape for destroying aerial drones contains a hollow body, open at the front and having an imaginary longitudinal axis, a means for air detonation of an expelling charge, an expelling charge, a cape having weights and connecting threads. The weights are located around an imaginary longitudinal axis, and their rear part is located inside the body. Each weight is equipped with a thread, which is attached to it at the first end.

Additionally, a cover with a barrel is introduced into the known ammunition, with the muzzle of the barrel facing backwards, the front part of the barrel is closed by means of air detonation of the expelling charge, and the expelling charge is located in the barrel. Additionally, a cassette was introduced, consisting of a coil and a tubular piston. The tubular piston is located at the front of the reel. The reel consists of a reel hub, rear and front flanges. The outer diameter of the coil bushing is smaller than the outer diameters of the flanges. The cassette has a through axial hole. The tubular piston is located inside the barrel. Additionally, a cylindrical piston is introduced, the first end of which is connected to the housing, the second end of which is located in the axial hole of the cassette. The end area of the cylindrical piston is greater than the annular area of the end of the tubular piston. The weights are located with their front part inside the cover. There is also an additional ring located outside the coil bushing. The inner diameter of the ring in the straightened state is larger than the outer diameter of the coil bushing. The second end of each thread is attached to a ring. Each thread is compactly laid with the possibility of straightening when pulled out by the second end. The cap, barrel, coil, tubular piston and cylindrical piston are on an imaginary longitudinal axis.

After detonating the expelling charge before the point of full opening of the cape, the tubular piston and the cylindrical piston located in it begin to move back from the cap, if the spatial coordinate system is tied to it. Moreover, the cylindrical piston moves back from the cover faster than the tubular one, due to its larger area. Thanks to the proposed design, it becomes possible to simultaneously release each load from the front and rear ends at the initial moment of opening the cape. The threads of the cape straighten out as the loads fly away, without twisting or tangling, forming a cape that is completely straightened by centrifugal forces.

In the proposed technical solution, it is possible to ensure the spread of cargo in optimal directions - only to the sides, i.e. perpendicular to the imaginary longitudinal axis of the ammunition in the ammunition coordinate system.

In addition, the cape may have at least three weights.

In addition, grooves may be provided on the interior surfaces of the body and cover parallel to the imaginary longitudinal axis such that the front portion of each weight is located in the cover groove, the rear portion of each weight is located in the housing groove, and the weights are located parallel to the imaginary longitudinal axis.

In addition, a protrusion located in the groove of the housing can be made on the outer cylindrical part of the rear flange of the coil.

In addition, a protrusion located in the groove of the cover can be made on the outer cylindrical part of the front flange of the coil.

In addition, a rear parachute may be located between the rear of the coil and the rear of the housing within the housing. In this case, the ends of the rear parachute lines must be connected to the front end of the swivel, and the rear end of the swivel must be connected to the body with a flexible connection.

In addition, a cavity can be made in the rear part of the coil, open to the body, in which the front part parachute will be located. The ends of the front parachute lines should be connected to the front end of the swivel, and the rear end of the swivel should be connected to the cassette by a flexible connection.

In addition, steel wire can be used as a cape thread.

In addition, a nylon cord can be used as a cape thread.

In the new design of the device, it is possible to increase the probability of hitting an aerial drone with a cape by increasing the effective area of destruction with a fully extended cape. Also, the new design of the device makes it possible to reduce the opening time of the cape.

Description of drawing figures

The indicated advantages of the invention, as well as its features, are explained by the best embodiments with reference to the drawings.

Fig. 1 shows a longitudinal section of ammunition with a cape for destroying aerial drones in the state before the air detonation of the expelling charge. The ammunition is the head part of the “shot” of a hand-held anti-tank grenade launcher. The means of delivering ammunition to the target is depicted with the stabilizer feathers open. The starting powder charge is not shown.

Fig. 2 shows a cross-section of the ammunition shown in FIG. 1. The section passes through the stowed cape weights and the cassette bushing.

Fig. 3 shows a cross-section of the ammunition shown in FIG. 1. The section passes between the stowed cape weights and the front flange of the cassette.

Fig. 4 shows a longitudinal section of the cape weight with the thread laid inside.

Fig. 5 - front view of the cape with a straightened elastic ring in the phase of spreading of loads. The arrows show the directions of expansion.

Fig. 6 shows a longitudinal section of a “shot” of an under-barrel grenade launcher, containing in the front part ammunition with a cape for destroying aerial drones in the state before being fired from a grenade launcher.

Fig. 7 is a cross-sectional view of the ammunition shown in FIG. 6. The section passes between the stowed cape weights and the front flange of the cassette.

Fig. 8 is a longitudinal section through the caped drone munition shown in FIG. 1, after the air detonation of the expelling charge, the release of the cape weights from the cassette and the beginning of their scattering. The ammunition is the head part of the “shot” of a hand-held anti-tank grenade launcher. The arrows show the directions of movement of the components.

Fig. 9 is the first frame of a schematic sequence depicting the operation of a caped munition to defeat aerial drones. The ammunition (as part of the “shot” of a hand-held anti-tank grenade launcher) flies up to the target - an aerial drone - to destroy it.

Fig. 10 is the second frame of a schematic sequence depicting the operation of the ammunition. The expelling charge is detonated, the cape weights fly apart, the stowed parachute of the rear part falls out of the body, and the stowed parachute of the front part falls out of the rear part of the reel.

Fig. 11 is the third frame of a schematic sequence depicting the operation of the ammunition. The weights flew apart, completely straightening the threads of the cape. Two threads came into contact with the drone's body and began to wrap around it from above. The parachute at the rear of the ammunition is deployed and deployed. The parachute of the front part of the ammunition expands.

Fig. 12 is the fourth frame of a schematic sequence depicting the operation of the ammunition. The threads of the cape are wrapped around the body of the drone. Some of the weights hit the body and propellers of the drone. The drone has lost its functionality and is crashing. The rear and front parts of the ammunition are lowered down by their parachutes.

Fig. 13 shows a longitudinal section of ammunition with a cape for destroying aerial drones after the air detonation of the expelling charge, the release of the cape weights from the cassette and the beginning of their dispersion. The ammunition is the head part of the “shot” of the under-barrel grenade launcher shown in Fig. 6 and 7. The powder charge burns, creating a whistle and a smoke trail.

Best Mode for Carrying Out the Invention

Ammunition with a cape for defeating aerial drones, shown in Fig. 1, contains a hollow body 1. The body 1 is open at the front and has an imaginary longitudinal axis 2. At the front, the body 1 is closed by a lid 3, into which a barrel 4 is built. The barrel 4 is a strong metal cylinder. The barrel 5 of the barrel 4 is facing backwards. In the muzzle 5 there is a narrowing of the barrel.

A means of air detonation of the expelling charge is screwed into the front part of the barrel 4, which is the remote tube 6 of an artillery shell, known from the prior art. An integral part of the spacer tube 6 is a spacer ring 7 with a scale. In the barrel 4, near the spacer tube 6, there is a powder expelling charge 8. Also inside the barrel 4 there is a tubular piston 9 with a round nut 10 screwed onto the front end. The round nut 10 has a slot at the end. The tubular piston 9 is made with the ability to slide in the direction of the imaginary axis 2 in the narrowing of the barrel in the barrel 5. The round nut 10 is made with the ability to slide in the direction of the imaginary axis 2 in the barrel 4. In the barrel 4 and the cover 3 there are holes 15 connecting the internal volume of the barrel 4 with the inner cavity of the cover 3. In the inner cavity of the cover 3 there are flammable compounds: to create a bright light trail 16 and to create colored smoke 17.

The tubular piston 9 is an integral part of the cassette, which also includes a coil 18. The coil 18, in turn, consists of a sleeve 19, rear 20 and front 21 flanges. The outer diameter of the sleeve 19 is smaller than the outer diameters of the flanges 20 and 21.

Twenty-four cape weights 26 are located on the cylindrical surface of the sleeve 19. The weights 26 (Figs. 1 and 2) are located with their rear part inside the housing 1 in grooves 27 made on the inner surface of the housing 1 around an imaginary longitudinal axis 2 parallel to it. Also, the weights 26 (Figs. 1 and 3) are located with their front part inside the cover 3 in grooves 28 made on the inner surface of the cover 3 parallel to the imaginary longitudinal axis 2. The weights 26 are located parallel to the imaginary longitudinal axis 2.

On the outer cylindrical part of the rear flange 20 of the reel 18 there are protrusions 30 located in the corresponding grooves 27 of the body 1. Also on the outer cylindrical part of the front flange 21 of the reel 18 there are protrusions 31 located in the corresponding grooves 28 of the cover 3.

Each weight 26 is provided with a thread 32 (Fig. 4). Thread 32 is steel wire. Each thread 32 is attached to the corresponding weight 26 by the first end 33. A ring 34 is located outside the cassette sleeve (Fig. 1, 3, 4, 5). Ring 34 is made of flexible material - hardened carbon steel wire. The inner diameter of the ring 34 in the straightened state is larger than the outer diameter of the sleeve 19 of the coil 18 (Fig. 1). The second end 35 (Figs. 4 and 5) of each thread 32 is attached to a ring 34. Inside each weight 26 there is a hole 36. Each thread 32 is laid inside the hole 36 of the weight 26 in a spiral in two layers.

The cassette has a through axial hole 25, in which there is a cylindrical piston 40. The end area of the cylindrical piston 40 is larger than the annular area of the end of the tubular piston 9. The first end of the cylindrical piston 40 is connected to the housing 1 by a screw 41, its second end is located in the axial hole 25 of the cassette.

Between the rear part of the reel 18 and the rear part of the body 1, a parachute of the rear part 45 is located inside the body. An elastic ring 44 is fixed along the perimeter of the lower part of the parachute canopy. The ends of the lines 47 of the parachute of the rear part 45 are connected to the front end of the swivel 46. The rear end of the swivel 46 is connected to body 1 cable 48.

In the rear part of the reel 18 there is a cavity open to the body 1, in which the stowed parachute of the front part 50 is located. An elastic ring 51 is fixed along the perimeter of the lower part of the parachute canopy. The ends of the lines 52 of the parachute of the front part 50 are connected to the front end of the swivel 53. The rear end of the swivel 53 is connected to the cassette by cable 54. Cover 3, barrel 4, coil 18, tubular piston 9, cylindrical piston 40 are located on an imaginary longitudinal axis 2. The junction of body 1 and cover 3 is covered with an easily torn sealing tape 55 with an adhesive layer.

The means of delivering ammunition to the target is a jet engine with a starting powder charge. It consists of a nozzle block 60, a reactive powder charge 61, a stabilizer with feathers 62, and a turbine 63. The starting powder charge is not shown. The stabilizer feathers 62 are shown open.

There is a simpler design of ammunition with a cape for destroying aerial drones. The ammunition is part of the “shot” of the under-barrel grenade launcher and is located in its front part. The ammunition contains a hollow body 1 (Fig. 6). The housing 1 is open at the front and has an imaginary longitudinal axis 2. At the front, the housing 1 is closed by a lid 3, into which a barrel 4 is made. The barrel 4 is a calibrated axial hole. The barrel 5 of the barrel 4 is facing backwards.

A means of air detonation of the expelling charge is screwed into the front part of the barrel 4 - a remote tube 6 of an artillery shell, known from the prior art. It also serves as a nose cone. Remote tube 6 is configured by the manufacturer to detonate the expelling charge at a certain time after firing the ammunition. The horizontal distance, after which the cape becomes fully extended, is indicated on the external distance tube 6. In the barrel 4 near the spacer tube 6 there is a powder expelling charge 8. Also inside the barrel 4 there is a tubular piston 9. In the barrel 4 there is a hole 15 connecting the internal volume of the barrel 4 with the internal cavity 42 of the lid 3. In the internal cavity 42 of the lid 3 there is a flammable composition to create colored smoke 17. The color of the smoke corresponds to the detonation time of the expelling charge 8 determined by the ammunition manufacturer after firing for a given remote tube. In body 3 there is a cutout 70 to create a whistling sound when the composition for creating colored smoke 17 burns. The cutout 70 is closed with a plug 79.

The tubular piston 9 is an integral part of the cassette, which also includes a coil 18. The coil 18, in turn, consists of a sleeve 19, rear 20 and front 21 flanges. The cassette is made of duralumin.

On the cylindrical surface of the sleeve 19 there are eight cape weights 26. The weights 26 (Figs. 6 and 7) are located with their rear part inside the housing 1 in grooves 27 made on the inner surface of the housing 1 around an imaginary longitudinal axis 2 parallel to it. Also, the weights 26 are located with their front part inside the cover 3 in grooves 28 made on the inner surface of the cover 3 parallel to the imaginary longitudinal axis 2. The weights 26 are made of carbon hardened steel and are located parallel to the imaginary longitudinal axis 2.

On the outer cylindrical part of the rear flange 20 of the reel 18 there are protrusions 30 located in the corresponding grooves 27 of the body 1. Also on the outer cylindrical part of the front flange 21 of the reel 18 there are protrusions 31 located in the corresponding grooves 28 of the cover 3.

Each weight 26 is equipped with a thread 32. Thread 32 is a nylon cord. Each thread 32 is attached to a corresponding weight 26 by a first end 33 (FIG. 4). Outside the cassette sleeve there is a ring 34 (Fig. 4 and 7). The second end 35 (Fig. 4) of each thread 32 is attached to a ring 34. Inside each weight 26 there is a hole 36. Each thread 32 is compactly laid inside the hole of the weight 26 with the possibility of straightening when it is pulled out by the second end. The cassette has a through axial hole 25 (Fig. 6), in which there is a cylindrical piston 40. The first end of the cylindrical piston 40 is connected to the body 1 by thread 71, its second end is located in the axial hole 25 of the cassette. The body 1 and the cover 3 are sealed around the circumference with a rubber ring 72. At the first end of the cylindrical piston 40 there is a blind axial hole filled with a tracer composition with beam ignition 69.

The means of delivering ammunition to the target is a chamber 73, fixed in the rear part of the housing 1, filled with a powder propellant charge 74 with a primer 75. In the rear wall of the chamber 73 there are holes 76 for the exit of jets of powder gases. For rotation along the flight path, a belt 77 with leading protrusions corresponding to the spiral rifling in the grenade launcher barrel is used. To fix the body 1 of the ammunition in the barrel of the under-barrel grenade launcher before firing, a groove 78 is provided.

The device works as follows. The ammunition shown in FIG. 1, are fired in the direction of the air drone 80 (Fig. 9) with the correct choice of the point of full expansion of the cape (set by rotating the distance ring 7 (Fig. 1) to the desired value on the scale) and the aiming point. When fired, the ammunition begins to rotate in flight. In this case, each load 26 is subject to a centrifugal force, pressing its rear part into the corresponding groove 27 of the body 1, and the front part into the corresponding groove 28 of the cover 3. At the designated point of the ammunition flight path directly in front of the drone, the cape must be completely open. To do this, at some distance to this point, the remote tube 6 is triggered, creating a beam of fire directed at the expelling charge 8 and detonating it. The expelling charge 8 creates excess gas pressure 83 in the barrel 4 (Fig. 8).

The tubular piston 9 and the cylindrical piston 40 located in it, under the influence of gas pressure 83 in the barrel 4, begin to move backward from the cover 3, if the spatial coordinate system is tied to it. Before this movement begins, the sealing tape 55 breaks. Moreover, the cylindrical piston 40 moves back from the cover 3 faster than the tubular piston 9, due to its larger area. Since the cylindrical piston 40 is connected to the body 1, the body 1 also moves backwards from the cover 3, opening more and more weights 26. Likewise, the cassette, consisting of a coil 18 and a cylindrical piston 9, also moves backwards from the cover 3, opening more and more least loads 26.

There comes a moment when the body 1 and the cover 3 release the weights 26 along with the threads of the cape 32 completely (Fig. 8), and under the influence of centrifugal forces they begin to fly apart perpendicular to the imaginary longitudinal axis of the ammunition 2. The threads of the cape 32 begin to come out of the holes 36 ( Fig. 4, 10) in weights 26 and straighten as the weights 26 fly away, without twisting or getting tangled, forming a cape completely straightened by centrifugal forces.

The flight speed of each load 26 (Fig. 4) in the direction perpendicular to the direction of flight of the ammunition gradually decreases. This occurs due to the work expended by the tension force of each thread 32 on its own straightening from the hole 36 in each load 26. Since the tension force of the thread 32 is also applied to the load, the work of this force constantly reduces the speed of expansion of the load 26. Straightening of the thread 32 and expansion of the load 26 occurs to the first end of the thread 33 attached to the load 26.

The round nut 10 (Fig. 8) at the front end of the tubular piston 9 stops at the narrowing of the barrel in the barrel 5, preventing the cover 9 and the cassette, together with the coil 18, from being separated from each other. Moving back along with the tubular piston 9, the round nut 10 opens the holes 15, connecting them with the space of the barrel 4, in which the expelling charge burns. Beams of fire from the barrel 4, penetrating through the holes 15 to the flammable compounds to create a bright light trail 16 and to create colored smoke 17, ignite them. When these compositions burn 86, they form a noticeable mark on the sky both in the light and in the dark. Using this trail, it is much easier for other shooters to notice an aerial drone and hit it if this was not possible with the first shot.

Under the influence of excess gas pressure in the barrel 4, the cylindrical piston 40, moving backward, leaves the hole 25 in the coil 18. The stowed parachute of the rear part 45, not being fixed in the internal cavity of the housing 1, with a sharp movement of the piston 40 and the housing 1 backwards, falls out of the housing 1 (Fig. 8, 10), straightens (Fig. 11), the elastic ring 44 (Fig. 8) opens its dome (Fig. 12). The rotation of the body 1 with the cylindrical piston 40 and the means of delivering ammunition to the target is not transmitted to the parachute canopy of the rear part 45 thanks to the swivel 46 (Fig. 8).

The stowed parachute of the front part 50, not being secured in the internal cavity of the coil 18, when the tubular piston 9 suddenly stops at the narrowing of the barrel 4 in the muzzle 5, falls back (Fig. 8, 10), straightens out (Fig. 11). The elastic ring 51 opens the dome (Fig. 12). The rotation of the cover 3 with the remote tube 6 and the cassette is not transmitted to the parachute canopy of the front part 50 thanks to the swivel 53 (Fig. 8).

In fig. 11 shows how, after the cape flew up to the aerial drone 80, its two threads 81 and 82 touched the body and began to cover the drone 80 from above. The drone 80 moves in the direction of movement of the cape and overturns due to force. The remaining weights 26 and the threads 32 of the cape, under the influence of forces transmitted to them from the ring 34, begin to move towards the drone 80. This movement ends with some weights 26 hitting the body and propellers of the drone 80, damaging them (Fig. 12). Also, the threads of the cape 32 are wound around the drone 80 from the top, sides and bottom. Drone 80 becomes inoperable and crashes. The rear and front parts of the ammunition fall down on their parachutes 45 and 50, without causing harm to personnel, mobile equipment and ground objects.

In an aircraft-type aerial drone, in the event of such damage from ammunition, the threads of the cape 32 are wrapped around its aerodynamic surfaces and block the rotation of the air rudders located on them. As a result, a drone, even one weighing hundreds of kilograms, loses the ability to control and carry out its mission.

A simpler design of ammunition with a cape for destroying aerial drones, which is part of the “shot” of an under-barrel grenade launcher, works as follows. The shooter determines the distance to the aerial drone visually or using a rangefinder. It then adjusts it upward based on the drone's altitude. This adjustment is made based on previous shooting experience or using a ballistic calculator that may be built into the rangefinder. Based on a certain distance value, the shooter selects ammunition with the corresponding marking on the body of the remote tube 6 from among the ammunition he has. If ammunition with the required distance value is not available, the shooter chooses ammunition with a lower value, taking into account that the cape flying when opened is capable of hitting a drone at a distance of several tens of meters.

The shooter then loads ammunition into the grenade launcher, selects an aiming point in front (in the case of a moving drone) and above the drone, and fires. The firing pin of the underbarrel grenade launcher breaks the primer 75 (Fig. 6). A ray of fire from it ignites the powder propellant charge 74 with the formation of powder gases. Excessive pressure is created in chamber 73, the gases come out into the part of the grenade launcher barrel closed by the ammunition through holes 76. The excess pressure of the powder gases formed in the grenade launcher barrel throws the ammunition forward towards the target. The leading protrusions of the belt 77, sliding in the rifling of the grenade launcher barrel, twist the ammunition around an imaginary longitudinal axis 2. Burning, the powder propellant charge 74 ignites the tracer composition with beam ignition 69. Thanks to this, in flight the ammunition leaves a bright trace to the point of deployment.

The ammunition begins to rotate in flight. In this case, each load 26 is subject to a centrifugal force, pressing its rear part into the corresponding groove 27 of the body 1, and the front part into the corresponding groove 28 of the cover 3. At the designated point of the ammunition flight path directly in front of the drone, the cape must be completely open. To do this, at some distance to this point, the remote tube 6 is triggered, creating a beam of fire directed at the expelling charge 8 and detonating it. The expelling charge 8 creates an excess gas pressure 83 in the barrel 4 (Fig. 13).

The tubular piston 9 and the cylindrical piston 40 located in it, under the influence of gas pressure 83 in the barrel 4, begin to move backward from the cover 3, if the spatial coordinate system is tied to it. Moreover, the cylindrical piston 40 moves back from the cover 3 faster than the tubular piston 9, due to its larger area. Since the cylindrical piston 40 is connected to the body 1, the body 1 also moves backwards from the cover 3, opening more and more weights 26. Likewise, the cassette, consisting of a coil 18 and a cylindrical piston 9, also moves backwards from the cover 3, opening more and more least loads 26.

There comes a moment when the body 1 and the cover 3 release the weights 26 along with the threads of the cape 32 completely (Fig. 13), and under the influence of centrifugal forces they begin to fly apart perpendicular to the imaginary longitudinal axis of the ammunition 2. The threads of the cape 32 begin to come out of the holes 36 ( Fig. 4) in the weights 26 and straighten as the weights 26 fly apart, without twisting or getting tangled, forming a cape completely straightened by centrifugal forces.

Moving backward, the tubular piston 9 (Fig. 13) connects the hole 15 with the space of the barrel 4, in which the expelling charge 8 burns. A ray of fire from the barrel 4, penetrating through the hole 15 into the internal cavity 42 to the flammable composition for creating colored smoke 17, ignites his.

Gas 85, generated by combustion 86 of the composition to create colored smoke 17, creates excess pressure inside the internal cavity 42, squeezes out the plug 79 and exits through the cutout 70. This creates a whistling sound. This sound attracts the attention of personnel, making it easier to target in case of a miss.

The highly flammable colored smoke composition 17, when burned, produces a noticeable smoke trail 84 in the sky. Using this trail, it is much easier for other shooters to notice an aerial drone and hit it if this was not possible with the first shot.

Personnel on the ground who hear a whistling sound from the sky after a shot at a drone can manage to hide behind cover from falling ammunition parts or, at a minimum, cover their heads with a durable object of sufficient area and turn sideways towards the falling parts. This will reduce the likelihood of an accident.

Due to the accumulated inertia, the cassette, consisting of a tubular piston 9 and a coil 18, after detonating the expelling charge 8, moving backwards, leaves the barrel 4. The ring 34, the perimeter of which in the straightened state is less than the outer diameter of the flanges 20 and 21, holds the rotating around an imaginary longitudinal axis 2 cassette included in the cape.

Likewise, moving rearward, the cylindrical piston 40 leaves the hole 25 in the cassette spool 18. The cylindrical piston 40, the means of delivering ammunition to the target connected to it and the body 1 continue to move towards the target, but at a lower speed than that of the cape with a cassette, being at this stage an additional damaging factor of the ammunition.

The cassette, having a slightly larger mass than the total mass of weights and threads, also has greater drag on the air flow in the direction of the target. Therefore, its flight speed is approximately equal to the speed of the loads in the direction of the target. It more than doubles the total mass of the cape. It also rotates inside the translationally moving ring 34. Its rear flange 20 slides along the ring 34, preventing it from moving backward relative to the weights and the cassette.

When the cape moves towards the target, the threads 32 bend under the pressure of the oncoming air flow. Each load 26 is acted upon by a force from the thread 32. The projection of this force onto the perpendicular to the direction of flight, passing through the load 26, causes the inevitable “closing” of the cape - a decrease in the effective area and the probability of hitting the target. The presence of a massive cassette in the center of the cape in the form of a kind of support for ring 34 approximately halves the magnitude of this force projection and proportionally slows down the time of “closing” the cape. This makes it possible to reduce the requirement for accuracy in determining the distance to the point of full expansion of the cape before firing.

The cover 3 and the remote tube 6, after being separated from the body 1 and the cassette, continue to move towards the target, but at a higher speed than that of the cape with a cassette, being an additional damaging factor of the ammunition.

When the threads 32 of the cape hit the air drone, it shifts in the direction of movement of the cape and overturns due to force. The remaining weights 26 and threads 32 of the cape, under the influence of forces transmitted to them from the ring 34, begin to move towards the drone, covering it from all sides. This movement ends with some of the weights 26, as well as the cassette, hitting the body and propellers of the drone, damaging them. The drone becomes inoperable and crashes.

If the cape misses or opens at the wrong point in the trajectory (after the drone or long before it), the shooter selects a second ammunition and fires a second shot, if the drone has not left the affected area during this time. The second shot at the drone can be carried out by another shooter, whose target designation and marking of ammunition was provided by the first shooter using a tracer, smoke 84 of a certain color and the whistling sound from the ammunition of the first shot.

The claimed device can be used on an ongoing basis to counter terrorism while ensuring the security of facilities (including airports and stadiums) and public events in open areas. Temporarily, during military operations, it can also be used in combat. When repelling an attack from a swarm of aerial drones, the device is used to fire a remote-controlled automatic weapon coupled with a fire control system. It is most successfully applied to drones that have a flight program that can be executed without radio control by the operator and without the use of radio navigation systems.

The invention has been described above with reference to specific embodiments thereof. Other embodiments of the invention that do not change its essence as disclosed in the present description may be obvious to those skilled in the art. Accordingly, the invention should be considered limited in scope only by the following claims.

Claims (9)

1. Ammunition with a cape for destroying aerial drones, containing a hollow body, open at the front, having an imaginary longitudinal axis, a means of air detonation of an expelling charge, an expelling charge, a cape having weights and connecting threads, the weights are located around an imaginary longitudinal axis, the weights are located at its rear part inside the body, each load is equipped with a thread, each thread is attached to the corresponding load at the first end, characterized in that a cover with a barrel is additionally inserted, the barrel barrel is facing back, the front part of the barrel is closed by means of air detonation of the expelling charge, the expelling charge is located in the barrel, additionally a cassette has been introduced, consisting of a coil and a tubular piston, the tubular piston is located in front of the coil, the coil consists of a coil bushing, rear and front flanges, the outer diameter of the coil bushing is smaller than the outer diameters of the flanges, a through axial hole is made in the cassette, the tubular piston is located inside the barrel, additionally a cylindrical piston is introduced, the first end of which is connected to the body, the second end of which is located in the axial hole of the cassette, the end area of the cylindrical piston is greater than the annular area of the end of the tubular piston, the weights are located with their front part inside the cover, an additional ring is inserted, located outside the coil bushing, the internal diameter the rings in its straightened state are larger than the outer diameter of the spool bushing, the second end of each thread is attached to the ring, each thread is compactly laid with the possibility of straightening when pulled by the second end; the cap, barrel, coil, tubular piston, cylindrical piston are on an imaginary longitudinal axis. 2. Ammunition according to claim 1, characterized in that the cape has at least three weights. 3. Ammunition according to claim 1, characterized in that grooves are made on the inner surfaces of the body and cover, parallel to the imaginary longitudinal axis, the front part of each load is located in the groove of the cover, the rear part of each load is located in the groove of the body, the weights are located parallel to the imaginary longitudinal axis . 4. Ammunition according to claim 1, characterized in that there is a protrusion on the outer cylindrical part of the rear flange of the reel, the protrusion is located in a groove in the housing. 5. Ammunition according to claim 1, characterized in that there is a protrusion on the outer cylindrical part of the front flange of the reel, the protrusion is located in the groove of the cover. 6. Ammunition according to claim 1, characterized in that between the rear part of the reel and the rear part of the body, a parachute of the rear part is located inside the body, the ends of the parachute lines of the rear part are connected to the front end of the swivel, the rear end of the swivel is connected to the body by a flexible connection. 7. Ammunition according to claim 1, characterized in that in the rear part of the reel there is a cavity open to the body, in the cavity there is a front part parachute, the ends of the front part parachute lines are connected to the front end of the swivel, the rear end of the swivel is connected to the cassette by a flexible connection. 8. Ammunition according to claim 1, characterized in that steel wire is used as the thread of the cape. 9. Ammunition according to claim 1, characterized in that a nylon cord is used as a cape thread.