RU2819117C1 - Ammunition with a cape for hitting flying drones - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention relates to ammunition with a cape for hitting flying drones. Ammunition with a cape for hitting flying drones comprises a 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 cartridge is introduced into the ammunition design. Cartridge includes a bushing, rear and front flanges. Outer diameter of the bushing is less than the outer diameters of the flanges. On an imaginary longitudinal axis in the cartridge there is a running hole. In addition, a cover with a front piston is introduced. Front end of front piston is fixed in cover. Rear end of the front piston is located in the running hole of the cartridge. Additionally, rear piston is introduced. Rear end of rear piston is fixed in housing. Front end of the rear piston is located in the running hole of the cartridge. Blow-out charge is located in the running hole of the cartridge between the rear end of the front piston and the front end of the rear piston. Weights are located with their front part inside the cover. In addition, a ring is introduced, which is located outside the bushing of the cartridge. Inner diameter of the ring in the expanded state is greater than the outer diameter of the cartridge 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, cartridge, front and rear pistons are located on imaginary longitudinal axis.

EFFECT: increasing the probability of the flying drone hitting by the cape owing to increasing the effective hitting area, as well as reducing the time of the cape straightening.

9 cl, 13 dwg

Description

The invention relates to means of combating flying 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 body open at the front, an expelling charge and a means for its air detonation, and a cape for destroying flying drones, consisting of weights and threads. The weights are located around the imaginary longitudinal axis of the body, and their rear part is placed inside it. 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 flying drones contains a 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 cassette is inserted into the known ammunition. The cassette includes a bushing, rear and front flanges. The outer diameter of the sleeve is smaller than the outer diameters of the flanges. There is a running hole in the cassette on an imaginary longitudinal axis. A cover with a front piston is also additionally introduced, the front end of the front piston being fixed in the cover, and its rear end located in the running hole of the cassette. A rear piston is also additionally introduced, with its rear end fixed in the housing, and its front end located in the running hole of the cassette. The ejector charge is located in the cassette bore between the rear end of the front piston and the front end of the rear piston.

The weights are located with their front part inside the cover. There is also an additional ring located outside the cassette sleeve. The inner diameter of the ring in the straightened state is larger than the outer diameter of the cassette 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 cover, cassette, front and rear pistons are located on an imaginary longitudinal axis.

After the expelling charge is detonated before the point of full deployment of the cape, the rear piston begins to move back from the cassette, if the spatial coordinate system is tied to it. And the front piston begins to move forward from the cassette. 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 portion of the cassette and the rear portion 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 cassette, open to the body, in which the front part parachute will be located. The ends of the front parachute line 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 link.

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 a cape hitting a flying drone by increasing the effective area of damage 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 illustrated by the best embodiments with reference to the drawings.

Fig. 1 shows a longitudinal section of ammunition with a cape for destroying flying 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 dispersal 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 flying 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 munition for engaging flying drones 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 flying drones. The ammunition (as part of the “shot” of a hand-held anti-tank grenade launcher) flies up to the target - a flying 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 casing, and the stowed parachute of the front part falls out of the rear part of the cassette.

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 flying 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.

The best embodiment of the invention. Ammunition with a cape for defeating flying 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 cover 3. In the front part of the cover 3, a means of air detonation of the expelling charge is fixed, which is the electric remote tube 6 of an artillery shell with an electric igniter 13, known from the prior art. An integral part of the spacer tube 6 is a spacer ring 7 with a scale. The front piston 11 is located on the imaginary longitudinal axis 2, its front end is fixed in the cover 3.

Inside the housing 1 and cover 3 there is a cassette 18. The cassette includes 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. On the imaginary longitudinal axis 2 in the cassette 18 there is a bore hole 25. In the front part of the bore hole 25 there is a narrowing 4. In the narrowing 4 there is a through relief groove 5. The rear end of the front piston 11 is located in running hole 25 of the cassette 18. At the front end of the front piston 11 there is a round nut 10 with an end slot screwed on, which is designed to move longitudinally together with the front piston 11 in the running hole 25. In the front part of the cassette 18 there is a tubular part 9 protruding inside the cover 3. The tubular part 9 has through radial holes 15.

In the housing 1, the rear piston 40 is fixed at its rear end. Its front end is located in the bore hole 25 of the cassette 18. In the bore hole 25 of the cassette 18 there is also a powder expelling charge 8. In the internal cavity of the cover 3 there are flammable compounds: to create a bright light trail 16 and to create colored smoke 17. The lid has radial holes 14 opposite these compositions.

On the cylindrical surface of the sleeve 19 between the rear 20 and front 21 flanges, twenty-four cape weights 26 are placed parallel to the imaginary longitudinal axis 2. 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.

On the outer cylindrical part of the rear flange 20 of the cassette 18 there are protrusions 30 located in the corresponding grooves 27 of the housing 1. Also on the outer cylindrical part of the front flange 21 of the cassette 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 cassette 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.

Between the rear part of the cassette 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 the body 1 cable 48.

In the rear part of the cassette 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, cassette 18, front piston 11, rear 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 flying 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 body 1 is open at the front and has an imaginary longitudinal axis 2, on which the front piston 11 is located, its front end is fixed in the cover 3. The head fairing 39 is also attached to the cover 3.

Inside the housing 1 and cover 3 there is a cassette 18. The cassette includes 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. On the imaginary longitudinal axis 2 in the cassette 18 there is a bore hole 25. The rear end of the front piston 11 is located in the bore hole 25 of the cassette 18. In the front part of the cassette 18 there is a tubular part 9 protruding inward covers 3. Cassette 18 is made of duralumin.

In the housing 1, with its rear end on the thread 71, the rear piston 40 is fixed. Its front end is located in the bore hole 25 of the cassette 18. In the rear piston 40 there is an axial hole filled with a powder composition, forming a powder tube 38. In the bore hole 25 of the cassette 18 there is a powder knockout charge 8.

In the internal cavity 42 of the cover 3 there is a flammable composition for creating colored smoke 17. The color of the smoke corresponds to the time of detonation of the expelling charge 8 determined by the ammunition manufacturer after the shot for a given remote tube. In the 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. A radial hole 15 is made in the inner partition of the lid 3. A discharge hole 29 is also made in the inner partition of the lid 3.

On the cylindrical surface of the sleeve 19 of the cassette 18 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 cassette 18 there are protrusions 30 located in the corresponding grooves 27 of the housing 1. Also on the outer cylindrical part of the front flange 21 of the cassette 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 body 1 and the cover 3 are sealed around the circumference with a rubber ring 72. The means of delivering ammunition to the target is a chamber 73, fixed in the rear part of the body 1, filled with a powder propellant charge 74 with a capsule 75. The capsule 75, the powder propellant charge 74 and the powder tube 38 form a fire chain for igniting the powder expelling charge 8. The horizontal distance, after passing which the cape becomes fully extended, is indicated on the outside of the head fairing 39. 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 is fired in the direction of the flying drone 80 (Fig. 9) with the correct selection of the full opening of the cape (set by rotating the distance ring 7 (Fig. 1) to the desired value on the scale) and the aiming point. After the shot, 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 a certain distance to this point, the remote tube 6 is triggered, causing ignition of the electric igniter 13 and the expelling charge 8. The expelling charge 8 creates an excess gas pressure 83 in the passage hole 25 (Fig. 8).

The rear piston 40, under the influence of gas pressure 83, begins to move backward from the cassette 18, if the spatial coordinate system is tied to it. And the front piston 11 begins to move forward from the cassette 18. Before this movement begins, the sealing tape 55 breaks. Since the rear piston 40 is connected to the body 1, the body 1 also moves backward from the cassette 18, revealing more and more weights 26. Likewise, the cover 3 , to which the front piston 11 is connected, moves forward from the cassette 18, increasingly opening the weights 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, 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 the loads 26 and straighten as the loads 26 fly apart, 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 rear end of the front piston 11 rests against the narrowing 4 of the passage hole 25 when the front piston 11 with the cover 3 moves forward, thereby preventing the cassette 18 and the cover 3 from being separated from each other. The radial holes 15 are opposite the radial holes 14. With this position of the holes, the space of the passage hole 25, in which the expelling charge 8 burns, is connected to the internal cavity of the cover 3. Rays of fire penetrate through the holes 15 and 14 to the flammable compositions to create a bright light trail 16 and to create colored smoke 17 by igniting 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 running hole 25, the rear piston 40, moving backward, leaves the hole 25 in the cassette 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 housing 1 backwards, falls out of 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 rear 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 falls back (Fig. 8, 10), not being secured in the internal cavity of the cassette 18, from a sharp blow of the round nut 10 into the narrowing 4 and a jerk of the cassette 18 forward, after which it 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 18 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 approached the flying 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 a flying aircraft-type 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 flying drones, which is part of the “shot” of an under-barrel grenade launcher, works as follows. The shooter determines the distance to the flying 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, spin the ammunition around an imaginary longitudinal axis 2. The ammunition begins to rotate in flight. The rear end of the powder tube 38 is ignited by the burning powder propellant charge 74.

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. Therefore, at some distance before this point, the fire in the powder tube 38 reaches the expelling charge 8 and ignites it. The expelling charge 8, burning, creates an excess pressure of gases 83 in the passage hole 25 (Fig. 13).

The rear piston 40, under the influence of gas pressure 83, begins to move backward from the cassette 18 (Fig. 1), if the spatial coordinate system is tied to it. And the front piston 11 begins to move forward from the cassette 18. Since the rear piston 40 is connected to the body 1, the body 1 also moves backward from the cassette 18, increasingly revealing the weights 26. Likewise, the cover 3, to which the front piston 11 is connected, moves forward from the cassette 18, opening more and more loads 26. At some point in time, the tubular part 9 of the cassette 18 opens the radial hole 15 for a beam of fire from the passage hole 25 to the flammable composition to create colored smoke 17. Combustion 86 begins in the composition 17 ( Fig. 13).

Then 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, 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 loads 26 and straighten as the loads 26 fly apart, without twisting or getting tangled, forming a cape completely straightened by centrifugal forces.

Gas 85 (Fig. 13), formed during 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 25 happening.

At a certain point in time, after ignition of the expelling charge, the cassette 18 is disconnected from the front piston 11, the cover 3 and the head fairing 39. 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 cassette 18 in rotating around 30 of the imaginary longitudinal axis 2 center of the cape.

Similarly, moving backward, the rear piston 40 leaves the hole 25 in the cassette 18. The rear 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 the cassette 18, being on at this stage with an additional damaging factor of 35 ammunition.

Cassette 18, having a slightly greater mass than the total mass of weights 26 and threads 32, 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 26 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 26 and the cassette 18.

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 18 in the center of the cape in the form of a kind of support for the 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 with the parts attached to it, after being separated from the body 1 and the cassette 18, continues to move towards the target, but at a higher speed than the cape with the cassette, being an additional damaging factor of the ammunition.

When threads 32 of the cape hit a flying 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 smoke 84 of a certain color and the whistling sound from the ammunition of the first shot.

Use in industry. 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 flying 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 flying drones, containing a 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 the rear inside the body, each weight is equipped with a thread, each thread is attached to the corresponding weight at the first end, characterized in that a cassette is additionally inserted, the cassette includes a sleeve, rear and front flanges, the outer diameter of the sleeve is less than the outer diameters of the flanges, on an imaginary longitudinal axis in the cassette a bore hole is made, a cover with a front piston is additionally inserted, the front end of the front piston is fixed in the cover, the rear end of the front piston is located in the bore hole of the cassette, a rear piston is additionally inserted, the rear end of the rear piston is fixed in the housing, the front end of the rear piston is located in the bore hole cassettes, the expelling charge is located in the running hole of the cassette between the rear end of the front piston and the front end of the rear piston, the weights are located with their front part inside the cover, an additional ring is inserted located outside the cassette bushing, the inner diameter of the ring in the straightened state is greater than the outer diameter of the cassette bushing, the second the end of each thread is attached to a ring, each thread is compactly laid out with the possibility of straightening when it is pulled out by the second end, the lid, cassette, front and rear pistons are located 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 cassette and the rear part of the body inside the body there is a parachute of the rear part, 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 cassette there is a cavity open to the body, in the cavity there is a parachute of the front part, the ends of the parachute lines of the front part 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.