Projectile with snares for incapacitating aerial drones

Abstract

The invention relates to weaponry, and more particularly to means for mechanically incapacitating aerial drones. A projectile with snares for incapacitating aerial drones comprises a base part 11. The projectile further has a cassette 4, and a cap 1 which is open at the back. The cap 1 has a rearwardly oriented piston 3. Also provided is a barrel 5 which is closed at the back, wherein the muzzle 6 of the barrel faces forwards. The piston 3 is disposed inside the barrel 5. Also provided are an air burst means for a propelling charge, and a propelling charge 9 disposed inside the barrel 5. The cassette 4 has fins 18-20 which are perpendicular to a longitudinal axis 2 and are connected to a shaft 21. The device further comprises snares disposed between the fins. Each snare comprises a ring 22, weights 23, and lines 24. Each weight 23 of a snare has a line 24 fastened to the respective weight 23 by a first end. A second end of each line 24 is fastened to the ring 22. The invention makes it possible to increase the likelihood of incapacitating an aerial drone.

Description

A projectile with capes for destroying aerial drones

[0001] The invention relates to weapons, specifically to means for the mechanical destruction of small objects using capes. The invention is applicable to countering terrorism by ensuring the security of stationary objects, vehicles, and public events in open areas.

[0002] The closest analogue of the claimed technical solution is a projectile with a cape for destroying aerial drones, described in Russian Patent No. 2819119, published May 14, 2024. The projectile comprises a base section with an imaginary longitudinal axis. It also has a cartridge and a cap open at the rear, located on the imaginary longitudinal axis. The cap has a rearward-facing piston. It has a closed-rear barrel, with the barrel facing forward. The piston is located in the barrel. It has an air-detonating device for the expelling charge and an expelling charge located in the barrel. A housing, open at the front, is connected to the base section of the projectile. The cartridge is located with its rear section inside the housing, and its front section inside the cap.

[0003] The device also includes a cape. The cassette comprises first and second jaws, perpendicular to an imaginary longitudinal axis and connected to a rod, where the outer diameter of the rod is smaller than the outer diameters of the jaws. The first jaw is located anterior to the second jaw. The cape contains a ring, cape weights, and cape threads. The cape is located between the first and second jaws. The cape weights are arranged around an imaginary longitudinal axis. Each cape weight is equipped with a cape thread. Each cape thread is attached to the corresponding cape weight at its first end. The ring is located outside the rod. The second end of each cape thread is attached to the ring. Each cape thread is compactly arranged so that it can be straightened when pulled by its second end.

[0004] When the projectile is fired, it begins to rotate around an imaginary longitudinal axis. The weights are pressed into the body and cap from the inside. The cartridge, like the cap, can slide relative to the body along the longitudinal axis. When the expelling charge detonates in the air, the cap and cartridge slide forward relative to the body. The forward ends of the weights, held by the cap, and the rear ends of the weights, held by the body, simultaneously release radially and exit the cartridge from the compartment formed on its core by the first and second jaws. The weights pull the threads, and the cape straightens. It flies forward and strikes an aerial drone.

[0005] In the known design of an expanding projectile, which provides for the simultaneous release of the front and rear ends of the weights from a single compartment, a limited number of threaded weights can be placed in the joint between the body and the cap. This is a drawback of the known projectile. The lethality of this number of threaded weights is limited. The probability of their hitting the target is low.

[0006] The purpose of this technical solution is to increase shooting efficiency.

[0007] To solve the technical problem and achieve the desired technical result, the design of a known device was modified. A known projectile with a cape for destroying aerial drones comprises a base section with an imaginary longitudinal axis. It also contains a cartridge and a cap with an open rear, located on the imaginary longitudinal axis. The cap has a rearward-facing piston. It has a closed-rear barrel, with the barrel muzzle facing forward. The piston is located in the barrel. It has an air-detonating device for the expelling charge and an expelling charge located in the barrel.

[0008] The device also includes a first cape. The cassette comprises first and second jaws, perpendicular to an imaginary longitudinal axis and connected to a rod, wherein the outer diameter of the rod is smaller than the outer diameters of the jaws. The first jaw is located behind the second jaw. The first cape contains a first ring, first cape weights, and first cape threads. The first cape is located between the first and second jaws. The first cape weights are arranged around an imaginary longitudinal axis. Each first cape weight is equipped with a first cape thread. Each first cape thread is attached to the corresponding first cape weight at its first end. The first ring is located outside the rod. The second end of each first cape thread is attached to the first ring. Each first cape thread is compactly arranged so that it can straighten when pulled by its second end.

[0009] The base of the known projectile is additionally connected to the cassette or is part of the cassette. The barrel is connected to the cassette or is part of the cassette. A third cheek is inserted forward of the second cheek, parallel to the second cheek and connected to the rod. A second cape is additionally inserted, located between the second and third cheeks, containing a second ring, second cape weights, and second cape threads. The second cape weights are arranged around an imaginary longitudinal axis. Each second cape weight is equipped with a second cape thread. Each second cape thread is attached to the corresponding second cape weight at its first end. The second ring is located outside the rod. The second end of each second cape thread is attached to the second ring. Each second cape thread is compactly packed so that it can be straightened when pulled by its second end. The cape weights are located inside the cap.

[0010] In addition, the gap between adjacent cheeks may be less than the largest overall dimension of the cross-section of the load, made by an imaginary plane passing through an imaginary longitudinal axis.

[0011] In addition, the cape can have at least three weights.

[0012] In addition, the rod between the cheeks can have recesses, with each load located in a recess.

[0013] Moreover, in such a design with recesses on the rod, an imaginary line segment-direction connects the center of mass of each load with an imaginary longitudinal axis, the orthogonal projections of all line segments-directions onto a plane perpendicular to the imaginary longitudinal axis can be uniformly distributed around the imaginary longitudinal axis.

[0014] Additionally, grooves parallel to the imaginary longitudinal axis can be made on the inner surface of the cap. The grooves are open at the rear, and each weight is positioned within a groove. A projection located within the groove can be made on the outer part of the rear cheek.

[0015] In addition, the cap and the cassette can be connected by a flexible connection.

[0016] In addition, the thread can be made of aromatic polyamide material.

[0017] In addition, the thread can be made of metal wire.

[0018] The technical result that this technical solution is aimed at achieving is to increase the probability of hitting an aerial drone.

[0019] The modified design of the device increases the number of compartments between the jaws on the cartridge stem, which contain the threaded payloads. These compartments are located inside the cap, allowing the cap to open them sequentially upon detonation of the expelling charge. This also increases the total number of threaded payloads in the munition. When the cap slides relative to the cartridge following detonation of the expelling charge, the payloads exit the cartridge, forming not one, as in its closest analogue, but two. The additional number of threaded payloads increases the probability of hitting a drone. Figure 1

[0020] Depicts a longitudinal section of an artillery shell with protective caps for destroying aerial drones, before the expelling charge is detonated. The shell's rod is indented. Figure 2

[0021] depicts a cross-section of the projectile shown in . The section passes in front of the loaded weights of the second cape. Figure 3

[0022] depicts a cross-section of the ammunition shown in. The cross-section runs along the second cheek. Figure 4

[0023] Depicts a longitudinal section of an artillery shell with caps for destroying aerial drones, before the expelling charge is detonated. The cap has longitudinal grooves on the inside. Figure 5

[0024] Shows a cross-section of the projectile shown in [image]. The cross-section passes in front of the loaded weights of the second cover. The slings, cable, and wire are not shown. Figure 6

[0025] Shows a cross-section of the projectile shown in . The cross-section extends along the second jaw. The slings, cable, and wire are not shown. Figure 7

[0026] depicts a longitudinal section of the cape load with a thread placed inside. Figure 8

[0027] depicts a front view of the cape with the ring straightened out before it is placed in the cassette. Figure 9

[0028] depicts a longitudinal section of the "shot" of an under-barrel grenade launcher, containing in the front part a projectile with capes for destroying aerial drones in a state before firing from the grenade launcher. Figure 10

[0029] depicts a cross-section of the projectile shown in . The section passes behind the stowed weights of the third cover. Figure 11

[0030] depicts a longitudinal section of the projectile with capes for defeating aerial drones, shown in, after the air detonation of the expelling charge and the release of all loads from the cassette by the cap. Figure 12

[0031] This is the first frame of a schematic sequence depicting the operation of a projectile with capes to destroy aerial drones. The projectile approaches its target—an aerial drone—to destroy it. Figure 13

[0032] This is the second frame of a schematic sequence depicting the projectile's operation. The propellant charge has detonated, the cape weights are scattered, the cartridge has been removed forward, and the smoke-generating compound is burning. Figure 14

[0033] Depicts a view from an aerial drone of an approaching projectile along the projectile's axis. The dotted lines indicate the positions of the strings with the weights after all the covers are fully deployed. Figure 15

[0034] Shows a view from an aerial drone of an approaching projectile along the projectile's axis. The arrangement of the weights and the cape threads differs from that shown in [image]. Figure 16

[0035] This is the third frame of a schematic sequence depicting the projectile's operation. The weights scattered across the entire length of the strings, fully deploying the capes. Three capes missed the target. Two strings, from the fourth and fifth capes, made contact with the drone. Figure 17

[0036] This is the fourth frame of a schematic sequence depicting the projectile's operation. The threads of two capes are wrapped around the drone's body. The drone has become inoperable and is falling. The sixth cape's threads are caught in the fourth and fifth capes and are falling down along with them. Figure 18

[0037] depicts a longitudinal section of the projectile shown in, after the air detonation of the expelling charge and the release of the weights of the first three capes from the cassette.

[0038] The projectile with capes for destroying aerial drones, depicted in 2 and 3, which is an artillery projectile, contains a hollow cap 1. Cap 1 is open at the rear and is located on an imaginary longitudinal axis 2. A piston 3 directed backwards is connected to cap 1. Inside cap 1, on an imaginary longitudinal axis 2, a cassette 4 is located. The rear part of cap 1 is connected to the rear part of cassette 4 by a splined connection 29. A barrel 5 is connected to cassette 4, wherein muzzle 6 of barrel 5 faces forward. The rear part of barrel 5 is closed. Piston 3 is located in barrel 5. Base part 11, having an imaginary longitudinal axis 2, is connected to the rear part of cassette 4 by a threaded connection.

[0039] The projectile contains a means for air-detonating the expelling charge, which is a distance tube 7 of an artillery projectile, known from the prior art, with a powder tube 16 and a firecracker 53. A component of the distance tube 7 is a distance ring 8 with a scale. In the barrel 5, between the piston 3 and the rear part of the barrel 5, a powder expelling charge 9 is located. In the cassette 4, an axial hole 10 is made, in which a smoke-generating composition 17 is located. A leading band 28 of the artillery projectile is fixed to the rear part of the cassette 4.

[0040] In the rear part of the barrel 5, a through axial hole is made in which a highly flammable composition 12 is fixed. To the opposite end of this hole with the composition 12, facing inside the cassette 4, a smoke-forming composition 17 is pressed. The composition 12 has high strength and strong adhesion to the walls of the hole, which excludes its mechanical destruction due to high pressure in the barrel 5 after ignition of the expelling charge 9.

[0041] Parallel cheeks are formed on cassette 4: for example, the first 18, the second 19, and the third 20. The cheeks are perpendicular to the imaginary longitudinal axis 2 and are connected by rod 21. The outer diameter of rod 21 is smaller than the outer diameters of the cheeks. Openings 27 are formed in first cheek 18 for the release of smoke generated by smoke-generating composition 17 out of cassette 4.

[0042] The first cape is located between the first (rear) 18 and second 19 cheeks. The second cape is located between the second 19 and third 20 cheeks. The remaining capes are located similarly. Each cape contains a ring 22, eight weights 23 and eight connecting threads 24 made of aromatic polyamide material. The weights 23 are located around an imaginary longitudinal axis 2. A thread 24 is attached to each weight 23 by its first end. Each ring 22 is located outside the rod 21. The second end 26 of each thread 24 of the corresponding cape is attached to the ring 22 by a knot 25. The gap between adjacent cheeks is less than the largest overall dimension of the cross-section of the weight 23, made by any imaginary plane passing through the imaginary longitudinal axis 2. Such a cross-section of the upper depicted weight of the last cape is shown in . The weights of all capes are located inside the cap 1.

[0043] On the rod 21 between the cheeks there are depressions 15 (and 2). Each load 23 of the cape is located in the depression 15. The number of depressions 15 is equal to the number of loads 23 of each cape. Each load 23 of the cape is located between its corresponding depression 15 and the inner surface of the cap 1. An imaginary segment-direction 14 can be drawn from the center of mass 13 of each load 23 to the imaginary longitudinal axis 2. The segment-direction 14 is designated by a line of dots, and its ends are marked with the Greek letters y and 5. The orthogonal projections of all segments-directions 14 of the cassette onto a plane perpendicular to the imaginary longitudinal axis 2 are uniformly distributed around the imaginary longitudinal axis 2.

[0044] A flexible cable 37, which is located between the front of cap 1 and the front of cassette 4, is located inside cap 1. Cable 37 connects cassette 4 and cap 1.

[0045] A similar design of a projectile with capes for destroying aerial drones is shown in , 5 and 6. Its design differs from the one described above in the elements that organize the arrangement of weights 23 in cap 1. Rod 21 is made in the form of a cylindrical part. The inner space of cassette 4 is isolated from the external environment by sealant 57. On the inner surface of cap 1 there are grooves 33 (and 5), parallel to the imaginary longitudinal axis 2 and open in front. Each weight 23 is located in the corresponding groove 33. Grooves 33 organize the arrangement of weights 23 in cap 1. In addition, on the outer part of all cheeks there are projections 34, located in the corresponding grooves 33 of cap 1. Protrusions 34 prevent mutual rotation of cap 1 and cassette 4 about axis 2. Expulsion charge 9 is less powerful than that of the design shown in .

[0046] In the design of the projectile shown in Figures 5 and 6, a stowed parachute 35 is located inside the opening 10 of the cassette 4. It is connected to the cassette 4 by straps 36 and a cable 38. The bottom part 11 and the plug 39 are also connected to the cassette 4 by a cable 38. The plug 39 closes the opening 10 at the rear. Stops 49 are located between them, preventing the plug 39 from falling out of the opening 10 at the moment of firing. The bottom part 11 is connected to the rear opening of the cassette 4 by means of a sliding fit and an annular stop from moving in the longitudinal direction, and is also secured by pins 48.

[0047] Between the base section 11 and the plug 39 is a controller 40, which contains a power source in the form of a supercapacitor or battery, a computing device, and internal acceleration sensors. Also located in the base section 11 are a parachute ejection charge 41 and an electrical connector 42 for charging and data input, with its input facing the outer surface of the projectile. At the rear of the barrel 5 is an electric igniter 51, with its output facing the inside of the barrel 5 toward the expelling charge 9.

[0048] The means for air detonation of the expelling charge in this design variant is a system that includes a controller 40 and an electric igniter 51. The parachute ejection charge 41, the electrical connector 42 and the electric igniter 51 are connected to the controller 40 by electrical wires 44.

[0049] The cross-section of the load 23 is shown in . It is shaped like a flat cylinder, with a recess 45 in the central part of the left end. A thread 23 is compactly laid in recess 45 and can be straightened by pulling its second end 26. The first end of the thread 24 is attached to the load 23 by means of a knot 46. A circumferential groove 47 is formed on the cylindrical surface of the load 23. When equipping the cassette 4 with caps, a section of the ring 22 (, 2, 4, 5) is placed in this groove.

[0050] A front view of the assembled cape shown in , with weights 23, threads 24 and the straightened ring 22 before it was placed in the cassette 4, is shown in .

[0051] A simpler design of a projectile with capes for destroying aerial drones exists. The projectile is part of the "shot" of an underbarrel grenade launcher and is located in its front part. The projectile contains a hollow cap 1 (and 10) on an imaginary longitudinal axis 2, open at the rear. In the front part of cap 1, inside, there is a piston 3, directed rearward. Piston 3 is part of cap 1 - these parts are made from the same blank. Cap 1 contains a cassette 4. The cassette has a base 11 on an imaginary longitudinal axis 2. Base part 11 is part of cassette 4 - these parts are also made from the same blank. In the front part of cassette 4, a barrel 5 is made, which is part of cassette 4 - these parts are also made from the same blank. Muzzle 6 of barrel 5 faces forward. The rear part of barrel 5 is closed. Piston 3 is located in barrel 5. Expulsion charge 9 is located in barrel 5.

[0052] The cassette 4 contains the means for air-detonating the expelling charge—connecting channel 52, propellant tube 50, and firecracker 53. Propellant tube 50 contains a composition capable of transmitting fire from connecting channel 52 to firecracker 53 and then to expelling charge 9. Propellant tube 50 is configured by the manufacturer for a specific ignition time for expelling charge 9 after firing the projectile. The distance, in the case of a horizontal shot, after which the cape becomes fully extended is indicated on the projectile's nose fairing 56.

[0053] The projectile is delivered to the target by chamber 63, secured behind base section 11, filled with propellant powder charge 64 and primer 65. Openings 66 for the release of propellant gas jets are provided in the rear wall of chamber 63. A band 67 with leading projections corresponding to the spiral grooves in the grenade launcher barrel is used to rotate the projectile along its flight path. A groove 68 is provided to secure base section 11 of the projectile in the barrel of the underbarrel grenade launcher before firing. The remaining components of the projectile are identical to those shown in Fig. 3.

[0054] The device operates as follows. The projectile, shown in [image], is fired from an artillery piece toward the aerial drone 70 () with the correct point of full deployment of the cape (set by rotating the remote ring 8 () to the desired value on the scale) and the aiming point selected. Upon firing, the projectile begins to rotate in flight.

[0055] At a designated point in the projectile's flight path, directly in front of the drone, the cape should be fully deployed. Weights 23 with threads 24 should form the structure shown in . The fully deployed threads are shown as dotted lines. To achieve this, at a distance before this point, remote tube 7 () is triggered, using powder tube 16 and firecracker 53 to create a beam of fire directed at expelling charge 9, igniting it. As a result of combustion, expelling charge 9 creates excess pressure of the powder gases in barrel 5. Piston 3 is pushed out of barrel 5 by the powder gases. Flammable composition 12 is ignited by the burning expelling charge 9 and burns within the axial bore in barrel 5.

[0056] Due to the action of the propellant gases, cap 1 and cassette 4 move in opposite directions relative to each other with high acceleration. Cap 1 opens one after another the areas between the cheeks in which the weights 23 are placed. In the non-inertial rotating coordinate system associated with cassette 4, each weight 23, due to its accelerated forward motion together with cassette 4, is acted upon by a longitudinal inertial force directed forward and pressing it against the cheek located in front of it. Also in this coordinate system, each weight 23 is acted upon by a centrifugal force directed outward from an imaginary longitudinal axis 2 (the axis of rotation of the projectile). The magnitude of the static friction force directed toward axis 2, arising in this contact from the action of the longitudinal inertial force, is equal to the magnitude of the centrifugal force. As a result, the weights 23 do not shift relative to the cheek and continue to rotate with it.

[0057] But the accelerated motion of the cartridge 4 and the cap 1 continues only until the moment when the cartridge 4 leaves the cap 1, or more precisely, until the significant aftereffect of the propellant gases on the front part of the barrel 5 and the front part of the cartridge 4 ends. At this moment, the force of static friction disappears, and all the weights 23 of all the capes simultaneously begin to move outward along a tangent to the circle of their rotation from the recesses 15 () in which each of them is located. Since the orthogonal projections of all the segments-directions 14 onto the plane perpendicular to the imaginary longitudinal axis 2 are uniformly distributed around this axis, the projections of the recesses 15 and the threads 24 () of the straightening capes are also uniformly distributed around axis 2.

[0058] Since the gap between adjacent cheeks of cassette 4 is less than the largest overall dimension of the cross-section of load 23, made by an imaginary plane passing through imaginary longitudinal axis 2, loads 23 before exiting cassette 4 do not have the opportunity to rotate relative to axes perpendicular to imaginary longitudinal axis 2. In a non-inertial rotating coordinate system associated with cassette 4, their centers of mass perform translational motion with a constant speed in a plane perpendicular to imaginary longitudinal axis 2, directed outward from the compartment between the cheeks.

[0059] A longitudinal section of a projectile with capes for engaging aerial drones is depicted, when all capes from cassette 4 are released by the rear edge of the cap and exit cassette 4. Cap 1 and cassette 4 have moved away from each other a significant distance and are connected only by cable 37. Weights 23 of all six capes fly apart, each in its own direction. At the same time, in the inertial coordinate system, they rotate relative to their longitudinal axes at a frequency equal to the rotational frequency of the munition in flight. Together with cassette 4, weights 23 fly forward toward the target. Smoke-generating composition 17, meanwhile, has ignited due to the flammable composition 12 () pressed against it and creates smoke that accumulates in opening 10 () inside cassette 4 and bottom part 11. After a moment, cable 37 will become taut and pull cassette 4 from the central region of the capes.

[0060] Figures 13, 16, and 17 show a schematic sequence of how the projectile with capes, depicted in figure 3, operates when engaging an aerial drone. In the first frame of this sequence, the projectile approaches aerial drone 70 to engage it. The gunner aimed the projectile at the target, not quite accurately, slightly below it.

[0061] The second frame shows the detonation of expelling charge 9, the projectile opening, and the 23 cape weights flying apart. For greater clarity, the distances between the capes along imaginary longitudinal axis 2 are depicted at greater intervals along imaginary longitudinal axis 2 than they were in cassette 4. Cap 1 (), due to its greater mass, has used cable 37 to pull cassette 4 back from the interior of the opening capes a considerable distance. Smoke from the combustion of smoke-generating composition 17 emerges from openings 27 (), creating a noticeable smoke trail in the sky. The smoke attracts attention and allows personnel to avoid injury from falling projectile parts and the damaged drone. Cap 1 and cassette 4, connected by cable 37, constitute an additional striking element.

[0062] The view from the drone's perspective of an approaching projectile along the projectile's axis is shown at the moment depicted in . The dotted lines show the positions of the strings with the weights at a moment that occurs somewhat later, after all the capes have fully unfolded. The weights in the figure have designations consisting of two symbols: a letter and a number. The capes are designated by the letters of the Latin alphabet from a to f. The number of the weight in the cape is indicated by the numbers from 1 to 8. The designations for the eighth and first weights of all capes in the figure are listed. Further along the circle, only the designations of the weights of the first cape are listed.

[0063] The weights 23 of the capes can be ejected from the cassette 4 at different angles. One variant is shown in . The weights of only two capes, the first (a) and the second (b), are indicated. As in the variant shown in , the threads 24 cover the entire affected area. The arrangement of the threads 24 in the open cape is determined by the position of the recesses 15 () on the rod 21 of the cassette 4.

[0064] In the third frame of the schematic sequence depicting the projectile's operation, weights 23 have spread out to the sides along the entire length of their threads 24, forming six fully extended capes. The first three capes—a, b, and c—failed to lock onto the target. Two threads from the fourth (d) and fifth (e) capes made contact with the drone. Moreover, the thread of weight d8 caught on the drone's body, and the thread of weight e8 entangled the propeller. The destruction diagram is shown in [image].

[0065] In the fourth frame, the threads of two capes are wrapped around the drone's body. The drone has become inoperable and is falling. The sixth cape (f) has caught its threads on the fourth and fifth capes and is falling down along with them.

[0066] A projectile with capes for engaging aerial drones of a different design, depicted in Figures 5 and 6, operates similarly. However, there are some differences in its deployment and the ejection of payloads 23 from cassette 4. Before loading the projectile into the gun barrel, a projectile deployment delay is entered via electrical connector 42. At a certain distance from the aerial drone, controller 40 sends an electrical pulse to electric igniter 51, which, in turn, creates a beam of fire directed at expelling charge 9 and ignites it. As a result of combustion, expelling charge 9 creates excess pressure of propellant gases in barrel 5. This excess pressure is small, since the magnitude of charge 9 is small compared to the magnitude of a similar charge 9 on...

[0067] The resulting longitudinal acceleration of the projectile and its components causes inertial forces acting on all components. Under the influence of inertial force, for example, plug 49 tends to fall out of opening 10 of cassette 4. However, it is held in place by stops 49, which rest against base 11.

[0068] The action of the propellant gases forces piston 3 out of barrel 5, causing cap 1 and cassette 4 to move in opposite directions relative to each other. Cap 1 opens one after another the areas between the cheeks in which weights 23 are placed. However, unlike the design shown in figures 3 and 11, the longitudinal inertial force directed rearward and pressing weight 23 against the cheek located behind it is small. The magnitude of the static friction force arising in this contact in the radial direction due to the action of the inertial force is less than the magnitude of the centrifugal force. As a result, weights 23 begin to move relative to the cheek outward from cassette 4 along a tangent to the circumference of their rotation ().

[0069] By the time the weights 23 of the first cape are ejected from cassette 4, the pressure of the propellant gases inside cap 1 decreases. The leading edge of cap 1, moving forward relative to cassette 4, exposes more and more weights 23 of the capes, stored between the jaws of cassette 4. The moment in time is depicted when only weights 23 of three capes have exposed themselves. Weights 23, no longer held by cap 1 and its grooves 33, cease rotation around imaginary axis 2 and move outward from cassette 4.

[0070] At the moment when the weights 23 of the first cape are completely released from cassette 4, this cape leaves the edge of cap 1 and then moves uniformly, without acceleration. The weights of the second cape leave the cassette a moment later. Due to the rotation of cassette 4, the second cape is rotated relative to the first by a small angle. This angle may be formed by thread 24 of weight 23 of the first cape, designated a1 (), and thread 24 of weight 23 of the second cape, designated b1.

[0071] It may also be a different angle. For example, the angle formed by thread 24 of weight 23 of the first cape, designated a1 (), and thread 24 of weight 23 of the second cape, designated b1. The power of expelling charge 9 (), the intensity of its combustion, and, accordingly, the speed with which cap 1 () moves forward, are selected such that all these angles of all weights 23 and all caps of the projectile ensure uniform coverage of the striking area by threads 24. Also, the power of expelling charge 9 and the intensity of its combustion are selected such that each subsequent cape exiting cassette 4 does not fall on the imaginary plane of the previous cape, which has already exited cassette 4.

[0072] Then, based on input information from internal accelerometers, the computing unit of controller 40 calculates two branches of the projectile's trajectory, into which the trajectory has divided after the detonation of ejection charge 9. The capes travel along the steeper, descending branch, while the remaining projectile components travel along the flatter branch. At the point along the flatter branch of the trajectory where the capes will not touch the projectile components descending on the deployed parachute 38, controller 40 sends an electrical pulse to parachute ejection charge 41.

[0073] The charge of the parachute ejection 41 burns, creating gas pressure in the bottom part 11 and the rear part of the cassette 4. The pins 48 are destroyed and the bottom part 11 flies back from the cassette 4. The cable 38, secured to the bottom part 11, is stretched and pulls out the plug 39, the stops 49 and the packed parachute 35 from the cassette 4. The electrical wires 44 break. The parachute 35 straightens out and smoothly lowers the cap 1, the cassette 4, the plug 39 with the stops 49, the bottom part 11 onto the ground or water surface with the help of cables 37 and 38, without causing damage to personnel, structures and vehicles.

[0074] A simpler projectile with capes for engaging aerial drones, shown in Fig. 10, which is part of the underbarrel grenade launcher's "shot," operates as follows. The shooter determines the distance to the aerial drone visually or using a rangefinder. Based on the determined distance, the shooter selects a projectile with the appropriate marking on the nose cone 56 from among the available projectiles. If a projectile with the required range is not available, the shooter selects a projectile with a shorter range, keeping in mind that the deployed cape can hit a drone from several dozen meters away.

[0075] The shooter then loads the projectile into the grenade launcher, selects an aiming point ahead (in the case of a moving drone) and above the drone, and fires. The underbarrel grenade launcher's striker breaks primer 65 (). The beam of fire from it ignites propellant powder charge 64, generating propellant gases. Excess pressure is created in chamber 63, and the gases escape through openings 66 into the projectile-covered portion of the grenade launcher barrel. The resulting excess pressure from the propellant gases propels the projectile forward toward the target. The leading lugs of band 67, sliding in the rifling of the grenade launcher barrel, spin the projectile around an imaginary longitudinal axis 2.

[0076] When burning, propellant charge 64 ignites the propellant mixture in connecting channel 52. For a certain period of time, the flame moves along propellant tube 50. The flame then passes to propellant firecracker 53, which ignites propelling charge 9. By this time, the projectile has flown to the target at the distance necessary for the cap to fully deploy. Cap 1 and cassette 4 accelerate relative to each other in opposite directions, causing the projectile to deploy. The deployment of the capes and the process of hitting a drone with a projectile for an underbarrel grenade launcher, shown in Figure 10, is similar to the operation of the projectile shown in Figures 3, 11-13, 16, and 17.

[0077] The claimed device can be used on a permanent basis to counter terrorism, ensuring the security of stationary facilities, vehicles, and public events in open areas. It can also be temporarily deployed in combat during military operations. When repelling a swarm of aerial drones, the device is used for a remotely controlled automatic weapon coupled with a fire control system. It is most successfully applied to drones with a flight program capable of executing without operator radio control or the use of radio navigation systems, as well as to radio-controlled drones with automatic target acquisition under an electronic warfare dome. The device can also be successfully used to engage drones controlled via fiber optics.

[0078] The invention has been disclosed above with reference to specific embodiments. Other embodiments of the invention may be apparent to those skilled in the art without altering its essence as disclosed herein. Accordingly, the invention should be considered limited in scope only by the following claims.

[0079] No

Claims

A projectile with capes for engaging aerial drones, comprising a base portion having an imaginary longitudinal axis; a cassette and a cap open at the back, located on the imaginary longitudinal axis, the cap has a piston directed backwards; a barrel closed at the back, wherein the muzzle of the barrel faces forward, the piston is located in the barrel; a means for air detonation of an expelling charge; an expelling charge located in the barrel; a first cape; the cassette contains first and second cheeks, perpendicular to the imaginary longitudinal axis and connected to a rod, the first cheek is located behind the second cheek, the outer diameter of the rod is less than the outer diameters of the cheeks;the first cape comprises a first ring, first cape weights and first cape threads, the first cape is located between the first and second cheeks, the first cape weights are located around an imaginary longitudinal axis, each first cape weight is provided with a first cape thread, each first cape thread is attached to the corresponding first cape weight by its first end, the first ring is located outside the rod, the second end of each first cape thread is attached to the first ring, each first cape thread is compactly laid with the possibility of straightening when pulled by its second end, characterized in that the bottom part is connected to the cassette or is part of the cassette; the barrel is connected to the cassette or is part of the cassette; a third cheek is introduced in front of the second cheek, parallel to the second cheek and connected to the rod;a second cape is additionally introduced, located between the second and third cheeks, containing a second ring, weights of the second cape and threads of the second cape, the weights of the second cape are located around an imaginary longitudinal axis, each weight of the second cape is provided with a thread of the second cape, each thread of the second cape is attached to the corresponding weight of the second cape by the first end; the second ring is located outside the rod, the second end of each thread of the second cape is attached to the second ring, each thread of the second cape is compactly laid with the possibility of straightening when pulling it by the second end; the weights of the capes are located inside the cap. A projectile according to paragraph 1, characterized in that the gap between adjacent cheeks is less than the largest overall dimension of the cross-section of the load, made by an imaginary plane passing through an imaginary longitudinal axis. The projectile according to paragraph 1, characterized in that the capes have at least three weights. A projectile according to paragraph 1, characterized in that the rod between the cheeks has recesses, each weight being located in a recess. A projectile according to paragraph 4, characterized in that an imaginary segment-direction connects the center of mass of each load with an imaginary longitudinal axis, the orthogonal projections of all segments-directions onto a plane perpendicular to the imaginary longitudinal axis are uniformly distributed around the imaginary longitudinal axis. A projectile according to paragraph 1, characterized in that grooves parallel to an imaginary longitudinal axis are made on the inner surface of the cap; the grooves are open at the back, each load is located in a groove. A projectile according to paragraph 6, characterized in that a projection is made on the outer part of the rear cheek, the projection being located in a groove. A projectile according to paragraph 1, characterized in that the cap and the cassette are connected by a flexible connection. The projectile according to paragraph 1, characterized in that the thread is made of an aromatic polyamide material. The projectile according to paragraph 1, characterized in that the thread is made of metal wire.

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