RU2830216C1 - Ammunition for grenade launcher against unmanned aerial vehicles - Google Patents

Abstract

FIELD: ammunition.

SUBSTANCE: invention relates to ammunition intended for neutralization of unmanned aerial vehicles (UAV). Ammunition for a grenade launcher against a UAV contains a tail part rigidly interconnected by an axisymmetric element, which includes a propellant charge with a primer, and a head part equipped with a guide belt for twisting in the grenade launcher barrel and including a catching net in a laying with peripheral metal elements evenly distributed and fixed on it, as well as a knockout device, with the possibility of dome-shaped opening of the catching net, due to the said knockout device and peripheral metal elements, with the midship of the opened catching net exceeding the ammunition midship, and without separation of the catching net from the ammunition. Axisymmetric element is made in the form of central bearing rod of ammunition. Head and tail parts of the ammunition are spaced apart along the said central bearing rod to form an open annular gap, with the possibility of a working exit through it to the outside of the catching net with peripheral metal elements under the effect of pressure from the knockout device. Knockout device is made in the form of a head powder charge provided in front of the catching net in the packing and connected to the propellant charge by an axial channel in the said central bearing rod of the ammunition with the initiating inert powder charge, with possibility of outlet under pressure together with catching net with peripheral metal elements from head part into said open annular gap between tail and head parts.

EFFECT: simpler design and higher safety of ammunition.

1 cl, 4 dwg

Description

The invention relates to ammunition, for example for hand-held grenade launchers with a caliber of 40 mm, intended for the destruction (neutralization) of unmanned aerial vehicles (UAVs), hereinafter referred to as "drones". Mainly based on VOG-25, VOG-25P grenades.

Tactics for conducting operations to intercept rogue drones is one of the most pressing modern topics with pronounced innovative activity.

There are many interception systems (systems) in service in the world's armed forces and developed in projects. They are aimed both at the unambiguous destruction of such "illegitimate" objects and at their capture. In both cases, this can be called "neutralization".

They use various shells, grenades, missiles, laser and radio-technical means, trained birds of prey, interceptor drones (the latter blow themselves up together with the target ("kamikaze"), ram or catch the target in a net; they operate alone or in groups - multi-agent systems), etc. [1. Effective methods of protection against quadcopters and other commercial drones. - URL: https://k-radio.ru/blog/effektivnye-sposoby-zashchity-ot-kvadrokopterov-i-drugikh-kommercheskikh-dronov/; 2. RU 2 738 383 C2, F41H 11/04, 11.12.2020, "UAV interception device", JSC Research Institute Vector; 3. RU 2 755 951, F41H 11/02, F41H 13/00, 23/09/2021, "Method of active protection of an object from the upper hemisphere"; 4. RU 2 495 359 C1, F41H 11/02, 10.10.2013, "Device for the destruction of remotely piloted (unmanned) aerial vehicles (RUAVs)".

For example, a method and device for destroying a drone are known, when a net is placed on the terrain, one edge of which is fixed, and at least two missiles are secured to the other edge of the net, the missiles are launched at a distance from the target on its trajectory, when the drone is not capable of maneuvering in the area of the net in a direction perpendicular to its course relative to the drone when the net intersects the drone’s trajectory before its approach, while, in particular, explosive devices are installed in the net [5. RU 97 110 432 A, F41H 11/02, 10.07.1999, “Method of destroying an aircraft”].

However, this analogue, firstly, is rather stationary (tied to a position on the ground) than mobile. In any case, it requires a relatively long deployment/disassembly. The drone may not wait for the promised missile launch. Secondly, it is clearly large and can be recommended mainly for a swarm of drones terrorizing a significant strategic object. Thirdly, the missiles experience significant maneuvering overloads of variable direction and magnitude (complex stereometry of the hunting net in the dynamics of interception).

An analogue of the claimed device is an anti-drone munition comprising a streamlined body, a propellant charge with a primer cap, a catching net with solid straightening elements fixed to it, with stowage in a cylindrical container with an open end and with an ejection device, with the possibility of opening into a mesh dome with the midsection of the latter exceeding the midsection of the body, and the possibility of mechanical interception of a drone in the airspace by the catching net, and the ejection device is equipped with an quickly adjustable timer with the possibility of preliminary manual setting of the ejection charge response distance, and also containing a warhead of directional high-explosive fragmentation action with a fuse and damaging solid elements, with the possibility of destroying a drone [6. RU 2 744 227 C1, F41H 11/02, F42B 5/02, F42B 12/58, 03.03.2021, patent holder - FGKA VOU VO "Peter the Great Military Academy of Strategic Missile Forces" of the Ministry of Defense of the Russian Federation].

In this device, the container with the catching net and the warhead (W) are structurally and functionally combined, with the orientation of the open end of the container and the direction of the action of the warhead in its front hemisphere, while the central part of the catching net, which is a nodal bundle of the same ends of radially oriented flexible elements of the net itself, is initially in a free (not connected to anything else) state, and the detonator is made pyrotechnic, as a diaphragm-controlled interconnection of the propellant charge with the propellant charge of the W, with the ability to operate exclusively at the set expected distance to the target.

The body is provided with a leading belt with projections for obturation, acceleration and twisting of the ammunition at the stage of internal ballistics in the rifled barrel (guide), which, in fact, is the basis for the method of automatic opening of the network due to centrifugal forces acting on solid bodies attached to the periphery of the network (they are here - mechanically damaging elements of the drone, in addition to individual fragments of the warhead).

However, this analog device also has the following specific disadvantages.

Firstly, the a priori display of the distance (range) of the warhead activation by means of a timer (which, obviously, was borrowed from the principles of activation of anti-aircraft shells against aircraft during the Second World War) already determines a very low probability of coincidence between the calculated (presumed) and actual range to the target (according to the interception task), especially with the incomparably greater maneuverability of the drone, in comparison with the bomber of that time.

Secondly, the constructive and functional unity of the “device for ejecting a catching net from a container + a high-explosive fragmentation warhead” (with the simultaneous ejection of the net and fragments, especially when the opening net ends up between the flying fragments and the target drone) creates unfavorable conditions for the strength and integrity of the catching net, since it, being a kind of “screen” on the path of damaging factors to the target, may not “live” to fulfill its purpose.

Thirdly, all other things being equal (primarily the distance to the point of impact of the munition with the drone), the detonation of the warhead with its high-explosive fragmentation effect and the generation of secondary damaging elements in the form of products of destruction of the munition and the drone will occur in dangerous proximity to both the shooter and other (own) people and equipment.

Fourthly, the third drawback will also appear in the event of a miss (to the delight of the drone owners).

These shortcomings, individually and in their totality, despite the unconditional usefulness of the analogue [6], are evidence of its still insufficiently high tactical and technical capabilities (characteristics) - TTC (TTX).

In order to save resources and reduce the time of serial production of new products, it is often advisable to rework previously adopted ammunition with their established serial production. This is also true in relation to the 40 mm VOG-25, VOG-25P and other grenades for the PG-25, PG-34 underbarrel grenade launchers [7. VOG-25/VOG-25P and other 40 mm rounds. - URL: https://war-time.ru/item/vystrel-vog-25 (Accessed 21.11.20220)].

Because they themselves are not adapted to effectively combat such small and maneuverable objects as UAVs.

Thus, the admissibility of converting combat grenades into ammunition with a payload that is released by parachute after separation from the munition, in particular reconnaissance and artillery fire correction purposes, is confirmed by information sources where the analogue of a catch net is a parachute built into the warhead of the munition in place of the warhead [8. RU 2 537 355 C1. F42B 5/00, F42B 12/36, F42B 12/42, F42B 15/01, 10.01.2015, “Method of packing a parachute and a container with payload attached to it into the warhead of a grenade body and a device for packing a parachute…”].

The closest analogue (prototype) to the claimed device is a munition for a grenade launcher against unmanned aerial vehicles, containing a tail section rigidly interconnected by an axisymmetric element, including a propellant charge with a primer cap, and a head section equipped with a guide belt for twisting in the barrel of the grenade launcher and including a trapping net in a stowage with evenly distributed and secured peripheral metal elements, as well as an ejection device, with the possibility of a dome-shaped opening of the trapping net, due to the aforementioned ejection device and peripheral metal elements, with the midsection of the opened trapping net exceeding the midsection of the munition, without separating the trapping net from the munition [9. A grenade launcher round for neutralization has been developed in Russia. - URL: https://topwar.ru/180767-v-rossi-razrabotan-granatometnyj-vystrel-dlja-nejtralizacii-bespilotnikov.html (Date of publication: 11.03.2021; date of access 23.11.2022); (Primary source - US patent 2019 for a 40 mm grenade for underbarrel grenade launchers, US Department of the Army - Applicant not found)].

The ammunition consists of two parts - a detachable warhead and a body, inside which a catching net is placed, designed to entangle the UAV in flight. The ammunition can be fired from a regular underbarrel or any other 40 mm grenade launcher.

However, the prototype, despite all its usefulness, is not yet perfect enough and is not always applicable due to the peculiarities of the layout and the need to separate one of the parts of the ammunition to throw out the catch net.

The task (the problem being solved) of the claimed proposed invention is to create a targeted munition "for neutralizing UAVs" that is devoid of the listed disadvantages (or with their significant mitigation), simpler in design (using standard VOG-25, VOG-25P and other grenades as initial products for partial reworking) and safer. As well as expanding the range (arsenal) of technical means for solving the "anti-drone problem".

The said task (problem) is solved in that in a grenade launcher ammunition against unmanned aerial vehicles, comprising a tail section rigidly interconnected by an axisymmetric element, including a propellant charge with a primer cap, and a head section provided with a guide belt for twisting in the barrel of the grenade launcher and including a trapping net in a stowage with peripheral metal elements uniformly distributed and secured to it, as well as an ejection device, with the possibility of a dome-shaped opening of the trapping net, due to the said ejection device and peripheral metal elements, with the midsection of the opened trapping net exceeding the midsection of the ammunition, without separating the trapping net from the ammunition, according to the claimed invention, the axisymmetric element is made in the form of a central supporting rod of the ammunition, and the head and tail sections of the ammunition are spaced apart along the said central supporting rod to form an open annular gap, with the possibility of a working outlet through it to the outside of the trap net with peripheral metal elements under the action of pressure from the ejection device, wherein the ejection device is made in the form of a head powder charge provided in front of the trap net in the stowage and connected to the propellant charge by an axial channel in the said central supporting rod of the ammunition with an initiating inert powder charge, with the possibility of an outlet under pressure together with the trap net with peripheral metal elements from the head part into the said open annular gap between the tail and head parts.

Among the known devices, no such devices have been found whose set of essential features would coincide with the declared one. At the same time, it is due to the latter that a new technical result is achieved in accordance with the set task (identified problem).

A clear distinction between the restrictive and distinctive parts of the given sets of essential features, reflecting the results of a comparative analysis of the claimed device with the prototype, is related to the world level of novelty of the technical solution. The world level of novelty is the first of the triad of features (criteria) of the invention.

Further, the sets of distinctive essential features of the claimed device are not simple sums of known technical results of using separately known devices and their fragments. There is an "emergence", i.e. a "super-effect" (in the patent meaning of this term), which was not obvious to a specialist from the achieved level of technology and military tactics, of course, before considering the claimed solution. With a spectrum of additional technical and operational capabilities. This convincingly demonstrates the inventive level of development as the second of the triad of qualifying features of an invention.

The third qualifying feature, industrial applicability, is also indisputable and follows, first of all, from the same accumulated experience in the design, production (military-industrial complex) and operation (practical use) of technical means for intercepting UAVs (drones) and complexes based on them, as well as from tactical developments and experience in use.

Examples of the claimed device are shown in Figs. 1-4, where the following are designated by positions: 1 - ammunition (as an anti-drone means); 2 - grenade launcher; 3 - UAV (drone) as a target; 4 - axisymmetric (supporting) element (rod) of the ammunition; 5 - tail section of the ammunition; 6 - propellant charge; 7 - primer-igniter (with propellant charge); 8 - head section of the ammunition; 9 - leading (obturating-guiding) belt of the body of the head section of the ammunition (under the barrel rifling); 10 - catching net (for capturing a drone); 11 - peripheral metal elements (masses); 12 - open annular gap between the head and tail sections of the ammunition; 13 - through windows (as the first, alternative to the claimed) version of the ejection device for the catching net) in the head section of the ammunition; 14 - head powder charge (of the ejection device according to the second, declared version); 15 - axial channel in the central supporting element of the ammunition;

Fig. 1 shows, without unnecessary details, the design of the ammunition according to the first variant (alternative to the claimed one) of a possible design (with an ejection device in the form of windows), a side view in section, where L is the size of the open annular gap between the head and tail parts of the ammunition.

Fig. 2 - the design of the ammunition according to the second (declared) variant of possible execution (with an ejection device in the form of a head powder charge with a “flame conductor”), side view in section, L - the size of the open annular gap between the head and tail parts of the ammunition.

Fig. 3 shows the process of capturing a UAV (target) with a munition (projectile) with a dome-shaped, straightened (opened) catching net, side view.

Fig. 4 is a simplified diagram of the neutralization of a UAV with a munition with a catching net, side view.

Ammunition 1 for a grenade launcher 2 against unmanned aerial vehicles (UAVs) 3 (see Fig. 4) contains a tail section 5, rigidly interconnected by an axisymmetric element (rod) 4, including a propellant charge 6 with a primer cap 7, and a head section 8, equipped with a guide belt 9 for twisting in the barrel of the grenade launcher 2 and including a catch net 10 in a stowage with peripheral metal elements (masses) 11 uniformly distributed and secured to it.

A knock-out device is also provided, with the possibility of dome-shaped opening of the catch net 10 (see Fig. 3, 4), due to the mentioned knock-out device and peripheral metal elements 11.

The axisymmetric element 4 is made in the form of a central supporting rod (4) of the ammunition, and the head 8 and tail 5 parts of the ammunition 1 are spaced apart (by a value of L along it with the formation of an open annular gap 12, with the possibility of a working outlet through it to the outside (into the space surrounding the ammunition in the section of external ballistics) of the catching net 10 with peripheral metal elements (masses) 11 under the action of a fluid medium (shown by arrows, for more details see below in the text), that is, under the action of pressure from the ejection device.

The midsection of the dome-shaped open fishing net 10 exceeds (as much as possible) the midsection of the ammunition 1 (see Fig. 3).

Separation of the trap net 10 from the rest of the ammunition 1 is not provided (constant connection of the trap net 10 with the head part 8 by a bundle of “slings of the trap net 10 or a leash as a continuation of the slings in the internal space of the ammunition 1).

Two alternative versions of the ejection device are proposed (see Fig. 1 and Fig. 2).

In the first variant (see Fig. 1), the ejection device is made in the form of through windows 13 in the streamlined frontal part of the head part 8 of the munition 1, with the possibility of an oncoming air flow under dynamic pressure (determined by the flight speed of the munition 1) entering through them and exiting together with the catch net 10 with peripheral metal elements 11 from the head part 8 into the annular gap 12 between the tail 5 and head 8 parts.

In the second variant (see Fig. 2) the ejection device is made in the form of a head powder charge 14, provided in front of the trap net 10 in the stowage and connected to the propellant charge 14 by an axial channel 15 in the central supporting element (rod) 4 of the ammunition 1 with an initiating inert powder charge (channel 15 is filled with it as a "fire duct"), with the possibility of exiting under pressure together with the trap net 10 with peripheral metal elements 11 from the head part 8 into the annular gap 12 between the head 8 and tail 5 parts. This is the claimed variant, declared for patent protection.

The described device operates (functions) as follows.

The method of neutralization (with interception) of UAV 3 by the declared ammunition 1 consists of the following sequence of operations (material means over material objects):

- upon detection of UAV 3, development of a forecast and interception parameters (most importantly, the expected distance/range of encounter) and determination of UAV 3 as a target, load (if this has not been done earlier) ammunition 1 into grenade launcher 2 with a barrel (preferably rifled) and fire ammunition 1 at UAV 3, using primer-igniter 7 and propellant charge 6 (in Fig. 1 UAV 3 is conventionally shown close to grenade launcher 2 - to accommodate the image in A4 format);

- having received the initial speed and spin thanks to the leading belt 9, in the section of internal ballistics, the ammunition (projectile) 1 enters the section of external ballistics (trajectory), approaching the expected meeting place with the UAV 3 (see Fig. 4, 3);

- in the device according to the first variant (see Fig. 1), at the stage of internal ballistics, the pressure of the powder gases in the barrel bore of the grenade launcher 2 exceeds the dynamic pressure of the oncoming air flow through the windows 13, preventing the trap net 10 in the stowage from being prematurely pushed out into the gap 12;

- at the stage of external ballistics - behind the muzzle of the grenade launcher 2, the pressure of the oncoming air flow (shown by arrows) begins to dominate in the mentioned approximate balance and the trapping net 10 with metal elements 11 is displaced into the annular gap 12 (to the left in Fig. 1), and as a result of the rotation acquired by the ammunition 2, causing the centrifugal effect, plus the internal and external air flows, the trapping net 10 with elements 11 are pushed out through the gap 12 into the surrounding air space, straightening out of the packing in a dome-shaped manner (see Figs. 3, 4);

- in the device according to the second (declared) variant (see Fig. 2) there is no problem at all with premature displacement of the trapping net 10 in the packing at the stage of internal ballistics, and behind the cut of the barrel of the grenade launcher 2, with a given time delay, thanks to the “flame guide” in the channel 15 of the rod 4, an ejection device in the form of a powder charge 14 is triggered, the combustion products of the powder of which under pressure push out the trapping net 10 with elements 11 through the gap 12 similarly to that described in the first variant;

- in this case, the dome-shaped open trap net 10 with elements 11 is held on the ammunition 1 by means of a bundle of “slings” of the trap net 10 or a common “leash” in continuation of the “slings”, moving in space along the trajectory of the ammunition 1 synchronously with it (see Fig. 3);

- in both design variants, in the event of a successful interception of UAV 3 (‘hitting’ it, although in fact, on the contrary, UAV 3 ‘hits’ the catching net 10), due to the excess of the midsection of the dome-shaped open catching net 10 over the midsection of the munition (by the maximum diameter of the warhead 8), UAV 3 hits the catching net 10, becoming entangled in it, in particular, due to its operating propeller-motor groups (propulsion);

- when UAV 3 hits the catching net 10, its body momentum (momentum) is transferred to the catching net 10, which sharply reduces the speed of the system “ammunition 1 with catching net 10 plus UAV 3”, which “falls” downwards and falls, completing the neutralization of the target;

- in the event of an unsuccessful interception of UAV 3 (“miss”), for example due to forecast errors, skillful maneuvering of the target, etc., there is no need for self-destruction by detonation (in a self-liquidator) due to the safety of ammunition 1 for those around (not counting the kinetic energy during the fall).

The damage from the fall of ammunition (projectile) 1, both together with the caught UAV 3, and the one that missed, into the enemy’s location is also a positive result.

The use of the proposed invention will eliminate or significantly reduce the above-mentioned shortcomings of the prototype, simplifying the design and increasing safety (absence of a combat charge of "explosives + fragments"), while expanding the range (arsenal) of technical means, by reworking Russian serial-produced grenades VOG-25, VOG-25P for under-barrel grenade launchers with a caliber of 40 mm.

Claims (1)

An ammunition for a grenade launcher against unmanned aerial vehicles, comprising a tail section rigidly interconnected by an axisymmetric element, including a propellant charge with a primer cap, and a head section provided with a guide belt for twisting in the barrel of the grenade launcher and including a trapping net in a stowage with peripheral metal elements uniformly distributed and secured to it, as well as an ejection device, with the possibility of a dome-shaped opening of the trapping net, due to the said ejection device and peripheral metal elements, with the midsection of the opened trapping net exceeding the midsection of the ammunition, without separating the trapping net from the ammunition, characterized in that the axisymmetric element is made in the form of a central supporting rod of the ammunition, and the head and tail sections of the ammunition are spaced along the said central supporting rod to form an open annular gap, with the possibility of a working exit through it to the outside of the trapping net with the peripheral metal elements under the action of pressure from the ejection device, wherein the ejection device is made in the form of a head powder charge, provided in front of the trap net in the stowage and connected to the propellant charge by an axial channel in the said central supporting rod of the ammunition with an initiating inert powder charge, with the possibility of exiting under pressure together with the trap net with peripheral metal elements from the head part into the said open annular gap between the tail and head parts.