RU2841784C1 - Grenade for hand grenade launcher round to hit unmanned aerial vehicles - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: grenade for a hand-held grenade launcher to destroy unmanned aerial vehicles contains a warhead, a jet engine, and a stabilizer placed in a powder charge. Grenade head part has a body representing a hollow shell, the internal volume of which is filled with complex spatial structures from star-shaped metal, which are monolithically connected to each other and to body walls, as well as with fine steel powder. Detonating elongated cord is located along central axis of the body. Mixture of exothermal disperse powder enclosed in tight cover is tightly laid around cord. Housing rear cover is connected via insert arranged in adapter with jet engine nozzle bottom housing. All pyrotechnic elements of the grenade are connected in series into a single fire circuit.

EFFECT: higher efficiency of hitting unmanned aerial vehicles, reliable and simple design of the round.

4 cl, 6 dwg

Description

The invention relates to ammunition for hand-held grenade launchers and is intended to destroy UAVs.

A number of fragmentation projectiles with combat striking elements installed in their bodies can be used to combat UAVs. Inventions are known under patents RU 2237231 C1, RU 2247929 C1, RU 236864 C1, RU 45818 U1. The task of these projectiles is to hit the target with an axial flow of ready-made striking elements. To increase the accuracy of fire, the projectile must additionally contain a target aiming device and a fuse.

The disadvantages of these devices are the formation of only the total axial flow of ready-made striking elements, which reduces the probability of hitting the target in the event of a miss caused by errors in setting the required moment of actuation of the trajectory fuse.

To increase the target defeat zone, a fragmentation grenade RU 219316 U1 is proposed, in which the striking elements are created by fragmentation of the body, equipped with fragmentation localizers in the form of symmetrical transverse grooves, external annular, conical and internal saw-tooth profile. The action of the projectile is carried out as follows. At the calculated point of the trajectory, the fuse (temporary, non-contact, command type) is triggered and the explosive is detonated, ensuring the formation of a fragmentation flow of striking elements.

The disadvantage of this device is the introduction of a complex fuse and insufficient density of the flow of damaging elements, which reduces the likelihood of hitting UAVs, some of which have a lattice frame design.

The fragmentation-beam over-caliber grenade "Tverityanka" with a trajectory break, intended for firing from a hand-held grenade launcher RU 2362962 C1, is known - the closest analogue of the proposed invention.

The grenade consists of a caliber part and an above-caliber warhead. The latter in turn consists of a rear section and a front section, which is a set of throwing blocks. The caliber part of the grenade contains a jet engine with a charge of solid fuel and a nozzle block, a rod attached by means of a detachable connection to the rear end of the jet engine, equipped with an opening stabilizer in the middle part, and a turbine in the rear part. The expelling powder charge is located along the entire length of the rod.

The rear section of the warhead contains a steel body of specified fragmentation, a bottom trajectory fuse of a temporary type with a receiver of installations, a charge of explosive substance (HE), a pyrotechnic charge of separation, connected by a channel to the trajectory fuse. The front section of the warhead contains a set of throwing blocks and a head cap. The throwing block contains a body with a charge of explosive, in the bottom of which a fuse is installed. On the front end of the charge of explosive there is a single-layer stacking of ready-made striking elements.

Before firing, the range to the target and the flight range before firing the front section are determined, which is calculated using a calculator built into the grenade launcher, the corresponding flight time is determined through the installer located on the barrel of the grenade launcher and the grenade command receiver, as well as the installation of a time fuse.

To ensure shooting accuracy, due to gyroscopic stability, the grenade rotates in flight by tilting the jet engine nozzles relative to the axis, one-sided bevels on the edges of the stabilizer blades and turbine. The distance to the target is measured by a laser rangefinder, the range value is sent to the ballistic computer in a contactless manner or via cable. The calculated time setting is sent to the over-barrel automatic setter.

The disadvantages of the described shot are the need to include fuses that have high sensitivity to impact, which are dangerous elements and require the introduction of a self-destructor into the design, the complexity of the design equipped with electronic equipment, which makes the device vulnerable to electronic warfare.

In addition, in this case, the UAV is damaged only by mechanical impact, and damage to its elements such as optical-electronic systems with thermal imaging and infrared channels, radar and direction finding equipment, and radio signal sources is unlikely.

The objective of the invention is to eliminate the above-mentioned shortcomings, improve the design of a grenade for a grenade launcher shot, characterized by obtaining a more effective nature of the propagation of the explosion process for hitting a target with greater reliability, and simplify the design.

The task is solved by the fact that the grenade for a hand-held grenade launcher to destroy unmanned aerial vehicles contains a warhead, a jet engine, and a stabilizer placed in a powder charge. The head part of the grenade has a body, which is a hollow shell, the internal volume of which is filled with complex spatial structures of a star-shaped form, monolithically connected to each other and to the walls of the body, as well as finely dispersed steel powder with an average particle size of 50-60 μm, and with a central detonating elongated cord located along the axis of the body, consisting of an explosive substance enclosed in a shell and a mixture of exothermic dispersed powder tightly packed around it in a sealed shell, fixed on one side in the nose of the body and on the other side with the rear cover of the body, pyrotechnically connected through a transfer charge with a detonator cap located in a piston with a safety spring-loaded striker inserted into the sleeve, and through an expelling charge with a pyro-retarder connected to a cavity with a powder charge formed by the rear cover of the body and an insert located in an adapter connecting the body with the nozzle bottom of the jet an engine having a central opening with a combustible plug, tightly connected to an insert having a blind central opening coaxially oriented with an opening in the nozzle bottom, each of which is connected to two or more openings, evenly spaced around the circumference and provided with combustible plugs having different geometric dimensions and combustion rates determined by the composition of the material, each of which is blocked by a spring-loaded rod with a lock that can move, connected to a cavity with a charge of gunpowder.

Fig. 1 - general view of the grenade shot, Fig. 2 - view of the filling of the housing shell, Fig. 3 - connection of the head part with the nozzle bottom of the jet engine, Fig. 4 - view with the arrangement of holes in the cylindrical insert, Fig. 5 - the housing in the form of a biconical design, connected to a cylindrical insert, Fig. 6 - the housing in the form of truncated cones connected by their bases, with a cylindrical insert between them.

In (Fig. 1) a shot consisting of a grenade (1) and a powder charge (2), the grenade consisting of a warhead (3), a jet engine (4) and a stabilizer (5) placed inside the powder charge (6), consisting of a crosspiece, four feathers freely rotating on axles, a base and a turbine (7).

The head part consists of a body made in two alternative versions.

The housing (8) is a hollow steel shell, the internal volume of which is filled with complex spatial structures of a star-shaped form, monolithically connected to each other and to the walls of the housing to ensure its rigidity (Fig. 2). The remaining volume inside the hollow shell of the housing is filled with finely dispersed steel powder with an average particle size of 50-60 μm.

The body of the head part shown in (Fig. 3) is connected by an adapter to the nozzle bottom (9) of the jet engine, which has a central opening with a combustible plug (10), tightly connected to an insert located in the adapter, which has a blind central opening, coaxially oriented with the opening in the nozzle bottom, which is connected to uniformly spaced openings (Fig. 4), located in the radial direction with an equal pitch, equipped with combustible plugs (11), having different geometric dimensions and combustion rates determined by the composition of the materials, each of which is blocked by the movement of a spring-loaded rod with a lock (12), which is not shown conditionally, connected to a cavity (13) with a charge of gunpowder (14).

As shown in (Fig. 5), along the central axis of the body there is a detonating extended cord (15), consisting of an explosive substance (ES), secured in a casing, tightly packed around it until completely filled with a mixture of exothermic powder (16) in a sealed casing, secured on one side in the nose of the body and on the other side in the rear cover of the body (17), shown in (Fig. 3), pyrotechnically connected through a transfer charge (18) to a detonator cap (19), located in a piston with a safety spring-loaded striker (20) inserted into the sleeve and through a knockout charge (21) with a pyro-retarder (22), connected to a cavity formed by the rear cover and an insert (23) with a powder charge.

The body can be made in the form of a biconical structure with an angle of 30 and 6 degrees, connected to a cylindrical insert, as shown in (Fig. 5) or in the form of truncated cones connected by bases with a cylindrical insert (Fig. 6).

The mixture of exothermic dispersed powder consists of a combustible metal: boron or aluminum and having fractions with a diameter of 1.0 to 20.0 μm and 1.0 to 10.0 μm, respectively, as well as an oxidizer: ammonium perchlorate or potassium perchlorate, having fractions with a diameter of 1.0 μm to 50 μm.

The tests conducted (Ignition and combustion of a mixture of boron with potassium and ammonium perchlorate in a free volume. UDC 536.46 Bauman Moscow State Technical University, 105005 Moscow, daiD@bmstu.ru) showed the combustion efficiency of these systems with a component ratio characterized by an excess coefficient of 0.35 to 0.5, providing the optimal combustion temperature of the mixture.

The composition of the mixture and the dispersion of the powder particles determine the ignition process and the stability of combustion in the air, the intensity of radiation, the spectrum of radiation, the presence of a condensed phase, the smoke in the screening zone, and stimulates the electrophysical properties of combustion products to ensure attenuation and reflection of the propagation of radio waves.

To form a given cloud size, the particle sizes are selected based on the conditions for determining the ignition induction period, which depends on the energy characteristics of the substance, the thermal characteristics of the environment, the conditions of gas flow around the particle, and the rate of their combustion.

Shooting from a hand-held grenade launcher, which includes a barrel with an inserted round, a thermal imaging sight with a built-in rangefinder attached to the barrel, a firing mechanism with a safety catch and a striker mechanism, to hit an aerial target is performed as follows. The grenade launcher detects the appearance of a drone and preliminarily estimates the distance to it. He turns on the thermal imaging sight with a laser rangefinder, moves one of the rods to the working position, thereby setting the required height of the grenade detonation and aims the grenade launcher at the drone, taking the necessary lead taking into account the trajectory of its flight. After the aiming point coincides with the point of impact, the grenade launcher is turned on by pressing the trigger, thereby ensuring the functioning of the powder charge, the combustion products of which impart a rotational motion to the grenade (using a turbine) and throw it out of the barrel bore. After the grenade flies out of the barrel, the powder charge of the jet engine ignites. At this time, the combustion products flow out through the nozzles and, at the same time, the plug located in the nozzle bottom burns. At the end of the combustion of the charge and the plug (10) located in the nozzle bottom (9), the combustion products of the gunpowder enter the hole opened by the rod (12) and ensure the combustion of the plug (11) with subsequent ignition of the gunpowder charge (14), which transmits through the pyro-retarder (22) a thermal energy flow for the operation of the expelling charge (21), moving the piston with the safety spring-loaded striker (20), ensuring the operation of the detonator cap (19) and through the transfer charge (18) creating a strong shock wave leading to the detonation of the high explosives in the detonating extended cord (15), thereby ensuring the destruction of the grenade body. The grenade design does not require the inclusion of a self-liquidator. After the combustion of the jet engine charge is finished, the grenade flies by inertia until it is destroyed in the UAV's kill zone. All pyrotechnic elements of the grenade are sequentially connected into a single fire chain, initially initiated by the combustion products of the powder charge, which ensures the combustion of all dangerous elements of the grenade and, in fact, its self-destruction occurs.

The destruction of the warhead body with the help of explosives with star-shaped striking elements, finely dispersed steel powder and exothermic dispersed powder reacting in flight, in combination with centrifugal forces from the axial rotation of the grenade ensures the fulfillment of the assigned task. The magnitude of the explosive power is selected for guaranteed destruction of the warhead body and the creation of a cloud of mechanical particles with reacting dispersed particles of a given size.

The advantage of the proposed device compared to the prototype is the creation of numerous striking elements and a high-temperature gas-dispersed cloud of a given volume and composition along the drone’s flight path.

When such a flow flows around the drone structure as it flies through the cloud, particles are deposited on its surface due to various transfer mechanisms associated with the action of inertial forces, turbulent pulsations, thermophoresis and Brownian diffusion. After the particles are deposited on the drone surface, a layer of melt film is formed, which enters into chemical reactions, and the drone material is destroyed, in addition, the drone structure is mechanically destroyed by the impact of the remains of the grenade body during the collision. All this leads to the failure of optical-electronic systems with thermal imaging and infrared channels, a digital aerial photo complex, radar equipment and direction finding equipment for radio signal sources, communication channels.

Claims (4)

1. A grenade for a hand-held grenade launcher for destroying unmanned aerial vehicles, consisting of a warhead, a jet engine, a stabilizer placed in a powder charge, characterized in that the warhead of the grenade, having a body that is a hollow shell, the internal volume of which is filled with complex spatial structures of a star-shaped form, monolithically connected to each other and to the walls of the body, as well as finely dispersed steel powder with an average particle size of 50-60 μm, and with a central detonating elongated cord located along the axis of the body, consisting of an explosive substance enclosed in a shell and tightly packed around it with a mixture of exothermic dispersed powder in a sealed shell, secured on one side in the nose of the body, and on the other side with the rear cover of the body, pyrotechnically connected through a transfer charge to a detonator cap located in a piston with a safety spring-loaded striker inserted into the sleeve, and through the expelling charge with the pyro-retarder, connected to the cavity with the propellant charge, formed by the rear cover of the housing and the insert, located in the adapter, connecting the housing with the nozzle bottom of the jet engine, having a central hole with a combustible plug, tightly connected to the insert, having a blind central hole, coaxially oriented with the hole in the nozzle bottom, each of which is connected to two or more holes, uniformly located around the circumference, and equipped with combustible plugs, having different geometric dimensions and combustion rates, determined by the composition of the material, each of which is blocked by a spring-loaded rod with a lock, capable of moving, connected to the cavity with the propellant charge. 2. A grenade according to claim 1, characterized in that the mixture of exothermic dispersed powder consists of a combustible metal: boron, aluminum, having fractions with a diameter of 1.0 to 20.0 μm, as well as an oxidizer: ammonium perchlorate or potassium perchlorate, having fractions with a diameter of 1.0 to 50.0 μm, tightly packed around a detonating elongated cord, in a sealed shell, with a ratio of components characterized by an oxidizer excess coefficient of 0.35 to 0.5. 3. A grenade according to item 1, characterized in that the body is made in the form of a biconical structure with an angle of 30 and 6 degrees. 4. A grenade according to item 1, characterized in that the body is made in the form of truncated cones connected by their bases, with a cylindrical insert between them.

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