RU202673U1 - UNMANNED AIRCRAFT COMBAT DEVICE - Google Patents

Abstract

The utility model relates to the field of capturing small-sized unmanned aerial vehicles (UAVs) and can be used in military equipment. An anti-unmanned aerial vehicle (UAV) device consists of a missile with a guidance unit that delivers at least one container to the UAV's location area with a trap net placed in it in a folded state with weights attached to the corners of the net, stretching this trap net , providing cover and capture of the UAV. The container is located in the nose part of the rocket, which is closed by a drop fairing. The net throwing unit and the launch control unit are located at the back of the container. The net throwing unit contains an explosion chamber with a propelling charge and an igniter connected to the launch control unit. The propellant charge is placed in the front part of the blast chamber cavity, from which propelling gas barrels emerge along the circumference, oriented at an acute angle relative to the longitudinal axis of the chamber in the direction of the rocket flight. Compensating gas vents exit the rear part of the blast chamber cavity along the circumference, oriented at an acute angle relative to the longitudinal axis of the chamber in the direction opposite to the direction of the rocket flight. Compensating gas vents are separated from the throwing shafts by locking them with seals. A wad is inserted into each of the barrels. Weights are placed each in its own throwing barrel. Each propelling gas barrel is equipped with a movable part installed in the specified barrel with the possibility of telescopic extension in the longitudinal direction when the load leaves the barrel. Each load is made in the form of a cylindrical body with a deep recess at the rear end, while an exhaust sling connected to the net is attached to the front end of the load. The technical result is an increase in the efficiency of capturing a high-speed UAV. 4 ill.

Description

The utility model relates to the field of capturing small-sized unmanned aerial vehicles (UAVs) and can be used in military equipment.

Known device for combating remotely piloted (unmanned) aircraft [RF patent for utility model No. 72754, IPC F41H 13/00, publ. 04/27/2008], consisting of a delivery unit (rocket), delivering to the UAV location area at least one container with a trap net placed in it with sinkers attached at the corners of the net, stretching this trap net, ensuring the covering and capture of the UAV, and guidance unit. The device also contains a direction finding unit. The trap network is aimed at the UAV using the guidance unit according to the direction finding unit data obtained by the sound-thermal method. Sinkers are made round with holes for fastening keeper tapes.

The disadvantage of the known device is that this device is ineffective for capturing a high-speed UAV capable of performing complex maneuvers, flying around obstacles. It is required to catch up with the target from above and "launch" the trap network with the speed agreed upon with the goal, which is very difficult and time-consuming. During this time, the target can hide.

Known device for combating unmanned aerial vehicles [RF patent for utility model No. 185949, IPC F41H 13/00, publ. 12/25/2018], taken as a prototype and consisting of a missile with a guidance unit, delivering at least one container to the UAV location area with a trap net placed in it in a folded state with weights attached to the corners of the net, stretching this trap net, providing covering and capturing of the UAV, the container is placed in the nose of the rocket part of the rocket closed by a discarded fairing, the net throwing unit and the launch control unit are located behind the container, the net throwing unit contains an explosion chamber with a propellant charge and an igniter connected to the launch control unit, the propellant charge is placed in the front part of the blast chamber cavity, from which propelling gas barrels emerge around the circumference, oriented at an acute angle relative to the longitudinal axis of the chamber in the direction of the rocket flight, while from the rear part of the blast chamber cavity along the circumference, compensation gas barrels emerge, oriented at an acute angle relative to the longitudinal axis of the chamber in nap the direction opposite to the direction of flight of the rocket, and the compensating gas barrels are disconnected from the propelling barrels by locking them with seals, a wad that locks it is inserted into each of the barrels, the weights are placed each in its own propelling barrel with the possibility of ejection from it due to the pressure of the propellant gases of the propellant charge, each weight is made in the form of a cylindrical body with a deep recess at the rear end, while an exhaust sling connected to the net is attached to the front end of the load.

The disadvantage of the prototype is that this device is not effective enough to capture a high-speed UAV capable of performing complex maneuvers, flying around obstacles.

The objective and the technical result to be achieved by the claimed utility model is to increase the efficiency of capturing a high-speed UAV by increasing the initial speed of cargo with attached exhaust lines connected to a trap net by telescopic transformation of throwing shafts when cargo leaves them.

The technical result is achieved by the fact that a device for combating unmanned aerial vehicles (UAVs), consisting of a missile with a guidance unit, delivering at least one container to the area where the UAV is located with a trap net placed in it in a folded state with weights attached to the corners of the net, stretching this trap net, providing covering and capturing of the UAV, the container is placed in the nose part of the rocket closed by a discarded fairing, the net throwing unit and the launch control unit are located behind the container, the net throwing unit contains an explosion chamber with a propellant charge and an igniter connected to the launch control unit , the propellant charge is placed in the front part of the blast chamber cavity, from which propelling gas barrels emerge along the circumference, oriented at an acute angle relative to the longitudinal axis of the chamber in the direction of the rocket flight, while compensating gas barrels emerge from the rear part of the blast chamber cavity along the circumference, or chambers oriented at an acute angle relative to the longitudinal axis in the direction opposite to the direction of flight of the rocket, and the compensating gas vents are separated from the throwing barrels by locking them with seals, a wad is inserted into each of the barrels, each of the weights is placed in its own throwing barrel, each load is made in the form a cylindrical body with a deep recess at the rear end, while an exhaust sling connected to a network is attached to the front end of the load, according to the utility model, each throwing gas outlet is equipped with a movable part installed in the specified barrel with the possibility of telescopic extension in the longitudinal direction when the load leaves the barrel ...

Equipping each throwing barrel with a movable part installed in the specified barrel with the possibility of telescopic extension in the longitudinal direction when the load is flying out of the barrel provides, in comparison with the prototype, an increase in the length of the throwing barrel, which leads to an increase in the departure speed of each load and, accordingly, to a reduction in the deployment time trap nets for capturing a high-speed UAV, increasing the efficiency of its capture.

The presence in the claimed utility model of features that distinguish it from the prototype, allows us to consider it as corresponding to the "novelty" condition.

The utility model is illustrated by drawings:

in fig. 1 shows a general view of the UAV;

in fig. 2 - view A, the design of the net throwing unit is shown;

in fig. 3 - the movable part of the throwing barrel in its initial state, view B in Fig. 2;

in fig. 4 - the movable part of the throwing barrel in its triggered state when the load leaves the barrel.

The device is made as follows.

The device for combating unmanned aerial vehicles (UAVs) (Fig. 1-2) consists of a remotely piloted aircraft - a rocket 1, delivering to the UAV location area (not shown) at least one container 2 with a network placed in it in a folded state - trap 3 with weights 4 attached at its corners, stretching the given trap net 3, providing cover and capture of the UAV. The container 2 is placed in the nose part of the rocket 1, which is closed by a discarded fairing 5, behind the container 2, in the rocket 1, a throwing unit 6 of a net, a launch control unit 7 and a guidance unit 8 are placed in a row. connected by an electric wire 12 with the launch control unit 7, made in the form of a battery with automatic ignition of the charge 10. The propellant charge 10 is placed in the front part of the cavity of the explosive chamber 9, from which propelling 13 gas barrels emerge around the circumference, oriented at an acute angle relative to the longitudinal axis of the chamber 9 in the direction of flight of the rocket 2. Compensation 14 gas barrels extend from the rear of the cavity of the explosive chamber 9 along the circumference, oriented at an acute angle relative to the longitudinal axis of the chamber 9 in the direction opposite to the direction of flight of the rocket 2. Compensation 14 gas barrels are separated from the propelling barrels 13 locking them with two front 15 and rear 16 compensating rubber disks (washers) with an inertial metal disc 17 placed between them. A wad that locks it is inserted into each of the barrels 14 18. The chamber cavity 9 is closed from the rear end with a plug-cap 19. The angle of inclination of the barrels 13 , 14 relative to the longitudinal axis of the chamber 9 does not exceed 40 °. Each propelling gas barrel 13 (Fig. 3) is equipped with a movable part installed in the specified barrel with the possibility of telescopic extension in the longitudinal direction when the load is flying out. The movable part is made up of several, for example, three, concentrically located sections 20, 21, 22, moving one relative to the other and provided with flanges 23 at the ends, limiting the movement of the sections relative to each other at their maximum extension from the barrel. In this case, each propelling gas outlet 13 has a stop shoulder 24, against which the outer section 20 of the movable part abuts against the shoulder 23. In this case, the outer section 20 is installed in the propelling gas barrel 13 with the condition that its front end does not go beyond the outer opening of the throwing gas barrel 13. The weights 5 are each placed in the channel of the inner section 22 with the possibility of escaping from it due to the pressure of the propellant gases. A wad 25 is inserted into each section 22. Each weight 5 is made in the form of a cylindrical body with a deep recess 26 at the rear end, while a pulling strap is attached to the front end of the load 4, one of the ends of the net is a trap (not shown) connected to network 3.

The device works as follows.

When an enemy UAV is detected, the ground-based system of a multichannel means gives a command to launch missile 1. According to commands from the ground, missile 1 is oriented so as to enter the enemy UAV from the nose, which makes it possible to attack the enemy UAV on a head-on course, greatly simplifying the attack task and reducing the time attacks, increasing the reliability of its neutralization. The guidance unit 8 fixes the target - the UAV and carries out its video capture and corrects the movement of the rocket 1. When the rocket 1 approaches the specified distance to the UAV, a signal is sent to the electronic unit, and from it the command to supply voltage to the igniter, according to the signal of the non-contact target sensor (not shown) block throwing 6 nets and shooting nets-traps 3 in the direction of the UAV. Block throwing 6 net-traps 3 operates as follows. The command from the electronic guidance unit 8 is sent to the battery of the launch control unit 7, from where the voltage is supplied through the wire 12 to the igniter 11. From the igniter 11, a hot stream of gases and particles ignites the propellant powder charge 10, during which combustion there is a release of gases and an increase in pressure in the front parts of the chamber 9. Under the action of this pressure, the washer 15 is compressed and the channels of the barrels 13 with the telescopic movable part and the projectile weights 4 open. sections 20, 21, 22 of the movable part of the barrel 13, which alternately extend into a single barrel, lengthening it, up to the maximum extension of the sections and fixing relative to each other with their collars 23. A further increase in pressure leads to the expulsion of the load 4 with an attached pulling strap at an increased speed trap nets 3. Thus, weights 4 are thrown, stretching with net-trap 3 in the required shape, providing coverage and capture of the high-speed UAV. By the outgoing weights 4, the fairing 5 is dropped. Trap net 3 immobilizes the UAV. In this case, under the action of powder gases from the charge 10, the washer 15 is gradually compressed and the disk 17 is displaced, followed by the compression of the washer 16, as a result of which the gas compensation shafts 14 are opened, closed by the wads 19. The pressure in the channels of the barrels 14 and the outflow of gases from them occurs. together with wads 19 in the direction opposite to the direction of flight of the UAV. This compensates for the pulse from the charge 10, which allows you to keep the direction and speed of the rocket 1 unchanged. The presence of the disk 17 between the two washers 15,16 serves as an inertial factor that keeps them moving into the area of the compensation shafts 14 of the chamber.

Currently, the development of documentation is underway, it is planned to manufacture and preliminary tests of prototypes of a device for combating high-speed UAVs, made in accordance with the claimed utility model. Efficiency is confirmed by calculations.

The presented information testifies to the fulfillment when using the claimed device under its following set of conditions:

- the means embodying the claimed utility model, in its implementation, is intended to capture small-sized unmanned aerial vehicles (UAVs) and can be used in military equipment;

- a tool that embodies the claimed utility model, when implemented, is capable of increasing the efficiency of capturing a high-speed UAV;

- for the claimed device for combating unmanned aerial vehicles in the form in which it is described in the formula of the utility model, the possibility of its implementation has been confirmed using the means and methods described in the application and known before the priority date.

Therefore, the claimed device for combating unmanned aerial vehicles meets the condition of "industrial applicability".

Claims (1)

A device for combating unmanned aerial vehicles (UAVs), consisting of a missile with a guidance unit, delivering at least one container to the UAV location area with a trap net placed in it in a folded state with weights attached to the corners of the net, stretching this trap net, providing covering and capturing of the UAV, the container is placed in the nose of the rocket part of the rocket closed by a discarded fairing, the net throwing unit and the launch control unit are located behind the container, the net throwing unit contains an explosion chamber with a propellant charge and an igniter connected to the launch control unit, the propellant charge is placed in the front part of the blast chamber cavity, from which propelling gas barrels emerge around the circumference, oriented at an acute angle relative to the longitudinal axis of the chamber in the direction of flight of the rocket, while from the rear part of the blast chamber cavity along the circumference, compensation gas barrels emerge, oriented at an acute angle relative to the longitudinal axis of the chamber in the direction opposite to the direction of flight of the rocket, and the compensating gas barrels are separated from the throwing barrels by locking them with seals, a wad that locks it is inserted into each of the barrels, each weight is placed in its own throwing barrel, each weight is made in the form of a cylindrical body with a deep recess at the rear end, while an exhaust sling connected to a network is attached to the front end of the load, characterized in that each propelling gas outlet is equipped with a movable part installed in the specified barrel with the possibility of telescopic extension in the longitudinal direction when the load leaves the barrel.

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