RU185949U1 - DEVICE FOR UNMANNED AERIAL VEHICLES - Google Patents

Abstract

The utility model relates to the field of capture of small-sized unmanned aerial vehicles (UAVs) and can be used in military equipment. The device for fighting unmanned aerial vehicles (UAVs) consists of a missile with a guidance unit that delivers at least one container with a trap network with loads attached to the corners of the network to the UAV's location and stretching this network trap , providing cover and capture of UAVs. The container is located in the nose of the rocket, which is closed by a discarded fairing. At the back of the container are a network throwing unit and a launch control unit. The network throwing unit contains an explosive chamber with a propelling charge and an igniter associated with the launch control unit. The propellant charge is placed in front of the cavity of the explosive chamber, from which circular propellant exhaust trunks come out, oriented at an acute angle relative to the longitudinal axis of the chamber in the direction of flight of the rocket. Compensating gas trunks oriented around an acute angle relative to the longitudinal axis of the chamber in the direction opposite to the direction of flight of the rocket exit from the back of the cavity of the explosive chamber around the circumference. Compensatory venting trunks are disconnected from the throwing trunks by their sealing seals. A wad locking it is inserted into each of the trunks. Each cargo is placed in its propelling barrel with the possibility of departure from it due to the pressure of the powder gases of the propellant charge. 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 network is attached to the front end of the cargo. The technical result is the provision of capture high-speed UAV. 1 s.p. f-ly, 3 ill.

Description

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

A device network-trap for combating remotely piloted (unmanned) aircraft [RF patent for utility model No. 72753, IPC F41H 3/00, publ. 04/27/2008 g], consisting of a remotely piloted aircraft delivering at least one container with a trap network with sinkers attached to it in the area where the UAV is located.

The network is made of a metallized thread that increases its strength and twisted in the form of springs to create a springy effect when capturing a UAV. Sinkers are made with containers in the form of folding bellows harmonies, allowing you to adjust the speed and direction of movement of the network during the flight. Containers for accumulators (capacitors) are placed in the sinkers to create a high voltage supplied along the metal surface of the network, to disable the UAV control equipment.

The disadvantage is the complexity of the design, as well as the complexity of the packaging and deployment of the network with metal thread.

A device for controlling remotely piloted (unmanned) aircraft, adopted as a prototype [RF patent for utility model No. 72754, IPC F41H 13/00, publ. 04/27/2008 g], consisting of a delivery unit (rocket), delivering to the UAV location area at least one container with a trap network in it with loads attached at the corners of the network, stretching this network trap, providing cover and capture of the UAV, and guidance block. The device also includes a direction finding unit. The trap network is guided by 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 attaching kiper tapes.

However, the disadvantages of the known device are:

- big sizes,

- high engine power for towing the network due to its high aerodynamic drag;

- the use of sound-thermal method of aiming at the target, which is ineffective due to the low power consumption of the target - UAVs and the high cost of the guidance device itself, and the mandatory use of low temperatures for infrared sensors,

- this device, like the previous analogue, 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 at the speed agreed with the goal to “launch” the network - a trap, which is very difficult and time-consuming. During this time, the target may disappear.

The objective and technical result of the proposed utility model is to capture high-speed UAVs.

The technical result is achieved by the fact that the device for controlling unmanned aerial vehicles (UAVs), consisting of a missile with a guidance unit that delivers at least one container with a trap network with loads attached to the corners of the network with UAVs in the folded state, stretching this network-trap, providing cover and capture of UAVs, according to a utility model, the container is placed in the nose part of the rocket closed by the discarded fairing, and a network throwing unit and a block are placed behind the container the launching board, the throwing unit of the network contains an explosive chamber with a propelling charge and an igniter associated with the launch control unit, the propelling charge is placed in front of the cavity of the blasting chamber, from which circular throwing trunks exit, oriented at an acute angle relative to the longitudinal axis of the camera in the direction missile flight, while from the rear of the cavity of the blasting chamber around the circumference go compensation gas shafts oriented at an acute angle relative to the longitudinal the axis of the chamber in the direction opposite to the direction of the missile’s flight, with the compensating gas exhaust trunks disconnected from the propelling trunks sealing them, a wad locking it inserted into each of the trunks, each placed in its propelling barrel with the possibility of escape from it due to the pressure of the propellant propellant gases charge, 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 network is attached to the front end of the cargo.

Placing the container in the nose part of the rocket covered with a discarded fairing makes it possible to attack an enemy UAV in the opposite direction of movement, which greatly simplifies the attack task and reduces the attack time, increasing the reliability of neutralizing a high-speed UAV.

Placing the rear of the container of the network throwing unit and the launch control unit, wherein the network throwing unit contains an explosive chamber with a propellant charge and an igniter associated with the launch control unit, and the propellant charge is placed in front of the cavity of the explosive chamber, from which circumferential propellant exhaust pipes go, oriented at an acute angle relative to the longitudinal axis of the chamber in the direction of flight of the rocket, while compensation gas vents exit the back of the cavity of the explosive chamber around the circumference trunks oriented at an acute angle with respect to the longitudinal axis of the chamber in the direction opposite to the direction of the missile’s flight, moreover, compensating gas outlet trunks are disconnected from the throwing trunks by their sealing seals, a wad locking it is inserted into each barrel, each load is placed in its throwing barrel with the possibility of departure from due to the pressure of the propellant gases of the propellant charge, it provides the necessary angle of expansion of the cargo to open the network - traps and the necessary high speed to capture full UAV. An explosive chamber allows the use of a powerful propellant powder charge. In addition, due to the pressure of the powder gases from the common blast chamber, the same departure speed is created for all cargoes, ensuring the synchronism of their movement and, accordingly, the predictable direction of the network movement - traps for deploying it in front of a high-speed flying object and capturing it. At the same time, compensation gas vent channels minimize the impact of the impulse of gases generated from the operation of the propellant propellant charge and keep the direction and speed of the rocket unchanged, as well as eliminate the destructive shock loads of the device during the release of the trap network.

The execution of each load in the form of a cylindrical body with a deep recess at the rear end, while an exhaust sling is attached to the front end of the cargo, connected to the network provides a high speed of movement of goods and a high speed of the opening of the grid, ensuring the capture of a high-speed UAV. As is known [M.E. Serebryakov Internal ballistics of barrel systems and powder rockets, Oborongiz, M., 1962., p. 315] there is a direct dependence of the value of the speed of cargo on the pressure in the explosive chamber and the size of the end area of the cargo. When performing cargo with a deep excavation, it is possible to increase the flight speed of the cargo by 30%. The recess at the end of the cargo can be made in the form of a hemisphere or segment or cone.

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

The utility model is illustrated by drawings:

in FIG. 1 presents a General view of the UAV;

in FIG. 2 - view A, the design of the launching throwing unit of the network;

in FIG. 3 - general view of the cargo.

The device is as follows.

The device for controlling unmanned aerial vehicles (UAVs) (Fig. 1-3) consists of a remotely piloted aircraft - rocket 1, which delivers at least one container 2 with a network located in it in the folded state to the UAV's location (not shown) - a trap 3 with cargo 4 attached at its corners, stretching this network-trap 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 the resettable fairing 5 of the rocket 1. At the rear of the container 2 in the rocket 1 are placed the throwing unit 6 of the network, the launch control unit 7 and the guidance unit 8. The network throwing unit contains an explosive chamber 9 with a propelling charge 10 and an igniter 11, connected by an electric wire 12 to the start control unit 7, made in the form of a battery with automatic ignition of the charge 10. The propellant charge 10 is placed in front of the cavity of the explosive chamber 9, from which the propellant 13 discharge the bottom trunks oriented at an acute angle relative to the longitudinal axis of the chamber 9 in the direction of flight of the rocket 2. From the rear of the cavity of the blasting chamber 9 also around the circumference there are compensating 14 exhaust trunks 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 shafts are disconnected from the propelling 13 shafts and their sealing gaskets - two front 15 and rear 16 compensation rubber disks (washers) with interposed among them inertial metal disc 17. In each of shafts 13, 14 inserted into its locking wad 18. Hollow chamber 9 is closed with the rear end stopper 19. stub shafts 13,14 inclination angle relative to the longitudinal axis of the chamber 9 does not exceed 40 °. Weights 5 are placed each in its throwing barrel 13 with the possibility of departure from it due to the pressure of the powder gases of the propellant charge 10. Each load 5 is made in the form of a cylindrical body with a deep recess 20 at the rear end, while an exhaust sling is attached to the front end of the cargo 4 ( not shown) associated with network 3.

The device operates as follows.

When an enemy UAV is detected, the multichannel ground-based system gives a command to launch rocket 1. According to commands from the ground, rocket 1 is oriented in such a way as to approach the enemy UAV from the nose, which makes it possible to attack enemy UAVs in the opposite direction, significantly simplifying the attack task and reducing attack time, increasing the reliability of its neutralization. Guidance unit 8 fixes the target - the UAV and captures and adjusts the movement of missile 1. When approaching missile 1 to a predetermined distance to the UAV, a signal is sent to the throwing block 6 of the network and the network is shot - traps 3 into the target sensor (not shown) (not shown) side of the UAV.

The throwing unit 6 network - trap 3 works as follows. The command from the electronic guidance unit 8 is supplied to the battery of the start-up control unit 7, from where voltage is supplied via wire 12 to the igniter 11. From the igniter 11, a hot stream of gases and particles ignites the propellant powder charge 10, during the combustion of which gas is released and pressure increases in the front parts of the chamber 9. Under the influence of this pressure, the washer 15 is compressed and the channels of the shafts 13 are opened with the missile "weights 4. The goods 4 are thrown, stretching the net-trap 3 into the necessary shape, ensuring cover and capture of UAVs. In this case, the fairing 5 is reset by the releasing goods 4. The net - trap 3 immobilizes UAVs. Under the action of powder gases from the charge 10, the washer 15 gradually compresses and the disk 17 is displaced, followed by the compression of the washer 16. As the disk moves 17, the shafts 14 are closed, closed by wad 19. The pressure in the channels of shafts 14 increases and gases flow out of them together with wad 19 in the direction opposite to the direction of flight of the UAV 2. Thus, the impulse from charge 10 is compensated, which allows saving thread 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 displaced in the region of the compensation trunks 14 of the camera.

Currently, documentation is being developed, production and preliminary testing of prototypes of a device for controlling high-speed UAVs made in accordance with the claimed utility model are planned. Performance confirmed by calculations.

The information presented indicates the fulfillment of the following set of conditions when using the claimed utility model:

- a tool that embodies 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 embodying the claimed utility model in the implementation, capable of capturing a high-speed UAV;

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

Therefore, the claimed device meets the condition of "industrial applicability".

Claims (2)

1. A device for the control of unmanned aerial vehicles (UAVs), consisting of a missile with a guidance unit that delivers at least one container with a trap network in it when it is folded in a folded state with a trap attached to the corners of the network with loads stretching this network - a trap, providing cover and capture of UAVs, characterized in that the container is placed in the nose part of the rocket closed by the discarded fairing, the network throwing unit and the launch control unit are placed behind the container, the network throwing unit contains an explosive chamber with a propellant charge and an igniter associated with the launch control unit, a propellant charge is placed in front of the cavity of the explosive chamber, from which circumferential propellant vents are oriented, oriented at an acute angle relative to the longitudinal axis of the chamber in the direction of missile flight, while from the rear part of the cavity of the blasting chamber around the circumference exit compensating exhaust trunks oriented at an acute angle relative to the longitudinal axis of the chamber in the direction opposite to a missile’s flight, moreover, the compensating gas outlet trunks are disconnected from the throwing trunks with their seals, a wad locking it is inserted into each barrel, each load is placed in its throwing barrel with the possibility of departure from it due to the pressure of the powder gases of the propellant charge, each load is made in the form a cylindrical body with a deep recess at the rear end, while an exhaust sling connected to the network is attached to the front end of the cargo. 2. The device according to p. 1, characterized in that the recess at the end of the cargo is made in the form of a hemisphere, or segment, or cone.

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