Interceptor drone
Patent Information
- Application Number
- PCT/RU2026/050063
- Authority / Receiving Office
- WO · WO
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2026-03-23
- Filing Date
- 2026-03-25
- Publication Date
- 2026-10-01
Smart Images
Figure RU2026050063_01102026_PF_FP_ABST
Abstract
Description
[0001] MIIK F41H 11 / 02
[0002] DESCRIPTION of the invention
[0003] The BILA unmanned aerial vehicle is an interceptor with ammunition for individual use.
[0004] Field of technology
[0005] The invention relates to countering unmanned aerial vehicles (UAVs), primarily those with a light payload, particularly for comprehensive protection against enemy personnel. The small size and visibility of such UAVs make them difficult targets for detection systems, especially at low altitudes and from the ground. The UAV interceptor is a personal protective equipment item. The UAV is also a contactless protection device and can be used in the development of a personal protection system for both humans and equipment.
[0006] Purpose
[0007] UAVs are used based on established aircraft types and employ counter-drone systems. However, existing anti-UAV systems require large payloads and payloads. It is important that the onboard ammunition supply, in terms of weight and dimensions, allows for multiple engagements of enemy UAVs in a single flight, as well as the reusability of the aircraft with the ability to reload. They are primarily used to engage UAVs such as small FPV drones, multicopters, and helicopter-type UAVs. Their purpose is to ensure compact size and weight for individual use, allowing them to be carried continuously in a soldier's or operator's kit for immediate protection in combat conditions, similar to small arms.The ability to equip an interceptor UAV with a container containing barrel-less ammunition with electrical firing initiation, equipped with a kinetic, incendiary, high-explosive, and high-explosive fragmentation warhead, and to receive a command to initiate firing.
[0008] Prior art
[0009] A known invention is the "Device-Fighter for Destroying Remotely Piloted (Unmanned) Aerial Vehicles," patent RU 2490585, published August 20, 2013, F41H 11 / 04. It is equipped with surveillance cameras and up to four motion sensors, as well as up to four interconnected containers for striking elements, designed as cartridge cassettes. However, it uses needles with ribbon parachutes, which are not very effective. A ribbon parachute attached to the needle is pulled from the cartridge case, creating significant aerodynamic drag on the flight of the remotely piloted aircraft. Furthermore, the ribbon parachute payload is significant in size and weight, and does not ensure accuracy or neutralize the UAV without the use of additional combat assets.
[0010] The invention "Device-fighter for the destruction of remotely piloted (unmanned) aerial vehicles (DILA)," patent RU 2 490 584, published August 20, 2013, MHKF41H 11 / 04, comprises a remotely piloted aerial vehicle and a ground guidance system in the form of a radar. The vehicle is equipped with surveillance cameras and motion sensors, as well as interconnected containers for destructive elements, made in the form of cassettes with nets made of high-strength polymer thread. The nets are used as trap nets.
[0011] It enables interception using ground-based radar guidance, precise targeting using optical surveillance devices (video cameras), and automatic ejection of projectiles. However, it requires the additional installation of cartridge-shaped weight containers with ribbon parachutes in the casings, which does not guarantee the net's protection from foreign objects entering the propeller. This complicates and increases the weight of the design and requires additional lattice protection for the propellers. All these elements add weight and increase the size of the aircraft.
[0012] The invention "Unmanned Aerial Vehicle-Interceptor," patent RU 2 699 148, published September 3, 2019, MIK B64C 39 / 02, B64D 7 / 04, F41A 25 / 10, comprises a fuselage designed as a truss structure, allowing for the installation of standard small arms without any special design modifications. The disadvantages of this solution include its high weight and size, as firing the system requires a bulky small arms system attached to the fuselage's structural frame.
[0013] A utility model, "Aircraft for Combating Short-Range Unmanned Aerial Vehicles," is known, patent RU 94690, published May 27, 2010, IPC F41H 13 / 00. It comprises a payload unit consisting of a munition with a control system for its detonation, mounted on a carrier shaped like a miniature unmanned aerial vehicle. This allows for remote detonation via the control system. However, this is a single-use device, which cannot be used multiple times or independently of the completed destruction mission. It is an expendable destruction tool and functions as a munition.
[0014] The invention "Cartridge with Electrothermal Ignition" (patent GB2349939A, published 0408 1999, F42B 5 / 08) is known. It comprises a cartridge and a cartridge with an electrothermal igniter. The cartridge contains a propellant charge that ignites due to the formation of electric arc discharges within the propellant charge. At least one wire is located within the propellant charge, through which a current of sufficient strength passes to ignite the charge, causing the wire to vaporize explosively. The cartridge contains a cartridge case at least partially filled with propellant powder. The cartridge has an electrothermal igniter. However, the invention solves a different problem and is aimed at increasing the power and / or high-voltage strength of the cartridge. It is based on a known solution for using the design of conventional large-caliber cartridges with a highly flammable cartridge case.
[0015] The invention "Strike Remotely Controlled Unmanned Aerial Vehicle," patent UA_31234, published March 25, 2008, H04N 07 / 185, B64C30 / 00, is a strike UAV containing a video surveillance system and an additional explosive charge with a contact fuse. It is used to protect ground targets, but is not intended to carry a cartridge containing barrel-less, electrically initiated ammunition.
[0016] The invention "Traumatic Cartridge and Traumatic Element for a Barrel-less Weapon" is known, patent RU 2 179 700 C1, published 20.02.2002, IPC F42B 5 / 073, F42B 5 / 08, F42B 30 / 02. It pertains to cartridges for hand-held, portable, and wearable barrel-less self-defense weapons. It contains a traumatic cartridge for a barrel-less weapon, comprising a cartridge case, a propellant charge, an igniting element, and a traumatic element. The igniting element is an electric primer, an igniter, and a gas generator pressed into the cartridge case.
[0017] Implemented in a barrel-less ammunition for a barrel-less pistol of the PB-4Osa type."
[0018] The cartridge and bullet are designed to prevent serious bodily injury to the shooter. However, they are used in hand-held, barrel-less self-defense weapons that fire traumatic elements to repel an attack through pain. They are not used in power supply and ammunition systems (PAS) for small UAVs designed to engage enemy aircraft.
[0019] The invention "Barrelless Launcher and Its Cartridge Case" (patent RU 2 793 003, IPC F42B 5 / 00, F41C 3 / 00) comprises a barrelless launcher and a cartridge case therefor. It enables electric initiation and uses electric cartridges with a cartridge case with conductive contacts. The cartridge case comprises a polymer housing designed to engage with the trigger mechanism's cartridge case locking and extraction mechanism and is equipped with conductive contacts at both poles. It pertains to hand-held portable firearms, specifically barrelless weapons, where the cartridge case serves as the chamber and barrel during firing. It is used as a means of defense against attack or in compact "pocket" pyrotechnics using a low-impulse charge. It addresses the issue of increasing shooting efficiency, reliability, safety in handling, ease of maintenance, ease of use and operation.But it is not used as a compact anti-drone device and is not installed on UAVs.
[0020] The closest technical solution, which has been adopted as a prototype, is the invention "Multipurpose Aircraft and Method for Neutralizing an Unmanned Aerial Vehicle Using It," patent RU 2 851 056, published 18.11.2025, IPC F41H 11 / 02. The multipurpose aircraft pertains to the field of aviation, in particular to devices and methods for countering UAVs such as airplanes and helicopters, and is equipped with kinetic weapons made with underbarrel devices for firing from a hook, located in equipped, controlled, rotating containers. Hooks or harpoons with a pyrotechnic cartridge inside are used as hooks. The containers are located on different external hardpoints of the multipurpose aircraft and / or in different internal compartments of the multipurpose aircraft.The destructive means used are hooks and parts of halyards, or the release of a targeted load and / or air braking means and / or their modules, designed for their attachment to an unmanned aerial vehicle in flight, which does not lead to the final neutralization of an enemy explosive device that is dangerous to humans.
[0021] Inventive problem
[0022] The inventive task is to develop a small UAV for the reliable protection of a soldier or operator on the ground when protection from the damaging effects of an enemy UAV explosion is required. This requires the acquisition of an enemy UAV at any altitude along its flight path, whether within the kill zone of an interceptor UAV and / or within the operator's line of sight, and the destruction or damage of the enemy UAV along with its explosive payload, preferably at a safe distance from the operator or soldier. Furthermore, after detecting an enemy UAV, the response time of the anti-drone system must be sufficient to promptly detect the enemy UAV, for example, no more than 60 seconds, and the ability to repeatedly use the interceptor UAV to destroy the enemy UAV. Furthermore, the proposed technical solution should not generate any significant recoil, requiring compensation devices.
[0023] The munition's small weight and dimensions, electric initiation, and barrel-less design allow it to be used on compact unmanned aerial vehicles weighing up to 2 kg. The use of an automated control and guidance system will allow the creation of a miniature personal UAV to intercept enemy kamikaze UAVs.
[0024] Technical result
[0025] The technical result of the proposed design of the UAV and the power supply and ammunition complex (PSAC) for this UAV is:
[0026] — expansion of the arsenal of technical means for a known purpose through the creation of an unmanned aerial vehicle with expanded functional capabilities;
[0027] — minimization of weight and dimensions - ease of wearing and use, safety of wearing;
[0028] — quick preparation for maneuvering - launch and flight of the UAV;
[0029] — the ability to capture an enemy UAV (targeting) and increase the likelihood of disruption of the enemy UAV's mission, i.e., putting it out of operational condition, for example, loss of stability.
[0030] The technical result is achieved due to the UAV being equipped with anti-drone means containing, at a minimum, kinetic weapons of various types. The kinetic weapons are provided with underbarrel firing devices and are housed and equipped in controlled rotating ammunition containers, with the rotating containers located in various internal compartments of the UAV. The UAV is also equipped with a hardware and software system with a processor, an onboard video monitoring system, a radio module, and a battery pack. A new feature is that the UAV is equipped with a frame (1), a launch preparation system (2), a control unit (3), a firing module (4), and a power supply and ammunition system (PSAS) (5). The frame (1) is designed with detachable or non-detachable joints with a handle (6) attached to it.The frame (1) with the handle (6) forms a single supporting body (7), in which internal compartments for the ECM (5) are placed with seats provided with locks (8) of the ECM body (7) with a reset button (9) of the ECM, and the frame is connected by rotary hinges (10) with beams (11) made with the possibility of folding. A clip with cartridges is placed in the ECM, provided with its own lock in the form of a latch (12). The beams can be in the form of beams of a frame structure or consisting of a single integral console. On the supporting body (7) of the frame (1) at least one static or rotating chamber (not shown) is placed. The rear and front rotary hinges (10) are fixed by means of a launch preparation system (2), including levers (13), beam locks (14), stoppers (15) and an electromechanical trigger button (16). The launch preparation system (2) is housed in the supporting body (7). The front and rear beams (consoles, girders) (11) are connected to the supporting body (7) by means of front and rear rotary hinges (10).The hinges can be made symmetrically and / or asymmetrically with respect to the longitudinal axis "A" of the supporting body (7). The levers (13) and locks (14) of the beams (11) of the launch preparation system (2) are made with the possibility of retracting (unlocking) after pressing the trigger button (16). On each beam (11) there is an engine (17), connected to the corresponding beam (11), which is provided with folding blades (18) of the rotors (19). And each engine (17) is connected to the control unit (3) and the stopper (15). The UAV is also provided with a power supply and ammunition complex (PSC) (5), which is provided with a battery (20) and a shot initiation system (21), located inside the body (22) of the PSC. The shot initiation system (21) of the PSC is electrically connected to the control unit (3) via the firing module (4). Moreover, the firing module (4) is connected by means of spring contacts (23) in a parallel circuit of electrical pairs (“+” and “-”) to a conductive clip (24) with each cartridge (25).The cartridge (25) may be of various types, such as bullet, shot, buckshot, gas, or incendiary bullet cartridges. However, the cartridges must be suitable for the KEB (5), which is equipped with an electric trigger for firing a barrel-less cartridge. The KEB (5) comprises a housing (22), in the rear portion of which a groove "a" is located for locating the locking device (8) of the housing (22) of the KEB (5) in the mounting positions of the supporting housing (7).
[0031] In particular embodiments, the control unit (3) is electrically connected to the battery (20), the firing module (4) and the launch preparation system (2) and is provided (unit 3) with sensors, indicators, a radio module (not shown conditionally). The control unit (3) can be provided with at least two rotating cameras implementing a binocular vision system (not shown conditionally). And the control unit (3) can be additionally provided with an external negative contact (ground contact) (26). For example, the launch preparation system (2) is configured to switch on power from the battery (20) to the control unit (3). In this case, it is possible to move the stoppers (15) away from the levers (13) and the locks (14) of the beams (11) to open the beams (11) with the blades (18). The ECU (5) can be equipped with a group of positive and negative contacts for connection to the storage battery (20), which are brought out of the ECU housing (22).In a particular case, the ECU (5) is provided with pairs of positive and negative contacts of the shot initiation system (21) brought out to the outside of the housing (22) for connection with the external contacts of the firing module (4). In the context of the application, the "ground" contact may structurally be one. The "ground" contact is understood to be the established name of the negative terminal. In other words, a plurality of positive contacts are connected to a single negative contact. In the lower part of the housing (22) of the ECU, for example, a conductive clip (27) for cartridges (25) or other ammunition is fixed, contacting the lower spring contacts (23) of the ECU. The current-conducting clip (24) and the clip for cartridges (27) may be made as a single part from a conductive material, or may be a composite part. The clip (27) may also accommodate at least two cartridges (25) of any type.For example, the KEB (5) is equipped with cartridges (25) in the form of a kinetic or incendiary or high-explosive or high-explosive fragmentation warhead, which can be combined into a clip (27). In a particular case, the cartridge (25) of the clip (27) for ammunition contains an incandescent filament (28), which is an electric igniter, gunpowder or a gunpowder charge (29) and a bullet (30). In various embodiments, at least two wide-angle static cameras can be placed on the supporting body (7) of the frame (1). These cameras can provide binocular vision. The hinges (10) of the beams (11) can be made in the form of spring hinges. The handle (6) and the frame (1) can be made with large openings to lighten the structure and reduce windage in flight. The start-up preparation system (2) is made, for example, in the form of a push-button (spring, stepped, electro-mechanical) start / stop button connected to hinges (10) and to a battery (20) and / or a control unit (3).The supporting body (7) of the frame (1) can be provided with a light indicator. For example, a battery (20) and contacts (23) made spring-loaded are located inside the body (22) of the ECU. Additionally, the UAV can be provided with a system for fixing to the UAV - a base, equipped with a system for releasing small UAVs for their use in a swarm (not shown conditionally). The control unit (3) can be automatically linked to the shot initiation system (21) by connecting the external negative contact ("ground") (26) of the firing module (4) with one of the spring-loaded contacts (23), which is the negative contact ("ground") (31) of the ECU via a cable (32) of the shot initiation system (21). The other spring-loaded contacts (23) of the ECU are positive and are connected to the corresponding ECU munition.In another embodiment, the firing module (4) may be automatically linked to the firing initiation system (21) based on the software of the control system (3), which is a hardware and software device and is triggered based on the results of analyzing the video stream from the UAV cameras and / or from the operator's console (not shown). In another embodiment, the firing module (4) may be automatically linked to the firing initiation system (21), for example, by connecting the spring-loaded negative contact (31) ("ground") of the ECU to the negative terminal of the battery (20) of the ECU.
[0032] The design of the UAV interceptor is illustrated by drawings, which, however, do not cover all possible UAV designs for individual use.
[0033] Fig. 1 shows the UAV in a folded position, side view;
[0034] Fig. 2 shows the UAV in a folded position, viewed from below;
[0035] Fig. 3 shows the UAV in the folded position, rear view;
[0036] Fig. 4 shows the UAV in the folded position, front view; Fig. 5 shows the UAV in the open position of the beams with blades, side view;
[0037] Fig. 6 shows the UAV with its beams and blades open, viewed from below;
[0038] Fig. 7 shows the UAV with its beams and blades open, rear view;
[0039] Fig. 8 shows the UAV with its beams and blades open, front view;
[0040] Fig. 9 shows the launch preparation system, side view;
[0041] Fig. 10 shows the launch preparation system, section A-A;
[0042] Fig. 11 shows the rotary hinge (10) of the launch preparation system: a) in the folded position; b) in the retracted position;
[0043] Fig. 12 shows the latch (8) of the housing (7) of the electronic control unit (5) with the reset button (9) of the electronic control unit (5): a) in the pressed position; b) in the released position;
[0044] Fig. 13 shows a shot initiation system (21) without an external negative contact (“ground”) (26);
[0045] Fig. 14 shows a shot initiation system (21) with an external negative contact (“ground”) (26);
[0046] Fig. 15 shows a section of the KEB without cartridges;
[0047] Fig. 16 shows the KEB in the open position.
[0048] The UAV interceptor with ammunition for individual use is designed as follows.
[0049] Implementation
[0050] A handle (6) is attached to the frame (1) with detachable or non-detachable joints. Together they form a supporting body (7). It is made hollow and can be provided with holes to lighten the structure and reduce windage in flight. Inside the supporting body (7) there is a cavity with mounting places for the body (22) of the ECB (5). In the rear part of the body (22) there is a groove "a" for placing the lock (8) of the body (22) of the ECB (5) (see Fig. 15, 16) in the mounting places of the supporting body (7). When the reset button (9) of the ECB (5) is pressed, the body (22) of the ECB is released, allowing the body (22) to be removed together with the storage battery or single battery (20), the shot initiation system (21), and the clip (27) with cartridges (25) located inside the body (22) of the ECB. This allows you to quickly and conveniently recharge or replace batteries and replace cartridges (25) in the clip (27).
[0051] The supporting body (7) also houses the launch preparation system (2), the control unit (3) and the firing module (4).
[0052] The launch preparation system (2) (see Fig. 9, 10, 11) ensures that the beams (11) are held on the frame (1) in the folded position and that the beams (11) are quickly retracted into the working position for the UAV flight. The frame (1) is connected by rotary hinges (10) to the beams (11), which also belong to the launch preparation system (2) (see Fig.
[0053] 11). The rear and front pivot joints (10) are fixed by means of the launch preparation system (2). The launch preparation system (2) is housed in the supporting body (7). The launch preparation system (2) is equipped with levers (13) connected to each beam (11), beam locks (14), stoppers (15) of the beams (11) and an electromechanical release button (16). The lever (13) is structurally provided with a projection on one side for fixing it with a tooth of the lock (14), and a hook on the other side for holding the beam (11) when the beams (11) are folded. The lever (13) is mounted on an axis with the possibility of rotation. When the electromechanical trigger button (16) is pressed, it mechanically acts on the locking tooth (14), the locking tooth (14) is moved away from the projection of the lever (13), thereby releasing the hook for holding the beam (11), at the same time the electrical contact of the electromechanical trigger button (16) is closed (see Fig. 13,14), supplying power from the battery (20) to the control unit (3).Under the action of the rotary hinges (10) between the beams (11) and the frame (1), which are made spring-loaded, the front and rear beams (11) open relative to the supporting body (7) of the frame by means of the front and rear rotary hinges (10). In the opened position, the rotary hinges (10) enter the projections of the frame of the stoppers (15) (see Fig. Pa, b) and are secured in the working position. The stoppers (15) of the beams (1) can be a torsion spring pressing the beam (11) to the supporting body (7). The hinges (10) can be made symmetrically and / or asymmetrically relative to the longitudinal axis "A" of the supporting body (7) of the frame (1) depending on the design of the blades (18). On each beam (11) there is an engine (17), connected to the corresponding beam (11), which is equipped with folding blades (18) of the rotors (19). And each engine (17), connected to the control unit (3), begins to spin the rotors (19) after the beams (11) are opened and after the stoppers (15) are retracted.
[0054] The UAV is also equipped with a power supply and ammunition system (PSAS) (5), which is equipped with a battery or one battery (20) and a shot initiation system (21), located inside the body (22) of the PSAS. The shot initiation system (21) of the PSAS is electrically connected to the control unit (3) via the firing module (4) (see Figs. 13, 14).
[0055] The firing module (4) is connected by means of spring contacts (23) in a parallel circuit of electrical pairs ("+" and "-") by a conductive collar (24) with each cartridge (25). The firing module (4) can be additionally provided with an external negative contact ("ground") (26). The spring contacts (23) are made with one negative contact (31), the rest are made positive. The ECU (5) can be provided with pairs of positive and negative contacts combined into a group for connection with a storage battery or accumulator (20), brought out to the outside of the ECU casing (22). In this case, the ECU (5) is provided with pairs of positive and negative contacts of the shot initiation system (21), brought out to the outside of the ECU casing (22) for connection with external contacts ("ground") (26) of the firing module (4).In this case, the control unit (3) and the firing module (4) are automatically connected to the firing initiation system (21) by connecting the external negative contacts ("ground") (26) of the firing module (4) with the negative contact ("ground") (31) of the KEB by means of a cable (32) and cables (33) with the remaining spring-loaded contacts (23), which are the positive contacts connected to the corresponding KEB ammunition in the firing initiation system (21).
[0056] In another case, the control unit (3) and the firing module (4) can be automatically connected to the firing initiation system (21), for example, by connecting the spring-loaded negative contact (31) ("ground") of the ECU to the negative terminal of the battery (20) of the ECU. (see Fig. 13).
[0057] In all embodiments, the control unit (3) and the firing module (4) can be automatically linked to the shot initiation system (21) based on the software of the control system (3), which is a hardware and software device and is triggered by the analysis of the video stream from the UAV cameras and / or from the operator's console. Also, the proposed UAV - interceptor with munitions for individual use can be additionally equipped with devices for fixing to the UAV - base, equipped with a system for dropping small UAVs for their use in a swarm. Since the proposed UAV is lightweight, it can be placed on a large carrier UAV in large numbers and it is reusable, i.e. can park independently. In the lower part of the body (22) of the KEB, for example, a clip (27) for cartridges (25) or other ammunition is fixed. This clip (27) can also contact the lower spring contacts (23) of the KEB and its structural part can be designed as a conductive clip (24).The magazine (27) is released by a latch (12), made, for example, in the form of a spring-loaded plate. The magazine (27) can also accommodate at least two cartridges (25) of any type. For example, the KEB (5) is equipped with cartridges (25) in the form of a kinetic or incendiary or high-explosive or high-explosive fragmentation warhead, which can be combined into the magazine (27). For example, the cartridge (25) of the magazine (27) for ammunition contains a filament (28), gunpowder (29), and a bullet (30).
[0058] Thus, the ECU (5) is a housing (22), in the rear part of which there is a groove "a" for fixing in the shaft of the housing (7) of the UAV-interceptor, in the front part at the top there are combined in a group positive and negative contacts of the storage battery (20), below - combined in a group positive contacts of the shot initiation system (21) and one negative contact ("ground") (31). In the lower part of the housing, a clip (24) made of a conductive material is fixed on a hinge, which comes into contact with each munition, and the ECU housing (22) is provided with a lock (8). Inside the housing there is a battery (20) and spring-loaded contacts (23), including one negative contact (31) and the remaining positive contacts.
[0059] For example, it's possible to use the "Osa" type ammunition, which has a diameter of 18 mm, a height of 45 mm, and a mass of 25 grams. The bullet's kinetic energy is 91 J, enough to destroy a target's plastic casing from a distance of several meters. Furthermore, the shot doesn't generate any significant recoil, requiring technical solutions to compensate for it.
[0060] The ammunition's small weight and dimensions, electric initiation, and barrel-less design make it ideal for installation on compact unmanned aerial vehicles weighing up to 2 kg. The use of an automated control and guidance system will allow the creation of a miniature personal UAV to intercept enemy kamikaze UAVs. The cartridge and bullet eliminate the risk of serious injury to the shooter at a distance of 1 m and guarantee a stopping effect. Various types of ammunition can be used, including metal, rubber, incendiary, and others.
[0061] The UAV interceptor with ammunition for individual use operates as follows.
[0062] The control unit (3) is started by the launch preparation system (2), receives electrical energy from the battery (20), receives data and is controlled by the sensor system and the indicator system, receives and sends control commands via the radio module, and transmits commands to the front and rear engines (17), and also controls the firing module (4) and the shot initiation system (21), located inside the ECU (5).
[0063] The firing module (4) initiates the firing of a specified cartridge (25) from a magazine (24, 27) located inside the ECM (5) via the firing initiation system (21).
[0064] Two rotating cameras are mounted outside the supporting body (7), enabling the implementation of a binocular vision system. A version with a single rotating or static camera is possible. A light indicator is located on the top of the body (7). The rear of the body (7) houses the beam locks (14), stoppers (15), and the radio module antenna. The radio module can be used for manual control of the UAV-interceptor, for transmitting a video stream or exchanging messages between several UAV-interceptors for interaction within a swarm, and for passive scanning of the radio airwaves in order to detect the transmitters of enemy UAVs. The beams (11) contain engines (17) with rotors (19) with folding blades (18).
[0065] To fire, it is necessary to connect the external negative contacts ("ground") (26) in the firing module (4) with the negative contacts ("ground") (31) of the KEB (5) of the shot initiation system (21) of the body (22) of the KEB (5) using a cable (32) and apply current to the corresponding positive contact to initiate the cartridge (30). The current applied to the external contact of the shot initiation system (21) passes through the cable (33) to the spring-loaded contact (23) of the corresponding cartridge (25), passes through it, initiating the shot through the conductive clip (24), then to the spring-loaded negative contact ("ground") (31) and through the cable (32) comes to the external negative contact ("ground") (26). (See Fig. 14) A circuit with no external negative contact ("ground") (26) is possible. In this case, the spring-loaded negative contact ("ground") (31) is directly connected to the negative terminal of the battery (20). (See Fig. 13)
[0066] To load the KEB (5) with ammunition, it is necessary to press the housing lock (22) of the clip (27), turn it around the hinge (see Fig. 15), remove the used ammunition, if any, from its grooves, insert new cartridges into the grooves and turn the clip (27) back until the latch clicks (see Fig. 15).
[0067] The operator charges the UAV's battery using the charger, loads it with electrically initiated tubeless ammunition, inserts the UAV into the housing (7), and stores the UAV-interceptor in its holster. If necessary, the operator removes the UAV-interceptor from the holster, positions it horizontally at arm's length, and presses the start / stop button (16), which initiates the launch preparation system (2). The latches (14) and stoppers (15) release the beams (11), which, under the action of spring hinges (10), come to the flight position. The control unit (3) is activated, which turns on the flight preparation light, signaling the operator of the start of preflight preparation, and starts the engines (17). Under the action of centrifugal force, the blades unfold. Once the control unit has completed its pre-flight preparation and the thrust level required to enable flight has been reached, the indicator light goes out, signaling to the operator that flight is possible.The operator releases the handle, and the interceptor UAV hovers in the air. Control of the interceptor UAV can be fully automated, manual, remote-controlled, or a combination of both.
[0068] The operator or program, based on analysis of the camera feed, detects an enemy UAV, directs the interceptor toward it so that it is positioned above it, within firing range of the munition, takes aim, and fires one or more shots, achieving target destruction. After expending the ammunition or battery power, the operator or program returns the interceptor to the operator. The operator grasps the hovering interceptor UAV by the handle and presses the start / stop button. The control unit stops the engines and shuts down. The operator presses the ECM reset button, removes the spent ECM from the silo, replaces it with a new one, folds the motor blades, folds the arms, and stores the interceptor UAV in a holster. The spent ECM can be recharged if necessary.
[0069] This ensures ease of use, portability, and safety of the interceptor UAV, while minimizing its weight and dimensions. It also enables rapid maneuver preparation, launch, and flight. It also enables the acquisition of enemy UAVs, targeting them, and increasing the likelihood of disrupting their mission.
Claims
FORMALS of invention Unmanned aerial vehicle (UAV) - interceptor with ammunition for individual use 1. An unmanned aerial vehicle (UAV) - an interceptor with ammunition for individual use with anti-drone means containing at least a kinetic weapon, wherein the kinetic weapon is made with underbarrel devices for shots, equipped in controlled rotating containers for ammunition, located in different internal compartments of the UAV, a software and hardware complex with a processor, an on-board video monitoring system, a radio module and a battery pack, characterized in that the UAV is equipped with a frame, a launch preparation system, a control unit, a firing module and a power supply and ammunition complex (PSAC); wherein the frame is made with detachable or non-detachable connections with a handle fixed to it, forming a single load-bearing body with the handle, in which internal compartments for the PAC are located with seats provided with PAC body locks with a PAC reset button and connected by rotary hinges to the beams,made with the possibility of folding, at least one static or rotating camera is placed on the supporting body of the frame, the rear and front rotary hinges are fixed by means of a launch preparation system, including levers, beam locks, stoppers and an electromechanical trigger button, placed in the supporting body, the front and rear beams are connected to the supporting body by means of front and rear rotary hinges, made symmetrically and / or asymmetrically relative to the longitudinal axis of the supporting body, and the levers and beam locks of the launch preparation system are made with the possibility of retracting / unlocking after pressing the trigger button, on each beam there is an engine connected to the corresponding beam, which is equipped with folding rotor blades, and each engine is connected to a control unit; a power supply and ammunition complex (PSAC), which is equipped with a battery and a shot initiation system,located inside the body of the ECB, and the ECB firing initiation system is electrically connected to the control unit via a firing module, wherein the firing module is connected via spring contacts in a parallel circuit of electrical pairs by a conductive clip with each ammunition, the ECB is equipped with barrel-less ammunition with electrical firing initiation and contains a body, in the rear part of which a groove is located for placing the ECB body lock in the mounting locations of the supporting body.
2. An interceptor UAV according to item 1, characterized in that the control unit is electrically connected to the battery, the firing module, and the launch preparation system and is equipped with sensors, indicators, and a radio module.
3. An interceptor UAV according to item 1, characterized in that the control unit is equipped with at least two rotating cameras implementing a binocular vision system.
4. An interceptor UAV according to item 1, characterized in that the firing module is additionally equipped with an external negative contact.
5. An interceptor UAV according to item 1, characterized in that the launch preparation system is designed with the ability to turn on power from the battery to the control unit and the ability to move the stoppers away from the levers and beam locks to open the beams with blades.
6. An interceptor UAV according to item 1, characterized in that the electronic control unit (ECU) is equipped with a group of positive and negative contacts for connection to a storage battery, which are brought out of the ECU housing.
7. The UAV - interceptor according to item 1, characterized in that the ECU is equipped with positive and negative contacts of the shot initiation system brought out to the outside of the ECU body for connection with the external contacts of the firing module.
8. An interceptor UAV according to item 1, characterized in that a conductive clip for ammunition is secured to the lower part of the KEB body, which contacts the lower spring contacts of the KEB, and at least two cartridges.
9. An interceptor UAV according to item 1, characterized in that the CEB is equipped with cartridges equipped with a kinetic or incendiary or high-explosive or high-explosive fragmentation warhead.
10. An interceptor UAV according to item 1, characterized in that the cartridge of the ammunition clip contains an electric igniter, gunpowder and a bullet; 11. The UAV - interceptor according to item 1, characterized in that the beam hinges are made in the form of spring hinges; 12. The UAV - interceptor according to I. 1, characterized in that the launch preparation system is made in the form of an electromechanical start / stop button connected to hinges and to a battery and / or a control unit.
13. The UAV - interceptor according to I. 1, characterized in that a battery and contacts made spring-loaded are located inside the body of the control unit.
14. The UAV-interceptor according to paragraph 1, characterized in that the UAV A is additionally equipped with a system for fixing to the UAV-base, equipped with a system for releasing small UAVs for their use in a swarm.
15. The UAV - interceptor according to paragraph 1, characterized in that the firing module is automatically connected to the firing initiation system by connecting the external negative contact with the negative contact of the KEB and the cable with the spring-loaded contact of the firing initiation system of the corresponding KEB ammunition.
16. An interceptor UAV according to item 1, characterized in that the firing module is automatically linked to the firing initiation system when the spring-loaded negative contact of the ECU is connected to the negative terminal of the ECU battery.
17. An interceptor UAV according to items 15 and 16, characterized in that the firing module is automatically linked to the shot initiation system based on the control system software based on the results of the analysis of the video stream from the UAV cameras and / or from the operator's console.