Unmanned aerial vehicle interceptor

Abstract

The invention provides an efficient and safe unmanned aerial vehicle interceptor which comprises a launching gun, a gas supercharger and a modular launching appliance, the gas supercharger presses air into a pressure cavity through a pump machine, and after a trigger is pulled, high-pressure gas is sprayed out from a side air outlet to push an intercepting net to be launched; the interception net mode drives an interception net to wind the unmanned aerial vehicle through a gas bomb to realize physical capture and force the unmanned aerial vehicle to land; the interceptor is provided with a control system; the device is reasonable in design structure, easy and convenient to operate, free of gunpowder or explosives, safe, reliable, suitable for the fields of military, security, important facility protection and the like, and capable of effectively coping with diversified unmanned aerial vehicle threats.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicle (UAV) capture, and particularly to a UAV interceptor. Background Art

[0002] With the rapid development of UAV technology, the application scope of UAVs has become increasingly extensive, but it has also brought potential safety hazards. For example, UAVs may be used for illegal surveillance, smuggling, or even terrorist activities. Therefore, there is an urgent need to develop an efficient, accurate, and safe UAV interceptor. Summary of the Invention

[0003] The present invention aims to solve at least one of the technical problems existing in the prior art, and provides a UAV interceptor.

[0004] A UAV interceptor includes a launching gun, a launching device, and a gas booster.

[0005] The launching gun includes a gun body, on which there is an air flow channel, and at the front end of the air flow channel, there are four side air outlets.

[0006] The gas booster includes a pressure chamber, which is arranged at the tail end of the air flow channel. Between the air flow channel and the pressure chamber, there is a trigger mechanism for releasing the gas in the pressure chamber.

[0007] The inlet of the pressure chamber is connected to a pump through a pipeline, and between the pressure chamber and the pump, there is a one-way valve, which allows the gas to flow only from the pump to the pressure chamber.

[0008] The launching device includes a docking body. On one side of the docking body, there is a conical air pipe that cooperates with the side air outlets. On the other side of the docking body, there is an interception net placement cylinder. Inside the interception net placement cylinder, there is a launching tube that cooperates with the conical air pipe. Inside the interception net placement cylinder, there is an interception net. The interception net is connected by a rope to an air bullet corresponding to the launching tube, and the air bullet can be placed inside the launching tube.

[0009] Furthermore, the launching device further includes an interception net. Around the center of the docking body, there are side launching tubes that are docked with several side air outlets. At the end of the side launching tube close to the side air outlet, there is a conical air pipe, and the outer surface of the conical air pipe can be hermetically docked with the inner surface of the side air outlet.

[0010] Near the center air outlet side of the center of the docking body, there is a conical plug that is docked with the center air outlet.

[0011] The interception net is provided with several air bullets, and the air bullets can be inserted into the side launching tubes from the end of the side launching tubes far from the side air outlets.

[0012] Further, a turntable for placing hollow projectiles is provided between the launch tube and the conical air tube inside the docking body.

[0013] Further, an interception net placement cavity is provided inside the interception net placement cylinder. A projectile temporary storage cavity is provided around the interception net placement cavity. A spring is provided at one end of the projectile temporary storage cavity close to the docking body. The end of the projectile temporary storage cavity far from the docking body is communicated with the launch tube, and a limiting elastic sheet is provided between the projectile temporary storage cavity and the launch tube.

[0014] Further, a lock is provided at the front end of the gun body of the launch gun and the docking body. The lock includes a lock groove and a lock hole provided at the front end of the gun body. A spring plate capable of extending into the lock groove is provided on one side of the docking body close to the gun body. A lock block cooperating with the lock hole is provided at one end of the spring plate far from the docking body.

[0015] Further, an auxiliary support plate for supporting the docking body is provided on the lower side of the front end of the gun body.

[0016] Further, a pressure gauge is provided on the pressure chamber.

[0017] Further, a pressure sensor is provided on the pressure chamber. The pressure sensor is used to control the working state of the pump.

[0018] Further, a battery and a controller are provided on the gun body. The controller is electrically connected to the battery, the pressure sensor, and the pump.

[0019] The beneficial effects of the present invention compared with the prior art: The structure of the present invention is reasonable. The drone interceptor of the present solution realizes efficient, precise, fast and safe interception effects through an innovative gas boosting system, modular design and intelligent control. Its multi-mode interception ability, environmental adaptability and cost-effectiveness make it have a wide application prospect in the field of drone defense, and can effectively cope with diverse drone threats, while taking into account safety and compliance;

[0020] Interception net: Launched through the side launch tube, the air projectile connected to the interception net is pushed by gas and the hollow projectile, and after unfolding, it wraps around the drone to capture the drone. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is the first three-dimensional schematic diagram of a drone interceptor of the present invention;

[0022] Figure 2 is the second three-dimensional schematic diagram of a drone interceptor of the present invention;

[0023] Figure 3 is the internal structure schematic diagram of a drone interceptor of the present invention;

[0024] Figure 4It is a schematic diagram of a launching device of an unmanned aerial vehicle interceptor according to the present invention;

[0025] Figure 5 It is another schematic diagram of a launching device of an unmanned aerial vehicle interceptor according to the present invention;

[0026] Figure 6 It is a block diagram of a pressure control method for a pressure chamber of an unmanned aerial vehicle interceptor according to the present invention.

[0027] As shown in the figure: 1. Gun body; 2. Air flow channel; 3. Gas supercharger; 4. Side air outlet; 5. Pressure chamber; 6. Trigger mechanism; 7. Pipe; 8. Pump; 9. Check valve; 10. Docking body; 11. Launching tube; 12. Conical air pipe; 13. Interception net placement cylinder; 14. Interception net; 15. Air bomb; 16. Turntable; 17. Lock track; 18. Lock hole; 19. Spring plate; 20. Lock block; 21. Auxiliary support plate; 22. Pressure gauge; 23. Hollow bullet; 24. Bullet body temporary storage chamber; 25. Bullet body temporary storage chamber; 26. Spring; 27. Limit elastic sheet; 601. Solenoid valve; 602. Control switch. Specific implementation manner

[0028] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0029] In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, "a plurality" means two or more unless otherwise specifically defined.

[0030] In the description of the embodiments of the present invention, if a certain feature is referred to as "set", "fixed", "connected", "installed" on another feature, it can be directly set, fixed, connected, installed on another feature, or indirectly set, fixed, connected, installed on another feature.

[0031] In the description of the embodiments of the present invention, if "several" is involved, it means more than one; if "multiple" is involved, it means more than two; if "greater than", "less than", or "exceeding" is involved, it should be understood as not including the base number; if "above", "below", or "within" is involved, it should be understood as including the base number. If "first" or "second" is involved, it should be understood as used to distinguish technical features, and cannot be understood as indicating or implying relative importance or implicitly indicating the quantity of the indicated technical features or the sequence relationship of the indicated technical features.

[0032] The following takes a drone interceptor according to an embodiment of the present invention as an example and describes it with reference to the accompanying drawings.

[0033] A drone interceptor includes a launch gun, a launching device, and a gas supercharger 3;

[0034] The launch gun includes a gun body 1, an air flow channel 2 is provided on the gun body 1, and four side air outlets 4 are provided at the front end of the air flow channel 2;

[0035] The gas supercharger 3 includes a pressure chamber 5, the pressure chamber 5 is provided at the tail end of the air flow channel 2, and a trigger mechanism 6 for releasing the gas in the pressure chamber 5 is provided between the air flow channel 2 and the pressure chamber 5;

[0036] The inlet of the pressure chamber 5 is connected to a pump 8 through a pipeline 7, and a one-way valve 9 is provided between the pressure chamber 5 and the pump 8, and the one-way valve 9 allows the gas to flow only from the pump 8 to the pressure chamber 5;

[0037] The launching device includes a docking body 10, a conical air pipe 12 matching with the side air outlets is provided on one side of the docking body 10, an interception net placement cylinder 13 is provided on the other side of the docking body, a launch tube 11 matching with the conical air pipe 12 is provided in the interception net placement cylinder 13, an interception net 14 is placed in the interception net placement cylinder 13, the interception net 14 is connected by a rope to an air bullet 15 corresponding to the launch tube 11, and the air bullet 15 can be placed in the launch tube 11. As Figure 4 shown, it shows a schematic diagram of the launching device of a single interception net 14.

[0038] A turntable 16 for placing a hollow bullet 23 is provided in the docking body 10 between the launch tube 11 and the conical air pipe 12, providing a method of using pneumatic force to fire the air bullet 15 of the interception net 14 through the hollow bullet 23. As Figure 5 shown.

[0039] The inside of the interception net placement cylinder 13 is provided with an interception net placement cavity 24. Around the interception net placement cavity 24, there is a projectile temporary storage cavity 25. One end of the projectile temporary storage cavity 25 close to the docking body 10 is provided with a spring 26. One end of the projectile temporary storage cavity 24 far from the docking body 10 is communicated with the launch tube 11, and a limiting elastic sheet 27 is arranged between the projectile temporary storage cavity 24 and the launch tube 11, as Figure 4 shown, which shows a schematic diagram of the launcher for multiple interception nets 14..

[0040] As a preferred implementation of this embodiment, as Figure 1 、 2 and Figure 3 show, a lock is provided at the front end of the docking body 10 and the gun body 1 of the launch gun. The lock includes a lock groove 17 and a lock hole 18 provided at the front end of the gun body 1. One side of the docking body 10 close to the gun body 1 is provided with a spring plate 19 that can extend into the lock groove 17. One end of the spring plate 19 far from the docking body 10 is provided with a lock block 20 that cooperates with the lock hole 18.

[0041] As a preferred implementation of this embodiment, an auxiliary support plate 21 for supporting the docking body 10 is provided at the lower side of the front end of the gun body 1.

[0042] As a preferred implementation of this embodiment, a pressure gauge 22 is provided on the pressure chamber 5, which is convenient for the operator to directly observe the pressure condition of the pressure chamber 5.

[0043] As a preferred implementation of this embodiment, a pressure sensor is provided on the pressure chamber 5, and the pressure sensor is used to control the working state of the pump 8.

[0044] As a preferred implementation of this embodiment, a battery and a controller are provided on the gun body 1. The controller is electrically connected to the battery, the pressure sensor, and the pump 8, and its control is as Figure 6 shown. The pump 8 is equipped with a switch. First, operate the switch to start the pump 8 to supply gas to the pressure chamber 5. After reaching the set pressure threshold, the pressure sensor senses and transmits the data to the controller. The controller processes and sends a closing signal to the switch of the pump 8, and the switch of the pump 8 closes, and the pump stops working.

[0045] As a preferred implementation of this embodiment, as Figure 3 shown, the trigger mechanism 6 includes an electromagnetic valve 601 provided at the connection between the air flow channel 2 and the pressure chamber 5. A control switch 602 for controlling the on / off of the electromagnetic valve 601 is provided on one side of the trigger. When the finger presses the trigger, the trigger triggers the control switch 602, and the electromagnetic valve 601 is turned on. When the finger is released, the trigger disengages from the electromagnetic valve 601 and closes.

[0046] The drone interceptor described in the present invention realizes the precise interception of drones through a gas pressurization system, a modular launcher, and intelligent control. The following is its specific working process:

[0047] S1. Preparation

[0048] Inflation and pressurization: Turn on the pump 8, pump air into the pressure chamber 5 through the one-way valve 9, the air pressure in the pressure chamber 5 gradually increases, and the pressure sensor monitors the air pressure in the pressure chamber in real time. When the air pressure reaches the preset value, the pump 8 automatically stops working;

[0049] Install the launching device: Select a suitable launching device according to the interception target: a single interception net or multiple interception nets;

[0050] Dock the docking body 10 of the launching device with the buckle at the front end of the launching gun to ensure that the conical air pipe 12 is hermetically connected to the corresponding side air outlet 4.

[0051] S2. The operator locks the target UAV through the sight.

[0052] S3. Launch and intercept

[0053] The operator pulls the trigger, the trigger mechanism 6 opens, and the high-pressure gas in the pressure chamber 5 is quickly released into the air flow channel 2 and sprayed towards the side air outlet 4 through the air flow channel 2;

[0054] Single interception net mode: The high-pressure gas pushes the gas bullet 15 in the launch tube 11, the gas bullet 15 drives the interception net 14 to fly out quickly, the interception net 14 unfolds in the air, covers the target UAV, and captures it by winding or wrapping;

[0055] Multiple interception net mode: The high-pressure gas pushes the hollow bullet 23 in the turntable 16, the hollow bullet 23 pushes the gas bullet 15 in the launch tube 11, the gas bullet 15 drives the interception net 14 to fly out quickly, the interception net 14 unfolds in the air, covers the target UAV, and captures it by winding or wrapping. After the previous interception net is launched, the spring 26 pushes the next gas bullet 15 into the launch tube 11 with the assistance of the limit elastic piece 27 to prepare for the next firing.

[0056] The UAV interceptor of the present invention is applicable to fields such as military, security, and protection of important facilities, and can effectively respond to the diverse threats of UAVs.

[0057] The content not described in detail in this specification belongs to the prior art well-known to those skilled in the art. For example, the pump, pressure sensor, one-way valve, etc. in this case are all prior art.

[0058] Through those skilled in the art, all the electrical components in this case are connected to their adapted power supplies through wires, and a suitable controller should be selected according to the actual situation to meet the control requirements. For the specific connection and control sequence, the electrical connection should be completed with reference to the sequential working order between the electrical components. The detailed connection means are well-known techniques in this field, and no further description of the electrical control will be given.

[0059] The above describes the present invention and its implementation manners. Such description is not restrictive. What is shown in the drawings is only one of the implementation manners of the present invention, and the actual structure is not limited thereto. Generally speaking, if those of ordinary skill in the art are inspired by it and, without departing from the gist of the present invention, creatively design structural manners and embodiments similar to the technical solution, they shall fall within the protection scope of the present invention.

Claims

1. A drone interceptor, characterized in that: Including firing guns, firing devices and gas boosters; The firing gun comprises a gun body, an air flow channel is provided on the gun body, and four side air outlets are provided at the front end of the air flow channel; The gas booster comprises a pressure chamber, the pressure chamber is arranged at the rear end of the air flow channel, and a trigger mechanism for releasing the gas in the pressure chamber is arranged between the air flow channel and the pressure chamber; The inlet of the pressure chamber is connected to a pump through a pipeline, and a one-way valve is provided between the pressure chamber and the pump, and the one-way valve allows gas to flow only from the pump to the pressure chamber; The launching device comprises a docking body, one side of which is provided with a conical air pipe cooperating with a side air outlet, the other side of which is provided with an interception net placement tube, the interception net placement tube is provided with a launching tube cooperating with the conical air pipe, the interception net is placed in the interception net placement tube, the interception net is connected to a gas bomb corresponding to the launching tube via a rope, and the gas bomb can be placed in the launching tube.

2. A drone interceptor according to claim 1, characterized in that: A turntable for placing hollow bullets is arranged in the docking body between the launching tube and the conical air tube.

3. The drone interceptor according to claim 1, characterized in that: An interception net placement cavity is provided in the interception net placement tube, and a projectile temporary storage cavity is provided around the interception net placement cavity. A spring is provided at one end of the projectile temporary storage cavity close to the docking body. The end of the projectile temporary storage cavity away from the docking body is connected to the launch tube, and a limiting spring piece is provided between the projectile temporary storage cavity and the launch tube.

4. A drone interceptor according to claim 1, 2 or 3, characterized in that: The docking body and the front end of the gun body of the launch gun are provided with a lock buckle, and the lock buckle includes a lock track and a lock hole arranged at the front end of the gun body. The docking body is provided with a spring plate that can extend into the lock track on the side close to the gun body, and the spring plate is provided with a lock block that cooperates with the lock hole on the end away from the docking body.

5. The drone interceptor according to claim 4, characterized in that: An auxiliary support plate for supporting the docking body is arranged at the lower side of the front end of the gun body.

6. The drone interceptor according to claim 1, characterized in that: The pressure chamber is provided with a pressure gauge.

7. The drone interceptor according to claim 2, characterized in that: The pressure pump is provided with a pressure sensor, and the pressure sensor is used to control the working state of the pump.

8. The drone interceptor according to claim 7, characterized in that: The gun body is provided with a battery and a controller, and the controller is electrically connected with the battery, the pressure sensor and the pump.

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