Portable unmanned aerial vehicle countering system based on unmanned aerial vehicle

Abstract

The technical problem to be solved by the invention is to provide the portable unmanned aerial vehicle countering system based on the unmanned aerial vehicle, the system effectively improves the recognition and locking precision of the target unmanned aerial vehicle, the capture success rate is less influenced by environment and control experience, and safe disposal and traceable management of illegal unmanned aerial vehicles are realized. The system comprises an unmanned aerial vehicle, a handheld emitter and a flight control terminal, wherein the unmanned aerial vehicle is arranged on the handheld emitter through a sliding structure; a control panel, an energy storage capacitor and a netting launcher track bin structure are arranged in the unmanned aerial vehicle, a seeker and a catching net are arranged at the front end of the unmanned aerial vehicle, a traction rope is arranged between the catching net and the seeker, the target unmanned aerial vehicle is aimed at through a handheld launcher, then the unmanned aerial vehicle is launched out, and the unmanned aerial vehicle is controlled to be close to the target unmanned aerial vehicle through a flight control terminal. The distance and the angle are controlled through the camera device arranged in the seeker, and then the catching net is launched through the arranged net catching launcher track bin structure to catch the target unmanned aerial vehicle and take the target unmanned aerial vehicle back together with the catching net.

Description

Technical Field

[0001] This invention relates to the field of counter-drone technology, and more specifically to a portable drone counter-drone system based on drones. Background Technology

[0002] In recent years, drone technology has developed rapidly. With its advantages of high mobility, low cost, and flexible deployment, it has been widely used in aerial surveying, logistics, emergency rescue, and law enforcement. However, with the surge in the number of drones, the phenomenon of unauthorized or unregulated "black flights" has become increasingly prominent, frequently occurring in airport airspace, major event sites, critical infrastructure, and densely populated areas, posing a serious threat to public safety, airspace order, and social stability.

[0003] To address the issue of unauthorized drone flights, existing drone flight management and countermeasures mainly include technologies such as radio detection, radio jamming, and GPS spoofing / deception. While these methods can detect or drive away illegal drones to some extent, they still have significant limitations. For example, radio jamming often suppresses drone communication links or navigation signals through high-power electromagnetic radiation. This not only makes it difficult to precisely control the effective range and easily causes collateral interference to nearby legitimate communication equipment, police drones, and civilian navigation systems, but it is also easily countered or rendered ineffective in the complex electromagnetic environment of cities. Furthermore, some drones possess anti-jamming, return-to-home, or autonomous flight capabilities, making countermeasures relying solely on radio jamming unstable and posing significant safety risks.

[0004] Furthermore, in law enforcement and critical area protection scenarios, countering drones requires not only "forcing them to become ineffective," but also emphasizing the controllable disposal and evidence preservation of illegal drones. Most existing countermeasures are insufficient to completely capture target drones; once a drone crashes, it may cause secondary damage and hinder subsequent tracing, evidence collection, and case investigation.

[0005] With the development of police drone technology, using police drones for aerial interception and physical capture of illegal drones is gradually becoming a safer, more controllable, and legally compliant countermeasure strategy. Among these, the "net-based capture" method, which launches a net structure at the target drone to disable its rotors and allow it to be encased or towed back, can effectively control "black-flying" drones without generating widespread electromagnetic interference. However, existing net-based capture systems still have many shortcomings in practical applications, such as insufficient target identification and locking accuracy, weak coordination between flight management and countermeasure systems, a high success rate heavily influenced by environment and operator experience, and a lack of unified management and scheduling mechanisms for multi-target or complex airspace environments. Summary of the Invention

[0006] The technical problem to be solved by the present invention is to provide a portable drone countermeasure system based on drones. The system effectively improves the accuracy of identification and locking of target drones, and the capture success rate is less affected by the environment and operating experience, so as to realize the safe disposal and traceable management of illegal drones.

[0007] The technical solution adopted by the present invention to solve its technical problem is as follows: a portable drone countermeasure system based on drones, including a drone, a handheld transmitter for launching the drone and a flight control terminal, wherein the drone is mounted above the front end of the handheld transmitter via a sliding structure;

[0008] The drone includes a main fuselage, four arms, and four tail fins;

[0009] The main fuselage is provided with a front fuselage section and a rear fuselage section. The flight control system and power system are housed inside the rear fuselage section. The flight control system is wirelessly connected to the flight control terminal.

[0010] The four arms are located at the front end of the rear section of the fuselage and are evenly distributed along its circumferential direction, and each of the four arms is equipped with a propeller.

[0011] The rear section of the fuselage is equipped with four tail fins, which correspond to the front and rear of the four arms respectively.

[0012] The rear end of the front section of the fuselage is equipped with a control board and an energy storage capacitor. The control board is connected to the flight control system.

[0013] The front end of the fuselage is equipped with a net-catching launcher track compartment structure and is connected to the control board via signal.

[0014] The front end of the fuselage section is provided with a seeker head, and the seeker head is provided with a camera device and a navigation computer. The camera device is connected to the navigation computer by signal, and the navigation computer is connected to the flight control system by signal.

[0015] The seeker head is provided with a capture net on its outside. Multiple fixed points on the edge of the capture net are connected to the track chamber structure of the net capture launcher. The track chamber structure of the net capture launcher is used to launch the capture net.

[0016] A traction rope is provided between the capture net and the outer wall of the guide head.

[0017] Furthermore, the track compartment structure of the net-catching launcher includes a mounting base;

[0018] The mounting base is provided with multiple launch tubes and they are evenly distributed along its circumferential direction. The front end of each launch tube extends obliquely forward and outward and completely penetrates the side wall of the front section of the fuselage. The multiple launch tubes are arranged radially.

[0019] Each launching tube is equipped with a launching weight, and multiple launching weights are fixedly connected to multiple fixed points on the edge of the capture net.

[0020] Each launch tube is equipped with a launcher for firing the launch hammer, and the launcher is connected to the control board via signal.

[0021] Furthermore, the transmitting device employs an electromagnetic coil, which is electrically connected to the energy storage capacitor and signal-connected to the energy storage capacitor control board.

[0022] Furthermore, the sliding structure includes a slide rail disposed below the main body;

[0023] The handheld transmitter has a slide rail adapted to the slide rail at the front end, and the slide rail is located in the slide rail and can slide freely along its length.

[0024] The front end of the handheld transmitter is also provided with a locking structure to limit the relative sliding of the slide rail and the slide path.

[0025] Furthermore, the locking structure includes an irregularly shaped locking housing disposed inside the front end of the handheld transmitter;

[0026] A sliding groove is provided on the rear side of the irregularly shaped locking housing, a sliding post is provided in the sliding groove, and a compression spring is provided between the lower end of the sliding post and the bottom of the irregularly shaped locking housing.

[0027] The upper end of the sliding column is provided with a locking rod, and the upper end of the locking rod extends through the upper side wall of the irregular locking housing and the upper side wall of the handheld transmitter to the outside.

[0028] The lower side wall of the slide rail is provided with a locking hole at the rear end. In the initial state, the upper end of the locking rod is located in the locking hole.

[0029] A servo motor is provided on the left side of the irregular locking housing. A connecting block is provided on the drive arm of the servo motor. The connecting block is connected to the side wall of the sliding column and is located in the lower middle part of the sliding column.

[0030] The handheld transmitter is equipped with an unlock control button, and the servo motor is signal-connected to the unlock control button.

[0031] Furthermore, a parachute compartment is provided above the rear end of the outer side wall of the rear section of the fuselage;

[0032] The parachute compartment is equipped with a parachute.

[0033] Furthermore, a radar is installed on the upper part of the outer side wall of the front section of the fuselage.

[0034] Furthermore, the capture net is rectangular in shape.

[0035] Furthermore, the number of the multiple launching tubes and multiple launching hammers is four, and the four launching hammers are respectively connected to the four corners of the capture net.

[0036] Furthermore, each launching hammer includes a cylindrical body with a streamlined pointed tip at the front end and a connecting hole at the rear end.

[0037] The beneficial effects of this invention are as follows:

[0038] 1. Aim at the target drone with a handheld transmitter, then launch the drone. Control the drone to approach the target drone via the flight control terminal. Control the distance and angle using the camera device inside the seeker head. Then, launch the capture net through the set net-capture launcher track chamber structure to capture the target drone. This effectively improves the accuracy of target drone identification and locking. Compared with existing wireless jamming countermeasures, the capture success rate is less affected by the environment and operating experience through the cooperation of the flight management system and the countermeasure system.

[0039] 2. By using the set tow rope, the drone can safely land the target drone after capturing it, avoiding the random fall of the target drone after being countered, and also avoiding the risk of injuring people. This ensures the integrity of the target drone as much as possible, and enables safe disposal and traceable management of the target drone. Attached Figure Description

[0040] Figure 1 This is a schematic diagram of the structure of a portable drone countermeasure system based on a drone as described in this invention;

[0041] Figure 2 This is a schematic diagram of the structure of the UAV described in this invention;

[0042] Figure 3 This is a side view of the drone described in this invention;

[0043] Figure 4 This is a schematic diagram of the guide head and its internal structure as described in this invention;

[0044] Figure 5 This is a side view of the internal structure of the front section of the fuselage described in this invention;

[0045] Figure 6 This is the track chamber structure of the net-catching launcher described in this invention;

[0046] Figure 7 This is a schematic diagram of the combined structure of the sliding structure and the handheld transmitter described in this invention;

[0047] Figure 8This is a schematic diagram of the combined sliding structure and locking structure described in this invention;

[0048] Figure 9 This is a side view of the combined sliding structure and locking structure described in this invention;

[0049] Figure 10 This is an exploded view of the sliding structure and locking structure described in this invention;

[0050] Figure 11 This is a schematic diagram of the launching hammer structure described in this invention;

[0051] Figure 12 This is a schematic diagram showing the state of the capture net being launched according to the present invention;

[0052] Explanation of markings in the diagram: 1. Handheld launcher; 2. UAV; 201. Main body; 201. Front section of fuselage; 2011. Rear section of fuselage; 2012. Arm; 202. Propeller; 203. Tail fin; 204. Control board; 3. Energy storage capacitor; 4. Net launcher track compartment structure; 5. Seeker head; 6. Camera device; 7. Navigation computer; 8. Sliding structure; 9. Slide rail; 901. Slide track; 902. Locking structure; 10. Parachute compartment; 11. Radar; 12. Capture net; 13. Towing rope; 14.

[0053] The track compartment structure 5 of the net capture launcher includes: mounting base 501, launch tube 502, launch counterweight 503, and launch component 504;

[0054] Locking structure 10: irregularly shaped locking housing 1001, sliding groove 1002, sliding column 1003, compression spring 1004, locking rod 1005, locking hole 1006, servo motor 1007, connecting block 1008;

[0055] Launching hammer 503: main body 5031, streamlined pointed top 5032, connecting hole 5033. Detailed Implementation

[0056] The specific embodiments of the present invention will be further described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0057] It should be noted that all directional indicator terms such as "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", and "outer" in the embodiments of this application indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the present invention. They are only used to explain the relative positional relationship and movement of the components in a specific posture. If the specific posture changes, the directional indication will also change accordingly.

[0058] In this application, unless otherwise expressly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0059] Furthermore, if the embodiments of this application involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions; for example, "A and / or B" includes solution A, solution B, or a solution where both A and B are satisfied simultaneously. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed in this application.

[0060] like Figure 1-12 As shown, this portable drone countermeasure system based on drones includes a drone 2, a handheld transmitter 1 for launching the drone 2, and a flight control terminal. The drone 2 is mounted above the front end of the handheld transmitter 1 via a sliding structure 9. The handheld transmitter 1 is existing technology and will not be described in detail here. The handheld transmitter 1 pushes out the sliding structure 9 of the drone 2, causing the drone 2 to fly quickly toward and approach the target drone.

[0061] The drone 2 includes a main body 201, four arms 202, and four tail fins 204;

[0062] The main fuselage 201 is provided with a front fuselage section 2011 and a rear fuselage section 2012. The rear fuselage section 2012 is equipped with a flight control system and a power system. The flight control system is wirelessly connected to the flight control terminal.

[0063] The four arms 202 are located at the front end of the rear section 2012 and are evenly distributed along its circumferential direction. Each of the four arms 202 is equipped with a propeller 203, which can be located on the front side or the rear side of the arm 202.

[0064] The rear end of the rear fuselage section 2012 is provided with four tail fins 204, which correspond to the front and rear of the four arms 202 respectively.

[0065] The rear end of the front section of the fuselage is equipped with a control board 3 and an energy storage capacitor 4. The control board 3 is connected to the flight control system.

[0066] The front end of the fuselage section 2011 is equipped with a net-catching launcher track compartment structure 5 and is signal-connected to the control board 3.

[0067] The front end of the fuselage section 2011 is provided with a seeker head 6. The seeker head 6 is equipped with a camera device 7 and a navigation computer 8. The camera device 7 is connected to the navigation computer 8. The camera device 7 is generally a high-definition camera that can identify and track target UAVs. The navigation computer 8 is connected to the flight control system. The flight management system and the countermeasure system cooperate through the flight control terminal, control board 3, and navigation computer 8.

[0068] The guide head 6 is equipped with a capture net 13. At this time, the capture net 13 is in a retracted state. Multiple fixed points on the edge of the capture net 13 are connected to the net capture launcher track chamber structure 5. The net capture launcher track chamber structure 5 is used to launch the capture net 13. When the UAV 2 approaches the target UAV at a suitable distance, the control board 3 controls the net capture launcher track chamber structure 5 to unfold the capture net 13, fly it toward the target UAV, and entangle it, causing it to lose its flight function.

[0069] A traction rope 14 is provided between the capture net 13 and the outer wall of the guide head 6. The traction rope 14 is used to constrain the target drone, which avoids the target drone falling randomly after being countered, and also avoids the risk of injuring people. The target drone is pulled to a stable landing at a designated location, ensuring the integrity of the target drone as much as possible.

[0070] like Figure 5 , Figure 6 , Figure 11As shown, in this embodiment, preferably, the net-catching launcher track compartment structure 5 includes a mounting base 501, which is disc-shaped and fixedly mounted on the inner side wall of the front section 2011 of the fuselage.

[0071] The mounting base 501 is provided with a plurality of transmitting tubes 502 and is evenly distributed along its circumferential direction. That is, the ends of the plurality of transmitting tubes 502 near the mounting base 501 are close to the center of the mounting base 501. The front end of each transmitting tube 502 extends obliquely forward and outward and completely penetrates the side wall of the front section 2011 of the fuselage. The plurality of transmitting tubes 502 are arranged radially.

[0072] Each launching tube 502 is equipped with a launching weight 503, and multiple launching weights 503 are fixedly connected to multiple fixed points on the edge of the capture net 13.

[0073] Each launch tube 502 is equipped with a launcher 504 for launching the launch hammer 503. The launcher 504 is connected to the control board 3. The control board 3 controls the launcher 504 to accelerate the launch hammer 503 so that it flies out along the launch tube 502. As the multiple launch hammers 503 fly, they gradually move away and disperse, so that the capture net 13 can be deployed.

[0074] In this embodiment, preferably, the launching element 504 is an electromagnetic coil. The electromagnetic coil is electrically connected to the energy storage capacitor 4 and signal-connected to the energy storage capacitor 4 control board 3. The electromagnetic coil accelerates the launching hammer 503, causing it to fly out of the corresponding launching tube 502, thereby driving the capture net 13 to unfold and fly with it. The launching hammer 703 is generally made of plastic or stainless steel.

[0075] like Figure 3 , Figure 7-10 As shown, in this embodiment, preferably, the sliding structure 9 includes a slide rail 901 disposed below the main body 201;

[0076] The handheld transmitter 1 has a slide rail 902 adapted to the slide rail 901 above its front end. The slide rail 901 is located in the slide rail 902 and can slide freely along its length. It should be noted that the slide rail 901 and the slide rail 902 cannot move relative to each other in the vertical direction.

[0077] The front end of the handheld transmitter 1 is also provided with a locking structure 10 for limiting the relative sliding of the slide rail 901 and the slide channel 902. By unlocking the locking structure 10, the handheld transmitter 1 can push the drone 2 and the slide rail 901 to slide out along the slide channel 902 until the slide rail 901 is completely separated from the slide channel 902 and then continue to fly.

[0078] like Figure 8-10As shown, in this embodiment, preferably, the locking structure 10 includes an irregularly shaped locking housing 1001 disposed inside the front end of the handheld transmitter 1. The irregularly shaped locking housing 1001 is detachably connected to the front end of the handheld transmitter 1 by means of screws or the like.

[0079] A sliding groove 1002 is provided on the rear side of the irregularly shaped locking housing 1001. A sliding post 1003 is provided in the sliding groove 1002. It should be noted that the sliding groove 1002 is provided with a bent edge to ensure that the sliding post 1003 can only move in the vertical direction and will not disengage from the sliding groove 1002. A compression spring 1004 is provided between the lower end of the sliding post 1003 and the bottom of the irregularly shaped locking housing 1001. The upper end of the compression spring 1004 is fixedly connected to the lower end of the sliding post 1003, and the lower end of the compression spring 1004 is fixedly connected to the bottom of the irregularly shaped locking housing 1001.

[0080] The upper end of the sliding column 1003 is provided with a locking rod 1005, and the upper end of the locking rod 1005 extends to the outside through the upper side wall of the irregular locking housing 1001 and the upper side wall of the handheld transmitter 1.

[0081] The lower side wall of the slide rail 901 is provided with a locking hole 1006 at the rear end. In the initial state, the upper end of the locking rod 1005 is located in the locking hole 1006. At this time, the compression spring 1004 is in a compressed state, and the weight of the sliding column 1003 and the locking rod 1005 is applied to the compression spring 1004.

[0082] A servo motor 1007 is provided on the left side of the irregular locking housing 1001, and a connecting block 1008 is provided on the drive arm of the servo motor 1007. The connecting block 1008 is connected to the side wall of the sliding column 1003 and is located in the lower middle part of the sliding column 1003. The servo motor 1007 drives the drive arm to swing downward, which drives the connecting block 1008 to move downward, thereby driving the sliding column 1003 to move downward along the sliding groove 1002 to further compress the compression spring 1004, until the upper end of the locking rod 1005 is completely disengaged from the locking hole 1006 to achieve unlocking.

[0083] The handheld transmitter 1 is equipped with an unlock control button (not shown in the figure). The servo motor 1007 is connected to the unlock control button. Before launching the UAV 2, the servo motor 1007 is controlled by the unlock button to drive the arm to swing downward and unlock.

[0084] like Figure 2 , Figure 3 As shown, in this embodiment, in order to further ensure the safe landing and integrity of the UAV 2 and the target UAV, a parachute compartment 11 is provided above the rear end of the outer side wall of the rear fuselage section 2012;

[0085] The parachute compartment 11 is equipped with a parachute. During descent, opening the parachute compartment 11 triggers the parachute to open, ensuring the safe landing and integrity of both the drone 2 and the target drone.

[0086] like Figure 2 , Figure 3 As shown, in this embodiment, in order to further ensure the distance between the UAV 2 and the target UAV, a radar 12 is provided on the upper side wall of the front section 2011 of the fuselage and is connected to the control board 3 by signal. The radar 12 is used for distance measurement. After the preset distance is reached, the control board 3 automatically controls the trigger to launch the net.

[0087] In this embodiment, preferably, the capture net 13 is rectangular, as rectangular nets are optimal in terms of deployment stability, capture efficiency, storage adaptability, and production and maintenance.

[0088] In this embodiment, preferably, there are four launch tubes 502 and four launch hammers 503, and the four launch hammers 503 are respectively connected to the four corners of the capture net 13.

[0089] like Figure 11 As shown, in this embodiment, preferably, each launching hammer 503 includes a cylindrical body 5031. The front end of the body 5031 is provided with a streamlined pointed tip 5032, and the rear end of the body 5031 is provided with a connecting hole 5033. The streamlined pointed tip can reduce airflow disturbance, allowing the launching hammer 503 to maintain a more stable attitude during flight and reduce the impact of factors such as crosswinds. The connecting hole facilitates the connection of the four corners of the capturing net 13 to the launching hammer 503.

[0090] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A portable unmanned aerial vehicle (UAV) countermeasure system based on unmanned aerial vehicles (UAVs), characterized in that: Includes a drone (2), a handheld transmitter (1) for launching the drone (2) and a flight control terminal, wherein the drone (2) is mounted above the front end of the handheld transmitter (1) via a sliding structure (9); The drone (2) includes a main body (201), four arms (202) and four tail fins (204). The main fuselage (201) is provided with a front fuselage section (2011) and a rear fuselage section (2012). The rear fuselage section (2012) is equipped with a flight control system and an energy system. The flight control system is wirelessly connected to the flight control terminal. The four arms (202) are located at the front end of the rear section (2012) and are evenly distributed along its circumferential direction. Each of the four arms (202) is equipped with a propeller (203). The rear end of the rear section (2012) is provided with four tail fins (204) which correspond to the front and rear of the four arms (202) respectively; The rear end of the front section of the fuselage is equipped with a control board (3) and an energy storage capacitor (4), and the control board (3) is connected to the flight control system signal. The front end of the fuselage section (2011) is provided with a net-catching launcher track compartment structure (5) and is connected to the control board (3) via signal. The front end of the fuselage section (2011) is provided with a seeker head (6), and the seeker head (6) is provided with a camera device (7) and a navigation computer (8). The camera device (7) is connected to the navigation computer (8) by signal, and the navigation computer (8) is connected to the flight control system by signal. The guide head (6) is provided with a capture net (13) on its outside. Multiple fixed points on the edge of the capture net (13) are connected to the net capture launcher track chamber structure (5). The net capture launcher track chamber structure (5) is used to launch the capture net (13). A traction rope (14) is provided between the capture net (13) and the outer wall of the guide head (6).

2. The portable UAV countermeasure system based on UAVs according to claim 1, characterized in that: The track chamber structure (5) of the net-catching launcher includes a mounting base (501); The mounting base (501) is provided with multiple launch tubes (502) and they are evenly distributed along its circumferential direction. The front end of each launch tube (502) extends obliquely forward and outward and completely penetrates the side wall of the front section of the fuselage (2011). The multiple launch tubes (502) are arranged radially. Each launching tube (502) is equipped with a launching hammer (503), and multiple launching hammers (503) are fixedly connected to multiple fixed points on the edge of the capture net (13); Each launch tube (502) is provided with a launcher (504) for launching the launch hammer (503), and the launcher (504) is connected to the control board (3) via signal.

3. A portable UAV countermeasure system based on a UAV according to claim 2, characterized in that: The transmitter (504) uses an electromagnetic coil, which is electrically connected to the energy storage capacitor (4) and signal connected to the energy storage capacitor (4) control board (3).

4. A portable UAV countermeasure system based on a UAV according to claim 1, characterized in that: The sliding structure (9) includes a slide rail (901) disposed below the main body (201). The handheld transmitter (1) has a slide rail (902) above its front end that is adapted to the slide rail (901). The slide rail (901) is located in the slide rail (902) and can slide freely along its length. The front end of the handheld transmitter (1) is also provided with a locking structure (10) for limiting the relative sliding of the slide rail (901) and the slide channel (902).

5. A portable UAV countermeasure system based on a UAV according to claim 4, characterized in that: The locking structure (10) includes an irregularly shaped locking housing (1001) disposed inside the front end of the handheld transmitter (1). The rear side of the irregular locking housing (1001) is provided with a sliding groove (1002), and a sliding post (1003) is provided in the sliding groove (1002). A compression spring (1004) is provided between the lower end of the sliding post (1003) and the bottom of the irregular locking housing (1001). The upper end of the sliding column (1003) is provided with a locking rod (1005), and the upper end of the locking rod (1005) extends to the outside through the upper side wall of the irregular locking housing (1001) and the upper side wall of the handheld transmitter (1). The lower side wall of the slide rail (901) is provided with a locking hole (1006) at the rear end. In the initial state, the upper end of the locking rod (1005) is located in the locking hole (1006). A servo motor (1007) is provided on the left side of the irregular locking housing (1001). A connecting block (1008) is provided on the drive arm of the servo motor (1007). The connecting block (1008) is connected to the side wall of the sliding column (1003) and is located in the lower middle part of the sliding column (1003). The handheld transmitter (1) is equipped with an unlock control button, and the servo motor (1007) is signal-connected to the unlock control button.

6. A portable UAV countermeasure system based on any one of claims 1-5, characterized in that: A parachute compartment (11) is provided above the rear end of the outer side wall of the rear section (2012) of the fuselage. The parachute compartment (11) is equipped with a parachute.

7. A portable UAV countermeasure system based on a UAV according to claim 6, characterized in that: A radar (12) is installed on the upper side wall of the front section (2011) of the fuselage and is connected to the control board (3) via signal.

8. A portable UAV countermeasure system based on a UAV according to claim 7, characterized in that: The capture net (13) is rectangular.

9. A portable UAV countermeasure system based on a UAV according to claim 8, characterized in that: The number of the multiple launch tubes (502) and multiple launch hammers (503) is four, and the four launch hammers (503) are respectively connected to the four corners of the capture net (13).

10. A portable UAV countermeasure system based on a UAV according to claim 9, characterized in that: Each launching hammer (503) includes a cylindrical body (5031), the front end of which is provided with a streamlined tip (5032), and the rear end of which is provided with a connecting hole (5033).

Images