Extended-range unmanned aerial vehicle magnetic flexible capturing system and method

Abstract

The invention provides an extended-range unmanned aerial vehicle magnetic flexible capturing system and method. The method is applied to interception and capture of unmanned aerial vehicles. A ground launching system and a range extending power system carried by the capturer are provided to jointly provide range extending flight power for the capturing system, and the working radius of capturing and defending of the unmanned aerial vehicle is increased. The capturing net is unfolded through the net casting small rocket, and flexible capturing of the flying target is achieved. Meanwhile, strong magnetic field interference is carried out on the target unmanned aerial vehicle through a strong magnetic magnet, the unmanned aerial vehicle is forced to be attracted into the capturing net by utilizing a large magnetic attraction effect, and flexible capturing is carried out on the target unmanned aerial vehicle. The method is high in reaction speed, high in capture efficiency and relatively low in cost. A low-altitude defense measure is provided for public areas such as airports, large meeting places and sensitive zones, and the threats of low, slow and small flyers such as unmanned reconnaissance aircrafts are solved to a certain extent; the unmanned aerial vehicle is captured by adopting the measures of ground high-pressure gas ejection and high-altitude net throwing, and the unmanned aerial vehicle is clean, safe and free of pollution.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of unmanned aerial vehicle interception and capture, in particular to a range-extending unmanned aerial vehicle magnetic attraction flexible capture system and method. BACKGROUND

[0002] With the rapid development of modern electronic communication technology and aviation technology, various types of small unmanned aerial vehicles are developing very strongly, and are showing the characteristics of increasing types, continuously improving performance, continuously expanding use fields, increasingly lower use threshold and increasingly increasing available channels. In addition to being used for a large number of legitimate purposes such as surveying, photographing and line inspection, low-altitude small unmanned aerial vehicles are also used for a large number of illegal purposes. The threat of unmanned aerial vehicles to the low-altitude area near the airport has attracted the high attention of the government and the Civil Aviation Administration, and there is a lack of effective technical defense means to deal with it, so that only strict control measures can be taken, which leads to another extreme, limiting the development of unmanned aerial vehicles, and without the guarantee of technology, the role of unmanned aerial vehicles cannot be played.

[0003] Currently, there are two means of unmanned aerial vehicle control: one is to introduce relevant laws and regulations for control; the other is to strengthen the research and development of anti-unmanned aerial vehicle technology, mainly including soft defense and hard defense. Soft defense refers to the interference to unmanned aerial vehicles by radio, sound wave and signal interference, and hard defense refers to the capture of unmanned aerial vehicles by laser weapons, special bullets and capture nets. Domestic defense means for low, small and slow unmanned aerial vehicles are lacking, and the main representative is the "Sky Net" defense system of a group company, which uses pyrotechnics to launch and capture a distance of 100m, but the system is bulky, expensive, slow in response and poor in flexibility, and four sets of launch cannot achieve the demand of capturing targets at a long distance, and the use of pyrotechnic launch brings safety problems. Another anti-unmanned aerial vehicle system is the "God Gun" system produced by a company, which is simple to operate and fast in response; it blocks the downlink signal link of the unmanned aerial vehicle to prevent illegal shooting and transmission of video images, and has provided security services for the G20 summit, but the disadvantage is that its attack height is only 200-300 meters, which cannot capture the unmanned aerial vehicle, and once the unmanned aerial vehicle has anti-interference capability, the system cannot function.

[0004] The current unmanned aerial vehicle defense means has the following problems: For unmanned aerial vehicles with small flight targets, low flight height and speed, it is difficult for traditional radars to capture flight information, and an integrated air defense and anti-missile defense system can effectively attack larger unmanned aerial vehicles, but the cost is too high; Traditional hard defense technology has a contradiction between action distance, attack efficiency and cost, and the cost-effectiveness ratio of long-distance and accurate attack is high; Current soft defense technology cannot solve the contradiction between the power and the device volume and the action distance, and the soft defense technology is invalid after the aircraft has the anti-interference and confrontation function, and cannot deal with the flying objects such as kites, Kongming lanterns and flying birds; In the personnel-intensive area, the direct destruction type (including the explosive) hard defense technology is easy to cause misfire, misinjury and panic, and is not conducive to post-analysis. SUMMARY

[0005] In order to solve the above problems, the present application provides a ground cold air launching system and a range-extended power system carried by the catcher itself, which jointly provide range-extended flight power for the capture system, so as to solve the problems of low efficiency and high cost of the existing defense technology. The present application can greatly increase the capture flight radius of the unmanned aerial vehicle, and can effectively defend and capture the low-speed and small unmanned aerial vehicle in the low-altitude and super-low-altitude airspace below 500m in height, and is a low-cost, high-efficiency and high-return surveillance means.

[0006] In order to solve the above technical problems, one of the objects of the present application is to provide a range-extended unmanned aerial vehicle magnetic attraction flexible capture system, which comprises a ground launching system, a terminal capture system and an intelligent identification and tracking system, The ground launching system serves as a launching carrier of the catcher, which is composed of a launching barrel 1, a catcher 2, a restraining rod 3, a sealing gasket 4, a launching barrel rear plug 5, a ground launching power source interface 6, a switch valve 32 and a ground launching power source 33. The launching barrel 1 serves as an acceleration track for ground storage and launching of the catcher 2. The catcher 2 is fixed at the tail of the launching barrel 1 through the restraining rod 3. The restraining rod 3 is fixed at the tail of the launching barrel 1 through the launching barrel rear plug 5 by bolts. The sealing gasket 4 is arranged between the restraining rod 3 and the launching barrel 1 to realize sealing. The restraining rod 3 is fixed at the tail of the launching barrel 1 by the launching barrel rear plug 5 through bolts, so as to ensure reliable connection and fixation between the catcher 2 and the launching barrel 1. The ground launching power source interface 6 at the tail of the launching barrel 1 is used for connecting the ground launching power source 33; The intelligent identification and tracking system serves as identification and positioning of the unmanned aerial vehicle target. The target unmanned aerial vehicle is tracked and positioned by the intelligent identification and tracking system. The image and position information returned by the intelligent identification and tracking system are transmitted to the ground launching system through a certain solving algorithm, so as to transmit the spatial position of the target unmanned aerial vehicle and the best launching opportunity to the ground launching system. The ground launching system implements directional launching according to the program instructions. After the catcher is ejected from the launching barrel and approaches the target unmanned aerial vehicle, the net-throwing small rocket and the capture net are ejected according to the instructions provided by the program at a certain initial speed and angle. The circumferentially distributed net-throwing small rockets carry the capture net to implement wrapping and capturing of the target unmanned aerial vehicle. The terminal capture system consists of a projectile-net power chamber 9, a high-pressure gas source 13 for the extended-range power system, an igniter assembly 19, a capture net 21, a front-mounted strong magnet 22, a small net-throwing rocket 23, and a projectile-net gas generating propellant 31. Under the guidance of the intelligent identification and tracking system, the ground launch system ejects the projectile-net from the tube at a certain speed. The high-pressure gas source 13 of the extended-range power system of the capture device 2 continuously provides endurance flight power. As it approaches the UAV, the command control activates the igniter assembly 19, providing trigger excitation for the projectile-net gas generating propellant 31 in the projectile-net power chamber 9 during the flight of the capture device 2. This causes the projectile-net gas generating propellant 31 to generate a large amount of high-pressure gas. The high-pressure gas generated by the projectile-net power chamber 9 ejects the capture net 21 and the small net-throwing rocket 23. The small net-throwing rocket 23 unfolds the capture net 21, achieving flexible capture of the flying target. At the same time, the front-mounted strong magnet 22 applies strong magnetic field interference to the target UAV and uses a large magnetic attraction effect to force the UAV to be attracted into the capture net, thus achieving flexible capture of the target UAV.

[0007] Furthermore, the ground catapult power source 33 is a high-pressure cold air source, and the gas flow between the high-pressure cold air and the launch tube 1 is controlled by the switching valve 32. The ground catapult power source 33 is connected to the launch tube 1 through the ground catapult power source interface 6 via the switching valve 32.

[0008] Furthermore, the capture device 2 is composed of a capture device head cover 7, a magnetic net compartment 8, a projectile-net power compartment 9, a projectile-mounted switch 10, a payload compartment shell 11, a power supply and control module 12, a high-pressure gas source for the range-extending propulsion system 13, a tail compartment 14, a tail rod 15, tail fins 16, a rear adapter 17, a sealing ring 18, an igniter assembly 19, and a front adapter 20. The capture device head cover 7 is threadedly connected to the payload compartment shell 11 to protect and constrain the internal magnetic net compartment 8 and the circumferentially distributed small projectile rockets 23. The payload compartment shell 11 is an intermediate section, with its front end threadedly connected to support the magnetic net compartment 8. The payload compartment 11 is equipped with a power supply and control module 12 connected to the middle of the payload compartment shell 11 by screws, and an onboard switch 10 is provided on the outer wall. The rear end of the payload compartment shell 11 is connected to the tail compartment 14 of the range-extending power system by threads. A sealing groove is provided in the middle of the outer side of the payload compartment shell 11, and a sealing ring 18 is installed in the sealing groove. An adapter slot is also provided at the front end of the outer side of the payload compartment shell 11 for installing a front adapter 20. An adapter slot is also provided on the outer side of the tail compartment for installing a rear adapter 17. The front adapter 20 and the rear adapter 17 are used to ensure that the capture device 2 moves continuously and smoothly inside the launch tube 1.

[0009] Furthermore, the magnetic net chamber 8 is composed of a capture net 21, a front-mounted strong magnet 22, a net-throwing rocket 23, a net chamber 24, a magnetic net chamber cover 25, a net chamber plug 26, and a cap 27. The net-throwing rocket 23 is uniformly fixed circumferentially around the outer edge of the capture net 21. The net-throwing rocket 23 is installed in the hole where it is placed. The hole is connected to the air cavity at the bottom of the front-mounted strong magnet 22. The cap 27 is installed on the head of the front-mounted strong magnet 22 for restraint. The relative positions of the capture net 21, the small rocket 23 for throwing the net, and the front strong magnet 22; the lower part of the front strong magnet 22 is connected to the net chamber 24, and a net chamber blocking plate 26 is installed inside the lower cylindrical section of the net chamber 24; a magnetic net chamber cover 25 is installed and connected to the lower end of the net chamber 24, and the magnetic net chamber cover 25 is provided with a vent hole. The vent hole distributes the high-pressure gas generated by the launch net power chamber 8 to the net chamber 24 in a proportional manner, which pushes the net chamber blocking plate 26 to launch the capture net 21 out of the magnetic net chamber 8.

[0010] Furthermore, the bomb-net power compartment 9 consists of a power compartment 28, a rupture disc 29, a bomb-net high-pressure gas generator 30, and a bomb-net gas generating medium 31. The upper end of the power compartment 28 is installed and connected to the magnetically attached net compartment 8, and the lower end of the power compartment 28 is threadedly connected and installed to the bomb-net high-pressure gas generator 30. The bomb-net gas generating medium 31 is stored in the bomb-net high-pressure gas generator 30.

[0011] Furthermore, the working medium 31 for generating the bomb-net gas is a solid energy storage reagent that rapidly converts chemical energy into the pressure potential energy of high-pressure gas through ignition or impact; the inert gas working medium is stored in the bomb-net high-pressure gas generator 30.

[0012] Furthermore, the working medium 31 for generating the explosive net gas is black powder, sodium azide, or high-pressure nitrogen.

[0013] Furthermore, the small rocket 23 for throwing nets is composed of a small rocket magnetic block 34, a small rocket power air source 35, a small rocket cabin 36, and a small rocket plug 37. The small rocket magnetic block 34 is fixed to the small rocket cabin 36 by a threaded connection, the small rocket plug 37 is fixed to the tail of the small rocket cabin 36 by a threaded connection, and the small rocket power air source 35 is stored inside the small rocket cabin 36 as a high-pressure air source.

[0014] Furthermore, the ejection power source 33 is a high-pressure cold gas cylinder, a low-temperature combustion gas source, or a combination of gas and water power source.

[0015] Based on the same concept, this invention also proposes a capture method for a range-extended unmanned aerial vehicle (UAV) magnetic flexible capture system, the specific steps of which are as follows: S1: When a target drone illegally intrudes into an important area, ground security personnel and security equipment will detect and activate the drone capture system to intelligently identify, track, and locate the target drone. S2: The image position and speed information transmitted back by the above tracking and positioning are solved by the algorithm, and the spatial position of the target UAV and the best launch and capture time are transmitted to the ground launch system. The operator adjusts the direction of the launch tube 1 to point at the target UAV, and launches the capture device 2 in a directional manner when the opportunity arises. S3: Specific actions of launching the capture device 2: Open the switch valve 32 of the ground ejection power source 33, and the high-pressure gas is connected to the ground ejection power source interface 6 through the pipeline. The high-pressure gas is quickly filled from the tail of the launch tube 1 into the area between the launch tube 1 and the capture device 2. Under the action of the first-stage high-pressure gas, the capture device 2 is ejected outward by the gas pressure, which breaks the restraint rod 3. The capture device 2 flies out of the launch tube 1 under the action of the high-pressure gas. S4: The capture device 2 and the restraining rod 3 are connected by threads. After the restraining rod 3 is broken, the gas in the high-pressure gas source 13 of the range-extending power system in the capture device 2 is ejected from the tail of the capture device 2 through the central hole of the tail rod 15 to form range-extending power. The capture device 2 continues to fly towards the target UAV according to the predetermined trajectory. S5: According to the programmed instructions, the capture device 2 approaches the target UAV at a suitable position. After receiving the actuation command, the front-mounted projectile-net propulsion system 9 of the capture device 2 activates the projectile-net gas generating propellant 31 to generate high-pressure gas, which breaks through the rupture disc 29 and releases the high-pressure gas instantaneously. The high-pressure gas passes through... Figure 4 The "ventilation channel" shown is via Figure 3 The "vent" shown diverts the high-pressure gas and quickly fills the magnetic net cabin system 8, which then acts on the circumferentially distributed net-throwing rockets 23 and the capture net 21. At the same time, it opens the end cap 27 at the front of the capture device, and the circumferentially distributed net-throwing rockets 23 fly forward at a certain angle, carrying the capture net 21 and deploying synchronously. S6: The circumferentially distributed small rockets 23 pull the capture net that flies forward and quickly surrounds the target UAV, causing it to lose its flight capability. At the same time, the small rocket magnetic blocks 34 exert a strong magnetic field interference on the target UAV and use the large magnetic attraction effect to force the UAV to be sucked into the capture net, thus achieving flexible capture of the target UAV.

[0016] The above-described technical solutions of this invention have at least one or more of the following technical effects: The flexible drone capture system of this invention addresses the current market demand for hard defense against low-altitude, small, and slow-moving unmanned aerial vehicles (UAVs / objects). Combining practical usage requirements, it develops capture systems for near-, medium-, and long-range defense and attack. By integrating with a low-altitude radar system, it achieves non-destructive capture and rapid recovery of low-altitude, small, and slow-moving UAVs / objects, meeting the needs of counter-terrorism and emergency response in densely populated areas and low-altitude air defense, reducing the security threat posed by UAVs, and guiding the healthy development of the UAV industry. The application of this invention provides a low-altitude defense measure for public areas such as airports, large venues, and sensitive areas, and to a certain extent solves the threat posed by low-altitude, slow, and small flying objects such as unmanned reconnaissance aircraft. This invention uses ground-based high-pressure gas ejection and high-altitude net throwing to capture UAVs, which is clean, safe, and pollution-free.

[0017] The UAV flexible capture system has the following advantages: 1) Intelligent target identification and tracking, portable by a single soldier, simple to operate, high capture efficiency, good portability, and all-weather identification and strike capability; 2) The combination of cold air power, ground launch power and range-extending power of the capture device allows for a larger operating radius for capturing drones; 3) By combining a flexible capture net system with a strong magnetic magnet, a strong magnetic field is applied to the target UAV, and the large magnetic attraction effect is used to force the UAV to be attracted into the capture net. This dual capture measure ensures safe operation, rapid response, and non-destructive capture of the UAV. 4) It can be equipped on various platforms according to usage requirements, and can be launched by a single soldier, as well as by vehicle-mounted or airborne launchers. It has continuous firing capability and can cope with swarm attacks. It is low in cost and can be reused multiple times after simple processing. Attached Figure Description

[0018] Figure 1 : Schematic diagram of the launch tube status before ground launch; Figure 2 : Schematic diagram of the catcher structure; Figure 3 Schematic diagram of the magnetic mesh cabin structure; Figure 4 Schematic diagram of the bomb-net power compartment structure; Figure 5 : Schematic diagram of the ground system status before ground launch; Figure 6 Schematic diagram of a small rocket that throws nets; Figure 7 : Schematic diagram of the catapult-launched net throwing process; Figure 8 : A diagram showing the unfolded capture net; The components are as follows: 1-launch tube, 2-capture device, 3-control rod, 4-sealing gasket, 5-launch tube rear cap, 6-ground ejection power source interface, 7-capture device head cover, 8-magnetic net compartment, 9-ejection net power compartment, 10-ejection on-board switch, 11-payload compartment shell, 12-power supply and control module, 13-range-extended propulsion system high-pressure gas source, 14-tail compartment, 15-tail rod, 16-tail fin, 17-rear adapter, 18-sealing ring, 19-igniter assembly, 20-front adapter, 21-capture net, 22-front strong magnet, 23-net-throwing rocket, 24-net compartment, 25-magnetic net compartment cover, 26-net compartment plug, 27-head, 28-power compartment, 29-rupture disc, 30-ejection net high-pressure gas generator, 31-ejection net gas generating working fluid, 32-switch valve, 33-ground ejection power source. 34-Small rocket magnetic block, 35-Small rocket power source, 36-Small rocket cabin, 37-Small rocket plug. Detailed Implementation

[0019] When a drone illegally intrudes, the ground-based intelligent identification and tracking system of the capture system aims at the target drone, automatically measures the target's position and speed relative to the shooter, completes parameter setting, and the shooter triggers the launch button to complete the capture and recovery of the drone.

[0020] This invention primarily relates to a range-extended magnetic flexible capture system for unmanned aerial vehicles (UAVs). It proposes that a ground-based launch system and the capture device's own range-extending propulsion system jointly provide extended flight power, increasing the operational radius for UAV capture and defense. A small rocket launcher deploys a capture net to achieve flexible capture of the target. Simultaneously, a strong magnetic field is used to interfere with the target UAV, and the significant magnetic attraction force compels the UAV into the capture net, achieving flexible capture. This extended-range UAV magnetic flexible capture system offers fast response, high capture efficiency, and low cost. Its application provides a low-altitude defense measure for public areas such as airports, large venues, and sensitive zones, mitigating the threat posed by low-altitude, slow-moving, and small flying objects like UAVs to some extent.

[0021] This invention provides a range-extended unmanned aerial vehicle (UAV) magnetic flexible capture system, mainly comprising a launch tube 1, a capture device 2, a restraining rod 3, a sealing gasket 4, a launch tube rear cap 5, a ground ejection power source interface 6, a capture device head cover 7, a magnetic net compartment 8, an ejection net power compartment 9, an ejection-on-feed switch 10, a payload compartment shell 11, a power supply and control module 12, a high-pressure air source for the range-extended power system 13, a tail compartment 14, a tail boom 15, a tail fin 16, a rear adapter 17, a sealing ring 18, and an ignition system. The system comprises the following components: 19, front adapter 20, capture net 21, front-mounted strong magnet 22, small rocket for net launching 23, net chamber 24, magnetic net chamber cover 25, net chamber plug 26, end cap 27, power chamber 28, rupture disc 29, high-pressure gas generator for the net launcher 30, working medium for the net launcher gas 31, switching valve 32, ground ejection power source 33, small rocket magnetic block 34, small rocket power gas source 35, small rocket chamber 36, and small rocket plug 37. A schematic diagram of a range-extended unmanned aerial vehicle (UAV) magnetic flexible capture system is attached. Figure 1 To be continued Figure 6 As shown.

[0022] The launch tube 1, the capture device 2, the restraining rod 3, the sealing gasket 4, the launch tube rear cover 5, the ground ejection power source interface 6, the switching valve 32, and the ground ejection power source 33 together constitute the ground launch system of the capture device. (See appendix) Figure 1 .

[0023] The catcher head cover 7 is threaded onto the front end of the catcher to protect the catcher 2.

[0024] The structure of the magnetic mesh compartment 8 is shown in the attached diagram. Figure 3 The system mainly consists of a capture net 21, a front-mounted strong magnet 22, a small rocket for launching the net 23, a net compartment 24, a magnetic net compartment cover 25, a net compartment blocking plate 26, and a cap 27. The small rocket for launching the net 23 is launched in a predetermined direction, pulling the capture net 21 out of the net compartment 24 and unfolding it to capture the drone. The front-mounted strong magnet 22 and the small rocket magnetic block 34 at the front of the small rocket 23 exert a strong magnetic field interference on the target drone, and utilize the large magnetic attraction effect to force the drone into the capture net. The magnetic net compartment cover 25, the net compartment blocking plate 26, and the cap 27 together form the two ends of the magnetic net compartment 8.

[0025] The structure of the missile net power compartment 9 is shown in the attached diagram. Figure 4 It mainly consists of a power compartment 28, a rupture disc 29, a high-pressure gas generator 30 for the net and projectile, and a working medium 31 for generating the net and projectile. The net and projectile power compartment 9 is a pressure chamber that generates high-pressure gas to propel the capture net 21 and the small rockets 23 that launch the net. The rupture disc 29 is a device that builds up high pressure after the high-pressure gas generator 30 generates the working medium 31 for generating the net and projectile. When the pressure reaches a certain level, the rupture disc shears along the weakening groove, allowing the high-pressure gas to enter the power compartment 28.

[0026] The on-board switch 10 is a switch that connects the circuit to supply power to the equipment on the capture device 2 before launch.

[0027] The payload compartment shell 11 is the intermediate section of the capture device 2.

[0028] The power supply and control module 12 is a control system that supplies power to the devices on the capture device 2 and receives and gives control signals.

[0029] The high-pressure gas source 13 of the range-extending power system is the high-pressure gas working medium of the range-extending power source of the catcher 2.

[0030] The tail compartment 14 is a storage chamber for the high-pressure air source 13 of the range-extended propulsion system.

[0031] The tail boom 15 is connected to the tail fin 16 via a screw interface, and the tail boom 15 is connected to the tail section 14 via a threaded connection, which is sealed with thread sealant.

[0032] The rear adapter 17, sealing ring 18, and front adapter 20 provide dynamic sealing for the capture device 2 during the process of being propelled by the high-pressure gas emitted in the launch tube 1.

[0033] The igniter assembly 19 provides a triggering excitation for the working medium 31 for generating bomb net gas in the bomb net power compartment 9 during the flight of the capture device 2, so that the working medium 31 generates a large amount of high-pressure gas.

[0034] When not in use, the capture net 21 is stored in the magnetic net compartment 8, and when in use, it is used to capture drones.

[0035] The front-mounted strong magnet 22 is part of the magnetic net compartment 8 and is connected to the payload compartment shell 11 by threads. The front-mounted strong magnet 22 exerts a strong magnetic field interference on the target UAV and uses a large magnetic attraction effect to force the UAV to be attracted into the capture net.

[0036] The net-throwing rocket 23 is housed within the magnetic net compartment 8, see attached. Figure 3 The small rocket 23, which is connected to the magnetic net compartment 8 by threads, consists of a small rocket magnetic block 34, a small rocket power air source 35, a small rocket compartment 36, and a small rocket plug 37.

[0037] According to the requirements of the UAV capture mission, the ground ejection power source 33 is opened by the switch valve 32, so that the launch tube 1 is filled with high-pressure gas. The high-pressure gas acts on the rear end face of the capture device 2. When the pressure reaches a certain value, the weakening groove at the connection between the tail rod 15 and the tail compartment 14 is broken, and the capture device 2 flies out of the launch tube 1 at high speed. After the weakening groove at the connection between the tail rod 15 and the tail compartment 14 is broken, the high-pressure gas source 13 of the range-extending power system is discharged at high speed through the gas channel of the tail rod 15 of the capture device 2, providing continuous range-extending power for the capture device 2.

[0038] When the capture device 2 approaches the target drone, the high-pressure gas generated by the launch net power chamber 9 ejects the capture net 21 and the small net-throwing rocket 23. The small net-throwing rocket 23 then deploys the capture net 21, achieving flexible capture of the flying target. Simultaneously, a strong magnetic field interference is applied to the target drone using a strong magnetic magnet, and the large magnetic attraction effect forces the drone to be sucked into the capture net, achieving flexible capture of the target drone.

[0039] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments and accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments obtained. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention are within the scope of protection of the present invention.

[0040] 5.1 Structural Composition and Functional Introduction This invention provides a range-extended unmanned aerial vehicle (UAV) magnetic flexible capture system, mainly comprising a launch tube (1), a capture device (2), a restraining rod (3), a sealing gasket (4), a launch tube rear cover (5), a ground ejection power source interface (6), a capture device head cover (7), a magnetic net compartment (8), an ejection net power compartment (9), an ejection-mounted switch (10), a payload compartment shell (11), a power supply and control module (12), a high-pressure air source for the range-extended power system (13), a tail compartment (14), a tail boom (15), a tail fin (16), a rear adapter (17), and a sealing ring (18). The system comprises an igniter assembly 19, a front adapter 20, a capture net 21, a front-mounted strong magnet 22, a small rocket for launching the net 23, a net chamber 24, a magnetic net chamber cover 25, a net chamber plug 26, a cap 27, a power chamber 28, a rupture disc 29, a high-pressure gas generator for the net and projectile 30, a working medium for generating the net and projectile gas 31, a switching valve 32, a ground ejection power source 33, a small rocket magnetic block 34, a small rocket power gas source 35, a small rocket chamber 36, and a small rocket plug 37, among other components. A schematic diagram of a range-extended unmanned aerial vehicle (UAV) magnetic flexible capture system is attached. Figure 1 To be continued Figure 6 As shown.

[0041] An extended-range unmanned aerial vehicle (UAV) magnetic flexible capture system mainly consists of a ground launch system, an end-capture system, and an intelligent identification and tracking system.

[0042] The ground-based launch system, serving as the launch carrier for the capture device, mainly consists of a launch tube 1, a capture device 2, a restraining rod 3, a sealing gasket 4, a rear cap 5 of the launch tube, a ground ejection power source interface 6, a switching valve 32, a ground ejection power source 33, and related fasteners. The launch tube 1 serves as the ground-based launch carrier for the capture device 2, acting as a storage device for the capture device 2 in its non-operating state. In its operating state, it serves as the primary launch guide and acceleration device for the capture device 2. The launch tube 1 serves as the capture device's storage and provides the flight propulsion acceleration track. Before launch, it is used to fix the capture device 2, which is secured to the tail of the launch tube 1 by the restraining rod 3. The restraining rod 3 is bolted to the tail of the launch tube 1 by the rear cap 5, and the sealing gasket 4 provides end-face sealing between the restraining rod 3 and the launch tube 1. The end of the restraining rod 3 is placed inside the launch tube 1 and connected to the tail rod 15 of the capture device 2 via threads, thus fixing the capture device 2 inside the launch tube.

[0043] The aforementioned launch tube 1 serves as the ground storage and launch acceleration track for the capture device 2. A restraining rod 3 passes through the launch tube 1 and is threadedly connected to and secured to the tail rod 15 of the capture system at the end of the capture device 2. The restraining rod 3 passes from the rear end, and a sealing gasket 4 seals the connection between the restraining rod 3 and the launch tube 1. The rear end cap 5 of the launch tube then secures the restraining rod 3 to the tail of the launch tube 1 with bolts, ensuring a reliable connection and fixation between the capture device 2 and the launch tube 1. The ground ejection power source interface 6 at the tail of the launch tube 1 is used to connect to the ground ejection power source 33, as shown in the attached diagram. Figure 2 As shown. The ground ejection power source 33 is a high-pressure cold gas source. The gas supply between the high-pressure cold gas and the launch tube 1 is controlled by the switch valve 32. The ground ejection power source 33 is connected to the launch tube 1 through the ground ejection power source interface 6 via the switch valve 32. After receiving the ejection command, the launch tube (1) is aimed and the switch valve 32 is opened. The high-pressure gas from the ground ejection power source 33 quickly fills the launch tube 1. The capture device 2 is limited in the launch tube 1 by the restraining rod 3 via the tail rod 15. Since the capture device 2 is equipped with a radial sealing ring 18, the high-pressure gas is continuously pressurized in the launch tube 1 until the pressure on the capture device 2 exceeds the tensile strength limit of the weakening groove of the tail rod 15. The tail rod 15 is cut off along the weakening groove, and the capture device 2 is ejected at high speed along the launch tube 1, completing the ground launch mission. After the capture device 2 flies out of the launch tube 1, the switch valve 32 is closed and the gas supply is stopped.

[0044] The ground-based launch system for the capture device can be launched in various forms, such as by a single soldier carrying it on their shoulder, using a simple launcher, or by a vehicle, depending on the actual application.

[0045] The ground launch power source 33 can be a high-pressure cold gas cylinder, a low-temperature gas source, or a combination of gas and water power source.

[0046] The intelligent identification and tracking system is used for UAV target identification and positioning. This system consists of three parts: a tracking and identification system, an image display and processing system, and an auxiliary alignment system. The tracking and identification system can utilize a visible light tracking camera, a visible light recognition camera, a laser rangefinder, and a two-axis tracking gimbal. The optical axes of the visible light tracking camera, visible light recognition camera, and laser rangefinder are parallel. The two-axis tracking gimbal controls the attitude of all three devices, acquiring target image data and distance information for tracking and identification. It also adjusts the camera's line of sight to achieve target tracking. The image display and processing system uses a portable industrial computer and image processing and display software. It is primarily responsible for target detection and tracking processing based on image data, displaying image data from multiple cameras, and generating control commands for the tracking gimbal. The auxiliary alignment system includes a level mounted on the tracking and identification system, a level mounted on the capture interceptor, and an azimuth calibration visible light camera. The level is mainly used for horizontal calibration, and the visible light camera is mainly used for initial azimuth registration and synchronization, while also assisting in multiple target identification and confirmation. The target UAV is tracked and located by an intelligent identification and tracking system. The images and location information transmitted back are processed by a specific algorithm to transmit the target UAV's spatial position and optimal launch timing to the ground launch system. The system then launches the UAV in a directional manner according to programmed instructions. After the capture device ejects from its launch tube and approaches the target UAV, it launches small net-throwing rockets and a capture net at a predetermined initial velocity and angle, as instructed by the program. The circumferentially distributed small net-throwing rockets, carrying the capture net, encircle and capture the target UAV. The intelligent identification and tracking system is a mature technology and is not included in this patent's invention.

[0047] Under the guidance of the intelligent identification and tracking system, the terminal acquisition system launches the target drone at a certain speed from the launch tube by the ground launch system. The high-pressure gas source 13 of the range-extending power system of the acquirer 2 continuously provides endurance for flight, rapidly approaching the drone. Under command control, the igniter assembly 19 is activated, providing trigger excitation to the working propellant 31 in the net-and-net power chamber 9 during flight, causing the working propellant 31 to generate a large amount of high-pressure gas. The high-pressure gas generated by the net-and-net power chamber 9 ejects the acquisition net 21 and the net-throwing rocket 23. The net-throwing rocket 23 deploys the acquisition net 21, achieving flexible acquisition of the target drone. Simultaneously, a strong magnetic field is used to interfere with the target drone, and the large magnetic attraction effect forces the drone into the acquisition net, achieving flexible acquisition of the target drone.

[0048] The capture device 2 is installed in the launch tube 1. The capture device 2 consists of a capture device head cover 7, a magnetic net compartment 8, a missile net power compartment 9, a missile-mounted switch 10, a payload compartment shell 11, a power supply and control module 12, a high-pressure air source for the range-extending power system 13, a tail compartment 14, a tail rod 15, a tail fin 16, a rear adapter 17, a sealing ring 18, an igniter assembly 19, a front adapter 20, and other components.

[0049] The capture device head cover 7 is installed on the payload compartment shell 11 in the middle of the capture device 2 by a threaded connection, protecting and constraining the magnetic net compartment 8 and the circumferentially distributed net-throwing rockets 23 inside.

[0050] The magnetic net compartment 8 is installed at the front end of the catcher 2 via a threaded connection. It mainly consists of a catch net 21, a front-mounted strong magnet 22, a small net-throwing rocket 23, a net compartment chamber 24, a magnetic net compartment cover 25, a net compartment plug 26, and a sealing head 27. The magnetic net compartment 8 serves to store and install the catch net 21, fix the small net-throwing rocket 23, and install the front-mounted strong magnet 22. The small net-throwing rocket 23 is evenly fixed circumferentially around the outer edge of the catch net 21. The small net-throwing rocket 23 is installed in the hole for placing the small net-throwing rocket 23, and the hole is connected to the air chamber below the front-mounted strong magnet. The end cap 27 is installed at the head of the front strong magnet 22 to constrain the relative positions of the capture net 21 and the net-throwing rocket 23 with the front strong magnet 22; the lower part of the front strong magnet 22 is connected to the net chamber 24, and a net chamber blocking plate 26 is installed inside the lower cylindrical section of the net chamber 24; a magnetic net chamber cover 25 is installed and connected to the lower end of the net chamber 24, and the magnetic net chamber cover 25 is provided with a vent hole. The vent hole distributes the high-pressure gas generated by the net propulsion chamber 8 to the net chamber 24 in a proportional manner, pushing the net chamber blocking plate 26 to eject the capture net 21 out of the magnetic net chamber 8. See the appendix for the specific structure. Figure 3 and attached Figure 7 .

[0051] The net-throwing rocket 23 is housed within the magnetic net compartment 8 and is connected to the magnetic net compartment 8 via threads (see attached). Figure 3 The net-throwing rocket 23 consists of a small rocket magnetic block 34, a small rocket power source 35, a small rocket cabin 36, and a small rocket cover 37. The specific function of the net-throwing rocket 23 is to pull and deploy the capture net 21, flying towards the target UAV to perform a flexible capture mission. See the appendix for the detailed structural components of the net-throwing rocket 23. Figure 6 .

[0052] The bomb-net power compartment 9 is installed on the load compartment shell 11 via a threaded connection. The bomb-net power compartment 9 mainly consists of a power compartment 28, a rupture disc 29, a bomb-net high-pressure gas generator 30, and a bomb-net gas generating medium 31. The upper end of the power compartment 28 is installed and connected to the magnetically attached net compartment 8, and the lower end of the power compartment 28 is installed and connected to the bomb-net high-pressure gas generator 30 via a threaded connection. The bomb-net gas generating medium 31 is stored in the bomb-net high-pressure gas generator 30.

[0053] The working medium 31 for generating the bomb-net gas is stored in the bomb-net high-pressure gas generator 30. The working medium 31 for generating the bomb-net gas can be a solid energy storage reagent such as black powder or sodium azide, which can rapidly convert chemical energy into pressure potential energy of high-pressure gas through ignition or impact. The working medium 31 for generating the bomb-net gas can also be an inert gas such as high-pressure nitrogen, which is stored in the bomb-net high-pressure gas generator 30.

[0054] The rupture disc 29 is fixed under compression at its edge, and is preferably a circular aluminum sheet with an annular weakening groove. The rupture disc 29 is installed between the high-pressure gas generator 30 and the power compartment 28. The contact surfaces of the power compartment 28 and the magnetic mesh cover 25 of the magnetic mesh compartment 8 are arc-shaped. The inner arc surface of the power compartment 28 has a cross-shaped vent groove, and the magnetic mesh cover 25 has corresponding vent holes. Part of the high-pressure gas generated by the high-pressure gas generator 30 flows through the vent groove into the outer chamber of the magnetic mesh compartment 8, directly acting on the circumferentially distributed net-throwing rockets 23, propelling them out of the magnetic mesh compartment. The high-pressure gas passing through the vent holes enters the mesh compartment 24 of the magnetic mesh compartment, directly acting on the mesh blocking plate 26. The capturing net 21 is propelled by the mesh blocking plate 26 to achieve rapid ejection from the compartment. The specific structure of the bomb-net power compartment 9 is shown in the figure and appendix. Figure 4 .

[0055] The main function of the projectile-net power compartment 9 is as follows: After receiving the projectile-net command from the power supply and control module 12, the igniter assembly 19 ignites the projectile-net gas generating medium 31 in the projectile-net high-pressure gas generator 30 in the power compartment 28, thereby generating high-pressure projectile-net gas. This high-pressure gas is then generated by the rupture disc 29, which acts as a device to increase the pressure of the projectile-net gas generating medium 31 generated by the high-pressure projectile-net gas generator 30. When the pressure reaches a certain level, the rupture disc 29 shears along the weakening groove, allowing the high-pressure gas to enter the power compartment 28. The high-pressure gas in the power compartment 28 propels the capture net 21 and the net-throwing rocket 23 out of the capture device 2. The high-pressure gas then passes through the vent of the magnetic net cover 25 and through the net compartment plug 26, propelling the capture net 21 and the end cap 27 out of the net compartment 24 at high speed, where the end cap 27 detaches automatically. Under the action of high-pressure gas, the small rocket 23 is cut off along the weakening shear groove by the small rocket plug 37, and the small rocket power source 35 in the small rocket 23 is released freely. Through action and reaction forces, the small rocket 23 is launched in a predetermined direction, pulling the capture net 21 out of the net compartment 24 and unfolding it to capture the UAV. The front strong magnet 22 and the small rocket magnetic block 34 at the front end of the small rocket 23 exert a strong magnetic field interference on the target UAV, and use the large magnetic attraction effect to force the UAV to be attracted into the capture net. The magnetic net compartment cover 25, the net compartment plug 26 and the end cap 27 together form the two ends of the magnetic net compartment 8.

[0056] The payload compartment shell 11 is an intermediate section. Its front end is threadedly connected to the magnetic net compartment 8 and the missile net power compartment 9. A power supply and control module 12 is screwed into the middle of the payload compartment shell 11, and an onboard switch 10 is installed on the outer wall. The rear end of the payload compartment shell 11 is threadedly connected to the tail compartment 14 of the range-extending power system. A sealing groove is provided in the middle of the outer side of the payload compartment shell 11, and a sealing ring 18 is installed inside the sealing groove. An adapter slot is also provided at the front of the outer side of the payload compartment shell 11 for installing a front adapter 20; an adapter slot is also provided on the outer side of the tail compartment for installing a rear adapter 17. The front adapter 20 and the rear adapter 17 ensure continuous and smooth movement of the capture device 2 inside the launch tube 1.

[0057] The onboard switch 10 is installed on the outer wall of the middle section of the payload compartment shell 11 and is used to start and stop the control system on the capture device 2.

[0058] The control system consists of a power supply and control module 12. The control system is installed in the tail compartment and is used to track and detect the flight trajectory of the capture device, as well as to receive ground bomb net commands and control the start-up of the bomb net power compartment 9 through the igniter assembly 19.

[0059] The tail compartment 14 is connected to the middle load compartment shell 11 by a threaded connection. The tail compartment 14 is a storage chamber for the high-pressure air source 13 of the range extender power system. A tail rod 15 is installed and connected to the tail of the tail compartment 14. Tail fin slots are evenly distributed around the end of the tail rod 15, and the tail fin 16 is installed in the tail fin slots.

[0060] The tail rod is connected to the restraint rod 3 at the tail of the launch tube.

[0061] The high-pressure gas supplied by the ground ejection power source 33 is continuously pressurized in the launch tube 1 until the pressure on the capture device 2 exceeds the tensile strength limit of the weakening groove of the tail rod 15. The tail rod 15 is cut off along the weakening groove, and the capture device 2 is ejected at high speed along the launch tube 1. The high-pressure gas source 13 of the range-extending propulsion system in the tail compartment 14 is ejected at high speed to the rear through the gas channel in the middle of the tail rod 15. Through action and reaction forces, the capture device 2 is propelled to fly along the predetermined trajectory, thus achieving extended-range flight of the capture device 2.

[0062] 5.2 Implementation Process This invention relates to a range-extended unmanned aerial vehicle (UAV) magnetic flexible capture system, which mainly comprises a ground launch system, a terminal capture system, and an intelligent identification and tracking system. The specific embodiments of this invention are described in detail below with reference to the accompanying drawings.

[0063] A range-extended unmanned aerial vehicle (UAV) magnetic flexible capture system includes the following steps for capturing the UAV: Step 1: When a target drone illegally intrudes into a large public place, a private or sensitive area, ground security personnel and security equipment will detect and activate the drone capture system to intelligently identify, track and locate the target drone. Step 2: The image position and speed information transmitted back from the tracking and positioning are processed by a certain algorithm to transmit the spatial position of the target UAV and the optimal launch time to the ground launch system, and the directional launch is carried out on time according to the program instructions; Step 3: Activate the ground-based power source, and the capture device flies out of the launch tube under the action of the first-stage ejection force; Step 4: Under the action of the second-stage extended-range power, the capture device continues to fly towards the target UAV along the predetermined trajectory; Step 5: According to the programmed instructions, when approaching the target UAV at a suitable position, the net-launching propulsion system releases high-pressure gas after receiving the net-launching actuation command. The high-pressure gas quickly fills the magnetic net-attracting compartment through the gas diversion device and acts on the circumferentially distributed net-launching rockets and the capture net. At the same time, the end cap at the front of the capture device is opened, and the circumferentially distributed net-launching rockets fly forward at a certain tilt angle, carrying the capture net and deploying synchronously.

[0064] Step 6: The capture net, which extends forward, quickly wraps around the target drone, rendering it incapable of flight. Simultaneously, a strong magnetic field is used to interfere with the target drone, and the significant magnetic attraction forces the drone into the capture net, achieving a flexible capture.

[0065] This invention addresses emergency control of unauthorized flights of low- and medium-altitude drones and can be used for aerial security protection in large public places, large conferences, confidential locations, and public places with security risks. It enables the non-destructive capture and rapid recovery of low-altitude, low-speed rotary-wing drones, meeting the needs of counter-terrorism and emergency response in densely populated areas and low-altitude air defense.

[0066] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the embodiments of the present invention. Thus, if these modifications and variations to the embodiments of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

[0067] The extended-range UAV magnetic flexible capture system disclosed in this invention has passed multiple assessment and verification tests as well as simulation tests, verifying the rationality and feasibility of the capture system's principle. This extended-range UAV magnetic flexible capture system offers fast response speed, high capture efficiency, and low cost. Its application provides a low-altitude defense measure for public areas such as airports, large venues, and sensitive areas, mitigating the threat posed by low-altitude, slow-moving, and small flying objects such as unmanned reconnaissance aircraft to a certain extent.

Claims

1. A magnetic flexible capture system for extended-range unmanned aerial vehicles (UAVs), characterized in that: Includes ground-based launch systems, terminal acquisition systems, and intelligent identification and tracking systems. The ground-based launch system, serving as the launch carrier for the capture device, comprises a launch tube (1), a capture device (2), a restraining rod (3), a sealing gasket (4), a rear cover of the launch tube (5), a ground ejection power source interface (6), a switching valve (32), and a ground ejection power source (33). The launch tube (1) serves as the ground storage and launch acceleration track for the capture device (2). The capture device (2) is fixed to the tail of the launch tube (1) by a threaded connection via a restraining rod (3). The restraining rod (3) is fixed to the tail of the launch tube (1) by bolts via the launch tube rear cover (5). The restraining rod (3) and the launch tube (1) are pressed together by a sealing gasket (4) to achieve end face sealing. The restraining rod (3) is then fixed to the tail of the launch tube (1) by bolts via the launch tube rear cover (5) to ensure reliable connection and fixation between the capture device (2) and the launch tube (1). The ground ejection power source interface (6) at the tail of the launch tube (1) is used to connect to the ground ejection power source (33), and the connection method is a threaded connection. The intelligent identification and tracking system is used for the identification and positioning of UAV targets. The target UAV is tracked and positioned by the intelligent identification and tracking system. The images and location information transmitted back are solved by a certain algorithm. The spatial position of the target UAV and the best launch time are transmitted to the ground launch system. The directional launch is carried out on time according to the program instructions. After the capture device pops out of the launch tube and approaches the target UAV, it will launch the net-throwing rocket and the capture net (21) in advance according to the instructions provided by the program at a certain initial velocity and angle. The circumferentially distributed net-throwing rocket (23) carries the capture net to surround and capture the target UAV. The terminal capture system mainly refers to the capture device (2). Under the guidance of the intelligent identification and tracking system, the ground launch system ejects the capture device (2) out of the tube at a certain speed. The high-pressure gas source of the extended range power system of the capture device (2) continuously provides the power for the flight. When it approaches the UAV, the command controls the ignition component to provide the trigger excitation for the working medium of the bomb net power cabin system during the flight of the capture device (2). This causes the working medium of the bomb net gas to generate a large amount of high-pressure gas. The high-pressure gas generated by the bomb net power cabin system ejects the capture net and the small rocket that throws the net. The small rocket then unfolds the capture net to achieve flexible capture of the flying target. At the same time, a strong magnetic field interference is applied to the target UAV through the front strong magnet. The large magnetic attraction effect forces the UAV to be attracted into the capture net, thus achieving flexible capture of the target UAV.

2. The extended-range UAV magnetic flexible capture system according to claim 1, characterized in that: The ground catapult power source (33) is a high-pressure cold air source. The gas flow between the high-pressure cold air and the launch tube (1) is controlled by the switch valve (32). The ground catapult power source (33) is threadedly connected to the launch tube (1) interface via the ground catapult power source interface (6) through the switch valve (32).

3. The extended-range UAV magnetic flexible capture system according to claim 1, characterized in that: The capture device (2) consists of a capture device head cover (7), a magnetic net cabin system (8), a projectile net power cabin system (9), a projectile switch (10), a payload cabin shell (11), a power supply and control module (12), a high-pressure gas source for the range-extending power system (13), a tail section (14), a tail boom (15), a tail fin (16), a rear adapter (17), a sealing ring (18), an igniter assembly (19), and a front adapter (20). The capture device head cover (7) is threadedly installed on the payload cabin shell (11) to protect and constrain the internal magnetic net cabin system (8) and the circumferentially distributed small net-throwing rockets (23). The payload cabin shell (11) is an intermediate section, with the front end threadedly connected to the magnetic net cabin system (8) and the projectile net power cabin system (23). The missile net power compartment system (9); the power supply and control module (12) is connected and installed in the middle of the payload compartment shell (11) by screws evenly distributed around the circumference, and the missile switch (10) is set on the outer wall of the payload compartment shell (11); the rear end of the payload compartment shell (11) is connected to the tail compartment (14) of the range-extending power system by threads, and a sealing groove is set in the middle of the outer side of the payload compartment shell (11), and a sealing ring (18) is installed in the sealing groove. An adapter slot is also set at the front end of the outer side of the payload compartment shell (11) for installing the front adapter (20); an adapter slot is also set on the outer side of the tail compartment for installing the rear adapter (17). The front adapter (20) and the rear adapter (17) are used to ensure that the capture device (2) moves continuously and smoothly inside the launch tube (1).

4. The extended-range UAV magnetic flexible capture system according to claim 3, characterized in that: The magnetic net cabin system (8) is composed of a capture net (21), a front strong magnet (22), a net-throwing rocket (23), a net cabin chamber (24), a magnetic net cabin cover (25), a net cabin plug (26), and a cap (27). The net-throwing rocket (23) is uniformly fixed around the outer edge of the capture net (21). The net-throwing rocket (23) is installed in the hole where it is placed. The hole is connected to the air cavity at the bottom of the front strong magnet (22). The cap (27) is installed on the head of the front strong magnet (22) to constrain the capture. The relative positions of the net (21) and the net-throwing rocket (23) with the front strong magnet (22); the lower part of the front strong magnet (22) is connected to the net compartment (24), and the net compartment plug (26) is installed inside the lower cylindrical section of the net compartment (24); a magnetic net compartment cover (25) is installed and connected to the lower end of the net compartment (24), and the magnetic net compartment cover (25) is provided with a vent hole. The vent hole distributes the high-pressure gas generated by the net propulsion compartment (9) to the net compartment (24) in proportion, and pushes the net compartment plug (26) to eject the capture net (21) out of the magnetic net compartment system (8).

5. The extended-range UAV magnetic flexible capture system according to claim 3, characterized in that: The bomb-net power compartment system (9) consists of a power compartment (28), a rupture disc (29), a bomb-net high-pressure gas generator (30), and a bomb-net gas generating medium (31). The upper end of the power compartment (28) is installed and connected to the magnetic net compartment system (8), and the lower end of the power compartment (28) is threadedly connected to the bomb-net high-pressure gas generator (30). The bomb-net gas generating medium (31) is stored in the bomb-net high-pressure gas generator (30).

6. The extended-range UAV magnetic flexible capture system according to claim 5, characterized in that: The working medium (31) for generating the bomb-net gas is a solid energy storage reagent that rapidly converts chemical energy into the pressure potential energy of high-pressure gas through ignition or impact; the inert gas working medium is stored in the bomb-net high-pressure gas generator (30).

7. The extended-range UAV magnetic flexible capture system according to claim 6, characterized in that: The working medium (31) for generating the explosive net gas is black powder, sodium azide, or high-pressure nitrogen.

8. The extended-range UAV magnetic flexible capture system according to claim 4, characterized in that: The small rocket (23) is composed of a small rocket magnetic block (34), a small rocket power air source (35), a small rocket cabin (36), and a small rocket plug (37). The small rocket magnetic block (34) is fixed to the small rocket cabin (36) by a threaded connection. The small rocket plug (37) is fixed to the tail of the small rocket cabin (36) by a threaded connection. The small rocket power air source (35) is stored inside the small rocket cabin (36) as a high-pressure air source.

9. The extended-range UAV magnetic flexible capture system according to claim 1, characterized in that: The ejection power source (33) is a high-pressure cold gas cylinder, a low-temperature gas source, or a combination of gas and water power source.

10. The capture method of the extended-range UAV magnetic flexible capture system according to any one of claims 1-9, characterized in that, The specific steps are as follows: S1: When a target drone illegally intrudes into an important area, ground security personnel and security equipment will detect and activate the drone capture system to intelligently identify, track, and locate the target drone. S2: The image position and motion speed information transmitted back by the above tracking and positioning are solved by the algorithm, and the spatial position of the target UAV and the best launch capture time are transmitted to the ground launch system. The operator adjusts the direction of the launch tube (1) to point at the target UAV and launches the capture device (2) in a directional manner when the opportunity arises. S3: Specific actions of launching the capture device (2): Open the switch valve (32) of the ground ejection power source (33), and the high-pressure gas is connected to the ground ejection power source interface (6) through the pipeline. The high-pressure gas is quickly filled from the tail of the launch tube (1) into the area between the launch tube (1) and the capture device (2). Under the action of the first-level high-pressure gas, the capture device (2) is subjected to the outward ejection gas pressure, which breaks the restraint rod (3). The capture device (2) flies out of the launch tube (1) under the action of the high-pressure gas. S4: The capture device (2) and the restraining rod (3) are connected by threads. After the restraining rod (3) is broken, the gas in the high-pressure gas source (13) of the range-extending power system in the capture device (2) is ejected from the tail of the capture device (2) through the center hole of the tail rod (15) to form range-extending power. The capture device (2) continues to fly towards the target UAV according to the predetermined trajectory. S5: According to the programmed instructions, when the capture device (2) approaches the target UAV at a suitable position, the net-launching power system (9) at the front of the capture device (2) receives the net-launching action instruction and activates the net-launching gas generating working medium (31) to generate high-pressure gas, which breaks through the rupture disc (29) and releases the high-pressure gas instantly. The high-pressure gas is diverted through the "ventilation slot" shown in Figure 4 and the "ventilation hole" shown in Figure 3 and quickly fills the magnetic net-capturing cabin system (8), and acts on the circumferentially distributed net-throwing rockets (23) and the capture net (21) respectively. At the same time, the end cap (27) at the front of the capture device is opened, and the circumferentially distributed net-throwing rockets (23) fly forward at a certain tilt angle and carry the capture net (21) to deploy synchronously. S6: The circumferentially distributed small rockets (23) pull the capture net that flies forward and quickly surrounds the target UAV, causing it to lose its flight capability. At the same time, the small rockets' magnetic blocks (34) exert a strong magnetic field interference on the target UAV, and the large magnetic attraction effect forces the UAV to be attracted into the capture net, thus achieving flexible capture of the target UAV.

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