Rotor unmanned aerial vehicle

Abstract

The invention discloses a rotor wing unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicles, the rotor wing unmanned aerial vehicle comprises an unmanned aerial vehicle main body and a plurality of rotor wing units with independent flight capability, the rotor wing units are detachably connected with the unmanned aerial vehicle main body through electromagnetic lock catches and high-speed photoelectric interfaces, and radio frequency antennas are arranged around the unmanned aerial vehicle main body; a positioning module for measuring position information of the unmanned aerial vehicle body is arranged in the unmanned aerial vehicle body, and a directional warhead for striking the anti-unmanned aerial vehicle device is arranged on the rotor wing unit; when the rotor unmanned aerial vehicle is interfered by the anti-unmanned aerial vehicle device, a main calculation module in the unmanned aerial vehicle main body can obtain coordinates of the anti-unmanned aerial vehicle device through a radio frequency antenna and a positioning module, distributes a flight path to the rotor units and unlocks the electromagnetic lock catches, so that the rotor units autonomously fly according to the distributed path; and after the unmanned aerial vehicle flies to the anti-unmanned aerial vehicle device, the anti-unmanned aerial vehicle device is accurately struck by utilizing the directional warhead, and the unmanned aerial vehicle main body can continuously complete a set task by utilizing the remaining rotor wing units.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and in particular to a rotary-wing UAV. Background Technology

[0002] With the rapid iteration of drone technology, its applications in civilian aerial photography, logistics transportation, agricultural plant protection, and military reconnaissance and target strike are becoming increasingly widespread. However, at the same time, security risks such as unauthorized drone flights and malicious intrusions are becoming increasingly prominent, leading to the emergence and research focus of counter-drone technology. Currently, counter-drone devices have become key equipment for ensuring the safety of important facilities (such as airports, nuclear power plants, and military bases) and large-scale events. They utilize various technical means to intercept, force landing, or destroy illegal or hostile drones, effectively restraining drones.

[0003] Current mainstream anti-drone technologies have formed a multi-dimensional system, and the core technology paths mainly include the following four categories: Radio jamming technology: This technique involves transmitting radio signals in specific frequency bands to block the communication link between the drone and its remote controller, or to interfere with its internal data transmission, causing the drone to lose control. This technology is widely used and relatively inexpensive, but its effective range is limited and it is susceptible to complex electromagnetic environments.

[0004] GPS spoofing technology: By simulating GPS satellite signals, false location information is sent to drones, misleading them from their planned flight paths and even forcing them to land in designated areas. This technology is highly effective against drones that rely on satellite navigation, but it is less effective against drones with multi-mode navigation capabilities.

[0005] Laser / microwave hard-kill technology: This technology uses high-energy laser or microwave beams to irradiate drones, directly destroying their critical components such as circuits and motors, achieving physical destruction. While this technology offers high precision and fast response, the equipment is bulky, energy-intensive, and its portability and sustained combat capability are limited.

[0006] Net capture / interception technology: This technology physically captures or forces away a target drone by launching capture nets or intercepting it with other drones. It is a non-destructive countermeasure suitable for scenarios requiring drone recovery, but it demands extremely high timing and precision in interception and is easily affected by the target drone's maneuverability.

[0007] However, when existing drones are on missions, they are often caught in a passive defense dilemma if they encounter radio jamming or GPS spoofing techniques from anti-drone devices. Once their core systems, such as communication and navigation, are disrupted, the drone is very likely to lose control, not only failing to complete its mission but also potentially being captured by the enemy, resulting in mission failure and equipment loss. In high-intensity scenarios such as military confrontations, this "disruption upon jamming" defect is particularly fatal.

[0008] In one known technology, when a drone encounters interference from an anti-drone device, it can perform passive evasion operations such as returning to home or making a forced landing through a preset program. Although it can avoid being captured by the enemy, it still cannot continue to complete the intended mission and cannot change the "suppressed" situation.

[0009] In another technology known to the applicant, when a drone encounters interference from an anti-drone device, it can perform a strike mission by approaching the drone device to strike it. However, this technology carries an extremely high risk of the drone being captured or damaged during the strike.

[0010] Therefore, there is an urgent need for a rotary-wing drone that can be detached for precision strikes while the main body of the drone can continue to complete its intended mission. Summary of the Invention

[0011] The purpose of this invention is to provide a rotary-wing unmanned aerial vehicle (UAV) to solve the problems existing in the prior art. When interfered with by anti-UAV devices, the rotor unit can be autonomously separated, and the separated rotor unit can fly independently to the anti-UAV device and use a directional warhead to strike the anti-UAV device.

[0012] To achieve the above objectives, the present invention provides the following solution: The present invention provides a rotary-wing unmanned aerial vehicle (UAV), including a UAV body and multiple rotor units with independent flight capabilities. The rotor units are detachably connected to the UAV body via electromagnetic latches and high-speed photoelectric interfaces. Radio frequency antennas are provided around the UAV body. A positioning module for measuring its own position information is provided inside the UAV body. A directional warhead for attacking anti-UAV devices is provided on the rotor units.

[0013] Preferably, the rotor unit includes a motor, a propeller, an independent flight control system for flight control, and an auxiliary power supply for providing endurance, wherein the motor is drivenly connected to the propeller.

[0014] Preferably, the rotor unit further includes a power management module for monitoring the power of the auxiliary power supply, and the power management module is connected to the control system of the UAV body through the high-speed optoelectronic interface.

[0015] Preferably, a lateral limiting mechanism is provided between the rotor unit and the drone body. The lateral limiting mechanism includes a limiting groove and a limiting block. The limiting groove and the limiting block are respectively provided on the end faces of the rotor unit and the drone body that are detachably connected to each other. The limiting block is inserted into the limiting groove.

[0016] Preferably, a catapult device is provided between the rotor unit and the main body of the UAV to assist the rotor unit in detaching.

[0017] Preferably, the ejection device is a spring.

[0018] Preferably, the UAV body is equipped with a main power supply system, a main computing module, and a multi-band communication module.

[0019] Preferably, the positioning module is a GPS / BeiDou dual-mode positioning system and an INS inertial navigation system; or the positioning module is an INS inertial navigation system.

[0020] Preferably, the main body of the drone is equipped with a parachute recovery system.

[0021] Preferably, the directional warhead is a shaped charge warhead, and the rotor unit is equipped with a fuse that triggers the shaped charge warhead based on the ranging information from the ranging module; the directional warhead is an electromagnetic pulse payload.

[0022] The present invention achieves the following main technical effects compared to the prior art: When a rotorcraft drone is interfered with by an anti-drone device, the main computing module inside the drone can obtain the coordinates of the anti-drone device through relevant data measured by the radio frequency antenna and the positioning module. Based on the coordinates of the anti-drone device, the drone can allocate a flight path to the rotor unit. At this time, the rotor unit can fly autonomously according to the allocated path by unlocking the electromagnetic lock. After the rotor unit flies to the anti-drone device, it can use the directional warhead to accurately strike the anti-drone device, achieving the tactical goal of "precise positioning and directional strike". The drone body with the rotor unit separated can continue to complete the predetermined mission using the remaining rotor unit.

[0023] Other solutions of the present invention achieve the following technical effects compared with the prior art: The drone is equipped with a multi-band communication module, which can automatically switch to another frequency band when a single frequency band is disturbed, ensuring emergency communication between the drone and the ground control center.

[0024] The drone's main body is equipped with an INS inertial navigation system in its positioning module. When satellite signals are interfered with, it can automatically switch to INS navigation mode and calculate its position through inertial measurement data, ensuring that the flight trajectory of the drone's main body and rotor unit is controllable. Attached Figure Description

[0025] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0026] Figure 1This is a schematic diagram of the structure of the rotary-wing UAV in an embodiment of the present invention; Figure 2 This is a front view of a rotary-wing unmanned aerial vehicle in an embodiment of the present invention; Figure 3 This is a left view of a rotary-wing UAV in an embodiment of the present invention; Figure 4 This is a top view of a rotary-wing unmanned aerial vehicle in an embodiment of the present invention; Figure 5 This is a flowchart illustrating the operation of a rotary-wing unmanned aerial vehicle (UAV) in an embodiment of the present invention. The components include: 1. the main body of the drone; 2. the rotor unit; 3. the electromagnetic latch; 4. the motor; 5. the propeller; 6. the visual sensor; and 7. the infrared remote sensing and miniature camera. Detailed Implementation

[0027] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] The purpose of this invention is to provide a rotary-wing unmanned aerial vehicle (UAV) to solve the problems existing in the prior art. When interfered with by anti-UAV devices, the rotor unit can be autonomously separated, and the separated rotor unit can fly independently to the anti-UAV device and use a directional warhead to strike the anti-UAV device.

[0029] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0030] Please refer to the following: Figures 1-5As shown, a rotary-wing unmanned aerial vehicle (UAV) is provided, including a UAV body 1 and multiple rotor units 2 with independent flight capabilities. The rotor units 2 are detachably connected to the UAV body 1 via electromagnetic latches 3 and high-speed photoelectric interfaces. Radio frequency antennas are provided on all four sides of the UAV body 1. A positioning module for measuring its own position information is provided inside the UAV body 1. A directional warhead for attacking anti-UAV devices is provided on the rotor units 2. When the rotary-wing UAV is interfered with by an anti-UAV device, the main computing module inside the UAV body 1 can obtain the coordinates of the anti-UAV device through the relevant data measured by the radio frequency antennas and the positioning module, and can allocate a flight path to the rotor units 2 according to the coordinates of the anti-UAV device. At this time, the electromagnetic latches 3 can be unlocked, allowing the rotor units 2 to fly autonomously according to the allocated path. After the rotor units 2 fly to the anti-UAV device, they use the directional warheads to accurately strike the anti-UAV device. The UAV body 1, after separating the rotor units 2, can continue to complete the predetermined mission using the remaining rotor units 2.

[0031] The detachable connection structure and principle between rotor unit 2 and drone body 1 are as follows: Electromagnetic latch 3 includes an electromagnet and an iron block. The electromagnet is mounted on drone body 1, and the iron block is mounted on rotor unit 2. The electromagnet's energization is controlled by drone body 1. When energized, the electromagnet attracts the iron block, thereby adsorbing rotor unit 2 onto drone body 1 (adsorption force ≥ 50N), ensuring a secure connection between rotor unit 2 and drone body 1 during flight. When de-energized, the electromagnet loses its attraction to the iron block, and rotor unit 2 detaches from drone body 1. The separation response time is ≤ 50ms. The high-speed photoelectric interface has male and female terminals. The male and female ends are respectively set on the end faces of the rotor unit 2 and the UAV body 1, which are detachably connected to each other. During the process of the rotor unit 2 being attached to the UAV body 1, the male and female ends are in the plug-in state, realizing high-speed data transmission between the UAV body 1 and the rotor unit 2 (the transmitted data includes target coordinates, flight commands, and status information, with the status information referring to the current attitude information of the rotor unit 2). The transmission rate is ≥1Gbps and the delay is ≤10ms. After the rotor unit 2 is separated, the high-speed photoelectric interface is automatically disconnected, and the independent flight control system of the rotor unit 2 is immediately started to take over the flight control. The UAV body 1 then adjusts its own attitude to maintain stable flight.

[0032] In this embodiment, four high-sensitivity radio frequency antennas are evenly arranged around the main body 1 of the UAV to form a 360° radio frequency monitoring antenna array, forming a 360° monitoring range without blind spots. The detection frequency range covers 0.8GHz-6GHz (covering the interference frequency band of mainstream anti-UAV devices), and can quickly capture the strength, frequency and phase information of interference signals, providing data support for the location of interference sources.

[0033] The main body 1 of the drone can be made of carbon fiber fuselage frame. The carbon fiber fuselage frame is integrally molded with high-strength carbon fiber composite material, which has the characteristics of light weight and strong impact resistance. It can withstand the vibration and stress during the flight of the main body 1 of the drone and the separation of the rotor unit 2. At the same time, the carbon fiber fuselage frame has a certain electromagnetic shielding capability, reducing the influence of external interference on the internal electronic components and improving the accuracy of the operation of the internal electronic components.

[0034] In this embodiment, the main body 1 of the UAV is equipped with four rotor units 2 around its perimeter, which can improve flight stability during normal flight. After one rotor unit 2 is separated, the remaining rotor units 2 can be used to continue to complete the predetermined task.

[0035] The rotor unit 2 includes a motor 4, a propeller 5, an independent flight control system for flight control, and an auxiliary power supply for providing endurance. The motor 4 and propeller 5 are connected by a drive. The independent flight control system mainly refers to the equipped micro flight control chip, which has built-in attitude control and path planning algorithms. It can receive target coordinates and flight path commands sent by the main UAV 1 and autonomously complete flight control. It also has obstacle avoidance function (detecting obstacles through built-in infrared sensors) to avoid collisions during flight. The motor 4 is a high-power brushless DC motor (power ≥ 50W), and the propeller 5 adopts a coaxial dual-propeller structure. The propeller 5 is a fiber propeller 5, which, together with the brushless motor, can reach a speed of 6000rpm, providing sufficient lift and maneuverability to ensure that the flight attitude can be quickly adjusted after separation to track the target. The auxiliary power supply provides power to the rotor unit 2 separately, supporting its continuous flight for more than 30 minutes, meeting the full process requirements of positioning, tracking, and attack. The auxiliary power supply can be a small high-rate lithium battery (capacity ≥ 2000mAh, voltage 11.1V) or a high-density lithium battery, which can increase the flight time to 45 minutes, suitable for long-distance, long-duration mission scenarios.

[0036] The rotor unit 2 also includes a power management module for monitoring the power of the auxiliary power source. The power management module is connected to the control system of the drone body 1 through a high-speed photoelectric interface. The drone body 1 can obtain the power information of the auxiliary power source through the power management module. The power management module can be equipped with a low power alarm function, which will provide feedback to the drone body 1 when the power is insufficient. The drone body 1 can transmit the alarm information to a remote terminal through its own remote data transmission module to remind the user to charge as soon as possible.

[0037] A lateral limiting mechanism is provided between the rotor unit 2 and the drone body 1. The lateral limiting mechanism includes a limiting groove and a limiting block. The limiting groove and the limiting block are respectively set on the end faces of the rotor unit 2 and the drone body 1 that are detachably connected to each other. The limiting block and the limiting groove are inserted into each other. After the two are inserted, the lateral limiting between the rotor unit 2 and the drone body 1 can be realized. With the help of the electromagnetic lock 3, it is ensured that the rotor unit 2 will not loosen due to vibration or airflow during flight.

[0038] The design of the lateral limiting mechanism will affect the smooth separation of the rotor unit 2 to some extent. Therefore, a miniature ejection device is set between the rotor unit 2 and the main body of the UAV to assist the rotor unit 2 in detaching. The ejection device can actively push out the rotor unit 2 after the electromagnetic lock 3 loses power, so as to achieve rapid separation of the rotor unit 2.

[0039] In this embodiment, the ejection device uses a spring. The spring can be set in the limiting groove, with one end fixedly connected to the bottom of the limiting groove and the other end abutting against the limiting block. Alternatively, a placement groove can be set separately on the drone body 1 or the rotor unit 2. One end of the spring is fixedly connected to the bottom of the placement groove, and the other end abuts against the rotor unit 2 or the drone body 1. The spring can generate thrust (≤10N) based on its own elasticity to quickly separate the rotor unit 2 from the drone body 1, avoiding collisions during separation.

[0040] In other embodiments, a small electric telescopic cylinder can be used instead of a spring to extend the rotor unit 2. The extension and retraction of the small electric telescopic cylinder is controlled by the main body 1 of the UAV.

[0041] In this embodiment, the main body 1 of the UAV mainly includes a main power supply system, a main computing module, and a multi-band communication module. The main power supply module includes a main power supply and an intelligent power management module. The intelligent power management module dynamically allocates power according to the energy consumption of each component. The main power supply provides power solely to the core components of the UAV body 1, ensuring that the UAV body 1 can continue to operate for more than 2 hours after the rotor unit 2 separates, in order to complete the intended mission. The main power supply can use two high-capacity lithium batteries connected in parallel (total capacity ≥ 10000mAh, voltage 22.2V), or a hydrogen fuel cell, extending the flight time to more than 4 hours. The multi-band communication module integrates 2.4GHz and 5.8GHz dual-band communication chips, supports frequency hopping communication technology, and can automatically switch to another band when one band is disturbed, ensuring emergency communication between the UAV body 1 and the ground control center. It also reserves a military-grade encrypted communication interface, allowing for upgrades to encrypted transmission functions according to scenario requirements. The main computing module is equipped with a high-performance embedded processor (such as ARM). (Cortex-A9 architecture), running a self-developed countermeasure control algorithm, responsible for receiving radio frequency monitoring data, calculating the location of interference sources, allocating strike missions, controlling rotor separation and subsequent actions of the UAV body 1, with a response time of ≤100ms, ensuring the speed of countermeasure operations.

[0042] A 1.5GHz band monitoring module can be added to expand the signal detection range; at the same time, a more advanced super-resolution positioning algorithm is adopted to reduce the positioning error to ≤3m, which is suitable for military scenarios with extremely high positioning accuracy requirements.

[0043] The positioning module used in this embodiment is a GPS / BeiDou dual-mode positioning and an INS inertial navigation system. The GPS / BeiDou dual-mode positioning is a GPS and BeiDou dual-mode satellite positioning module with a positioning accuracy of ≤10m. The INS inertial navigation system has built-in sensors such as gyroscopes and accelerometers. When satellite signals are interfered with, it can automatically switch to INS navigation mode and calculate the position through inertial measurement data to improve the accuracy of position calculation and ensure the accuracy of the subsequent flight path of the UAV body 1 and the subsequently calculated flight path of the rotor unit 2. This ensures that the flight trajectories of the UAV body 1 and rotor unit 2 are controllable. When using the INS inertial navigation system, the continuous navigation time must be guaranteed to be ≥30 minutes to ensure sufficient time for subsequent navigation. Of course, a separate INS inertial navigation system can be used as the positioning module, combined with terrain matching navigation technology, which is suitable for complex environments where satellite signals are completely blocked (such as underground facilities and canyon areas) to ensure the continuity of positioning and navigation.

[0044] The main body of the drone 1 is equipped with a parachute recovery system. When the main body of the drone 1 malfunctions, runs out of power, or too many rotor units 2 separate, the parachute will be automatically activated to achieve safe recovery, reduce the risk of equipment loss, and is suitable for valuable equipment or long-range mission scenarios.

[0045] The directional warhead can be a shaped charge warhead with a charge weight of ≤50g. Its explosive power can accurately destroy the circuit modules and antenna systems of anti-drone devices while avoiding large-scale damage. The rotor unit 2 is equipped with a fuse that triggers the shaped charge warhead based on the ranging information from the ranging module. In this embodiment, a laser / millimeter-wave proximity fuse integrating both laser ranging and millimeter-wave radar detection methods is selected. The laser ranging accuracy is ≤0.1m, and the millimeter-wave radar can penetrate obstacles such as smoke and dust. The combination of the two can greatly improve the ranging accuracy, thereby improving the accuracy of the fuse triggering. It can be set that when the rotor unit 2 approaches the target (distance ≤5m), the fuse will automatically trigger the directional warhead to detonate. The shaped charge warhead can adopt a directional detonation design, releasing energy only in the direction of the target, thereby improving the strike efficiency.

[0046] Directed warheads can also be electromagnetic pulse payloads, which can paralyze the electronic systems of anti-drone devices by releasing electromagnetic pulse signals, achieving non-destructive strikes. This is suitable for scenarios where it is necessary to preserve physical evidence of anti-drone devices (such as security law enforcement).

[0047] The main body of the drone 1 is equipped with auxiliary equipment such as a visual sensor 6, an infrared remote sensing device, and a miniature camera 7.

[0048] The workflow of this rotary-wing UAV revolves around five core stages: "interference detection, location analysis, task allocation, separation and strike, and continuous mission." The entire process is automated and requires no human intervention. The specific steps are as follows: Interference detection: During the mission, the 360° radio frequency monitoring antenna array continuously scans the surrounding electromagnetic environment, collects signal data in real time and transmits it to the main computing module. The main computing module analyzes the collected signals through signal feature recognition algorithms to determine whether they are hostile interference (such as signal strength exceeding a preset threshold, frequency matching known anti-drone device interference frequency bands, or signals exhibiting malicious frequency hopping or suppression characteristics).

[0049] Link Disconnection: When the main computing module determines that it has encountered hostile interference, it immediately cuts off the non-essential data links between the UAV body 1 and the rotor unit 2 (non-critical status monitoring data links: such as the real-time temperature of the rotor unit 2, detailed statistics of the remaining battery power, and redundant data on fuselage vibration; redundant communication links: backup communication links other than the 2.4GHz / 5.8GHz dual-band core emergency channel, and unencrypted data transmission channels; non-mission-related auxiliary function links: such as real-time transmission of aerial images, non-essential equipment self-test data interaction, and secondary information synchronization channels with the ground control center, etc.), retaining only the core command transmission channel; at the same time, it activates the anti-interference communication mode of the UAV body 1 to ensure emergency communication with the ground control center and avoid the complete blockage of the entire link.

[0050] Interference source localization: The main computing module calls the interference source localization algorithm. Based on the phase difference and time difference of arrival of the interference signals collected by the four radio frequency antennas, and combined with the self-position information provided by GPS / BeiDou dual-mode positioning or INS navigation, the precise coordinates of the interference source (anti-drone device) are calculated through the triangulation principle. The positioning error is ≤5m. After the positioning is completed, the main computing module verifies the coordinate data, eliminates false signal interference, and ensures the accuracy of the positioning result.

[0051] Task allocation: The main computing module assigns an attack path to at least one separable rotor unit 2 based on the location and distance of the interference source and its own flight status. When multiple rotor units 2 are separated, a "multi-directional coordination" strategy is usually adopted, flying towards the target from different angles to improve the success rate of the attack. If too many rotor units 2 are separated (three or four), the subsequent task execution work of the UAV main body 1 will be cancelled, and the UAV main body 1 will automatically land. At the same time, if one or two rotor units 2 are separated, the subsequent task mode of the UAV main body 1 is set (such as continued reconnaissance, data transmission or return to home), and the relevant instructions are transmitted to the flight control systems of each rotor unit 2 and the UAV main body 1 respectively.

[0052] Separation execution: The main computing module issues a separation command, the electromagnetic lock 3 is de-energized, and the ejection device pushes the rotor unit 2 to separate from the UAV body 1; after separation, the independent flight control system of each rotor unit 2 starts autonomous flight mode according to the assigned path and flies towards the interference source; the UAV body 1 adjusts its flight altitude and route according to the preset command and continues to perform the predetermined mission or return to base.

[0053] Precision strike: During flight, rotor unit 2 corrects its trajectory in real time through an independent flight control system, and a laser / millimeter-wave proximity fuse continuously detects the distance to the target; when it approaches the target (distance ≤ 5m), the fuse triggers the directional warhead to detonate, accurately destroying the anti-drone device; after the strike, if rotor unit 2 still has remaining power, it can perform a simple reconnaissance mission according to preset instructions and then self-destruct, or return to a designated area (requires an additional recovery module, such as a parachute recovery system).

[0054] Follow-up actions: After the main body of the UAV 1 separates from the rotor unit 2, it continues to perform its mission (such as continuing to reconnoiter the target area and transmitting the collected data). If the mission is completed or a serious malfunction occurs, it will receive ground instructions through the anti-jamming communication link and return to the take-off and landing point autonomously.

[0055] Any adaptive changes made according to actual needs are within the scope of protection of this invention.

[0056] It should be noted that, for those skilled in the art, it is obvious that the present invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the present invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0057] Specific examples have been used to illustrate the principles and implementation methods of this invention. The descriptions of the above embodiments are only for the purpose of helping to understand the method and core ideas of this invention. Furthermore, those skilled in the art will recognize that, based on the ideas of this invention, there will be changes in the specific implementation methods and application scope. Therefore, the content of this specification should not be construed as a limitation of this invention.

Claims

1. A rotary-wing unmanned aerial vehicle, characterized in that, The device includes a main body of a drone and multiple rotor units with independent flight capabilities. The rotor units are detachably connected to the main body of the drone via electromagnetic latches and high-speed photoelectric interfaces. Radio frequency antennas are provided around the main body of the drone. A positioning module for measuring its own position information is provided inside the main body of the drone. A directional warhead for attacking anti-drone devices is provided on the rotor units.

2. The rotary-wing UAV according to claim 1, characterized in that, The rotor unit includes a motor, a propeller, an independent flight control system for flight control, and an auxiliary power supply for providing endurance. The motor is driven to the propeller.

3. The rotary-wing UAV according to claim 2, characterized in that, The rotor unit also includes a power management module for monitoring the power of the auxiliary power supply. The power management module is connected to the control system of the UAV body through the high-speed optoelectronic interface.

4. The rotary-wing UAV according to claim 1, characterized in that, A lateral limiting mechanism is provided between the rotor unit and the drone body. The lateral limiting mechanism includes a limiting groove and a limiting block. The limiting groove and the limiting block are respectively provided on the end faces of the rotor unit and the drone body that are detachably connected to each other. The limiting block is inserted into the limiting groove.

5. The rotary-wing UAV according to claim 4, characterized in that, A catapult device is provided between the rotor unit and the main body of the UAV to assist the rotor unit in detaching.

6. The rotary-wing UAV according to claim 5, characterized in that, The ejection device is a spring.

7. The rotary-wing UAV according to claim 1, characterized in that, The main body of the drone is equipped with a main power supply system, a main computing module, and a multi-band communication module.

8. The rotary-wing UAV according to claim 1, characterized in that, The positioning module is a GPS / BeiDou dual-mode positioning system and an INS inertial navigation system; or the positioning module is an INS inertial navigation system.

9. The rotary-wing UAV according to claim 1, characterized in that, The drone is equipped with a parachute recovery system.

10. The rotary-wing UAV according to claim 1, characterized in that, The directional warhead is a shaped charge warhead, and the rotor unit is equipped with a fuse that triggers the shaped charge warhead based on the ranging information from the ranging module; the directional warhead is an electromagnetic pulse payload.

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