Active defense device for unmanned aerial vehicle

Abstract

The invention relates to the technical field of unmanned aerial vehicle defense, in particular to an unmanned aerial vehicle active defense device. A base is installed on the upper surface of the damping support, a cylindrical sleeve is installed on the upper surface of the base, the upper end of the inner side face of the cylindrical sleeve is rotationally connected with a stepped main shaft through a bearing, a first motor is installed in the cylindrical sleeve, and an output shaft of the first motor is connected with the stepped main shaft through a first gear transmission mechanism. The unmanned aerial vehicle active defense device integrates an infrared wide-angle camera, a coaxial high-speed camera and a high-power infrared LED (light-emitting diode), so that the capability of detecting a'low, slow and small 'target is enhanced; especially under the condition of low illumination or complex weather, the recognition precision is greatly improved; a high-speed camera is combined to capture a target motion track in real time, and data support is provided for dynamic interception.

Description

Technical Field

[0001] The present application relates to the technical field of active defense of unmanned aerial vehicles (UAVs), and specifically to an active defense device for UAVs. Background Art

[0002] Drones, with their small size, low flight altitude, and high maneuverability ("low, slow, and small"), can penetrate traditional defense systems with swarming, saturation attacks, posing a lethal threat to vulnerable areas such as the top and sides of armored equipment. However, existing drone defense technologies suffer from bottlenecks such as poor adaptability, low efficiency, and high costs, necessitating the development of new active defense methods.

[0003] Traditional air defense systems (such as short-range air defense missiles and anti-aircraft guns) rely on radar detection and firepower coverage, with low recognition rates for "low, slow, and small" targets. Furthermore, system deployment is complex and mobility is poor, making it difficult to adapt to the rapid advance requirements of armored forces. Defense costs are also high. Another defense method is passive protection (such as wire mesh and armored roofs): these only partially cover the top of the turret, sacrificing equipment mobility and observation range, and are unable to withstand attacks from multiple angles. Manual defense (such as shotgun fire) relies on the operator's reaction speed, has a low kill rate in actual combat, exposes personnel to enemy fire, and poses an extremely high risk of casualties.

[0004] Directed energy weapons and microwave weapons require sustained high-power irradiation to damage drone circuits, consume significant energy, and significantly reduce their effectiveness against fast-moving targets. Laser weapons are limited by atmospheric attenuation and targeting accuracy, have limited effective range, require independent energy carriers, and are difficult to integrate into armored platforms.

[0005] Electronic countermeasures, electromagnetic suppression: by interfering with the drone's communication link to force it out of control, but new drones use fiber optic towed remote control or autonomous navigation technology to avoid electromagnetic interference, resulting in a higher probability of defense failure.

[0006] The existing defense system has three core flaws: lack of terminal defense capabilities: the traditional air defense system has an interception radius that is too large to deal with drones that penetrate within 100 meters of armored equipment; when facing drone cluster attacks, the existing system has limited firepower channels and a high interception response time, making it difficult to form an effective barrage. Summary of the Invention

[0007] This application provides an active defense device for drones, which realizes efficient and low-consumption terminal defense through the full-link technical innovation of "intelligent identification trajectory prediction and dynamic interception", and can effectively solve the problems in the background technology.

[0008] To achieve the above-mentioned purpose, the present application provides the following technical solutions: an active defense device for unmanned aerial vehicles, comprising a shock-absorbing bracket; a base is installed on the upper surface of the shock-absorbing bracket, a cylindrical sleeve is installed on the upper surface of the base, the upper end of the inner side surface of the cylindrical sleeve is rotatably connected to a stepped main shaft through a bearing, a motor 1 is installed inside the cylindrical sleeve, the output shaft of the motor 1 is connected to the stepped main shaft through a gear transmission mechanism 1, and a turntable is installed on the upper end of the cylindrical sleeve.

[0009] A turret bracket is installed in the middle of the upper surface of the turntable, and a strip-shaped through groove is provided on the upper surface of the turret bracket. The inner side of the strip-shaped through groove is rotatably connected to the hollow main shaft, and a launching tube is installed on the outer side of the hollow main shaft. An optical component cabin is provided on the outer side of the launching tube near the hollow main shaft, and an optical component is installed inside the optical component cabin. A coaxial high-speed camera is installed on the outer side of the optical component cabin. Motor 2 is installed inside the turret bracket, and motor 2 is rotatably connected to the hollow main shaft through gear transmission mechanism 2. Support frame 2 is installed on the left side of the turret bracket, and an electric-controlled telescopic rod 1 is installed on the upper surface of the support frame 2. A three-camera wide-angle photoelectric cabin is installed at the telescopic end of the electric-controlled telescopic rod 1. A liquid storage tank and a tray are also installed on the upper surface of the support frame 2, and a three-camera wide-angle photoelectric cabin cleaning mechanism is installed on the tray.

[0010] A support base 1 is installed on the right side of the turret bracket, an ammunition box is installed on the upper surface of the support base 1, a strip arrangement groove is installed on the lower end of the inner side of the ammunition box, the lower end surface of the strip arrangement groove is connected to the ammunition feed hole on the launch tube through the ammunition feed system, and a high-pressure gas tank connector is installed at the end of the launch tube.

[0011] Preferably, steel wire shock absorbers are installed on all four sides of the lower surface of the shock-absorbing bracket, and a mounting seat is installed on the lower end of the outer side surface of the steel wire shock absorber.

[0012] Preferably, a positioning groove is provided on the upper surface of the mounting seat, a hydraulic positioning rod is provided on the edge of the upper surface of the shock-absorbing bracket, the telescopic end of the hydraulic positioning rod is correspondingly arranged to be plugged into the positioning groove, and a conical opening is provided on the upper end of the inner side surface of the positioning groove.

[0013] Preferably, the output shaft of the motor 1 is installed with gear 1, and the lower end of the outer side surface of the stepped main shaft is installed with gear 2, and gear 2 is meshed with gear 1.

[0014] Preferably, the optical components include electrically heated glass, a high-power infrared LED, an infrared wide-angle camera, an infrared coaxial high-speed camera, and a coaxial high-speed camera.

[0015] Preferably, the output shaft of the motor 2 is installed with a gear 3, the outer side surface of the hollow main shaft is sleeved with a gear 4, and the gear 4 is meshed with the gear 3.

[0016] Preferably, the cleaning mechanism includes a water pump, an air pump and a T-shaped three-way pipe installed on the upper surface of the tray, and the tray is connected to a hollow annular air duct and a hollow annular flow guide pipe through a support rod arranged on its upper surface, and the outer side surfaces of the hollow annular air duct and the hollow annular flow guide pipe are provided with diversion holes facing the three-camera wide-angle optoelectronic cabin, and the T-shaped three-way pipe is assembled by a liquid inlet and two liquid outlets, and the two liquid outlets are both equipped with solenoid valves, one of the liquid outlets is arranged toward the strip groove on the upper surface of the turret bracket, and the other liquid outlet is connected to the hollow annular flow guide pipe through a conduit, and the liquid outlet of the water pump is connected to the liquid inlet of the T-shaped three-way pipe, and the liquid inlet of the water pump is connected to the liquid storage tank.

[0017] Preferably, a solenoid valve is installed on the high-pressure gas tank connector, and the high-pressure gas tank connector is connected to the gas outlet of the external high-pressure gas tank through a conduit.

[0018] Preferably, a plurality of through holes arranged in a strip shape are provided inside the strip-shaped arrangement groove, and an open tapered connecting section is provided at the upper end of the through hole.

[0019] Preferably, the ammunition feeding system includes an automatic loading mechanism and a magazine, and the automatic loading mechanism includes a strip-shaped seat, the upper surface of the strip-shaped seat is provided with a U-shaped groove, the U-shaped groove is arranged closely against the lower surface of the strip arrangement groove, the lower end of the inner side surface of the U-shaped groove is provided with a plurality of through grooves distributed at equal intervals, the inner side surface of the through groove is slidably connected with a baffle, the upper surface of the baffle is provided with an arc groove, the lower surfaces of the plurality of baffles are connected together by a lifting plate, the lower surface of the strip-shaped seat is connected to the upper surface of the lifting plate through an electrically controlled telescopic rod three, the upper end of the outer side surface of the strip-shaped seat is slidably connected with a strip baffle, the end of the strip baffle is connected to the upper end of the outer side surface of the strip-shaped seat through an electrically controlled telescopic rod two, the outer side surface of the strip-shaped seat is provided with an electrically controlled telescopic rod four, and the telescopic end of the electrically controlled telescopic rod four is installed with a push rod;

[0020] The magazine includes an L-shaped bracket installed inside the turret bracket, and the upper end of the outer side surface of the L-shaped bracket is rotatably connected to a cylindrical loader, and a stepping motor is installed at the lower end of the outer side surface of the L-shaped bracket. The output shaft of the stepping motor drives the cylindrical loader to rotate through a gear transmission mechanism, and a linear motor is installed at the upper end of the outer side surface of the L-shaped bracket. A push plate is installed on the slide of the linear motor. A plurality of cylindrical bullet grooves are evenly distributed in an inner ring of the cylindrical loader, and a strip-shaped bullet pushing groove is provided on the outer side surface of the cylindrical bullet groove. The push plate is slidably connected to the strip-shaped bullet pushing groove. A loading hole is provided on the outer side surface of the L-shaped bracket, and the loading hole is arranged close to the feed hole. When the cylindrical bullet groove rotates to the uppermost end, the cylindrical bullet groove is communicated with the loading hole, and the automatic loading mechanism is used to load steel balls into the cylindrical bullet groove.

[0021] Compared with the prior art, the present invention has the following advantages:

[0022] 1. The UAV active defense device of this application integrates an infrared wide-angle camera, a coaxial high-speed camera, and a high-power infrared LED to enhance the detection capability of "low, slow, and small" targets, especially in low light or complex weather conditions, significantly improving recognition accuracy;

[0023] 2. Combined with high-speed cameras to capture target motion trajectories in real time, intelligent algorithms are used to predict drone attack paths, providing data support for dynamic interception and resolving the issue of low recognition rates for low-altitude, slow-moving targets in traditional radar systems.

[0024] 3. This application uses a high-pressure gas tank to drive the steel ball launch, which has an extremely low cost per shot, a fast firing rate, and no recoil, and can form a dense barrage to deal with saturation attacks by drone clusters. The magazine and cylindrical loader cooperate with stepper motors and linear motors to achieve continuous ammunition supply, significantly improving firepower sustainability and breaking the bottleneck of limited firepower channels in traditional air defense systems.

[0025] 4. The dual-degree-of-freedom design of a stepped main axis (horizontal rotation) and a hollow main axis (pitch adjustment) allows the launch tube to rotate 360° horizontally and pitch at multiple angles, covering threats from all directions, including the top, sides, and rear of armored equipment, and compensating for the partial coverage defects of passive protection. The motor-driven turntable and turret bracket, combined with the electrically controlled telescopic rod to adjust the angle of the electro-optical cabin, achieve millisecond-level aiming, and the interception response time is far lower than that of manual operation or high-energy-consuming directed energy weapons.

[0026] 5. The shock-absorbing bracket and hydraulic positioning rod are compatible with a variety of armored platforms without the need for additional vehicles, solving the problems of poor mobility and complex deployment of traditional air defense systems. The three-camera wide-angle optoelectronic cabin cleaning mechanism automatically removes lens stains through a water pump, a guide tube and a solenoid valve, ensuring the reliability of optical components in harsh battlefield environments and avoiding the risks of manual maintenance. It relies on physical ammunition rather than continuous energy (such as laser and microwave weapons), and energy consumption is concentrated only on high-pressure gas tank inflation and motor drive. The overall energy consumption is low, making it suitable for field environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 This is a schematic diagram of the structure of this application;

[0028] Figure 2 This is the main view of this application;

[0029] Figure 3 This is the left view of this application;

[0030] Figure 4 This is the main view of this application;

[0031] Figure 5 This is the main view of the automatic loading mechanism;

[0032] Figure 6 It is a structural diagram of the automatic loading mechanism;

[0033] Figure 7 This is the main view of the magazine;

[0034] Figure 8 It is a structural diagram of the magazine;

[0035] Figure 9 This is the right side view of the magazine;

[0036] Figure 10 This is the left side view of the magazine;

[0037] Figure 11 Schematic diagram of the launch tube structure.

[0038] In the figure: 1 turret bracket, 2 water pump, 3 electric telescopic rod 1, 4 hollow annular gas guide tube, 5 three-camera wide-angle optoelectronic cabin, 6 hollow annular guide tube, 7 air pump, 8 optical component cabin, 9 launch tube, 10 ammunition box, 11 shock absorber bracket, 12 hydraulic positioning rod, 13 steel wire shock absorber, 14 support base 1, 15 cylindrical sleeve, 16 mounting base, 17 base, 18 turntable, 19 motor 1, 20 gear transmission mechanism 1, 21 positioning groove, 22 stepped main shaft, 23 support rod, 24 liquid storage tank, 25 support frame 2, 26 gear transmission mechanism 2, 27 motor 2, 28 T-shaped tee, 29 ammunition supply system, 291 strip baffle, 292 strip seat, 293 U-shaped slot, 294 electric telescopic rod 2, 295 electric telescopic rod 3, 296 lifting plate, 297 baffle, 298 electric telescopic rod 4, 299 push rod, 2910 ejection plate, 2911 linear motor, 2912 cylindrical loader, 2913 gear transmission mechanism 3, 2914 L-shaped bracket, 2915 stepper motor, 2916 cylindrical bullet slot, 2917 loading hole, 2918 strip bullet ejection slot, 30 strip arrangement slot, 31 optical component, 32 coaxial high-speed camera, 33 high-pressure gas tank connector, 34 feed hole, 35 hollow spindle, 36 tray. DETAILED DESCRIPTION

[0039] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of this application.

[0040] In the description of this application, if the direction description is involved, for example, the direction or position relationship indicated by "up", "down", "front", "back", "left", "right", etc. is based on the attached Figure 2The orientations or positional relationships shown are for the purpose of facilitating the description of this application and simplifying the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limiting this application. When a feature is referred to as being "disposed," "fixed," or "connected" to another feature, it may be directly disposed, fixed, or connected to the other feature or indirectly disposed, fixed, or connected to the other feature.

[0041] See also Figure 1-11 The present application provides the following technical solutions: an active defense device for a UAV, comprising a shock-absorbing bracket 11; a base 17 is installed on the upper surface of the shock-absorbing bracket 11, a cylindrical sleeve 15 is installed on the upper surface of the base 17, the upper end of the inner side surface of the cylindrical sleeve 15 is rotatably connected to a stepped main shaft 22 through a bearing, a motor 19 is installed inside the cylindrical sleeve 15, the output shaft of the motor 19 is connected to the stepped main shaft 22 through a gear transmission mechanism 20, and a turntable 18 is installed on the upper end of the cylindrical sleeve 15.

[0042] Specifically, the shock-absorbing bracket 11, the base 17, and the cylindrical sleeve 15 constitute a modular support platform. The motor 19 drives the gear transmission mechanism 20 to drive the stepped main shaft 22 to rotate horizontally, so that the turntable 18 can achieve 360° omnidirectional defense coverage, adapting to the rapid maneuvering requirements of armored vehicles while reducing the complexity of the mechanical structure.

[0043] A turret bracket 1 is installed in the middle of the upper surface of the turntable 18. The upper surface of the turret bracket 1 is provided with a strip-shaped through groove. The inner side of the strip-shaped through groove is rotatably connected to the hollow main shaft 35. The outer side of the hollow main shaft 35 is provided with a launching tube 9. The outer side of the launching tube 9 is provided with an optical component cabin 8 near the hollow main shaft 35. The optical component 31 is installed inside the optical component cabin 8. The outer side of the optical component cabin 8 is provided with a coaxial high-speed camera 32. A motor 27 is installed inside the turret bracket 1. The motor 27 is rotatably connected to the hollow main shaft 35 through a gear transmission mechanism 26. A support frame 25 is installed on the left side of the turret bracket 1. An electric-controlled telescopic rod 1 3 is installed on the upper surface of the support frame 25. The telescopic end of the electric-controlled telescopic rod 3 is installed with a three-camera wide-angle photoelectric cabin 5. A liquid storage tank 24 and a tray 36 are also installed on the upper surface of the support frame 25. A cleaning mechanism for the three-camera wide-angle photoelectric cabin 5 is installed on the tray 36.

[0044] Specifically, the turret bracket 1 is connected to the launch tube 9 through the hollow main shaft 35, and is combined with the motor 27 to drive the gear transmission mechanism 26 to adjust the pitch angle, thereby achieving precise strikes on targets at multiple heights; the optical component cabin 8 integrates the optical component 31 (electrically heated glass, infrared LED, etc.) and the coaxial high-speed camera 32 to support all-weather target tracking; the electric-controlled telescopic rod 1 3 dynamically adjusts the monitoring angle of the three-camera wide-angle optoelectronic cabin 5, and cooperates with the liquid storage tank 24 and the cleaning mechanism (tray 36) to ensure the long-term reliability of the optical system.

[0045] A support base 14 is installed on the right side of the turret bracket 1, and an ammunition box 10 is installed on the upper surface of the support base 14. A strip arrangement groove 30 is installed at the lower end of the inner side of the ammunition box 10. The lower end surface of the strip arrangement groove 30 is connected to the ammunition feeding hole 34 on the launch tube 9 through the ammunition feeding system 29, and a high-pressure gas tank connector 33 is installed at the end of the launch tube 9.

[0046] Specifically, the strip-shaped arrangement groove 30 is used to arrange the projectiles so that the projectiles can be queued and enter the projectile feeding system 29 in sequence.

[0047] Furthermore, steel wire shock absorbers 13 are installed around the lower surface of the shock absorbing bracket 11 , and a mounting seat 16 is installed at the lower end of the outer side surface of the steel wire shock absorber 13 .

[0048] Specifically, the provision of the steel wire shock absorber 13 increases the overall stability of the device when the device moves with the vehicle.

[0049] Furthermore, a positioning groove 21 is provided on the upper surface of the mounting seat 16, and a hydraulic positioning rod 12 is provided on the upper surface edge of the shock-absorbing bracket 11. The telescopic end of the hydraulic positioning rod 12 is plugged into and corresponding to the positioning groove 21, and a conical opening is provided on the upper end of the inner side surface of the positioning groove 21.

[0050] Specifically, when a projectile is launched, the hydraulic positioning rod 12 is extended and inserted into the positioning groove 21. At this time, the flexible contact of the wire shock absorber 13 fails, which can effectively reduce the up and down shaking of the defense device caused by the recoil force when the projectile is launched.

[0051] Furthermore, the output shaft of the motor 19 is installed with gear 1, and the lower end of the outer side surface of the stepped main shaft 22 is installed with gear 2, and gear 2 is engaged with gear 1.

[0052] Furthermore, the optical component 31 includes electrically heated glass, a high-power infrared LED, an infrared wide-angle camera, an infrared coaxial high-speed camera, and a coaxial high-speed camera.

[0053] Specifically, the optical component 31 integrates a high-power infrared LED, an infrared wide-angle camera and electrically heated glass, breaking through the limitations of optical detection in complex environments such as rain, fog, and dust, and achieving a high target recognition rate.

[0054] Furthermore, the output shaft of the second motor 27 is installed with a gear three, and the outer side surface of the hollow main shaft 35 is sleeved with a gear four, and the gear four is engaged with the gear three.

[0055] Furthermore, the cleaning mechanism includes a water pump 2, an air pump 7 and a T-shaped three-way pipe 28 installed on the upper surface of the tray 36. The tray 36 is connected to a hollow annular air guide pipe 4 and a hollow annular flow guide pipe 6 through a support rod 23 arranged on its upper surface. The outer sides of the hollow annular air guide pipe 4 and the hollow annular flow guide pipe 6 are provided with diversion holes facing the three-camera wide-angle optoelectronic cabin 5. The T-shaped three-way pipe 28 is assembled by a liquid inlet and two liquid outlets. Both liquid outlets are equipped with solenoid valves, one of which is arranged toward the strip groove on the upper surface of the turret bracket 1, and the other liquid outlet is connected to the hollow annular flow guide pipe 6 through a conduit. The liquid outlet of the water pump 2 is connected to the liquid inlet of the T-shaped three-way pipe 28, and the liquid inlet of the water pump 2 is connected to the liquid storage tank 24.

[0056] Specifically, the water pump 2 transports the cleaning liquid to the hollow annular guide tube 6 through the T-shaped three-way pipe 28 to clean the lens of the three-camera wide-angle optoelectronic cabin 5; the air pump 7 drives the hollow annular air guide tube 4 to quickly dry the surface of the cleaned lens, ensuring the reliability of the optical system in harsh battlefield environments.

[0057] Furthermore, a solenoid valve is installed on the high-pressure gas tank connector 33, and the high-pressure gas tank connector 33 is connected to the gas outlet of the external high-pressure gas tank through a conduit.

[0058] Furthermore, a plurality of through holes arranged in a strip shape are provided inside the strip-shaped arrangement groove 30 , and an open tapered connecting section is provided at the upper end of the through hole.

[0059] Furthermore, the ammunition feeding system 29 includes an automatic loading mechanism and a magazine. The automatic loading mechanism includes a strip-shaped seat 292. The upper surface of the strip-shaped seat 292 is provided with a U-shaped groove 293. The U-shaped groove 293 is arranged close to the lower surface of the strip arrangement groove 30. The lower end of the inner side surface of the U-shaped groove 293 is provided with a plurality of equally distributed through grooves. The inner side surface of the through groove is slidably connected to a baffle 297. The upper surface of the baffle 297 is provided with an arc groove. The lower surfaces of the plurality of baffles 297 are lifted by The lowering plate 296 is connected together, the lower surface of the strip-shaped seat 292 is connected to the upper surface of the lifting plate 296 through the electric-controlled telescopic rod three 295, the upper end of the outer surface of the strip-shaped seat 292 is slidably connected with a strip baffle 291, and the end of the strip baffle 291 is connected to the upper end of the outer surface of the strip-shaped seat 292 through the electric-controlled telescopic rod two 294. The outer side surface of the strip-shaped seat 292 is provided with an electric-controlled telescopic rod four 298, and the telescopic end of the electric-controlled telescopic rod four 298 is installed with a push rod 299.

[0060] The magazine includes an L-shaped bracket 2914 installed inside the turret bracket 1, the upper end of the outer side surface of the L-shaped bracket 2914 is rotatably connected to the cylindrical loader 2912, the lower end of the outer side surface of the L-shaped bracket 2914 is installed with a stepper motor 2915, the output shaft of the stepper motor 2915 drives the cylindrical loader 2912 to rotate through the gear transmission mechanism 2913, the upper end of the outer side surface of the L-shaped bracket 2914 is installed with a linear motor 2911, and the slide of the linear motor 2911 is installed with a push plate 2910. The inner ring of the L-shaped loader 2912 is evenly distributed with multiple cylindrical bullet grooves 2916, and the outer side of the cylindrical bullet groove 2916 is provided with a strip-shaped bullet pushing groove 2918. The bullet pushing plate 2910 is slidably connected to the strip-shaped bullet pushing groove 2918. The outer side of the L-shaped bracket 2914 is provided with a loading hole 2917, and the loading hole 2917 is arranged close to the feeding hole 34. When the cylindrical bullet groove 2916 rotates to the uppermost end, the cylindrical bullet groove 2916 is connected to the loading hole 2917, and the automatic loading mechanism is used to load steel balls into the cylindrical bullet groove 2916.

[0061] Specifically, the baffle 297 cooperates with the electric-controlled telescopic rod three 295 to sort the steel balls through the lifting plate 296, and the push rod 299 is accurately pushed to the magazine by the electric-controlled telescopic rod four 298, so the loading efficiency is high; the cylindrical loader 2912 is driven to rotate by the stepper motor 2915, and the pushing plate 2910 pushes the steel balls into the loading hole 2917 through the linear motor 2911 to realize fully automatic feeding.

[0062] 1. Installation and Deployment

[0063] 1. Basic installation

[0064] Platform fixing: Fix the mounting base 16 to the top of the armored equipment or the modular interface of the mechanical dog carrier with bolts, ensuring that the mounting surface is level and the load-bearing capacity meets the standards.

[0065] Calibration of the shock absorption system: Align the hydraulic positioning rod 12 with the conical opening of the positioning groove 21, adjust the compression amount of the steel wire shock absorber 13 to the preset value, and activate the hydraulic system to lock the shock absorption bracket 11 during firing.

[0066] Fire control computer integration: A fire control computer is installed in the crew compartment and connected to the main control module in the turret bracket 1 through a shielded cable to ensure electromagnetic compatibility.

[0067] 2. Energy and ammunition configuration

[0068] Gas tank inflation system: Connect the external high-pressure gas tank to the air pump, which is integrated into the gas tank bracket and supports automatic pressure replenishment.

[0069] Ammunition loading: Fill the strip arrangement slots 30 of the ammunition box 10 with 6mm spherical steel ball projectiles, with a single capacity of ≥500 rounds, and ensure that the ammunition feeding system 29 is aligned with the ammunition feeding hole 34 of the launch tube 9.

[0070] 2. System startup and calibration

[0071] 1. Hardware initialization

[0072] Power on: When the main power is turned on, the fire control computer automatically loads the operating system and starts the self-test program.

[0073] Multispectral sensor calibration:

[0074] Coaxial dual cameras: Synchronously calibrate the infrared high-speed camera and visible light high-speed camera in the optical component compartment 8, and compensate for low-light environments through the built-in infrared light source.

[0075] Triple-camera wide-angle optoelectronic cabin 5: Activates the wide-angle infrared lens to scan the battlefield, and the infrared light source actively illuminates to generate an environmental heat map.

[0076] 2. Algorithm loading and optimization

[0077] Multi-target recognition model: loads the improved YOLOV10 algorithm, integrates the human recognition model (based on the COCO dataset), and prioritizes human targets.

[0078] The specific steps of the improved YOLOv10 algorithm are as follows:

[0079] 2.1. Data Preparation and Enhancement

[0080] Dataset construction:

[0081] The COCO dataset (containing 80 categories of objects, including humans) is integrated with a drone-specific dataset (labeled with the "drone" category) to ensure that the data covers a variety of scenarios (daytime, nighttime, foggy, etc.).

[0082] Enhance drone data: add motion blur, low-light simulation, and infrared thermal imaging data (for multispectral training).

[0083] Label adjustments:

[0084] A new "human body" category is added to the annotation file, alongside "drone", to support multi-target detection tasks.

[0085] 2.2. Model architecture improvement Backbone network optimization:

[0086] Use a lightweight YOLOv10 backbone (such as CSPDarknet-Lite) to reduce the number of parameters (from 30M to 15M) and improve inference speed (frame rate ≥ 60fps).

[0087] Cross-stage partial connection (CSP) and attention mechanism (CBAM module) are introduced to enhance the ability to distinguish targets in complex backgrounds.

[0088] Multi-tasking head design:

[0089] Separate detection head:

[0090] Head1: Detect drones (output bounding box, confidence, category).

[0091] Head2: Recognize human bodies (independent confidence branch to avoid category interference).

[0092] Shared feature maps: Fusing shallow details with high-level semantic information through feature pyramid networks (FPN).

[0093] 2.3. Loss Function Design

[0094] Joint loss function:

[0095] Drone detection loss: CIoULoss (Complete Intersection over Union) is used to optimize bounding box regression.

[0096] Human Recognition Loss: Use FocalLoss to alleviate category imbalance and focus on difficult samples (such as occluded human bodies).

[0097] Confidence weighting: The confidence of drone targets is given a higher weight (λ=0.7), and the weight of human targets is λ=0.3.

[0098] 2.4. Training strategy Two-stage training:

[0099] Phase 1: Freeze the backbone network and train only the detection head, initialized with COCO pre-trained weights (learning rate 1e-4).

[0100] Phase 2: Unfreeze all networks and jointly optimize the drone and human detection tasks (learning rate 1e-5, cosine annealing scheduling).

[0101] Adversarial Training:

[0102] Add adversarial examples (such as infrared jamming and optical camouflage drones) to improve model robustness.

[0103] 2.5. Optimization of the Inference Phase

[0104] Dynamic confidence threshold:

[0105] Drone detection: The confidence threshold is set to 0.5 (balancing recall and false alarm rate).

[0106] Human recognition: The confidence threshold is set to 0.95 (only high-confidence human targets are retained).

[0107] Target filtering logic**:

[0108] If a drone and a human body are detected in the same area at the same time, the human target will be excluded first (triggering the safety protocol).

[0109] Post-processing enhancements:

[0110] Improved NMS (Non-Maximum Suppression): Soft-NMS is used for drone targets to reduce missed detection of dense targets; hard NMS (IoU threshold 0.7) is used for human targets.

[0111] 2.6. Algorithm Integration and Security Assurance

[0112] Fire control system linkage:

[0113] When a human target is detected (confidence level ≥ 0.95), the fire control computer immediately locks the launch tube (9), prohibits the projectile from being launched, and prompts "Human body avoidance" through the HUD.

[0114] Real-time logging: Saves detection results and interception decisions, supporting post-event review and algorithm optimization.

[0115] Edge computing optimization:

[0116] Deploy a lightweight inference engine (TensorRT or ONNX Runtime) to support real-time operation on a fire control computer (NPU computing power ≥ 4TOPS).

[0117] 2.7. Verification and Testing

[0118] Performance indicators:

[0119] Drone detection: mAP@0.5 (average precision) ≥ 98%, recall ≥ 95%.

[0120] Human body recognition: false detection rate <0.1%, missed detection rate <1%.

[0121] Extreme scenario testing:

[0122] Night mode: Relying on infrared cameras and active light sources, the verification detection distance is ≥ 200m.

[0123] Smoke interference: Generative adversarial networks (GANs) are used to simulate smoke environments and test the robustness of the algorithm.

[0124] 2.8. Continuous Iteration and Deployment

[0125] Online Learning:

[0126] Deploy an incremental learning framework, receive real-time battlefield data (after desensitization), and dynamically update model parameters.

[0127] Modular upgrade:

[0128] Supports updating algorithm models via OTA (over-the-air download) and is compatible with new drone variants (such as folding-wing and swarm drones).

[0129] Through the above steps, the improved YOLOv10 algorithm not only achieves efficient detection and interception of drones, but also ensures the reliability and ethics of the system in complex battlefield environments through strict human recognition and safety mechanisms.

[0130] Fire control calculation logic: The fire control computer receives the target direction (polar coordinate format) output by the wide-angle lens in real time, combines it with the IMU data to calculate the barrel rotation angle, with an error compensation of <0.1°.

[0131] 3. Servo mechanism joint debugging

[0132] Dual-axis drive test: Motor 1 19 drives the turntable 18 to rotate horizontally 360°, and motor 2 27 controls the pitch adjustment of the launch tube 9, eliminating the return gap through the gear transmission mechanism.

[0133] Modular docking: When combined with a robotic dog, the quick-release interface completes the mechanical / electrical connection and synchronizes the vehicle's navigation data.

[0134] 3. Target Detection and Interception Operations

[0135] 1. Wide-area search and coarse locking

[0136] Wide-angle lens detection: The three-camera wide-angle optoelectronic cabin 5 scans the airspace in real time, and the infrared wide-angle lens identifies "low, slow and small" targets, and outputs the target direction, speed and cluster density to the fire control computer.

[0137] Threat prioritization: The algorithm automatically generates an intercept sequence based on target distance (near → far), speed (fast → slow), and cluster size (large → small), and displays it through the HUD interface.

[0138] 2. Accurate tracking and trajectory calculation

[0139] Coaxial camera lock: The turntable 18 drives the launch tube 9 to turn towards the target direction, and the coaxial dual camera switches to the narrow field of view mode, and the target trajectory is predicted by the spatiotemporal context algorithm (STCKF).

[0140] Dynamic barrage generation: The fire control computer calculates the projectile dispersion parameters and combines them with the target motion vector to generate a three-dimensional interception barrage.

[0141] 3. Ammunition firing and charging

[0142] High-pressure gas tank linkage: the solenoid valve responds to the fire control command, releases compressed gas to drive the projectile, and the inflation pump automatically replenishes the pressure according to the feedback from the pressure sensor.

[0143] Multi-target interception: For cluster targets, the ammunition supply system 29 loads projectiles in order of priority, and the automatic loading mechanism (magazine) supports continuous feeding.

[0144] IV. Maintenance and Security

[0145] 1. Optical system maintenance

[0146] Dual-mode cleaning process:

[0147] Liquid-gas mixed cleaning: The water pump 2 draws the cleaning liquid, which is diverted to the hollow annular guide pipe 6 through the T-shaped three-way pipe 28 and sprayed to cover the wide-angle lens and the coaxial camera;

[0148] Pneumatic drying: The air pump 7 starts the high-pressure air flow to blow away the residual liquid to prevent the lens from fogging.

[0149] 2. Gas tank and ammunition management

[0150] Air pump maintenance: Check the air pump seal and filter element every month to prevent oil from contaminating the air path.

[0151] Projectile Compatibility: Supports 6mm / 8mm projectile switching. When changing magazines, the spacing of the strip arrangement slots 30 of the feed system 29 must be adjusted synchronously.

[0152] 3. Human body recognition verification

[0153] Algorithm reliability testing: Perform human model simulated attacks daily (wearing thermal imaging camouflage clothing) to verify that the system false trigger rate is less than 0.1%.

[0154] 5. Extended Application: Individual Air Defense Mode

[0155] 1. Robot dog collaborative deployment

[0156] Modular disassembly: Remove the quick-release interface and combine the defense device with the mechanical dog carrier, with a total weight of ≤50kg, supporting field mobility.

[0157] 2. Low power algorithm optimization

[0158] Edge computing: The fire control computer has a built-in NPU unit that runs a lightweight human avoidance algorithm.

[0159] VI. Safety and Ethical Standards

[0160] Human body avoidance forced logic: When the algorithm recognizes the human body outline (skeletal key points ≥ 15), it immediately terminates the shooting command and triggers the sound and light alarm.

[0161] Identification of Friend or Foe: Supports the implantation of friendly beacons to avoid accidental damage to one's own drones.

[0162] 7. Quick disassembly and transportation

[0163] Mechanical dog separation: The electrical / mechanical interface is separated within 30 seconds, and the device can be independently loaded into a standard transport box.

[0164] Safe pressure relief of gas tank: Start the air pump pressure relief program before disassembly to avoid gas shock during disassembly.

[0165] Through the above upgrades, the device can adapt to the needs of multiple scenarios, from armored platforms to individual air defense, realize the full-link intelligence of "detection, control, attack and evaluation", and significantly improve the terminal defense effectiveness against drone swarms.

[0166] When in use: first fix the mounting base 16 on the vehicle so that the device can move with the vehicle. When the device moves with the vehicle, the hydraulic positioning rod 12 contracts and the steel wire shock absorber 13 works to protect the equipment installed on the surface of the turret bracket 11.

[0167] After starting the equipment, the hydraulic positioning rod 12 is first extended to insert its telescopic end into the interior of the positioning slot 12. At this time, the steel wire shock absorber 13 is in an overhead state. Then the electric telescopic rod 13 is extended to push out the three-camera wide-angle photoelectric cabin 5. The photoelectric equipment installed inside the three-camera wide-angle photoelectric cabin 5 detects the environment of the surrounding airspace. When the drone approaches, the photoelectric equipment inside the three-camera wide-angle photoelectric cabin 5 sends the drone's information to the external controller, and the controller controls the launch tube 9 to turn and aim at the drone.

[0168] When the launch tube 9 turns, the motor 19 drives the turntable 18 to rotate through the gear transmission mechanism 1 20, thereby realizing a 360-degree rotation of the launch tube 9 in the horizontal plane. Then, the motor 2 27 drives the hollow main shaft 35 to rotate through the gear transmission mechanism 2 26, thereby realizing the pitch adjustment of the launch tube 9 in the vertical plane.

[0169] When the optical component 31 and the coaxial high-speed camera 32 that follow the launch tube 9 lock the drone, the projectile launch device can be started.

[0170] When firing projectiles, first the round projectiles in the ammunition box 10 are arranged through the strip arrangement groove 30, and the projectile at the bottom of the strip arrangement groove 30 falls into the inside of the U-shaped groove 293, and the projectiles are linearly arranged inside the U-shaped groove 293. Then the electric-controlled telescopic rod three 295 is extended to remove the baffle 297 between adjacent projectiles, and the electric-controlled telescopic rod four 298 is contracted to send the projectiles in the U-shaped groove 293 into the cylindrical bullet groove 2916. Then the stepping motor 2915 drives the cylindrical loader 2912 to rotate through the gear transmission mechanism three 2913 until all the cylindrical bullet grooves 2916 on the cylindrical loader 2912 are filled.

[0171] After the cylindrical bullet groove 2916 is full, the projectile in the cylindrical bullet groove 2916 at the upper end begins to be fired. At this time, the linear motor 2911 drives the pushing plate 2910 to move along the cylindrical bullet groove 2916. The pushing plate 2910 pushes the projectiles inside the cylindrical bullet groove 2916 one by one through the loading hole 2917 into the feeding hole 34. The projectiles enter the launch tube 9 through the feeding hole 34. The pulse solenoid valve located at the bottom of the launch tube 9 and connected to the high-pressure gas cylinder is in the open state at this time, and the high-pressure gas pushes the projectile in the launch tube 9 to be fired quickly.

[0172] The entire feeding system 29 is tilted toward the launch tube 9 to prevent the projectiles in the cylindrical bullet groove 2916 from escaping.

[0173] When cleaning the triple-camera wide-angle optoelectronic chamber 5, optical assembly 31, and coaxial high-speed camera 32 is required, water pump 2 pumps the cleaning fluid from the reservoir 24 into the T-shaped tee 28. The cleaning fluid diverted from the T-shaped tee 28 is used to clean the exterior surfaces of the triple-camera wide-angle optoelectronic chamber 5, optical assembly 31, and coaxial high-speed camera 32. To clean the optical assembly 31 and coaxial high-speed camera 32, motor 2 27 rotates the optical assembly 31 and coaxial high-speed camera 32 to the liquid outlet of the T-shaped tee 28.

[0174] It is worth noting that the input ends of the water pump 1, the electric telescopic rod 1 3, the three-camera wide-angle photoelectric cabin 5, the air pump 7, the optical component cabin 8, the motor 1 19, the motor 2 27, the electric telescopic rod 2 294, the electric telescopic rod 3 295, the electric telescopic rod 4 298, the linear motor 2911, the stepper motor 2915, the optical component 31 and the coaxial high-speed camera 32 are all electrically connected to the output end of the external power supply through the external controller, and the external controller controls the operation of the water pump 1, the electric telescopic rod 1 3, the three-camera wide-angle photoelectric cabin 5, the air pump 7, the optical component cabin 8, the motor 1 19, the motor 2 27, the electric telescopic rod 2 294, the electric telescopic rod 3 295, the electric telescopic rod 4 298, the linear motor 2911, the stepper motor 2915, the optical component 31 and the coaxial high-speed camera 32 using methods commonly used in the prior art.

[0175] Although the embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations may be made to these embodiments without departing from the principles and spirit of the present application, and the scope of the present application is defined by the appended claims and their equivalents.

Claims

1. An active defense device for drones, characterized by: The invention comprises a shock-absorbing bracket (11); a base (17) is installed on the upper surface of the shock-absorbing bracket (11); a cylindrical sleeve (15) is installed on the upper surface of the base (17); the upper end of the inner side surface of the cylindrical sleeve (15) is rotatably connected to a stepped main shaft (22) through a bearing; a motor (19) is installed inside the cylindrical sleeve (15); the output shaft of the motor (19) is connected to the stepped main shaft (22) through a gear transmission mechanism (20); and a turntable (18) is installed on the upper end of the cylindrical sleeve (15); A turret bracket (1) is installed in the middle of the upper surface of the turntable (18), and a strip-shaped through groove is provided on the upper surface of the turret bracket (1). The inner side of the strip-shaped through groove is rotatably connected to a hollow main shaft (35), and a launch tube (9) is installed on the outer side of the hollow main shaft (35). An optical component cabin (8) is provided on the outer side of the launch tube (9) near the hollow main shaft (35), and an optical component cabin (31) is installed inside the optical component cabin (8). A coaxial high-speed camera (32) is installed on the outer side of the optical component cabin (8). The second motor (27) is installed on the upper surface of the turret bracket (1), and the second motor (27) is rotatably connected to the hollow main shaft (35) through the second gear transmission mechanism (26). The left side of the turret bracket (1) is installed with a support frame (25), and the upper surface of the support frame (25) is installed with an electric control telescopic rod (3), and the telescopic end of the electric control telescopic rod (3) is installed with a three-camera wide-angle photoelectric cabin (5). The upper surface of the support frame (25) is also installed with a liquid storage tank (24) and a tray (36), and the tray (36) is installed with a three-camera wide-angle photoelectric cabin (5) cleaning mechanism; A support seat 1 (14) is installed on the right side of the turret bracket (1), an ammunition box (10) is installed on the upper surface of the support seat 1 (14), a strip arrangement groove (30) is installed on the lower end of the inner side of the ammunition box (10), the lower end surface of the strip arrangement groove (30) is connected to the ammunition feeding hole (34) on the launch tube (9) through the ammunition feeding system (29), and a high-pressure gas tank connector (33) is installed at the end of the launch tube (9).

2. The active defense device for a drone according to claim 1, characterized in that: Steel wire shock absorbers (13) are installed around the lower surface of the shock-absorbing bracket (11), and a mounting seat (16) is installed at the lower end of the outer side surface of the steel wire shock absorber (13).

3. The active defense device for a drone according to claim 2, characterized in that: A positioning groove (21) is provided on the upper surface of the mounting seat (16), and a hydraulic positioning rod (12) is provided on the edge of the upper surface of the shock-absorbing bracket (11). The telescopic end of the hydraulic positioning rod (12) is plugged into and corresponding to the positioning groove (21), and a conical opening is provided on the upper end of the inner side surface of the positioning groove (21).

4. The active defense device for a drone according to claim 1, characterized in that: The output shaft of the motor 1 (19) is equipped with a gear 1, and the lower end of the outer side surface of the stepped main shaft (22) is equipped with a gear 2, which is meshed with the gear 1.

5. The active defense device for a UAV according to claim 1, characterized in that: The optical component (31) includes electrically heated glass, a high-power infrared LED, an infrared wide-angle camera, an infrared coaxial high-speed camera, and a coaxial high-speed camera.

6. The active defense device for a UAV according to claim 1, characterized in that: The output shaft of the motor 2 (27) is mounted with a gear 3, and the outer side surface of the hollow main shaft (35) is sleeved with a gear 4, which is meshed with the gear 3.

7. The active defense device for a UAV according to claim 1, characterized in that: The cleaning mechanism includes a water pump (2), an air pump (7) and a T-shaped three-way pipe (28) installed on the upper surface of the tray (36). The tray (36) is connected to a hollow annular air guide pipe (4) and a hollow annular flow guide pipe (6) through a support rod (23) arranged on its upper surface. The outer side surfaces of the hollow annular air guide pipe (4) and the hollow annular flow guide pipe (6) are both provided with flow guide holes facing the three-camera wide-angle photoelectric cabin (5). The T-shaped three-way pipe (28) is assembled by a liquid inlet and two liquid outlets. Both liquid outlets are equipped with solenoid valves, one of which is arranged toward the strip groove on the upper surface of the turret bracket (1), and the other liquid outlet is connected to the hollow annular flow guide pipe (6) through a conduit. The liquid outlet of the water pump (2) is connected to the liquid inlet of the T-shaped three-way pipe (28), and the liquid inlet of the water pump (2) is connected to the liquid storage tank (24).

8. The active defense device for a drone according to claim 1, characterized in that: A solenoid valve is installed on the high-pressure gas tank connector (33), and the high-pressure gas tank connector (33) is connected to the gas outlet of an external high-pressure gas tank through a conduit.

9. The active defense device for a UAV according to claim 1, characterized in that: A plurality of through holes arranged in a strip shape are provided inside the strip-shaped arrangement groove (30), and an open tapered connecting section is provided at the upper end of the through hole.

10. The active defense device for a UAV according to claim 1, characterized in that: The feeding system (29) includes an automatic loading mechanism and a magazine. The automatic loading mechanism includes a strip-shaped seat (292). The upper surface of the strip-shaped seat (292) is provided with a U-shaped groove (293). The U-shaped groove (293) is arranged close to the lower surface of the strip-shaped arrangement groove (30). The lower end of the inner side surface of the U-shaped groove (293) is provided with a plurality of through grooves distributed at equal intervals. The inner side surface of the through groove is slidably connected to a baffle (297). The upper surface of the baffle (297) is provided with an arc groove. The lower surfaces of the plurality of baffles (297) are connected by a lifting plate (296). ) are connected together, the lower surface of the strip-shaped seat (292) is connected to the upper surface of the lifting plate (296) through the electric-controlled telescopic rod three (295), the upper end of the outer surface of the strip-shaped seat (292) is slidably connected with a strip-shaped baffle (291), the end of the strip-shaped baffle (291) is connected to the upper end of the outer surface of the strip-shaped seat (292) through the electric-controlled telescopic rod two (294), the outer side surface of the strip-shaped seat (292) is provided with an electric-controlled telescopic rod four (298), and the telescopic end of the electric-controlled telescopic rod four (298) is installed with a push rod (299); The magazine comprises an L-shaped bracket (2914) mounted inside the turret bracket (1), the upper end of the outer side surface of the L-shaped bracket (2914) is rotatably connected to a cylindrical loader (2912), a stepper motor (2915) is mounted on the lower end of the outer side surface of the L-shaped bracket (2914), the output shaft of the stepper motor (2915) drives the cylindrical loader (2912) to rotate through a gear transmission mechanism (2913), a linear motor (2911) is mounted on the upper end of the outer side surface of the L-shaped bracket (2914), a push plate (2910) is mounted on the slide of the linear motor (2911), and the cylindrical The inner ring of the loader (2912) is evenly distributed with a plurality of cylindrical bullet grooves (2916), the outer side of the cylindrical bullet groove (2916) is provided with a strip-shaped bullet pushing groove (2918), the bullet pushing plate (2910) is slidably connected to the strip-shaped bullet pushing groove (2918), the outer side of the L-shaped bracket (2914) is provided with a bullet loading hole (2917), the bullet loading hole (2917) is arranged close to the bullet feeding hole (34), when the cylindrical bullet groove (2916) rotates to the uppermost end, the cylindrical bullet groove (2916) and the bullet loading hole (2917) are communicated, and the automatic loading mechanism is used to load steel balls into the cylindrical bullet groove (2916).

Images