Optical fiber transmission low-light camera shooting infrared light supplementing unmanned aerial vehicle and use method

Abstract

The invention relates to the technical field of unmanned aerial vehicles, and discloses an optical fiber transmission low-light camera shooting infrared light supplementing unmanned aerial vehicle and a use method. The invention discloses an optical fiber transmission low-light camera shooting infrared light supplementing unmanned aerial vehicle and a using method. Four rising and falling supporting mechanisms used for assisting an unmanned aerial vehicle body structure in rising and falling are annularly arranged on the outer side of the unmanned aerial vehicle body structure. According to the optical fiber transmission low-light-level camera shooting infrared light supplementing unmanned aerial vehicle and the using method, the lower end of a vehicle body structure of the unmanned aerial vehicle is provided with a butt joint assembly used for stably installing four rising and falling supporting mechanisms, and the optical fiber transmission low-light-level camera shooting infrared light supplementing unmanned aerial vehicle integrates the self-adaptive rising and falling supporting mechanisms and a multi-dimensional scanning view finding mechanism; the problem that a traditional unmanned aerial vehicle inclines and is unstable in posture when taking off and landing on a complex terrain is effectively solved, high-definition data return is achieved through the optical fiber transmission technology, and the all-weather operation capacity is ensured by combining infrared light supplementing and low-light camera shooting.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, specifically to a fiber optic transmission low-light imaging infrared supplementary lighting UAV and its usage method. Background Technology

[0002] Fiber optic transmission low-light camera infrared supplemental lighting drone is a special type of drone connected to a ground station via fiber optic cables. The fiber optic cable simultaneously handles power transmission and high-speed data transmission, giving it theoretically unlimited endurance and enabling real-time, zero-latency transmission of 4K or even 8K ultra-high-definition video, while being completely immune to electromagnetic interference. This drone is equipped with a camera module integrating low-light and infrared supplemental lighting functions, enabling clear imaging in pitch-black environments. Infrared supplemental lighting technology can extend night vision distance to over 300 meters. Combined with thermal imaging and laser ranging, it possesses all-weather, all-time precise reconnaissance and monitoring capabilities. With its core advantages such as anti-interference, long endurance, and high-definition transmission, this type of drone is widely used in high-requirement scenarios such as military reconnaissance, border patrol, critical infrastructure inspection, and emergency communication relay.

[0003] However, the landing gear structure of traditional UAVs in existing technologies is relatively fixed and lacks adaptive adjustment capabilities. When taking off and landing in complex terrains such as mountains and gravel slopes, the fuselage is prone to severe tilting or lateral tilting due to uneven ground, resulting in serious instability of the aircraft's attitude. This instability directly interferes with the aiming accuracy of the airborne fiber optic transmission low-light and infrared camera modules, causing image jitter, target loss, and reconnaissance failure. More seriously, the center of gravity shift caused by the fuselage tilt and the ground impact load cannot be effectively buffered, which can easily cause landing gear breakage, structural deformation, or even disintegration. In extreme cases, the UAV may roll over and crash, not only damaging expensive optoelectronic reconnaissance equipment but also causing secondary disasters due to fuel leakage or battery short circuits, severely restricting its survivability and mission reliability in complex environments. To address this, we propose a fiber optic transmission low-light camera infrared supplementary lighting UAV and its usage method. Summary of the Invention

[0004] The purpose of this invention is to provide a fiber optic transmission low-light imaging infrared supplementary lighting drone and its usage method to solve the problems mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a fiber optic transmission low-light camera infrared supplementary lighting drone and its usage method, comprising a drone body structure for takeoff, four landing support mechanisms for assisting the drone body structure in taking off and landing are arranged in a ring on the outer side of the drone body structure, a docking assembly for stably installing the four landing support mechanisms is provided at the lower end of the drone body structure, and a scanning and framing mechanism for inspecting a designated area is provided at the center of the lower end of the docking assembly.

[0006] Preferably, the UAV body structure includes a lower base plate, a positioning seat is fixedly connected to the center of the upper end of the lower base plate, and a final control motherboard is fixedly connected to the upper end of the positioning seat. An optical fiber interface is fixedly welded to one side of the center of the upper end of the final control motherboard. An upper cover plate is provided at the upper end of the lower base plate. Two plug-in bolts are inserted into the lower base plate and the upper cover plate at four opposite corners. A first locking nut is threaded onto the lower outer side of each of the eight plug-in bolts. Multiple positioning studs are fixedly connected to the center of the lower end of the lower base plate near the edge. The eight plug-in bolts are grouped in pairs. Four connecting arms are sleeved on the outer side of the four groups of plug-in bolts. A brushless motor is fixedly connected to the upper, mutually distant ends of the four connecting arms. A propeller is fixedly sleeved on the upper rotating end of each of the four brushless motors. A battery is assembled at the center of the upper end of the upper cover plate.

[0007] Preferably, the docking assembly includes a first docking plate, with multiple positioning holes extending through the center of the first docking plate near its edge. Multiple second locking nuts are provided at the lower end of the first docking plate, with the upper ends of the multiple second locking nuts fitting against each other. Four sets of irregularly shaped support plates are fixedly connected to the outer side of the first docking plate. Irregularly shaped support inclined plates are fixedly connected to the sides of the four sets of irregularly shaped support plates that are far apart from each other. Fluorocarbon rubber strips are fixedly connected to the lower ends of the four irregularly shaped support inclined plates.

[0008] Preferably, the lifting support mechanism includes a docking ramp. Two first lugs are fixedly connected to the upper middle part of one side of the docking ramp. Second lugs are fixedly connected to the lower middle parts of both sides of the docking ramp. Two third lugs are fixedly connected to the lower center of the side of the docking ramp where the two first lugs are fixedly connected. A first rotating shaft is fixedly inserted into the center of the four third lugs. A second rotating shaft is rotatably sleeved at the center of the two first lugs through a bearing. A columnar rotating seat is fixedly sleeved at the center of the outer side of the second rotating shaft. A support column is fixedly connected to one side of the columnar rotating seat. A first connecting rod is fixedly connected to the middle area of ​​the side of the support column away from the columnar rotating seat. An expansion joint is rotatably connected to the side of the first connecting rod away from the support column.

[0009] Preferably, the expansion joint is rotatably connected to the two sides of the end away from the first connecting rod. Electric telescopic rods are rotatably sleeved on both ends of the outer side of the support column via bearings. A third rotating shaft is rotatably sleeved on the inner center of the two second lugs via bearings. A first hollow triangular arm is fixedly sleeved on the outer center of the third rotating shaft. A docking post is fixedly connected to the two sides of the first hollow triangular arm away from each other near the end of the third rotating shaft. The telescopic ends of the two electric telescopic rods are rotatably sleeved on the outside of the two docking posts. A docking piece is fixedly connected to the end of the first hollow triangular arm away from the third rotating shaft. A first docking shaft and a second docking shaft are fixedly sleeved on the inner center of the docking piece near both ends. The end of the second connecting rod away from the expansion joint is rotatably connected to the two outer ends of the first docking shaft away from each other. Balance connecting rods are provided between the two third lugs on one side and between the two third lugs on the other side. The two balance connecting rods are rotatably sleeved on the outer center of the first rotating shaft near both ends. A second hollow triangular arm is provided between the two third lugs near the center.

[0010] Preferably, the second hollow triangular arm is rotatably sleeved at the outer center of the first rotating shaft via bearings. Rotary joints are rotatably sleeved at both ends of the outer center of the second docking shaft via bearings. An MRC electromagnetic suspension rod is fixedly connected to the rotating joint on the side away from the second docking shaft. A shaped docking block is fixedly sleeved at the upper outer center of the MRC electromagnetic suspension rod. Three hollow slots are horizontally arranged and penetrated on one side of the inner center of the shaped docking block. A docking pin is fixedly inserted on one side of the inner center of the shaped docking block. The ends of the two balance rods away from the first rotating shaft are respectively located inside two mutually spaced hollow slots, and the ends of the two balance rods away from the first rotating shaft are rotatably sleeved at the outer centers of the docking pins on both ends. Two hollow triangular arms are positioned with their ends away from the first pivot shaft inside a hollow groove near the center. The ends of the second hollow triangular arms away from the first pivot shaft are rotatably sleeved around the center of the docking pin. An upper connecting block is fixedly sleeved at the lower center of the MRC electromagnetic suspension rod. A lower connecting block is fixedly sleeved on the outer side of the lower telescopic end of the MRC electromagnetic suspension rod. First triangular connecting pieces are rotatably connected to both ends of the upper connecting block. Second triangular connecting pieces are rotatably connected to the ends of the two first triangular connecting pieces away from the lower connecting block. The ends of the two second triangular connecting pieces away from the two first triangular connecting pieces are rotatably connected to the outer center of the lower connecting block at both ends. A strip-shaped lifting plate is fixedly connected to the lower part of the telescopic end of the MRC electromagnetic suspension rod.

[0011] Preferably, the scanning and framing mechanism includes a docking ring, with multiple support rods fixedly connected in a ring at equal intervals near the edge of the lower center of the docking ring. The lower ends of the multiple support rods are fixedly connected to a second docking plate. A first stepper motor is fixedly sleeved at the upper center of the second docking plate. A connecting pipe is rotatably sleeved at the lower center of the second docking plate via a bearing. An upper protective cover is fixedly sleeved at the lower center of the connecting pipe. An upwardly inclined protective shell is fixedly connected to one side of the upper protective cover. A first side protective cover is fixedly connected to the lower end of the upwardly inclined protective shell.

[0012] Preferably, a second stepper motor is fixedly sleeved inside the first side protective cover near one side. A first conductive slip ring is fixedly connected to the lower center of the first stepper motor near the edge. A lower protective cover is fixedly connected to the lower end of the upper protective cover. A retaining ring is fixedly connected to the center of the lower inner wall of the lower protective cover. The lower rotating end of the first stepper motor is fixedly connected to the center of the lower inner wall of the lower protective cover. The lower rotating end of the first conductive slip ring is engaged inside the retaining ring. A lower inclined protective shell is fixedly connected to the lower side of the upper inclined protective shell. The lower inclined protective shell and the lower protective cover are fixedly connected. A second side protective cover is fixedly connected to the lower end of the lower inclined protective shell. The second side protective cover and the first side protective cover are fixedly connected. A retaining sleeve is fixedly sleeved inside the second side protective cover on the side away from the first side protective cover. A second conductive slip ring is engaged inside the retaining sleeve.

[0013] Preferably, a docking plate is fixedly sleeved on the rotating end of the second conductive slip ring on one side. The rotating end of the second stepper motor on one side is fixedly connected to the center of the docking plate near the second conductive slip ring. A first expansion plate and a second expansion plate are fixedly connected to the two opposite sides of the docking plate. A third stepper motor is fixedly connected to the center of the first expansion plate. The third stepper motor and the rotating end of the second conductive slip ring are connected via a flexible flat cable. A third conductive slip ring is fixedly sleeved on the center of the second expansion plate. The non-rotating end of the third conductive slip ring and the rotating end of the second conductive slip ring are connected via a flexible flat cable. A viewfinder module is fixedly connected to the rotating end of the third conductive slip ring near the third stepper motor. The viewfinder module is fixedly connected to the rotating end of the third stepper motor on the side near the third stepper motor. The viewfinder module and the third conductive slip ring are connected via wires. The viewfinder module integrates multiple infrared emitting LEDs and multiple terrain laser scanning radars on one side.

[0014] A method for using a fiber optic transmission low-light camera infrared supplementary lighting drone includes the following steps: S1. The final control motherboard achieves zero-delay high-definition image transmission with the ground station through the fiber optic interface. During takeoff and landing, the docking component acts as a force transmission hub, connecting the takeoff and landing support mechanism to the aircraft body. S2. The landing support mechanism drives a multi-link mechanism, including the first hollow triangular arm and the second link, to perform complex spatial movements through the electro-hydraulic coordinated control of the electric telescopic rod and the MRC electromagnetic suspension rod, thereby adjusting the height and angle of the four strip landing plates in real time and forcibly correcting the fuselage attitude. S3. Under the graded drive of the first stepper motor, the second stepper motor and the third stepper motor, the scanning and framing mechanism, in conjunction with the uninterrupted power transmission of the first conductive slip ring, the second conductive slip ring and the third conductive slip ring, realizes the three-dimensional all-round scanning of the framing module. The S4's viewfinder module integrates low-light photography, infrared illumination, and LiDAR technology, ensuring clear images and accurate terrain data can be obtained even in complete darkness.

[0015] Compared with the prior art, the beneficial effects of the present invention are: This fiber-optic transmission low-light camera infrared supplementary lighting UAV effectively solves the problems of fuselage tilt and unstable attitude of traditional UAVs when taking off and landing in complex terrain by integrating an adaptive take-off and landing support mechanism and a multi-dimensional scanning framing mechanism. It uses fiber optic transmission technology to achieve high-definition data transmission, and combines infrared supplementary lighting and low-light photography to ensure all-weather operation capability. Its core lies in the multi-link electric adjustment and MRC electromagnetic suspension technology of the take-off and landing support mechanism, as well as the multi-axis linkage and conductive slip ring design of the scanning framing mechanism, which realizes real-time correction of the fuselage attitude and all-round coverage of the reconnaissance perspective, greatly improving the survivability and reconnaissance accuracy of the UAV in harsh environments. Attached Figure Description

[0016] Figure 1 A three-dimensional structural diagram of a fiber optic transmission low-light camera infrared supplementary lighting drone; Figure 2 A three-dimensional structural diagram of a fiber optic transmission low-light camera infrared supplementary lighting drone from another perspective; Figure 3 A three-dimensional structural schematic diagram of a docking component for a fiber optic transmission low-light camera infrared supplementary lighting drone; Figure 4 A three-dimensional structural diagram of a fiber optic transmission low-light camera infrared supplementary lighting drone docking component from another perspective; Figure 5 A three-dimensional disassembled structural diagram of a fiber optic transmission low-light camera infrared supplementary lighting drone; Figure 6 A three-dimensional disassembled structural diagram of the drone's airframe; Figure 7 A three-dimensional disassembled structural diagram of the docking components; Figure 8 A three-dimensional, disassembled structural diagram of the landing support mechanism; Figure 9This is a schematic diagram of the three-dimensional structure of the irregularly shaped docking block; Figure 10 A schematic diagram of the three-dimensional disassembled structure of the scanning viewfinder mechanism; Figure 11 A schematic diagram of the three-dimensional split structure of the scanning viewfinder from another perspective; Figure 12 This is a 3D structural diagram of the viewfinder camera.

[0017] In the diagram: 1. UAV body structure; 101. Lower base plate; 102. Positioning seat; 103. Final control motherboard; 104. Fiber optic interface; 105. Upper cover plate; 106. Connecting bolt; 107. First locking nut; 108. Positioning stud; 109. Connecting arm; 1010. Brushless motor; 1011. Propeller; 1012. Battery; 2. Connecting components; 201. First connecting plate; 202. Positioning hole; 203. Second locking nut; 204. Irregular support upright plate; 205. Irregular support inclined plate; 206. Fluorocarbon rubber strip; 3. Lifting and lowering support mechanism; 301. Docking inclined plate; 302. First lug; 303. Second lug; 304. Third lug; 305. First pivot; 306. Second pivot; 307. Columnar swivel; 308. Support column; 309. First connecting rod; 3010. Extension joint; 3011. Second connecting rod; 3012. Electric telescopic rod; 3013. Third pivot; 3014. First hollow triangular arm; 3015. Docking column; 3016. 3017. Connecting piece; 3018. First docking shaft; 3019. Second docking shaft; 3020. Balance connecting rod; 3021. Second hollow triangular arm; 3022. Rotary joint; 3023. MRC electromagnetic suspension rod; 3024. Irregular docking block; 3025. Hollowed-out groove; 3026. Docking pin; 3027. Upper connecting block; 3028. Lower connecting block; 3029. First triangular connecting piece; 3030. Strip lifting plate; 4. Scanning and framing mechanism; 401. Docking ring; 402. Support rod; 403. Second docking plate; 404. First stepper motor; 405. Docking tube; 406. Upper protective cover; 407. Upper sloping protective shell; 408. First side protective cover; 409. Second stepper motor; 4010. First conductive slip ring; 4011. Lower protective cover; 4012. Snap ring; 4013. Lower sloping protective shell; 4014. Second side protective cover; 4015. Sleeve; 4016. Second conductive slip ring; 4017. Docking plate; 4018. First expansion plate; 4019. Second expansion plate; 4020. Third stepper motor; 4021. Third conductive slip ring; 4022. Viewfinder module; 4023. Viewfinder camera; 4024. Infrared emitting LED; 4025. Terrain laser scanning radar. Detailed Implementation

[0018] 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.

[0019] Please see Figures 1-5 As shown, the present invention provides a technical solution: a fiber optic transmission low-light camera infrared supplementary lighting drone, including a drone body structure 1 for takeoff, four takeoff and landing support mechanisms 3 arranged in a ring on the outer side of the drone body structure 1 for assisting the takeoff and landing of the drone body structure 1, a docking component 2 for stably installing the four takeoff and landing support mechanisms 3 at the lower end of the drone body structure 1, and a scanning and framing mechanism 4 for patrolling a designated area at the lower center of the docking component 2.

[0020] This fiber-optic transmission low-light camera infrared supplementary lighting UAV effectively solves the problems of fuselage tilt and unstable attitude of traditional UAVs when taking off and landing in complex terrain by integrating an adaptive take-off and landing support mechanism 3 and a multi-dimensional scanning framing mechanism 4. It uses fiber-optic transmission technology to achieve high-definition data transmission, and combines infrared supplementary lighting and low-light photography to ensure all-weather operation capability. Its core lies in the multi-link electric adjustment and MRC electromagnetic suspension technology of the take-off and landing support mechanism 3, and the multi-axis linkage and conductive slip ring design of the scanning framing mechanism 4, which realizes real-time correction of fuselage attitude and all-round coverage of reconnaissance perspective, greatly improving the survivability and reconnaissance accuracy of UAVs in harsh environments.

[0021] In the preferred embodiment of this technical solution, please refer to Figure 6As shown, the UAV body structure 1 includes a lower base plate 101. A positioning seat 102 is fixedly connected to the center of the upper end of the lower base plate 101, and a central control motherboard 103 is fixedly connected to the upper end of the positioning seat 102. A fiber optic interface 104 is fixedly welded to one side of the center of the upper end of the central control motherboard 103. An upper cover plate 105 is provided on the upper end of the lower base plate 101. The positioning seat 102, the central control motherboard 103, and the fiber optic interface 104 are located between the lower base plate 101 and the upper cover plate 105. Two insertion bolts 106 are inserted into the lower base plate 101 and the upper cover plate 105 at each of the four diagonal points. A first locking nut 107 is threaded onto the lower outer side of each of the eight insertion bolts 106. The upper ends of the eight first locking nuts 107 are connected to the lower base plate 101. The lower ends of the four base plates 101 are fitted together. Multiple positioning studs 108 are fixedly connected to the center of the lower end of the base plate 101 near the edge. Eight plug bolts 106 are arranged in pairs. Four connecting arms 109 are sleeved on the outside of the four sets of plug bolts 106. The lower ends of the four connecting arms 109 are fitted together with the upper end of the base plate 101. The upper ends of the four connecting arms 109 are fitted together with the lower end of the upper cover plate 105. A brushless motor 1010 is fixedly connected to the upper ends of the four connecting arms 109 that are far apart from each other. A propeller 1011 is fixedly sleeved on the upper rotating end of the four brushless motors 1010. A battery 1012 is installed at the center of the upper end of the upper cover plate 105. The battery 1012 and the final control motherboard 103 are connected by wires to achieve communication.

[0022] Furthermore, the UAV body structure 1 serves as the power core and control center of the entire device. Its working principle involves forming a stable structure through the combination of the lower base plate 101 and the upper cover plate 105. The positioning seat 102, the central control motherboard 103, and the fiber optic interface 104 are securely installed by the fastening action of the plug bolts 106 and the first locking nut 107. The battery 1012 provides power to the central control motherboard 103 and the four brushless motors 1010. The central control motherboard 103 communicates with the ground station at high speed through the fiber optic interface 104. Simultaneously, the brushless motor 1010 drives the propeller 1011 to rotate and generate lift. The four connecting arms 109 are evenly distributed between the lower base plate 101 and the upper cover plate 105 through the plug bolts 106, forming a stable quadcopter power layout. The beneficial effects of this structure are that the modular design facilitates quick maintenance, the high-strength connection method ensures the stability of power transmission, provides a solid foundation platform for the subsequent installation of the landing support mechanism 3, and the setting of the fiber optic interface 104 ensures the anti-electromagnetic interference capability of image transmission.

[0023] In the preferred embodiment of this technical solution, please refer to Figure 7As shown, the docking assembly 2 includes a first docking plate 201, which is disposed at the lower end of the lower base plate 101. Multiple positioning holes 202 are provided through the center of the first docking plate 201 near the edge. The multiple positioning holes 202 are respectively sleeved on the outside of multiple positioning studs 108. Multiple second locking nuts 203 are provided at the lower end of the first docking plate 201. The multiple second locking nuts 203 are respectively threaded onto the lower center of the outside of the multiple positioning studs 108, and the upper ends of the multiple second locking nuts 203 are in contact with the lower end of the first docking plate 201. Four sets of irregular support plates 204 are fixedly connected to the outside of the first docking plate 201. Irregular support inclined plates 205 are fixedly connected to the side of the four sets of irregular support plates 204 that are far apart from each other. Fluorocarbon rubber strips 206 are fixedly connected to the lower ends of the four irregular support inclined plates 205.

[0024] The working principle of the docking component 2 is to construct a rigid force transmission bridge between the UAV body structure 1 and the landing support mechanism 3. The first docking plate 201 is sleeved on the positioning stud 108 at the lower end of the bottom plate 101 through the positioning hole 202 and locked by the second locking nut 203 to achieve precise positioning and fixation. Four sets of irregular support upright plates 204 and irregular support inclined plates 205 are spliced ​​to form a specific triangular mechanical structure, which disperses and transmits the ground impact force borne by the landing support mechanism 3 to the first docking plate 201. The fluorocarbon rubber strip 206 at the lower end of the irregular support inclined plate 205 generates elastic deformation when in contact with the ground. Utilizing its high coefficient of friction and damping characteristics, it not only increases the grip during take-off and landing, but also initially filters high-frequency vibrations. The beneficial effect of this structure is that the inclined design of the irregular support upright plate 204 and the inclined plate widens the support base and lowers the center of gravity. Combined with the buffering effect of the fluorocarbon rubber strip 206, it effectively avoids the damage of rigid impact to the UAV body structure 1 and provides a stable mechanical fulcrum for subsequent adaptive adjustment.

[0025] In the preferred embodiment of this technical solution, please refer to Figures 8-9As shown, the lifting support mechanism 3 includes a docking ramp 301, which is fixedly connected to the side of the irregular support ramp 205 away from the first docking plate 201. Two first lugs 302 are fixedly connected to the upper middle part of the side of the docking ramp 301 away from the irregular support ramp 205. Second lugs 303 are fixedly connected to the lower middle parts of both sides of the docking ramp 301. Two third lugs 304 are fixedly connected to the lower center of the side of the docking ramp 301 where the two first lugs 302 are fixedly connected, near both ends. A first rotating shaft 305 is fixedly inserted into the center of the four third lugs 304. A second rotating shaft 306 is rotatably sleeved on the center of the two first lugs 302 via bearings, and a column is fixedly sleeved on the center of the outer side of the second rotating shaft 306. A columnar rotating base 307 has a support column 308 fixedly connected to one side. A first connecting rod 309 is fixedly connected to the middle area of ​​the side of the support column 308 away from the columnar rotating base 307. An expansion joint 3010 is rotatably connected to the side of the first connecting rod 309 away from the support column 308. A second connecting rod 3011 is rotatably connected to both sides of the end of the expansion joint 3010 away from the first connecting rod 309. Electric telescopic rods 3012 are rotatably sleeved on both ends of the outer side of the support column 308 via bearings. The two electric telescopic rods 3012 are connected to the central control board 103 via wires. A third rotating shaft 3013 is rotatably sleeved on the center of the two second lugs 303 via bearings. A first hollowed-out part is fixedly sleeved on the center of the outer side of the third rotating shaft 3013. The hollow triangular arm 3014 has two ends of the first hollow triangular arm 3014 that are far apart from each other and are near the end of the third rotating shaft 3013, with docking posts 3015 fixedly connected to each other. The lower telescopic ends of the two electric telescopic rods 3012 are respectively rotatably sleeved on the outside of the two docking posts 3015. A docking piece 3016 is fixedly connected to the end of the first hollow triangular arm 3014 that is far away from the third rotating shaft 3013. The first docking shaft 3017 and the second docking shaft 3018 are respectively fixedly sleeved at the two ends of the inner center of the docking piece 3016. The end of the second connecting rod 3011 that is far away from the expansion joint 3010 is rotatably connected to the two ends of the first docking shaft 3017 that are far apart from each other. There are two third lugs 304 on one side and two third lugs 304 on the other side. A balance link 3019 is provided, with two balance links 3019 respectively rotatably sleeved at the outer center of the first rotating shaft 305 near both ends. A second hollow triangular arm 3020 is provided between two third lugs 304 near the center, and the second hollow triangular arm 3020 is rotatably sleeved at the outer center of the first rotating shaft 305 via bearings. A rotary joint 3021 is rotatably sleeved at the outer center of the second docking shaft 3018 near both ends via bearings. An MRC electromagnetic suspension rod 3022 is fixedly connected to the side of the rotary joint 3021 away from the second docking shaft 3018. The MRC electromagnetic suspension rod 3022 is connected to the final control mainboard 103 via a wire for communication. A non-standard docking block 3023 is fixedly sleeved at the upper outer center of the MRC electromagnetic suspension rod 3022.The irregularly shaped docking block 3023 has three horizontally arranged through slots 3024 on one side of its internal center. A docking pin 3025 is fixedly inserted into the irregularly shaped docking block 3023 on one side of its internal center. Two balance rods 3019 are respectively located in the two slots 3024 that are far from the first rotating shaft 305. The ends of the two balance rods 3019 that are far from the first rotating shaft 305 are respectively rotatably sleeved on the outer center of the docking pin 3025 at both ends. The end of the second hollow triangular arm 3020 that is far from the first rotating shaft 305 is located in the hollow slot 3024 near the center. The end of the second hollow triangular arm 3020 that is far from the first rotating shaft 305 is rotatably sleeved on the outer center of the docking pin 3025. At the lower outer center of the MRC electromagnetic suspension rod 3022, an upper connecting block 3026 is fixedly sleeved. A lower connecting block 3027 is fixedly sleeved on the outer side of the lower telescopic end of the MRC electromagnetic suspension rod 3022. First triangular connecting pieces 3028 are rotatably connected to both ends of the outer side of the upper connecting block 3026. Second triangular connecting pieces 3029 are rotatably connected to the ends of the two first triangular connecting pieces 3028 away from the lower connecting block 3027. The ends of the two second triangular connecting pieces 3029 away from the two first triangular connecting pieces 3028 are rotatably connected to the outer center of the lower connecting block 3027 at both ends. A strip-shaped lifting plate 3030 is fixedly connected to the lower part of the telescopic end of the MRC electromagnetic suspension rod 3022.

[0026] Furthermore, the working principle of the landing support mechanism 3 is to achieve adaptive conformity to complex terrain through the coordinated action of the multi-link mechanism and the electric telescopic pole 3012. When the UAV lands on uneven ground, the central control motherboard 103 sends a command to control the extension and retraction of the electric telescopic pole 3012. Its extension end pushes the docking column 3015 to drive the first hollow triangular arm 3014 to rotate around the third rotating shaft 3013. The rotation of the first hollow triangular arm 3014 drives the docking piece 3016 and the second link 3011 to move. The second link 3011 pulls the first link 309 through the extension joint 3010, so that the support column 308 can be angled around the second rotating shaft 306. At the same time, the MRC electromagnetic suspension... The rod 3022 adjusts its length in real time according to ground feedback. Its extension and retraction drive the upper connecting block 3026 and the lower connecting block 3027 to move relative to each other. Through the lever action of the first triangular connecting piece 3028 and the second triangular connecting piece 3029, the strip landing plate 3030 is driven to remain horizontal. The balance connecting rod 3019 and the second hollow triangular arm 3020 maintain force balance through the docking pin 3025, ensuring the synchronicity of the mechanism's movement. The beneficial effect of this structure is that it can independently adjust the height and angle for each support point, so that the fuselage always maintains a horizontal posture and avoids the risk of tipping over due to single-point suspension. The millisecond-level response speed of the MRC electromagnetic suspension rod 3022 greatly improves the impact resistance.

[0027] In the preferred embodiment of this technical solution, please refer to Figures 10-12As shown, the scanning and framing mechanism 4 includes a docking ring 401, which is fixedly connected to the lower center of the first docking plate 201. Multiple support rods 402 are equidistantly arranged in a ring near the edge of the lower center of the docking ring 401. A second docking plate 403 is fixedly connected to the lower ends of the multiple support rods 402. A first stepper motor 404 is fixedly sleeved at the upper center of the second docking plate 403. The first stepper motor 404 communicates with the central control board 103 via a wire. A connecting pipe 405 is rotatably sleeved at the lower center of the second docking plate 403 via a bearing. An upper protective cover 406 is fixedly sleeved at the lower center of the connecting pipe 405. An upwardly inclined protective shell 407 is fixedly connected to one side of the upper protective cover 406. A first side protective cover 408 is fixedly connected to the lower end. A second stepper motor 409 is fixedly sleeved inside the first side protective cover 408 near one side. A first conductive slip ring 4010 is fixedly connected to the lower center of the first stepper motor 404 near the edge. The non-rotating end of the first conductive slip ring 4010 is connected to the central control board 103 via a wire. The rotating end of the second stepper motor 409 is connected to the rotating end of the first conductive slip ring 4010 via a flexible flat cable. A lower protective cover 4011 is fixedly connected to the lower end of the upper protective cover 406. A retaining ring 4012 is fixedly connected to the center of the lower inner wall of the lower protective cover 4011. The rotating end of the first stepper motor 404 is fixedly connected to the center of the lower inner wall of the lower protective cover 4011. The first conductive slip ring 401... The lower rotating end of the first conductive slip ring 4010 is engaged inside the retaining ring 4012. A lower inclined protective shell 4013 is fixedly connected to the lower part of the upper inclined protective shell 407. The lower inclined protective shell 4013 is fixedly connected to the lower protective cover 4011. A second side protective cover 4014 is fixedly connected to the lower end of the lower inclined protective shell 4013. The second side protective cover 4014 is fixedly connected to the first side protective cover 408. A retaining sleeve 4015 is fixedly fitted inside the center of the second side protective cover 4014, away from the first side protective cover 408. A second conductive slip ring 4016 is engaged inside the retaining sleeve 4015. The non-rotating end of the second conductive slip ring 4016 and the rotating end of the first conductive slip ring 4010 are connected via a flexible flat cable. The rotating end of the second conductive slip ring 4016 is located on one side... A docking plate 4017 is fixedly sleeved on the outside of the first end. The rotating end of the second stepper motor 409 on one side is fixedly connected to the center of the docking plate 4017 near the second conductive slip ring 4016. A first expansion plate 4018 and a second expansion plate 4019 are fixedly connected to the two opposite sides of the docking plate 4017, respectively. A third stepper motor 4020 is fixedly connected to the center of the first expansion plate 4018. The third stepper motor 4020 and the rotating end of the second conductive slip ring 4016 are connected via a flexible flat cable. A third conductive slip ring 4021 is fixedly sleeved on the center of the second expansion plate 4019. The non-rotating end of the third conductive slip ring 4021 and the rotating end of the second conductive slip ring 4016 are connected via a flexible flat cable.A viewfinder module 4022 is fixedly connected to the rotating end of the third conductive slip ring 4021 near the third stepper motor 4020. The viewfinder module 4022 is fixedly connected to the rotating end of the third stepper motor 4020 near the third stepper motor 4020. A communication connection is established between the viewfinder module 4022 and the third conductive slip ring 4021 via wires. One side of the viewfinder module 4022 integrates a viewfinder camera 4023, multiple infrared emitting LEDs 4024, and multiple terrain laser scanning radars 4025.

[0028] Furthermore, the working principle of the scanning and framing mechanism 4 lies in utilizing the cooperation of multi-step motors and conductive slip rings to achieve omnidirectional coverage of the reconnaissance view and tangle-free cable transmission. The first stepper motor 404 drives the docking pipe 405 to rotate, causing the upper protective cover 406, lower protective cover 4011, and internal components to rotate horizontally in all directions. The second stepper motor 409 drives the docking plate 4017 to rotate through the power transmission between the first conductive slip ring 4010 and the second conductive slip ring 4016, thereby causing the first expansion plate 4018, the second expansion plate 4019, and the framing module 4022 to perform pitch movement. The third stepper motor 4020, through the third... The conductive slip ring 4021 drives the viewfinder module 4022 to rotate, enabling multi-angle fine-tuning. The viewfinder camera 4023, infrared emitting LED 4024, and terrain laser scanning radar 4025 integrated in the viewfinder module 4022 work synchronously during rotation. The infrared LED provides supplementary lighting, the camera captures low-light images, and the radar constructs a terrain model. The design of the conductive slip ring solves the problem of cable entanglement in rotating components. The beneficial effect of this structure is that it achieves "clear vision" and "comprehensive scanning" on the basis of "stability". It can perform a three-dimensional scan of the surrounding environment without blind spots while maintaining the stability of the camera body, significantly improving the target capture rate at night and in low-light environments.

[0029] Please see Figure 1-10 A method for using a fiber optic transmission low-light camera infrared supplementary lighting drone includes the following steps: S1. The final control motherboard 103 achieves zero-delay high-definition image transmission with the ground station through the fiber optic interface 104. During the take-off and landing phase, the docking component 2 acts as a force transmission hub to connect the take-off and landing support mechanism 3 to the aircraft body.

[0030] S2. The landing support mechanism 3 drives the multi-link mechanism, including the first hollow triangular arm 3014 and the second link 3011, to perform complex spatial movements through the electro-hydraulic coordinated control of the electric telescopic rod 3012 and the MRC electromagnetic suspension rod 3022. It adjusts the height and angle of the four strip landing plates 3030 in real time and forcibly corrects the fuselage attitude.

[0031] S3. Under the graded drive of the first stepper motor 404, the second stepper motor 409 and the third stepper motor 4020, and with the uninterrupted power transmission of the first conductive slip ring 4010, the second conductive slip ring 4016 and the third conductive slip ring 4021, the scanning and framing mechanism 4 realizes the three-dimensional all-round scanning of the framing module 4022.

[0032] The S4 and 4022 viewfinder module integrate low-light imaging, infrared illumination, and LiDAR technology to ensure clear images and accurate terrain data can be obtained even in complete darkness.

[0033] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0034] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A fiber optic transmission low-light camera infrared supplementary lighting drone, characterized in that: The device includes a drone body structure (1) for takeoff, and four landing support mechanisms (3) for assisting the drone body structure (1) to take off and land are arranged in a ring on the outside of the drone body structure (1). A docking assembly (2) for stably installing the four landing support mechanisms (3) is provided at the lower end of the drone body structure (1). A scanning and framing mechanism (4) for patrolling a designated area is provided at the center of the lower end of the docking assembly (2).

2. The fiber optic transmission low-light imaging infrared supplementary lighting UAV according to claim 1, characterized in that: The UAV body structure (1) includes a lower base plate (101), a positioning seat (102) is fixedly connected to the upper center of the lower base plate (101), and a final control motherboard (103) is fixedly connected to the upper end of the positioning seat (102). An optical fiber interface (104) is fixedly welded to one side of the upper center of the final control motherboard (103). An upper cover plate (105) is provided on the upper end of the lower base plate (101). Two plug-in bolts (106) are inserted into the lower base plate (101) and the upper cover plate (105) at the four diagonal corners. The eight plug-in bolts (106) are screwed on the lower outer side. The lower base plate (101) is fitted with a first locking nut (107). Multiple positioning studs (108) are fixedly connected to the lower center near the edge of the lower base plate (101). The eight plug bolts (106) are arranged in pairs. Four connecting arms (109) are fitted on the outside of the four sets of plug bolts (106). A brushless motor (1010) is fixedly connected to the upper ends of the four connecting arms (109) that are far apart from each other. A propeller (1011) is fixedly fitted on the upper rotating end of the four brushless motors (1010). A battery (1012) is assembled at the upper center of the upper end of the upper cover plate (105).

3. The fiber optic transmission low-light imaging infrared supplementary lighting UAV according to claim 1, characterized in that: The docking assembly (2) includes a first docking plate (201). Multiple positioning holes (202) are provided through the center of the first docking plate (201) near the edge. Multiple second locking nuts (203) are provided at the lower end of the first docking plate (201), and the upper ends of the multiple second locking nuts (203) are in contact with the lower end of the first docking plate (201). Four sets of irregular support plates (204) are fixedly connected to the outside of the first docking plate (201). On the side of the four sets of irregular support plates (204) that are far apart from each other, irregular support inclined plates (205) are fixedly connected. Fluorocarbon rubber strips (206) are fixedly connected to the lower ends of the four irregular support inclined plates (205).

4. The fiber optic transmission low-light imaging infrared supplementary lighting UAV according to claim 1, characterized in that: The lifting support mechanism (3) includes a docking ramp (301). Two first lugs (302) are fixedly connected to the upper part of the middle of one side of the docking ramp (301). Two second lugs (303) are fixedly connected to the lower part of the middle of both sides of the docking ramp (301). Two third lugs (304) are fixedly connected to the lower center of the side of the docking ramp (301) where the two first lugs (302) are fixedly connected. A first rotating shaft (305) is fixedly inserted into the center of the four third lugs (304). Two first ear pieces (302) are rotatably connected to a second rotating shaft (306) through a bearing at their inner center, and a columnar rotating seat (307) is fixedly fitted at the outer center of the second rotating shaft (306). A support column (308) is fixedly connected to one side of the columnar rotating seat (307), and a first connecting rod (309) is fixedly connected to the middle area of ​​the side of the support column (308) away from the columnar rotating seat (307). An expansion joint (3010) is rotatably connected to the side of the first connecting rod (309) away from the support column (308).

5. The fiber optic transmission low-light imaging infrared supplementary lighting UAV according to claim 4, characterized in that: The expansion joint (3010) is rotatably connected to the two sides of the end away from the first connecting rod (309) by a second connecting rod (3011). Electric telescopic rods (3012) are rotatably sleeved on both ends of the outer side of the support column (308) via bearings. A third rotating shaft (3013) is rotatably sleeved on the center of the two second lugs (303) via bearings. A first hollow triangular arm (3014) is fixedly sleeved on the center of the outer side of the third rotating shaft (3013). A docking post (3015) is fixedly connected to the two sides of the first hollow triangular arm (3014) near the end of the third rotating shaft (3013). The telescopic ends of the two electric telescopic rods (3012) are rotatably sleeved on the outside of the two docking posts (3015). The first hollow triangular arm (3014) is rotatably sleeved on the outside of the two docking posts (3015). 014) A docking piece (3016) is fixedly connected at one end away from the third rotating shaft (3013). The first docking shaft (3017) and the second docking shaft (3018) are respectively fixedly sleeved at the two ends of the inner center of the docking piece (3016). The end of the second connecting rod (3011) away from the expansion joint (3010) is rotatably connected to the two ends of the first docking shaft (3017) that are far apart from each other. A balance connecting rod (3019) is provided between the two third ear pieces (304) on one side and between the two third ear pieces (304) on the other side. The two balance connecting rods (3019) are respectively rotatably sleeved at the two ends of the outer center of the first rotating shaft (305). A second hollow triangular arm (3020) is provided between the two third ear pieces (304) near the center.

6. The fiber optic transmission low-light imaging infrared supplementary lighting UAV according to claim 5, characterized in that: The second hollow triangular arm (3020) is rotatably sleeved at the outer center of the first rotating shaft (305) via bearings. Rotary joints (3021) are rotatably sleeved at both ends of the outer center of the second docking shaft (3018) via bearings. An MRC electromagnetic suspension rod (3022) is fixedly connected to the side of the rotating joint (3021) away from the second docking shaft (3018). A shaped docking block (3023) is fixedly sleeved at the upper outer center of the MRC electromagnetic suspension rod (3022). The shaped docking block (3023) contains... Three hollow slots (3024) are horizontally arranged and penetrate one side of the center of the part. A docking pin (3025) is fixedly inserted into the center of the irregular docking block (3023) on one side. The two balance rods (3019) are respectively set in the two hollow slots (3024) that are far away from the first rotating shaft (305). The two balance rods (3019) are respectively rotatably sleeved on the outer center of the docking pin (3025) near both ends. The second hollow triangular arm (3020) The end away from the first rotating shaft (305) is located inside the hollow groove (3024) near the center, and the end of the second hollow triangular arm (3020) away from the first rotating shaft (305) is rotatably sleeved on the outer center of the docking pin (3025). The upper connecting block (3026) is fixedly sleeved on the lower part of the outer center of the MRC electromagnetic suspension rod (3022), and the lower connecting block (3027) is fixedly sleeved on the outer side of the telescopic end of the lower part of the MRC electromagnetic suspension rod (3022). The outer side of the upper connecting block (3026) A first triangular connecting piece (3028) is rotatably connected to both ends. A second triangular connecting piece (3029) is rotatably connected to the ends of the two first triangular connecting pieces (3028) away from the lower connecting block (3027). The ends of the two second triangular connecting pieces (3029) away from the two first triangular connecting pieces (3028) are respectively rotatably connected to the outer center of the lower connecting block (3027) near both ends. A strip-shaped lifting plate (3030) is fixedly connected to the lower telescopic end of the MRC electromagnetic suspension rod (3022).

7. The fiber optic transmission low-light imaging infrared supplementary lighting UAV according to claim 1, characterized in that: The scanning and framing mechanism (4) includes a docking ring (401). Multiple support rods (402) are fixedly connected in a ring at equal intervals near the edge of the lower center of the docking ring (401). A second docking plate (403) is fixedly connected to the lower end of the multiple support rods (402). A first stepper motor (404) is fixedly sleeved at the upper center of the second docking plate (403). A connecting pipe (405) is rotatably sleeved at the lower center of the second docking plate (403) through a bearing. An upper protective cover (406) is fixedly sleeved at the lower center of the outer side of the connecting pipe (405). An upper inclined protective shell (407) is fixedly connected to one side of the upper protective cover (406). A first side protective cover (408) is fixedly connected to the lower end of the upper inclined protective shell (407).

8. The fiber optic transmission low-light imaging infrared supplementary lighting UAV according to claim 7, characterized in that: A second stepper motor (409) is fixedly fitted inside the first side protective cover (408) near one side. A first conductive slip ring (4010) is fixedly connected to the lower center of the first stepper motor (404) near the edge. A lower protective cover (4011) is fixedly connected to the lower end of the upper protective cover (406). A retaining ring (4012) is fixedly connected to the center of the lower inner wall of the lower protective cover (4011). The rotating end of the first stepper motor (404) near the bottom is fixedly connected to the center of the lower inner wall of the lower protective cover (4011). The rotating end of the first conductive slip ring (4010) near the bottom is engaged with the retaining ring (4012). Inside, a lower inclined protective shell (4013) is fixedly connected to the lower inclined protective shell (407) at its lower angle. The lower inclined protective shell (4013) is fixedly connected to the lower protective cover (4011). A second side protective cover (4014) is fixedly connected to the lower end of the lower inclined protective shell (4013). The second side protective cover (4014) is fixedly connected to the first side protective cover (408). A retainer (4015) is fixedly fitted on the side of the second side protective cover (4014) away from the first side protective cover (408). A second conductive slip ring (4016) is snapped into the retainer (4015).

9. The fiber optic transmission low-light imaging infrared supplementary lighting UAV according to claim 8, characterized in that: A docking plate (4017) is fixedly sleeved on the outside of the rotating end of the second conductive slip ring (4016) on one side. The rotating end of the second stepper motor (409) on one side is fixedly connected to the center of the docking plate (4017) near the second conductive slip ring (4016). A first expansion plate (4018) and a second expansion plate (4019) are fixedly connected to the two opposite sides of the docking plate (4017). A third stepper motor (4020) is fixedly connected to the center of the first expansion plate (4018). The third stepper motor (4020) and the rotating end of the second conductive slip ring (4016) are connected via a flexible flat cable. A third conductive slip ring (4019) is fixedly sleeved on the center of the second expansion plate (4019). The non-rotating end of the third conductive slip ring (4021) and the rotating end of the second conductive slip ring (4016) are connected via a flexible flat cable. A viewfinder module (4022) is fixedly connected to the rotating end of the third conductive slip ring (4021) near the third stepper motor (4020). The viewfinder module (4022) is fixedly connected to the rotating end of the third stepper motor (4020) near the third stepper motor (4020). The viewfinder module (4022) and the third conductive slip ring (4021) are connected via wires. The viewfinder module (4022) integrates a viewfinder camera (4023), multiple infrared emitting LEDs (4024), and multiple terrain laser scanning radars (4025) on one side.

10. A method of using a fiber-optic transmission low-light imaging infrared supplementary lighting UAV according to any one of claims 1-9, characterized in that, Includes the following steps: S1. The final control motherboard (103) achieves zero-delay high-definition image transmission with the ground station through the fiber optic interface (104). During the take-off and landing phase, the docking component (2) serves as the force transmission hub, connecting the take-off and landing support mechanism (3) to the aircraft body. S2. The landing support mechanism (3) drives the multi-link mechanism, including the first hollow triangular arm (3014) and the second link (3011), to perform complex spatial movements through the electro-hydraulic coordinated control of the electric telescopic rod (3012) and the MRC electromagnetic suspension rod (3022), and adjusts the height and angle of the four strip landing plates (3030) in real time to forcibly correct the fuselage attitude. S3. Under the graded drive of the first stepper motor (404), the second stepper motor (409) and the third stepper motor (4020), the scanning and framing mechanism (4) cooperates with the uninterrupted power transmission of the first conductive slip ring (4010), the second conductive slip ring (4016) and the third conductive slip ring (4021) to realize the three-dimensional all-round scanning of the framing module (4022). S4, the viewfinder module (4022) integrates low-light imaging, infrared illumination and lidar technology to ensure clear images and accurate terrain data can be obtained even in complete darkness.

Images