Unmanned aerial vehicle for geological disaster detection
Through the coordinated control of the adjustable rotor system and the folding wing, the geological disaster monitoring drone's attitude instability and fuselage collision problems in complex environments are solved, stable flight and multi-level mission adaptation are achieved, and anti-interference ability and lift distribution are enhanced.
Patent Information
- Application Number
- CN202510556426.3
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-04-29
- Publication Date
- 2025-07-04
AI Technical Summary
Existing geological disaster monitoring drones are prone to instability in complex geological environments, and the fixed body size leads to collisions with obstacles, low electromagnetic interference and thermal management efficiency.
The coordinated control of an adjustable rotor system and folding wings is adopted, combined with hydraulic drive and mechanical locking mechanisms, and dynamic adjustment of rotor pitch and wings is achieved through the PLC controller to enhance anti-interference ability and lift distribution. The wings can be quickly deployed or folded to meet different task needs.
Achieve stable flight in complex geological environments, expand operation coverage, improve lift and anti-interference capabilities, avoid hydraulic leakage and electromagnetic interference, and adapt to multi-level task requirements.
Smart Images
Figure CN120246292A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of unmanned aerial vehicles (UAVs), and in particular to an unmanned aerial vehicle (UAV) for geological disaster detection. Background Art
[0002] In the field of geological disaster monitoring, traditional UAV technology faces multi-dimensional technical bottlenecks. Existing monitoring UAVs mostly adopt a fixed rotor layout, and their power systems often present rigid structural characteristics. The rotor spacing and position cannot be dynamically adjusted according to the actual terrain characteristics or sudden airflow disturbances. This structural defect causes the aircraft to be prone to attitude instability or even loss of control when encountering mountain turbulence or canyon crosswinds, which seriously restricts the reliability of operations in complex geological environments. At the same time, the conventional equipment cabin adopts a single cavity design, and the battery pack, control module and sensor unit are mixedly arranged, which not only causes electromagnetic interference problems, but also causes key components to experience performance degradation during long-term operations due to inefficient thermal management. In terms of aerodynamic layout adaptability, traditional solutions generally have the disadvantage of a single functional form; most geological disaster monitoring UAVs adopt a fully-deployed fixed wing and rotor composite structure. Although they can take into account both cruising efficiency and hovering capability, when performing tasks such as narrow gap exploration and close-range scanning of landslides, the excessive body size is prone to collision with obstacles. For this reason, we propose a UAV for geological disaster detection. Summary of the invention
[0003] The technical problem to be solved by the present invention is to overcome the existing defects and provide a drone for geological disaster detection, which can adjust the size of the body according to needs and effectively solve the problems in the background technology.
[0004] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a UAV for geological disaster detection, comprising a UAV body and an adjustment component; UAV body: An installation cavity is provided at the lower end of the interior, and a battery, an inertial measurement unit, a PLC controller and a wireless transmission module are installed inside the installation cavity. A main control chip is installed at the upper end of the interior of the UAV body. Two corresponding wing assemblies and two corresponding fastening assemblies are installed on the front and rear sides of the UAV body, and the fastening assemblies are connected to the wing assemblies; Adjustment assembly: It includes a fixed frame, a fixed tube, a hydraulic rod, a connection disk, a connection bar, and a card hole. Six corresponding fixed frames are fixed on the surface of the UAV body. A fixed tube is fixed inside the fixed frame. A hydraulic rod is arranged inside the fixed tube. The hydraulic rod is installed inside the fixed frame. A connection disk is fixed on the telescopic arm of the hydraulic rod. Connection bars are fixed on the end face of the connection disk. Uniformly distributed card holes are formed on the side surface of the connection bar. A locking assembly is installed on the end face of the fixed tube. The locking assembly is connected to the corresponding card hole. A pulling assembly is installed on the side of the fixed frame. The pulling assembly is connected to the locking assembly. A rotor assembly is installed above the connection bar. The length of the rotor assembly is adjusted by setting the adjustment assembly; Among them: The input end of the PLC controller is electrically connected to the output end of the battery. The PLC controller is bidirectionally electrically connected to the main control chip and the inertial measurement unit respectively. The output end of the PLC controller is electrically connected to the input end of the hydraulic rod.
[0005] Further, the locking assembly includes a connection ring, a card head, a connection ring, and a first spring. A connection ring is fixed on the end face of the fixed tube away from the fixed frame. Two corresponding mounting holes are formed on the circumferential surface of the connection ring. A connection ring is fixed inside the mounting hole. A card head is arranged inside the mounting hole. The card head is connected to the connection ring through a first spring. Both card heads are clamped at both ends inside the corresponding card hole. The connection bar is locked and fixed by setting the locking assembly.
[0006] Further, the pulling assembly includes an electric telescopic rod, a sliding ring, and a pulling rope. Two corresponding electric telescopic rods are installed on the side of the fixed frame. A sliding ring is fixed on the telescopic arms of the two electric telescopic rods. The sliding ring is sleeved on the circumferential surface of the fixed tube. Two corresponding pulling ropes are fixed on the end face of the sliding ring. The pulling ropes are slidably connected inside the corresponding connection ring. The end of the pulling rope away from the sliding ring is fixed on the end face of the corresponding card head. The input end of the electric telescopic rod is electrically connected to the output end of the PLC controller. The connected card head is driven to move by setting the pulling assembly.
[0007] Further, the rotor assembly includes a mounting barrel, a first motor, a rotating shaft, and rotor blades. A mounting barrel is fixed on the upper side edge of the connection bar. A first motor is installed at the upper end inside the mounting barrel. A rotating shaft is fixed on the output shaft of the first motor. Two corresponding rotor blades are fixed on the circumferential surface of the rotating shaft. The input end of the first motor is electrically connected to the output end of the PLC controller. The UAV body can take off conveniently by setting the rotor assembly.
[0008] Further, it further includes a length measurement component, which comprises an infrared rangefinder and a reflector. The infrared rangefinder is installed on the end face of the connecting ring, and the reflector is fixed on the side of the connecting bar away from the connecting disc. The infrared rangefinder and the reflector correspond to each other. The infrared rangefinder is bidirectionally electrically connected to the PLC controller. By setting the length measurement component, the moving length of the rotor assembly is detected.
[0009] Further, the wing assembly comprises a fixing plate, a mounting shaft, a clamping groove, a rotating ring, a wing and a second motor. Two corresponding fixing plates are fixed on the front and rear sides of the UAV body. A mounting shaft is rotatably connected between the two fixing plates. Four corresponding clamping grooves are formed on the circumferential surface of the mounting shaft. Two corresponding rotating rings are fixed on the circumferential surface of the mounting shaft. Wings are fixed at the lower ends of the circumferential surfaces of the two rotating rings. A second motor is installed on the left side of the left fixing plate. The output shafts of the two second motors are respectively fixed at the left ends of the two mounting shafts. The input end of the second motor is electrically connected to the output end of the PLC controller. By setting the wing assembly, additional lift is provided.
[0010] Further, the fastening component comprises a mounting groove, an electromagnet, a mounting ring, a connecting rod, an iron disc, a clamping column and a second spring. Two corresponding mounting grooves are formed on the front and rear sides of the UAV body. The electromagnet is installed inside the mounting groove. The mounting ring is fixed inside the mounting groove. The connecting rod is slidably connected inside the mounting ring. One end of the connecting rod is fixed with an iron disc, and the iron disc corresponds to the electromagnet. The other end of the connecting rod is fixed with a clamping column, and the clamping column is clamped inside the corresponding clamping groove. A second spring is sleeved on the circumferential surface of the connecting rod. One end of the second spring is fixed on the end face of the mounting ring, and the other end of the second spring is fixed on the end face of the clamping column. The input end of the electromagnet is electrically connected to the output end of the PLC controller. By setting the fastening component, the mounting shaft is fixed.
[0011] Further, four corresponding legs are fixed on the lower side of the UAV body, and two corresponding support bars are fixed on the lower sides of the four legs. By setting the legs and the support bars, the UAV body is supported.
[0012] Further, a buffer rubber sleeve is fixed on the surface of the support bar, and uniformly distributed anti-slip grooves are formed on the lower side of the buffer rubber sleeve. Buffering is carried out by setting the buffer rubber sleeve.
[0013] Further, a camera is installed on the lower side of the UAV body, and the camera is bidirectionally electrically connected to the PLC controller. Shooting is facilitated by setting the camera.
[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: This geological disaster detection UAV has the following advantages: 1. Through the coordinated control of the adjustable rotor system and the folding wings, the UAV can quickly switch flight modes and achieve stable flight in typical geological disaster scenarios such as narrow spaces and complex airflows. The intelligent adjustment of the rotor spacing effectively optimizes the lift distribution and significantly enhances the anti-interference ability of the aircraft under strong turbulence.
[0015] 2. The dual locking mechanism of hydraulic drive and mechanical locking ensures the reliability of the rotor extension positioning, avoiding displacement drift caused by hydraulic oil leakage or pressure fluctuation that may occur in traditional pure hydraulic systems. 3. The quick deployment and folding functions of the wing assembly enable the UAV to flexibly switch between cruise monitoring and fine exploration modes. Combined with the dynamic deformation ability of the rotor system, it can adapt to multi-level mission requirements from large-area scanning to detailed inspection of local high-risk points, significantly expanding the single-aircraft operation coverage and effectively increasing the lift at the same time. BRIEF DESCRIPTION OF THE DRAWINGS
[0016] Figure 1 It is a schematic front structure view of the present invention; Figure 2 It is an enlarged view at A of the present invention; Figure 3 It is a schematic structure view at the inertial measurement unit of the present invention; Figure 4 It is a schematic structure view of the pulling component of the present invention; Figure 5 It is an enlarged view at B of the present invention; Figure 6 It is a schematic structure view of the length measurement component of the present invention; Figure 7 It is a schematic structure view of the main control chip of the present invention; Figure 8 It is an enlarged view at C of the present invention.
[0017] In the figure: 1 UAV body, 2 adjustment component, 21 fixing frame, 22 fixing tube, 23 hydraulic rod, 24 connecting disk, 25 connecting bar, 26 card hole, 3 locking component, 31 connecting ring, 32 card head, 33 connecting ring, 34 first spring, 4 pulling component, 41 electric telescopic rod, 42 sliding ring, 43 pulling rope, 5 rotor component, 51 installation barrel, 52 first motor, 53 rotating shaft, 54 rotor blade, 6 length measurement component, 61 infrared rangefinder, 62 reflector, 7 wing component, 71 fixing plate, 72 installation shaft, 73 card slot, 74 rotating ring, 75 wing, 76 second motor, 8 fastening component, 81 installation groove, 82 electromagnet, 83 installation ring, 84 connecting rod, 85 iron disk, 86 clamping column, 87 second spring, 9 leg, 10 support bar, 11 buffer rubber sleeve, 12 main control chip, 13 storage battery, 14 inertial measurement unit, 15 PLC controller, 16 wireless transmission module, 17 camera. Detailed implementation mode
[0018] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.
[0019] Please refer to Figure 1-8 , this embodiment provides a technical solution: an unmanned aerial vehicle for geological disaster detection, including an unmanned aerial vehicle body 1 and an adjustment component 2; Unmanned aerial vehicle body 1: An installation cavity is provided at the lower end inside. A storage battery 13, an inertial measurement unit 14, a PLC controller 15, and a wireless transmission module 16 are installed inside the installation cavity. A main control chip 12 is installed at the upper end inside the unmanned aerial vehicle body 1. Two corresponding wing components 7 and two corresponding fastening components 8 are installed on the front and rear sides of the unmanned aerial vehicle body 1. The fastening component 8 is connected to the wing component 7. The wing component 7 includes a fixing plate 71, a mounting shaft 72, a card slot 73, a rotating ring 74, a wing 75, and a second motor 76. Two corresponding fixing plates 71 are fixed on the front and rear sides of the unmanned aerial vehicle body 1. A mounting shaft 72 is rotatably connected between the two fixing plates 71. Four corresponding card slots 73 are provided on the circumferential surface of the mounting shaft 72. Two corresponding rotating rings 74 are fixed on the circumferential surface of the mounting shaft 72. Wings 75 are fixed at the lower ends of the circumferential surfaces of the two rotating rings 74. A second motor 76 is installed on the left side of the left fixing plate 71. The output shafts of the two second motors 76 are respectively fixed to the left ends of the two mounting shafts 72. The input end of the second motor 76 is electrically connected to the output end of the PLC controller 15. The fastening component 8 includes a mounting groove 81, an electromagnet 82, a mounting ring 83, a connecting rod 84, an iron plate 85, a clamping column 86, and a second spring 87. Two corresponding mounting grooves 81 are provided on the front and rear sides of the unmanned aerial vehicle body 1. An electromagnet 82 is installed inside the mounting groove 81. A mounting ring 83 is fixed inside the mounting groove 81. A connecting rod 84 is slidably connected inside the mounting ring 83. One end of the connecting rod 84 is fixed with an iron plate 85. The iron plate 85 corresponds to the electromagnet 82. The other end of the connecting rod 84 is fixed with a clamping column 86. The clamping column 86 is clamped inside the corresponding card slot 73. A second spring 87 is sleeved on the circumferential surface of the connecting rod 84. One end of the second spring 87 is fixed on the end surface of the mounting ring 83, and the other end of the second spring 87 is fixed on the end surface of the clamping column 86. The input end of the electromagnet 82 is electrically connected to the output end of the PLC controller 15. By setting the fastening component 8 to fix the mounting shaft 72, additional lift is provided by setting the wing component 7; Adjusting Assembly 2: It includes a fixing frame 21, a fixing tube 22, a hydraulic rod 23, a connecting disk 24, a connecting bar 25 and a clamping hole 26. Six corresponding fixing frames 21 are fixed on the surface of the UAV body 1. A fixing tube 22 is fixed inside the fixing frame 21. A hydraulic rod 23 is arranged inside the fixing tube 22. The hydraulic rod 23 is installed inside the fixing frame 21. A connecting disk 24 is fixed on the telescopic arm of the hydraulic rod 23. A connecting bar 25 is fixed on the end face of the connecting disk 24. Uniformly distributed clamping holes 26 are formed on the side surface of the connecting bar 25. A locking assembly 3 is installed on the end face of the fixing tube 22. The locking assembly 3 is connected to the corresponding clamping hole 26. A pulling assembly 4 is installed on the side surface of the fixing frame 21. The pulling assembly 4 is connected to the locking assembly 3. A rotor assembly 5 is installed above the connecting bar 25. The locking assembly 3 includes a connecting ring 31, a clamping head 32, a connecting ring 33 and a first spring 34. A connecting ring 31 is fixed on the end face of the fixing tube 22 away from the fixing frame 21. Two corresponding mounting holes are formed on the circumferential surface of the connecting ring 31. A connecting ring 33 is fixed inside the mounting hole. A clamping head 32 is arranged inside the mounting hole. The clamping head 32 is connected to the connecting ring 33 through a first spring 34. Both clamping heads 32 are clamped at both ends inside the corresponding clamping hole 26. The pulling assembly 4 includes an electric telescopic rod 41, a sliding ring 42 and a pulling rope 43. Two corresponding electric telescopic rods 41 are installed on the side surface of the fixing frame 21. A sliding ring 42 is fixed on the telescopic arms of the two electric telescopic rods 41. The sliding ring 42 is sleeved on the circumferential surface of the fixing tube 22. Two corresponding pulling ropes 43 are fixed on the end face of the sliding ring 42. The pulling ropes 43 are slidably connected inside the corresponding connecting ring 31. One end of the pulling rope 43 away from the sliding ring 42 is fixed on the end face of the corresponding clamping head 32. The input end of the electric telescopic rod 41 is electrically connected to the output end of the PLC controller 15. The rotor assembly 5 includes a mounting barrel 51, a first motor 52, a rotating shaft 53 and rotor blades 54. A mounting barrel 51 is fixed on the upper side edge of the connecting bar 25. A first motor 52 is installed at the upper end inside the mounting barrel 51. A rotating shaft 53 is fixed on the output shaft of the first motor 52. Two corresponding rotor blades 54 are fixed on the circumferential surface of the rotating shaft 53. The input end of the first motor 52 is electrically connected to the output end of the PLC controller 15. It further includes a length measuring assembly 6. The length measuring assembly 6 includes an infrared distance measuring instrument 61 and a reflector 62. An infrared distance measuring instrument 61 is installed on the end face of the connecting ring 31. A reflector 62 is fixed on the side surface of the connecting bar 25 away from the connecting disk 24. The infrared distance measuring instrument 61 and the reflector 62 correspond to each other. The infrared distance measuring instrument 61 is bidirectionally electrically connected to the PLC controller 15. By setting the length measuring assembly 6 to detect the moving length of the rotor assembly 5, by setting the rotor assembly 5 to facilitate the takeoff of the UAV body 1, by setting the pulling assembly 4 to drive the connected clamping head 32 to move, by setting the locking assembly 3 to lock and fix the connecting bar 25, and by setting the adjusting assembly 2 to adjust the length of the rotor assembly 5; Among them: The input end of the PLC controller 15 is electrically connected to the output end of the storage battery 13. The PLC controller 15 is bidirectionally electrically connected to the main control chip 12 and the inertial measurement unit 14 respectively. The output end of the PLC controller 15 is electrically connected to the input end of the hydraulic rod 23.
[0020] Among them: Four corresponding legs 9 are fixed to the lower side of the UAV body 1. Two corresponding support bars 10 are fixed to the lower sides of the four legs 9. The UAV body 1 is supported by arranging the legs 9 and the support bars 10.
[0021] Among them: A buffer rubber sleeve 11 is fixed to the surface of the support bar 10. Uniformly distributed anti-slip grooves are formed in the lower side of the buffer rubber sleeve 11. Buffering is carried out by arranging the buffer rubber sleeve 11.
[0022] Among them: A camera 17 is installed on the lower side of the UAV body 1. The camera 17 is bidirectionally electrically connected to the PLC controller 15. Shooting is facilitated by arranging the camera 17.
[0023] The working principle of a UAV for geological disaster detection provided by the present invention is as follows: The inertial measurement unit 14 integrated inside the UAV body 1 includes a three-axis MEMS accelerometer, a gyroscope, and a magnetometer to collect flight attitude data in real time at a high sampling rate. The main control chip 12 fuses angular velocity, linear acceleration, and geomagnetic information through an extended Kalman filter algorithm to accurately calculate the three-dimensional spatial pose of the UAV in complex airflows. When an abnormal yaw angle caused by a crosswind on the side of a mountain valley is detected, the PLC controller 15 drives the hydraulic rod 23 of the adjustment assembly 2 to accurately extend and retract, driving the connection disk 24 to axially displace along the fixed tube 22, causing the six connecting bars 25 to expand or contract synchronously, changing the distribution radius of the rotor assembly 5. The rotor blades 54 are driven by the first motor 52 to form a reconstructed lift surface. After the distribution radius of the rotor assembly 5 changes, the chuck 32 of the locking assembly 3 is embedded in the corresponding card hole 26 of the connecting bar 25 by the pre-tightening force of the first spring 34 after the hydraulic rod 23 is in place, forming a mechanical-hydraulic double-stage lock. When entering the slit area of a landslide body, the electromagnet 82 of the fastening assembly 8 receives a pulse signal from the PLC controller 15 to generate a magnetic suction force, pulling the iron disk 85 to overcome the resistance of the second spring 87 to make the clamping column 86 disengage from the card slot 73 of the mounting shaft 72. The second motor 76 drives the rotating ring 74 to drive the wing 75 to fold to be parallel to the axis of the UAV body 1, reducing the lateral dimension to avoid obstacles. In the non-operating state, an external instruction is received through the wireless transmission module 16, and the electromagnet 82 is continuously powered on to keep the clamping column 86 disengaged. The second motor 76 drives the mounting shaft 72 to rotate 180°, causing the wing 75 to completely fold to the rear side of the UAV body 1, and the folded state is locked through the buffer rubber sleeve 11 of the support bar 10, greatly reducing the overall volume of the machine for transportation and storage. When the wing 75 is unfolded during normal use, the overall lift can be increased and the flight stability can be improved.
[0024] It should be noted that the PLC controller 15 disclosed in the above embodiments has a specific model of Siemens S7-200, and the hydraulic rod 23, the electric telescopic rod 41, the first motor 52, the second motor 76, the electromagnet 82, the main control chip 12, the storage battery 13, the inertial measurement unit 14, the wireless transmission module 16, the camera 17 and the infrared rangefinder 61 can be freely configured according to the actual application scenarios. The PLC controller 15 controls the operation of the electric telescopic rod 41, the first motor 52, the second motor 76 and the electromagnet 82 by using the commonly used methods in the prior art.
[0025] The above are only the embodiments of the present invention, and do not limit the patent scope of the present invention accordingly. Any equivalent structure or equivalent process transformation made by using the content of the specification and drawings of the present invention, or directly or indirectly applied in other related technical fields, shall be equally included in the patent protection scope of the present invention.
Claims
1. An unmanned aerial vehicle for geological disaster detection, characterized in that: It includes a drone body (1) and an adjustment component (2); Drone body (1): An installation cavity is provided at the lower end inside. A storage battery (13), an inertial measurement unit (14), a PLC controller (15), and a wireless transmission module (16) are installed inside the installation cavity. A main control chip (12) is installed at the upper end inside the drone body (1). Two corresponding wing assemblies (7) and two corresponding fastening assemblies (8) are installed on the front and rear sides of the drone body (1). The fastening assembly (8) is connected to the wing assembly (7); Adjustment component (2): It includes a fixing frame (21), a fixing tube (22), a hydraulic rod (23), a connection disk (24), a connection bar (25), and a card hole (26). Six corresponding fixing frames (21) are fixed on the surface of the drone body (1). A fixing tube (22) is fixed inside the fixing frame (21). A hydraulic rod (23) is provided inside the fixing tube (22). The hydraulic rod (23) is installed inside the fixing frame (21). A connection disk (24) is fixed on the telescopic arm of the hydraulic rod (23). A connection bar (25) is fixed on the end face of the connection disk (24). Uniformly distributed card holes (26) are opened on the side of the connection bar (25). A locking component (3) is installed on the end face of the fixing tube (22). The locking component (3) is connected to the corresponding card hole (26). A pulling component (4) is installed on the side of the fixing frame (21). The pulling component (4) is connected to the locking component (3). A rotor assembly (5) is installed above the connection bar (25); Among them: The input end of the PLC controller (15) is electrically connected to the output end of the storage battery (13). The PLC controller (15) is bidirectionally electrically connected to the main control chip (12) and the inertial measurement unit (14) respectively. The output end of the PLC controller (15) is electrically connected to the input end of the hydraulic rod (23).
2. The unmanned aerial vehicle for geological disaster detection according to claim 1, wherein: The locking component (3) includes a connection ring (31), a chuck (32), a connection ring (33), and a first spring (34). A connection ring (31) is fixed on the end face of the fixing tube (22) away from the fixing frame (21). Two corresponding installation holes are opened on the circumferential surface of the connection ring (31). A connection ring (33) is fixed inside the installation hole. A chuck (32) is provided inside the installation hole. The chuck (32) is connected to the connection ring (33) through a first spring (34). Both chucks (32) are clamped at both ends inside the corresponding card hole (26).
3. The drone for geological disaster detection according to claim 2, characterized in that: The pulling component (4) includes an electric telescopic rod (41), a slip ring (42) and a pulling rope (43). Two corresponding electric telescopic rods (41) are installed on the side surface of the fixed frame (21). A slip ring (42) is fixed on the telescopic arms of the two electric telescopic rods (41). The slip ring (42) is sleeved on the circumferential surface of the fixed pipe (22). Two corresponding pulling ropes (43) are fixed on the end surface of the slip ring (42). The pulling rope (43) is slidably connected inside the corresponding connecting ring (31). The end of the pulling rope (43) far from the slip ring (42) is fixed on the end surface of the corresponding chuck (32). The input end of the electric telescopic rod (41) is electrically connected to the output end of the PLC controller (15).
4. The drone for geological disaster detection according to claim 1, wherein: The rotor component (5) includes an installation barrel (51), a first motor (52), a rotating shaft (53) and rotor blades (54). The installation barrel (51) is fixed on the side edge of the upper side of the connecting bar (25). The first motor (52) is installed at the upper end inside the installation barrel (51). The output shaft of the first motor (52) is fixed with the rotating shaft (53). Two corresponding rotor blades (54) are fixed on the circumferential surface of the rotating shaft (53). The input end of the first motor (52) is electrically connected to the output end of the PLC controller (15).
5. The unmanned aerial vehicle for geological disaster detection according to claim 2, wherein: It further includes a length measurement component (6). The length measurement component (6) includes an infrared rangefinder (61) and a reflector (62). The infrared rangefinder (61) is installed on the end surface of the connecting ring (31). The reflector (62) is fixed on the side surface of the connecting bar (25) far from the connecting disk (24). The infrared rangefinder (61) corresponds to the reflector (62). The infrared rangefinder (61) is bidirectionally electrically connected to the PLC controller (15).
6. The drone for geological disaster detection according to claim 1, characterized in that: The wing component (7) includes a fixing plate (71), a mounting shaft (72), a card slot (73), a swivel ring (74), a wing (75) and a second motor (76). Two corresponding fixing plates (71) are fixed on the front and back sides of the UAV body (1). A mounting shaft (72) is rotatably connected between the two fixing plates (71). Four corresponding card slots (73) are formed on the circumferential surface of the mounting shaft (72). Two corresponding swivel rings (74) are fixed on the circumferential surface of the mounting shaft (72). The lower ends of the circumferential surfaces of the two swivel rings (74) are fixed with the wing (75). The second motor (76) is installed on the left side of the left fixing plate (71). The output shafts of the two second motors (76) are respectively fixed at the left ends of the two mounting shafts (72). The input end of the second motor (76) is electrically connected to the output end of the PLC controller (15).
7. The drone for geological disaster detection according to claim 1, characterized in that: The fastening assembly (8) includes an installation groove (81), an electromagnet (82), an installation ring (83), a connecting rod (84), an iron disk (85), a clamping post (86) and a second spring (87). Two corresponding installation grooves (81) are formed on the front and rear sides of the UAV body (1). The electromagnet (82) is installed inside the installation groove (81). The installation ring (83) is fixed inside the installation groove (81). The connecting rod (84) is slidably connected inside the installation ring (83). One end of the connecting rod (84) is fixed with the iron disk (85), and the iron disk (85) corresponds to the electromagnet (82). The other end of the connecting rod (84) is fixed with the clamping post (86), and the clamping post (86) is clamped inside the corresponding clamping groove (73). The second spring (87) is sleeved on the circumferential surface of the connecting rod (84). One end of the second spring (87) is fixed on the end face of the installation ring (83), and the other end of the second spring (87) is fixed on the end face of the clamping post (86). The input end of the electromagnet (82) is electrically connected to the output end of the PLC controller (15).
8. The UAV for geological disaster detection according to claim 1, wherein: Four corresponding legs (9) are fixed to the lower side of the UAV body (1), and two corresponding support bars (10) are fixed to the lower sides of the four legs (9).
9. The unmanned aerial vehicle for geological disaster detection according to claim 8, wherein: A buffer rubber sleeve (11) is fixed to the surface of the support bar (10), and uniformly distributed anti-slip grooves are formed on the lower side of the buffer rubber sleeve (11).
10. The drone for geological disaster detection according to claim 1, characterized in that: A camera (17) is installed on the lower side of the UAV body (1), and the camera (17) is bidirectionally electrically connected to the PLC controller (15).