Wind turbine generator detection device

Abstract

The invention relates to the technical field of unmanned aerial vehicle detection, in particular to a wind turbine generator detection device. Comprising a main unmanned aerial vehicle, an auxiliary unmanned aerial vehicle and a ground base station. Each of the main unmanned aerial vehicle and the auxiliary unmanned aerial vehicle is a fuselage with four supporting wings, an embedding groove is formed in the tail end of each supporting wing, a cylinder base with an opening in the upper end is embedded in each embedding groove, a through hole is formed in the axis of the bottom wall of each cylinder base, a propeller is embedded in each cylinder base, a stud penetrating through the through hole is arranged at the lower end of each propeller, and a nut abutting against the lower end face of the corresponding supporting wing is screwed on each stud; a mesh enclosure for covering the propeller is arranged on the cylinder seat, and a notch for the propeller to pass through is formed in the side edge of the mesh enclosure. When the mesh enclosure is installed, the propeller firstly penetrates through the notch of the mesh enclosure and enters the mesh enclosure. The cylinder seat is arranged in the caulking groove, then the propeller is embedded in the cylinder seat, and then the nut is screwed, so that the integral installation of the mesh enclosure and the propeller is completed, only one nut needs to be disassembled, and the disassembly is quicker.

Description

Technical Field

[0001] The present application relates to the technical field of unmanned aerial vehicle detection, and in particular to a wind turbine detection device. Background Art

[0002] Nowadays, the society implements the policy of sustainable development, making clean energy more and more valued, and wind power generation is one of them. The equipment that uses wind power to generate electricity is the wind turbine, which includes a wind wheel and a generator. The blades of the wind wheel generate mechanical energy when the wind blows, and the generator converts the mechanical energy into electrical energy, thereby realizing wind power conversion. In order to ensure the normal operation and life of the wind turbine, the blades need to be inspected regularly to avoid problems and defects in time and repair them.

[0003] Since wind turbines are installed outdoors in an exposed and windy environment, their blades are subjected to fatigue loads and environmental loads for a long time under the influence of the natural environment and various weather conditions, and are easily damaged. The quality of the blades directly affects the operation and efficiency of the wind power system.

[0004] At present, the inspection of wind turbine blades is mainly carried out by drones. Using drones equipped with cameras to take pictures not only eliminates the need for high-altitude operations and is safer, but also drones fly faster and inspections are faster.

[0005] However, the operation of traditional drones is easily affected by high-altitude gusts, which can cause the drone to fall or the entire fan blades to be damaged. Therefore, most of them will be equipped with a mesh cover on the rotor to protect the propeller and cushion the impact. The installation method of the traditional cover is either to assemble two half mesh covers and then tighten them one by one with fasteners; or to directly set the rotor and the mesh cover as one. The first method requires disassembly and assembly one by one. When problems arise during the inspection process, the disassembly and assembly speed is slow, affecting efficiency. The second method is suitable for smaller models. Since wind power inspection drones need to be equipped with high-definition cameras, infrared imagers and other inspection equipment, their size is relatively larger. After the rotor and the mesh cover are integrated, the exposed area of ​​the body is large and it is more prone to damage, so the replacement cost is higher.

[0006] To this end, the present application provides a wind turbine detection device to improve the efficiency of disassembly and assembly of the UAV rotor protection net cover.

[0007] Application Contents The purpose of the present application is to solve the problems existing in the prior art and to propose a wind turbine detection device.

[0008] In order to achieve the above purpose, this application adopts the following technical solutions: A wind turbine detection device comprises a main UAV, a secondary UAV, a ground base station and a parking platform arranged on the side of a cabin; The main UAV and the auxiliary UAV are both equipped with an image acquisition device, a flight control subsystem, a communication system, and a GPS positioning system; The ground base station includes a flight control main system, and the flight control subsystem is electrically connected to the flight control main system via a communication system; The main UAV and the auxiliary UAV both have a four-wing fuselage, and four supporting legs distributed around the fuselage are arranged under the fuselage. The supporting legs have buffering properties. A groove is arranged at the end of each wing, and a cylinder seat with an upper opening is embedded in the groove. A through hole is arranged at the axis of the bottom wall of the cylinder seat, and a propeller is embedded in the cylinder seat. A stud passing through the through hole is arranged at the lower end of the propeller, and a nut is screwed on the stud and abuts against the lower end surface of the wing. A mesh cover for covering the propeller is arranged on the cylinder seat, and a notch is arranged on the side of the mesh cover for the propeller to pass through.

[0009] Preferably, the mesh cover comprises a first ring and a second ring arranged vertically at intervals, the sides of the first ring and the second ring are provided with a plurality of U-shaped protective columns in an annular array, and a plurality of connecting columns are provided in an annular array between the inner wall of the second ring and the side wall of the cylinder seat; The diameter of the first ring shall not exceed half of the maximum size of the propeller, and the diameter of the second ring shall not be less than 2 / 3 of the maximum size of the propeller.

[0010] Preferably, the number of connecting columns does not exceed 6.

[0011] Preferably, the cartridge seat and the propeller, as well as the cartridge seat and the embedding groove, are vertically slidably matched.

[0012] Preferably, the support leg is an outwardly expanded arc shape, and a plurality of penetrating weight-reducing holes are provided on the support leg. A buffer notch 1 is provided on the outwardly expanded surface of the support leg near the connection with the fuselage, and a buffer notch 2 is provided in the lower middle part of the inner support surface of the support leg.

[0013] Preferably, a triangular auxiliary support foot is provided at the bottom end of the inner supporting surface of the supporting leg.

[0014] Preferably, the fuselage is in a hollow frame shape.

[0015] Preferably, the image acquisition device on the master UAV includes a hyperspectral camera mounted on the fuselage, and the image acquisition device on the slave UAV includes a thermal imager mounted on the fuselage.

[0016] Compared with the prior art, the present application provides a wind turbine detection device, which has the following beneficial effects: 1. The main drone and the auxiliary drone take off one after another, and are controlled by the remote control to move in a spiral from the root of the blade to the tip, thereby performing an all-round scan of the blade to obtain sufficient image information and improve the accuracy and comprehensiveness of detection.

[0017] 2. An embedding groove is provided at the end of the wing, and a cylinder seat with an upper opening is embedded in the embedding groove. A through hole is provided at the axis of the bottom wall of the cylinder seat, and a propeller is embedded in the cylinder seat. A stud is provided at the lower end of the propeller to pass through the through hole, and a nut is screwed on the stud to abut against the lower end surface of the wing. A mesh cover for covering the propeller is provided on the cylinder seat. During installation, the propeller is first passed through the notch of the mesh cover and enters the mesh cover. Then the cylinder seat is placed in the embedding groove, and then the propeller is embedded in the cylinder seat, and then the nut is screwed on, thereby completing the overall installation of the mesh cover and the propeller. Only one nut needs to be disassembled, making disassembly and assembly faster.

[0018] Other advantages, objectives and features of the present application will be described in the following description to some extent; and will be apparent to those skilled in the art based on the following examination and study to some extent; or, may be taught from the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a top-down stereoscopic schematic diagram of the main drone of this application.

[0020] Figure 2 This is a schematic upward-looking stereoscopic diagram of the secondary drone of the present application.

[0021] Figure 3 This is a front view schematic diagram of the main UAV of this application.

[0022] Figure 4 This is a front view schematic diagram of the secondary drone of this application.

[0023] Figure 5 This is a schematic cross-sectional view of the mesh cover installation part of the present application.

[0024] Figure 6 For this application Figure 5 Local schematic diagram of point A.

[0025] Figure 7 This is a three-dimensional schematic diagram of the mesh cover of this application.

[0026] Figure 8 This is a schematic front view of the support legs of the present application.

[0027] In the figure: 1. main UAV; 2. auxiliary UAV; 3. hyperspectral camera; 4. thermal imager; 5. fuselage; 6. wing; 7. mesh cover; 8. support leg; 9. barrel seat; 10. propeller; 11. stud; 12. nut; 13. weight reduction hole; 14. auxiliary support foot; 15. buffer notch 1; 16. buffer notch 2; 17. wind guide cover; 701. ring 1; 702. ring 2; 703. protective column; 704. connecting column; 705. notch. DETAILED DESCRIPTION

[0028] The following will be combined with the attached examples of the present application Figure 1-8 , the technical solutions in the embodiments of the present application are described clearly and completely. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments.

[0029] Embodiment 1, in order to solve the problems existing in the prior art, this embodiment provides a wind turbine detection device, including a main UAV 1, a secondary UAV 2, a ground base station and a parking platform arranged on the side of the cabin; The main UAV 1 and the secondary UAV 2 are both equipped with an image acquisition device, a flight control subsystem, a communication system, and a GPS positioning system; The ground base station includes a flight control main system, and the flight control subsystem is electrically connected to the flight control main system via a communication system; The main UAV 1 and the auxiliary UAV 2 both have a fuselage 5 with four wings 6, and four supporting legs 8 are arranged around the fuselage 5. The supporting legs 8 have buffering performance. A groove is arranged at the end of each wing 6, and a cylinder seat 9 with an upper end opening is embedded in the groove. A through hole is arranged at the axis of the bottom wall of the cylinder seat 9, and a propeller 10 is embedded in the cylinder seat 9. A stud 11 passing through the through hole is arranged at the lower end of the propeller 10, and a nut 12 is screwed on the stud 11 and abutted against the lower end surface of the wing 6. A mesh cover 7 for covering the propeller 10 is arranged on the cylinder seat 9, and a notch 705 for the propeller 10 to pass through is arranged on the side of the mesh cover 7.

[0030] Principle details of this embodiment: A wind turbine detection device comprises a main UAV 1, a secondary UAV 2 and a ground base station.

[0031] The main UAV 1 and the secondary UAV 2 are both provided with an image acquisition device, a flight control subsystem, a communication system, a GPS positioning system, a barometer, and an IMU.

[0032] The image acquisition device is used to acquire corresponding leaf images.

[0033] The communication system uses high-gain antennas and dual-frequency settings. High-gain antennas can significantly improve signal reception and transmission capabilities, avoiding signal interference that affects information transmission. Dual-frequency settings can select dual-frequency modes (such as 2.4GHz and 5.8GHz. The 2.4 GHz frequency band has a long transmission distance but weak anti-interference ability; the 5.8GHz frequency band has strong anti-interference ability but a short transmission distance) in the image transmission settings of the remote control, allowing the drone to switch to a more suitable frequency band to adapt to different application scenarios. At the same time, a signal repeater can be added between the main drone 1, the secondary drone 2 and the ground base station, which can effectively extend the control distance and improve the flexibility of use.

[0034] The GPS positioning system is used to obtain the latitude and longitude information of the drone and determine its own location. The barometer is used to obtain the atmospheric pressure of the drone's current location and obtain the altitude information of the drone. The GPS positioning system cooperates with the barometer to feedback the location of the blade detection.

[0035] IMU is an inertial measurement unit, which includes a three-axis accelerometer and a three-axis gyroscope to measure the angular velocity and acceleration of the drone in three-dimensional space to obtain the attitude of the object.

[0036] The ground base station includes a flight control main system, and the flight control subsystem is electrically connected to the flight control main system via a communication system to realize the interaction between the UAV and the ground. The flight control main system includes a remote control system, and the remote control system includes a remote control. The flight control subsystem of the UAV includes a receiving module. The instructions on the remote control are transmitted to the UAV through the transmission system of the remote control and the wireless signal of the communication system, and the receiving module of the flight control subsystem on the UAV receives the signal.

[0037] The ground base station also includes an imaging device, which is electrically connected to the image acquisition device through a communication system. After receiving the detection imaging picture, the picture is first pre-processed to improve the image quality, and then compared with the factory status of the corresponding position of the blade in the database and the last detection image to obtain the specific changes of the blade position in this detection.

[0038] The parking platform is a rotating plate. The rotating plate is rotatably installed on the side of the cabin (the cabin is a place to prevent key equipment such as gear boxes and discharge motors). The cabin side is rotatably installed on the side of the rotating plate. The extended end of the electric telescopic rod is rotatably connected to the ends of both sides of the rotating plate, so as to control the turning of the rotating plate and keep it stable. A viewing window is provided on the side of the cabin above the rotating plate. The size of the viewing window is smaller than the rotating plate, and the size of the rotating plate is larger than the parking space of the main UAV 1 and the auxiliary UAV 2.

[0039] The main UAV 1 and the auxiliary UAV 2 are both of a fuselage 5 structure with four wings 6. Four supporting legs 8 are arranged around the fuselage 5. The supporting legs 8 have a buffering performance and provide support for the take-off and landing of the UAV. Each wing 6 is provided with an annular embedding groove at the end, and a through jack is provided at the axis of the embedding groove. A barrel seat 9 is embedded in the embedding groove, the upper end of the barrel seat 9 is open, and a through hole is provided at the axis of the bottom wall of the barrel seat 9. A propeller 10 is embedded in the barrel seat 9, and the propeller 10 includes blades, a motor, and a motor seat. An electric speed controller and a power battery are provided on the fuselage 5. The motor is a brushless motor. The blades are fixed on the motor shaft and rotate with the rotation of the motor shaft. The electric speed controller is an electronic speed regulator, which converts the direct current provided by the power battery into three-phase alternating current that can directly drive the motor. During installation, the motor seat is embedded in the barrel seat 9 and the motor output shaft extends out of the barrel seat 9, and the blades are located outside the barrel seat 9.

[0040] A stud 11 is provided at the lower end of the propeller 10, and the stud 11, the through hole, and the jack are coaxially arranged. After the stud 11 is inserted into and passes through the through hole and the jack, a nut 12 is screwed on the lower end of the stud 11, and the nut 12 rests on the lower end surface of the wing 6. The nut 12 is a self-locking nut 12, and the thread between the nut 12 and the stud 11 is self-locking and has the characteristic of preventing falling off. A mesh cover 7 for covering the propeller 10 is provided on the barrel seat 9 to protect the blades. A notch 705 is provided on the side of the mesh cover 7 for the propeller 10 to pass through, leaving a passage space for the disassembly, assembly, and placement of the propeller 10.

[0041] According to the above technical solution: The staff controlled the drones with a remote controller at the ground base station. The main drone 1 and the auxiliary drone 2 took off one after another, and the remote controller controlled the rotation speed of the four motors of the drones, so as to achieve the drones' ascent, descent, translation and hovering, so as to fly stably on the navigation route. The main drone 1 and the auxiliary drone 2 were controlled by the remote controller to move in a spiral state from the root of the blade to the tip, so as to scan the blades in all directions to obtain sufficient image information and improve the accuracy and comprehensiveness of detection.

[0042] At the same time, in order to prevent the drone from entering the cabin and blocking the signal transmission, affecting the control of the drone, when inspecting the cabin's internal environment and equipment, the electric telescopic rod is extended to deflect the rotating plate to the horizontal to form a parking platform. At the same time, the viewing window is opened. The drone is then parked on the rotating plate to take pictures of the cabin's internal environment and equipment. Compared with traditional blade drone inspections that only inspect the blade condition, this method allows for a wider range of inspections, a more comprehensive inspection, and a more accurate grasp of the wind turbine equipment condition.

[0043] Preferably, a windproof cloth is commonly connected between the two sides of the rotating plate and the side walls of the cabin, so that the wind impact is reduced after the drone is parked on the rotating plate, making the parking more stable and the imaging clearer.

[0044] The installation process of the drone's mesh cover 7: Place the drone body 5 on a stable base surface, and first pass the propeller 10 through the notch 705 of the net cover 7 and into the net cover 7. Then place the cartridge seat 9 in the embedding groove, and then pass the stud 11 at the lower end of the propeller 10 through the through hole and the plug hole so that the propeller 10 is embedded in the cartridge seat 9, and then screw on the nut 12 to complete the overall installation of the net cover 7 and the propeller 10. Only one nut is needed, making disassembly and assembly faster.

[0045] Embodiment 2, in a further embodiment of the present invention, the mesh cover 7 comprises a circular ring 1 701 and a circular ring 2 702 which are arranged vertically at intervals, and a circular array on the sides of the circular ring 1 701 and the circular ring 2 702 has a plurality of side U-shaped protective columns 703, and a circular array between the inner wall of the circular ring 2 702 and the side wall of the cylinder seat 9 has a plurality of connecting columns 704; The diameter of the ring 1 701 is not more than half of the maximum size of the propeller 10 , and the diameter of the ring 2 702 is not less than 2 / 3 of the maximum size of the propeller 10 .

[0046] Details of the principles of this program: The net cover 7 includes a ring 1 701 and a ring 2 702 arranged vertically at intervals, with the ring 1 701 located at the top and the ring 2 702 located at the bottom. The side rings 1 701 and 702 are provided with a plurality of U-shaped protective columns 703 in an annular array. The spacing between the ring 1 701 and the ring 2 702 is greater than the height of the propeller 10 to ensure that there is enough space for maneuvering during disassembly and assembly. A plurality of connecting columns 704 are provided in an annular array between the inner wall of the ring 1 701 and the side wall of the cylinder seat 9 to complete the connection between the cylinder seat 9 and the net cover 7.

[0047] In this solution, when the propeller 10 rotates, the curved design of the blades allows the propeller 10 to draw air from the top and eject air downward. Therefore, in this embodiment, the diameter of the ring 1 701 does not exceed half of the maximum size of the propeller 10, which can not only leave enough air intake space to minimize the impact on the intake airflow, but also reduce the exposed area of ​​the propeller 10 from the upper ring, reducing the risk of hitting debris from the upper ring. The diameter of the ring 2 702 is not less than 2 / 3 of the maximum size of the propeller 10, and the diameter of the ring 2 702 is larger to avoid affecting the flow of the jet airflow and affecting the flight state.

[0048] In the preferred solution of this embodiment, a plurality of connecting columns 704 are fixedly connected together with an internal threaded sleeve at one end facing the axis of the circular ring, and the outer wall of the cylinder seat 9 is provided with an external thread. The internal threaded sleeve cooperates with the external thread, so that the mesh cover 7 and the cylinder seat 9 can be detachably matched, so that the mesh cover 7 can be replaced separately after being damaged.

[0049] Embodiment 3, in a further embodiment of this solution, the number of the connecting columns 704 is no more than 6. This reduces the blocking area of ​​the jet airflow below the propeller 10 and provides sufficient connection strength.

[0050] Embodiment 4, in a further embodiment of the present invention, radial torque is inevitably generated during the rotation of the propeller 10 blades, thereby driving the stud 11 to deflect, which may cause the nut 12 to loosen and affect the assembly tightness. Therefore, in this embodiment, the cartridge seat 9 and the propeller 10, and the cartridge seat 9 and the embedded groove are all vertically slidably matched.

[0051] Principle details of this embodiment: The side walls of the barrel seat 9 and the motor seat of the propeller 10 are both provided with splines, and the embedded groove and the inner wall of the barrel seat 9 are both provided with keyways, so that the barrel seat 9 and the propeller 10, and the barrel seat 9 and the embedded groove are vertically slidably matched. Thus, radial deflection is limited. The embedded groove and the ends of the barrel seat 9 are chamfered for easy insertion.

[0052] Embodiment 5, in a further embodiment of the present scheme, the traditional support leg 8 buffer structure is mostly provided with a telescopic structure, and then equipped with a spring. However, in this structure, the elastic deformation resistance of the spring is large, so the buffering effect will be poor; if the elastic deformation resistance of the spring is small, the fuselage 5 is prone to vibration after landing and such a spring is prone to elastic fatigue and failure. Moreover, in general, the size of the support leg 8 of the drone is not large, and the space for modification of the spring or telescopic structure is small, so any modification of the telescopic structure will easily affect its own strength. Therefore, in this embodiment, a specific support leg 8 structure that can provide buffering performance is provided: See attached Figure 8 As shown, the support leg 8 is an outwardly expanded arc, and the cross-sectional size gradually decreases from top to bottom. The arc structure itself has the ductility of movement and has a certain buffering performance, and the change in size makes the support leg 8 have sufficient supporting strength. The support leg 8 is provided with a plurality of penetrating weight-reducing holes 13 for reducing the load. A buffer notch 15 is provided on the outward expansion surface of the support leg 8 near the connection part with the fuselage 5, and a buffer notch 2 16 is provided at the lower middle part of the inner support surface of the support leg 8. The setting of buffer notch 15 and buffer notch 2 16 enables the support leg 8 to contact the ground and bear the load of the fuselage 5 when the drone lands. When bearing the impact of the load, the support leg 8 has a certain bending and deformation ability, thereby playing a buffering function.

[0053] Embodiment 6, in a further embodiment of this solution, a triangular auxiliary support foot 14 is provided at the bottom of the inner support surface of the support leg 8 to expand the support surface and improve the support stability. At the same time, it prevents the support leg 8 from deforming outwards after being bent downward under the load of the fuselage 5.

[0054] Embodiment 7, in a further embodiment of this solution, the fuselage 5 is a hollow frame. The load is reduced as much as possible, and the wind resistance and lateral wind are reduced. Conical wind guides 17 are provided around the fuselage 5 in front of each device. The wind fan is guided to reduce wind resistance and reduce the impact of wind blowing on the fuselage 5 on the stability of the UAV flight.

[0055] Embodiment 8, in a further embodiment of the present scheme, in this embodiment, a specific image acquisition device is provided: the image acquisition device on the main UAV 1 includes a hyperspectral camera 3 mounted on the fuselage 5 through a gimbal; the image acquisition device on the secondary UAV 2 includes a thermal imager 4 mounted on the fuselage 5 through a gimbal.

[0056] The gimbal is a three-axis gimbal that can eliminate jitter in all directions.

[0057] Hyperspectral camera 3, you can choose Phase One camera. Phase One industrial camera uses medium format CMOS (photosensitive element). Compared with ordinary zoom cameras, it has a wider shooting range and more comprehensive shooting content. 1-2 photos can achieve coverage shooting of a single leaf. At the same time, the camera resolution of up to 100 million / 120 million can ensure the clarity of the shooting picture, ensuring that after the image is magnified, it can still clearly show various details such as wear and dents on the surface of the blade. The back-illuminated sensor design of Phase One industrial camera with 83db high dynamic range makes the image sharper and more transparent, with less noise, and the picture looks brighter.

[0058] Thermal imager 4, also known as infrared thermal imager 4, is a device that uses infrared thermal imaging technology to detect the infrared radiation of the target object and convert the image of the temperature distribution of the target object into a visible image by means of signal processing, photoelectric conversion, etc. The infrared thermal imager 4 accurately quantifies the actual detected heat and images the entire target object in real time in the form of a surface, so it can accurately identify the suspected fault area that is heating. The operator preliminarily judges the heating situation and the fault location through the image color displayed on the screen and the hot spot tracking display function, and strictly analyzes it, thereby reflecting high efficiency and high accuracy in confirming the problem.

[0059] When in use, the main drone 1 is equipped with a high-definition camera to obtain high-definition pictures of the blades; the slave drone 2 follows the route of the main drone 1 to collect thermal images of the blades to accurately obtain the fault conditions of the imaged parts.

[0060] The above is only a preferred specific implementation manner of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can make equivalent substitutions or changes within the technical scope disclosed in the present application according to the technical solution and application concept of the present application, which should be covered by the protection scope of the present application.

[0061] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0062] Although the embodiments of the present application have been shown and described above, it can be understood that the above embodiments are exemplary and cannot be understood as limitations on the present application. Ordinary technicians in this field can change, modify, replace and modify the above embodiments within the scope of the present application.

Claims

1. A wind turbine detection device, characterized in that: It comprises a main drone (1), a secondary drone (2), a ground base station and a parking platform arranged on the side of the cabin; The main UAV (1) and the auxiliary UAV (2) are both provided with an image acquisition device, a flight control subsystem, a communication system, and a GPS positioning system; The ground base station includes a flight control main system, and the flight control subsystem is electrically connected to the flight control main system via a communication system; The main drone (1) and the auxiliary drone (2) are both fuselages (5) with four wings (6). Four supporting legs (8) are arranged on the lower side of the fuselage (5). The supporting legs (8) have a buffering property. A groove is arranged at the end of each wing (6). A cylinder seat (9) with an upper opening is embedded in the groove. A through hole is arranged at the axis of the bottom wall of the cylinder seat (9). A propeller (10) is embedded in the cylinder seat (9). A stud (11) passing through the through hole is arranged at the lower end of the propeller (10). A nut (12) is screwed on the stud (11) and abuts against the lower end surface of the wing (6). A net cover (7) for covering the propeller (10) is arranged on the cylinder seat (9). A notch (705) for the propeller (10) to pass through is arranged on the side of the net cover (7).

2. A wind turbine detection device according to claim 1, characterized in that: The net cover (7) comprises a first circular ring (701) and a second circular ring (702) arranged vertically at intervals, a plurality of U-shaped protective columns (703) are arranged in a circular array on the sides of the first circular ring (701) and the second circular ring (702), and a plurality of connecting columns (704) are arranged in a circular array between the inner wall of the second circular ring (702) and the side wall of the cylinder seat (9); The diameter of the first ring (701) is not more than half of the maximum size of the propeller (10), and the diameter of the second ring (702) is not less than 2 / 3 of the maximum size of the propeller (10).

3. A wind turbine detection device according to claim 2, characterized in that: The number of the connecting columns (704) does not exceed 6.

4. A wind turbine detection device according to claim 1, characterized in that: The cylinder seat (9) and the propeller (10), as well as the cylinder seat (9) and the embedding groove, are all vertically slidably matched.

5. A wind turbine detection device according to claim 1, characterized in that: The support leg (8) is in an outwardly expanding arc shape, and is provided with a plurality of penetrating weight-reducing holes (13). A first buffer notch (15) is provided on the outwardly expanding surface of the support leg (8) near the connection portion with the fuselage (5), and a second buffer notch (16) is provided at the lower middle portion of the inner supporting surface of the support leg (8).

6. A wind turbine detection device according to claim 1, characterized in that: A triangular auxiliary support foot (14) is provided at the bottom end of the inner support surface of the support leg (8).

7. A wind turbine detection device according to claim 1, characterized in that: The fuselage (5) is in the shape of a hollow frame.

8. A wind turbine detection device according to claim 1, characterized in that: The image acquisition device on the main UAV (1) comprises a hyperspectral camera (3) mounted on a fuselage (5), and the image acquisition device on the secondary UAV (2) comprises a thermal imager (4) mounted on a fuselage (5).

Images